OLDWILLWAYNE
O
SEI~VICE
O
AND
MAINTEN ANCE
MANUAL
~I OONEY LOUIS
AIRCR AFT
SCHREINER
ORIGINAL ISSUE
CORPOR ATION
FIELD, KERRVILLE,
APRIL 1999
TX
78028
MANUAL NUMBER
51
OLDWILLWAYNE KERRVILLE, TEXAS
MOONEY AIRCRAFT CORPORATION
WARNING: harm
This the
public
Manufactured with 1.1,1 Trichloroethane substances which are determined to destroying ozone in the upper atmosphere.
health and environment by
placards manufactured at Mooney Aircraft Corporation facility Model(s) addressed in this publication.
warning applies
Mooney Aircraft
to
and installed
WARNING: harm
public
Manufactured with 1,1,1 Trichloroethane substances which are determined to health and environment by destroying ozone in the upper atmosphere.
warning applies to certain adhesives procured form vendors and utilized Mooney Aircraft Model(s) addressed in this publication.
This
on
on
the
applicable
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
LOG
M20M
SERVICE AND MAINTENANCE MANUAL
DF REVISIONS ALwavs destrov suPerseded
DATE OF REVISION
SECTIONS AFFECTED
Da9es
when
DATE CIF REVISION
vou
Insert revised
SECTILINS AFFECTED
NOTE: A list of effective Daaes wil~ appear at the bea;nninn of
each chapter,
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
INTRODUCTION This manual provides servicina and maintenance information for the Mooney Mlodel M20M, Serial Numbers 27-0001 and ON. Maintenance actions that refer to a limited number of aircraft will be designated by serial number of applicable airplanes. The Part Numbers of replacement or repair parts should be identified using the illustrated Paris Catalog applicable to model S/N of aircraft being worked on. The current P/N can be ordered through any Mooney Marketing Center (MMC). See SECTION 91 for exceptions on electrical components. The format and contents of this manual are prepared in with accordance GENERAL AVIATION MANUFACTURER’S ASSOCIATION (GAMA) Specification No. 2. The manual is supplemented with wiring schematics for the various model year airplanes,as necessary. These are located in envelopes at the back of the manual texts pages.
are
not to
SYSTEM/CHAPTER The various groups contain major systems information such as Right controls, landing gear, etc. The systems are arranged numerically per GAMA recommended number assignment, It is suggested, for example,that "Fuel" be identified with the SystemlChapter number "28". The sequence of numbers, 28-00-00, refers to the General information of the Fuel Systems.
SUB-SYSTEM/SECTION
major systems of an aircraft are broken down into sub-systems. These sub-systems are identified by the Th,
UNIT/SUBJECT
automatically provided
The individual units within a sub-system may be identified by a third dement of the sequence of numbers, ie.,28-20-01. This number is assigned by the manufacturer and may or may not be used depending upon the c0mple~y of the maintenance action recommended.
manual holders. Holders of these and other Mooney Technical Publications should complete the informatjon on the YECLOW CARD located at the front of the Title Page and send to Mooney Aircraft Corp_oratSon, Louis Sctitelner Field, Kerrville, TX., 78028, Attn: Service Parts
APPLICATION OF NUMBERING SYSTEM
Corporation prepares all applicable publications to GAMA format. All publications concerning maintenance of aircraft will conform to this basic numbering system. Any person wishing information concerning the Fuel Distribution System would refer to the pages identified as 28-20-00 in any maintenance publication. These pages will be numbered sequentially within each system breakdown in the current Mooney series of aircraft. As Mooney aircraft models become more complex the page numbers may be sequentially numbered within
Notification is sent to known manual holders when another manual is prepared to replace the subscription and advises that no more revisions will be sent out, The new manual will require a new subscription If additional Technical Publications are service. desired, contact the Service Parts Department at Mooney Aircraft Corporation at (830) 896-6000 UCT. 2092.
sub-systems. The
numbers on an model number and serial number. The serial number appears on the identification placard located on the aft end, left hand side of the tailcone below the horizontal stabilizer.
is
organized
of
contents
in
the
28-00
General
28-10
Storage
front of each of sub-systems
CTanks, vents, repair, etc.) 28-20
Distribution
(Boost pumps, 28-40
ASSIGNMENT OF SUBJECT MATERIAL
publication
table
System/Chapter will provide a list covered in the Chapter. For example:
concerning maintenance or part airplane should contain the aircraft
The content of this levels:
Aircraft
MOO"ey
technical
Department.
Correspondence
GROUP These are primary divisions of the manual that enable broad separation of content, ie., Airframe systems VS Powerplant systems. These groups are identified by tabs.
second element of the sequence of numbers, ie., 28-20-00. The element -20- indicates the distribution portion of the fuel system.
NOTE Revisions or reissues to this manual number
SERVICE AND MAINTENANCE MANUAL
M20M
fuel lines, etc.)
Indicating (Sender Units, quantity gauges,
etc.)
at four
If there is a reason to distinguish between LEFT HAND RIGHT HAND fuel quantity sending units then the number would be expanded to 28-40-01 (Left Hand) and 28-40-02 (Right Hand). This concept will apply to any expanded information throughout the publications.
Group
or
UnitlSubject
4-99
INTRODUCTION
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
SUPPLEMENTARY PUBLICATIONS
following list of Manufacturers and/or publications can provide servicing and maintenance information on components of the Mooney-TLS, Model M20M. No avionics equipment Manufacturers or publications are listed due to the many configurations that can be installed in the aircraft. These can be obtained from the repair stations for a particular avionics manufacturer.
The
Publications available from Mooney Aircraft Mooney Service Center.
Corporation
are
listed in the Parts Price List and
are
available
through
any As
publications on
various components become available,
VENDOR ADDRESSES
or
they will be added
to the list below.
PUBLICATIONS
ENGINE
The following maintenance 17701.
publications
can
be obtained
through TUCTRON-Lycoming Division, Wiliiamsport, PA.,
Overhaul Manual for
TEXTRON-Lycoming Aircraft Engines Direct Drive Models. Illustrated Parts Catalog for TEXTRON-Lycoming TIG-540 series aircraft engines. Operators Manual for TEXTRON-Lycoming TIG-540 aircraft engines. Service Bulletins Specify model of engine for which maintenance data is desired. PROPELLER
McCauley Propellers Obtain publications from McCauley Accessories Division, Cessna McCauley Drive, Vandalia, OH.,45377. Service Manual No. 761001 for McCauley C400 series constant speed propellers.
Aircraft
Company,
3535
MAGNETO
Slick Electro, 530 Blackhawk Park Avenue, Rockford, 1161101, for Slick Model 6260
or
6261
magneto.
TURBORCHARGER
Rotomaster, c/o Garrett-Aftenarket Division, 2511 South Edison Way, Compton, CA
90220-6035, Attn: Don
Winters
ALTERNATOR Prestolite Electronics Division, 511 Hamilton Street, Toledo, OH 43694 STARTER B
C
Specialty
FUEL PUMP Lear
Siegler,
Products Inc., 123 East 4th Street, PO Box B, newton KS 67114-0894. Telephone
(Engine Driven)
Romec
Division,
241 South Abbe
Road, Elyria, OH 44035
FUEL INJECTOR
Precision Airmotive, 3220-100th Street, S.W. #E, Everett, WA 98204 SPEEDBRAKES Precise
Flight,
Inc. 63120 Powell Butte Rd., Bend, OR
97701,Telephone: (503) 382-8684.
DE-ICING/ANTI-ICING (TKS)
Aerospace Systems
\NTRODUCTION
8
Technologies, Inc.,
110 Riverfront
Road, Suite C. Lawrence, KS 66044,
4-99
(316)
283-8662.
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER CHAPTER
SECTION
TITLE
SERVICE AND MAINTENANCE MANUAL INDEX GUIDE TITLE
SECTION
MAY BE USED LATER
1 -4
RESERVED
5
TIME LIMITS/MAINTENANCE CHECKS
GENERAL TIME LIMITS SCHEDULED MAINTENANCE CHECKS
00 10 20
DIMENSIONS AND AREAS
6
GENERAL
00
LIFTING
7
JACKING
10
LEVELING AND WEIGHING
8
LEVELING
00
TOWING AND TAXIING
9
GROUND HANDLING TOWING TAXIING
00 10 20
PARKING AND MOORING
10
GENERAL PARKING MOORING
00 10 20
PLACARDS AND MARKINGS
11
GENERAL MARKINGS PLACARDS- EXTERIOR/INTERIOR
00 10 20
SERVICING
12
SERVICING REPLENISHING SCHEDULED SERVICING
00 10 20
STANDARD PRACTICES AIRFRAME
20
GENERAL
00
ENVIRONMENTAL SYSTEMS
21
CABIN VENTILATION SYSTEM HEATING COOLING
00 40 50
ELECTRICAL POWER
24
GENERAL DC GENERATION ELECTRICAL LOAD DISTRIBUTION
00 30 50
SEATS
25
THIS SECTION IS NOT INCLUDED IN THIS MANUAL.
GENERAL FLIGHT COMPARTMENT PASSENGER COMPARTMENT CARGO COMPARTMENT EMERGENCY EQUIPMENT ACCESSORY COMPARTMENT
00 10 g0 50 60 70
4-99
INTRODUCTION
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL CHAPTER
M20M
SECTION
TITLE
27
FLIGHT CONTROLS 00 10 20 30 40 50 90
GENERAL AILERON SYSTEM RUDDER SYSTEM ELEVATOR SYSTEM STABILIZER TRIM SYSTEM WING FLAP SYSTEM
MISCELLANEOUS
28
FUEL 00 10 20 30 40 50
GENERAL STORAGE DISTRIBUTION DUMP INDICATING MISCELLANEOUS
30
ICE AND RAIN PROTECTION 00 10 30 60
GENERAL AIRFOILS PITOT AND STATIC PROPELLER
32
LANDING GEAR 00 10 20 30 40 50 60 80
GENERAL MAIN LANDING GEAR 8 DOORS NOSE LANDING GEAR 8 DOORS EXTENSION AND RETRACTION WHEELS 8 BRAKES STEERING POSITION AND WARNING MISCELLANEOUS
33
LIGHTS 00 20
GENERAL INTERIOR LIGHTS MAINTENANCE PRACTICES INTERIOR LIGHTS MAINTENANCE PRACTICES
40
34
NAVIGATION 00 10
GENERAL PITOT STATIC AIR PRESSURE SYSTEM DIRECTIONAL GYRO COMPASS
20
35
OXYGEN 00
GENERAL
37
VACUUM 00 10
GENERAL DISTRIBUTION INDICATION
20
INTRODUCTION
MOONEY AIRCRAFT CORPORATION
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
CHAPTER
M20M
SECTION
SERVICE AND MAINTENANCE MANUAL TITLE
39
ELECTRICAL PANELS AND COMPONENTS GENERAL INSTRUMENT
00 10 20
CONTROL
PANELS, ELECTRICAL ELECTRONICS EQUIPMENT RACKS.
51
STRUCTURES
GENERAL STRUCTURAL REPAIR
00 10 52
GENERAL
DOORS 00 10
GENERAL CABIN DOOR MAINTENANCE PRACTICE BAGGAGE COMPARTMENT DOOR MAINTENANCE PRACTICE
30
53
FUSELAGE GENERAL MAIN FRAME AUXILIARY STRUCTURE
00 10 20 30 40 50
PLATES/SKIN ATTACH FITTINGS
FILLETS/FAIRINGS
55
STABILIZERS GENERAL HORIZONTAL STABILIZER ELEVATOR VERTICAL STABILIZER RUDDER
00 10 20 30 40 56
WINDOWS
GENERAL WINDSHIELD CABIN WINDOWS PLEXIGLASS DRILLING
00 20
50
WINGS
57
GENERAL
00 30 40 50
PLATES/SKINS ATTACH FITTINGS FLIGHT SURFACES
60
STANDARD PRACTICES PROPELLERS
61
PROPELLERS GENERAL PROPELLER ASSEMBLY CONTROLLING
00 10 20
POWERPLANT
71
GENERAL COWLING
00 10
4-99
INTRODUCTION
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL CHAPTER
M20M
SECTION
TITLE
72
ENGINE- RECIPROCATING 00
GENERAL
73
ENGINE FUEL SYSTEM 00 10 20 30
GENERAL DISTRIBUTION CONTROLLING INDICATING
74
IGNITION 00 12 20
GENERAL POWER CONTROL EMERGENCY SHUTDOWN
76
ENGINE CONTROLS 00 10
GENERAL POWER CONTROLS RIGGING
77
ENGINE INDICATING 00 10 20
GENERAL POWER TEMPERATURE
78
EXHAUST 00 10 30 40
GENERAL NSTALLATION EXHAUST SYSTEM REPLACEMENT COMPONENTS
79
OIL 00 10 20 30
GENERAL STORAGE DISTRIBUTION
INDICATING
80
STARTING 00 10
GENERAL CRANKING
81
TURBINES 00 10 20
GENERAL POWER RECOVERY TURBOCHARGER
91
ELECTRICAL 00 20
GENERAL ELECTRICAL SYSTEM HARDWARE CHARTS SCHEMATICS
30 95
MOONEY AIRCRAFT CORPORATION
[NOT INCLUDED MANUAL]
SPECIAL EQUIPMENT
IN THIS
INTRODUCTION
4-99
OLDWILLWAYNE
CHAPTER
TIME LIMITS/
MAINTENANCE CH EC KS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 5 TIME LIMITS/MAINTENANCE CHECKS
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT 5-00-00
PAGE
SUBJECT
5
General
5
5-00-04.
Landing Gear System FlightControl Systems Wing Flap Systems Electric Power System
5-00-05.
Instruments
5
5-00-06.
Cabin
5-00-07.
Fuel
5-10-00.
Time Limit Components Overhaul and Replacement Schedule
6
Schedule Maintenance Checks
7
5-00-01. 5-00-02. 5-00-03.
5-10-01 5-20-00.
Heating System
g
Ve~ilating Systems
5 5 5
5 5
6
11
5-20-03
Points,TorqueValues Aircraft File Inspection. Engine Functional Check
5-20-04
First 25 Hour
11
5-20-05
50 Hour
11
5-20-06
100
12
5-20-07
Access Cover identification, Lubrication and Service Guide
5-20-01
5-20-02
Check
Inspection
Inspection Hour Inspection
7
11
17
9-CONTENTS
3/48LANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT
PAGE
DATE
1/2BLANK 3/4BLAN K
4-99
5-00-00
5.
4-90
5-10-00
6.
4-99
5-20-00
7.
4-99
5-20-01
8.
4-99
5-20-01
9.
4-99
5-20-01.
10
4-99
5-20-02
11
4-99
5-20-06
12
4-99
5-20-06
13
4-99
5-20-06
14
4-99
5-20-06
15
4-99
5-20-06
16
4-99
5-20-07
17
4-99
5-20-07
18
4-99
5-20-07
19
4-99
5-20-07
20
4-99
5-Effectivity 5-Contents
4-99
5-EFFECTIVITY 4-99
1/2BLANK
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 5-00-00
M20M
GENERAL
AIRCRAFT DESCRIPTION. The four aircraft are place,
5-00-03
M20M
series
of
high-performance, turbocharged, single-engine, low-wing monoplanes.
LANDING GEAR SYSTEM
landing gear system has a steerable nose wheel. Single disc self-adjusting hydraulic brakes are featured on the main gear. Gear position lights, a warning horn and a gear position indicator on the floorboard are standard equipment. Bungee springs that preload the the retraction mechanism in an over-center position lock the gear down. An air pressure actuated safety switch in the electrical system prevents electric gear retraction on takeoff until a safe flying speed is attained. A gear throttle warning horn sounds when the manifold pressure is less than a pre-set value with the landing gear up. The electric gear retraction system has a manual extension system connected to the gear actuator that permits manual lowering of the gear in the event of an electrical malfunction. Lan~iing gear doors fully enclose the wheel wells to reduce sound levels and increase The electric
Wing flaps are electrically actuated and by a spring loaded "up-off-down" switch )00-04
are on
controlled the center
ELECTRIC POWER SYSTEM
1. The Master Switch and power relay control the electrical power system, comprised of two belt driven 70 AMP, 28 Volt, alternators and two 10 AMP HR, 24 batteries. The have altemator Volt, systems overvoltage protective relays and overvoltage annunciator lights. Circuit breakers or circuit breaker switches protect the electrical wiring and equipment from overloads. Standard electrical equipment includes: 2-100 watt landing lights, 2-100 watt taxi lights, navigation lights, interior lights,instrument panel/glareshield lights, gear and stall warning system, an electrical fuel boost electric electric an an starter, pump, gear retraction/extension system, with manual extension override, an electric trim system (optional) and an electrical flap system.
5-00-05
INSTRUMENTS
All flight instruments are in the shock-mounted Night Panel. Engine instruments are in the co-pilot’s panel. The pitot system provides air pressure to operate the airspeed indicator. The instrument static pressure system has two static air pickup ports tone on each side of the tailcone) that open to the atmosphere. An alternate static source is provided on center console. The instrument panel/glareshield lighting systems have manual dimming mechanisms. 5-00-06
CABIN HEATING SYSTEMS
VENTILATING
The heater muff encasing the exhaust system is the cabin heat source. Hot air from the heater muff, mixed with ambient air, controls cabin temperature. Air routed from the main heater duct system to noules at the windshield base defrosts the windshield. An optional defrost blower motor system is available.
performance. 5-00-02
WING FLAP SYSTEM
console.
The all-metal airframe has a tubular-steel cabin frame covered with nonstructural aluminum skins, a semi-monocoque tailcone, and a fuil-cantilever, laminar-flow wing. Control surfaces have structural spar construction with stressed skins riveted to the spars and ribs. Dual control wheels accompany the conventional flight controls. The pilot’s rudder pedals have toe brakes linked to individual hydraulic cylinders that supply pressure to the hydraulic disc brakes on each main gear wheel. Removable cc-pilot rudder pedals are standard equipment. The tricycle landing gear, having a steerable nose wheel controlled by rudder pedal action, is fully retractable. The wide-span trailing-edge wing flaps are electrically operated. For stabilizer trim, the entire empennage pivots vertically about its attaching points, 5-00-01
MOONEY AIRCRAFT CORPORATION
FLIGHT CONTROL SYSTEMS
The dual flight control systems can be operated from either the pilot or co-pilot seat. All flight controls are conventional in operation, using pushpull tubes to link the control surfaces to the control wheels and rudder pedals. Formica guide blocks maintain control tube alignment and dampen vibration. An interconnect spring mechanism links the aileron and rudder systems to assist in control coordination. The standard cc-pilot’s rudder pedals are removable. A dual brake installation is optional for the cc-pilot’s position. The manual or electric trim system sets the horizontal stabilizer angle of attack.
5-00-07
FUEL SYSTEM
The fuel system has sealed, integral wing tanks in the forward, inboard section of each wing. Vents at the aft, outboard top comer of each tank vent through a NACA scoop on the lower wing surface. Fuel sump drains are at the lowest point in each tank. The electric fuel pump is in the bottom left forward section of the fuselage, aft of the firewall. The engine-driven fuel pump mounts on the engine crankcase. Two fuel quantity transmitters in each tank are wired in series to fuel quantity gauges in the engine cluster gauge. The Master Switch, left side of the pilot’s panel, activates the fuel quantity indicating systems. The optional visual sight gauges are for partial fueling of wing tanks.. A "low fuel" warning annunciator light for each tank is activated when usable fuel quantity goes below 2 1/2
gallons.
4-99
5-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
The
TIME LIMIT COMPONENTS
5-10-00
It is recommended that overhaul
or
components should be accomplished
SERVICE AND MAINTENANCE MANUAL
M20M
replacement of
not later than the
specified overhaul
time limits, if
applicable
to a
component, do not constitute a guarantee that the component will reach that time limit without requiring maintenance.
of operation for that component or in data or manufactures service accordance with airworthiness directives.
specified period
NOTE "ON CONDITION" items are to be repaired, replaced or overhauled when inspection or performance revea!s~an unserviceable condition.
OVERHAUL AND REPLACEMENT SCHEDULE
5-10-01
RECOMMENDED OVERHAUL OR REPLACE TIME LIMITS
ITEM
Landing Gear 1000 Hours On Condition
Actuator No-Back Spring All other Components
Powerplant
Engine
2000 Hours (Reference Lycoming SI 1009AJ) 2000 Hours or 6 years (Refer to Mfg.’s maintenance data) 4 years or Engine O/H CTBO)(refer to Slick Electro
Propeller
Magneto
:Slick
repair/O/H data)
induction Ai; Filter
Natural Rubber Engine isolators Gaskets V-Band Couplings All other Components Fuel Fuel Selector Valve
(Airight
Oil
500 Hours 10 years At Engine O/H On Condition
(siack)
On Condition
Christopher Tool) as
7 years or Engine 24 Months
below)
All Cbmponents
VacuumPump,
100 Hours 500 Hours (CVIJ4 Filter 500 Hours or Annually 200 Hours On Condition
System’
occurs
first.
On
Condition)
On Condition
Controls
On Condition
Miscellaneous systems
On Condition or 500 Hours or Engine O/H 200 Hours (Inspect Drive Coupling) 2 Years or 1 Hour Total Use
Primary
Stand-by Vacuum PumplClutch E.L.T. Battery Oxygen Cylinders Lt. Wt. Steel Cylinders Composite Cylinders Scott Oxygen Regulator. All Other Components (Excluding
24 years or 10,000 recharge cycles 15 years or 10,000 recharge cycles 6 years-overhaul; 3 years-test
Avionicsi
On Condition (See NOTE above) Refer to Manufacturers Publications Refer to Bendix/King Service Memo No. 292
Avionics
Bendix/King Systems X
O/H, whichever
On Condition
Instruments Vacuum Regulator Garter Filter
Flight
On Condition
System
Flexible Hoses (All, except Aeroquip 601 Fuel Hoses All other Components (includes teflon hoses)
Filters Vacuum Pump Filters Gym Instruments TIT Probe Other Components Electrical All Components.
or
Hydrostatic Test Required
3 year intervals.
NOTE
Components
5-10-00
should be
inspected and serviced at regular intervals per the servicing, lubrication and inspection chart of this manual. 4-99
OLDWILLWAYNE SCHEDULED MAINTENANCE CHECKS
5-20-00
Inspection Intervals. Perform a 25, 50, or 100-hour inspection of the aircraft, components and engine at recommended intervals as outlined in the following paragraphs. NOTE Aircraft operated in a salt air environment are considered high risk for corrosion damage, and should be cleaned and inspected at more frequent intervals. Refer to AC 43-4. INSPECTION CHECK POINTS
5-20-01
The general points to be covered during inspection are grouped in accordance with the nature and function of
the items discussed.
Moving Parts shall be inspected and checked as applicable for: proper operation, security of attachment, sealing, cleanliness, lubrication, servicing, safetying, adjustment, tension, travel, condition of hinges, excessive corrosion, cracking, wear, binding, deformation, and any other apparent damage. 2. Metal Parts shall be inspected and checked as applicable for: security of attachment, condition of finish and/or sealant, distortion, fatigue cracks, welding cracks, corrosion, and any other apparent damage. The tubular frame structure should be inspected during each annual inspection for any signs of corrosion or damage. 3. Fuel, air, oil and hydraulic oil lines and hoses shall be inspected as applicable for: cracks, dents, kinks, deterioration, obstruction, chaffing, improper bend radius, and insecure installation. Replace or correct if any of these conditions exist. Hose clamp installations on fuel and hydraulic systems between systems or between systems and the engine shall be torqued to 25 inch pounds. Hose clamp installations on blast 1.
tubes, air ducts, shall be 4.
torqued
Pipe
Lubricate
vacuum
Use only MlL-T-5542 thread Oxygen Lines compound or TeRon thread seal tape on threads of valves, connectors, fittings, parts or assemblies which contact with oxygen. The thread be applied sparingly to the first three threads of the male fitting only. No compound is to be used on the coupling sleeves or on the outside of the tube flares. Exireme care should be exercised to prevent the contamination of the thread compound or teflon tape with oil, grease or other lubricant.
might come in comp0u"d must
Fuel, Hydraulic, Air, Oil Lines or
Vacuum Lines No lubrication is to be used. Check when instructions ma"ufacturers installing components. Refer to Section 37 for maintenance
p’ocedures
on vacuum
system.
Tapered Threads Use TeRon Threadseal Tape. (1) Continue to tighten until fitting is correctly positioned but do not overrun or backoff. (2) If leaks are detected, tighten one full tum more.
(3)
If
disconnected
leaks and
persist, the parts rejected; replace
should with
be new
components. 5´• Electrical wiring shall be checked as applicable for: loose, corroded, or broken terminals; chaffed, broken, or worn insulation; insecure installation; heat deterioration; and any other apparent damage.
6. Bolts and nuts in critical areas shall be checked for: fretting, wear, damage, stretch, proper torque, (Figure 5-3) and safetying. 7. Filters and screens shall be
lines, drain and vent lines
inspected
pounds. Tightening and torque procedures. as
Use "Parker Thread
equivalent on male mings only. Apply lubricant, omitting the first two threads, sparingly and carefully. Use only aircraft engine oil to Engine Fittings lubricate fittings threaded directly to engine. tube"
to 15 inch
Threads pipe threads
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
for contamination
or
removed, cleaned and
damage that would
require replacement.
follows:
TORQUE VALUES SEE FOLLOWING TABLES
4-99
5-20-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION FLARE NUT TORQUE VALUES-
SERVICE AND MAINTENANCE MANUAL
M20M
Tighten
These torque values
to minimum
torque value for appropriate size
CAUTION derived from oil-free
are
as
shown
(Figure 5-1).
cadmium-plated threads.
FITTING STEEL TUBING
ALUMINUM TUBING.
SIZE
MINIMUM
MINIMUM
MAXIMUM
-3 -4
40
65
MAXIMUM
30
70
50
90 120
-5
60
80
70.
-6
75
125
90.
150
-8
150
250
155
250
-10
200
350
300
400
-12
300
500
430
575
-16
500
700
550
750
-20
600
900
-24
600
900
FLARE NUT TORQUE FIGURE 5-1 METRIC BOLTS, SCREWS
NUTS
TORQUE VALUES
Failure of threaded fasteners due to over-tightening can occur by bolt shank fracture or by stripping of the nut A bolt or screw assembled with a nut of the appropriate class is intended to provide an assembly capable of being tightened to the bolt proof load without thread stripping occurring. The torque value to be set for a particular size of screw is dependent upon: 1) Material of the screw. 2) Parent material (steel, non-ferrous metal or plastic). 3) Whether the screw is untreated or plated. 4) Whether the screw is dry or lubricated. 5) The depth of the thread.
and/or bolts thread.
TIGHTENING TORQUES NOMINAL DIAMETER
Untreated Screw(Black Finish) Friction Coefficient 0. 14
5.6
8.8
PROPERTY CLASS
10.9
12.9
Nm/ft.lb.
Nmm.lb.
TORQUE Ma
Nm/ft.lb.
Nmm.lb.
1.92/1.42 4.40/3.25 8.65/6.38 15/11
2.30/1.70 5.25/3.87
25/1 8.4
29/21.3 43/31
(Coarse Thread)
M5
0.60/0.44 1.37/1.01 2.70/1.99
Ms
4.6/3.3
M7
7.6/5.6
M3
1.37/1.01
M10
22/16
M12
39/28
M14 M16
62/45 95/79
3.10/2.29 6.15/4.54 10.5/7.7 17.5/1 2.9 26/19 51/37 89/65 141/103 215/158
M18
130/95
295/217
M20
184/1 35 250/1 84 31 5/232
420/309
M4
M8
M22 M24
M27 M30 M33
M36 M39
5-20-01
470/346 635/468 865/637 1111/819 1440/1062
36/26 72/53 125/92 198/146 305/224 420/309 590/435 800/590 1020/752
570/420 725/534
1510/1113 2050/1 511 2770/2042 3560/2625 4620/3407
1070/789 1450/1 069 1970/1 452 2530/1 865 3290/2426
4-99
10.417.6 18/13
87/64
150/110 240/177
365/269 500/368 71 0/523 96onos 1220/899 1 810/1334 2450/1 806 3330/2455 4280/31 56 5550/4093
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
(METRIC TORQUE
TABLES
CONTINUED)
8.8
10.9
12.9
Nmlft.\b.
Nmtft.\b.
45/33 88/64 160/118 250/1 84 3801280 550/405 770/567 1050/774 1300/958
(Fine Thread) NmP.\b.
~BPUE Ma
M12x1.25
95/70
38/28 73/53 135/99
M14x1.5
150/110
21 0/1 54
M16x1.5
2251165 325/239 460/339 610/449 780/575
3151232 460/339 640/472
M8x1
27/19
M10x1.25
52/38
M18x1.5 M20 x1.5 M22
x
1.5
M24 x2
TIGHTENING TORQUES DIAMETER
860/634 1100/811
E\ectrically Zinc
P\ated Friction Coefficient 0. 125
10.9
129
Nmlft.lb.
Nmlft.lb.
2.15/1.59
3050/2249
1.80/1.33 4.10/3.02 8.10/5.97 14/10.3 23/1 6.9 34/25 67/49 117/86.2 185/136 285/210 390/287 550/405 745/549 960/708 1400/1032 1900/1 401 2580/1 902 331 0/2441 4290/3163
8.8
10.9
12.9
Nmlft.lb.
Nmm.lh.
35/25 68/50 125/92
42/30 82/60 150/110
195/143 295/217 425/313 600/442 800/590 1000/737
235/1 73 350/258
5.6
8.8
Nmm.lb.
Nm/ft.lb.
(Coarse Thread)
M3
0.56/0.41
1.2810.94
M4
1.2810.94
M5
2.50/1.84
2.90/2.14 5.75/4.24
M6
4.3/3.1
9.9/7.3
M7
16.5/12.1
M8
7.1/5.2 10.5/7.7
M10
21/15
48/35
M12
36/26 58/42
132/97
M14
24/1 7.7 83/61
M16
88164
M18
121/89
200/1 47 25/202
M20
171/126
390/287
M22
230/1 69
M24
295/217
530/390 675/497
M27
435/320 590/435
995/733 1350/995
800/590 1030/759 1340/988
1830/1349
M30 M33 M36
M39
TORQUE Ma
2360/1 740
4.95/3.65 9.70/7.15 16.5/12.1 27/1 9.9
40/29 81/59 140/103 220/1 62 340/250 470/346 660/486 890/656 1140\840 1 680/1 239
2280/1 681 3090/2278
3980/2935 5150/3798
(Fine Thread) Nm~ft.lb.
M8x1
25/18
M10x1.25
49/36
M12x1.25
88/64
M14x1.25
140/1 03
M16x1.5
0/154 305/224 425/313 570/420
M18x1.5
M20 x1.5 M22 x1.5 M24
x
2
TORQUE Ma
21
720/531
METRIC CONVERSION FACTOR: One Nm(Newton Meter) 1.355818 Nm One Foot Pound FIGURE 5 -2
4-99
51 0/376
720/531
960/708 1200/885
.7375 Foot Pound;
5-20-01
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
AN/MS STANDARD BOLT, NUTS TORQUE TABLES FINE-THREAD SERIES
TENSION-type
SMEAR -type BOLTS
BOLT/NUT
AN() BOLTS
SMEAR-type AN() BOLTS
TENSION-type NAS() BOLTS
NAS()
SIZE
AN365/AN310
AN364/AN320
AN365/AN310
AN364/AN320
8-36
12-15
7-9
10-32.
20-25
12-15
25-30
15-20
1/4-28
50-70
30-40.
80-100
50-60
5/1 6-24 3/8-24 7/16-20 1/2-20 9/1 6-18 5/8-18 3/4-16 7/8-14 1-14
11/8-12 11/4-12
100-140
60-85
120-145
70-90
160-190
95-110
200-250
120-150
450-500
270-300
520-630
300-400
480-690
290-410
770-950
450-550
800-1 000
480-600
1100-1300
650-800
1100-1300
600-780
1250-1 550
750-950
2300-2500.
1300-1500
2650-3200
1600-1 900
2500-3000.
1500-1800.
3550-4350
2100-2600
3700-5500.
2200-3300.
4500-5500
2700-3300
5000-7000.
8000-4200
6000-7300
3600-4400
9000-11 000
5400-6600
11000-13000
6600-8000
COARSE-THREAD SERIES
8-32
12-15
7-9
10-24.
20-25
12-15
1/4-20 5/1 6-18 3/8-16 7/16-14 1/2-13 9/16-12 5/8-11 3/4-10 7/8-9
40-50
25-30
80-90
48-55
160-1 85
95-1 00
235-255
140-155
400-480
240-290
500-700
300-420
700-900
420-540
1150-1600
700-950
2200-3000.
1300-1 800
TORQUE VALUES
(Units
are
Inch-pounds)
Reference: Federal Aviation
Figure 5 1(A), p.
3
118 Agency Advisory Circular No. 43.13 Torque Values for Nut-Bolt combination (Units are inch-pounds) 1. Be sure nut and/or bolt threads are clean and dry(unless Mfg. states otherwise). 2. Run bolt down near contact with washer or bearing surface and check ’’friction drag torque" required to
Recommended
turn
bolt/nut. 3. Add ’Yriction drag Torque Value".
torque"
to the recommended
(FRICTION
torque value from Figure
DRAG TORQUE
REC’MD TORQUE
5-2. This value is considered "Final
FINAL
TORQUE).
CAUTION DO NOT REUSE LOCKNUTS IF THEY CAN BE RUN UP FINGER TIGHT.
5-20-01 10
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
-AIRCRAFT FILE INSPECTION
5-20-02
Propeller Log Book, Registration Certificate,
Balance Record, Airworthiness Certificate, Weight Engine Service Information, Aircraft Radio Station License (if applicable), FAA Airworthiness Directives, and Mooney service documents.
or
annual
and/or 25 hours after installation of
new or
Prior to
a
scheduled 100-hour
The 50-hour inspection includes all requirements of the 25-hour inspection, plus the necessary removal of inspection doors, panels, or fairings. After the first 25 hours of operating time, a new, remanufactured, or newly overhauled engine should be given a 50-hour inspection including replacement of the lubricating oil and filter. 1.
inspection,
FIRST 25-HOURS INSPECTION
C.
E. Remove and clean fuel
injector fuel
filter
strainer.
F. Service engine oil sump with proper type, and amount of lubricating oil.
grade,
G. Inspect ennine intake and e~haust systems for evidence of lea~kage and looseness. Reference Lycoming Service Instruction No. 1422A or subsequent revision ~br exhaust and TIT inspection procedures. elbows and
shielding
nuts for
Inspect cylinders for evidence of overheating. turbocharger for security of clamps and
L.
Inspect engine controls
for full travel, freedom of
M. Visually Inspect fuel and oil lines for security of co""ections and evidence of leakage or damage. N. Visually inspect induction air system; check operation of alternate-air door (refer to paragraph 71-62-00). 2.
Propeller. Inspect propeller
hub and spinner for general condition, looseness, and/or oil leakage. A.
Inspect security and condition of equipment on engine. 5. Inspect fuselage, wing and empennage for extemal evidence of damage. Pay particular attention 4.
B. to next
Inspect Right.
blades for nicks and cracks.
Repair prior
3. Cabin. A. Inspect brake and parking brake control systems for proper operation and fluid level. B. Inspect trim system and indicator for free operation and travel.
to scratches and dents.
6. Inspect windshields and windows for crazing, cracks, and scratches. 7. Inspect control systems for binding, excessive freeplay, and damage. 8. Inspect pitot and static systems for possible
C. Inspect cabin and baggage doors for proper operation, and sealing.
damage,
D. Inspect cabin, instrument panel, glareshield, position, anticollision, landing and taxi, lights. E. Inspect fuel selector valve, gascolator, and
obsbuctions. of bolts,
screws, etc.
10.
oil
movement, and security.
installed
security
full-flow
K. Inspect baffles for secure anchorage, close fit around cylinders, and freedom from cracks.
exhaust leaks.
for
the
D. Drain and clean fuel strainer.
I.
1. Visually inspect propeller, spinner, and engine cowling; remove cowling. 2. Inspect and clean induction air filter if aircraft has been operating under dusty conditions. Check operation of alternate air door. 3. inspect engine compartment for evidence of fuel,
exterior
replace
J. Inspect attachments.
recommended engine inspection.
Inspect aircraft
and
H. Inspect spark plug security.
Airplane Flight Manual. The inspection does not require removal of all access panels or disassembly of components; however, it should include completion of all lubrication 8 service requirements. The inspection should be extensive enough to detect any damage or maladjustment which might jeopardize flight safety. After the first 25 hours of a new or overhauled engine operation, refer to paragraph 5-20-05 for the
9.
Remove
cartridge.
the
or
engine oil sump
B. Remove and clean suction oil strainer; reinstall strainer and plug. Safety wire strainer plug.
The, one time, 25-hour inspection consists of a visual inspection of the propeller, engine, and aircraft general condition, including a preflight inspection as outlined in
oil
Engine.(Refer to engine manufacturer service data or subsequen, for oil change frequency)
A. Drain
overhauled engine, wash down the engine and engine components. Then perform an engine runup in accord with procedure recommended in the Airplane Flight Manual. Make a record of all malfunctions and abnormalities. After the engine runup, complete a differential (hot engine) compression check. To verify correction of malfunctions and abnormalities, perform a second engine runup and a flight test after completing the inspection. 5-20-04
-(Repetitive)
SE #408A
ENGINE FUNCTIONAL CHECK
5-20-03
50-HOUR INSPECTION
5-20-05
Aircraft 100-hour and annual inspections cover, in addition to examining the aircraft proper, a review of the status of compliance with current Federal Aviation Regulations. This review includes inspection of the Airplane Flight Manual, Aircraft Log Book, Engine Log
Book,
MOONEYAIRCRAFT CORPORATION
boost pump for proper
Inspect and service batteries.
4-99
operation.
5-20-02
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
C. Drain engine oil sump; remove, inspect and clean oil suction screens; reinstall and safety. Remove full-flow oil filter cartridge; replace with new cartridge and safety. Inspect crank case breather lines for obstruction. Safety wire oil filter installation.
F. 4.
Inspect oxygen system (tf installed). Landing Gear.
A. inflation.
Inspect ´•tires for cuts, blisters,
wear,
and proper
B. Inspect shock discs for proper extension at aircraft static weight.
D. Refill engine oil sump with the proper type, grade, and quantity of lubricating oil. E. Inspect fuel injector and all fuel line connections for security and condition. Remove and inspect gascolator strainer, F. reinstall strainer. Inspect fuel lines and connections:
C. Inspect hydraulic brakes for wear, warpage and proper installation.
Wings. Inspect surfaces and tips for damage. B. Inspect ailerons, aileron attachments, bellcranks for damage and proper operation. C. Inspect flaps and attachments for damage proper operation. 5.
A.
D.
Lubricate
controls
per
Section
and
pressure check fuel system with mixture control at IDLE CUTOFF and BO~ST PUMP ON.
and
G. Inspect all air ducting and connections in the heating and induction air systems for leaks. Remove and
5-20-07
clean induction air filter (replace at 500 Hrs). Inspect altemate air door and magnet for security and operation. Leak check ail exhaust manifold connections, engine exhaust manifolds. Inspect for security.
if
necessary, 6.
Fuselage
and
Empennage.
H´•
A. Inspect stabilizer, elevators, fin, and rudder for damage and proper attachment. B.
Lubricate
controls
per
Section
5-20-07
C.
Inspect Trim System
for proper
inspections and component 5-20-06
service
50 hour
Inspect cylinders for burned paint and cracked or broken fins. Inspect baffle sealant. J. inspect accessory case, starter, aitemators, vacuum pumps hose, firewall and fittings for security or damage. K. Inspect turbocharger for cracks or damage. Inspect turbocharger control components for obvious damage. Inspect intercooler for damage or obstruction. L. Inspect tubular engine mount for cracks, damage or corrosion; check all bolts and rubber isolation mounts for security and condition. M. inspect engine and propeller controls for free operation, full travel, proper connection (security) of cable housing swage at the HEAD tube and security of
Service Bulletins and Instrudions. Check for aircraft conformance to FAA Specification 2A3.
attachment. NOTE Cablecraft control cables are lubricated for the life of the control cable. DO NOT REMOVE seals or lubricate control cable.
Recommended 100-hour/annual and special inspection requirements are outlined in the following paragraphs: 1. ENGINE INSPECTION. Prior to the inspection, the engine cowling and propeller spinner. Wash down the engine and engine compartment. Then perform an engine runup in accord with the procedure recommended in the Engine Maintenance and Operators Manual. To verify correction of malfunctions and abnormalities, perform a second runup and flight test after the 100-hour/annual inspection engine remove
N. Inspect enaine fuel pump pressure. (See Textron-Lycoming Service information and Section 71-00-50 for this procedure). O. Inspect and reinstall cowling. Check cowl flap’s for operation, condition, proper opening and position
indication.
set-up.
P.
differential compression check: clean and gap plugs if necessary.
or
ignition
(hot engine) replace spark
Inspect battery cables, electrical wiring, and harness for condition, secure anchorage, loose
tenninals, and burned
or
chaffed insulation.
Q. Inspect batteries, battery mount areas, and vent system for condition and corrosion. Inspect blast tube for obstruction. Flush battery mount areas with soda solution to neutralize corrosive action if necessary.
B. Inspect engine for evidence of excessive fuel or oil leakage. Inspect oil cooler. Inspect oil fuel hoses for condition security. Repair as required. 5-20-06 12
and
I. Inspect baffles for secure anchorage, cracks, holes, deformation, and for close fit around cylinders.
components is to be included at this interval when applicable. Comply with applicable FAA Directives, AD Notes, and applicable Mooney or Vendor mandatory
a
grounding
components, if required.
100-HOUR or ANNUAL INSPECTION
Complete
for
and timing. Inspect distributor block for erosion and cracks. Inspect cam follower felt for proper lubrication, and remove excessive oil from breaker compartment. Inspect magneto pressurization per Slick magneto maintenance manual. Repair or replace
(Refer to Fig. 54) The 100-hour (or annual) inspection is a thorough, searching inspection of the entire aircraft. Preparation for the inspection includes the thorough cleaning of exterior and engine compartment, removal of all fuselage, wing, and empennage inspection doors, cover plates, and fairings at all systems attach, hinge, and bearing locations (including wing and empennage to fuselage mating points). Operating limit replacement (See Section 5-10-01) and special testing of
A.
magnetos
clearance,
if
operation.
repetitive guide.
I"spect
synchronization; Inspect magneto points for condition,
necessary. 7. See Section 5-20-07 for any
SERVICE AND MAINTENANCE MANUAL
M20M
4-99
OLDWILLWAYNE R. Inspect exhaust system for cracks, looseness and for evidence of leakage. Replace or repair damaged components. Reference (G) 50 hour inspection.
Inspect exhaust stacks for burned
S.
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
areas,
J.
Inspect exhaust couplings, seals, clamps and slip-joints for cracks, deformation, leaks and security. U. Inspect studs, nuts, bolts, etc. for damage and proper torque. re-install cowling. Check cowl flaps for V. Inspect proper operation, condition and proper position indication. T.
Inspect spinner and bulkhead for cracks and
bulkhead for snug fit be~veen Inspect spinner spinner support. Use shims as propeller cylinder G.
necessary to obtain correct snug frt. 3. LANDING GEAR and RETRACTION SYSTEM INSPECTION. tires for proper inflation, cuts, blisters, excessive wear. Replace with new, tire if necessary.
A. Inspect slippage, and
CAUTION
Landing Gear Retraction checks after any tire has been removed and/or replaced before flying the aircraft. run
at least 5
Cycle
B. Inspect wheels misalignment, corrosion
condition of felt seals and 250 hour intervals,
for
A.
bolt
failure.
discs for warpage or wear C. Inspect brake pads (Ref. Section 32-40-04). D. Inspect hydraulic reservoir for proper fluid level. E. Inspect hydraulic brake lines and hoses for leakage, dents, cracks chafing, kinks, and security. F. ~lnspect parking brake system for proper
engagement and release. on main 6 nose landing (See 32-81-00) H. Conduct Hard/Overweight Landing Inspection
G. Check shock disc gap
or
stain.
and
inspect tank
C. Inspect fuel tank drains for water contamination.
interior
when
leakage, sediment,
Inspect fuel-tank vents for obstruction. E. Inspect fuel selector valve for proper tank smooth operation, or any leakage when in OFF position. F. Inspect gascolator for leakage; check sump for D.
sediment, water
or
other contamination.
G. Inspect electric boost pump for leaks, security of mounting, adequate fuel pressure, switch operation, and condition of wiring and electrical connections.
(1) Inspect electric boost pump for proper operation by "T ing" into the line with a calibrated fuel pressure gauge. Boost operation should result in a 4555 P.S.I. reading (mixture full RICH, throttle-IDLE). (2) Adjust relief setting on pump if needed. H. Inspect fuel quantity gauges and transmitters for security of mounting and condition of wiring and electrical connections. fuel tank filler port for cleanliness, cap condition of servicing placards. Inspect fuel filler cap O’rings for condition and replace if needed (Reference SECTION 23-00-01). I. Inspect security, and
5. EXTERIOR INSPECTION. A. Inspect fuselage exterior surfaces for corrosion, dents, loose rivets, or popped damage, or cracks, scratches, skins), oilcans(stretched deteriorated paint. 8. Inspect windshields and windows for cracks, crazing, scratches, condition of sealant, and security of
installation.
C. Inspect wings, flaps, and ailerons for corrosion, damage, loose or popped rivets, dents, scratches, cracks, condition of attaching points, lubrication, freedom of operation, free-play, travel, and balance weight attachment. Inspect speedbrake cartridges for damage or wear. Check for proper operation. Every 200 hours remove speedbrake cartridges per 27-96-01. D. Inspect empennage for corrosion, damage, loose or popped rCvets, free-play, dents, scratches, cracks, condition and lubrication of hinge points, attachment of balance weights, and freedom of operation, manually and electrically.
per SECTION 32-32-00.
paragraph
or
Drain tank seepage is evident. 8.
gear.
Jack aircraft as recommended in the following inspections:.
Inspect fuel tank exterior for evidence of fuel
seepage
distortion,
cracks,
Inspect bearings; repack bearings at or
main gear for cleanliness and
4. FUEL SYSTEM INSPECTION.
spinner (if not already removed). B. Inspect security of propeller installation. C. Inspect hub bolts for proper torque (61-00-20) security and damage. D. Inspect hub components for damage or leaks and blades for cracks and nicks. Repair prior to next flight. E. Inspect Anti-ice boots for security and operation.
Always
Inspect
Section 32-30-01.
A. Remove
approved,
mechanism for and lubrication.
steering
pivots, and bearings for wear, damage, distortion, misalignment, corrosion, cleanliness, and lubrication. M. Inspect landing gear actuator for security of mounting, deanliness,and indication of overheating, damage, and operation. Inspect motor brushes for wear. N. Perform landing gear operational Inspection per
2. PROPELLER INSPECTION.
F.
wheel
nose
damage. L. Inspect landing gear retraction linkage, bdlcranks, K.
cracks,
distortion and looseness.
Inspect
adjustment, alignment, corrosion,
7-10-00 for
I. Inspect nose gear for cleanliness and damage. Check nose gear retraction tube bungees for sheared or broken roll pins.
NOTE Maximum allowable towing damage on leg assembly is 1/32 inch dent. No repair allowed on heat treated landing gear components 4-99
5-20-06 13
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION E.
Inspect cabin
M20M
door and door frames for
SERVICE AND MAINTENANCE MANUAL
H.
damage,
Inspect wing
interior
for
foreign material,
corrosion, nicks, dents, hinge security, and lubrication.
corrosion, and/or evidence of fuel leakage.
F. Inspect cabin door lock mechanism for lubrication and proper engagement. See Section 52-11-00 for rigging procedures.
I. Inspect empennage hardware for corrosion.
G.
Inspect
compartment for
the
baggage door damage, corrosion,
A. Inspect control column and control wheels for full travel, proper rigging, free-play, binding, security of mounting, proper lubrication, and direction of control surface movement with relation to control wheel
condition to door frame and door seals, condition and operation of door locking mechanism, and condition of cargo restraints/tiedowns.
movement.
Inspect ventilating system drain line for obstruction. Inspect landing and taxi Tights for security,
I. condition and adjustment. proper 33-43-00 for adjustment procedures.
See
CAUTION All flight control components should be checked to verify that all moisture drain holes are free of obstructions.
Section
J. Inspect Decals 8 Placards for condition and proper location.
K. LIGHTNING STRIKE
B. Inspect elevator system for rigging, adjustment, condition of all bearings, hinges; wear on downspring eyes, cable fittings, security of mounting, damage,
INSPECT FOR:
(1) Seized Bearings Engine and Airframe (2) Failed Electronics Radios, Instruments, etc. (3) Bumed (melted) Metal-trailing edges,antennas, etc. (4) Burned Wiring--throughout aircraft (5) Burned marks on Propeller--Leading edges, tips 6. INTERIOR INSPECTION.
proper
E.
check for free movement of toe-brake and proper rudder and nose wheel travel.
and
Open access panels and inspection doors, and fairings as required. B. Inspect fuselage~uing attaching bolts for proper torque and sadetying and evidence of damage or corrosion (interior side panels will require removal to accomplish ~tl7is inspection).
NOTE All control rigging checks should be made with the aircraft jacked and leveled and with the
Some elevator trim tubes have poly tape wrapped at bulkhead penetrations. If tape shows signs of wear, rewrap (1/2 lap) tube with 2" wide Y9265 polyurethane tape. Trim tubes, without tape, which show signs of abrading grommet should be wrapped. See SE M20-185.
damage.
Inspect tubular structure for corrosion or damage (interior side panels will require removal). (Reference Mooney Service Bulletin M20-208A (or D.
revision) forspecific procedures) (annually).
MAX. TUBE WEAR-.007 in. wall thickness diameter reduction.
E. Inspect wing ribs and stringers for cracks and evidence of damage or corrosion. F.
cracks,
Inspect wing or
spars
for
9.
damage, distortion,
G. inspect electrical wiring, fuel, oil and hydraulic lines, and air ducts for security, damage, interf~erence,
chaffing,
B. Clean and inspect vacuum filter. filter on vacuum regulator.
de-bonding.
C.
.014 in.
plumbing
for
Replace garter
Inspect vacuum regulator at vacuum manifold. operation of high-and low-vacuum waming lights or vacuum gage. Inspect Stand-by vacum System per Section 37-40-00.
NOTE Seal all receptacles and plugs outside cabin environment with Dow Coming #4. 5-20-06
or
INSTRUMENT/AVIONICS INSPECTION.
A. Inspect all instrument wiring and condition and proper connections.
corrosion.
or
pedals
F. Inspect flap system for rigging, travel, and stop adjustment; flap rods, interconnects, bellcranks and hinges for corrosion, security, and lubrication.
A.
current
control
E. Inspect stabilizer ~trim control system for security and proper adjustment, shaft and stop nuts for proper rigging, trim coc~ol wheel for smooth operzrtion, u-joints for freeplay and good working order, ac~ator threads for lubrication, linkage for corrosion, and guide blocks for looseness or excessive wear. See Section 27-42-00 for inspection lubrication of bearing block for pitch trim system.
remove
of firewall for
to
hinges;
7. INTERNAL INSPECTION.
Inspect forward side
relation
D. Inspect rudder system for damage, corrosion, lubrication, security of link bolts, rod endbearings and
proper location.
C.
proper
and
corrosion,
Ilin~ bolt security.
equipment that might restrict
Inspect Oxygen system per SECTION 35. Inspect Decals 8 Placards for condition
and
pulley
C. Inspect aileron system for damage, corrosion, iubrioation, rigging, travel, stop adjustment, condition of hinges, bellcranks, pivots and rod end bearings, and
8. Inspect safety belts, hamesses and attaching brackets for cleanliness, condition, latch operation, and security of attachment.
D.
lubrication
travel, stop bellcranks,
movement.
A. Inspect seats, seat tracks, and upholstery for cleanliness and mounting security; check seats for condition and operation of position locks; inspect seat structure for cracks, deformation, corrosion, and mechanism lubrication,
C. Inspect for loose controlmovement.
8
brackets
8. FLIGHT CONTROL INSPECTION.
baggage warpage, hinge and
security, H.
attachment
Check
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M E.
D. Inspect all instruments for proper pointer indication,range and limit markings, condition of indicator markings, cracked or loose glass, slippage marks, and security of installation.
Check operation Check rheostat.
lights.
of instrument and
placard
operation of pitot head heater. Check operation of cluster gauge.
F. Check
G.
for lighting, Inspect proper compass compensation, security of mounting, liquid leakage, and discoloration. Swing compass at annual inspection and after any new equipment has been installed. Degaussing tubular structure may be necessary if compass will not compensate with in 100. See Service E.
operation of fuel gauges. Check operation of annunciator light press-to-test
H. Check I. switch.
Operatian of ignition switch, and starter
Instruction M20-95. K. Flight check operation of and warning horn.
Inspect altimeter for scale error, disrolored markings, proper pointer readings, setting knob freedom, and synchronization of barometric scale with F.
L.
reference markers.
Inspect Avionics Equipment for proper operation security. i. Inspect Avionics antennas, wiring, and shielding for obvious damage or defects. J. Inspect pitot head for port obstruction; check H.
Flight
check
position
operation of stall warning hem.
N. Inspect batteries, batteries’ connections for cleanliness.
and
battery box proper
11. MISCELLANEIUS/OPTIONAL
areas,
installation
and and
EQUIPMENT
A. Inspect anyu installed equipment not covered by previous paragraphs for proper operation, attachment
lines for cracks, dents, kinks, proper bend radius, and security of attachment. Drain system and check for leaks. obstruction
gear
M. Check operation of "Prop De-ice" (if installed). Push switch "ON", observe prop de-ice annunciator for illumination (BLUE light). Observe "BUS LOAD" meter (27-0001 thru 27-0052) or ammeter (27-0053 thru 27-TEA) for fluctuation during cycle action of timer.
G. Inspect Right panel for security of mounting, condition of shock mounts, freedom from interference with structure, and condition of ground straps.
for
landing
lights
or
obvious defects. 12. POST INSPECTION FLIGHT TEST.
and
K. Inspect static ports aerodynamic smoothness at port installations. Inspect lines kr bends, cracks, dents, kinks, and security of
Flight test the aircraft to verify correction of all malfunctions and abnormalities. Make proper entries in aircraft log book.
attachment. Drain system and check for leaks. Check alternate static pressure source located on left flight
Wing
access covers may between model year aircraft. Component locations remain
panel. 10. ELECTRICAL FUNCTIONAL TEST.
vary
to
some
degree
basically unchanged.
operation of navigation lights. taxi lights. Check operation of landing Check operation of dome lights and cigar
A. Check B.
C.
lighter. D. Check
operation
of anticollision
lights.
4-99
5-20-06 15
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
SERVICE GUIDE
ACCESS COVER IDENTIFICATION, LUBRICATION
34
23
U
n Ls
7-/ L5
~-4
L3
2J
18
29
13
13
28
30
31 10
10
R
32
o
000
I
O
C3
o,,,
0
I’ 1~1 ’I
I
I
I
000
00
r
11
I
r 32
o
o
O"
000
o
12
12
14
14
12
12
11
0
o
27
27
35
35
27
15
17
19
27
19
16
c>
o o
27
27
27 21
20
34
22
O
i I
7
25
33
26
ten
24
SMR5-3
FIGURE 5 -4
Access
5-20-06 16
covers
riveted in
NOTE need not be removed for routine
place during production
4-99
inspections.
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
5-20-07
MOONEY AIRCRAFT CORPORATION
M20M
ACCESS COVER IDENTIFICATION, LUBRICATION AND SERVICE GUIDE
ITEM NO..
ITEM DESCRIPTION
1
Flight
LUBRICATION SYMBOL*
INTERVAL
(HRS)
8
Instruments
Vacuum Regulator Tum Coordinator Vacuum Filters--Replaceat Garter Filter. Control System Control Column Bearing Ball Rod End Bearings Universal Joints Bellcranks
Ad;ustments:
2
I: X
100 100 100 100
Engine Cowling Pumps
8 8
500m*t
Nose Gear Grease Fittings Retraction Tube Rod End Bearings Bellcranks
52
W
Vacuum 3
Bungees Gear Door Rod End
Bungees
Bearings:
W 5Z ~C Z
Gear Door Rod Enb Electric Gear Actuator Gear Box** Electric Gear Actuator Ball Screw.
Bearings:
SZ
Rudder Controls: Elevator Control Tube Rod End Bearings Bellcranks Batteries Stabilizer Trim ’Con’trol’Shaft: UniversalJoints. Guide Blocks Hydraulic Reservoir Oxygen, High Pressure Fittings
5
~k Z 8 Z
13 8
Rudder Controls: Elevator Control Tube Rod End Bearings Bellcranks Stabilizer Trim jack Variable Downspring System Tail Strobe Light Power Supply
6
Sdrev;lAci~uator Brgs.
Empennage
7
Attach Points.
Stabilizer trim Attach Point
XkkM
100
Z Z
Main Gear Grease Fittings Retraction Tube Rod End Bearings Bellcranks
4
500
8 8
100 100 100 100 50 100 100 100 100 50 AR 1000
100 100 25 100 100 50 50
8
100 100 100 100 100
8 8
100 100
Z 0
See last page of section for lubrication symbol legend. No periodiclubricant on Avionics Products #102000-2. If necessary to relubricate, use Aeroshell 22, Mobil 28 or MlL-G-81322 ONLY. Change garter filter on vacuum regulator every 100 hours. Change instrument filters at 500 hours, clean every 100 hours. Inspect Stand-by Vacuum Pump drive coupling every 200 hours. (Refer to Airborne Service Letter No. 34)
4-99
5-20-07 17
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION ITEM
M20M
ITEM DESCRIPTION
LUBRICATION
NO..
8
9
SERVICE AND MAINTENANCE MANUAL
SYMBOL"
Elevator Rudder controls: Control Tube Rod End Bearings
Aileron Control Tube Guide Blocks
11
Aileron Controls: Control Tube Rod End Bellcranks
(HRS)
100
Elevator Rudder Controls: Control Tube Rod End Bearings
10
INTERVAL
’LCI
100
100
Bearings C
100 100
12
Aileron Control Tube Guide Blocks
13
Main Gear Retraction
Z
100
14
Wing
Points Control Tube
8 8
100 100
0
8
100 100 100
Z B Z SZ
100 100 100 100 500 100
8 Z
100 50
’IC~
I: Z X
100 100 100 100 100 100
8
100 100
15
16
100
duide Blbcks
Stabilizer Trim Screw Stops. Indicator Adjustment Point Stabilizer Trim Chain Gear Elevator Rudder Controls: Control Tube Rod End Bearings Bellcranks Guide Blocks
FlaplndicatorCable Electric FlapActuatorGearBox Electric Flap Actuator Ball Screw 17
18
ElectricBoost Gascolator.
Pump
Control Systems: Control Tube Rod End Bearings Control Yoke (Lower Section) Nose Gear Steering Link Rod End Rudder Pedal Cross Shaft Rudder-Aileron Bunwee. Hydraulic Brake Cylind~er Pedal
Brgs
Linkage
19
20
Aileron Control Tube Rod End Outboard Flap Stops
Baggage Compartment Hinges Latches Lock. Seals Hold Open
21
Bearings
Door: Z o.
6 h
arm
Cabin Door:
Hinges
Z
Latches Lock. Seals
Hold-Open
w.
18
6 6 h
Arm
See last page of section for lubrication
5-20-07
100 100 100 100 100
symbol legend. 4-99
100 100 100 100 100
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL ITEM NO..
ITEM DESCRIPTION
22
Engine
M20M
MOONEY AIRCRAFT CORPORATION LUBRICATION SYMBOL"
Instruments Radios. Controls
(HRS)
8 8
Stick, Oil Filler Tube
100 100 100
cP´•
per
Whkels&Eimhes:.
24
INTERVAL
Wheel Bearings. Brake Pressure Plates Anchor Bolts Guide Pins Shock Discs.
Oil changed L´•ycoming SE
every 25 hours or 4 months 480A (or subsequent issue)
h
250 50
W
8
50
8
100
25
Elevator
26
Nose Wheel: Wheel Bearings. Shock Discs.
h 8
250 50
27
Control Surface
Z
100
28
Turbocharger Assy
8 8
100 50
Rudder Control
Stops
Hinges
ExhaustTTIT Probe Air Induction Filter. Starter Drive
8
30
Cowl
8
100.
31
Remote
Flux Valve
8
100
32
Strobelight
Supply (Wing)
8
100
33
ELT
8
100
34
ELT ANTENNA
8
AR
35
SPEEDBRAKE CARTRIDGES
8
200
29
Flap
i
Indicator Potientiometer
Compass Power
(Batteries) (UNDER DORSAL FIN)
See section below for lubrication
50 20
CL.
symbol legend.
LUBRICATION SYMBOL LEGEND SYMBOL
MIL. SPEC. NO.
Z P h
MlL-L-7870 MlL-G-81322 MlL-L-3545 MIL-H-5606
p
.DESCRIPTION Low
Temperature
Oil
(General Purpose)
Grease Grease
(High Temperature) Hydraulic Fluid (Red) Graphite MIL-G-3273 Grease or MlL-G-23827 Powdered Graphite TeRon Spray CTri-Flow) or Equivalent Stick Lubricant (Door Ease or Equivalent)
’ICI u,
Aeroshell Grease NO. 7 (On jackscrew and inside Actuator
0
Bearing Housing) Lubriplate 630AA (10% by Volume Molybdenum Disulfide Mixture Permissible) Seal
6 8 6
Dressing Inspect Tape, Tetrafluoroethylene (MlL-T-2n30) Permacel Tape Corp., New Brunswick, NJ
Q,
MlL-L-22851
Textron-Lycoming Spec. (Ref. Lye. SL L229A) Kerosene 6 Graphite, Lubriplate 777 4-99
5-20-07 19
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
VISCOSITY RECOMMENDATIONS All
Temperature OOF to 700F OOF to 900F Below 100 F (-i20d) The ambient
determining
SAE SAE SAE SAE
A;nbIent,’S.i.
15W-50
SAE 20W-50 or SAE 20W-40 20W-50 ro SAE 15W-30 30 or SAE 20W-30 or
30, SAE 40,
temperatures listed above are only a guide to be used by the owner/mechanic in the proper viscosity oil for your specific operations or flight conditions. Refer to Textron Lycoming Service Instruction No. 1014("). NOTE
Mooney Aircraft are delivered with the proper break-in oil; Mll-L-22851 or SAE-J1899 Spec. This oil 8 filter should be changed, after 25 hours or after oil consumption has stabilized, to oil conforming to TEXTRON-Lycoming Specifications (Reference Lycoming SI 81014("). For M20M aircraft S/N 27-0001 8 ON
Mooney Aircraft Corporation multiviscosity oil in these aircraft.
Textron
Depicts
5-20-07 20
recommends
NOTE recommends that all Textron Lycoming turbocharged equipped broken in and operated with ashless dispersant oil only. (REF. SI #1014
Lycoming
current
or
Subsequent
Revision Letter.
4-99
using
engines
be
OLDWILLWAYNE
CHAPTER
DIMENSIONS AND AREAS
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 6 DIMENSIONS AND AREAS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
PAGE
DATE
1/2BLANK
4-99
6-00-00
3.
4-99
6-00-02..
4.
4-99
6-00-03
5.
4-99
6-00-03
6.
4-99
6-00-03
7.
4-99
6-00-03
3.
4-99
6-Eff/Contents
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT 6-00-00
SUBJECT Dimensions and Areas
PAGE 3
6-00-01.
Aircraft
6-00-02.
Aircraft Dimensions
4
6-00-03.
Aircraft Stations
5
Specifications
3
6-EFF/CONTENTS 1/2BLAN K 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 6-00-00
DIMENSIONS AND AREAS
6-00-01
AIRCRAFT SPECIFICATIONS
ENGINE
TEXTRON-Lycoming TIO-540-AF1A
-AF1B
359.6 Liters 336.9 Liters
95 U.S. Gal. 89 U.S. Gal.
Refer to TCDS for
engine configuration MIL-L-22851
Specification
Oil Grade-Above 300 F(-l Below 300 F(-l"
*X
or
6 270 HP 2575 100 or 100 LL.
RPM. Min. Fuel Octane Fuel Capacity Total Useable
Oil Capacity Minimum for
METRIC/OPT/MISC.
STANDARD
Engine Manufacturer Engine Model No. Cylinders Rated Horsepower
Oil
SERVICE AND MAINTENANCE MANUAL
M20M
C)Ambient air C)Ambient air
SL SL
SAE 40 SAE 30
or
or
15W-50 20W-30 9.5 Liters 5.7 Liters
10 qts. 6 qts.
Flight Oil’Lev~l
Break in oil for Lycoming turbocharged engines is required to be ashless dispersant oil per SI 1014(M (or current revision) corresponding to MIL-L-22851 or SAE J1899.
Max Operational Induction Air Max Continous Operation TIT Normal Operating TIT Oil Pressure Idle, MinimumNormal Operation Max. Allowable (cold oil)
Temperature
1380
C.
F
25 PSI 55-95 PSI 115 PSI
Oil Temperature Max. Allowable Recommended Takeoff-Min Recommended Flight Operation
Cylinder Head Temperature Max. Allowable. Recommended Cruise
2800 F 17500 F 1300 17500
Lycoming
1180_ C
iCrui’se)
100U.F
38-1180.C
(CHT)
Turbocharger Turbocharger Mfg. Type Turbocharger Model
5000 F 5Q00
250 to
F.
2440 F 380 C 100 2440 2600 C 2600
121 to
F
C
Airesearch Exhaust Driven TA0413
PROPELLER
McCauley
PropellerMfg. Type Model Pitch Angle
LOW HIGH Diameter Governor
Constant Speed B3D32C41 7/GS2NRD-7 30 in. 15.1 DEG (-e/-)0.2 DEG. 43 DEG (+/-)0.5 DEG. 75.0 Inches.
190.5
cm
McCauley
4-99
6-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL AIRFRAME WEIGHTS 8 LOADINGS: A. Approximate Empty Weight B. GrossWeight (27-0001 thru (27-0053 thru C. Average Useful Load D. Wing Loading. E. Power Loading Retrofit of these A/C to 3368
MOONEY AIRCRAFT CORPORATION
M20M
27-0052)* 27-TEA)
STANDARD
M ETRI C10 PT/M I SC
2100 Ib. 3200 Ib.* 3368 Ib. 1100 Ib. 18.3 Lbs./Sq.Ft.
953 Kg. 1452 KS.X 1528 Kg. 521.63 Kg.
11.85
Gross
Weight
is allowed when
Ib/hp.
5.4
Kgkp
compliance with SE M20-248 is accomplished.
WINGS:
A. B. C. D. E. F.
Airfoil AtWing Root Airfoil At Wing Tip Mean Aerodynamic
dhord At Wing Sta.94.85
Center-of-Gravity Range. Geometric Twist (DEG) Incidence Angle (DEG)
From Sta 20. to G. Dihedral angle (DEG) H. Aspect Ratio i. Taper Ratio (CS/CT)
632215 641412 61 in. 41.0 to51.0
241
cm
1.5"
2.50 5.50
Wing Tip
7.448 2.271
FUSELAGE: A. Cabin Dimensions:
(1) Height (2) Width (3) Length (4) Cabin Door Width (5) Cabin Door Height. B. Baggage Campartment: (1) MAX.Loading (2) Baggage Space (3) Baggage Door Width (4) Baggage Door Height (5) Hat Rack Capacity C. Landing Gear: (1) Type (2)0peration (3) Wheel Track (4) Wheel Base (5) Tire Size-Nose (6) Tire Size--Main (7) Tire Pressure--Nose (8) Tire Pressure--Main 6-00-02
44.5" 43.5" 126". 29". 35".
113 cm 110.5 cm 315 cm 73.4 cm 88.9 cm
120 \bs 22.6 Cu. Ft. 17" 20.5" 10 Ibs.
0.678 Cu. M. 43.2 cm 52.1 cm 4.5
kg
kg
Tricycle, Retractable Electrical 9’ 2" 6’7 9/16" (6-Ply Rating) 5.00x5 (6-Ply Rating) 6.00x6 49 42
Ibs/sq. Ibs/sq.
279.4 cm 202.08 cm
in. in.
AIRCRAFT DIMENSIONS
DIEIIENSIONS: A. Wing Span B. Fuselage Length C. Tail Height. D. Stabilizer Span AREAS: A. Wing B. Ailerons C. Flaps D. Vertical Fin E. Rudder F. Horizontal Stabili;er G. Elevators
6-00-02
54.4
36’1" 26’9" 8’4" 11’9"
10.998 meters 8.153 meters 2.54 meters 3.581 meters
174.786 so. ft. 11.4 so. ft.
16.24 so. meters 1.06 so. meters 1.66 so. meters 0.73 so. meters 0.52 so. meters 1.90 so. meters 1.21 so. meters
17.9sq.ft. 7.8 so. ft. 6.25 so. ft. 21.42 so. ft.
13.0sq.ft.
4-99
OLDWILLWAYNE 6-00-03
SERVICE AND MAINTENANCE MANUAL
M20M
MOON EY AIRCRAFT CORPORATION AIRCRAFT STATIONS
NOTE The datum line station 0.0 is 13 inches aft of the nose gear trunnion
pivot point.
(Reference Figure
6-2.) --1
(815.3
127~
75’
(190.5
,´•-4´• (254 cn)
cm)
I
bb
I
L,., (27.9 cn)
r
(202.09
cn)
(1099.8
I
(358.1
cn)
PRINCIPAL AIRCRAFT DIMENSIONS 4-99
FIGURE 6-1 6-00-03
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
STA
STA
210,97
147,75
STA 103150
STA
STA
59,25
24,50
STA 193,50
r"Z,,L
I
I
I
I
WING
STATION
RIBS
FIGURE 6-2
STA -5,375 STA
3168
r
I
STA
STA
STA
STA
STA
211,50
176,00
142,00
100,00
53,00
FUSELAGE
FIGURE 6-3 6-00-03
4-99
STATIONS
STA
STA
21180 -5100 SMLMR6-3
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
STA
STA
STA
67,75
42~25
4143
STA 42,25
STA 7010
STA 52,50
STA 25,75
STA 5125
EMPENNAGE
STATIONS SM6-4
EMPENNAGE STATIONS FIGURE 6-4
4-99
6-00-03
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
8-00-09
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
LIFTING AND
SHORING
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 7 LIFTING AND SHORING
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT.
PAGE 1 /2BLAN K
7-Effectivity/Contents
DATE 4-99
7-10-00
3.
4-99
7-10-00
4.
4-99
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT 7-1 0-00
PAGE
SUBJECT
3
Jacking
7-EFF/CONTENTS 1/28LANK 4-99
OLDWILLWAYNE -JACKING
7-1 0-00
When
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
it is necessary to
When
raise the aircraft off the
pressure
ground:
evenly
CAUTION aircraft on
jacks, bleed off all jacks simultaneously and to keep aircraft level as it is lowered.
lowering on
CAUTION CAUTION Individual wheels may be raised without raising the entire aircraft. Wheels not being raised should be checked fore and aft.
Do not raise the aircraft on jacks out of doors when wind velocity is over 10 MPH. Jacks should be on hard surface. 1. Install jack points (2) in tiedown mounting holes outboard of each main gear. 2. Use standard aircraft jacks at both wing hoist points (wing tiedown eyebolt receptacles) outboard of the main gears and at the nose jack point. While holding
in
jack point
place,
raise
jack
to
firmly
contact
NOTE It is not recommended to
jack
Station -5.51.
3. Raise
aircraft, keeping wings
as
nearly
level
as
possible. 4. Secure
safety locks
on
each
tail-tie down
to lift nose wheel
CAUTION Do not leave aircraft on jack for extended periods of time without tailstand in place. The wing jack(s) may bleed down and put excessive loads on the front jack point and tailcone.
point. Nose jack point is located under the cowling at
~uselage
use
fitting during jacking process off ground.
jack.
4-99
7-10-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
7-10-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
LEVELING AND VVEIGHING
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 8 LEVELING AND WEIGHING
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT
8-Effectivity/Contents
PAGE
DATE
1/2BLANK
4-99
8-00-00
3.
4-99
8-00-01
4.
4-99
TABLE OF CONTENTS
CHAPTER SECTION SUBJ ECT 8-00-00 8-00-01
SUBJECT
Leveling Weight
PAGE 3
and Balance
4-99
3
8-EFWCONTENTS 1/2BLANK
OLDWILLWAYNE 3. Ground aircraft and drain fuel tanks per Section
-LEVELING
8-00-00
12-10-02,2.
Place a spirit level on the skin splice or leveling screws above the tailcone access door when levding the aircraft longitudinally. Level the aircraft by increasing or decreasing air pressure in the nose wheel tire. Level aircraft laterally (wingtip to wingtip) by placing level across center seat tracks in front of spar. Front seats must be in the full forward position when weighing. Use leveling screws on tailcone above left side battery access door (See Figure 8-2.).
To
the aircraft select
weigh
Handbook for proper 5.
6´• the three wheels.
7~ Level aircraft as described in Section 8-00-00 and center nose wheel.
Weigh the aircraft. 9´• Find reference point by dropping a plumb-bob from center of nose gear trunnion (retracting pivot axis) to the floor. Mark the point of intersection. 8.
level and draft free work
a
area, then: 1. Check for installation of all equipment as listed in the Weight and Balance Record. 2. Charlie Weight Installation. The aircraft as delivered from the factory has the correct ballast added (if any) to compensate for installed equipment. If addition or deletion of equipment at a future time affect the weight and balance of the aircraft sufficiently to require ballast the proper Charlie Weight Installation shown (Figure 8-1) is to be used.
See Pilot’s
NOTE Handbook for Balance reference data.
Operating
CENTER
of
10. Locate centerline of the main wheel axles in the same manner.
11. Measure the horizontal distance from the reference Measure to main wheel axle center line. horizontal distance from center line of nose wheel axle
point
to center line of main wheel axles.
Weight and F.S.
GRAVIN
tank, (see Pilot’s Operating quantity of unusable fuel). Fill oil to capacity (10 quarts). Position a 2000-pound capacity scale under each of
4. Add unusable fuel to each
WEIGHT AND BALANCE
8-00-01
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
-mm
i
Ila
2500
dP~
(Kg) 8 2400
~105r
23WI
I
I
I
I
I
I
I
all
r~C
505
1
O;IN~EABOVE’
I
1
2200
b
r, sso
i
2100
v~ 8~Lnsr WEIGHT
rn
REOVIREO
2000
~900
1
I~Jg
I ‘3i~
137
~ENTER
OF
1
GRA;I;Y
I
I
I
Airpone empty ~eighs 23441 with CG. ot 42.15... F;om chart, this airplane requires -505 Charlie Weight Install. Moment. For license, calculate new weight. C.G. 98810 42.15 2344 X Aircraft as weighed 3981 19 X 209.5 -505 Charlie Weight
EX1IMPLE:
2363#
Empry Weight
Licensed
Empty Weight C.G. Location
B
503
1:
102791
Licensed
i
8" ~j
i5.-inched:
-501
43.5~’
CHARLIE WEIGHT INSTALLATION FIGURE 8-1
4-99
8-00-00
OLDWILLWAYNE weights and LM/R -13 -LM
12. Record
LC/G a.
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL measurements and
compute the basic weight and CG
as
follows:
CG Forward of Main Wheels
Weight
IN.
X
LBS
Total
Distance Between
Nose
Main
1N.
LBS.
i
Weight
CG Forward of
of
Main Wheels
Aircraft
Nose Wheel
Axel Centers
b. CG Aft of Datum
(Lhn)
ONT)
(LM/N)
OIVN)
(Station O)
Distance from center
Nose GEar
Center of Main Wheel
Trunnion to
(Horizontal) (LM/R)
Datum
Axles
CG
Result of
Distance from
Nose Gear Trunnion to
IN.
IN.
131N.
IN.
Above
computation (a.)
(FUS STA)
Distance Aft of Datum
(Emptr Weight CG) (LC/G)
(LM)
(CONSTANT)
NOTE:
REF,POINT (NOSE GEAR TRUNNION STA, -13>
REFERENCE DATUM(STA,O>
I
LEVEL REF, (LEVELING SCREWS>
1~
I
I MEASUREMENTS
C/ /r
LM/R
Lm/n
Nose Jack Point Main Jack Point
INCHES/CM
Wr WI
Wn
LM/N INCHES/CM
Sta. -5.866 Sta. 56.658
WEIGHT AND BALANCE DIAGRAM FIGURE 8-2
8-00-01
4-99
OLDWILLWAYNE
CHAPTER
TOVVING AND TAXIING
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 9 TOWING AND TAXIING
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT.
PAGE
9-Effectivity/Contents
DATE
1/2BLAN K
4-99
9-00-00
3.
4-99
9-30-00
4.
4-99
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT 9-00-00
9-1 0-00. 9-20-00.
9-30-00.
SUBJECT Ground
Handling Towing Taxiing Emergency Procedures
4-99
PAGE 3
3 3 3
9EFF/CONTENIS 1/2BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 9-00-00 81 0-00
GROUND HANDLING
4. Check operation of gym instruments and tum coordinator during turns.
-TOWING
5. Check engine instruments for sluggish engine control movements.
Use a towbar for moving the aircraft. The towbar attaches to the nose gear crossbar. One man can move the aircraft providing the ground surface is relatively smooth and the tires are properly inflated. When no towbar is available, or when assistance in moving the aircraft is required, push by hand: (1) on the wing leading edges, (2) on the inboard portion of propeller blades adjacent to the propeller hub. Towing by tractor or other powered equipment is NOT RECOMMENDED.
1.
Maximum allowable damage to nose gear assembly is 1/32 inch dent.
3. While
taxiing, gear steering.
few
feet
and
check
make shallow tums to test
During Starting. cranking engine
with starter.
8. Set mixture control at IDLE, CUTOFF. C. Turn fuel selector handle to OFF. D.
Open
throttle to FULL.
E. Turn Master switch OFF F. Push cabin heat control to OFF. G. Close cowl H. If fire is not
flaps. extinguished, proceed
as
follows:
(1) Turn electrical switches OFF. (2) Discharge fire extinguisher into engine compartment through nose cowl openings and through cowlflap openings. (3) Call for fire-fighting equipment. 2. Fuselage or Wheel Well Fire. In case of fire in wheel well (or in the cabin or fuselage area), turn all fuel, electrical, and ignition controls to the OFF position before evacuating the aircraft to extinguish the flames. 3. Electrical Fire. Circuit breakers (or circuit-breaker switches), that automatically interrupt the Row of power
leg
Before attempting to warmup or taxi the aircraft, ground personnel should be checked out by quaiified pilots or other responsible personnel, 1. Start and warmup engine. (Refer to POH/AFM Manual.) a
Fire
A. Continue
WARMUP AND TAXIING
2. Taxi forward effectiveness.
Engine
response to
EMERGENCY PROCEDURES
930-00
CAUTION Exercise care not to turn the nose wheel past its normal swivel angle of 11" left or 130 tight of center. Exceeding the turn limits shown on the turn indicator may cause structural damage.
9-20-00
SERVICE AND MAINTENANCE MANUAL
M20M
brake
when an overload or short circuit occurs, protect all electrical circuits (except the ignition-starter circuits). In the event of an electrical fire, immediately tum OFF the Master and Altemator Field switches. Make sure that only a fire extinguisher approved for electrical fires is used.
nose
4-99
9-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
9-30-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
PARKING, MOORING, STO RAG E, RTN TO SVC.
OLDWILLWAYNE M20M
SERVICE AND MAINTENANCE MANUAL
MOONEYAIRCRAFT CORPORATION
CHAPTER 10 PARKING AND MOORING
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION PAGE
SUBJECT.
1/2BLANK
l0-Effectivi~sllContents
DATE 4-99
10-00-00.
3.
4-99
10-20-00.
4.
4-99
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT 10-00-00 10-1 0-00
10-10-01
PAGE 3
General
Parking Storage (Flyable)
3
3
10-10-02
Storage (Prolonged)
3
10-10-03
Return to Service
3
10-20-00
3
Mooring
1 O-EFF/CONTENTS
1/2BLANK 4
-99
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
CAUTION If weight is not removed from tires, rotate wheels to a new position at least once each 30 days to prevent flat-spotting the tires.
-GENERAL
10-00-00
parking brakes are set by applying the brakes and pulling outon the parking brake knob. Release the brakes by pushing in on the parking brake control
The
knob.
There is no need to depress the brake pedals to relieve the pressure in the lines during release of parking brake control. There are three tiedown points on the aircraft, one on each wing outboard of main gear (tiedown rings are to be threaded into built in receptacles) and the tail skid/tiedown fitting on the aft end of the tailcone.
If the aircraft has been stored for an extended period of time, it is advisable to perform a 50-hour periodic inspection after completion of the following preliminary
steps: 1. Remove blocks from wheels. Check tire inflation.
STORAGE
spark plugs. and
noules
14. Check fuel tank vents for obstruction, and drain sumps to remove moisture and sediment.
Complete
50-hour and
preffight inspections.
Service Lycomong appropriate Bulletins/lnformation for servicing of the engine. See
16.
10-20-00
When
on
paragraph
2. Place chocks fore and aft of each main wheel.
pitot head, engine
3. Drive stakes in ground approximately three feet outboard of each main gear and to either side of tailskid.
all exterior surfaces
4. Install tiedown rings in wing receptacles outboard of each main gear. Tie a 600-pound tensile strength rope to each wing tiedown ring and anchor to ground stake. Allow a little slack in each tiedown rope.
(PROLONGED)
10-20-00
for
5. Tie the center of a rope to tail skid tiedown ring and anchor rope ends to ground stakes at either side of tail.
mooring
6. For additional gear and anchor to
openings.
battery, charge fully,
and store in
a
weight from the tires,
security, attach
a
rope to the
nose
ground stake. 7. Lock controls by looping right front seat safety through the control wheel and drawing belt snug.
cool
place. remove
mooring
-A1100RING
the aircraft out of doors:
1´• Head aircraft into the wind.
If the aircraft is to be stored for an extended period of time, the following steps are recommended for protection:
4. Raise aircraft to block up the wheels.
air-inlet filter.
CUTOFF
protective openings, static ports, etc. 3. Maintain a good wax finish after 90 days.
all
ignition
engine
oil.
grade of lubricating
Check and clean fuel injector screens. Drain oil from fuel injector.
15.
covers over
or cover
temperature bypass valve.
13.
cowl
Tape
screens.
harness.
12. Clean and regap
6. Keep fuel tanks filled at least one-half full to minimize moisture condensation. Keep batteries fully charged.
2.
engine
11. Check
5. Rotate propeller 6 revolutions every seven days; STOP propeller 45 to 90 degrees from original position.
3. Remove
and pressure
sump with proper
10. Clean and reinstall
3. Throttle....................CLOSED
to
Replace engine oil filter. Clean engine oil suction
9. Fill
Magneto switches..........OfF
Refer 1. instructions.
openings.
waming placards (if any).
3. Clean and check oil
instructions.
10-10-02
from
7. Clean and check oil pressure relief valve.
requires
7. Install
covers
6.
STORAGE
4. Mixture...........lDLE
battery.
3. Remove tape and
5.
(FLYABLE) adequate mooring and The facilities. iollowing measures are recommended for keeping serviceable and ready-to-fly. Refer to 1. paragraph 10-20-00 for mooring 2.
2´• Check and install
4. Remove
CAUTION Do not set parking brakes when they are overheated or when cold weather could freeze moisture and slush accumulation in the brake mechanism. Do not set parking brakes when aircraft is tied down. For maximum protection, hangar the aircraft during severe weather and high winds.
storage
preservation procedures make
if
RETURNING TO SERVICE
10-10-03
PARKING
lo-lo-ol
Service
Lycoming
appropriate
waming placards e"gine inoperable.
When parking the aircraft, place wheel chocks fore and aft of the main wheels. The parking brakes may be used for short-duration parking.
Outdoor tiedown
See
5.
Bulletin/information for engine preservation. Attach
NOTE
10-10-00
SERVICE AND MAINTENANCE MANUAL
M20M
and
4-99
a
belt
10-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
10-20-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
PLACARDS AND MAR KI NGS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 11
PLACARDS AND MARKINGS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION PAGE
SUBJECT.
DATE
1/2BLANK
4-99
11-00-00
3.
4-99
211-20/30-00
4.
4-99
Il-EffectivitylContents
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT 11-00-00 11-10-00
11-20/30-00
PAGE 3
General Exterior Paint.
3
Placards, Exterior/interior
3
Markings
11-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
11-00-00
FAA
GENERAL
required placards
and
markings.
NOTE All
M20M
placards should be inspected for proper location, readability and security during maintenance actions. When an airplane has been painted, inspect all placards to assure that they are not obscured by paint.
11-10-00
The exterior aircraft are
SERVICE AND MAINTENANCE MANUAL
MARKINGS- UCTERIOR PAINT
paint schemes for the various model year depicted in the M20M Illustrated Parts
Catalog. 11-20/30-M)
-PLACARDS, UCTERIOR/INTERIOR
All required placards and their locations, both interior and exterior, are listed in SECTION II of the FAA Approved Flight Manual and Pilot’s Operating Handbook. All placards are listed in the M20M 11-20-00 Parts Catalog, SECTION Illustrated 11-30-00.
4-99
11-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
11-20/30-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
SERVICING
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 12 SERVICING
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT.
PAGE
DATE
1/2BLANK
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12-00-00.
3.
4-99
12-10-04.
4.
4-99
12-20-02.
5.
4-99
12-20-06.
6.
4-99
12-Eff/Contents.
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT 12-00-00
12-00-01 12-10-00
SUBJECT
Servicing Servicing Intervals Replenishing
PAGE 3 3 3
12-10-01
Fuel Tanks
3
12-1 0-02
Fuel Drains
3
12-1 0-03
EngineOil Oxygen System. Scheduled Servicing
3
12-10-04
12-20-00
4 4
12-20-01
Induction Air Filter
4
12-20-02
Battery
5
12-20-03
Tires
12-20-04
Brake Reservoir.
5
12-20-05
Hydraulic Brake.
5
12-20-06
Cleaning
6
Wheels
5
12-EFF/CONTENTS 1/28LANK 4-99
MOONEY AIRCRAFT CORPORATION 12-00-00
OLDWILLWAYNE M20M
-SERVICING
SERVICE AND MAINTENANCE MANUAL
WARNING cold weather operation, frequently check fuel gascolator drain for ice formation by repeating procedures 1., A, B and C above.
During
12-00-01
SERVICING INTERVALS
The specified intervals (refer to Chapter 5) are considered adequate to meet average requirements under normal operating conditions. It is advisable, however, to shorten service and maintenance intervals when operating under abnormal environmental conditions, such as extreme temperature ranges, dusty
atmospheric conditions, high humidity and moisture, unimproved airport facilities, or unusual operating requirements. 12-1 0-00
12-10-01
-REPLENISHING FUEL TANKS
fuel tanks at least half filled to minimize condensation and moisture accumulation in tanks. (Fuel capacity is given in Chapter 6.)
Keep
NOTE If conditions conducive to fuel system icing exist Isopropyl Alcohol may be added to fuel tanks. It is extremely important to thoroughly BLEND the isopropyl alcohol in with the fuel supply in quantities not to exceed 1% of the total, by volume. 2. Defueling. Fuel tanks may be drained by pumping fuel out with the electric boost pump, siphoning fuel through the filler ports, or removing tank quick drain valves.
WARNING Allow no smoking or open game within 50 feet of the defueling area. Ground the aircraft and fuel container during all defueling operations. A. To defuel the aircraft
WARNING Ground the aircraft and fuel service vehicle. permit no smoking or open flame within 50 feet of aircraft or vehicle.
using
boost pump:
(1) Disconnect fuel line from electric boost pump outlet at the fitting forward of the firewall.
(2) Connect to output fitting a Rexible line that will receptacle. (3) Turn fuel selector valve to the tank to be
reach fuel
WARNING Each fuel tank is vented to the atmosphere at its outboard aft corner; vent openings are on the lower wing surface. Check vents for obstruction before each flight. 12-10-02
drained, and
remove
filler cap from fuel filler port.
(4) Turn on boost pump until tank Repeat steps (3) and (4) to drain other tank. (5) To completely drain fuel system wing sumps and the fuel gascolatorvalve
FUEL DRAINS
fuel stops
A fuel-drain valve is located in the aft inboard comer of each tank to provide for drainage of moisture and sediment. Use the small plastic cup furnished with the Ryaway kit to drain the fuel sumps. Drain wing tank sumps and gascolator before the first Right of the day and after each fuel service to inspect for water and/or contamination. Continue draining until free of water or contamination.
is
empty.
also drain sump until
running.
NOTE When defueling using removable tank quick drains it is only necessary to remove the drains and to operate the gascolator drain. 12-10-03
ENGINE OIL
Check
engine oil level after engine has been stopped long enough for oil to drain back into sump. The oil filler cap access door is located in the top cowling. Any lubricating oils conforming to (MlL-L-22851 or SAE
WARNING After servicing the aircraft with fuel, wait at least five minutes for moisture and sediment to settle before draining and checking both the fuel tank sumps and the fuel selector valve drain.
J1899) or as approved by TUCTRON-Lycoming are acceptable for use after break-in period. Approved products and engine oil viscosity requirements are shown in CHAPTER 5-20-07.
1. Fuel Gascolator Drain. The fuel gascolator is at the lowest point in the fuel system and has a drain valve operated by a control on the floor in the cabin. To drain the fuel gascolator:
A. Switch fuel selector valve handle to L and fuel drain valve control ring for 10 seconds.
pull
B. Switch fuel selector valve handle to R and fuel drain valve control ring for 10 seconds.
pull
C. After draining, be sure fuel drain valve control is retumed to the closed position and the valve is not leaking outside the aircraft.
4-99
12-00-00
OLDWILLWAYNE delivered
CAUTION The terms
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
"detergent", "additive", "ashless
from
(MlL-L-22851
and "compounded" used in this manual are intended to refer to a class of aviation engine lubricating oils to which certain substances have been added to improve them for aircraft use. These terms do not refer to such materials commonly known as "top cylinder lubricant", "dopes" and "carbon remover" which are sometimes added to fuel or oil. These products may damage the engine and therefore, should not be used. Under no circumstances should automotive oil be used, since such oils could cause engine damage,
dispersant"
or
Mooney with SAE J1899).
break-in
proper
oil
OIL and FILTER CHANGING RECOMMENDATIONS The oil and filter should be changed at 25 hour flight operation intervals or every four months (per Lycoming SI #480A). Use TEXTRON-Lycoming filter or approved
equivalent. Depicts current
or
Revision Letter.
subsequent
OXYGEN SYSTEM
12-10-04
(OPTIONAL)
when fully charged, contains approximately 115 cubic feet of aviators breathing oxygen (Specifications No. MlL-O-27210). Recharging of this oxygen cylinder should be accomplished by using the appropriate Scott recharging fittings to the pressure shown on (Figure 12-1), Pressure vs Temperature Table.
The oxygen
Oil Recommendations for New-Engine or Newly Overhauled Engine Break-IN. New or newly overhauled engines should be operated and broken in on aviation grade ashless dispersant oil [ref. Lycoming SI 1014 n. Breakin oil and filter should be changed after thefirst 25 hours of operation.. The aircraft is
cylinder,
WARNING other lubricants in contact with oxygen create a serious fire hazard, and such contact must be avoided when handling oxygen
Oil, grease
or
equipment.
FI LLING
AMBIENT
FI LLING
AMBIENT
TEMPERATURE.
TEMPERATUREPRESSURE
PRESSURE
DEGREES F
PSIG.
DEGREES F
PSIG
0.
1650
50
1875
10
1700
60
1925
20
1725
70
1975
30
1775
80
2000
40
1825
90
2050
OXYGEN PRESSURE VS TEMPERATURE TABLE FIGURE 12-1 NOTE The oxygen cylinder should not be run down to less than 100 p.s.i. Below this pressure atmospheric contamination of the cylinder may occur, requiring valve removal and cylinder cleaning and inspection at an FAA approved repair stations.
NOTE Refer to CHAPTER 35-00-00 for pressure check.
periodic
time
disconnected should be threads
fittings
are
SCHEDULED SERVICING
12-20-01
INDUCTION AIR FILTER
The importance of keeping the induction air filter clean cannot be overemphasized. A clean filter promotes fuel economy and longer engine life. The dry-type filter can usually be washed six to eight times within 500 hours or one year before replacement is necessary.
bottle
To clean the dry-type induction air filter: 1. Direct a jet of air from inside of filter out. Cover entire filter area with air jet.
the oxygen with treated system the tetrafluoroethylene tape (M IL-T-17720). Prior to reconnection the system should be checked for leaks with leak testing compound (Mll-L-25567). If no leaks are found wipe the system clean and dry.
Any
12-20-00
on
CAUTION Do not
use a
compressor unit with
pressure greater than 100
a
noule
p.s.i.
Inspect for damage or ruptures by holding before a or by holding light bulb inside filter. If damage is evident, replace filter with new one. 2.
light,
12-10-04
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION NOTE If filter shows an accumulation of carbon, soot, or oil, continue with cleaning steps 3 through 5.
Use only hydraulic fluid (red), per specification MIL-H-5606. Do not fill reservoir above two inches below filler port.
3. Soak filter in nonsudsing detergent for 15 minutes; then agitate filter back and forth for two to five minutes to free filter element of deposits. 4. Rinse filter element with until rinse water is clean, 5. 180
Dry filter thoroughly. Do deg. F. for filter drying.
a
stream of clean water
not
use
light
6. Check alternate air door for proper
or
air above
operation and
sealing, 7. Reinstall filter in aircraft
sealing
and
sure
of proper
security.
batteries
with
distilled
water
to
maintain
electrolyte above plates. After adding water in freezing weather, charge battery long enough to mix electrolyte and water. Keep battery electrolyte above a specific gravity of 1.225 to avoid freezing. To service the battery(ies): 1. Remove battery caps. Check electrolyte and service battery as required. Battery
CAUTION gases may be
explosive.
2. Inspect battery mounting area for corrosion and spilled electrolyte. To clean cables, terminals, mounting area and battery case, use a solution of
bicarbonate of soda and clean water to neutralize corrosion and spilled electrolyte. CAUTION When cleaning, do not allow bicarbonate of soda to enter battery cells permanent damage will result if soda mixes with electrolyte, 3. Rinse battery with clean water, and with a dry cloth.
wipe
SINGLE BRAKE SYSTEM
(PILOTS SIDE ONLY)
2. Immerse open end of drain line into Ruid container or catch container.
a
hydraulic
3´• Attach pressurized hydraulic Ruid service unit to wheel cylinder bleeder valve and open valve. Hydraulic service unit should be free of air prior to servicing aircraft system. 4. Feed fluid from service unit into brake system. Check for air bubbles at end of drain line immersed in fluid.
5. When Ruid is Rowing, slowly depress pilot’s brake pedal by hand and slowly release. Repeat three (3) to four (4) times. 6. Allow fluid to flow until clear of air bubbles.
If shume valve is installed in
single
brake system
7. Loosen pluglcap on shuttle valve (port is plugged if no cc-pilot’s brake system is installed). Allow air bubbles to purge from back side of shuttle valve; indicated by clear Ruid Rowing from shuttle valve into catch container.
cylinder
bleeder valve and
remove
brake system
IF DUAL BRAKES AND SHUTTLE VALVE ARE INSTALLED -(See steps 1 8 2, Single Brake System 1. While pressurized hydraulic fluid service unit is still attached to either wheel cylinder bleeder valve.
Inspect tires for wear, cuts, and bruises.
2. Inspect valve stems for evidence of tire slippage or pulling. 3. Inspect wheels for damage. 4. Inspect wheel bearings for condition and
2. Loosen cc-pilot’s brake line at shuttle valve. Provide another catch container.
3. Resbict outflow fnrm container.
lubrication. 12-20-04
For best results, use a diaphram type hydraulic pressure service unit (pressure pot) to back bleed the system through the wheel cylinder bleeder valves.
9. To bleed opposite brake, (single only) repeat steps 3 through 8.
TIRES AND WHEELS
Keep the tires at recommended air pressure. (Refer to CHAPTER 6-00-01. 1.
hydraulic system servicing.
NOTE Brake pedal may need to be pulled back in order for fluid to bleed back into reservoir.
etc.
12-20-03
(Bleeding)
CAUTION FIuid in the wheel cylinders may be under high pressure due to expansion. Therefore, be sure parking brakes are released prior to beginning
8´• Close wheel service line.
clean
4. To retard corrosion, coat terminals with petroleum jelly after cleaning and tightening them. 5. Inspect battery vent lines for obstruction, line
kinks,
HYDRAULIC BRAKES
12-20-05
1. Remove hydraulic Ruid reservoir filler plug, and install a suitable fitting for attaching a flexible drain line.
BATTERIES
12-20-02
Service
making
SERVICE AND MAINTENANCE MANUAL
M20M
reservoir dtai~ hibe to catch
4. Allow fitting to remain loose until fluid is clear of air bubbles as it drains from shuttle valve fitting into catch
BRAKE RESERVOIR
Co"tainer.
reservoir for proper Ruid level. See~CHAPTER 12-20-05 for location. See CHAPTER 5-20-07 for proper fluid.
Frequently inspect brake
5. When clear, tighten cc-pilot line fitting and restriction from reservoir out flow tube.
remove
6. Stroke cc-pilot’s brake pedal several times and allow any purged air to exit through reservoir.
CAUTION Do not fill reservoir while parking brake is set. 4-99
12-20-02
OLDWILLWAYNE 7. Shut off bleeder valve at wheel fluid pressure unit. 8. To bleed opposite repeat steps 2 through 8.
cylinder;
2.
remove
brake, (dual brake system)
to
pedals
are
depressed, -CLEANING
12-20-06
washing
cover
brake
B. Flush away loose dirt and mud.
C. Wash exterior with a mild aircraft detergent in cool water, and a soft cleaning cloth or chamois. Rinse away soap film.
CAUTION called "mild" household detergents to wash aircraft exterior. Such detergents may damage finish and corrode aluminum components,
with
an
NOTE Minor scratches or abrasions may be polished out by using plexiglas resurfacing kits, ie, Micro-Mesh, available from aircraft accessory 3. ENGINE COMPARTMENT Accumulation of dirt and oil within the engine compartment creates a fire hazard and hampers inspection.
A.
heavy oxidation film,
use a
pre-wax
E. Apply an exterior-finish wax recommended for protection of urethane enamel. Apply a heavy coating of wax to leading edges of wings, empennage, and nose section to reduce drag and abrasion.
down a
engine
cowling
and
Dry engine cowling washing.
and engine
compartment
4. CABIN INTERIOR Use normal household
practices for
engine
nonflammabie solvent.
B.
after
routine interior
cleaning
care.
A. Frequently vacuum seats, rugs, upholstery panels, and headliners to remove surface dust and dirt. B. Clean interior components with cleaners shown below. Use soft cloth to apply. Dry with soft, dry cloth.
CAUTION
apply wax or use pre-wax cleaners during initialpaint curing period. Use only mild aircraft detergent and cool water when washing exterior during the first 90 days after repainting.
Wash
compartment using
Do not
(1) Leather
Leather cleaner
(2) Vinyl Vinyl cleaner. Wool 8 Leather Izit (new interior (3) Woolite H20 to 1 part (3 parts window/upper sides) Woolite) (4) Carpet Carpet cleaner (See CAUTION below) CAUTION
apply household cleaners to interior furnishings. Do not use alcohol or strong solvents on interior plastics. When using commercial cleaning and finishing compounds, carefully follow the manufacturer’s instructions. Never
CAUTION
hydraulic fluid, or other fluid containing dye is spilled on painted surfaces, remove it at once to prevent staining. Flush away spilled battery electrolyte immediately When fuel,
Never saturate fabrics with solution which could damage the backing and padding
with water. Treat the area with bicarbonate of soda solution followed by thorough washing with a mild aircraft detergent solution.
12-20-06
windshields
Inspect door seals for damage that could cause leakage. E. Inspect cabin and baggage door mechanism for proper working order.
use so
remove
or craze
suppliers. aircraft exterior,
discs, pitot head, and static ports.
D. To cleaner,
soft cloth saturated
D.
1. UCTERIOR
Do not
a
use
C. Clean windows and antistatic plexiglas cleaner.
Cleanliness is a major prerequisite to adequate inspection and maintenance of an aircraft. Cleanliness enhances the appearance of an aircraft and reduces the probability of corrosion. A. Before
oil with
windshields. Such solvents will soften the plexiglas surface.
Inspect
4. Depress brake pedals to check for sponginess. Resistance should be solid and even when brake
or
CAUTION
plug.
brake linings for excessive wear and proper installation. Refer to CHAPTER 32-40-04 for Brake Removal and Inspection Procedures. 3.
prior
gasoline, benezene, carbon tetrachloride, acetone, fire extinguisher fluid, de-icer fluid, lacquer thinner, or household window cleaning sprays on windows or Never
port.
2. Reinstall filler
A. Flush windshield and windows with water Never wipe while dry.
wiping.
TO
RESERVOIR
1. Lower fluid level in reservoir to two inches below
filler
WINDSHIELDS, WINDOWS AND DOORS
B. Remove grease in kerosene.
9. Remove drain line from reservoir.
REPLENISH HYDRAULIC OPERATING LEVEL
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
materials. To minimize wetting of carpets, keep foam as dry as possible and rub in circles. Use a vacuum cleaner to remove foam. Do not allow carpetsto remain damp; dry them thoroughly.
4-99
OLDWILLWAYNE
C H A PT E R
STANDARD PRACTICES
(AIRFRAME)
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 20 STANDARD PRACTICES -AIRFRAME
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SU&IECT
PAGE
DATE
20-Effectivity/Contents
1/2BLANK
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20-00-00.
3.
4-99
20-00-01.
4.
4-99
20-00-02.
5.
4-99
20-00-02.
6.
4-99
20-00-03
7.
4-99
20-00-03.
8.
4-99
TABLE OF CONTENTS
CHAPTER SECTION
SU&IECT 20-00-00
SUBJECT
General
PAGE 3
20-00-01
Skin
3
20-00-02
Corrosion Detection and Prevention.
5
20-00-03
Painting
7
20-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 20-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
-GENERAL
and Alteration and Sub Parts A, D and E of FAR 65, Certification. Advisory Circular 43.13-1( Outlines inspection and repair practices acceptable to the F.A.A. Administrator.
Rebuilding
This chapter of the manual discusses treatment of metal surfaces for corrosion control and the Identiiicat[on of skin panels for replacement purposes, Those who inspect or repair aircraft should consult FAR 43, Maintenance, Preventive Maintenance,
SKIN SPECIFICATIONS
20-00-01
STA
STA
STA
STA
SIA
~10.97
!47,75
103.50
59.~5
~4.50
STA
193,50
5
1
r3
r4
"7
18
--1
ii
i
I 15
19
i
13
1~ 17 -J
11
j
10
16 ’9
WII\IG
SKIN
PAI\IELS SM-mrs20-:
INDEX NO.
SKIN THICKNESS
MATERIAL
INDEX NO.
SKIN THICKNESS
1. 2.
0.063 0.050 0.040 0.040 0.025 0.025 0.032 0.040 0.025 0.025 0.025
2024T-3CLAD 2024T-3ClAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024 T-3 CLAD 2024 T-3 CLAD 2024 T-3 CLAD
12. 13. 14. 15. 16. 17. 18. 19.
0.025(c) 0.020(a).
3. 4.
5. 6. 7.
8. 9. 10. 11.
MATERIAL
2024 T-3 CLAD 2024 T-3 CLAD 2024 T-3 CLAD 0.032 2024 T-3 CLAD 0.040(b). 2024 T-3 CLAD 0.040(d). 2024 T-3 CLAD 0.016(a). 2024 T-3 CLAD 0.050(b). Polyester Glass-Fiber Reinforced
(a) Same thickness on top and bottom. (b) Top of wing only. (c) Top aft flap skin that section). (d) Top inboard flap skin. WING SKIN PANELS FIGURE 20 -1
4-99
20-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
STA 14
6
7
rl
2~
87\
6~
4-\
-5,375
3
STA 3,68
O
12
I
to
I
STA
211,50
I
STA
I
I
I
STA 100,00
STA
/142,00
176,00
1
1--’
11
9
I
1 L
6
5
-1
L
I
STA
STA
STA
53,00
21,80
-5,00
L
5
FUSELAGE SKIN PANELS
SMM20-2
INDEX NO.
SKIN THICKNESS
MATERIAL
INDEX NO.
SKIN THICKNESS
1. 2. 3. 4. 5.
0.025
10. 11. 12. 13. 14.
0.032 0.032 0.032
6.
0.020 0.025
2024T-3CLAD 2024 -0 CLAD 2024T-4CLAD 2024T-3CLAD 2024T-3CLAD 2024 T-3 CLAD 2024 T-3 CLAD 2024 -0 CLAD 2024 T-3 CLAD
7. 3.
9.
0.040(d). 0.025(c)(b) 0.025
0.025(b). 0.032(d)(e) 0.025
(a) (b) (c) (d) (e)
4-99
MATERIAL
T-3 CLAD T-3 CLAD T-3 CLAD T-3 CLAD 0.025(a). Polyester Glass-Fiber Reinforced 2024 2024 2024 2024
Left side only. Right side only. 0.032 can be used. Heat treated to T-42 condition after Shell.
FUSELAGE SKIN PANELS FIGURE 20 -2
20-00-01
1
I
13
I
forming.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
4
5
STA 42,25
1 3--1
SERVICE AND MAINTENANCE MANUAL
M20M
1 7
STA 42,25
9
~V
STA 25~75
6’
6
13
EMPENNAGE
INDEX NO.
SKIN THICKNESS
MATERIAL
1. 2. 3. 4. 5. 6. 7.
0.025
2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024T-3CLAD 2024 T-3 CLAD
0.025 0.025 0.025 0.025 0.020 0.025
SKIN
NO.
PANELS
INDEX THICKNESS
SKIN
MATERIAL
8. 9. 10. 11. 12. 13.
0.025 0.020 0.032
2024 T-3 CLAD 2024 T-3 CLAD 2024 T-3 CLAD
(a)
Polyester Glass-Fiber Reinforced. 0.020
0.025(a).
2024 T-3 CLAD 2024 T-3 CLAD
Heat treated to T-42 condition.
EMPENNAGE SKIN PANELS FIGURE 20 -3 20-00-02
Chemical Co., Inc., 6700 Lookout Road, P.O. Box 32101, San Antonio, TX. 78216) should be used. Paint
CORROSION DETECTION PREVENTION
removing substances left in metal crevices will cause further corrosion. Turco 2662(3 or 3002 will remove corrosion from aluminum and treat the metal surface in one application. This paragraph discusses corrosion types and their prevention along with suggested for zinc chmmating internal aimame
Most metallic fabrication materials are susceptible to corrosion. Corrosion may occur on aircraft in any climate, but it will be a problem more often in climates where the aircraft is exposed to salt air or high humidity, or where there are industrial contaminants in the atmosphere. The aircraft should be inspected frequentlyto detect and correct corrosion before serious damage occurs. form of corrosion should be removed at once. If it is necessary to remove paint, only an approved aircraft
Any
paint
remover
such
as
Eldorado PR-3400, (Eldorado 4-99
20-00-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL of Corrosion
Types
1.
Aluminum
Corrosion normally appears in one or more of four forms. Each type of corrosion can be precluded or controlled by a preventative maintenance program. Chemical corrosion normally occurs where battery acid or exhaust gases come in contact with metal surfaces. A few simple precautions will prevent chemical corrosion. Be
sure
battery
C. Use only liquid (non-alkaline) soap to wash the exterior airframe. Cover vent scoops when the aircraft is being washed. Rinse aircraft exterior after exposure to salt air or industrial fallout.
vent is free from obstruction
(2) Repaint all scratches and worn spots found in painted with acid-resistant paint. (3) If acid is spilled on metal surfaces, flush entire
D. Since moisture promotes corrosion, thoroughly and frequently inspect areas where water is apt to collect. Use an air hose to drive water from crevices before wiping the exterior surface dry after washdown.
with sodium bicarbonate and water. The solution should be rinsed away at once and the area dried by driving all water from crevices with an air hose before wiping surface dty with a clean cloth. area
clean exhaust gas
(4) Frequently
cleaning.
paint layer.
at all times.
areas
Carefully examine seams, lap joints, and crevices where moisture or dirt can collect. Areas exposed to exhaust gases require frequent inspection and B. Corrosion may attack metal even though the surface is painted. Inspect painted areas for a blistered or scaly appearance that warns of corrosion below the
A. ChemicalCorrosion.
(1)
MOON EY AIRCRAFT CORPORATION
M20M
E.
Hangar the
aircraft when not in
i". If battery acid is spilled on any part of the aircraft, immediately wash the area with a solution of
deposits from
sodium bicarbonate in water. Rinse with water and with clean towels.
metal surfaces. B. Local-Cell Corrosion.
be fogged into skin areas. It is recommeded that electrical connections and electrical components be protected (sealed off)
bare
FAA
forming
under rivet heads,
3´• Zinc
longeron
area
Chromating/Corrosion
Resistant Primer.
as
on
product (usually white or aluminum) from the corroded
down to sound metal.
(1) If the base metal is aluminum, clean off the cO"OSio" product by scrubbing with aluminum wool or a nonmetallic scounng pad such as the nylon pads made by the Carborundum Company, P.O. Box 277, Niagara Falls, N.Y. 14302.
reassembling.
(2) If the base metal is steel, remove the corrosion product with emery cloth (320 grit or finer) or steelwool.
metals,
(3) If the corrosion is too advanced to remove the light mechanical cleaning methods of (1) and refer to Advisory Circulars 43.13-1() and/or 43-4 alternate methods of cleanup and repair.
epoxy-polymide primer before reassembling. 2. Corrosion Prevention
A. Thoroughly examine unpainted metal surfaces inspections, and check corrosion when found.
20-00-02
NOTE Circular 43-4 addresses corrosion problems.
A. Remove all corrosion
such stainless steel and as aluminum, in contact with each other sometimes develop galvanic corrosions. To remedy this form of corosion, separate the parts, remove the corrosion, and paint both surfaces with Zinc Chromate or
at
wing
Advisory
grey-white powder
D. Galvanic Corrosion Dissimilar
can
When corrosion is detected, it should be treated follows:
along faying
contact surfaces and other similar areas is called concentration cell corrosion. Detection requires close inspection. Rivets must be removed and skin laps must be separated to remove concentration cell corrosion. Use aluminum wool soaked in solvent such as methyl-ethyl-ketone to scour corrosion deposits from the surface before painting both faying surfaces with zinc chromate primer
and
or
Zinc chromating or Corrosion Resistant Priming of internal airframe surfaces will not eliminate the necessity for periodic inspections. The most likely areas for corrosion to begin are in hidden crevices such as skin laps, under rivet heads or any opening where moisture can collect. Periodic inspection of these areas is most important so that any corrosion which may be present can be detected and treated in its very earliest stages.
C. Concentration Cell Corrosion at skin to
equivalent
during fogging.
7075 are vulnerable to this type of attack. Aluminum extrusions may contain nonuniform areas, which in turn may result in galvanic attack along grain boundaries. This type of corrosion is difficult to detect in its original stages. When the attack is well advanced, the metal is usually blistered or delaminated. This is referred to as "exfoliation". It is very difficult to completely remove and stop this type of corrosion, and replacement of the affected part is recommended wherever possible.
surfaces,
or
fuselage, empennage
blistering. Selective attack (1) Intergranular Corrosion along grain boundaries of metal alloys is referred to as intergranular corrosion. Aluminum alloys 2024 and
Corrosion
dry
NOTE
ACF-BO
metal surfaces, in an early development, local-cell corrosion appears as a whitish powder deposit. Surface pits warn of advanced local-cell corrosion. On painted surfaces, the first indication of corrosion will be evidenced by paint On
use.
4-99
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
M20M
B.
(4) Chemical cleaning solutions should be used with extreme caution on both aluminum and steel parts. Such solutions are not recommended for use in areas where they cannot be easily and completely neutralized,
(1) Fuel Servicing Decal Removal: (a) Cover the decal with a hot, wet towel for approximately 2 minutes. (b) Lift one corner of the decal and slowly
(1) To get a good clean surface for zinc chromate priming use a clean cloth or piece of cheesecloth and apply one of the solvents noted above. The surface should be wiped dry with a second piece of clean cloth.
remove.
(2) Remove all old following methods: (a) On aluminum
Do not allow the solvent to dry on the cleaned area as will redeposit dissolved soil and grime upon
evaporation. CAUTION solvents are generally flammable and toxic and should not be used without adequate ventilation and fire precautions,
Wipe
C. Apply zinc chromate primer to cleaned area by spray or brush. Area needs to be painted within 24 hours of zinc chromate primer coat. -PAINTING
The exterior is painted with urethane enamel. When exposed to humid salt air or to an atmosphere having corrosive fallout, the aircraft should be hangared when not in use.
Repairs.
paint,
pads,
320
paint by
one
of the
Remove all grease, grime, loose with a wipe solvent and rags. Do not allow the wipe solvent to evaporate. Wipe it dry! Steel parts may be cleaned to bare metal by sanding with emery cloth or steel wool. If the parts are removable, they can be cleaned by sandblasting. Regardless of the scouring method, all parts should be wiped with a tack rag and cleaned with fresh wipe solvent. The part should now be ready for priming and
(b)
A. Materials.
(1) Aluminum wool, nylon scouring finer emery cloth or steel wool.
loose
for uniformity of finish appearance, the entire skin panel should be prepared for repainting. If the paint is in very bad condition or if a filler is to be used, remove all of the paint by use of lacquer thinner, MEK or similar solvent. Careful application of paint stripper is acceptable. The solvent shbuld be wiped on and wiped off before it evaporates. If the solvent is allowed to evaporate, it will redeposit the soils and paint that were being carried. Any scouring required should be done at this point. Scouring with nylon pads or aluminum wool may be done dry or wet with one of the wipe solvents listed above. After the old paint, grime, etc. has been loosened and removed, the scoured area should be wiped with a tack rag, and again cleaned with fresh wipe solvent. The part should now be ready for priming and painting.
it
or
Procedures. NOTE
B. Wash all areas to be zinc chromated with a solvent such as methyl ethyl ketone (MEK), Turco T-657 (Turco Products, Inc., 6135 South Central Ave., Los Angeles, California), lacquer thinner, #3094 wash thinner (Pratt Lambert, Inc., 25th and N.Y. Avenue, Wichita, Kansas) or similar solvents.
1. Paint
Cleaning
Fiberglass components are attacked and deteriorated by products containing the following chemicals: Ketone, aliphaticesters, chlorinated hydrocarbons and slightly softened by aromatic hydrocarbons.
cleaning
20-00-03
SERVICE AND MAINTENANCE MANUAL
grit
(2) Tack rags. (3) Wipe solvents such as: methyl ethyl ketone, T-657 -(Turco Products, Inc.); #3094 wash thinner -(Pratt 8 Lambert, Inc.); lacquer thinner or equivalent
etc.
On steel
by wiping
painting. C. Priming
solvents.
(4) Body putty or aerodynamic filler such as: Flex-Bond -CTaylor 8 Art Plastics); Flex --(3M (NAPA Co.);or Cut polyester body filler #6372 ~Martin Senour Paintsl). (5) Compatible paints for the item (such as steel tubular structure or exterior skin) and for the year and model being repainted. (Refer to Mooney Parts Manual). (6) Thinners which are compatible with the paints being used both for paint thinning and for burn-down
and
Painting.
(1) On aluminum Cleaned and dried surfaces to be painted should be coated with a wash primer conforming to MIL-C-8514 or MIL-P-15328. Read and follow the manufacturer’s instructions carefully. The wash primer should be applied to attain a dry film thickness of 0.3 to 0.4 mils (a transparent film). A good wash primer coating is a must since the top coating can be only as good as the primer coat. As a general rule the wash primer should dry from .05 to 1.5 hours but not more than 2 hours before application of the top or intermediate primer coat. When an intermediate coat is applied, it should be mixed very carefully per the manufacturer’s instructions. It should be thinned per manufacturer’s instructions and applied to a dry film thickness of 0.8 to 1.0 MILS. The intermediate primer should be allowed to dry a minimum of 0.5 to 1.5 hours depending upon the application temperature and relative humidity. Follow manufacturer’s instructions.
thinners.
4-99
20-00-03
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
NOTE
The intermediate primer coat can be dry-scuffed lightly with No. 400 to No. 600 sandpaper prior to top coat application and give a higher gloss finish. As many coats of paint as desired may be applied. A higher gloss will be attained if the surface is scuffed lightly and tack rage cleaned between each coat.
M20M aircraft are painted with ACRO-GLO urethane gname~l.Inquiries concerning application of this finish should be directed to: Shen~vin-Williams Aerospace, 630 E. 13th,
Andover, KS. 67002, (316)
The same general procedure (2) On steel used on aluminum can be applied to steel. However, MlL-P-8585 primer or epoxy primer is recommended for the steel coat. If epoxy primer is used, it should have a wash primer (Mll-C-8514) pre-treatment,
NOTE abrasive polish compounds or harsh soaps and detergents on urethane finishes. Once the surface gloss is damaged it cannot be Never
humid
use
restored
weather, allow fifteen minutes between coats.
(2) Use a small round watercolor brush trimmed to a point for application of undiluted touch-up paint to small scratches and bare spots. Do not thin acid resistant black paint or exterior finish touch-up paint for brush-on application.
20-00-03
text. 144).
CAUTION
coats of white base and/or color coats to ten
allowing three to five minutes between depending upon weather conditions. Allow five minutes between coats in cold, dry weather; in
finish
733-1316
Any flight control surface that is to be repainted should be stripped of all paint prior to repainting. It is required that repainted control surfaces-be removed and rebalanced prior to flight per paragraph 24-9900.
D.
Painting. (1) Apply three
MOONEY AIRCRAFT CORPORATION
M20M
4-99
by polishing.
OLDWILLWAYNE
C H A PT E R
Al R
CONDITIONING
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 21
ENVIRONMENTAL SYSTEMS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
21-Effectivity/Contents
PAGE
DATE
1/2BLANK
4-99
21-40-00.
3.
4-99
21-50-00.
4.
4-99
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT 21-00-00
Cabin Ventilation
21-40-00
Heating Cooling
21-50-00
PAGE
SUBJECT
System
3 3 3
21-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 21-00-00
CABIN VENTILATION SYSTEM
21-40-00
environmental system consist of three ventilating systems that supply heated or fresh air as the pilot or passengers prefer. CABIN AIR, CABIN HEAT and OVERHEAD VENTILATION. The cabin air and heat system controls and vents are located on the console between the pilot and cc-pilot seats. Individual fresh air outlets are located on each side of the cabin side panels just forward of the pilots and cc-pilots knees. The overhead ventilation system consists of individual outlets ONemac valves) located between and above each seat position. The aircraft has a regulator system with the control knob located above and between the pilot’s and co-pilot’s head. The systems are basically trouble free but inspection should be made at regular intervals to ensure proper operation. The
SERVICE AND MAINTENANCE MANUAL
M20M
cabin
4-99
HEATING
Heat is supplied to the cabin through flexible hoses connected to a heat distribution box assembly and muff/shroud assemblies located on the exhaust manifold on the engine. It is recommended that the condition of these i~ems be checked each time the cowling is removed. This will provide a continuing check for the prevention of carbon monoxide in the cabin. Any deteriorated flexible ducts should be replaced. Heat shrouds should be inspected for cracks other deteriorations and repaired or replaced or promptly. Inspect the exhaust system for any leaks or cracks and replace or repair as needed. 21-50-00
COOLING
May be provided
at later date, if available.
21-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
21-50-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
ELECTRICAL POVVER
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 24 ELECTRICAL POWER
TABLE OF CONTENTS CHAPTER SECTION
24-00-00 24-30-00
24-31-01
PAGE
SUBJECT
SUBJECT
5
General
5
D.C. Generation Alternator
Charging System’Maintenance Maintenance
24-33-00
Voltage Regulator Auxiliary Power System. Battety Maintenance Warning Circuits
24-34-00
Power Plant Circuits
24-31-02
2451-03 24-32-00
-Low
5 5
5 6 7 7
Battery Starting
Procedures
7
Lighting Circui~s. Landing GearCircuits Fuel System Circuits
8
24-38-00
Miscellaneous Circuits
9
24-39-00
Trouble
24-35-00 24-36-00 24-37-00
24-39-01 24-39-02 24-39-03 24-39-04 24-39-05
24-50-00 24-51-00
Shooting
8 9
Charts
Alternator Trouble
Shooting
RESERVED.
Battery Trouble Shooting. Shooting Annunciator Trouble Shooting Starter Trouble
Electrical Load Distribution Power Distribution system.
9 9
10 10 11
13 19 19
24-CONTENTS 3/4BLANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 24 ELECTRICAL POWER
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT.
24-Effectivity
PAGE
DATE
1/2BLANK 3/4BLANK
4-99
24-00-00.
5.
4-99
24-31-03.
6.
4-99
24-33-00.
7.
4-99
24-34-00.
8.
4-99
24-36-00.
9.
4-99
2459-00
10
4-99
24-39-02
11
4-99
24-39-04
12
4-99
24-39-05
13
4-99
24-39-05
14
4-99
24-39-05
15
4-99
24-39-05
16
4-99
24-39-05
17
4-99
2459-05
18
4-99
24-50-00
19
4-99
24-51-00
20
4-99
24-Contents.
4-99
24-EFFECTIVITY
1/2BLANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 24-00-00
M20M
MOONEY AIRCRAFT CORPORATION
GENERAL
C.
Two 28 volt, 70 AMP altemators utilizing transistorized voltage regulators/over voltage controls supply electrical power. Two 24 volt, 10 AMP HR storage batteries are installed in the tailcone. The altemators, during nonal operation, supply power in conjunction with the selected battery when the Master Switch and Altemator Field Switches are ON. The circuit breaker panel is on the n’ght subpanel. The electrical system is capable of supplying current for simultaneous operation of multiple radios, anticollision lights and navigation lights. 27-0001 thru 27-0052 Alternator load is indicated by measuring the voltage drop across a shunt. This is of alternator capacity. Buss load is expressed in indicated in the same manner but is expressed as 150% of total altemator capacity so that any load over 100X indicates current is being drawn from the selected battery. A voltmeter indicates buss voltage.
27-0053 thru 27-TEA A shunt type ammeter PUSH for VOLTS) is located on instrument panel.
(with
24-30-00
-D.C. GENERATION
24-31-01
ALTERNATOR CHARGING SYSTEM MAINTENANCE
1. Alternator
D. Check charging system wiring and connectors to be sure they are clean and tight. E
CAUTION DO NOT ATTEMPT TO POLARIZE ALTERNATORS. Alternators are polarized every time Master Switch is turned on. 3. Alternator Removal and Installation.
A. Altemator Removal.
(1) Turn Master Switch OFF before alternator wiring. (2) Remove attaching beltfrompulley.
drive belt on and adjust belt tension (mid-span deflection: 14 Ib., used belt .31 in. belt -.31 in. 10 Ib.).
(3) Connect altemator wiring throughout system.
charging systems requires
wiring
special
no
damage the alternators and wiring. There are precautions that must be observed when servicing the alternator systems:
NOTE is removed from either alternator, the proper washers (for alignment) must be re-installed and the alternator pulley/shaft nut torqued to 75 80 ft. Ibs. it installed with out a Woodruf key. If Woodruff key is installed (S/N 27-0140 8 ON) torque to 50 ft.lbs. (+/-5#) If
pulley
24-31-02
several
the Master Switch is OFF alternator or voltage regulator.
sure
when
B. When either battery is removed from the aircraft for charging, be sure that the charger is correctly connected. Use the correct charging rate when charging battery, refer to Manufacturers procedures. It is possible to reverse the polarity of a battery by connecting a charger backwards.
on
using
a
E. Use an auxiliary ground power unit when trouble shooting electrical accessory equipment or when performing electrical landing gear maintenance and retraction system testing. 2. Alternator System Inspection. A. Check altemator circuit breakers on the main circuit breaker panel. Reset breaker if open. on
High Charging
Rate. Check the follawing
Fly aircraft for 15 to 20 minutes; charging rate slowly drop to 10 amperes or less. A very low battery will take longer to show a drop in charging current B. Measure voltage with a voltmeter connected to the bus. At 800 F., voltage should be 27.5 to 31.8 volts). An excessively high voltage regulator setting will cause excessive battery heating and water loss. 2. Low Charging Rate. Check battery charging rate (normal rate is not to exceed four amperes). The regulator should not be considered defective because of a low charging rate until: A. A voltmeter check indicates that voltage at the bus is below requirements. B. A battery hydrometer check indicates that battery is not fully charged. 3´• Hydrometer Read~g. If battery electrolyte
when the
B. Check alternator field circuit breakers circuit breaker panel. Reset if open.
The battery charging rate depends upon the battery condition and the vot~ige regulator setting. Wrth all equipment tumed off and the engine running at 2000 RPM or faster, the normal battery charging rate will be 5 to 35 amperes. A. should
fiight.
C. Be sure to check battery polarity by voltmeter prior to reinstallation in the aircraft.
VOLTAGE REGULATOR MAINTENANCE
1. Excessive~
CAUTION Both batteries MUST BE in aircraft for
D. Do not leave the Master Switch aircraft is parked.
and check
connectors
can
an
drive
slip
B. Alternator Installation.
new
attention; however, improper maintenance procedures
repairing
hardware and
(2) Install attaching hardware, place
replacement.
Be
disconnecting
pulley
When the loadmeter shows a higher than the altemators output at higher RPM, a charging system component is malfunctioning. On-the-plane testing should indicate which component is faulty and needs to be removed from .the aircraft for bench testing and repair or
A.
inspect dsnrassrs,~dbge reglab, znd wiing for drmage
(1) Be sue MasB~ ~ilch 6 ~med OFF. Do not ~m Masler ~1Nilch ON ulbl all mnections h~e been seared
Systems Setvicing.
The alternators
for corroded cable connections; and clean cable if corrosion is found.
Inspect batteries
’emove
temperature is below
80
F., subtract
4
pointso
from
hydrometer reading for every 100 F. below 80 F. If battery acid temperature is above 800 F., add 4 points to hydrometer reading for every 100 F. above 800 F.
main
4-99
24-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M EXAMPLE:
Hydrometer reading 1.260 Battery electrolyte temperature 300 F. 800- 300 500 5x4 20 points 1.240 Corrected reading 1.260 20
1.280
100
1.250
75
1.220
50
1.190 1.130
"Hi"
or
Overvolt
or
25
below
Adjustment
Very little
at
Connect
Regulator. supply to
the a variable voltage power regulator, positive to pin 5 8 negative to pin 9. Connect a voltmeter to the regulator to pin 6 and pin 9. Adjust voltage to 31.8 volts. Adjust trim pot (accessable through hole in case marked "OV") to relay trip point as indicated by voltage indication on test voltmeter. Decrease voltage until relay closes and note voltage. Readjust as necessary until a trip point of 31.8 (+/-).3 volts. Regulator Adjustment
Connect an accurate voltmeter to the aircraft bus. Turn off all electrical equipment and start engine. Run engine at moderate RPM (1500-1800) until ammeter drops to low charge rate. Increase RPM to 2000 and adjust trim pot (accessible through hole in case marked "REG") for a voltage reading of between 28.6 and 28.8 volts. Increase throttle to full RPM and observe that voltage does not exceed 30 volts. 24-31-03
AUXILIARY POWER SYSTEM
auxiliary power plug and related circuitry is installed to provide an outside source of electrical power to the aircraft (through No. 1 Battery Switch), to charge the No. 1 battery, or to start the engine. The Auxiliary Power Plug guide pin must have A+ voltage connected to it in order to activate the Auxiliary Power Relay. The No. 1 battery can be charged using the approved Auxiliary Power Cable connected to a charge cart capable of regulating the charging current. To prevent battery damage, the charging current should be low (3 4 amps) to begin and then increased as the battery voltage capacity is increased. The MASTER SWITCH is not required to be ON for the auxiliary power source to charge the batteries. The No. 2 battery will receive a trickle charge while the No. 1 battery is receiving the current. primary charging flight, the During non-selected battery is receiving a trickle charge from the aircraft alternators to keep it at peak voltage. A. When
auxiliary
power
or a
booster
battery
B.
See information. 24-31-03
using an auxiliary power paragraph 24-34-00, A
BATTERY MAINTENANCE
24-32-00
CAUTION
Battery 1.
Battery
gases
are
explosive.
Removal.
A. Turn Master Switch OFF. B. Remove tailcone dow"S.
access cover
C. Disconnect battery cables, battery from aircraft.
and
battery hold
negative lead first,
remove
D. Install battery in reverse sequence of removal. Use a voltmeter to check battery polarity before installation.
Battery Cleaning and Corrosion Removal. one pound of baking soda in one gallon
of
B. Wash battery mounting area and flush battery with the mixture. Do not allow soda water to enter battery cells; permanent damage will result if soda mixes with electrolyte. C. Rinse
thoroughly
with clear water and
dry
the
area.
D. Test each cell with
a
temperature corrected
hydrometer. Specific gravity should be 1.265 to 1.280 for a fully charged battery. E. Check electrolyte level and maintain at split ring. F. Clean battery terminals with emery cloth, reinstall and tighten cables. Coat terminals and connectors with petroleum jelly to retard corrosion.
is
source.
for
auxiliary power receptacle.
A. Mix water.
used, be sure cables are connected correctly--positive to positive and negative to negative. DO NOT by-pass batteries when
NOTE It is recommended that the approved Auxiliary Power Cable be connected to the booster battery first and then the plug inserted into the
2.
An
useful
additional
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL -WARNING CIRCUITS
24-33-00
necessary turn annunciator calibration dockwise to extinguish "low fuel" light).
1. Landing gear position lights and waming hem. RED and green landing gear position lights are in the
annunciator panel. The gear-down limit switch controls the green gear-down light. Both limit switches control the red gear unsafe light. The throttle control operates landing gear warning horn (intermittent tone) when the throttle is retarded to within 1/4 in. of IDLE position and the landing gear is still in the UP position. Check gear warning system during flight for proper operation. 2. Prestall Warning Circuit. The prestall warning horn has a high frequency continuous tone that sounds when airspeed drops to within 4.3 to 8.7 KIAS above stalling speed. A vane in the left wing leading edge actuates the prestal\ warning hom switch. (This vane is made of heat treated steel and any attempt to adjust switch operation by bending the vane will damage the switch). Refer to Section 27-93-00 for adjustment
(7) reconnect install
standard,
set switch to install annunciator front panel and
to annunciator
panel,
glareshield.
(1) Remove glareshield and assembly.
remove
annunciator
(2) Install and connect new annunciator assembly leaving off front panel. (Set switch to "Cal"). (3) Drain fuel from tanks and replace with unusable fuel plus 2 1/2 gallons in both tanks. See Section 28-43-01,2 for unusable fuel quantity. (4) Turn on master switch and adjust calibration pots to position where "low fuel" lamps just tum on for left and right tanks. (5) Turn OFF master switch, set annunciator "Gal" switch to "Norm" position, install annunciator front a"d install glareshield. (6) Refuel aircraft. Annunciator 5. Alternate Air Light Warning Circuit Panel. The light illuminates onthe annunciator panel when the alternate air door has opened for any reason. Annunciator 6´• Hi/Low Voltage Warning Circuit Panel. Remove annunciator top cover. Connect a voltmeter to aircraft bus. Start engine and increase RPM until FLASHING "Volr light extinguishes. This should be at a bus voltage above 26.6 volts. Add load, such as Pitot Heat 8 Nav Lights. Slowly decrease RPM, while monitoring voltage, until "VOLT" light begins too flash. This should occur between 26.6 8 26.4 volts. Adjust trim pot (see Figure 24-1) to obtain desired result.
Mooney Service Centers. I.A.I.,
transfer
calibration
counter
If calibration transfer standard, P/N 9500324000, is not available use the following method to calibrate "low fuel" warning:
4. Low Fuel Warning Circuit. The low fuel indicators will illuminate when a minimum of 2 1/2 gallons usable fuel remains in either left or right hand tank. When it becomes necessary to replace the annunciator panel for any reason other than "low fuel" waming malfunction, the following procedure should be used to set the "low fuel" warning circuits. The calibration transfer standard (I.A.I., P/N 9500324000) is required for this procedure. Adapters can be ordered through
using
plug
screw
8. Alternate method for calibration without l.Al. unit.
3. High and Low Vacuum Warning Circuit. A switch in the vacuum system controls the vacuum waming light on the annunciator panel. Vacuum below 4.25 \N. Hg. causes the vacuum waming light to flash. Vacuum above 5.5 IN. Hg. trips the high-vacuum switch causing the vacuum warning light to illuminate steadily.
Procedures
Remove
"Normal" position,
procedures.
Calibration A. 9500324000
MOONEY AIRCRAFT CORPORATION
M20M
P/N
(1) Remove glareshield, disconnect plug from of annunciator, remove annunciator front panel, and place "Norm-Cal" switch in "Cal" position. rear
(2) Plug, P/N 9500324000 calibration transfer standard to rear of old annunciator and reconnect harness plug.
(3) Turn Master Switch ON and turn right hand variable resistor on transfer standard slowly counter clockwise until right "low fuel" light just turns on. (If necessary turn variable resistor clockwise to extinguish "low fuel’’ light). (Do not adjust annunciator calibration screws). Repeat for left "low fuel". (4) Turn Master Switch OFF and remove old annunciator assembly after disconnection of harness and transfer standard unit. (5) Install new annunciator and connect calibration transfer standard to annunciator panel and hamess plug. Remove front plate and legend on new annunciatorpanel to expose the Norm-Gal switch and the Left and Right trim potentiometers. (Switch must be in "Cal" position).
(6)
Adjust
left and clockwise "low fuel"
calibration
screws
resistors)
until
right
annunciator
fuel
(not the adapter variable lights just turn on. (If 4-99
24-33-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION POWER PLANT CIRCUITS
24-34-00
1. Starter-ignition Circuit. The starter-ignition switch has five positions: OFF, R (right), L (left), BOTH, and START. In the OFF position both magnetos are grounded. At the R position the left magneto grounds. At the L position the right magneto grounds. At the BOTH position both magnetos are HOT and the ignition system is on. Turning the ignition switch to start and pushing in, closes the starter solenoid, engages the starter and allows the impulse coupling to automatically retard the magneto until the engine is also at its retard firing position. The spring action of the impulse coupling is then released to spin the rotating magnet and produce the spark to fire the engine. After the engine starts, the impulse coupling Ryweights do not engage due to centrifugal action. The coupling then acts as a straight drive and the magneto fires at the normal firing position of the engine. The starter-ignition switch is spring loaded to return from START to the BOTH position when released.
CAUTION
WARNING Do not turn the
propeller when the magnetos grounded. Ground the magneto points
not before removing rwlhh wires or eloctrloal connectors. All spark plug leads can be removed as an alternate safety measure.
A. LOW BATTERY STARTING PROCEDURE. A been discharged to the point where it will not turn the engine over but has sufficient power remaining for other equipment; should NOT have the engine jump started with another power source for two reasons:
The discharged aircraft battery is not because it will not have the necessary reserve capacity required to operate the aircraft electrical system and avionics in the event of the failure of the generating system during flight.
(1) airworthy
(2) Active material on the positive plate expands when the battery is discharged and the fast recharge from the higher potential source, battery, alternator, rectifier, etc., will severely damage the battery. A slow charge is recommended prior to flight.
3. The oil pressure instrument circuit contains an electrical instrument and a transducer which varies resistance with pressure. 4. Fuel Flow read on the indicator uses an electrical instrument which counts electrical pulses produced by .turbine flow transducer.
LIGHTING CIRCUITS
24-35-00
Navigation Lights. A circuit breaker switch on the flight panel controls the navigation lights. 2. LandingTTaxi Lights. A pair of circuit breaker split switches on the upper left Right panel controls the landing and taxi lights located in the left and right wings. 3. Cabin Lights. A three-position (Bright, Off, Dim) rocker switch overhead, between the pilot and cc-pilot in the overhead panel controls the cabin lights. 1.
upper left
Lights. A circuit breaker switch on upper flight panel controls the white anti-collision strobe lights. 5´• Instrument and Radio Lights. Switches are located on the lower co-pilot’s control panel for the glareshield, and radio lights. The glareshield rheostat also controls the compass light. Lighting is controlled by manually pushing top of switch to intensify or bottom to dim either light system (S/N 27-0001 thru 27-0107) S/N left
27-0108
ON have
a
rotary type rheostat
to dim these
lights. 6. Baggage Compartment Lights. (Bright, -Off, Dim) rocker switch in controls this light.
A three-position overhead panel
Aircraft S/N 27-0053 thru 27-0107 may have a door switch and timer mechanism that illuminate aft set of interior lights while baggage door is open. After door is closed, if rocker switch is left ON, aft interior lights will remain ON for approximately 2 minutes. The rocker switch is connected through the MASTER switch on these aircraft and aft interior lights will go OFF when MASTER switch is turned OFF if door is closed.
The M20M has a second battery that selected as the primary battery for a particular The battery not being utilized will be recharged by a trickle charge from the aircraft alternator’s charging system. Therefore if only one battery is discharged to the point that it will not start the engine the other battery may be selected and the Right continued.
CAUTION On S/N 27-0001 thru 27-0052 the cabin and baggage interior lights are not connected to the master switch circuitry and can be operated with master switch in the Off position. Care must be exercised to prevent leaving switch ON and discharging one of the batteries.
Oil and Cylinder Head Temperature Gauge Circuits. Both the oil and cylinder head temperature indicators operate electrically. The oil temperature gauge circuit has a resistance bulb in the filter adapter adjacent to vern-a-therm valve.. Changes in resistance caused by changes in oil temperature alter current Row rate, thereby varying the magnetic field in the indicator The cylinder head coils. temperature indicator connects to a tip sensitive resistance bulb in a cylinder head, normally No. 5 cylinder. Increase or decrease in 2.
24-34-00
COilS.
4. Strobe
battery that has
major
temperature causes an increase or decrease in bulb resistance, varying the magnetic field in the indicator
Aircraft S/N 27-0053 thru 27-0107 may have a door switch and timer mechanism that illuminate forward set of interior lights while cabin door is open. After door is closed, if rocker switch is left ON, forward interior lights will remain ON for approximately 2 minutes. The rocker switch is~connected through the MASTER switch on these aircraft and forward interior lights will when MASTER switch is tumed OFF if door is
Do not operate the starter in excess of 15 seconds or re-engage the starter without allowing it time to cool.
are
SERVICE AND MAINTENANCE MANUAL
M20M
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
1. Fuel Pump Circuits. A controlled by 1 switch.
7. Map Light. (27-0001 thru 27-0052) A push button switch on top of control wheel center section controls the map light. (27-0053 thru 27-TEA) A switch/rheostat on top of control wheel control the map light and brightness. The co-pilots map light is optional.
1. Limit switches and relays landing gear actuator motor.
operate the reversible
A landing gear air safety switch, actuated by pitot air pressure, prevents landing gear retraction until a safe flying speed is attained. The landing gear control switch operates the actuator motor through the safety switch and relays. When the landing gear control switch is up and a safe flying speed has been attained, the safety switch closes to activate the control relay starting the
1. Turn Coordinator Circuit. The turn coordinator is a instrument which operates from an electrical
flight
power
As the gear reaches the up and locked mechanical stop opens the limit switch and the actuator stops. When the landing gear control switch is placed in the down position, the gear motor down-relay closes and the actuator starts. When the gear reaches the down-and-locked position, the mechanical stop opens the limit switch and the actuator stops, the gear-up limit switch controls the landing gear un-safe light. The red light comes on when the gear is in transit. The green light comes on when the gear reaches the down-and-locked position; controls the limit switch the gear-down green gear-down light. The GEAR DOWN annunciator light is dimmed whenever navigation lights are ON.
option. Cigar Lighter. A cigar lighter is mounted ’ight instrument panel. 5. Current Sensor (Monitor).(Reference Figure or 24-18) 4.
in the
24-1A
CURRENT SENSOR ADJUSTMENT Effective S/N 27-0053 thru 2i~BA A. Remove front
cover
from Annunciator.
B. Start engine and run at moderate ammeter charge rate drops to near zero.
speed until
C. Tum OFF all equipment avionics, lights, pitot so only the equipment connected to buss is
heat, etc.,
operating (instruments). D. Turn OFF right altemator field switch. E. Adjust LH potentionmeter clockwise until light illuminates; then counterclockwise until light is
DOWN" and "GEAR UNSFE" lights will
illuminate. Push and hold the red button switch beside the landing handle until the gear is up and both lights .g_O_O.U~:
gp~t’
extinguished.
warning horn. Reset circuit breaker
F. Tum left altemator OFF and turn
prior to extending gear.
right
altemator
ON. G.
BULBS
E 6 F with RH
potentionmeter. if either light illuminates, adjust appropriate potentionmeter slightly
FUEL SYSTEM CIRCUITS
H.
The fuel system has an electric fuel boost pump. The fuel quantity indicating system is comprised of two transmitters in each fuel tank (inboard and outboard) and two fuel quantity gauges in the instrument panel.
O
switch
as an
2. Gear Safety By-Pass Switch. The gear will not retract if airspeed above the set limit has not been attained when the gear handle is placed in the up position. A warning hom will sound and both "GEAR
INSTRUMENT LIGHT
breaker
circuit
3. Hour Meter. The hour meter operates from the electric tachometer. A Hobbs meter may be installed
a
24-37-00
source.
2´• Heated Pitot Tube. A controls the pitot tube heater.
actuator.
RELAr’ to stop
MISCELLANEOUS CIRCUITS.
24-3&00
pressure
position,
pump is
single auxiliary fuel
2. Fuel Ouantity Gauge Circuits. Changes in fuel level vary fuel quantity transmitter resistance (two in each tank work in series with each other) that operates the fuel quantity gauges. The master switch activates the fuel quantity indicating system. Refer to Section 2843-00 for Adjustment Procedures.
LANDING GEAR CIRCUITS
24-36-00
MOONEY AIRCRAFT CORPORATION
M20M
Repeat Steps Turn
both
altemators
counterclockwise until J.
Replace
(TYP.)
cover
extinguished. secure in original location.
light
and
ON;
Alternator
is
null
adj.
screws.
NORM CAL
0~0
3 O
O
o__o o o o o LEFT-FUEL
Lo~ Fuel
(S/N
Q
(LH)CH10-ALT
CAL7~
27-0053
FIGURE 24-1A
THRU
Warning aclj.
ADJ-CH1I(RH)
screws.
27-0239>
CURRENT MONITOR ADJUSTMENT
4-99
24-36-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION -TROUBLE SHOOTING CHARTS
24-39-00
-ALTERNATOR
24-39-01
SERVICE AND MAINTENANCE MANUAL
M20M
FUEL LEVEL-RIGHT
MINIMUM
DIM. LEVEL
O
O
FUEL LEVEL-LEFT
0\0 O
TROUBLESHOOTING LEFT
ALTERNATOR RIGHT ALTERNATOR
FIGURE 24-1b
TROUBLE
FUEL
NORM
SET CAL
CURRENT MONITOR ADJUSTMENT
PROBABLE CAUSE
REMEDY
overcharges battery; battery uses excessive water.
Regulator faulty.
Check bus voltage with engine running. Observe aircraft ammeter. Ammeter should indicate near zero after ten minutes of engine operation. Replace voltage regulator if defective.
ALT FIELD circuit breaker
Circuit shorted in wiring.
Disoonnect lead from pin 5 of regulator, and reset circuit breaker. If circuit breaker trips, check wiring.Repair as required. If breaker does not trip, replace regulator. Reconnect lead to regulator. AItemator field Master Switch to ON and check for 24 volts at pin 5 of regulator. Repair wiring if no voltage is present.
Short circuit in
Disconnect lead from post of alternator, and reset ALT circuit breaker. If circuit breaker trips, check
Altemator
trips.
ALT circuit breaker trips.
wiring.
wiring
between alternator and circuit breaker.
Short circuit in alternator. WARNING:
Alternator will not
Replace lead
to
post of alternator.
ENSURE THAT MAGNETO SWITCH IS OFF WHEN TURNING PROPELLER. Rotate propeller by hand to rotate altemator through 360 degrees of ~Flvel. If circuit breaker trips replace aitemator.
keep battery
Battery malfunction.
charged.
1. Start engine and adjust for 1500 RPM. Ammeter should indicate a heavy charge rate with all electrical equipment turned off. Rate should taper off in 1 3 minutes.
voltage check at the bus should indicate a reading of 28.6 to 28.8 volts. If charge rate tapers off very quickly and voltage is normal, check battery for malfunction. If ammeter shows a low charge rate or any discharge rate, and A
voltage Defective
is
low, proceed
to
step 3.
2. Check voltage at terminal 5, with Alt.Fld. Master switch ON.
wiring.
Meter should indicate bus voltage. If voltage is not present, check wiring between regulator and bus. 3. Remove connector from start engine.
Regulator faulty.
24-39-00 10
4-99
regulator and
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
Momentarily jump pins 5 7 together on plug. Aircraft ammeter should show heavy rate of charge. If heavy charge rate is observed, replace regulator. If heavy tate is not observed, proceed to step 5.
the
CAUTION Pull alternator field C/B. Start
engine; while at idle RPM reset C/B. Slowly monitoring bus voltage. DO NOT U(CEED 28 volts
Alternator will not
keep battery
charged (con’t.)
Defective wiring alternator.
regulator to
increase RPM while
4. Check resistance from nd terminal of attemator to pin 7 of reg. plug. Normal
indica~on is a very low resistance. If indicates no, or poor continuity, repairer replace wiring from regulator to altemator.
reading
Defective altemator.
5. Check resistance from
case to field of altemator. Normal indication is 3 4 ohms. If resistance is high or low, repair or replace altemator.
6. Check resistance from F2 terminal of altemators to altemator case. Normal indication is high. If resis~ance is low, repair or replace altemator.
-RESERVED
24-39-02
BATTERY TROUBLE SHOOTING
24-39-03
TROUBLE
REMEDY
PROBABLE CAUSE
Discharged battery.
Battery wom
Replace battery.
out.
Improper charging Excessive
rate
setting.
Standing too long. left
on.
Impure electrolyte. Short circuit Low
Cracked cell
Compound
jars.
on
top of battery
(ground)
charging
runs
out of vent
wiring.
on
recharge battery.
Remove and
recharge battery.
Check
wiring.
Adjust voltage regulator.
rate.
Loose hold-down bracket. Frozen Battery
Replace battery and Replace Battery.
Charging
Reduce charging rate by adjusting voltage regulator.
rate too
high.
Too much water added to
battery; charging
Excessive corrosion
Remove and
Replace battery. in
melts,
Electrolyte plugs,
rate.
Tum off some equipment when alternator is not charging. Decrease starter usage by using extemal power when possible.
discharging.
Equipment accidentally
charging
Reset
rate too
high.
Spillage from overfilling.
secure
Drain battery and keep at adjust voltage regulator. Flush
area
with
firmly.
proper level;
baking soda solution.
mounting surface.
Leaking or clogged vent Charging Battery freezes.
rate too
line.
high.
Repair or clean
vent line.
Adjust voltage regulator.
Discharged battery.
Replace battery.
Water added and
Always recharge battery for 1/2 hour following addition of water in freezing
battery not charged immediately.
weather.
Leaking battery Reversed
case.
Frozen
electrolyte.
Replace battery.
battery polarity. 4-99
24-39-02
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
Cables connected backwards
Battery should be slowly discharged completely, then charged correctly and
on
battery or charger,
tested.
Excessive water consumption
Charging
rate too
in all cells.
Excessive water consumption in
one
cell
high.
Correct
Cracked jar.
charging
rate.
Replace battery.
only. STARTER TROUBLE SHOOTING
2459-04
TROUBLE
PROBABLE CAUSE
Motor fails to operate.
Low
REMEDY
battery.
Check and
recharge battery
if
necessary.
Defective, improper,
or
loose
Refer to electrical check all wiring.
wire connections,
Binding,
worn
improperly
Brushes should fit free in brush boxes without excessive side play. Clean binding brushes and brush boxes with Varsolmoistened cloth. New brushes should be run-in until at least 50 percent seated; however, a facilities are not available for running in brushes, seat brush by inserting strip of No. .0000 sandpaper between brush and commutator with sanded side next to brush. Pull sandpaper in direction of rotation, being careful to keep it in same contours as commutator.
seated brushes; brushes have excessive side play,
CAUTION:
wiring diagram and
Do not
Dirty
use coarse
sandpaper
commutator.
or
emery cloth. After seating, thoroughly clean brushes and commutator to prevent excessive wear. Keep motor bearing free from sand or metal particles. If commutator is rough or dirty, smooth and polish with No. 6000 sandpaper. If too rough and pitted, remove commutator and turn down. Blow out all
Shorted, grounded,
or
open
armature.
Grounded Slow
cranking speed.
or
open field circuit.
Worn, rough,
or
improperly
lubricated motor
Same causes "Motor fails to
Excessive motor brush
arcing.
as
or
starter.
listed with
foreign
material.
Remove and replace with an armature known to be in good working order. Test and repair circuit if replace with new parts.
possible
or
Disassemble, dean, inspect, and relubricate components, replace won bearing. Same remedies.
operate."
Binding, worn, or improperly seated brush or brushes have excessive side play. Dirty, rough, pitted, or scored
Repair as Clean
as
outlined above.
outlined.
commutator.
Excessive motor brush and arcing.
wear
Rough
or
scored commutator.
Armature assembly not concentric.
24-39-04 12
4-99
Remove and turn commutator on lathe.
Reface commutator.
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ANNUNCIATOR TROUBLE SHOOTING
24-39-05
The following is a brief 1.0 GENERAL
operational analysis which pertains to the
I.A.I. annunciator on the 2.0 POWER SUPPLY
Mooney
M20M.
This document is intended to be a guide to assist the service technician in understanding the theory and operation of the International Avionics, Inc. (IAl) Part Numbers, 9500326000 8 9500326001 annunciators. it is not intended to serve as a bench service aid in that the reference designator in the various Figures are not consistent with those found in the actual annunciators,
The
Service
The Test Switch, S1, switches unfiltered aircraft 28VDC to the internal test line, identified with the m"emonic "TEST+". diode isolated by is also CR5, "OUTTEST+". as supplied Additionally"TEST+’’ is_applied to the inverter to supply the internal test line, "TEST-", and the diode isolated "OUTTEST-". The dimmer circuit, applicable to certain channels, requires a bias source, "DIMBIAS", with a magnitude of 12 VDC to dim the applicable ACTIVE channels, approximately 3 VDC to maintain the dim level of those channels previously dimmed, and near 0 VDC to reset the dimmed channels to a bright condition. The channels having the capability of t~ing dimmed by the above circuiby ae channels 3, 4 6 7 8, 14, and 15. Channel 1, Landing Gear, dims by means of a separate circuit and is discussed in Section 4.0 below. Wrth all both the Dim Switch and Test Switch relaxed, transistor 03 is in sab~mtion and 02 is off, giving "DIMBIAS" a value of 9 VD=. When the Dim Switch is depressed Q3 comes wt of saduration and "DIMBIAS" rises to 12 VDC, and when the Test is depressed 02 and "DIMBIAS" drops to near 0 VDC. In the event that bc4h switches are depressed simultanewsty the 0 VDC value of "DIMBIAS’ will prevail and the dimmed c~anneis, with the exception of Channel 1, are reset to a brigM condition.
literature
is
available
from
International
Avionics, Incorporated (IAl), 1611 N. 1-35, Suite 428, Carrollton, TX 75006, telephone number (214) 446-1185, to identify the location of a particular component and the exact manner in which the components are interconnected. The
following
sections address nine
which, used singularly
comprise the
or
in
(9) basic circuits multiple combinations,
annunciators. These
sections
are
as
follows:
Section Section Section Section Section Section Section Section Section
2
3 4 5 6 7 8 9
10
Power Supply, with Test Dim switches Flasher Landing Gear Indicators Left and Right Low Fuel Hi/Lo Vac Left Alternator/Low Volts/Over Volt Right Alternator/Over Volt Typical Positive Apply W/Dim Typical Positive Apply W/O/Dim.
’´•;I"""’" I"~""’" 1
PowerSupply, shown in Schematic Figure 1, provides 12 VDC, reverse voltage protection by means of CR1, spike and overvoltage filtering by means of the low pass network of R1, R2, Ct and C2 with spike clamping provided by CR2. The actual power supply is a 12 VDC, integrated circuit regulator. Output filtering is provided by C2.
I 1ZUDC R11
R13
331(
R14 FL~SH
R12
I""" RS
P:1
Z~FSD
~:KOj F[GURE
4-99
Z
FLAS~ER
24-39-05 13
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
3.0 FLASHER
The Flasher, shown in Schematic Figure 2, provides the circuit to flash the outputs of the left and right alternator warnings, the low voltage warning and the low vacuum warning. The flasher consists of an astable oscillator driving an NPN common emitter connected transistor, 04. This allows the open collector of 04, identified as FLASH, to sink the drive from the output amplifiers of the appropriate warning channels.
s
a~
s
~a
~E
9 l_z
1’2 I
I
S
-TT
~g
s
~a
sa
1
4.0 LANDING GEAR INDICATORS
The
Landing Gear Indicators, shown in Schematic Figure 3, provide the status of the landing gear position, that is, whether the landing gear is Down or not and whether the landing gear Is safe or unsafe, unsafe being in transit. The circuit shown is the identical circuit that has been used for many years in the IAl annunciators used on Mooney aircraft. The GEAR DOWN channel is dimmed for night operation; however, in the interest of reliability, the dimming circuit is separate from the dimming technique used on the other dimmed channels. The gear down
I a~
"I
+28 VDC, is
applied through input and CH1RET is returned to the Nav Light bus. When +28 VDC is applied to INPOS1 and the Nav Lights are off, the impedance of this point is very low due to the low filament resistance of the Nav Light bulbs, and signal, CR7,
ai 1
g~
I
I’
11
GEAR DOWN illuminates at near full brilliance. When the Nav Lights are on, however, CH1RET is also +28
H c01"
n~
g-,
5
CR7 InPOS1
X
=Y
LnPPOS1 CRL)
’ZTi
(N4aas
DS1
’I
CR(P
I 11
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OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
VDC and CR9 switches this return path off, the return path for the GEAR DOWN lamp being through R15 to Ground and GEAR DOWN now illuminates at reduced brilliance. The GEAR UNSAFE channel accepts +28 VDC, INPOS2, through isolation diode CR10, illuminates at full brilliance and does not dim. A test signal, ’ITEST+" is applied to both GEAR DOWN and G~AR UNSAFE through CR8 and CR11 respectively, 5.0 LEFT AND RIGHT LOW FUEL
The Left and Right Low Fuel circuits are shown in Schematic Figure 4. The left and the right channels are similar, and only the left channel will be discussed herein. Signals from the junction of the left and right fuel transducers and the left and right fuel quantity gauges are applied, respectively, to each of the inputs INPOS3 and INPOS4. This signal is an analog signal that indicates the quantity of fuel measured, the typical low fuel point being on the order of 0.1 volt. The low fuel circuits can, however, annunciate an input up to approximately 0.7 volt, The input, INPOS3, is applied through an isolation resistor R55 to the inverting input of open collector comparator U5:C. The input is compared with the set point effected by the setting of R51, accessible through the front of the annunciator, and, when the input is less than the set point, the comparator’s output is allowed to rise by means of the pull-up resistor R54 and the network R48, R49, and‘CS. Feedback resistor R53 provides a small amount of hysterisis to preclude oscillation at the transition point. The exponentially rising output of U5:C is applied to the inverting input of open collector comparator U5:B and is compared with a reference voltage of approximately 6 VDC. When U5:B switches its output to ground Q10 conducts and drives 08 into saturation to light the L LOW FUEL channel lamp, DS3. The Q10 08 network is required to provide the transition between the intemal 12 VDC and aircraft +28 VDC. The delay provided by the charge of C9 through R48 and R49 provides filtering to preclude false annunciation in rough air. When the fuel level rises, due to sloshing in the tank and U5:C switches to a low output state, C9 is discharged rapidly throuah R49. The delay time of the charging network proviaes a delay in low fuel annunciation of approximately 20 seconds. A test of the functioning of the low fuel channel is accomplished by applying ’LTEST+" through R43 CR18 to the input of U5:C to switch U5:C and applying ’’TEST+" through R42 CR15 to accelerate the charging rate of the filter C9, thus reducing the delay to approximately 2 seconds. In order to calibrate the low fuel channel the set point, R51, is adiusted with the screwdriver adjustment accessible through the front of the annunciator while there is a preset number of gallons in the tank. The time delay must be removed from the circuit by moving S3, accessible through the front of the annunciator, from the NORMAL position to the CALIBRATE position. This opens the return for capacitor C9 and the indication on the L LOW FUEL channel will not be delayed. After calibration is accomplished, restore the time delay by moving S3 from the CALIBRATE position back to the NORMAL position. The position S3 can be without determined removing the front of the 4-99
MOONEY AIRCRAFT CORPORATION
annunciator. When the TEST switch is depressed observe the indication of L LOW FUEL and R LOW FUEL. With S3 in the NORMAL position there is a delay of approximately 2 seconds in illumination, but with S3 in the CALIBRATE position there is no delay in illumination. Up to this point the circuits used to annunciate low fuel are the same circuits that have been used for many years in IAl annunciators used on Mooney aircraft. The method of dimming, however, has been changed and expanded from what has been used in the past. In the past only the low fuel channels dimmed, excluding GEAR DOWN discussed above, while now the dimmina has been e~cpanded to include additional 5 channej-~. From the perspective of the pilot the operation is the same, depress the DIM switch and active channels dim, depress the TEST switch and active dimmed channels return to bright. When a dimmed channel is extinguished and then reactivates it will reactivate bright. The method to accomplish this, however, is considerably different from the past. Each channel to be dimmed is driven by a transistor, in this case 08 which retums the lamp to ground through two parallel paths. The path to provide a dim indication is through resistor R29 which reduces the brilliance of the lamp. In the bright mode R29 is shorted by 06 and CR13 which provide a low impedance path to ground. Transistor 06 is controlled in conduction by a latch composed of U3 and its associated resistors R22, R23, R24, R25, R26 and R27 as well as the signals IDIMBIAS" and "DIMIN3". If the channel is active "DIMIN3" will be near ground and with "DIMBIAS" near 3 VDC, the output of U3 will be high, thus driving 06 into conduction. When the DIM Switch is depressed momentarily, "DIMBIAS" goes high to 12 VDC and U3 switches its output low and latches through R26. This low output removes the drive from 06 and DS3 dims. When the TEST Switch is depressed momentarily, ’DIMBIAS" goes low and U3 switches its output high, latches through R26, and drives 06 into conduction. When the channel deactivates, 08 opens the retum to ground and "DIMIN3" rises which retums latch U3 to a
high output state. 6.0 HI/LO VAC
High/Low Vacuum circuits are shown in Schematic Figure 5. This channel is designed to accept two +28 VDC signals, one from a low vacuum sensor and one f’om a high vacuum sensor. When low vacuum is detected the annunciator will Rash and when high The
is detected the annunciator will illuminate A +28 VDC signal applied to LOW VAC INPUT will drive Q11 into conduction through the bias network R56, R57, CR17, and CR22, thus illuminating DS9. The signal FLASH will, however, remove this drive signal as the Rasher cycles, thus flashing DS9. A +28 VDC signal applied to HIGH VAC OVERRIDE will bypass the above network and drive Q11 into c0"duction regardless of the state of LOW VAC INPUT. Similarly ’’TEST+" will drive Q11 into Co"duction regardless of the state of LOW VAC INPUT. The channel High/Low Vac does not dim. vacuum
steady.
7.0 LEFT ALTERNATOR/LOW VOLTS/OVER VOLT
Th, Left Alternator/Low Volts/Over Volts circuits are shown in Schematic Figure 6. This channel is designed t,accept three signals, the analog signal LAINPUT 24-39-05 15
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
8UDC DS9 7327
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internally or when low current is detected the annunciator channel flashes, and when overvoltage tripped is detected the annunciator channel illuminates
VDC +28 from current sensor, the a signal LOVERRIDE from the overvoltage tripped output on the left alternator regulator, and one signal derived internally that indicates that the aircraft bus voltage is less than 26.5 VDC. When low voltage is detected
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28 VDC by R68 with the and R65. The output of U6, an open collector comparator is normally low. When low voltage is detected the output of U6 rises and drives Q12 into conduction through the bias network R60, CR24, and CR28, thus illuminating DS10. In a manner similar to the Hi/Lo Vac channel, the signal FLASH will remove this drive signal as the flasher cycles, thus flashing DS10. A +28 VDC signal applied to LOVERRIDE will bypass the above network and drive Q12 into conduction regardless of the state of the comparator U6.
Similarly "TEST+" will drive 012 into conduction regardless of the state of the comparator U6. Comparator U7 monitors the output of a Hall Effect
1N4005
1 N4005
current sensor which measures the left alternator output current. The signal from the Hall Effect sensor is compared with a predetermined bias set by_adjusting
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24-39-05 16
VAC
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R59. It should be noted that the divider of R74, R59, and R75 actually consists of R74, R59 in parallel with R83 (see Schematic Figute-/), and R75.The points labeled ALTBIASH and ALTBIASL are common to both left and right alternator sense circuits. As LAINPUT is reduced in value below the voltage set by R59 the comparator U7 goes high and again drives Q12 into conduction through the bias network R70, ICR23, and CR28, thus illuminating DS10, but the signal FLASH will remove this drive signal as the flasher cycles, thus flashing DSIO. A +28 VDC signal applied to LOVERRIDE also drives Q12 into conduction regardless of the states of either comparator U6 or U7. Similarly’7EST´•t´•" will drive Q12 into conduction regardless of the states of either comparator U6 or U7. I The channel Left Alternator/Low VoltslOver Volt does not dim. The variable resistor R59 is accessible through the Part Number front of the annunciator on IAl 4-99
OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
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4-99
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24-39-05 17
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
9500326001, while
an equivalent variable resistor mounted external to the annunciator is required for the 9500326000 annunciator.
associated resistors R86, R87, RS8, R89, R90 and R91 well the as as signals "DIMBIAS" and "DIMINPUT". If the channel is active "DIMINPU~’ will be near ground and with "DIMBIAS" near 3 VDC, the output of U9 will be high, thus driving 014 into conduction. When the DIM Switch is depressed momentarily, "DIMBIAS" goes high to 12 VDC and U9 switches its output low and latches through R87. This low output removes the drive from 014 and DS-X ~When the TEST Switch dims. is depressed momentarily, "DIMBIAS" goes low and U9 switches its output high, latches through R87, and drives 014 into conduction. When the channel deactivates, 015 opens the retum to ground and "DIMINPUT’ rises which returns latch U9 to a high output state.
8.0 RIGHT ALTERNATOR/OVER VOLT
The Right Altemator/Over Volts circuits are shown in Schematic Figure 7. This channel is designed to accept two signals, the analog signal RAINPUT from a current sensor, and the +28 VDC signal ROVERRIDE from the overvoltage tripped output on the right alternator regulator. This circuit is an exact duplicate of and functions in a similar manner to the Left Alternator/Low Volts/Over Volts circuit with the single exception that this circuit does not detect low aircraft bus voltage. When low current is detected, the annunciator channel Rashes, and when overvoltage tripped is detected, the annunciator channel illuminates
steady. Comparator
U8 monitors the output of
a
SERVICE AND MAINTENANCE MANUAL
10´•0 TYPICAL POSITIVE APPLY W/O/DIM A typical Positive Apply, Non-Dimmable circuit is shown in Schematic Figure 9. This channel is designed to accept a +28 VDC signal to illuminate an indicator channel, but does not provide for dimming of that cha""el. The input, YINPUT, is applied through CR38 to light DS-Y. "TEST+" is applied through CR37 to also light DS-Y.
Hall Effect
current sensor which measures the right alternator output current. The signal from the Hall Effect sensor is compared with a predetermined bias set by adjusting
R83. It should again be noted that the divider of R74, R59, and R75 (see Fig 6) actually consists of R74, R59 in parallel with R83, and R75. The points labeled ALTBIASH and ALTBIASL are common to both left and right alternator sense circuits. As RAINPUT is reduced in value below the voltage set by R83 the cbmparator U8 goes high and drives 013 into conduction through the bias network R82, and CR33, thus illuminating DS11, but the signal FLASH will remove this drive signal as the flasher cycles, thus flashing DS11. A +28 VDC signal applied to ROVERRIDE also drives conduction into 013 regardless of the state of comparator U8. Similarly "TEST+" will drive 013 into conduction regardless of the state of comparator U8. The channel Right Alternator/Over Volt does not dim. The variable resistor R83 is accessible through the front of the annunciator on 1Al Part Number 9500326001, while an equivalent variable resistor mounted external to the annunciator is required for the 9500326000 annunciator.
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A
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Apply, Dimmable circuit is shown in Figure 8. This channel is designed to accept a +28VDC signal to illuminate an indicator channel and provide for dimming of that channel, as well. Dimming is accomplished in a manner similar to Positive
Schematic
that described for low fuel channel above. The input, XINPUT, is applied through CR35 and R84 to drive 015 into saturation and light DS-X. "TEST+" is applied through CR36 and R84 to also drive 015 into saturation and light DS-X. These 5 channels may be dimmed by depressing the DIM switch to dim the active channels. Depressing the TEST switch returns the active dimmed channels to bright. When a dimmed channel is extinguished and then reactivates it will reactivate bright. -~ach channel to be dimmed is driven by a transistor, in this case 015 which returns the lamp to ground through two parallel paths. The path to provide a dim indication is through resistor R8j which reduces the brilliance of the lamp. In the bright mode R85 is shorted by 014 and CR34 which provide a low impedance path to ground. Transistor 014 is controlled in conduction by a latch composed of U9 and its 24-39-05 18
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OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 24-50-00
ELECTRICAL LOAD DISTRIBUTION
24-51-00
POWER DISTRIBUTION SYSTEM
M20M
MOONEY AIRCRAFT CORPORATION
The power buss distributes direct current power to the electrical system from the alternators and from the selected battery through the battery relay. The batteries negative leads attach to a structural ground on the airframe. The master switch "ON" closes the relay and supplies power to the aircraft electrical
system. CAUTION Do not reset a circuit breaker after it has tripped a second time. If necessary to do so to locate the malfunction, be alert for a possible electrical fire. Breakers are "Trip Free" type and cannot be held in the closed position.
4-99
24-50-00 19
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
BLANK
24-51-00 20
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
C H A PT E R
FLIGHT
CONTROLS
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 27 FLIGHT CONTROLS
TABLE OF CONTENTS CHAPTER SECTION
27-00-00
PAGE
SUBJECT
SUBJECT General
5
27-60-00
System Rudder 8 Steering System Elevator System Allowable Freeplay Limits Variable Downspring System Trim Systems digging. Stabilizer Trim System RudderTrim System Rigging StabilizerTrim System Troubleshooting Electric Trim System Maintenance Wing Flap System 8 Rigging Aileron/Rudder Interconnect System
27-90-00
Miscellaneous
27-10-00
27-20-00 27-30-00 27-30-01 27-31-00 27-40-00
27-40-01 27-40-02 27-41-00 27-42-00 27-50-00
27-91-00 27-92-00 27-93-00 27-93-01 27-94-00
2785-00 27-95-01
27-96-00
Aileron
6 7
8 8 9 9
10 12 12 12 14 14
Control Surface
Static8alancins Equipment 8 Materials Static Balancing General Procedures Static Balancing Detail Procedures Static Balancing. Control Surface Trailing Edge. Stall Warning Maintenance Practices. Trouble Shooting Stall Waming System Speed Brake System
27-96-02
Removal- Installation -Speed Brakes Maintenance -Speed Brakes
27-96-03
Trouble
27-96-01.
5
Shooting
Guide
14 14 14
14 15 16 17
17 17 17
17
27-CONTENTS 4-99
3/4BLANK
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 27 FLIGHT CONTROLS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT
PAGE
DATE
1/2BLANK 3/4B14NK
4-99
27-00-00
5.
4-99
27-20-00
6.
4-99
27-30-00.
7.
4-99
27-30-01.
3.
4-99
27-40-00.
9.
4-99
27-40-02
10
4-99
2740-02
11
4-99
27-41-00
12
4-99
27-50-00
13
4-99
27-60-00
14
4-99
27-93-01
15
4-99
27-94-00
16
4-99
27-95-00
17
4-99
27-96-03
18
4-99
27-Effectivity 27-Contents.
4-99
27-EFFECTIVITY 4-99
1/2BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 27-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
-GENERAL
NOTE station 147.75 is located at skin splice line between flap outboard end and aileron inboard end.
Wing
The aircraft has dual Right controls and can be Rown from either the pilot or co-piTot seat. Dual pairs of foot pedals control the rudder and nose wheel steering mechanisms. The cc-pilot pedals are removable if dual brakes are not installed. Push pull tubes actuate the all-metal Right control surfaces. Rod-end bearings are used throughout the Right control systems. These bearings are simple and require little maintenance other than occasional lubrication. Specially designed aluminum-alloy OaD ii extrusions, that permit Rush skin attachment, form the leading edges of the rudder and elevators. Electrically actuated wing Rap systems installed on all models. Longitudinal pitch trim is achieved through a trim control system that pivots the entire empennage around the tailcone B~ attachment points.
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27-10-00
B
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-AILERON SYSTEM
The ailerons are of all-metal construction with beveled trailing edges. Three hinges of machined, extruded aluminum attach the ailerons to the aft wing spar outboard of the wing I Raps. The ailerons link to the control wheel through push-pull tubes and bellcranks. Lead counter-weights static balance the ailerons.
D
I
I
1. Aileron Removal and Installation.
A. Remove control tube and washer at aileron horn.
attaching bolt, nut, 12
~su
3
F
C. Remove aileron by pulling it straight aft until hinges are clear; rotate inboard portion down and forward to allow aileron balance weights to clear wing tip. D Rei~s&il deron in
re~se
E. Recheck bolts for
sec~ence of remc~d. and safety.
4
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L~
D
B. Remove bolts, nuts, and washers from the three attaching hinges.
2. Aileron
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AILERON/ELNATOR CONTROL WHEEL RIGGING
security
FIGURE 27-1
Rigging.
A. Level control wheels-
(A) (Fig. 27-1). rig-pins Jackshaft (C) (Figure 27-1)
B. Install 3/16 dia.
)1(:ta
(2) Bellcrank (E) (Figure 27-1) (3) Bellcranks (9) (Figure 27-2) (L.H. and R.H.) C. Adiust control tubes (J) (7) (Figure 27-2) (L.H. and R.H.) to position ailerons at 0 degrees to 2
o
degrees down D. Adjust remaining control tubes (F) II st (D) 2, (Figure applicable) in order to freely attach to the bellcranks and jackshaft. E. Remove rig-pins. F. Adjust aileron stops (8) (Figure 27-2) per the i following procedures: (1) Position travel board, GSE030003-200, ad
o
Q
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o
I I
o
W.S. 147.75.
(2) Adjust sWic position fmm 00 to 20 DOWN. (Ref. point is 00 mark on travel board. (3) DOWl\ltravel: 80 +/-10 from static position. (4) UP travel: 12.50 to 14.50 from static position.
7j SMM27-2
AILERON STOP ADJUSTMENTS 4-99
FIGURE 27-2 27-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
NOTE The above aileron rigging and adjustment instructions apply to both the left and right ailerons.
I
TRAVEL BOARD LOCATION STA. TRAVEL BOARD LOCATION 1/2´• ABOVE C/L OF RIVET ROW
‘P~B\
SKIN
LEVELING SCREWS
STA. 16~00 TRAVEL BOARD LOCATION 1/4´• OB Cn OF RIVET ROV
SKIN LAP
STA 147.75
TRAVEL BOARD LOCATION BETWEEN FLAP a AILERON
~V
SC(N27-4
A
TRAVEL BOARD LOCATIONS
RUDDER AND STEERING SYSTEM
27-2090
The rudder attaches to the aft vertical fin
5~427-3
RUDDER PEDAL ADJUSTMENT
FIGURE 27-4
at four
hinge points. Push-pull tubes and bellcranks link the rudder to the rudder pedals. A rudder trim system is incorporated into the M20M aircraft for pilot comfort for high power settings during climb and if needed for cruise power settings
FIGURE 27-3
1. Rudder Removal and Installation.
push-pull tube from rudder horn. attaching hardware at rudder hinges. Remove rudder by pulling it straight aft.
A. Detach rudder B. Remove
I
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SMX27-6
NOSE GEAR STEERING LINKAGE ADJ. 27-20-00
FIGURE 27-3 4-99
RUDDER 8( ELEVATOR TRAVEL ADJUSTMENT FIGURE 27-6
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
C ~J
D
D 2
=2
9
SMX27-8
SMX27-7 ELEVATOR HORN ADJUSTMENT RUDDER HORN ADJUSTMENT
FIGURE 27-7
at
D. Install rudder in reverse sequence of removal. Recheck attaching bolts for security and safety. 2. Rudder
Rigging
A. Raise aircraft
and
nose.
See Section 7-10-00.
11 turns OUT
as
position
stalling point.
(D), (Figure 27-7) rod end
Unclamp
I rudd
rudder
23
wall
ELEVATOR SYSTEM
1. Elevator Removal and Installation.
A. Remove push-pull control tube by taking attaching boits, nuts, and washer.
bolts
off all
B. Remove bolts, nuts, and washers from the four
attaching hinges.
K. Center
(1),
.014 inch reduction in diameter, the tube must be replaced.
Elevator construction is essentially the same as that of the ailerons. Both elevators attach to the stabilizer at four hinge points. Push-pull tubes and bellcranks link the elevators to the control yoke. Lead countennreights static balance the elevators. A lead bob-weight under the instrument panel refines aircraft handling in flight.
and secure;
bolt
or
27-30-00
IM~. (Fiaure 27-9~. so that and I~ft.
jam nuts,
Torque
NOTE
pedals.
all
to front.
Control tube wear allowables. If any portion of the control tube exceeds .007 inch wear per
NOTE On aircraft S/N 25-0824 6 ON steering stops (3) Fig. 27-5, should be adjusted so .020 clearance exists between adjustment stop (3) and gear truss assembly (4) (Figure 27-5) when rudder is at extreme left and right travel position. J. After
Rudder
to
NOTE Rudder bellcrank, aft tailcone, should be modified per SI-M2094. H.
rear
Tube Removal. The rudder be inspected thoroughly and replaced if any damage is found. Remove shield from front of cabin floorboard that covers torque tube. Remove attaching hardware from hinges and rudder pedal control rods. Carefully remove torque tube by Sliding out toward the right side of cabin and through cabin door. 3.
Adjust control tube (C) at tear tailcone bulkhead bellcrank, (Figure 27-6) approximately 12 turns OUT as a starting point. F. Adiust control tube
shown from
torque tube should
E.
bearing (2) 11 turns OUT as a starting point G. Adjust rod,end (H~ bearing (B) (Fig. 27-3) position Rudder 1 to the t;ght.
as
NOTE Measure rudder travel with travel board on rivet line at station indicated on travel board GSE 030005´â&#x20AC;˘100, and with longitudinal trim (stabilizer) set in the 0 degree position. Sta. 26.50 is located 3/4 in. above skin splice on vertical fin.
C. Clamp pilots rudder pedals (A), (Figure 27-3), in neutralpositioi~. D. Adjust rod end bearino i B, Fig.27-3)
approximati~ly
(2). Bolts, nuts and washers (5) and (6) must be
installed
Adjustment.
B. Set stabilizer trim control in neutral (stabilizer parallel with aircraft center line),
FIGURE 27-8
nose wheel by removing nut, washer (Figure 27-5), and adjusting ~steering linkage
C. Remove elevator to the
4-99
rear.
27-30-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
Elevator Stop limiter (E) clearances and positive
27-9).
may be bent to obtain with (P), (Figure
cont~ct
H. Rotate trim full down to check clearance of bellcrank at wing rear spar. Adjust rod end bearing at bulkhead if n~eded for clearance. rear tailcone Recheck elevator up and down travel. I. Rotate trim full up to check that up stop makes solid contact on stop limiter.
/E
J. Re-tighten all jam nuts, attach bolts and secure necessary; recheck all control tube clearances and travel limits.
R
o
as
0~0
RUDDER
o
-ELlPENNAGE FREE PLAY LIMITS
27-30-01
y TUBE
M ~JI
Allowable free-play movement of the empennsKle assembly on the fail~cone of the aircraft,â&#x20AC;&#x2122;with the tailcone fixed at the tail skid.
o
Tip:
Horizontal stabilizer P o
o
RUDDER
a
ELEVATOR
STOP
ELEVATOR O TUBE
ADJUSTMENT
0. Install elevators in reverse sequence of removal. Recheck attachina bolts for security and safety. Set elevators, R~LH, to be even with horizontal stabilizer. Adjust rod end bearings (9), Fig. 27-8, at elevator hem.
Rigging
and
Fore 6 Aft
0.10 inch
max.
Up
Rudder 0.08 inch
Lower max.
Up
Down
trailing edge: 8 Down.
(c) 27-31-00
Bolts and brackets
attaching empennage
to
-VARIABLE DOWNSPRING SYSTEM
hooked into the elevator control system in the tailcone refines the feel of the elevator in Right. A bellcrank and cable tailors the spring tension appropriate to the trimmed position of the stabilizer.
A,p,ing
fuselage structure.
B. Level aircraft and set control column in neutral with stabilizer parallel to center line of aircraft, NOTE Measure elevator travel from 0 degrees stabilizer thrust line with travel board positioned at stabilizer station 16.00 as indicated on travel board, P/N GSE 030004-503 and with stabilizer at 0 degrees. (See Figure 27-12 and Figure 27-4 for travel board
NOTE
Negative stabilizer degrees) settings mean that stabilizer leading edge is moved down relative to the thrust line.
placement. NOTE Elevator bellcrank, aft tailcone, should be modified per SI-M20-44.
N
(L),
D. Adjust elevator hom rod end OUT 7 or 8 tums as a starting
RH, (Fig. (9) LH point. E. Main spar adjustable rod end bearing is turned OUT approximatley 6 turns as a starting point; to obtain ~dditional el~vator travel adjust as re~quired. F. Set stops (P) (Figure 27-91, in empennage stinger for,elevator ulptra\iel of 22â&#x20AC;&#x2122;(+0/-2) and down travel of 22"(+0/-2). G. After stops (P 8 M) are set, rotate elevators
27-8)
thru full range i~f travel to~assure solid contact with stops and th-~t nuts and bolt heads clear stop limiter.
SM27DNSP VARIABLE DOWNSPRING
27-30-01
to
tailcone.
Adjustment
C. Adiust rod end bearings of control tube (Figure 21-6), at rear tailcone bulkhead,
the
trimscrew.
A. Adiust rod end bearina (3), (Figure 27-1)~ ,t control yoke (G) for control shaft (H) clearance from iirewall and control yoke and bob w~eight (P) clearance
from
max.
(1) if excessive free-play exists check following areas for wear: (a) TrimscrewjackshaA. (b) Trim link connecting empennage
FIGURE 27-9
2. Elevator
0.12 inch
4-99
FIGURE 27-10
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M 2790-00
TRIM SYSTEMS
2790-01
-STABILIZER TRIM SYSTEM/RIGGING
provide pitch trim control, the entire empennage pivots around its main hinge points. The system I consists of a manually operated actuator that operates a series of torque tubes and universal joints connected To
FWD
I to a jack screw on the aft tailcone bulkhead.
c
I
UP STOP
STOP7
I
NOTE
"stepped stop nut", with a "jam nut" configuration has been incorporated, This can A
E
be retrofitted to all M20M aircraft, if desired. This allows trim screw nut (F) (Fig. 27-11) to contact stepped portion of these two nuts and not bind.
I
B~
8
Rigging
1.
SM27-TRIM STOP
TRIM CONTROL ACTUATOR RIGGING
FIGURE 27-11
A. Nose Down Stabilizer Trim Control
and
Rigging
Rigging
Adjustment.
(1) Loosen setscrew in stopljamnut (A) (Figure 27-11), break torque on jam nut/stepped nut (if installed) and turn stop (A) or jamlstepped nut (A E) clockwise or counterclockwise to align aft edge of stop
Spring System A. Set stabilizer at maximum positive setting and elevators full down. (Figure 27-10 B. Adjust turn buckle for a 14.0 to 16.0 Ib. tensiometer reading on cable. C. Check for positive clearance between cable end and pulley sheave. Tensiometer reading should be 20 1.
System
The basic rigging, for either configuration, is identical to procedures below except that stepped nut and jam nut require being torqued together with two wrenches prior to jam nut set screw tightened against threaded trim screw. Stepped nuts are required at the nose up and the nose down positions facing trim screw nut (F);
I
F
Stabilizer Trim
Variable Down
jam/stepped nut (A&E) with last thread of trimscrew (C) (Figure 27-11). Tighten setscrew and turn trim control wheel to full NOSE DOWN position (trim screw ,,t (F) against stop (A) or stepped nut (E). (2) Disconnect torque shaft (B) from trim screw (C), (Figure 27-11). (3). Turn disconnected torque shaft (B) clockwise
Ib. maximum.
or
counterclockwise
until
horizontal
stabilizer
measured, using the travel board, P/N 030004-503, shown
by (Figure 27-12),
+3.80 to
is within the
following
as as
limits:
+4.2â&#x20AC;&#x2122;.
NOTE Positive degrees) stabilizer degrees mean that stabilizer leading edge is moved up relative to thrust line.
(4) Connect torque shaft (B) to trim screw (C) (Figure 27-12). NOSE DOWN stabilizer trim control rigging is now complete. B. Nose Up Stabilizer Trim Control Rigging and Adjustment. (1). Loosen setscrew in stop or jamnut (A) and turn stop(s) on threaded shaft to move it toward the screw gear box. Turn trim control wheel toward NOSE UP position until horizontal stabilizer is within the following limits: -6.50 to -7.00
trim
NOTE stabilizer (-degree) settings mean that stabilizer leading edge is moved down relative to thrust line.
Negative B SM27-il
ELEVATOR TRIM ADJUSTMENT
1
FIGURE 27-12
4-99
(2) Rotate UP stop or stepped nut (E), (Figure 27-11) clockwise or counterclockwise to make contact with trim screw nut (F). Tighten setscrew. NOSE UP stabilizer trim control rigging is now complete. 27-40-00
OLDWILLWAYNE
â&#x20AC;&#x2122;JY
y\
21+/- 2 inch Ibs.
(2) l<AP 100 (3) KFC 150 (4) EDO AIRE (5) S-TEC
1
WHEEL ASSEMBLY
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
1
21+/- 2 inch Ibs. 18 inch Ibs. -30 inch Ibs.
5. Stabilizer Trim Chain
Adjustment. (Reference
Figure 27-13). A. With four mounting bolts (1) slack, adjust two NAS423-3-4 bolts .(2) to obtain maximum ten~sion on chain without causing binding.
RUDDER TRIM SYSTEM/RIGGING
27-40-02
1. Rudder Trim
FLOCIRBCIARD
I
7
2
STEPPED STOP NUT
0~
I
A.Aiacrdt should be liisltt tested aK1 tir#ed for t~erd a~ecsond trin pior.t~ ~iggâ&#x20AC;&#x2122;ng ~flhe Nddertrin s~8twn. B. Jack aircraft
I
U
JAM NUT
i
\L r
GEAR ASSEMBL
Rigging
Rudder Trim consist of an electric actuator driving a capstan/balancing bellcrank and spring system to compensate for engine/propeller forces during long climbs or takeoff power.
nose
(S~e S$ctibn 21-60-00)
D. Deflect and lock rudder at 100 left Use Rudder Travel Board GSE 0300005.
battery
Adjust stabilizer trim
to FULL DOWN
B. Adjust potentiometer on trim wheel to illuminate bottom bar on ir;dicator.
position. assembly, ACTUATOR UMIT SWITCH
846
F. Adjust R1 on 41D board to illuminate top bar on I display. G. Repeat steps B through F until no furtherl adjustmentsare required. H. Re-install and secure display indicator into instrument panel.
NOTE When removing trim screw from empennage, use block of wood cut to fit opening between tailcone and empennage to prop empennage up when trim screw is removed.
torque for the electric trim system should adiusted for the following settings to operate
autopilbt systems properly:
27-40-02 10
TURNBUCKLE SMM27-14
FIGURE 27-14
NOTE The following steps are easier to accomplish if the actuator assembly is removed from the aircraft but they can be done while actuator is in its normal operating location.
A. Clutch
200
\CABLE
RUDDER TRIM RIGGING
3. Electric Trim.
(1) KFC
access cover (left access to
CAPSTAN
C. Run stabilizer trim to FULL UP position. D. Top bar on display indicator should be illuminated: If not illuminatdd ~djustment to R1 resistor inside indicator housing is necessary. E. Remove indicator from instrument panel. Leave harness connected. Pull indicator down as far as possible to allow removal of housing covet and access to adjustment.
be
position.
side~ and aft fiberglass bs!ly panel to gain rudder trim actuato~r assemoly.
2. Stabilizer Trim Indicator Rigging. The indicator is connected to the trim control wheel assembly to indicate stabilizer position relative to the aircraft thrust line.
A.
ground.
C. Aileron-rudder interconnect system shall be riaaed properly Drier to rigging of rudder trim system.
E. Remove tailcone 27-1
wheel off
F.
Electrically
(depress
21+/- 2 inch Ibs. 4-99
left
run
sides
actuator for left rudder deflection of both RUDDER TRIM split
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
switches)
until limit switch turns OFF actuator motor.(Aft limit switch is for LEFT rudder trim).
M. Verify that required number of threads screwed into~both turnbuckle barrels.
G. Wrap cable around capstan five full tums with forward eye of cable ending up 12 inches from forward circumfer~nce edge of capStan (See Figure 27-1e). .Aft end of cable win be in proper location for naglnn
N. Remove spring extenders from both springs. Remove tape from cable and capstan and rudder lock from ruddei.
procedure. Temporarily
secure
O. The rudder should be "neutral" at 3 to rudder.
cable/capstan poi5ifio~
uang several wraps of suitable adhesive tape around cable and capstan.
t, position right rudder at 23’. recheck right rudder deflection.
Q. The TRIM LIMITS RIGHT.
Rudder trim actuator assembly will need to be re-installed at this time, if it was removed to accomplish the preceding steps.
the
3 to
are:
2. Rudder Trim Indicator
system and
50 LEFT; 230
Rigging
A. Use rudder trim switch in aircraft to trim full right.
I. Attach one end of both springs to brackets on Stations 90.0 and control tube bellcranks at 142.0.
Fusel~ge
8. Adjust
run
rudder
potentiometer on motor/cable assembly right bar on display.
to illuminate far
J. Separate barrels and eyes of both turnbuckles and attach one eye of turnbuckle to fonnrard spnng; screw proper end of turnbuckle barrel to eye from 2 to
C. Use rudder trim switch in aircraft to run rudder adjust R1 on A/D rudder trim board (see Figure 27-14A) to illuminate left bar on display.
trim full left and
5 turns.
no
further
E. Remove rudder travel board; re-install and belly skin.
access
D.
K. Start turnbuckle eye attached to forward cable end into barrel. Tighten turnbuckle barrel until tension JUST begins on spring.
Repeat
steps
adjustmenf isrequired.
the aft spring and
A
C
through
until
cover
F.
Flight
PIN
~RSI
PINI AO
Cycle
R. Secure aft tumbuckle and make sure there is no interference between rudder trim mechanism and Right control tubes or bellcranks during cycle or full traveTof Right control surfaces.
NOTE
on
50 left
P. Electrically run actuator for right rudder deflection. The actuator motor should stop when rudder is deflected 2j’) right. If not, slightly bend the forward limit switch’s (RIGHT 5Cldder stop~ a~tuator arm
H. Extend and secure both springs to 9.8 inches inside measurement between hooks. Insert spring extender, P/N GSE 030035-501, end caps into spnnn coils so that the 9.8 inch dimension is maintained. Place the spacer, P/N GSE 030035-005 over spnng coils and secure to -503 assembly with MS3367-1-9 straps. Two spring extenders, GSE 030035-503, are required for rigging procedures.
L. Repeat steps I. through K. cable end.
are
U’p, r~
test aircraft. The rudder trim shall center the tum coordinator ball with no .pilot application of rudder dunnn fun’oower climbs at 105 KIAS. If it does not, gain access to forward tumbuckle and tighten for an additional .25 to .38 inch extension of
Secure
forward forward G.
access ReDlace and repeat Right
cover(~ check
F3.D O.
O
In
entry
step 20.
log book aircraft to complete any maintenance
Complete
H.
and
seMce
rema~nlng action.
or
return
O RUDDER TRIM INDICATOR ADJUSTMENT 4-99
FIGURE 27-14A 27-40-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
6. If bearing block assembly replacement is required, refer to following procedures: Trim torque tube/pitch trim servo assembly should be removed from aircraft to replace bearing block,
StabilizerTrim System Troubleshooting
27-41-00
Check control tubes at bulkhead grommets for rub marks. Check Trim Actuator threads for
BINDING
galling ELECTRIC CLUTCH SLIPPING
or not
therefore manual trim wheel and electric trim switch should be flagged so inadvertent movement will not
lubricated, lubricate
occur.
per Sect. 5. Check BINDING symptoms above, Check for proper c[utdh settings. Confirm full bus voltage is avail. at trim motor.
A. Disconnect tailcone bulkhead,
assembly mounting
universal Sta. 142, brackets.
B. Disconnect electrical
joint and
wiring,
located between pitch trim servo to servo
motor, at
connector.
C. Disconnect ELT harness from connector and any other wiring that may interfere with the removal of torque tube assembly froin tailcone.
NOTE Maximum wear on trim tube, where it passes thru bulkhead grommets, is.007 inch per wall or.014 inch diameter.
D. Remove nuts, washers, bolts/screws from upper and lower pitch trim servo brackets holding bracketS to bulkhead.
-ELECTRIC PITCH TRIM SYSTEM MAINTENANCE
27-42-00
MOONEY AIRCRAFT CORPORATION
M20M
E. Carefully lift torque tube/pitch trim servo assembly up and pull aft end of torque tube from trim actuator socket on aft tailcone bulkhead. Support aft
If installed, the AlliedSignal (Bendix-King) Electric Pitch Tn’m System requires periodic maintenance at each annual inspection for cam’er bearing added to existing aircraft pitch trim torque tube. If not already installed, an annual service placard, 057-05747-0001, ~vailable from Al\iedSignal) MUST be added to the Electric Pitch Trim servo bracket area to call attention to the annual maintenance requirement Carrier bearing assembly must be inspected and lubricated per the following procedures:
end of torque tube if needed.
Pull
F.
tailcone
servo assembly from access cover on left side of tailcone.
torque tubeArim
through
G. Place torque tube/pitch trim servo assembly on work bench for removal and replacement of bearing block. H. Remove components carefully until access to is obtained. Install new bearing block and assemble in reverse sequence. I. Reinstall torque tube/pitch trim servo assembly into tailcone.
bearing block
1. Gain access to area
by removing electrical bay from left hand side of tailcone. Locate Electric Pitch Trim servo system, just aft of Fuselage Sta. 142 bulkhead. Carrier bearing is located around existing pitch trim torque tube, aft of lower chain sprocket, on aft side of electric pitch trim servo bracket and below electric pitch trim servo motor. access cover
J.
After
reinstallation
and
reconnection
of
all
components, electrical and ~mechanical, it will be essential to check stabilizer pitch trim system rigging in
accordance with Section 27-40-01.
-WING FLAP SYSTEM
27-50-00
Loosen electric pitch trim servo drive chain. Remove four lock nuts which secure carrier bearing block to aft side of electric pitch trim servo bracket. Slide bearing block aft until it is clear of stainless steel sleeve which is secured to existing airplane pitch trim 2.
Push-pull tubes and bellcranks interconnect the flaps. The flaps are operated by an electrical motor driven actuator (1) connected to a jack shaft (2). The jack shaft is connected to actuator bracket (3) (Figure 27-15) on each flap just outboard of hinges (4) by a push-pull rod end bearing (5) and hardware. Each flap pivots about four hinges. Travel is controlled by limit switches (6) and (7) and UP stops located at ou~board
torque tube. 3. Carrier bearing can now be inspected. If carrier bearing or torque tube sleeve show evidence of scoring or wear, replace damaged items with new parts. Bendix-King P/N’s are:
hinges (Figure 27-15). Flap position is indicated in the cockpit through an electrical potentiometer (8) connected to the jack shaft actuator horn (9). The flap switch is S/N 27-0001 THRU 27-0107 self centering from the down position and located on the console adjacent to the flap position indicator. The flaps can be retracted completely by placing the switch in the up position or to any setting between 0 and 33 degrees by holding in up position to setting desired and then centering to stop the actuator.
BEARING BLOCK ASSY. 047-04143-000 TORQUE TUBE SLEEVE 076-00971-000 ROLL PIN (for torque tube sleeve) 090-00052-0022
scoring or wear is not present, clean any dried grease andlo~r dirt from bearing and torque tube sleeve. Relubricate, using MIL-G-23827 or MlL-G-81322 grease. Use a grease needle or other suitable tool to When
apply grease. bearing to aft side of electric bracket. Re-tension drive chain,
4. Reinstall carrier
trim
servo
Lubricate the actuator gear box and ball screw at intervals with lubricants prescribed in Chapter 5.
pitch
S/N 27-0108 thru 27-TEA
5. Clean any dirt and grease from placard location on forward side of tailcone bulkhead. Install annual service placard (057-05747-0001) on forward, vertical portion of bulkhead, fuselage Sta. 142.
27-41-00 12
4-99
incorporates
a
be activated
as
The flap system preselect feature which allows flaps to
desired, UP, TAKEOFF
or
DOWN.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 1.
Wing Flap A. Remove
push-pulltube. B.
M20M
Removal and Installation.
wing flap hinge fairing
Remove bolt, attachment.
nut,
and
washer
B. Holding both rudder and aileron controls in neutral position, install springs P/N 110003-007, between 110002-005 bellcrank a~tach point and both stops. Position each stop on 915031 rudder control tube so that installed length of each spring is 4.90 in.
flap
to expose
from
flap-actuating
C. Remove bolts, nuts, and washers at
SERVICE AND MAINTENANCE MANUAL
flap hinge
points. D. Remove
flap by pulling it down and aft. E. Install wing flaps in reverse sequence of removal. Recheck security and safety of attaching
bolts. 2.
Wing Flap Rigging
and
Adjustment.
NOTE Flap deflections are to be measured with travel board GSE 030003 at the station indicated on the travel board. (See Section 27-20-00,
Fig. 27-5) S/N 27-0001 THRU 27-0107 at rod end of Retiact flaps to 0 degree (+1-2 degree~; set flap outboard travel stops (ndt illuStrated) so that flaps align with ailerons in
A.
Adjust right and left inboard linkage ure
neutral
27-16) to obtain
a
Ra~ deflection
position.
g
B. The limit switches, #6 8 7, should be adjusted so that under actuator over run will not allow the either up or down position limits. S/N 27-0108 THRU 27-TEA
I ~k
Q~jl
(Fi9ure 27-15)
fligh~f loads flaps
the
to exceed
j
I Verify flap travel is per 2. A. above. TAKEOFF to +I-lq. (10" flaps position C. Adjust switch stack until Bottom Micro-Switch
â&#x20AC;&#x2122;cC~
A.
Sb[L127-15
B. Extend
just opens. D. Top switch will be automatically adjusted. E. Cycle flaps UP TAKEOFF 8 DOWN; verify proper s~ttings atTAK~OFF when traveling from full up position.
Verify step 2., B. above is correct. 3. Wing Flap Indicator- Rigging A. Position flaps in full DOWN position. B. Adiust flap potentiometer (8 Fig. 27-15)
FLAP ACTUATOR ASSEMBLY FIGURE 27-15
INSTALLATION
~1
F.
FWD on
aircraft to illuminate bottom bar. C. Position
flaps
in UP
I
position.
D. Adjust R1 on A/D board (see illuminate ~op bar of flap display.
Figure 27-17)
to
I C
E. Repeat steps A throuah D until no further adjusbnent is required to depictiull d~wn full up. 27-60-00
h I
-AILERON/RUDDER INTERCONNECT
ooci~
SYSTEM The aileronlrudder interconnect system assist in coordinated maneuvers and reduction of adverse yaw during turns. The system is connected through springs to allow override of either control movement when
input separately. 1. Aileron/Rudder Interconnect
System
Rigging
SMX27-14
A. With rigged controls in neutral position, oosition 110002-101 on LH. center ailâ&#x20AC;&#x2122;eron control link, so the end of 110002-005 bellcrank assembly (round end) will be 7.25 in. AFT of 310020-3 fuselage former.
WING FLAP ADJUSTMENT 4-99
FIGURE 27-16 27-60-00 13
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
optional equipment), and light assembly installed.
O1N 8,
rudder
taillight and/or strobe
Control surfaces must be rebalanced in accordance with the procedures in Section 27-93-00.
B1N
I
B
MOONN AIRCRAFT CORPORATION
M20M
R81Q
CAUTION All control surfaces should be
PIN 7
stripped prior to
repainting.
I I R5
I R7
QIR1C)I
a
design of the balancing fixture is not critical providing the requirements of this section are met. 1. Obtain or otherwise fabricate two (2) knife edge supports approximately one (1) foot in height so that they can be placed on a table and be stabilized to prevent tipping (See Fig,27-18). The knife edge hinge
8
IC1
IC2
CITATS-TNEMPIUQE
The
R
~l*e
BALANCING
27-92-00
PIN 3
I
supports MUST be LEVEL and PERPENDICULAR to the
’hinge axis of the control
Weight Scales: Scales used to record 0.02 Ibs or 112 oz.
surface.
2.
WING FLAP INDICATOR ADJUSTMENT FIGURE 27-17 C. Clamp stops 8 bracket in place. Drill throuah stops 8 bracket and into each control tube for AN~30-4R6 PK screws. Make sure PK screws are in place to secure the two stops and the one bracket. 27-90-00
-MISCELLANEOUS
27-91-00
CONTROL SURFACE STATIC BALANCING
weights
must be accurate within
27-93-00
BALANCING PROCEDURE 27-93-01 DETAIL PROCEDURES BALANCING
1´• A line drawn through the hinge line support points must be level and perpendicular to the supporting knife
Control surface balance must be checked when control surfaces is repaired, altered or repainted. It is recommended that control surfaces be stripped prior to repainting. The control surface balance limits shown in Figure 27-19 apply to a complete painted control surface only. Complete control surfaces include las applicable) balance weight, control attachment horn and attaching hardware, static wicks (when installed as
edges. 2. The supporting knife edges must be horizontal and to each other within the requirements of step 1.
parallel above.
Ailerons
NOTE balanced up-side down knife edge supports.
are
on
3. Elevators and rudders KNIFE
I with the "Control
I TI
EDGE
SUPPDRT
STATIC
Horn"
are
balanced
pointing upward.
4. All control surfaces are balanced with the hinge center line and the tip rib chord line level. Two tooling holes are located in the tip ribs and are on the rib chord line (rib center line). Chordwise level can be obtained by using a spirit level and pins inserted into these tooling holes.
~8/
a 1/4 inch bolt or pin through inboard and outboard AILERON hinge bracket. Install a No. 10 bolt or pin outboard and inboard through ELEVATOR hinge bearing, and top and bottom RUDDER hinge bearing.
5. Install
the
TRAILING RESTING
EDGE SUPPORT
1
tOPTIoNAL)
6. Positon and level the control surface on
SMJ27-16
CONTROL SURFACE STATIC BALANCE DIAGRAM FIGURE 27-18 27-90-00 14
4-99
edge hinge supports. Accurately measure control
the knife
surface load at a measured distance from the hinge axis as far from the hinge axis as possible (Figure 27-18). Measurements draft in free be taken should a 7.
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
M20M
environment. Calculate the moment (arm times and compare the results with Figure 27-19.
SERVICE AND MAINTENANCE MANUAL
weight)
8. Control surfaces MUST BE RECHECKED for balance after any painting, stripping, repair or alteration.
NOTE
RE 27-21 NOT USED.
SURFACE DESCRIPTION
IAIRCRAFT EFFECTIVP(
BALANCE MOMENT LIMITS
430026-507 8( -508 ELEVATOR
27-0001 THRU 27-TEA
UNDERBALANCE 11.00 IN.
460043-507 RUDDER (UPPER LOWER WEIGHTS REQD.
27-0001 THRU 27-TEA
UNDERBALANCE OVERBALANCE
1.50 IN. 5.00 IN
TO
230015-509 AILERON
27-0002 THRU 27-0024, 27-0026 THRU 27-0069
UNDERBALANCE OVERBALANCE
1.40 IN. 5.00 IN.
TO
27-0001, 27-0025, 27-0070 THRU
UNDERBALANCE OVERBALANCE
1.00 IN. 5.00 IN.
TO
1.00 IN. 5.00 IN.
TO
I TO
8.50 IN.
-510
27-TEA
NOTE: Al RCRAFT SERIAL NUMBER 27-0002 THRU 27-0024 AND 27-0026 THRU 27-0069 MAYIUNDERBALANCE BE IN COMPLIANCE WITH I OVERBALANCE SERVICE INSTRUCTION M20-94. IF SO, USE BALANCE MOMENT LISTED IN COLUMN TO THE RIGHT.
*UNDERBALANCE IS TRAILING EDGE HEAVY. OVERBALANCE IS NOSE HEAVY.
M20M FLIGHT CONTROL SURFACE BALANCE LIMITS
DISIAI\ICE (Re-fer
to
AFT
Figure 27-17
(NOIE:
Aileron
is
ior
OF
HIIUGE
dimensions
8c
FIGURE 27-19
LIIUE UNBALANCE
limits)
upside down.)
ba anced
FORCE
DISTANCE FROM HINGE POINT TO UNBALANCE POINT CONTROL SURFACE TRAILING 27-94-00 If specified moments cannot be met (reference EDGE can be Figure 27-19), heavier balance FIGURE 27-20
o~btained
weights
thi´•ough
Service Center. This approach should be examined before reworking any repair or restripping and repainting the affected control surface. A linhter weight can be produced by shaving existjng balance weight. a
Mooney
NOTE
Verify flight control rigging is correct bending trailing edge. 1.
A special pair of widenose vicegrip be used to bend the trailing edges as
Trimming.
pliers
are to
necessary A.
(See Figure 27-22).
Aileron.
condition, correct for a aileron trailing
4-99
before
To
correct
aileron
for
left wing-heavy a trailing edge down; to
condition,
bend
left
27-94-00 15
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ADJUST UP TO ACTUATE SOONER .070
MAX.
IPOWNWARD
ALLOWABLE OEFLECTON
AILERONS Q~
IO
.08 MAX. ALLOWABLE DEFLECTION LEFT OR RIGHT
8
1
1 ADJUST DOWN TO ACTUATE LATER
RUDDER TRAILING EDGE TRIMMING
FIGURE 27-22
STALL VANE ADJUSTMENT
NOTE NEVER TRY TO ADJUST THE SWITCH BY BENDING THE VANE. This part has been heat treated and cannot be bent without damaging or breaking the vane or switch.
NOTE The aileron trailing edge MUST NOT BE BENT UP under any circumstance. Any deformed rivets must be replaced after trimming aileron or rudder trailing edge. B. Rudder. The rudder trailing trimmed right or left as required
edge may
a rule of thumb, moving the vane tip 1/4 inch will change the time the stall waming actuates by about 5 mph ~ofindicated air speed. The only way to test the accuracy of the setting is to fly the airplane into a stall, noting the speed at which the warning hom comes on and the speed at which the full stall occurs. The stall must be made in various configurations, clean, gear and flaps down and power on and power off. It may be necessary to make several alternate adjustments and test flights before the desired setting can be reached. The stall warning should actuate at no less than 5 KTS. nor more than 10 KTS. preceding the stall and shall
As
be
C. Elevator. A full span tab is built into each elevator trailing edge and is fixed 7 degrees 1/2 degree trailing edge down. No further tolerance is allowed. 27-95´•00 1. Stall
A. access
STALL WARNING MAINTENANCE PRACTICES
Warning
Switch Removal.
Remove the screws or rivets attaching the cover aft of the switch on the lower wing
until in stall occurs the power off The rate of speed reduction shall not exceed one knot per second with the airplane trimmed to 1.5 times the stall speed. The switch setting should be checked and adjusted as necessary whenever a wing or wing leading edge is replaced or extensively repaired, or if a new switch is installed. The switch should require no adjustment in normal service. continue
surface.
B. Remove the two adiustment the switch to the wing leadii~g edge.
screws
configuration.
which hold
C. Disconnect the two wires from the switch. 2. Stall
Warning Switch
Installation.
A. Connect the electrical wires to the switch. B. Position the switch in the opening of the lower
wing leading edge, install the two adjustment C. Replace the access cover securely.
screws.
D. Adiust the switch. See STALL WARNING INDICATION SYSTEM ADJUSTMENT. 3. Stall Warning Indicating System Adjustment (Figure 27-23). The stall warning switch is adjusted when the airplane is test flown at the factory. Should it require readjusting, proceed as follows: Locate the switch installation on the under surface of the left wing leading edge and loosen the two phillips head screws,
either side of the vane. If the stall warning has been activating too early, pull the vane back and down. If the stall warning has been activating too late, push the vane up and forward. Moving the vane with the phillips head screws loosened moves the entire unit up or down inside the wing, causing the switch to be closed earlier or later. Re-tighten the screws after making each adjustment. one on
27-95-00 16
FIGURE 27-23
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 27-95-01
TROUBLE SHOOTING
TROUBLE
STALL WARNING SYSTEM
Warning tripped. Open
Hom continues to blow.
Check for
circuit.
waming
hom
Replace
switch.
warning
horn.
Replace
hem.
Defective switch.
warning horn
Replace
switch.
Every procedures
1. Remove speedbrake Section 27-96-01,1.
E. Clean 8 loosness.
or
C. Remove D. Remove
cartridge slot.
from top of
wing around top
1.
inspect
all
moving parts. gear (Aeroshell No.7). for damage, corrosion, 8 on
worm
unit
Placards
in
are
place.
TROUBLESHOOTING GUIDE
Cartridge
Fails to
Operate.
B. Check
cannon
plugs for security.
C. Check cannon plug, wiring, reference Dwg.
2. INSTALLATION
procedures.
2. Cam
(1) Leave attachment screws loose until proper alignment of cartridge to slots in wing is verified. (2) Tighten all screws. (3) Test operation of Speed Brakes on the ground to assure there is no binding either up or down. Air loads on Speed Brakes can cause a slightly different alignment during deployment, therefore it is a
8
A. Check Circuit Breaker
E. Slide cartridge forward to start mount strap bottom hole; slide cartridge out from bottom df
recommended that
worm
Verify proper
27-96-03
of
through wing.
A. Reverse removal
hardware
H. Inspect pulleys ton vacuum units) for any wear damage. 2. Report any deficiencies to Precise Flight, Inc. 3. Reinstall Speed Brakes into wing in accordance
4´•
from bottom of wing j,,t ,ft of mount strap to bottom of wing.
screw
screws
mounting
with Section 27-96-01, 2.
the electrical connector
cartridge holding
in accordance with
F. Manually operate the speedbrake doors and feel for smooth operation, both exfending and retracting. G. Inspect cable ton vacuum units) especially around pulleys for fraying.
wing,
B. Disconnect either the vacuum line connection on the cartridge.
Visually inspect for chafing
D. Lubricate
or
from under side of
maintenance
B. Check drain tubes for debris. C.
is
1.REMOVAL
panel cartridge.
cartridges
A. Visually inspect doubler and fo’ Structrual Integrity.
SPEED BRAKE CARTRIDGE REMOVAL AND REPLACEMENT
the
SPEED BRAKES
hours the following are recommended:
200
Schematics located in envelopes, and the electrical component parts list, Section 91 of this Service 3 Maintenance manual, cover the electrical system component identification and electrical connections.
access
MAINTENANCE
27-96-02
The relay for the Electric Speed Brake System located under the rear seat area, on LH bulkhead.
A. Remove
continuity.
Defective switch Defective
SPEED BRAKE SYSTEM
directly beneath
If circuit breaker persist in tripping, check for grounded circuit.
circuit breaker
The speedbrake system is currently installed in all M20M aircraft standard The as equipment. manufacturer, Precise Flight, Inc., can provide detail parts and maintenance information for the cartridge assembly. Some of the electrical circuity wiring, relays, C/B, etc. are installed by Mooney. These Mooney components are available through your Mooney Service Center.
27-96-01
REMEDY
PROBABLE CAUSE
Warning system inoperative.
2786-00
SERVICE AND MAINTENANCE MANUAL
M20M
P/N 01726, for correct Precise
Flight.
Electrical Units
Adjustment Speedbrake for squareness.
A. Check
Turn aircraft electrical power OFF.
B. With 5/64 Alien wrench, loosen desired cam set still has friction. (AFT cam is for retract position/FWD cam is for deployed position)
screw so cam
C.
Adjust
1/4 inch
TEST FLIGHT be done to test
so
AFT cam to actuate microswitch 118 to microswitch clicks before door is fully
retracted.
operation of Speed Brake System to verify proper operation. Readjust alignment of cartridge to wing slots until proper operation in flight is obtained.
D. Adjust FWD cam to actuate microswitch inside door edges are parallel when fully deployed. E.
Actuate
adjustments. F. Tighten 4-99
speedbrakes electrically
to
so
check
Set Screws.
27-95-01 17
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
27-96-03 18
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
FUEL
OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 28 FUEL
TABLE OF CONTENTS CHAPTER SECTION
28-00-00 28-00-01 28-1 0-00
PAGE
SUBJECT
SUBJECT
5
General.
FillerCap Storage
5
Maintenance
6
28-11-00
Fuel Tank Field
28-12-00
Fuel Tank Leak
6
Repair Repair
8
Bubble Fluid Formula
28-13-00
Soapless
28-14-00
Fuel Additives
Preparation 28-20-00
for Leak Check
10
10 10
Distribution
Pump
Removal and Installation
10
28-21-00
Fuel Boost
28-22-00
GascolatorScreen
28-23-00
11
28-24-00
Cleaning Injection System Engine Priming.
10
Fuel
28-25-00
Fuel Selector Valve Removal and Installation
11
28-30-00
11
Dump
28-31-00
Fuel
28-32-00
FuelVents
28-40-00 28-41-00 28-42-00
Fuel
28-43-00
Fuel
28-43-01 28-43-03 28-90-00
System
11
Drains
11 11
Indicating Fuel
11
Transmitters.
Quantity Indicating Quantity Indicator. Quantity Adjustment Procedure Fuel TankTransmitterAdjustment Fuel Quantity Gauge Adjustment
Miscellaneous
11 11
12 12 12 14
28-91-00
Trouble
14
28-92-00
Flared
14
Shooting Fittings
28-CONTENTS
3/48LANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 28 FUEL
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT
a&Effectivity. aS-Contents
PAGE
1/2BLANK 3/4BLANK
DATE 4-99 4-99
28-00-00
5.
4-99
28-10-00
6.
4-99
28-11-00
7.
4-99
28-12-00
8.
4-99
28-12-00
9.
4-99
28-13-00
10´•
4-99
28-23-00
11.
4-99
28-43-00
12.
4-99
28-43-03
13´•
4-99
28-90-00
14´•
4-99
28-92-00
15´•
4-99
28-EFFECTIVITY
1/2BLANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 28-00-00
M20M
-GENERAL
MOONEY AIRCRAFT CORPORATION
low-point drain, through the emergency pump to the engine-driven fuel pump and to the fuel injector system on the engine. Fuel quantity indicators are electrically operated with 2 transmitters located in each tank.
Internally sealed, integral fuel tanks are in the forward inboard sections of the wings. Fuel feeds from either tank to a selector valve thru a gascolator, with a
’t’~AECE
INDICATOR
L-
r-----
R FUEL
MEiEij~NG SYSTEM GASWLLATOR
FUEL DISTRIBUTION SYSTEM
FUEL
ELEC~ FUEL
ENGINE DRIVEN
PUHP
m~UcER
FUEL
I(()IPN~
V~NE
TOR
FIREWALL
oUT’ET DRAIN
FUEL SYSTEM
28-00-01
2 PLACES
VALVE (I EACH TANK>
FUEL FILLER CAP ASSEMBLY MAINTENANCE
2 PLA(XS
FIGURE 28-1
WARNING Water
can
fitting
Fuel filler port cap assemblies should be checked
enter the fuel tank
or
damaged
corrected
periodically for proper sealing and should be serviced occasionally to prevent hard to open or close
through
a
loose
cap. This should be
as soon as
possible.
3. The sealing capability of each cap assembly should be checked periodically and at each annual inspection. This can be accomplished per the following
conditions. 1. The o’ring seal (1) (Figure 28-2) around the cap assembly should be kept clean and free of dirt or grit that might cause abrasive action on seal or mating flange. Occasional lubrication with petroleum jelly or Tri-Flow will keep the o’ring soft and pliable. 2. The shaft (2) running through the center of the cap housing, that actuates the rotating lock plate (3) should be lubricated occasionally with Tri-Flow, or equivalent, to prevent binding while opening or closing the cap assembly. This should also lubricate the o’ring (4) that
procedures: A. Remove cap assembly from wing filler port and inspect o’ring (1) for damage, cracks or brimeness. Remove and replace if needed. B. Adjust tension of shaft (2) and rotating lock plate (3) by removing cotter pin (5) from nut (6) on threaded portion of shaft (2). Tighten nut (6) so cap assembly handle (7) can be opened, turned and shut with hand
pressure and still provide the necessary seal assembly to keep water from entering fuel tank.
seals this shaft,
4-99
of cap
28-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
1.
7
Approved
Materials.
A. Sealants. WARNING Sealants are safe only when handled with reasonable care. Avoid ingestion and all contact with the body, especially with open breaks in the skin. Wash hands before eating or smoking. If accelerator contacts the skin, flush area with warm water.
PR1422-A-1/2 or A-2 or (1) Brush sealant CS3204 A-1/2, A-2 or Pro-Seal 890-A (MlL-S-8802D Class A).
(2) Filleting Compound PR1422 8-1/2, (MlL-S-8802D Class B).
8-2
or
CS3204 8-1/2, 8-2
~s
(3)
r3
Removable
PR1403-G-B2
or
access
PR1428-8()
or
panel sealant CS3330-B(
(4) Protective sealant PR1005-L or CS3600, (MlL-S-43838). B. Gloves- Polyethylene C. Metal cleaning solvent Turco 657 wipe solvent. D. Cheese cloth.
~6
57
E. Turco leak detector PR
or
bubble fluid.
F. Methyl ethyl keytone (MEK) (thinner for 1005-L). NOTE
Approved materials may be obtained from your local Mooney Marketing or Service Center.
SMX28-2
Sealants may also be obtained from
FUEL FILLER CAP ASSEMBLY MAINTENANCE FIGURE 28-2
Products Research Co., 5454 San Fernando Road, Glendale, CA. 91209;
NOTE Fuel selector should be in the OFF position before proceeding with paragraph Cto pressurize the fuel tanks.
or
Chem Seal
Use
only
psi)
2.
STORAGE
28-11-00
FUEL TANK FIELD REPAIR
Handling and Mixing Sealants.
(1) Application life is the time that the mixed compound remains suitable for application. Application life ratings are always based on standard conditions of 75 degrees F. and 50 percent relative humidity. For every 10 degree F. rise in temperature, application life and cure time is reduced by half; for every 10 degree F. drop in temperature, application life and cure time is doubled. High at the time of mixing slightly reduces the sealant application life. (2) Maximum unopened container life, with
This paragraph outlines the procedures recommended for repair of the integral fuel tanks. Tank repairs should not be attempted until these instructions are fully understood. Refer to Service Bulletin SE M20-230 during resealing of tanks,
28-10-00
Compton,
A. Sealant Material Characteristics.
of air
28-10-00
Sun
or
Coast Pro-Seal, 19451 Susanna Rd., CA 90221
C. Connect rubber hose to each tankâ&#x20AC;&#x2122;s vent line. Apply ONLY one-half pound (112 psi) air pressure. Check for fuel cap leaks by soaping circumference and shaft area of filler cap assembly and observing bubbles. Replace oâ&#x20AC;&#x2122;ring if bubbles are observed and adjustment of the nut does not stop the leak. CAUTION one-half pound (0.5 pressure in tank.
Corp., 11120 Sherman Way, Valley, CA. 91352.
sealant at 80 and
4-99
degrees F., is six months. (3) Sealant application life, tack-free curing time, curing rates are as follows on next page
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
(a) Brushable Type Sealants Application Life (HOURS)
Cure Rate
Tack-Free Time
CLASS A
(HOURS)
(HOURS)
PR1422 A-1/2 PR1422 A-2
10
30
112
36
72
2
8
30
1/2
24
72
2
10
30
1/2
36
72
2
Cure Rate
Application (HOURS)
CS3204 A-1/2 CS3204 A-2 PRO-SEAL 890-A1/2 PRO-SEAL 890-A2
(b) Filleting Compound land
wing walk access Tack-Free Time
on
panel).
CLASS B
(HOURS)
(HOURS)
PR1422 8-1/2 PR1422 8-2
10
45
1/2
36
72
2
CS3204 8-1/2 CS3204 8-2
8
30
1/2
24
72
2
CS3204 8-4
36
76
4
Cure Rate
Follow
procedures
(c) Access
Door
with sealant kits to
PR1403-G-B2
tanks.
walk access Tack-Free Time
Sealant(except on wing
CLASS B PR1428-82
properly seal
or
or
CS3330-B2
panel)
(HOURS)
(HOURS)
Application (HOURS)
10
48
2
8
16
2
16
2
8
(d) Brushable Top Coat
Life
Life
Protective Sealant
PR1005L
1/3
4
CS3600 Allow 24 hours
B.Sealant
cure
time
prior to refueling tanks.
Air must be allowed to circulate
kits with proper use and accelerator.
NOTE
Apply sealant as soon as possible after cleaning. Store and handle parts in a manner that will prevent finger prints, dust, dirt, or other foreign substances from accumulating on
To avoid excessive air entrapment, slowly stir accelerator into base compound. Continue mixing for seven to ten minutes. Scrape sides and bottom of container to include all compound in mixture and to insure uniform blending. Scrape mixing paddle on edge of container to remove unmixed compound. Be sure to use all of the accelerator.
(2)
surfaces to be sealed. NOTE Refer to Mooney SE M20-230 for proper application and drain holes to be left open.
(3) Place a small amount of mixture on a clean strip of aluminum and spread sealant. Visually examine
4. Sealant Application. Old sealant must be removed. Use a sharp non-metallic scraper (Formica or lexan). When sealant has been removed clean area throughly and, reseal tank as follows:
sealant film to determine whether accelerator is visible in particle form. If particles of accelerator are visible, continue mixing operation. If course particles of accelerator persist after mixing thoroughly, reject the mixed batch.
A. Fillet
Cleaning
Sealing.
Be certain that the surface to be sealed is clean and free from oil, grime, finger prints, etc.
(1)
NOTE Sealant in tube form have mixing instructions on each tube. Read and comply with these mixing instructions prior to sealant application. 3.
access covers.
B. Allow cleaned surface to dry five to ten minutes before sealant application.
Mixing
(1) For best results, proportions of base compound
through tank
totally
(2) Refer to (Figure 28-3) for typical (3) Join fillets laid produce a continuous fillet.
Surfaces to be Sealed.
on
fillet size.
intersection
joints
to
(4) Seal all difficult and hard-to-reach areas first preclude the possibility of their being overlooked or improperly sealed. B. Filleting Compound Application.
A. Clean metal surfaces to be sealed with Turco 657 Wipe Solvent or Methyl Ethyl Keytone (MEK). Wipe surface dry with a clean cloth. Do not allow solvent to evaporate.
to
4-99
28-11-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 3/8
TO 1/2 IN,
1/32
IN,
3/8 10 1/2 IN,
STEP
3/16
TO
APPLY BRUSH SEALANT
THIRD
1/4
STEP
IN.
1
APPLY FILLETING COMPOUND 1 IN,
I
i~
IN,
SEALANT
FILLET
SECOND
STEP
protective sealant coat should extend one inch beyond edge of the filleting compound. (2) Allow the first protective coat to cure 20 minutes at 75 degree F., or until tack-free; then apply a second brush coat of PR 1005-L. Make every effort to obtain a completely bubble-free, top coat. DO NOT REBRUSH over doing so will only cause dragging and will break coating continuity. E. Upper Wing Tank Access Panel Sealing. (1) Apply a coat of access door sealant (PR1428) to either faying surface using a short Stiff bristle brush, spatula, or extrusion gun. If an areas,
as
extrusion gun is used, smooth the sealant with a brush or spatula. Cover the entire faying surface with a sealant coat of sufficient thickness (1/32 to 1/16 inch) to assure extrusion along the edges of 1/16 IN, the favinn surface when the mating parts are APPLY assemble~d. Access panels in wing walk area PROTECTIVE should be sealed with PRC 1422, Class B filleting
FILLET
3/16 TO 1/4 IN,
FOURTH
compound. (21
STEP
obtain as contact. FASTENER SEALING WITH BRUSH SEALANT <1/32 TO 1/16 IN. THICK)
C. Brush
spatula to pack sealant firmly in place pockets. Shape each fillet evenly.
out air
Sealing.
(1) Brush sealant (PR 1422-A-1/2, A-2 or CS3204 A-1/2, A-2) over all seams, rivets, nuts, and bolts. A one inch stiffbristle brush is recommended for sealant application. Force sealant into all gaps with brush strokes parallel to seams. Use a circular brush action to deposit an even coating of sealant around and bolts. rivets, nuts, Coating ´•should be approximately 1/32-inch thick. Use considerable brush
spatula.
(2) When the edge of
a
Range protrudes
0.040
less, or where the seamcannot be clearly defined, apply two 1/32-inch brush coats. Allow the first or
cure about four hours or until´• it becomes before applying the second coat. The second coat should overlap the edges of the first coat by about 114 inch.
coat to
rubbery
D. Protective Sealant.
(1) Using short,
even
strokes, brush
and continuous coat of PR 1005-L 28-12-00
over
possible
a
metal-to-metal
FUEL TANK LEAK REPAIR
2´• Classification of leaks as to Intensity and Location. (Refer to Figure 28-4). A. Intensity Classification. (1) Stain--A slow fuel leak that tends to evaporate as soon as it is exposed to air. (2) Seep--A fuel leak that reappears shortly after area is wiped clean. (3) Heavy Seep--A fuel leak that reappears immediately after area is wiped clean. (4) Running Leak--A fuel leak that flows steadily.
action to force sealant into all small crevices and to obtain good adhesion. Air pockets under the sealant, that will open up in the form of holes or voids soon after application, will result from improper application. To repair holes or voids, press sealant in place using a
inch
as
classification of fuel leaks that occur in both confined and open areas is necessary to differentiate between those leaks that require repair before Right and those which do not constitute a flight hazard. The size of the wetted area around a leak is an indication of the leak intensity. All fuel leaks must be recorded by describing the location and intensity of the leak in the aircraft log book.
pack tightly. a
near
immediately after tighten screws to
It is 1. Leak Description. necessary to periodically inspect the fuel tanks. Inspection is particularly important in confined areas of the aircraft that are not exposed to the airstream. Identification and
(1) Use a spatula or an extrusion gun with a 1/8 to 1/4 inch nozzle opening for laying fillets at edges of all seams. When using an extrusion gun, hold gun perpendicular to seam so that extruded sealant will (2) Use working
Assemble parts of sealant and
(3) Remove the extruded sealant from the wing surface after installing the fasteners. 28-12-00
28-3
while
UAL
continuous
I
SEAL GAPS HOLES WITH FILLETING COMPOUND
FIRST
SERVICE AND MAINTENANCE
M20M
on a smooth sealant. The
4-99
I
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
3-i/i!
TO 4 IN,
MOONEY AIRCRAFT CORPORATION
M20M
and fuel may Row through or along a from one seam to another. Fuel may channel a few inches or several feet to where it appears on external skin surface.
1/2 TO 3/4 IN~
seams
seam or
(´•1) Enter tank through inspection panels and inspect sealant in general outside leak point. Look first for bare and
rivets,
of
seams,
difficult-to-seal
areas.
Inspect sealant for blisters, pin holes, cracks, splits, and loss of adhesion. Mark all suspected flaws with masking tape.
:::::::::::::::’C)1 TAIN
HEAVY
in
bolts
access area
I
SEEP
(2) Test each suspected flaw from inside tank using compressed filtered air at 20 to 30 PSI. Hold air noule against Raw and closely check outside leak point for evidence of fuel. (3) After testing each suspected flaw from inside tank as outlined above, and if no leak source
can
be
discovered, apply soapless
bubble Ruid to exterior and again pressure to Raws from inside tank.
(4)
If
above
tests
fail
apply
locate
to
air
leak
apply air pressure (10 PSI MAX) to external leak point after removing all traces of fuel from tank and applying soapless bubble
source,
fluid to tank 28-13-00.
1
RUNNING LEAK
FIGURE 28-4
seams
per
Section
Repair. Temporary Repair of Fastener Leaks. Generally, all leaks in enclosed areas and running leaks in open areas constitute a flight 4. Leak
A.
SMM28-4
FUEL LEAK CLASSIFICATION
interior
hazard. Fastener leaks of this category may be a sealant fillet over fastener head on fuel tank exterior. For a temporary repair to be satisfactory, structural integrity must be retained in leak area. To make a temporary fastener-leak repair:
temporarily repaired by applying
B. Slow-to-heavy seeps occuring in open areas, such as wing surfaces exposed to the airstream, are leaks which do not constitute a Right hazard and need not be repaired prior to flight, providing the condition causing the leak cannot result in a leak of greater intensity during flight. Seeps considered permissible for flight must be frequently inspected to insure that no increase in intensity has occured.
(1) Remove enough fuel from tank to level below leaking fasteners.
drop
fuel
Clean fastener head and adjacent surface Turco 657 Wipe Solvent or MEK and dry thoroughly. Fastener head and adjacent metal must be entirely free from paint, dirt, and oil.
(2)
with
C. A running leak and any leak in a confined area that is not exposed to the airstream should be repaired before the next flight.
(3) Apply a 118 inch thick coat of PR 1422 (or CS3204) 8-1/2 or 8-2 over head and around fastener. (4) Allow sealant to cure until firm and rubbery. (5) Refill tank and examine repair periodically. If
3. Leak Detection.
A. External Leak Detection After Refueling. To be able to trace a leak from where it appears on an outer tank or wing skin to its true source inside the tank the exact point where fuel is escaping from tank must be dete rm ined
leak
recurs,
sealant
must
be
removed
and
area
prior to making another temporary repair. B. Permanent Leak repair. If leak source is found to be around a rivet or threaded fastener, the repair procedure shall be to restrike rivet or retorque fastener to maximum permitted torque value. Any one rivet may be restruck only one time. If leak continues, replace recleaned
(1) Use compressed air to blow and evaporate fuel from seams and crevices of leak area. Attempt to define exact point where fuel is escaping from tank. (2) Small seep leaks can be traced with raw edges of torn paper. The fuuy edge absorbs fluid and gives a good visual indication of fuel presence when brought in contact with suspected leak points,
the rivet.
or
(1) Repair any sealant damage retorqueing a fastener.
due to
restriking
(3) After tracing leak to its exterior source, mark location and drain fuel tank. B. Internal Leak Detection. To make a permanent it is mandatory that the true source of the interior leak be located. The fuel tank is a network of
repair,
4-99
28-12-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
Remove sealant in immediate area of leak a using sharp non-metallic tool. A chisel-shaped formica tool is recommended. Scarf or taper ends of existing sealant so that new sealant can form a continuous and smooth overlap.
(2)
source
(3) Thoroughly clean repair area using Turco 657 Wipe Solvent or MEK. Wash one small area at a time. To prevent redeposit of oil and dirt on surface, dry with a clean cloth before solvent evaporates. Always pour
28-1 4-00
Under certain conditions of
fuel volume per tank. CAUTION
Ethylene glycol monomethyl other additives
potential
(4) Thoroughly dry
(6) Allow all repaired sealant to cure tack-free apply two brush coats of PR 1005-L to repair area (Refer to paragraph 28-11-00, 4, D).
system. -DISTRIBUTION
28-20-00
FUEL BOOST PUMP REMOVAL AND INSTALLATION
28-2190
LEAK CHECK
1.Auxiliary
1. Materials. ounces
of either sodium
or
ounces
bichromate,
Thickening
ounces
Alkaryl
B. Turn fuel selector valve OFF.
Wax
D. Remove fuel pump. Sufonate
wetting agent.
2. Reverse the removal
D. Distilled water.
Preparation. one of the compounds
one
listed in item
(B) above with one cup distilled water. C. Mix item (C) above with four to four and one half gallons distilled water until wetting agent dissolves completely. D. Mix the three ingredients (A), (B) and (C) together and add enough distilled water to make five gallons of solution.
run
28-22-00 Gascolator
(a) (b) (c)
CAUTION bubble fluid is slightly corrosive and
more
than 15 seconds.
paragraph 4,G.
for 100 hour
GASCOLATOR SCREEN CLEANING screen
Remove
belly
removal and
skin
just
Turn selector valve to OFF
Remove
safety
wire
cleaning;
aft of
on
nose
wheel well,
position,
bottom nut and
remove
nut,
by washing freely scrubbing.
(d) (e)
Remove sump and
screen
Clean screen and reinstall. Take care not to
CAUTION When removing lower inboard access panels, caution should be exercised during removal so fuel outlet tubes wSII not be damaged or bent.
10
dry for
See Section 5-20-06, inspection information.
Amount of each ingredient may be reduced for a smaller quantity of solution. Solution life is about one week.
must be completely removed with water followed by
pump
FUEL BOOST PUMP INSPECTION
28-21-01
NOTE
28-13-00
for reinstallation.
NOTE When the aircraft will not be gown for a period of time, refer to Sections 10-10-01,10-10-02 8 10-1093.
(A)
cup distilled water.
B. Mix item
Soapless
procedure
CAUTION Do not
2. Solution
A. Mix above with
Removal.
Pump
C. Disconnect inlet and outlet fuel lines.
(Carbo
C. Thirteen
Electric Boost
A. Remove electrical leads.
potassium dichromate.
B. Three and one-quarter Wax 1500).
or
pump malfunction.
SOAPLESS BUBBLE FLUID FORMULA PREPARATION FOR
A. Three
(EGME)
system is comprised of two fuel pumps, an engine dnven gear type pump and an electrically driven auxiliary boost pump. The boost pump is connected to a switch on the instrument panel. The boost pump is used to provide sufficient fuel pressure to operate the engine in case of engine dnven fuel
and
potassium chromate,
ether
not recommended due to deteriorating effects within the fuel are
The fuel
(5) Apply sealant as required for repair (See Figure 28-3). Repaired fillets must be blended into existing fillets with a spatula or an appropriate tool.
28-13-00
temperature and humidity,
water can be present in the fuel in sufficient quantities to create ice formations within the fuel system. To prevent this, add Anhydrous ISO-PROPYL Alcohol to the fuel supply in quantities not to exceed 1% of total
solvent onto wash cloth to prevent contamination of solvent supply; do not dip cloth into solvent. clean area by blowing filtered air over immediate area until there is no possibility of solvent or fuel entrapment under adjacent sealant.
FUEL ADDITIVES
by pulling down,
reverse
removal process to
damage O-rings, O-rings with clean engine
(f) Lubricate installing, (0) torque 10 to 15 in. Ibs., (h) Safety wire exactly as original
4-99
oil before
installation.
SERVICE AND MAINTENANCE MANUAL 28-23-00
FUEL INJECTION SYSTEM
28-24-00
ENGINE PRIMING
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
gauges in the cluster gauge and work in series with each other.
no
A. I/B Transmitter removal
FUEL SELECTOR VALVE REMOVAL 8 INSTALLATION
1. Drain both fuel tanks.
body. valve body.
screws
rib
that mount valve to the tubular
8. Leak check fuel
fuel
procedure
to install valve.
DUMP
tanks
can
or
RH
as
needed.
screws
attaching
transmitter to
through
lower
access
cover
Locate 8
remove
sbe
transmitter wires.
screws
attaching transmitter
to
Remove transmitter from rib. the
fuel
quantity
C. The torque and screw clamp load will naturally relax as the gasket flows to a normal condition. NEVER RE-TORQUE JUST TO RESTORE ME 20-25 INCH LBS.
"DO NOT OVER TORQUE" DO NOT RE-TORQUE UNLESS LEAKING D. Excessive torque or re-torqueing may warp or distort the transmitter mounting flange and cause a malfunction. E. Make certain wire from outboard transmitter goes under head of insulating sleeve against the inboard transmitter flange and not under the mounting screw head.
F. System voltage should NOT BE APPLIED to the transmitter terminal. The exicitation from the fuel quantity indicator must be current and voltage limited and incapable of causing ignition of fuel vapor if transmitter wire is inadvertently shorted to ground.
FUEL VENTS
The fuel tanks are vented from the outboard upper This vent is routed outboard thru the wing structure and vented overboard through a NACA vent
edge.
of Vuel takes
application devise quantity transmitters.
B. Snug each screw, then TORQUE each screw to 20-25 INCH LBS. in a cross flange-random order.
be
Expansion
access area.
do~leRremOve
FUEL SYSTEM DRAINS
lower wing surface. inside the tank.
LH
transmitter wires.
must be used to install the fuel
Fuel drains are installed in the inboard corners of the tanks and at the gascolator, the lowest point in The the fuel manifold and engine system. engine-driven fuel pump drains join at a juncture on the right side of the engine. A single drain line dumps fuel overboard below the cowling at the left cowl flap opening. Tank drains are recessed and spring loaded, An O-ring at the lower flange seals the valve seat.
on
Remove transmitter from rib.
panel,
remove
needed.
as
A. A calibrated, certified torque
system.
wing
28-32-00
(5)
or
2. For reinstallation, reverse transmitter removal procedure.
emptied for maintenance purposes by (1) removing the sump drains in the lower panel of each fuel tank and allowing fuel to drain into suitable container or (2) disconnect the fuel line at outlet of the fuel pump and use boost pump to transfer fuel from both tanks into a suitable storage container. 28-31-00
(3) (4)
Locate
(4)
7. Reverse the removal
28-30-00
Remove interior
(2)
6. Remove valve.
The
(2)
(1) Gain outside of tank
4. Remove handle above floorboard in fuel selector
Remove structure.
Remove Pilot
B. O/B Transmitter removal
2. Disconnect inlet lines at valve
pan.5.
Go-Pilot seat
(1)
Remove six rib doubler.
The fuel selector valve is located below the floor board just aft of the console.
3. Disconnect outlet line at
Removal.
Drain fuel from tank. Reference 28-30-00.
SECTION IV for chart). 28-25-00
Quantity Transmitter
1. Fuel
independent priming system on the M20M Operating the boost pump switch in the cockpit turns on the auxiliary fuel pump. The time for running the pump for starting purposes is dependent upon the outside ambient temperature (See POH/AFM There is aircraft.
place
G. Care must be taken to insure that the bottom on the terminal stud is not disturbed when the electrical connection is made. This bottom terminal stud nut torque is factory set to provide the correct terminal stud seal preload. nut
NOTE
important that the fuel tank vent tube protrude only enough to be flush with lower wing skins. It is
28-40-00
INDICATING
28-41-00
FUEL QUANTITY INDICATING
H. Other nuts on the electrical terminals should be as follows:
tightened #6
6 in.
2892-00
TRANSMITTERS
Ibs./ #8 -12 in. Lbs./#lO
14 in. Ibs.
FUEL QUANTITY INDICATOR
quantity gauges are in the instrument cluster gauge. These gauges indicate percentage of fuel
Two fuel
fuel quantity indicating system has two fuel quantity transmitters in each wing tank, one on I/B wing tank rib and one on O/B wing tank rib. The transmitters are electrically connected to the fuel
The
Each gauge operates by the change in resistance of two transmitters located in the fuel tanks.
remaining. 4-99
2823-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
FUEL QUANTITY ADJUSTMENT PROCEDURE
28-43-00
SERVICE AND MAINTENANCE MANUAL
8. Place "EMPTY-FULL" switch EMPTY position. 9.
AIRCRAFT MUST BE LEVEL -TO CALIBRATE FUEL GAUGES-
Place
SW2
switch
(SW1)
Test
on
11. Place "EMPTY-FULL" switch 12.
unusable fuel to either tank.
for aircraft with
gallons
14. Place Test Box back to "FULL" and 15.
analog
panel so low fuel warning light just (See SECTION 24-33-00. 4 A and B). 5. Add 8.125 or 8.625 gals. (or 5.125 or 9.125 gals.) for 1/4 gauge reading. Continue adding fuel in 11.125 gallon increments fdr 1/2 and 3/4 gauge readings. in annunciator
16.
comes on
to
1 needle width.
7. Trim pot marked "FULL" (upper hole) should be if necessary, so each gauge reads "F" +1-1 needle width.
Repeat steps
Cluster
gauges
(27-0001
installed
thru
on
have
thru
2.
22. Add additional 6
panels
3.
or
4.
to
Harness 2 Pin
Power
12
OFF.
25. Remove Test Harness.
26. Repeat Steps setup.
1
through
25 for
opposite
fuel tank
27. After fuel calibration is completed on both tanks, return "NORMAL-CAL" settingon Annunciator to
Source),
NORMAL. 28-43-00
fuel is burned off.
"hgC~,f
24. Turn power to aircraft
Fuel
Digital Voltmeter to Test Female Pin Plug (millivolts out). 7. Tum aircraft power ON (or use Aux. 6. Connect
as
23. After verification that Low Fuel Warning when approximately 7 gallons useable been added, continue to fuel tank to 44 gallons (FULL) and if required, readjust Master Gain Control to 818mv.
Pin
between
Low Fuel 7 gallons
extinguishes
connector). 5. Connect 9-Pin Test Harness Processor and Fuel Gauge plug.
Verify
NOTE
remains in the tank
(15
tank.
post setup Test Flight should be conducted to verify that the Low Fuel Warning Light illuminates when approximately 6 gallons fuel
Figure 28-58). Processor
to
1
A
Processor Test Box 28-5A) and O-Pin Test
Connect Test Box to Fuel
gallons
8
re-adjust No.
useable fuel added.
IAl
shown in Figure Harness (Schematic shown in
(S
ON.
gallons of additional -~uel. The Warning light should extinguish at about
27-TEA)
interior lower side Remove seats fuel quantity processors LH 8 RH. construct
IAl Annunciator
OFF.
the full 6
access
Obtain
on
Annunciator Low Fuel Wamng light is illuminated for
and 00 roll. Verify Level aircraft to Annunciator NORMAL-GAL switch is in CAL mode, 1.
Warning light
21´• Load unusable fuel (3 gallons); Bias to read 170mv (if required).
this
1. With "unusable" fuel in tanks, adjust pot marked "EMPTY" so gauge reads "E". If intermediate or "F" indications are out of tolerance as tank is filled, adjust pot marked "FULL" for correct calibration.
(27-0258 00 pitch
Low Fuel
20. Tum power to aircraft
adjustment:
DIGITAL GAUGES
Adjust
aircraft 19. Connect wiring from Fuel Qty. Transmitter to IAl Processor Box. Leave Test Harness connected to other end of Processor Box.
27-0257)
aircraft
needed to
18. Disconnect Test Box and Fuel Processor.
2 thru 7 for other tank.
ANALOG GAUGES
as
illuminate to the Test Box setting. In the "LOW the miliivolts will range behrueen
17. Tum power to the aircraft
FUEL QUANTITY GAUGE ADJUSTMENT
28-43-03
13
NOTE See Section 24-33-00, 4. A. or B. for detail procedures for adjusting Annunciator Low Fuel Warning for Analog Fuel Gauge systems.
filling tank until 47.5 gallons total fuel wing tank. Gauge should read "F".
adjusted, 8.
adjust to 170mv. adjust to 818mv.
After completion of Step 14, set switch SW1 in Test Box to "LOW FUEL". Wait 2 3 minutes for system to stabilize.
part of additional 11.125 gallons required for 1/4 gauge reading. Adjust "LOW FUEL" waming trim pot
read within
Repeat Steps 9, 10, 11, 12,
(see
obtain correct values (EMPTY 170mv; FULL 818mv). The correct values will converge in 2 3 adjustment iterations.
is
6. Finish volume is in
Gain Bias to read 818mv for location of Master Gain Bias).
13. Place Test Box back to "EMPPIP’ and
gauges (27-0001 thru 27-0257). Add 6 to 8 gallons for aircraft with digital gauges (27-0258 thru 27-TEA). This
C;auge to
Test Box
on
position. Adjust Master
Figure 28-5
3. Adjust trim pot marked "EMPTY" on each gauge to read "E" to 1/2 needle width below "E". "EMPTY" trim pot is lower hole on fuel gauge.
4. Add 2.50 to 3
(SW1)
to "FULL"
1. Fuel tanks EMPTY.
gallons
M20M/R
to
1 Bias to read 170 my; if unable to read 170 my, set to read IlOmv (see Figure 28-5 for location of No. 1 Bias)
FUEL TANK CALIBRATION PROCEDURES.
2. Add 3.0
Box
position. 10. Adjust No.
NOTE See Section 24-33-00 for low fuel warning calibration. 2843-01
Test Box to
on
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
GainO
gNO.’
DATA
PLATE
Master
IAI
PIN
15
ia
No .2
Bias
I
USED ONLY
IF
COVERED BY DECAL
NOT
PRELIMINARY
<prlor LOCATED UNDER SIDE PANELS ADJACENT
to
TO INBOARD TANK RIB
FUEL QUANTTTY PROCESSOR MATERIALS
REQUIRED~
COTY
I
SETUP (Set to 80nv) on Bics Steps,
adjustnent
FIGURE 28-5
EA)
SWITCH WITH MINIWUY e AMP CONTACT R*TIHG´• ANY SPDT SWITCH WITH CIINIWUW 1 AMP CONTACT RATING. e2 W 1/8 WATT IX TOLERANCE RESISTOR. II RI~ 5.O W 1/8 WATT iX TOLERANCE RESISTOR. RZ~ RPI 12 W I/B WATT LSC TOLERANCE RESISTOR. R41 JD W I/B WATT IX TOLERANCE RESISTOR. I CONNECTOR. l~i PIN D-WB. D1\-1~P OR EWIVALENT. JL AVG 22 WIRE, AS REWIRED. ENCLOSURE. BUD BOX OR EOUlVALENT. SHOP PREFERENCE. MORE THAN ONE RESISTOR MAY BE PARALLELED TO ACHIEVE THE TWE ABOVE RESISTOR VALUES IF WIGCI TOLERENCE RESISTORS ARE
1. 2.
TWII SVBI
J.
O
6. I.
8. 9. ´•I
NOT
ANY
LH B RH
DPOT
APPROX.
2~
INCHES
AVAILABLE. ENCLOSURE
AS
DESIRED
3 9
’L
OUT *WC1
+SIOK V XDUC1
I
AlRFRALE CIXIVWD OG 0M0
10 ’0
~uCe
OG 0(0
]OUU
F
mJcl
L OU1
13+ SVI
I R4
1
I´•~C
I r
I I
I r
i
I
i
--1
4
I re
11 ir 14 10
DIGITAL
GAUGES
FUEL
OUA~TITY
CALIBRATION
TEST
BOX
FIGURE 28-5A 2 PIN CONNECT PRELIMINARY SET--UP <80 nv>
w/
e,p~S
~D-l.
PIN CONNECTOR 2 MILLIVOLTS OUT
j t f
1 1 Dc
DIGITaL
G~UGEZ
FUEL
TEft/EXTENStON
HaRNESS
INTEKFnCE
CnBLE
FIGURE 28-5B 499
2343-03 13
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
NOTE When removal 8 replacement of individual DIGITAL FUEL GAUGES are required due to malfunctions, re-calibrate each new fuel gauge to read same as the replaced one in accordance with the adjustment procedures shown in FIGURE 39-48.
28-90´•00
-MISCELLANEOUS
28-91-00
TROUBLE SHOOTING
TROUBLE Fuel gauge not
indicating.
FUEL SYSTEM
PROBABLE CAUSE
REMEDY
Broken wire.
Check and
Faulty transmitting
Open Fuel gauge indicates full when tanks are not full.
No fuel pressure indication
unit.
Replace
circuit breaker.
Repair.
and
adjust.
Check and reset.
Incomplete ground.
Check ground connection at transmitter.
Broken wire.
Check and
Tank empty.
Check and service tank.
Defective fuel pump.
Check pump for proper pressure buildup. Check for obstruction in boost pump screen. Check engine fuel pump and check valve.
Open
Repair or replace
repair.
(calibrated test gauges nnected).
cc
fuel line.
Fuel selector in "OFF" Fuel pressure low or surging (calibrated test gauges
Select proper position.
position.
Obstruction in inlet side of pump.
line.
Check and clear fuel lines. Replace rebuild pump. Check fuel lines and connection for leakage or damage.
Faulty engine pump,
connected.) Fuel selector not in proper
Select proper
or
position.
positio n. Air leak in
28-92-00
Repair
system.
FLARED FITTINGS
TAPERED PIPE THREADS
7
leak.
When installing flared fittings and hoses, make sure the threads are properly lubricated with W-P-236
LUBRICATE
’0: NOT LUBRICATE FEMALE THREADS
DO
STRAIGHT THREADS
NEVER TO
ALLOW
LUBRICANT
CONTACT THESE
´•SURFACES LUBRICATION OF FLARED FITTINGS 28-90-00 14
4-99
FIGURE 28-6
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
petrolatum per (Figure 28-6). When previously installed fittings are removed, they should be wiped clean and relubricated before they are reinstalled.
Torque
ail
fittings
in accordance with flare
fitting torque
chart, CHAPTER 5, Figure 5-1.
4-99
2&92-00 15
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
BLANK
28-92-00 16
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
CHAPTER
ICE AND RAIN
PROTECTION
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAR~ CORPORATION
CHAPTER 30 ICE PROTECTION
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT 30-00-00
PAGE
SUBJECT General
5
icing Prot~ction
5
30-1 0-00
Airfoil
30-11-00 30-11-01
Servicing, Airfoil Washing.
30-11-02
Lubrication
5
30-11-03
Electrtical
5
30-1 2-00
Troubleshooting -Airfoil Icing Protection Schematics Airfoil Icing Protection Maintenance Practices
30-12-02 30-31-00
5 5
Maintenance, Airfoil Icins Protedion:
30-12-01
3050-00
Ice Protection
Pitot Ice Removal, Description Stall Warning Vane Heated
ab,,tia,
30-60-01
Propeller De-icing Syistem Propeller, (Electric) Ice Removal Description &Operation Propeller De-ice Power Requirements
30-61-00
ServiceGuide
5 7
6&7 9
14 14
Electric 30-60-00
Helpful Tips Trouble Shooting
30-61-01
30-61-02 30-62-00
15
15 15
Chart
Electric Prodeller
15 17 19
Not used
30-69-00
Electric De-lcerTimerCheck
19
30-64-00
Inspection Continuity Test Brush to Slip Ring Resistance Test. Brush Assembly Resistance Check Brush Block Assembly Repair Brush Replacement/Alignment Alignment of Slip Ring Servicing/Cleaning
19
30-65-00
30-66-00 30-67-00 30-68-00 30-68-01 30-69-00 39-70-00
100 Hour
19 20 20 20 20 20 20
30-CONTENTS
3/4BLANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 30 ICE PROTECTION
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
PAGE
DATE
30-Effedivity
IRBLANK
699
30-Contents.
3/4ELANK
699
30-00-00.
5.
4-99
30-12-00.
6.
699
30-12-01.
7.
4-99
30-12-01.
6.
4-99
30-12-02.
9.
4-99
30-1 2-02
10
4-99
30-1 2-02
11
699
30-1 2-02
12
4-99
30-1 2-02
13
4-99
30-30-00
14
4-99
30-61-01
15
4-99
30-61-01
16
4-99
30-61-02
17
4-99
30-61-02
18
4-99
30-62-00
19
4-99
30-66-00
20
4-99
SO-EFFECTIVITY IRBLANK 4-99
SERVICE AND MAINTENANCE MANUAL 30-00-00
OLDWILLWAYNE M20M
-GENERAL
MOONEY AIRCRAFT CORPORATION
30-11-03
The M20M aircraft incorporates an alternate air system that is designed to open automatically any time the air induction system becomes blocked. This system should be inspected to assure that no heated air is entering the induction system during routine engine (See Section 71-62-00 for rigging operation.
instructions).
-ELECTRICAL
1. Clean electrical
circuitry, I.E., contacts, terminals, pins switches, relays, potentiometers, etc. in areas
protectionfluid flows. 2. Inspect and check operation of electrical comoonents/svstems which have circuitry in ice protection Ruid flow areas prior to each flight. where ice
This aircraft includes, as standard equipment, a heated pitot tube assembly. The aircraft may also include as
30-12-00
optional equipment:
1. Inspect ice at all panels.
an
electrically operated propeller
de-ice system and an airfoil anti/de-ice system. Refer to the manufacturers service data for specific maintenance information. 30-10-00
-AIRFOIL ICING PROTECTION
The current airfoil/airframe icing protection system utilizes a thin film of ethylene glycol, to minimize the adherence of ice. The system is comprosed of porous, stainless steel, panels fitted to the leading edges of the wing, horizontal and vetical stabilizer. The installation icing pmtection forthe pild’s side of the The glycol based de-icing fluid is stored in two interconnected tanks looted under the rear seat. These tanks have a total capacity of 6.0 U.S. gallons and are filled through a filler on the right side of the aft fuselage. Fluid is pumped through nylon lines to proportioning units located in each wing and in the aft fuselage. From these, the Ruid is routed to the porous panels and pumped through later drilled holes in the panels to flow over the airfbil surfaces. The pilot’s side of the windshield is provided fluid through a spraybar fed by a separate pump. 30-11-00
Ethylene Glycol
fluid absorbs and retains moisture. Residual fluid that is not washed from the aircraft at recommended intervals can get into skin laps and other faying surfaces and hold moisture. This may eventually dissolve lubricants, and break down particles of corrosion-protection coatings. Solid various foreign materials may attach themselves to the Ruid and cause corrosive action of adjacent structural or
rotating components.
30-11-01
panels
proper Ruid Row
with pump in the OFF
position.
3. Check system metering pumps (2 each, located u"de’ rear seats), for proper operating pressure. Use System Control Panel for valid pressure verification.
A. Select "De-lce".
(1) The "De-lce"
LED should flash
altemating
RED/GREEN and the "Anti-lce" LED should Rash REDIOFF as system pressure rises. It may take
NOTE few minutes to build to proper operating pressure.
a
(2) When system pressure is obtained, the "Anti-lce" LED should extinguish and the "De-lce LED should show steady GREEN. (3) Repeat procedure
with both
metering pumps.
B.
Switch OFF for sufficient time pressure to fall (approximately 2 minutes).
for
system
C. Select "Anti-lce". The "Anti-lce" LED should Rash
altemating
RED/GREEN and the "De-lce" LED should Rash RED/OFF as system pressure rises (approximately 20
seconds). (2) When system pressure is obtained, the "De-lce" LED shoujd extinguish and the "Anti-lce" LED should show steady GREE~N. (3) Repeat procedure with both metering pumps. Operate Windshield Spraybar on each windshield pump to ensure proper operation and absence of 4.
leaks.
WASHING
5. Filter is located at FUS. STA. 88 under rear seats. as needed. Inspect system filter and replace
Replace
It is recommended that the aircraft be rinsed with clear water after each flight in which ethylene glycol is used for icing protection. Special cleaning attention should be given to skin lap areas and areas where antennas are mounted if ethylene glycol tends to flow there. 30-11-02
AIRFOIL ICE
protection system for
2. Check for leaks at all
and ON
(1)
-SERVICING- AIRFOIL ICING PROTECTION
MAINTENANCE
PROTECTION
aS
"eeded.
A. The "high pressure" UED will illuminate YELLOW if the filter element requires replacing. It should NOT illuminate during testing but may be tripped ON occasionally during aircraft electrical system switching or during engine start. Cancel by depressing "Reset" switch (use ball point pen tip or Similar devise).
-LUBRICATION
1. Rod End bearings on Flight Controls and Landing Gear systems should be inspected frequently for indication of lubrication being washed off by ice protection fluid. Re-lubricate as needed.
B. Test "High Pressure" LED by depressing "Reset" switch. Y~ELLOW LED should illuminate while SWitCh is depressed, but go OFF when "Reset" is ’eleased.
2. Inspect hinge point of all flight control surfaces, landing gear doors, linkages, bellcranks, etc. for indication of lubrication being washed off by ice protection fluid.
5.
See ice protection
system schematic
on
next
pages. 4-99
30-00-00
OLDWILLWAYNE
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OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
Windshield De-ice Pump
A;rfrome/Propelle~ Pump 2
forth
Metering Pump Rel~y
HI
’Y
ov
MOONEY AIRCRAFT CORPORATION
M20M
I
I
LO
1 Blue
~X
Red
Windshield De-ice Pump 2 Blue
Red
Valve
Earth Valve
HI
2
LO
LO
High Pressur
Airframe/Propeller
rn,ng Switch
Pump Low
Stoll
Vane
Pressure Switches
Pitot Heat
Heat
"C~
I
I
I
I
I
I
I
I I
Tank
Assy.
Knife Connector aI
ct
’9t ge To
C3
ioy Box
i
Other
Heat
Tank Contents Transmitter
T Red F0103
28VDC
Optional Equipment Relay
Block F0101
cZjb PL117
Relay
is
octivated
Airspeed S6itch
keep stall warning
vane
NOTE: Later
A/C
have box
relay
a
new
connector
II
instolled.TKS relay is seporate relay. in ne9 box.
$ith no A/S applied: po~er then goes thru the dropping resistor to
81 rl~
Pitot Heot Breoker itch
Normally
term.
28JGDC
~hen
Closed
no
A/S
applied.
C1 Control
-TROUBLESHOOTING
TROUBLE
AIRFRAME/PROPELLER
Panel
PI~ 12 equotes to PIN 2, PIN 8 eauates to PIN 1 PlN 4 eauotes to p(N
AIRFOIL ICE PROTECTION ELECTRICAL SCHEMATIC 30-12-01
~31
FIGURE 30-2
AIRFOIL ICING PROTECTION
PROBABLE CAUSE
REMEDY
Tank contents
inadequate
Pressure illuminated
Warning
Replenish fluid
contents.
SYSTEM DOES NOT OPERATE.
High
LED
Check electrical power to pump(s) Check pump or control panel
Pump(s) inoperative
Low Pressure
Supply
Waming
lines blocked
Renew Filter Element
or
4-99
Replenish fluid
ON
Check tank contents
leaking.
Check lines for leaks or blockage Check Tank outlet strainer for blockage
30-12-01
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
TROUBLESHOOTING -AIRFOIL ICING PROTECTION
TROUBLE
(con’t.)
PROBABLE CAUSE
NO FLOW FROM OUTLETS OF AIRFRAME WING PANELS or EMPENNAGE PANELS
Supply lines to Proportioning
NO FLOW FROM PROPELLER OUTLETS
Supply lines to Proportioning
Units restricted
Units restricted
Supply line blockage misalignment
or
noule
REMEDY
Check supply lines to Proportioning Units for blockages or kinks
Check supply lines to Proportioning Unit for blockages or Kinks Check for blockage noule or slinger Check
WINDSHIELD SYSTEM DOES NOT OPERATE
HIGH PRESSURE WARNING LED ILLUMINATES DURING OPERATION
Temperatures
Inadequate
Fluid content
or
Proportioning
Replenish
misalignment of
Unit for
Pump(s) inoperative
Check pump(s) and
Solenoid
Check power to solenoid Check Solenoid Valve(s)
OAT
Valve(s) Inoperative
blockage
Fluid in tanks
pump(s) wiring valve(s)
COLD
below -300 C
No immediate action necessary, monitor operation at warmer temperatures with Anti-ice selected
Temperatures above -300 C
Renew Filter Element and bleed filter Check system for blockage.
HIGH PRESSURE WARNING
Connect Pin 10 of connector C1 to
(LED ILLLUMINATES)
ground (C1, pin 1).
When aircraft buss
powdered
Check wiring from C1 Pin 10 to High Pressure Warn Switch for continuity.
up.
Check High Pressure Warn Switch. With no pressure applied, continuity should exist through connections in use.
LOW PRESSURE WARNING (LED’S FLASH RED)
Inadequate Fluid content. Pump(s) malfunctioning.
Check system for proper operation Connect Pin 2 of connector C1 to
When system selected ON
ground (C1, Pin 1). Check wiring from C1 Pin 2 to Low Pressure Warn Switch(es) for
continunity. Check Low Pressure Warn Switch(es). With System operating, circuit should exist through connections in use. When aircraft buss ON.
30-12-01
powered
Check Control Panel for fault. Replace Control Panel.
4-99
Repair or
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
TROUBLESHOOTING
M20M
MOONEY AIRCRAFT CORPORATION
AIRFOIL ICING PROTECTION
(con’t.)
PROBABLE CAUSE
TROUBLE
REMEDY
CONTROL PANEL/CONTENTS INDICATING SYSTEM FAULT.
Depress High Pressure Reset. Tank Contents Illuminated
Amber L~D illuminates: Check Auto-dimmer Setting. Check voltage at Control Panel Output C2 (w/ plug
Display
disconnected): Pin 1 +5 volts Pin 3 5 volts. Reconnect C2 and check voltages on this connector: Pin 1 5 volts Pin 2 Signal should vary from 0 volts (tank empty) to +1.8 volts (approx.) (tank full). Pin 3 5 volts. Repair/Replace Control Panel. tank contents Check wiring transmitter. Correct wiring or reset
potentiometer. Does not operate: Check Power to Control Panel. Depress High Pressure Reset: Illuminates =Check Auto Dimmer
CONTROL PANEL FAULT LED malfunction
AMBER
(High Pressure Warn)
setting. Does not illuminate =Repair or place Control Panel. Will not cancel Replace High Pressure Switch LED malfunction
re-
Does not operate: Check Auto-dimmer setting. Repair or Replace Control Panel.
GREEN
(System Status \nd.)
Operates Continously: Repair or Replace Control Panel. Does not operate: Check Auto-dimmer setting. If OK, disconnect cable from Pin 2 of Connector C1. LED’s should Rash when De-ice or Anti-ice selected: If no Rash: Check wiring Low Pressure Warn
LED Malfunction FLASHING RED
Switch(es) If NOT OK: Repair Control Panel.
or
Replace
Operates Continously: Check system for restriction
or
blockage. ReDlace Low Pressure
Switch(es)
30-1~U
MAINTEWANCE PRACTICES
Daily and/or Preflight if icing is forecast or expected. This level of checking is intended to determine the immediate the use of tools or special procedures.
security and
serviceability of
the
equipment without
recourse
to
Notes/Procedures
Maintenance Practice
Check
Waming
condition of visible components.
4-99
30-12-02
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION Level I Maintenance Practice
SERVICE AND MAINTENANCE MANUAL
M20M
Notes/Procedures
(conâ&#x20AC;&#x2122;t.)
Switch on electrical power. Check that contents display illuminates and stabilizes at a sensible value within 1.5 minutes. Replenish tank contents if necessary for intended flight,
The time taken for the display to stabilize will depend on the quantity of fluid present in the tank as the display reading will rise from 0 at about 0.1 gallon per second.
Operate Airframe/Propeller system at "De-lce". Check that both indicator LED;s flash RED then change to a single GREEN (opposite De-ice) as pressure rises. Check that HighPressure Warning LED does not illuminate. Press High Pressure Reset. Check that AMBER LED illuminates while switch is depressed. Switch Airframe/Propeller system directly to "Anti-lce", check that pump speed reduces (audible check) and that GREEN LED, which is illuminated, changes to match switch selection. Check that de-icing fluid flow is evident from visible panels if weather conditions permit. Switch Airframel Propeller system OFF. Press windshield De-ice Switch. Check that fluid is discharged from spraybars. Check that
de-icing
ice
inspection lamp functions. Switch off electrical power if no longer required. Check that fluid flows evenly from active zone of all porous panels. Check that fluid is discharged into the propeller slinger ring from the noule fitted at the front of the engine wing
It may not be possible to observe fluid flow if moderate or heavy rain is falling.
If
night flight.
crankcase. NOTE The TKS ice protection system is not intended to remove frozen deposits while aircraft is on the ground. It is essetial that all critical areas are de-iced before any attempt to T/O is made.
Check aircraft surfaces for ice or snow. Remove all ice or snow from all flying surfaces.
Level II 50 Hour Inspections This level inspection extends the functions recommended for Level I tests of a qualitative nature.
inspections
and includes
more
comprehensive
Notes/Procedures
Maintenance Practice Remove Engine cowling. Check security and condition of visible components paying particular attention to those components attached to the engine and spinner.
Switch electrical power ON. Check contents display illuminated and stabilizes at
If in doubt regarding accuracy of indication make calibration check. Indicator is electronically damped and should rise from 0.0, at switch ON, at an average rate of about one display count per second.
a
sensible value within 1.5 minutes. Replenish tank contents, if necessary.
Operate Airframe/Propeller system at "De-lce". Check that both indicator LEIDâ&#x20AC;&#x2122;s flash RED then change to a single GREEN (opposite De-ice) as pressure rises. Check that High Pressure Waming LED does not illuminate. Check operation
of High Pressure Warn. LED by Pressure Reset. The AMBER LED should illuminate while switch is depressed and cancel at switch release.
depressing High
30-12-02
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
Notes/Procedures
Level II Maintenance Practice
(con’t.) Switch Airframe/Propeller system directly to "Anti-lce", check pump speed reduces (audible) and that GREEN LED which is illuminated changes to match switch
Note Fluid should be exuded evenly over active zone of porous panels. At high temperatures a "waterline" may be observed at the top of some panels due to insufficient pressure being developed to expel entrapped air. This is acceptable unless performance of panel in icing conditions indicates that this is other than a
selection.
temporary
nature.
Check that de-icing fluid flows from all porous panels and that a jet is directed into the slinger ring from the nozzle at the front of the engine. Switch
Airframe/Propeller system
OFF.
Press Windshield De-ice switch. Check that fluid is discharged from spraybars. Check that are blocked.
de-icing no
holes
Switch electrical power OFF. Level III Annual Inspections. At Level III, it is recommended that all Level II
Inspections
are
complied with and
that the
following inspections
are
added/included. Notes/Procedures
Maintenance Practice Remove tailcone panels and empennage panels. Check security and condition of component’s supply lines and wiring. Pay particular attention to components close to contror rods, etc.
Drain tanks. Remove and clean strainer in tank outlets. Refill tanks. Check accuracy of tank contents indicator during refilling process.
The contents indicator does not display actual Refer to contents over the entire range. calibration chart (Figure 30-3).
Level IV
Component Checks. The following checks are detailed for use in conjunction with SECTION 30-12-01, TROUBLESHOOTING. In cases where components can be checked on the aircraft as an alternative to bench testing, both methods are described. Procedures
Maintenance Practice Check fluid
delivery
rate from
1. Fill tanks to at De-Ice or
Airframe/Propeller Pump.
top of filler tube. Operate pump(s)
Anti-ice, as required, for a time period. Refill tanks; measure quantity necessary
to
replenish
to
original
level. Calculate Row rate.
Permitted limits are: De-ice 280 to 300 mi/min. Anti-ice 140 to 150 mi/min. OR 2. Remove Airframe/Propeller
Pump. Bench
test.
Check
High
1. Disconnect Nylon Tube from inlet~to Filter. Connect pressure gauge (0 180 Ibf/in’) (0 to 13 bar) to tube. Use TKS Nylon Tube fittings. Operate Airframe/Propeller pump in a series of short bursts tin order to limit rate of pressure rise) and observe pressure at which High Pressure Warn LED illuminates. Permitted limits
Pressure Warn Switch.
are:
75 to 90
Ibf/in2
(5
6
bar)
OR 2. Remove
4-99
High
Pressure Switch. Bench test. 30-12-02
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION Level IV Maintenance Practice
M20M
SERVICE AND MAINTENANCE MANUAL
(con’t.)
Notes/Procedures
Check Low Pressure Warn Switch.
Remove fairing for access. empennage Disconnect Nylon tubefrom outlet of suspect 5 pressure switch. Connect a pressure gauge (0 ibflinL) (0 to 3 bar) to the pressure switch outlet (use TKS nylon tube fittings as needed). Disconnect plugs at end of pressure switch pigtails from wiring harness and connect a suitable resistance and 2 of continuity measuring device across Pins 1 each switch plug. With no pressure present ,there should be no circuit through either switch and the resistance should be greater than 10 megohms. Operate Airframe/Propeller pump in a series of short bursts to limit the rate of pressure rise at each switch and observe the pressure at which each operates. This pressure should not be greater than 1.5 Ibf/ine (0,1 bar). With the switch at a pressure above the operating pressure, there is to be a circuit between 2 with a resistance not greater than 10 Pins 1 ohms. Switch pump OFF and observe pressure when switch resets. This is to be not less than 0.5 1.
NOTE Two Low Pressure Switches are located on tail bracket in empennage assembly. It may be necessary to test both to determine which one is malfunctioning.
Ibf/in2 (0,03 bar). OR 2. Remove Low Pressure
Check
Proportioning Unit(s) Empennage]
Panel flow rates
are
[Wing,
shown in the
WING PANELS
LH RH Outboard LH Middle, O/B LH Middle, I/B RH I/B VH R/H Middle
EMPENNAGE PANELS LH Rh Horizontal Stabilizer Vertical Stabilizer PROPELLER
Propeller
LH
Switch(es) and bench test. panels necessary to obtain access to suspect Proportioning Unit. Disconnect Nylon tube from outlet of suspect Proportioning Unit. Operate Airframe/Propeller pump(s) and observe fluid Row from outlet. If flow rate is questionable, measure quantity over a timed period.
RH
following
1. Remove
chart:
NORMAL
(+/-20%)
MAXIMUM
(ml/min)
(ml/min)
18.45 9.3 5.7 10.4 15.0
36.9 18.6 11.4 20.8 30.0
NORMAL
(+1-20%)
MAXIMUM
(ml/min)
(ml/min)
11.24 7.0
22.48
NORMAL
(+/-20%)
(+/-20%)
14.0
(+1-20%)
MAXIMUM
(ml/min)
(ml/min)
17.0
34.0
(+/-20%)
TKS FLOW RATE CHART
Level IV Maintenance Practice
(con’t.)
Procedures
Check Porous Panels
30-12-02 12
1. Remove Access panels for access to applicable ProportioningUnit. Disconnect Nylon tube connecting suspect panel from outlet of Proportioning Unit. Connect suitable pressureable supply of filtered fluid to this tube. Purge~ube and panel at a pressure not exceeding 40 Ibf/in’ (2,6 bar). If a blockage exists, it will probably become apparent at this stage. 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL LevellV
Maintenance Practice
Check Porous Panels
Check fluid
M20M
(conâ&#x20AC;&#x2122;t.)
Notes/Procedures Reduce pressure to 4 Ibf/in2 (0,26 bar) and examine porous region of panel for even fluid coverage. OR 2. Bench test. This is last resort due to having to remove panel from airfoil.
(CONâ&#x20AC;&#x2122;T.)
delivery from
Windshield
MOONEY AIRCRAFT CORPORATION
Pump.
1. Remove panels to gain access to pump(s). Disconnect Nylon tube connecting Pump to Solenoid Valve. Operate pump by pressing "WINDSHIELD" switch on control panel. collect fluid ove a timed period of 5 seconds. The fluid quantity dispensed should not be less than 25 OR mi. 2. Remove Windshield Pump and bench test.
Check Solenoid Valve. NOTE: Solenoid Valves have a history of reliability. It is recommended that all other components be checked out prior to further troubleshooting of Solenoid Valves.
1. Check Windshield Pump as detailed above. Reconnect Windshield Pump to Solenoid Valve. Operate pump be pressing "WINDSHIELD" switch on control panel. Fluid should be discharged onto the windshield, if not, disconnect Nylon tube from outlet of Solenoid Valve and repeat test. Fluid should be discharged from outlet of Solenoid Valve. If not, check electrical power at connections to Solenoid valve (See Figure 30-2) when pump is operating. If Solenoid Valve is suspected of not closing, -~isconnect electrical power to the valve and operate Windshield Pump. No fluid should be discharged from the spraybar (or Solenoid Valve outlet). OR 2. Remove Solenoid Valve and bench test.
Check Control Panel. NOTE:
Voltages specified
in Procedures are based on a voltmeter with a resistance of at least 10,000 ohms will differ if a lower per volt. Readings marked with resistance voltmeter is used.
1. Remove screws and pull Control Panel out as far as wiring will allow. Use voltmeter probe to measure voltage at the various pins in connectors C! C2 on rear panel (Figure 30-2
Schematic) [1] Aircraft Power ON all switches OFF All pins zero volts except: C1 -3 to be aircraft voltage. C1 -2 to be 7.5 volts C2 -1 to be +5 volts. C2 -2 to be between zero and +2 volts" (depending on tank contents) Ca -3 to be 5 volts.
[2] As [1] but with MAXIMUM selected. All pins zero volts except: C1 -3, -5 to be aircraft voltage. C1 -2 to be 7.5 volts* initially, changing to as pressure rises. All pins on connector C2 as [1].
[3] As [1] but with NORMAL selected. All pins zero volts except: C1 -3, -4 to be aircraft voltage. C1 -2 to be 7.5 volts* initially, changing to as pressure rises. All pins on connector C2 as [1].
zero
zero
[4] As [1] but with WINDSHIELD 1 selected. All pins zero volts except: C1 -3, -6, -8 to be aircraft voltage. C1 -2 to be 7.5 volts*. All pins on connector C2 as ~1].
4-99
30-12-02 13
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
LevellV Check Control
Maintenance Practice
M20M
SERVICE AND MAINTENANCE MANUAL
(conâ&#x20AC;&#x2122;t.)
Notes/Procedures
Panel.(conâ&#x20AC;&#x2122;t.)
[5] As [1] but with WINDSHIELD 2 selected. All pins zero volts except: C1 -3, -9, -11 to be aircraft voltage. C1 -2 to be 7.5 volts*. All pins on connector C2 as [1]. OR 2. Remove Control Panel and bench test.
[6]
As in
All
pins
[1], but with PUMP
1 selected. volts except: C1-3 and -7 to be aircraft voltage. C1-2 to be 7.5 volts*. All pins on connector C2 as [1]. zero
[7] As in [1], but with PUMP 2 selected. All pins zero volts except: C1-3 to be aircraft voltage. C1-2 to be 7.5 volts". All pins on connector C2 as [1]. Check Tank Contents Transmitter.
Remove seatlwing panel(s) to obtain access. 1. Disconnect connector C3. Measure resistance across contents transmitter leads at pins C3 as follows: All pins to ground >10 megohms Pin 1 to Pin 3 10,000 ohms (nominal) Pin 1 to Pin 7 should vary from 1/2 the resistance between Pins 1 3 (5,000 ohms nominal) with tank to approximatdy 3000 ohms with tank full.
emg~
2. Remove Contents Transmitter and bench test. 30-30-00- PITOT- DESCRIPTION AND OPERATION
6 v,
P c3
A standard heated pitot tube is located on left wing at Wing Station No. 145. The pitot heat circuit breaker switch located on C/B panel, in front of the pilots right knee, supplies power to the
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i
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4 Contents
6 Gallons
tube heating element. ABLUE light illuminate on annunciator panel when Pitot Heat switch has been pushed ON and current is being drawn by heating element. On some foreign aircraft a RED light will illuminate when pitot heat element is NOT drawing any current and will be OFF when properly operating. When the flight into known icing system is installed the heated pitot tube is a part of the TKS system (same location) but different from the standard heated pitot tube. 30-31-00
STALL WARNING VANE HEATED
The stall
warning
the
Right
into
vane
is heated when
i(nown
icing system is installed on the M20M. See Figure 30-2. The Stall Warning Vane heat is activated when the Pitot Heat switch is selected ON.
30-30-00 14
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
PROPELLER DESCRIPTION
30-60-00
MOONEY AIRCRAFT CORPORATION
OPERATION
Propeller ice removal is accomplished by either of two methods. If the Airfoil Ice Protection System is installed for Right into known icing, the ethelyne-glycol system is installed. Another configuration is optional, electrically heated de-ice boots bonded to each propeller blade. This system uses airplane’s electrical power to heat de-ice boots, in cycles controlled by a timer.
The ON/OFF switch is located on switch panel in front of pilots right knee. The BLUE light," PROP DE ICE", annunciator panel will illuminate at each cycle 90 seconds) the boots are drawing current. The ammeter may show a slight flicker each 90 second interval as timer tums de-ice boots ON/OFF/ON. This is normal operation. The timer is located on the equipment rack in tailcone. De-icer boot replacement should be done per de-ice kit on
(evety
manufacturer’s service information. McCauley Manual No. 830415, Spec. No. Me 2611-B McCaulley Dwg. No. D-40496. or TKS System from Aerospace Systems
Technology,
Inc.
PROPELLER DE-ICE
30-60-01
POWER REQUIREMENTS FOR 28 VOLT SYSTEM TERMINAL C
ON
OFF
90 SECONDS
TOTAL CYCLE TIME
8 AMPS
3 MINUTES
RECOMMENDED WIRE SIZE CHART
AWG SIZE
LOCATION
MAX LENGTH
BUS BAR TO TIMER
#14
15’
TIMER TO GROUND
#18
5’
TIMER TO BRUSH MODULE BRUSH MODULE TOGROUND SHUNT LEADS
#14
15’
#20
5’
30-61-00
SERVICE GUIDE
2. Use "heat test" (30-64-00) and "load meter test" (30-62-00) to determine which De-leers are not operating. Use wiring schematic to trace circuits. 3. Excess current reading on the ammeter may indicate a power lead shorted to ground. Thus, when
INTRODUCTION Whether in flight or during ground testing, the ammeter can be used to determine the general nature of most electrical problems. A Trouble Shooting Chart is provided later in this Section and it is assumed that the user understands normal operating modes of system. (See Section IX of P.O.H.). Read all 7rouble" entries to locate matching conditions of system being checked. The "Probable Cause" and "Remedy" entries pertinent to each trouble are arranged in recommended check out sequence. McCauley Manual, No. 830415 is recommended for maintenance actions. See Trouble schematics
3061-01
1. The Voltmeter is
following
4. A considerable number of timers have been retumed for repair which proved, on test, to be fully operable. Before concluding that the timer is faulty, test itper "De-lcer Timer Check" (30-63-00).
5. For insulation resistance tests, use a "megger" ("Meg" type insulation tester, James G. Biddle Company, Plymouth Meeting, PA.) or other tester having a 500 VDC, 1000 megohm capacity. 6. Defective wiring in propeller mounted components may be indicated by normal current readings in ground checkouts (propellers not rotating) but low current with propellers rotating at cruise RPM.
page.
HELPFUL TIPS will be slightly battery voltage
reading
system is operated
engine
on
trouble of this nature is found, it is vital that the S’ou"ded power lead be located and corrected.
on
lower when than when
running.
4-99
30-60-01
15
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
LEFT
SIDE
PANEL
PANEL
FLIGHT
M-PL206A
M-RC206A hl-~P03A14
M-MP02A14
M-MP07A14
M-MP06*14
M-~PIIA14
M-MP12A14
F~-MPr5A14
k-kP16A14
#2
M-PLE11A
k-RC211A
M-MPOIA14
IEcl
I
M-MP05A14
PROP DE-ICE DE-ICE TERMINAL BLOCK M-MP105A PROP
FIREWALL #2 M-RC225A ~-PL225A rr;c~
M-MP12A14
M-MPIO1A 20A
M-~P13A14
3-kP16A14 ---------------I
160C------
M-MP19A14
12~--- M-MP18A14
M-MP17A14
I L
POWER BUS BPIR #9 M-PB117A
GRND PLUG #2 M-PL17A
TPIILtONE M-RC231A M-PL231A M-MP03A14 M-MP04A14
k-MP07A14
L F(-MP09A14 I
PROP
G
M-MP08A14
M-kPllc\l4
M-MPIOAr4
~-MP15A14
M-MP14A14 EFF.:
C
27-0001
THRU 27-0052
PROP. DE-ICE SCHEMATIC-FIGURE 30-1A
27-0052)
(27-0001
PANEL #2 M-RC211PI M-PL211A
LEFT SIDE PANEL M-PL206A k-RC206A
M-MPa3A14
DE-ICE
TIMER M-MP102A
I-B
FLIGHT
k-MP02C14
M-lrlPO1AI4
---´•I
M-MP104A M-MPIIA14
PROP
M-MPIZP114
IIE-ICE
MONITOR
CURRENT
~-MP02C14
PROP DE-ICE
M-WC03B20
M-lrlPIOLA
M-wrlola
FIREW
20A DE-ICE
TERMINAL BLOCK
POWER
M-PL17A M-MP19B14
GRND
TL\ILCDNE
TAILCONE M-PLZJLLI
M-RCZ31~
27-0053
THRU
LEFT SIDE PANEL PLC0A RCEOA U
MP09Bi4
V
DE-ICE
C
27-0107
PROP. DE-ICE SCHEMATIC-FIGURE 30-1B
MPOSB1
PROP
TIMER M-MP102A
~-B
M-MP10A14
EFF.:
#2
Lhl-MPOSP1141PG
M-MPD3A14M-kPD4A14 F1-MPIIA14
PLUG
(27-0053 27-0107)
FLIGHT RC14A
PANEL #2
PL14A
4- ~P04A14
MPD1B14
MPIOA14
PL09A1
MP03B14
PROP
DE-ICE
CURRENT MONITOR CF(I
PROP DE-ICE
JUMPER FIREWALL RC32A
#1
~IO MP12B14
TAILCONE
27-0108
BAR BUSBA
PROP
G
THRU 27-TEA
(27-0108
DE-ICE
TIMER MPIOEA
C
4-99
M-
BUS
~-B
PROP. DE-ICE SCHEMATIC-FIGURE 30-1C
16
PL25A
MPIOBA
MP08A14
EFFJ
30-61-01
DE-ICE
20A
TERMINAL BLOCK
L MP07A14
PL14A MP05B14MP06A14 RC14A
MPa9B14
PROP
MPIO1A
IATOR
WC03A20
PL32A
~PIOA1hlP13814
ON)
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 3061-02
MOONEY AIRCRAFT CORPORATION
M20M
TROUBLE SHOOTING CHART- ELECTRIC PROPELLER DE-ICE
TROUBLE
Buss load meter/ammeter shows 0 current all phases of the timer cycle.
PROBABLE CAUSE
If no voltage into circuit breaker, locate and correct open.
No power from aircraft.
Tripped
Open
Locate and correct short before resetting circuit breaker.
circuit breaker.
Circuit breaker
or
switch
REMEDY
faulty.
Buss load meter/ammeter
to timer.
If no voltage at circuit breaker output with voltage at input and circuit breaker does not reset, replace circuit breaker. If voltage is OK at output, check switch in same manner.
Disconnect harness at timer and check for voltage at hamess Terminal B to ground. if none, locate and correct open.
Open
timer to brush
assembly.
Disconnect wire hamess at brush and check voltage to ground from leads. (See de-icing system wiring schematic for power and ground lead and pin identification.) If low or no voltage, locate and correct open or high resistance in wire hamess.
assembly
Check continuity from Terminal G, or lead to ground; if high resistance is indicated, check ground wire for breakage and ground connections for correctness and tightness. Correct as
required. Open
in
harness leads.
De-leer, De-leer wire or
slip ring assembly
Disconnect De-leer leads and check resistance per manufacturerâ&#x20AC;&#x2122;s service data. If not OK, replace faulty De-leer boot. If OK, check for land repair) open in de-ice boot wiring hamess leads. Ohmmeter needle must not flicker when leads are stretched or flexed. Replace as
Open
Buss load meterlammeter shows normal current part of cycle, zero current rest of cycle.
on
both
ground
brushes.
in wiring between timer and brush block assembly.
Open
Open in De-leer wire harness.
or
de-ice boot
4-99
required.
Remove brush block assembly and check both ground brushes for continuity between the brush and pigtail lead. If an open is found, repair brush block assembly. If OK, reinstall and check for proper face alignment and brush proiection per manufacturerâ&#x20AC;&#x2122;s Service Data. See "Open Timer to Brush above. See
"Open
Assembly"
in De-leer" above.
30-61 -02 17
OLDWILLWAYNE
TROUBLE (con"t.)
Buss load meter/ammeter shows normal current part of
cycle,
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
PROBABLE CAUSE
Timer
REMEDY
Test timer per Section 30-63-00.
faulty.
zero
current rest of
cycle. (con"t.) Faulty brush
block
assembly.
Check for broken brushes and test for opens.
Bus load meter/ammeter shows normal current part of cycle, low current rest of cycle.
Open
circuit or high resistance in De-leer or slip ring assembly leads. High resistance in circuit with low current.
See
"Open
in De-leer" above.
Check contact of brushes to slip rings per Section 30-66-00; correct as
indicated; check wiring from timer to De-leers for loose or corroded connections or partially broken wiring. Correct as required. Bus Load/Ammeter shows low over entire cycle.
current
Aircraft voltage low under normal operating conditions. Switch, or circuit breaker faulty.
into switch.
Check voltage up to and out of switch and circuit breaker. If low output is found through any of these items, replace defective component.
resistance up to timer.
Check for partially broken wire, or loose or corroded connection in wiring between aircraft supply and timer input. Correct as required.
High
contact resistance in timer.
Test timer per manufacturerâ&#x20AC;&#x2122;s service data.
Power lead shorted to
ground.
cycle.
Timer Bus Load/Ammeter indicates normal current part of cycle, excess current remainder of
voltage
High
One De-leer element (or wiring connections to De-leer) in each cycle out,
Bus Load/Ammeter shows excess current over entire
Check
Perform
a
heat test
on
each De-leer
per Section 30-64-00. Replace defective components. Check power leads from Buss load meterlammeter to timer, then to De-leers for evidence of damage or arcing. (See Section 30-60-01). If ground is indicated, locate and correct. Test timer per Section 30-63-00.
faulty.
Short to ground or short between timer and brush block,
Disconnect leads at brush block
timer, check for short or ground. Repair as
required.
cycle. Short between Timer
Bus Load/Ammeter does not â&#x20AC;&#x2122;Ylicker" each 90 seconds,
slip rings.
ground cycling.
open; timer not
system),
18
MEK.
Disconnect harness at timer and check
ground connection with ohmmeter from terminal G.
Timer contacts welded together (caused by short in electrical
Bus Load/Ammeter flickers between 90 second phase
Loose connection between aircraft power supply and timer
periods,
input,
30-61-02
slip ring assembly with
Test timer per Section 30-63-00.
faulty.
Timer
Clean
4-99
Test timer per Section 30-63-00. If timer is faulty, repair or replace it, but insure that short causing original failure has been located and corrected. Trace wiring from power source to timer input. Insure that good electrical contacts are made at each connection in the circuit.
OLDWILLWAYNE M20M
SERVICE AND MAINTENANCE MANUAL TROUBLE
Bus Load/Ammeter flickers between 90 second phase
Loose
poor connection; timer
or
to De-leers.
periods. (con"t.)
Timer Radio noise or interference with De-leers on.
Brushes
alignment. Check for dirty rough slip rings. If found, clean, machine or replace slip ring assembly. Check slip ring alignment. Check brush
arcing.
or
Switch
not correct.
wear or
frequent
or
See "Buss load meter/ammeter flicks between 90 second periods" above.
30-63-00
circuit breaker
faulty.
Place jumper wire across switch or circuit breaker; if radio noise disappears, replace switch or circuit breaker.
Wiring too close to radio equipment or associated wiring.
Relocate De-leer wiring at least 8" from radio equipment and wiring.
Crossed connections between timer and De-leers.
Check system wiring
Brush block out of
Check brush
alignment.
against circuit
diagram.
alignment. Correct as required.See section 3.3.3 of McCauley Manual No. 830415.
Slip ring
30-62-00
If trouble occurs only part of cycle, determine which De-leer is affected, check for rough or dirty slip rings causing brush to skip. Check circuits for loose or poor connections. Test timer per Section 30-63-00.
cycles erratically.
Loose connection.
Rapid brush breakage.
REMEDY
PROBABLE CAUSE
(con’t.)
Cycling sequence
MOONEY AIRCRAFT CORPORATION
Check slip ring alignment with dial indicator per Section 30-69-00.
wobbles.
Rough slip rings.
Re-machinelre-finish.
Dirty slip ring surfaces.
Clean
Brushes
Check brush
arcing.
slip rings with MEK.
alignment.
-FIOT USED DE-ICER TIMER CHECK
Experience in the field has indicated that often the timer is considered defective when the source of the trouble lies elsewhere. For this reason, the tests should be performed before the timer is removed as defective. Refer to manufacturer’s service data,
McCauley Manual No. 830415, Section 4, for test criteria.
TIMING SEQUENCE
TIME ON
AREAS OF PROP DE-ICERS HEATED
Terminal C
90
All Blades
30-64-00
sec.
30-65-00
100 HOUR INSPECTIONS
CONTINUITY TEST
removing plug continuity from:
After
Refer to manufacturer’s service inspection data for these steps. (McCauley Manual No. 830415, Section
from timer,
use
ohmmeter to check
1. Terminal C to outboard terminal of
4)
2. Terminal G to airframe
CAUTION Stand clear of propeller, verify magnetos OFF. Use extreme caution during this
ON then OFF
3. Ground terminal of
one
one
prop boot.
ground. prop boot to
ground.
are
procedure. 4-99
30-62-00 19
OLDWILLWAYNE
30-6600
BRUSH TO SLIP RING RESISTANCE TEST
To check for incorrect ~sistance or presence of a short or open circuit at brush-to-slip ring contact, disconnect harness at timer and check resistance from each De-leer circuit lead, Terminal C, to ground with a low range ohmmeter. If resultant readings are not 1.55 to 1.78 ohms, disconnect De-leer lead straps to measure boot Individual heater resistance individually. resistance should measure between 4.58 and 5.26 ohms. If readings in first check are not within accepted limits but those in second check are, the trouble is
If readings in second check are also off, the De-leer concerned is damaged and must be replaced.
probably in brush-to-slip ring
30-67-00
area.
BRUSH ASSEMBLY RESISTANCE CHECK
To check for an open circuit, a short, or high resistance in brush assembly, measure resistance from face of brush to its terminal studs with a low range ohmmeter. If this resistance measures over 0.013 ohms, locate and repair cause of excessive resistance. If resistance is infinite, locate and correct the open circuit or ground, or else replace brush assembly. Check resistance between the three terminal studs. This resistance should not be less than S megohms,
30-68´•00
BRUSH BLOCK ASSEMBLY REPAIR
Refer to manufacturer’s Service Data, McCauley Manual No. 830415, Section 6.5.1, for this procedure, 30-6801
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
-BRUSH REPLACEMENTIAUGNMENT
Refer to manufacturer’s Service Data, McCauley Manual No. 830415, Section 6.5.2, for brush replacement and brush to slip ring alignment. ALIGNMENT OF SLIP RING
30-69-00
slip ring assembly, securely engine and place pointer on a slip ring (see Figure 30-4). Grasp propeller blade and rotate it slowly, noting any deviation of slip ring from a 7RUE" plate as indicated on dial indicator. Check that To check alignment of attach a dial indicator to
total run-out does not exceed 0.008 inch total indicator
reading CTIR). CAUTION Due to loose fit of some propeller thrust bearings, a considerable error may be induced in readings by pushing in or pulling out on propeller while rotating it. Care must be taken to exert a uniform push or pull on propeller to
hold this
error
to
a
minimum.
CAUTION Do not, under any circumstances, attempt to correct run-out of slip rings by shimming assembly or changing torque of mounting screws or bolts. if slip ring run-out is within limits specified, no corrective action is required, If it is not within limits, check for dirt on ring gear mounting surfaces; clean, and recheck alignment. If run-out is still out of tolerance, refer to manufacturer’s service data for machining procedures or return the slip ring assembly to manufacturer.
30-70-00
-SERVICING/CLEANING
Thoroughly cleaning the slip ring area with MEK or standard engine degreaser on a routine basis is recommended. Keeping the
<P~
brushes free of dirt, oil, grease and carbon buikl-up will prevent thosecontaminants from being transferred to the slip ring.
ALIGNMENT OF SLIP RING 30-66-00 20
FIGURE 30-3 4-99
OLDWILLWAYNE
CHAPTER
LAN DING G EAR
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M CHAPTER 32 LANDING GEAR
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
32-00-00 32-1 0-00
PAGE
SU&IECT
General Main
LandingGearad doors
5 5
Main Gear Removal.
5
32-10-02
Main Gearlnstallation
6
32-10-03
Main Gear Door
6
32-10-04
Inboard Door
6
32-10-01
Rigging Rigging Bungee
32-10-06
Install Assist
32-20-00
Nose Gear and Doors
7 7
32-20-01
Nose Gear Removal
7
32-20-02
Nose Gear Installation
7
32-20-03
Nose Gear Door
32-30-00
Rigging
32-30-01
Gear
32-30-02
Main
3250-07
System Operational Inspection Ldg Gear System Rigging. Nose Ldg Gear System Rigging Emergency Gear Extension System Rigging Landing Gear Actuator, Clutch Landing Gear Actuator Manual Emergency Gear Extension System
32-30-08
FinalChecks
32-30-03 32-30-04 32-30-05 32-30-06
32-31-00
Trouble
32-40-00
Wheels and Brakes.
7
8
Extension and Retraction
8 9 11 12 13 15
16 16 16
Shooting
17
32-40-01
Main Wheels
17
32-40-02
Main Wheel
17
32-41-00
DissassemblylAssembiy Brake System TroubleShooting -BrakeSystem
22
32-50-00
Steering.
22
32-40-03 3240-04
Nose Wheel
32-50-01
Nose
32-50-02
Steering Tracking and\l\laming Electric Gear Safety Devices Landing Gear Warning System Airspeed Safety Switch Adjustment
32-60-00 32-60-01
32-60-02 32-60-03
Geara,ering system
Nose Gear
8
Position
32-80-00
Miscellaneous
32-81-00
Landing
32-82-00
Recommended
19
22
22
23 23 23
23 24
Gear Shock Disc
Inspection
18
Inspection
HardlandinglOvenrveightLandinsâ&#x20AC;&#x2122;
24
25
32-CONTENTS
Page 3/48LANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 32 LANDING GEAR
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT
32-Effectivity 32-Contents.
PAGE
DATE
1/2BLANK 3/4BLANK
4-99
4-99
32-00-00.
5.
4-99
32-10-02.
6.
4-99
32-10-06.
7.
4-99
32-30-00.
8.
4-99
32-30-02.
9.
4-99
32-30-02
10
4-99
32-30-03
11
4-99
3250-04
12
4-99
32-30-05
13
4-99
32-30-05
14
4-99
32-30-06
15
4-99
32-30-07
16
4-99
32-40-00
17
4-99
32-40-03
18
4-99
32-40-04
19
4-99
32-40-04
20
4-99
32-40-04
21
4-99
32-41-00
22
4-99
32-60-00
23
4-99
32-80-00
24
4-99
32-82-00
25
4-99
32-82-00
26
4-99
32-EFFECTIVITY
PaSel/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
This releases hydraulic pressure at the wheel and therefore releases the brake discs.
GENERAL
32-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
The
landing gear is operated by an electrical, motor driven, actuator. The travel during the extend and retract cycle is controlled by down and up limit switches located beneath the floorboard under the pilots seat. Power is supplied to the actuator through a set of relays actuated by the gear selection switch. The gear selection switch Is located at the top of the instrument panel in front of the pilot. The actuator worm gear ball nut is connected to the retract bellcrank which is connected to push-pull retract tubes and bellcranks throughout the entire retraction system. An airspeed safety switch is mounted to the back of the airspeed indicator and incorporated into the landing gear electrical circuit to prevent landing gear retraction while on the ground until a safe takeoff speed is reached. A by-pass switch is installed adjacent to the gear selection switch in order to override the safety switch circuitry if the gear does not retract, The constructed of welded legs are gear chrome-molybdenum tubular steel, heat treated for greater strength and wear resistance. Main gear attaching points have bushings installed in the gear mounting box attached to the wing spar. The steerable nose gear mounts to the cabin tubular steel frame.
cylinders
32-10-00
MAIN LANDING GEAR AND DOORS
32-10-01
MAIN GEAR REMOVAL
1. Raise aircraft
on
jacks.
Partially retract gear 32-60-01, pam. 1. 2.
as
described in SECTION
Cap
3. Disconnect gear door links and brake lines. ,II lines and fittings. 4. Remove gear door and mud
guard (if desired). from from
gear retracting tube retracting truss (G), and remove bolts retracting truss mounting block (Figure 32-11). 5.
Detach
main
three screws from small skin panel 6. Remove covering aft portion of landing gear leg trunnion and bearing bracket from bottom of wing. Slide panel from position to gain access to bracket bolts. 7´â&#x20AC;˘ Remove six mounting bolts (2) from rear gear leg trunnion shaft mounting block assembly (3) 8 (4) at stub spat (5). Shims (6) may fall out. 3. Slide aft bearing block (4) down. (Fig. 32-1)
bearing block (3) down/ aft and remove. 10. Slide gear leg assembly (1) aft until dear of front bearing (7) on main spar (8). Carefully remove gear assembly from wing. 11. Identify position of all components removed, and DO NOT intermix right and left gear components. 12. DO NOT attempt to repair any heat treated component of main landing gear assembly. 9. Slide front
NOTE Heat treated components should NOT be repaired; replace them. The main gear wheels have hydraulic disc brakes with a parking brake valve incorporated into the system. Rubber discs in the gear leg assemblies absorb the shock of landing and taxiing. LANDING GEAR EMERGENCY EXTENSION SYSTEM.
Emergency gear extension is available through a manual override system. This system is built into the actuator unit. Thedisengage controls are located aft and between the front seats.
I
LANDING GEAR WARNING SYSTEM. The landing gear warning system provides the pilot with an audible warning that the landing gear is nod INBD down and locked when the throttle is retarded. The waming system on is activated when the throttle is retarded approximately 1/4 inch from idle Dosition. When the landing gear is down and locj<ed the electrical circuit is opened and the intermittent horn is FWD stopped. This warning switch is mounted on the throttle housing forward of the instrument panel and can be adjusted for the proper setting by loosening the screw and repositioning the switch.
C
BRAKE SYSTEM.
The
brake system is hydraulically operated by depressing the brake pedals mounted on the pilots rudder pedals. (Dual brake system is optional cc-pilots). Individual wheel brakes are available by depressing either left or right pedal. Parking brakes are actuated by depressing both brake pedals and pulling the parking brake control cable knob. This actuates a lever on the parking brake valve and traps the hydraulic fluid from the valve to the wheel cylinders thus
holding
parking
the
brakes
pucks
to the discs.
by pushing
the
parking
SMX32-7
Release the brake knob in.
GEAR REMOVAL 4-99
FIGURE 32-1 32-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MAIN GEAR INSTALLATION
32-10-02
1. Lubricate wheel bearings, retraction linkage, and fore and aft trunnion bearings prior to installation at lubrication fittings !9). Refer to SECTION 5-20-07 for
recommended lubncants.
2. Installation of main gear is the exact reversal of the main gear removal procedure.
NOTE -003 or -005 bolt to 270 to 300 in. Ibs.
Torque 510073-001,
3. Check fore and aft movement of gear in bearing blocks. Maximum allowable movement is .020 in. Shim excess by inserting maximum of two shims (6) between the two rear blocks. 4.
Temporarily
attach gear door link rods to gear
leg
brackets. 5. Retract gear while checking for binding in door linkage and proper contact of gear door edges with wing. DO NOT make final gear door adjustments until gear has been rigged (Ref. 32-30-02).
MAIN GEAR DOOR RIGGING
32-10-03
1. Raise aircraft
on
jacks.
See SECTION 7-10-00.
MOONEY AIRCRAFT CORPORATION
any reason the following rigging used when reinstalling them:
procedures
should be
A. Disconnect outboard doors at forward and aft
linkages (B)(Fig.32-2). B. Disconnect inboard doors at forward linkage and springs (A) (Fig.32-3). C. Raise gear electrically to the full UP position. D. Forward leading edge and aft trailing edge of the mid-gear door should be tight against the wing skin. Spacers (A) (Figure 32-2) should be added or removed as required to obtain a good fit with no binding or distortion with the gear in the UP position. AN960-10 or
AN960-416 washers may be used
as
spacers.
3. Reconnect outboard and mid-gear doors and check that doors are faired with wing skin/wheel well opening and that there is no binding or distortion where links attach to door. Adjust linkage/spacers if required. (Figure 32-2) Extend gear to adjust, then retract to check adjustment. 4. Check main gear overcenter preload torque for proper values. Re-rig entire landing gear system, if 32-30-03). necessary (See SECTION 32-30-02
32-10-04
INBOARD DOOR RIGGING
Adjust inboard door link to close doors with "O" gap. Doors must be closed with gear extended and retracted. If door is not closed in both positions refer to landing Qear rigging procedures in SECTION 32-30-02. Any adjustment to rod end on main retract tube (L) (Fig. 32-7) and rod end on retract tube (V) (Fig. 32-11) is at a 2 to 1 ratio, respectively; this adjustment will change rigging values. Re-check preload values. 1.
e~.´•.-. -..=L~
EXAMPLE: If the inboard gear door is open a small landing gearis down, but closed when gear is UP. Adjust by turning retract tube (V) rod Lbl 1/2 turn, and retract tube (L) (Fig. 32-7) rod end amount when
I; /7
l:IIU~dne turn.
EXAMPLE: If the inboard gear door is closed with landing gear in the DOWN position, but open a small amount with landing gear in the UP position. Adjust by tuming retract tube (Fig.32-11) rod end PUI 1/2 1 tum. turn, and retract tube (Fig.32-7) rod end
1
I1
\ii
i:
rl
II
i.
2. Tighten jamb nuts and reconnect inboard gear door bellcrank (A) (Fig.32-3).
’I
NoT,
3. Adjust outboard door link to close all gap at leading edge of door. If door is rigged too tight, skin will be under stress (concave) at the point where the linkage is attached to door. It could also cause mid
and inboard doors to gap open.
MID-GEAR DOOR ADJUSTMENT POINTS FIGURE 32-2
4. Cycle gear manually inspecting for clearances. system rigging values.
NOTE Gear system must be properly rigged prior to gear door rigging, see SECTION 32-30-01. 2.
Normally no
once
the doors
installed at the be required. doors be removed for are
further adjustment should
However, should the mid-gear 32-10-02
on
Do not rig doors shut more than necessary as this may resutt in higher actuator loads than necessary.
.I 1;
factory
springs
4-99
and electrically while Re-check landing gear
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
II
I´•Ei’ 1.35 in.
ii D
II
v
c
B
ASSIST BUNGEE
MAIN INBOARD GEAR DOOR RIGGING
5. Remove aircraft from
3. Disconnect link
FIGURE 32-3
INSTALLING ASSIST BUNGEE
(560213-501) 1. Retract gear. 2. Pull gear down with emergency extension until main retract bellcrank and rod end bungee line up. Install proper length AN3 bolt through rod end bearing and proper length AN4 bolt through block. Torque nuts
4.
32-20-02
preload
NOSE GEAR AND DOORS
32-20-01
NOSE GEAR REMOVAL.
2.
Partially
jacks per
gear
steering
32-20-03 1. Raise 7-1 0-00.)
per steps
(B)
NOSE GEAR INSTALLATION
linkage and
procedure.
NOSE GEAR DOOR RIGGING aircraft
on
jacks.
(Refer
to
SECTION
NOTE Gear system must be properly rigged prior to gear door rigging, see SECTION 32-3091. 2. Adjust gear door link rods (H and J obtain proper door fit when closed.
SECTION 7-10-00.
retract gear as described
link
horn
2. Install gear in reverse order of removal
32-20-00
on
nose
1. Lubricate wheel bearings, retraction left and right mount bearings.
CAUTION
1. Raise aircraft
Disconnect
5. Remove left and right gear mounting bolts (D) and (E) (Figure 32-5) from tubular structure and nose gear truss assembly. 6. Carefully remove nose gear assembly. DO NOT attempt to 7. repair heat treated components of nose landing gear assembly.
Bump gear up, CAREFULLY, just to take load off the 3/16 in. installation pin at (B). Remove pin from (8) (Fig. 32-4). 3. With bungee installed re-check 30 thru 34 of SECTION 32-30-02.
assembly
(Figure 32-5).
safety,
and
gear truss
CAUTION Eccentric bushings at (J) (Fig. 32-6) may have a flush head screw installed on either side. This flushhead screw and counter sunk eccentric MUST BE re-installed at same locations.
6. Retum aircraft to service.
32-10-06
on nose
(Figure 32-5).
jacks.
NOTE To remove INBOARD GEAR DOORS use a sharpened punch less than .093 dia. or a short piece of hinge pin to open the crimped hinge assembly pin hole.
(A)
FIGURE 32-4
Figure 32-5)
to
by SECTION
32-60-01. 4-99
32-10-06
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
F,e
Q
F:
K -;u
a FWD
NOSE GEAR RETRACTION TUBE 8 DOOR ADJUSTMENT POINTS -FIG.32-6 NOSE GEAR RETRACTION TUBE ADJUSTMENT POINTS FIGURE 32-5
to
3. To increase or decrease nose gear-up travel in wheel well, adjust eccentrics on trunnion bearings (J),
(Figure 32-6)
as
8. Check
EXTENSION AND RETRACTION
32-30-01
GEAR SYSTEM OPERATIONAL INSPECTION
on
preload.
A. Place rigging tool O P/N GSE 030007 on retraction truss. Hold tool stationary by thumb on rear end of tool (S) and press fonnrard.
32-11)
(Figure placing
8. Hold 10" torque wrench (R) and place thumb on wing bottom; apply force until joint (4) breaks open slightly, insert shim stock (.005 .008 in, thickness) between link and truss at (P). Release force on
wrench.
C. With fingers on torque wrench and thumb on wing bottom apply force on wrench while maintaining a pulling force onshim stock. Read torque value on wrench at the exact moment the shim stock pulls loose. Torque value should be 250 to 280 inch pounds.
lower gear.
With zero airspeed place gear switch in UP position. Gear horn should sound regardless of throttle position, both gear position lights and safety bypass switch will illuminate. 5.
3250-00
follows:
bungees. (No load)
9. Check main gear overcenter
3. Close throttle and confirm gear horn sounds.
closing;
gear
as
D. If spring deflection is not within prescribed limits, adjust tube rod ends (F) (Figure 32-6) in increments of 112 turns as required.
jacks. (See SECTION 7-10-00).
Inspect gear doors for proper
nose
preload
C. Measure nose gear bungee springs (Fig.32-8). Deflection from zero load condition in (A) above must be .030 to .070 inches for each bungee.
2. With Master Switch ON and gear switch in UP position apply pressure to pitot tube (see SECTION 32-60-01). Verify gear retraction occurs at 60 +/-5 KIAS. Allow gear to raise completely. Check for any tire interference as tire enters wheelwell.
4.
gear overcenter
B. Extend gear manually (See SECTION 32-30-07) stopping extension the moment the GREEN Gear DO" Light comes ON. Gear switch in DOWN position.
CAUTION After any abnormal, over gross or hard landing the Gear System Operational Inspection should be done. 1. Raise aircraft
switch and hold IN
(Fig. 32-8).
after
32-30-00
nose
A. Measure
CAUTION Nose gear overcenter preload must be re-checked after any adjustment to nose wheel eccentrics.
linkage as required (Figure 32-6, K.)
bypass
7. Pull "GEAR ACT" circuit breaker.
required.
4. Readjust nose gear door eccentrics have been moved.
6. Push RED gear safety partially retract gear.
D. 4-99
Repeat
on
other main gear.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
H
Iq,L
J
I
I
Bci~l!
O\\I
~o
da
MAIN GEAR RETRACTION TUBE ADJUSTMENT POINTS E. If
preload is
not within prescribed limits, proceed Gear Rigging procedures, SECTION
F. If main gear
preload needs re-adjusting, the gear bungees should be re-checked per 8, (C) above (Fig. 32-8). nose
NOTE When gear overcenter preload check is completed, electrically extend the gear and check the nose gear tube bungee springs to assure they have not compressed completely resulting in no remaining deflection. This would indicate excessive preload or weak bungees. 32-30-02
Raise aircraft on jacks and remove three 1~ fiberglass belly access panels. Assist Bungee Assy Removal (when required). Retract landing gear until rigging pin holes (B)(Fig. 32-4) line up on bungee assembly and insert 3/16 in. pin. CAREFULLY BUMP gear UP, with the gear safety bypass switch, until there is zero load on bungee assy
rod end. Remove AN3 bolt at rod end and AN4 bolt at
block;
bungee assembly. landing gear actuator circuit breaker out. 3. Loosen jam nuts (E) on the main retraction tubes (L), Fig.32-7; disconnect tubes at inboard bellcranks (M). 4. In nose gear well, loosen jam nuts (G), Fig.32-6, on nose gear retraction tubes (F). 5. At the main retraction bellcrank (A), Fig.32-12, remove
2. Pull the
MAIN LANDING GEAR SYSTEM RIGGING
Changing
eccentric
bearing position can change bungee spring. Shortening tube assy. creates compression on bungee (refer to Fig. 32-8) deflection
FIGURE 32-7
on
disconnect the
nose
actuator barrel nut at
560245
(REF)
Deflection of to
Nose Gear
spring rigged position to
Bungee
gear retraction tubes and the 32-12.
(N), Fig.
6. Check dimension from the rod end center to the end of the barrel nut housing on actuator (Avionics Products only, Plessey is non-adjustable) to be 1.25 +.000/-.010. Adjust rod end bearing, if necessary, and secure with set screw and jam nut.
from static length be .030 to .070 in.
NOSE GEAR BUNGEE SPRING
FIGURE 32-8 4-99
32-30-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 8. Disconnect
MOONEY AIRCRAFT CORPORATION
M20M
approximately
gear doors, outboard main gear doors, and inboard door links. On outboard main gear doors, disconnect springs. On inboard door bellcranks, disconnect springs. Loosen jamb nut (X) on retraction tube 01) (Fig. 32-11) and back off pressure on spring (W) by loosening nut C~. Disconnect retraction tube O~ from bellcrank (C) (Fig. 32-3). nose
truss at F.S. 33
from forward face of Detail A).
1.56 inches
(Fig.32-12,
*kX
NOTE This dimension m may vary to permit connection of retraction tubes with zero preload at bolt hole.
10´• With main retract bellcrank held in position, turn actuator barrel nut until rod end bearing aligns with in bellcrank; install connection bolt at (N), Fig. -12.
9. Position main retraction bellcrank (A) so center of forward hole in the left outboard arm of bellcrank is
11. Position bellcrank
(C) (Fig. 32-3),
so
center of
top leg is 1.35 inches from bottom of spar cap (E). This will be the starting position
pin (D)
O
on
landing gear is in down and locked over center, preload set. 12. Adjust retraction tube (V) (Fig. 32-11), at rod until it will connect to bellcrank (C) (Fig. 32-3) with
~Vith cut any
~L
connection bolt/hardware, t thisa time. evael
Adjust rod end on retraction tube (L) (Fig. 32-7) attach hole is aligned with inboard bellcrank at (M). connection bolt/hardware.
13.
14. Disconnect retraction tube
(V)
at bellcrank
(C)
end; position disconnected gear full down and
center. Both LH and RH landing gear be in this configuration at this time.
over
15. PUSH
landing
gear actuator C/B
16. Turn MASTER Switch
IN.
ON.
Extend main gear actuator to fully extended Make certain lugs on main retract bell crank not contact fuselage tubes, floorboard or actuator nut. If there is any contact, run actuator back up
17.
MECHANICAL DOWN STOP ADJUSTMENT MECHANICAL DOWN STOP
FIGURE 32-9
18. There should be .050 to .100 inch clearance (B) obtained between actuator barrel (C) (Fig.32-9) and mechanical down stop (A). Shims (D) (Fig. 32-9) may be added to the mechanical downstop (A) (4 max).
LEGEND FOR FIGURE 32-9
A. 560252-009
Adjustable Stop (use 560252-011 shims) 19. Run actuator down and recheck retraction bellcrank clearance at F.S. 33.. Check clearance of bellcranks (M) (Fig.32-7) and center section.
NOTE Use 1 to 4 560252-011 shims with 560252-009 stop to achieve proper clearance. Use
one
DOWN STOP
on
each side
as
20. Reconnect retraction tubes O~ (Fig 32-11). With main gear fully extended, if necessary, adjust main gear retraction tubes (L) (Fig.32-7) so they are connected with zero preload.
required
(Pick
B..050 of ball nut)
up existing hdw). .100 clearance (between down-stop and end
C. Actuator ball nut. D. 560252-011 maximum of 4).
E. AN515-6R
shims*
screw
(use
with
560252-009,
i
22. NOSE GEAR RETRACTION TUBES ARE TO retraction main at DISCONNECTED REMAIN bellcrank (A), Fig.32-12, during remainder of
M
AN936A6 Lock Washer
procedures.
(Typ. 2 pie.) (use with 560252-009). longer screws with each additional shim. (Secure screw with Blue LocMite #83-31 grade C). Use .063
F. Loosen set 3230-02
10
screw
21. Adjust nut (Y) of retraction tube (V) (Fig. 32-11) until main gear is preloaded. Preioad is correct when a "clean break" can be felt when pushing UP on ’et’action link (Fig. 32-11).
32-10. 4-99
23. Place
landing gear switch
in UP
position.
RED gear safety by-pass switch IN to "BUMP UP" (retract) landing gear until left main tire just contacts bumper bracket which covers 24.
PUSH
intermittently
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
31. Place 10 inch torque wrench ~R) as shown in Fig.32-11 and apply an to retraction truss.
on
C
rigging
tool
unlodting force
(T)
FWD
32. When joint at (4) breaks open slightly, insert shim stock (.005 to .008 in. thickness) between retraction link and truss at (P), then release force on torque wrench. 33. While applying a pulling force on the shim stock, exert an increasing unlocking force with torque wrench. 34. Read torque wrench value moment shim stock pulls loose.
B
35. Repeat steps landing gear leg.
through
30
34
EXACT
the
at
on
other main
36. Use adjusting nuts (Y) on retract tubes (V) to equalize breakaway torque values within 10.0 inch Ibs. Adjust torque to 250 to 280 inch Ibs (ref. Fig. 32-11). 37. Turn Master Switch
I
o
ON.
38. RUN GEAR DOWN ELECTRICALLY AND CHECK THAT TORQUE VALUES DO NOT EXCEED POUNDS TORQUE INCH USING 325 WRENCH/SHIM STOCK METHOD.
GEAR WARNING ADJUSTMENT Check that landing breaker pushed IN. 1.
MECHANICAL UP STOP
FIGURE 32-10
2´• Check that
bulb stringer in wheel well. Make certain actuator barrel does not contact main retract bellcrank in UP position.
3. Turn Master Switch
25. Set UP limit switch paddle (striker arm) (H), so GEAR UP limit switch is just CLOSED and RED "GEAR UNSAFE" light is OFF. Secure striker arm in position.
OFF.
NOTE The main gear preload torque should not exceed 325 inch Ib. using the torque wrench/shim stock procedure after electrical extension.
32-10-06.
28. Using emergency gear extension, move gear down until GREEN gear down light JUST illuminates.
The main landing gear system is gear down and locked condition.
29. Turn Master Switch -OFF.
NOTE The left main gear truss will probably lock over center first. Continue to slowly lower gear manually while monitoring compression of bungee spring on retraction tubes (V) Pig. 32-11. If spring coils are fully compressed, retract tube (V) must be removed from aircraft for
32-30-03
now
rigged for
the
NOSE LANDING GEAR RIGGING PROCEDURE
1. Check the eccentric bushings (J), Fig.32-6, on gear truss assembly to be installed with bolt hole at the upper forward position. nose
modification:
CAUTION The eccentric bushings, on either or both sides, may be countersunk and have a flush head screw installed to allow clearance of nose gear truss during retraction/extension cycle. This configuration MUST be maintained during any removal/installation action for the truss or eccentric bushing.
bungee portion of tube (V); remove space washer O and reassemble.
Dismantle
Re-install modified retraction tube and overcenter requirement. The addition of spacer washers may be prior to obtaining final configuration for the retraction tube 01).
complete above or
required
ON.
position.
5. Tum Master Switch
(C).
removal
in
arm
Loosen set screw (C) Fig. 32-10. Adjust mechanical up-stop (A),Fig. 32-10, for a clearance of .050 to .070 inches at main retraction truss (B); tighten
one
actuator circuit breaker is
4. Set DOWN limit switch paddle (striker arm) (J),FIg. so that gear down limit switch is just CLOSED and GREEN "~EAR DOWN" light is ON. Secure striker
26.
bungee per SECTION
circuit
32-7,
MECHANICAL UP STOP ADJUSTMENT
27. Reinstall assist
landing gear
waming light
pulled OUT.
Fig.32-7,
set screw
gear
Place 30. rigging tool CT) (Fig.32-11) P/N 030007-100 on retraction truss assembly (G). Hold tool stationary by pushing at point (S) toward main gear
nose gear retraction tubes (F),RS. 32-5, so be reconnected to the main retraction bellcrank with zero preload.
2.
they
leg. 4-99
Adjust can
32-30-03
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
X
1.SB(MAX)
W
S
V
RETRACTION I I I I I I
LINK\
T RIGGI IU G
TOOL 030007-100
R ETRACTI O r\i Ld/
G’
TRUSS
LEFT
(VIEW
MAII\I
TORQUE WRENCH
II\ICH LBS.R
GEAR
LOOKING
cE
FWD FIGURE 32-1 1
MAIN LANDING GEAR RIGGING TOOL APPLICATION
Measure nose bungee assemblies gear dimension "P" as shown in Fig. 32-8. If the springs have deflected less than .030 inches or more than .070 inches from the static dimension las recorded in Step 2), adjust the length of the bungee assembly’s to bring the deflection within tolerance.
NOTE
15.
The eccentric a new
bushings may require rotating to position in order to meet zero preload condition.
3. Measure
nose
gear
250 -280
bungees
dimension
(P),RS.
32-8, and record for future reference. 4. Push
5. Place
IN.
gear actuator C/B
landing
gear switch in the UP position.
6. Turn Master Switch
DISENGAGE RIGGING:
ON
1´• Insert cable thru hole in actuator
7. Push RED GEAR SAFETY BY-PASS SWITCH IN and hold it IN to partially retract landing gear; release switch.
8. Turn Master Switch
9. Pull 10.
landing
Screw
nose
gear
tube
3. Install D222 wire stop, to clevis pin, (D).
(F),Fig.32-5, IN (clockwise looking toward the front of the aircraft) one (1) full turn, then re-attach to main landing
4. Lift RED lever and
gear switch in DOWN
felt check cable
32-13)
13. Pull RED lever
(1), Fig. 32-13, back and upward engage manual emergency gear extension system.
’T’ handle
(2) (Fig. 32-13)
to
verify
routing through pulleys whether it is cable
3 and 4 (Fig. or actuator
routing
resistance. 5. Move RED lever to full UP position; pull "T" handle to verify manual extension system is engaged. Resistance should be felt at once.
14. Pull ’7" handle return it to its original
(2) UP (slowly until engaged) and position. Continue thisprocedure, stopping when the gear down light JUST illuminates. 12
pull
system to verify that it is fully disengagf?d by pulling "T" handle; no resistance should be felt. If a resistance is
(5), Fig. 32-13, FORWARD on manual emergency extension controls ton floorboard).
32-30-04
nut and connect
aside; re-engage RED lever. Check manual extension
position.
12. Push latch
to
(C) tighten
spring (E)
retraction bellcrank. 11. Place
arm,
2. With RED lever (1) (Fig. 32-13) in full disengaged position (down and latchedj, push actuator disengage arm (B) (FIG.32-12) to full forward position and apply approximately 5 Ibs. pull to cable to remove slack.
OUT. retraction
disengage
(B) (Figure 32-12).
OFF.
gear actuator C/B each
EMERGENCY GEAR EXTENSION SYSTEM RIGGING.
32-30-04
landing
slowly 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL c
FWD
1.25
in.
(+0/-.01)
E B
D
N
F
FUS.
STA.
33.0
-1
C~-- 1.56 IN. (APPROX.) DETAIL A ’SIART’NG POSITION
DETAIL
ONLY)
LANDING GEAR ACTUATOR ADJUSTMENTS 6. Replace "T" handle under RED lever and return RED lever to disengage position, (down and latched). Manual extension system is now rigged.
i
B
FIGURE 32-12 NOTE
Plessey actuators should be lubricated every 2000 cycles with MIL-G- 81322 grease. Run actuator to mechanical extended position. Fill tube cavity with grease via MS15001-1 grease fitting until old grease is purged from screw assembly; remove old grease from and relubricate exposed screw. Run actuator to approximately 0.5 in. or mechanical retract and remove the major excess grease extruded from barrel nut assembly. 32-30-05
LANDING GEAR ACTUATOR, CLUTCH SPRING REPLACEMENT
P/N 102000,
Clutch Spring Kit, less shims, number SI 20-52-001
provided
in MAC kit
Landing gear actuator clutch spring replacement is mandatory at each 1000 hours of aircraft operation (See SI M20-52(current revision). all dash #’s require this 1000 Hr. maintenance) ~ETRACTiON CABLE
ACTUATOR REMOVAL FROM AIRCRAFT 1. Jack aircraft in accordance 7-10-00. Belly panels should be OFF. 2.
Partially
retract
landing
with
SECTION
gear from the overcenter
position. DI~HOAOE Rovruco
3. Loosen set
handle/cable
on
extension’7" screw on emergency cabin floor. Pull cable from handle.
4. Remove two nuts, (1) (Figure 32-14); note of cable support bracket (2) and remove.
EMERGENCY GEAR EXTENSION SYSTEM FIGURE 32-13
position
5. Remove manual extension system disengage cable from actuator disengage arm (Ref. Fig. 32-12). 4-99
32-30-05 13
OLDWILLWAYNE
ACTUATOR
PLESSEY SEE
MOONR( AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
M20-92
INSTRUCTION
SERVICE
15
,%I
2
MOD. 5
IDENT.
PLATE
7
12
9/
SEE SERVICE
LDG. GR. ACTUATOR 6.
Remove
bolt from
Helm
bearing
at
(EXPLODED VIEW)
7. Disconnect electrical connection from actuator.
lug
impact screwdriver
to
(3), and two short screws secured with LocMite Grade A.
screws are
With 2. identification
razor
two long Screw 8 bolts
remove
(4).
tool, slice entire recoiler
similar
or
plate and
remove
FIGURE 32-14
through assembly
(5). NOTE Care should be taken to not allowbearings or shims to drop out of clutch housing mount
Be
3. Remove input gear assembly (6) from clutch housing (8) by rotating and pulling with slight force. 4. Remove two screws (7) and remove clutch housing (8), clutch (00-back) spring (9), and input gear assembly (10) from actuator body.
sure
spring
When clutch
input gear (6) and small
14
can
be
NOTE is properly seated, large be rotated in either direction gear (10) will follow rotation direction.
spring can
output
output gear teeth (10) with MIL-G-81322 and install clutch housing, gear and spring into actuator body by mating (10) gear to the output gear train assembly. To engage gear teeth and 4. Lubricate
poly-lube assembly
NOTE
Spring
NOTE is all the way in and seated around cam.
3. Insert clutch gear assembly (10) into clutch spring and housing frrom cylindricalend of husing, insuring that spring tangs fit into recess in cam.
5. Remove clutch (no-back) spring (9) from clutch housing using input gear assembly (6) as remova tool. Insert (6) into clutch spring from flanged end of housing (8), and remove clutch spring by rotating gear CCW and pulling slightly.
32-30-05
for
1. Lubricate clutch housing I/D and new clutch spring thoroughly with lube (Mll-G-81922) poly-lube. 2. Using gear assembly (6) as insertion tool, place new clutch spring (9) on cam end of assembly and tuming CCWI install spring into clutch housing (8) to about mid-point. Do not force spring. While continuing to turn CCW, gently push clutch spring into bore until fully seated. Withdraw gear assembly (6).
assembly.
DO NOT TURN CW.
reassembly
RE-ASSEMBLY OF ACTUATOR
DISSASSEMBLY OF ACTUATOR Use
INSTR. M20-5ZB
8. See 32-30-06 procedure prior to additional maintenance, if necessary.
at Hat Section.
9. Remove actuator from aircraft.
1.
102000)
6. After disassembly, clean clutch, gears, and housing thoroughly. Discard removed screws (3) 8 (4). Discard old clutch (no-back) spring.
retract
bellcrank.
8. Remove bolt from
ACTUATOR
(P/N
i,,
SMM3~-14
EATON
13 11
damaged. 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
fully
seat hub into
assembly
9. Reinstall cable support bracket and lock nuts to -43 bolts. Torque lock nuts to 20 25 in. Ibs.
5. Reinstall screws (7) to secure clutch housing into actuator body. Use Loctite Grade A on threads,
10. Install modification plate adjacent to I.D. plate first 1000 hours only). Mark the first block of modification plate with the figure "1" using metal stamp or etching tool. Mark plate at each succeeding clutch spring replacement with the next consecutive number.
may be
bearing,
rotation of gear
SERVICE AND MAINTENANCE MANUAL
M20M
required.
Reinstall input gear assembly (6) into clutch an clutch spring assembly until fully seated, Lubricate (6) gear teeth with MlL-G-81322 lubricant, 6.
housing
Ila. Install Actuator to
Ilb. Install Helm to retract bellcrank. Ilc.
Insert cable into
32-30-06
through support
handle and
tighten
on
set
floorboard.
screw.
belly panels.
LANDING GEAR ACTUATOR, RECOILER P/N 102000-("), SPRINGS/ CABLE AND DRUM
ASSEMBLY REPLACEMENT
Normally the existing shims (12) already installed behind bearing (11) will be correct for the new clutch spring. However, due to manufacturing tolerances, it may be necessary to change shim thickness for proper spring adjustment.
All dash numbers actuators
are
applicable
for P/N
102000-(
aircraftper SECTION 32-30-05. 1. Carefully separate pulley housing from recoiler assembly (5) by removing screws (14) (Ref. Fig. 32-14). Retain pulley on shaft. 2. Slide pulley drum and cable off shaft. 3. Remove two (2) recoiler springs, and two (2) of three (3) spring spacers leaving third spacer in housing. Be certain that spacer is in place before installation of two (2) new recoiler springs and previously removed spacers. 4. Install new recoiler springs placing a spacer between each spring and over top spring. IMPORTANT Recheck proper installation of springs. Remove actuatorfrom
7b. Three different thickness of shims are available MAC Service Centers, EATON P/N’s:
through
(.003 in. thk.) (.005 in.thk.) (.010 in.thk.)
Any combination of these shim thickness are allowed to obtain correct rotational torque (inch Ibs. of torque) of input gear shaft after clutch housing mount assembly is installed and torqued. 7c. The rotational torque used by EATON for new actuators is 5.0 to 5.5 inch pounds of consistent running rotational torque in both the CW 8 CCW directions. If this recommended rotational torque is not obtained on the first assembly attempt, the clutch housing mount assembly will require removal and shims must be added or removed until the proper rotational torque is obtained. A special "socket" can be made to properly fit the flats on the input gear shaft to use on the ’/4 inch drive, 0 to 15 inch Ibs.,Torque Driver.
NOTE When looking at recoiler assembly with shaft end toward you, the spring tabs in the housing slot should curve to the right as shown
(Figure 32-14).
Inspect cable for sheathing damage. Replace cable if sheathing is cut or strippTed. Measure overall cable length prior to reassembly. Cable length should be 31 1/2" +1- 1/2" long. 5.
7d. When the correct rotational torque has been obtained, reinstall clutch housing mount assembly (5A)
assembly (5). Reinstall portion of actuator.
"T’
13. Reinstall aircraft
ALLOW BEARING OR SHIMS TO DROP OUT OF CLUTCH HOUSING MOUNT ASSEMBLY.
to recoiler transmission
cable
12´• Verify rigging per SECTION 32-3002. Caution Shwld be observed during installation for proper placement Of washers and bushings on the system.
desired, disassemble clutch housing mount assembly (5A) from recoiler assembly (5). DO NOT
if removed) assembly to
emergency
Ifd. Reconnect electrical connection. Check for proper electrical and mechanical operation.
7a. If
110117-3
Route
bracket, pulleys to ’7" handle position
7. NOTICE In some instances, the new clutch (no-back) spring chatters during electrical extension or retraction cycle. Proper shimming of the clutch spring housing 10, and bearing (11) with assembly, items 6,7,8,9 shims (12) is necessary to eliminate the chatter. Shimming procedures follow:
110117-1 110117-2
procedures below: hat section lug.
11. Reinstall actuator into aircraft per
NOTE Clutch assembly can now be verified for proper installation by rotating input gear (6) both CW CCW. Gears should turn with moderate friction to hand torque. Observe that output screw jack rotates in both directions.
this
6. Slide drum onto shaft and be certain that spring detent on drum engages both recoiler springs by slightly rocking drum end.
NOTE Flats on gear shaft (6) MUST line up with the Brass manual drive clutch for proper assembly. Pull manual drive cable slightly to position brass clutch to align with flats on gear shaft (6).
7. When full engagement is obtained, wrap cable around drum in a clockwise direction-leaving 2" to 5" of cable free of drum.
8. Align slot in pulley housing with cable and slide puiley housing over cable and drum assembly. 9. Holding housings together, pull properly aligned cable several times to ensure the absence of binding conditions. Measure cable length from side of housing.
two (4) 8. Install two new bolts (3) ADS145-10-43 ADS145-10-38 (availableonly through S120-52-001 kit). Apply Loctite Grade A to threads prior to installation. Torque bolts to 20 25 in. Ibs.
4-99
32-30-06
OLDWILLWAYNE
At full extend, the length of cable should be 29" minimum. In retracted position, cable length should be 5" to 8" long.
CAUTION DO NOT continue to pull T-Handle after GEAR DOWN light is ON. Actuator may bind on Down
damaged or worn, remove pin (11) from disengage arm (12) and slide disengage arm out so bronze clutch (13) can be pulled from its driveshaft. 12. Replace bronze clutch and reassemble disengage arm into recoiler assembly. 13. Attach clutch recoiler assembly to actuator gear housing with the four (4) screws removed in 32-30-05 (supplied in clutch spring kit).
Stops. 32-30-08
MANUAL EMERGENCY GEAR EXTENSION SYSTEM
The manual emergency gear extension system is used only. The controls are in the floorboard aft and between the front seats. To manually extend the gear:
2.
TROUBLE Retraction. Gear retracts to an intermediate position and stops short.
Incomplete
Retorque all jam
LANDING GEAR SYSTEM PROBABLE CAUSE
Bind in gear retraction system because gear is out of rig. Malfunction in gear electrical
circuit, inoperative actuating motor,
or
weak
battery.
Oversized/Stretched tire will not go into wheel well Gear will not retract at 61 to 70 KIAS.
nuts.
3. Reattach main and nose landing gear door links. Check to see that main and nose landing gear doors are still rigged per paragraph 32-10-03 and 32-20-03.
landing gear actuator C/B.
TROUBLE SHOOTING
FINAL CHECKS
1. Raise and lower landing gear through five complete cycles, pausing after each cycle to check required tolerances and dimensions, and annunciator light indications. Make certain that no bungee springs are compressed to solid height, and that nose gear tire clears top of wheel well a minimum of .25 in. when landing gear is retracted. Make adjustments per above procedures, as required, to correct any deficiencies.
to extend gear
32-31-00
DOWN
CAUTION DO NOT operate landing gear electrically with manual extension system engaged. Landing gear actuator C/B will pop out.
If
1. Pull
to
right thumb. 4. Pull RED lever back and upward (engaging manual extension system). 5. Pull â&#x20AC;&#x2122;7" handle up and return to original position and continue until green gear-down indicator light is illuminated and/or lines on visual gear position indicator on floor aft of console are aligned when viewed from directly above the indicator (this will normally take 12 to 20 pulls).
Bronze
32-30-07
switch
3. Push latch forward with
clutch (13) should be inspected for damage or wear at slot where gear assemble engages during manual extension of the landing gear. 11.
Move landing gear control
2.
position.
NOTE Cable length in retract position may be adjusted shorter or longer by holding clutch with the finger of one hand (to prevent shaft rotation), and then with the other hand, rotating pulley housing one (1) full turn CW (10 shorten) or CCW (to lengthen). Retention of clutch with finger will not allow pretensioning of springs. Slight spring tension should be noted starting at 8" to 10". 10.
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
REMEDY Refer to landing gear rigging procedure. Examine all movable parts for proper lubrication and freedom from binding. Check for actuator worm gear binding and lubricate as needed. Any malfunction can cause the landing gear circuit breaker to trip: therefore check electric circuit for loose connection, broken wires or defective relay switches. Recharge battery.
Replace tire
with smaller diameter tire.
properly.
Insufficient airspeed. Pressure switch inoperative. Circuit breaker tripped.
Check pitot tube and line for obstructions. Examine pressure switch for proper adjustment and operation. Reset circuit breaker. Does gear retract using override check system operation.
Gear will not retract at 61 to 70
KIAS (conâ&#x20AC;&#x2122;t.)
32-30-07 16
Actuator ball nut binding on mechanical DOWN STOPS.
4-99
Gear may have been extended manually 8 ball nut is jammed tight against STOPS on motor; use wrench on ball nut flat to move off STOPS.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
REMEDY
PROBABLE CAUSE
TROUBLE
Manual engage handle in
Gear will not retract and gear actuator C/B trips, Aircraft does not track or steer
Disengage
manual system.
engaged position. See SECTION 32-50-02.
Nose wheel location
improper.
Lamp burned out in -green -light circuit.
annunciator
properly. Gear will extend; green indicator-light will not illuminate.
Down-limit switch
Actuating
motor extends gear to
Same
Push press-to-test on annunciator and replace bumed out lamp if needed. Check circuit and/or down-limit switch.
inoperative.
Same remedies as listed with "lncomplete Retraction" above.
listed with Retraction".
causes as
an
"lncomplete
intermediate position. Gear will extend manually, but green indicator light will not
Gear switch is not in DOWN
Place gear switch in DOWN
position.
position.
illuminate.
Lamp bumed out indicator light.
Replace
in green
Actuator internal clutch spring broken (Avionics Products/Eaten Actuator only). Manual engage arm improperly
Manual system will not lower gear.
bumed out
lamp.
Replace spring. Rig
manual engage
arm.
rigged. Sheared female
spline
in drive
Replace drive stripped.
connector if female
Adjust control
cable tension of drive
spline
is
connector.
Drive connector is out of
rig.
connector.
Landing retract
Any of the above
Gear Actuator will not extend gear.
brushes
nor
or
Bearing cups MAIN WHEELS
3240-01
The main wheels have standard brand, 6:00 ill, six-ply rated tires with standard tubes. To remove main wheel/tire assemblies: i. Remove MID gear door.
x
6, Type
3. Remove 2 bolts from single (4 bolts on dual puck caliper).
puck
screws
brake
4. Remove wheel by removing cotter spacer from axle. (SeeFigure 32-15.)
6´â&#x20AC;˘
and
of
nut and
To install cup, heat wheel half again cup with dry ice. Position cup and tap proper seating.
5. Slide wheel off axle.
i. Remove snap ring, (10) grease seal felt seals (9) (See Figure 32-16).
2. Remove 3.
rings, (8)
and
bearings (7).
WARNING Do not loosen wheel half retaining nuts before tire is completely deflated. Failure to observe this warning may result in bodily injury, 4. Remove nuts,
4) and
remove
as
above; cool
lightly
to insure
ii. Position tire 8 tube
on
wheel half with valve stem
hole; then position other wheel half in tire to match
mounting
holes.
CAUTION Use correct axle spacer to position brake disc .12 inches from MLG assy.
washers, and wheel half retaining (2), separate halves, (3 8
brake disc tire and tube.
remove
evidence
9. Replace bearing cones that show signs of wear or bearing fretting. in. Repack wheel bearings and lubricate seals with grease. Install bearings, grease seal rings, and felt seals in wheel halves. Secure with snap rings.
Completely deflate tire.
bolts, (5);
or
8. Polish small burrs or nicks out of wheel halves with No. 400 grit sandpaper, clean thoroughly, and refinish protective coating as required.
MAIN WHEEL DISASSEMBLY/ ASSEMBLY
32-40-02
I"spect all parts for cracks, corrosion,
wear.
7. Inspect bearing cups and replace if cups are damaged or wom. If necessary to remove bearing cups, heat wheel in boiling water for at least 30 minutes. Then remove cup by tapping evenly.
caliper;
key,
are
5. Clean all wheel parts thoroughly in cleaninn fluid (Federal Specification PS-661). Exercise special~ care in cleaning bearing cones and felt rings to insure thorough cleaning.
(Ref. Figure 32-15)
2. Detach dust shield. Remove three washers.
or
NOTE shrink fitted; do not remove them unless necessary for replacement.
WHEELS AND BRAKES
32-40-00
Applicable remedy listed above replace motor or brushes.
motor
worn.
4-99
32-40-00 17
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 12. Install brake disc
NOTE
(2),Fig.32-16, and wheel half When
retaining bolts, washers and nuts. 13. Tighten pounds.
and torque to 150 inch
evenly
nuts
will turn with
16. Install dust shield and IB/MID gear door.
or
improper torque sequence may
cause
bolt
or
caliper securely and safety.
18. Remove aircraft from
wheel failure.
15. Install wheel assembly, bearing spacer, washer, and axle nut. Tighten axle nut until bearing binds slightly, back nut off to nearest castellation, and install
jacks.
NOSE WHEEL DISASSEM BLY/ASSEMBLY
3290-03
14. Inflate tire to 42 PSI.
cotter
properly installed, the wheel a slight resistance.
17. Reinstall brake
CAUTION
Uneven
MOONEY AIRCRAFT CORPORATION
M20M
The standard brand, tube-type, 5:00 wheel tire is six-ply rated.
x
5, Type III,
nose
1. Nose wheel removal.
pin.
A. Remove cotter
key, nut,
and washer from axle.
(Figure 32-15). SCREW
(TYP.
3
8. Remove
PLCS.)
nose
2. Installation is in
NUT SPACER
wheel.
reverse
sequence of removal.
3. Nose wheel A.
disassembly. Completely deflate tire by removing
valve
B. Remove nuts, washers, and wheel half bolts (15), Fig. 32-16.
core.
retaining
C. Separate wheel halves, (13 and 14) and remove tire and tube. Refer to SECTION 32-40-02 steps 5 thru 10 for wheel inspection. COTTER
D. Reassemble nose wheel in reverse sequence of removal. Tighten wheel half retaining bolt nuts evenly and torque to 90 inch-pounds. Inflate tire to 49 PSI.
PIN
BRAKE--’~\h \a
>y/
DISC
MAIN SPACER
TI RE
(AS REQ’D. .12
IN.
TO POS~TION BRAKE D\SC FROM MLG LEG ASSY.) MAIN GEAR IEG ASSY.
MAII\I
WHEEL
14
NOSE WHEEL ASSY. 13
zP,
NOSE
TIRE
NOSE
GEAR
LEG
ASSY.
COTTER
PINWASHERSI~BNUT
9
j/ 4
MAIN
I~OSE
WHEEL ASSY. 3
WHEEL
LANDING GEAR WHEEL REMOVAL
FIGURE 32-15 WHEEL ASSEMBLIES
32-40-03 18
2
4-99
FIGURE 32-16
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
F. Drill out rivets (9) attaching linings (7) to back lining plate (2) and the pressure plate (5). Remove piston assembly (10) and "0" ring (11). It is permissible
CAUTION When ANY tire andlor wheel assembly is removed or replaced and re-installed, conduct at least 5 complete retrcttonnextenssorn cycles to verify tires enter and exit wheelwells without interference. [Ref. AC 43.13( A i, Chap.8, pam. 332, a,
Mounting Flange
Cleveland
(9)1
75´•16
Torque
Plate assy.
BRAKE SYSTEM
32-40-04
SERVICE AND MAINTENANCE MANUAL
M20M
.111
NOTE SIN 27-0108 and later A/C have a dual puck wheel brake cylinder installed. 1. BRAKES
V~heel 8
Assembly
(TYPICAL) Lining inspection
and/or
A. Place aircraft
on
replacement
or
Plate
Tire
REMOVAL AND INSTALLATION
cylinder repair.
jacks.
B. Remove middle gear doors. Remove safety wire and two AN4H17A bolts (1) attaching back lining plate
assembly (2)
to
I
brakecylinder assembly (Figure
32-1 7).
Visually inspect linings for wear and brake disc for warpage. Brake linings should be replaced when they are wom to a minimum thickness of 1/8 inch. If lining replacement is necessary proceed with steps D C.
thru O. Otherwise reassemble in
reverse
sequence of
disassembly. CAUTION Brake disc should be replaced if width is .205 inch or less. D. Disconnect and cap hydraulic line (4) at brake Remove nuts from anchor bolts, E. Remove pressure
ke
Cylinder
(SINGLE PUCK BRAKE CYLINDER ONLV) (214401 THRU 27-0106) TORQUE PLATE ASSY.CORRECT RELATIONSHIP FIGURE 32-18 to use compressed air applied to the brake line to remove the piston (10) from the brake cylinder.
cylinder assembly.
plate assembly (Figure 32-17)
G.
Clean
parts
Specification PS-661 oil-free compressed air.
8
in or
frtting
cleaning solvent (Federal equivalent) and dry with
H.
10
6
Replace linings with Cleveland 66-30 linings Cleveland #561-2 rivets. Rivet shanks must be rolled with special tool for proper installation.
using
4
8
I. Inspect brake cylinder bore for scoring. A scored cylinder may cause the "0" ring to leak or cause rapid wear of the "0" ring. A scored brake cylinder should be replaced. Replace AN6230-2 "O" ring (11) with a new one.
-p
.J.gnir
Do not
11 VALVE-~
the old ’0"
L. Service and inspect main wheels as described in SECTION 32-40-02. Inspect single puck torque plate assembly; make sure the .125 thickness is toward brake cylinder assembly. If thicker .250 protrusion is outboard, remove torque plate from axle mounting flange and install as shown (Figure 32-18).
fS~107 THRU 27-TEA)
COVER
DUAL PUCK BRAKE ASSEMBLY
reuse
K. Lubricate cylinder and piston with MIL-H-5606 red hydraulic fluid and assemble components with care to prevent damage to the’0" nng.
10 LEED
Assembly
_pP~h
M. Reassembly brake cylinder assembly and back lining plate assembly onto the airplane in the reverse sequence of disassembly.
FIGURE 32-17
(5) sliding it off the anchor bolts (6). Note the condition of the anchorbolts. if they are nicked or gouged
N. Bleed hydraulic SECTION 12-20-05.
should be sanded smooth to prevent binding with When the the pressure plate (5) or torque plate (8) anchor bolts are replaced they should be pressed out. New ones can be installed by tapping them in place with a soft hammer.
they
system
as
described
in
O. Remove aircraft from jacks.
4-99
32-40-04
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 2.BRAKES
M20M
BREAKINPROCEDURES.
by spring (5) when roll pin is removed), spring (5) piston (7). (5) Remove O-ring packing (6) from piston. (6) Remove stat-o-seal (8) from piston rod. (7) Clean all parts with cleaning solvent (Federal Specification No. PS-661). (8) Inspect cylinder for cracks, scoring, or and
NOTE Brake pad conditioning is required to properly cure the resins binding the lining composition together. Excessive heat created prior to conditioning will carburize the lining matetial and prevent the attainment of maximum braking coefficient.
Proper conditioning
may be
accomplished as follows: A. Perform a minimum of six (6) light pedal effort braking applications and two (2) hard stops from 21 to 35 KIAS. Allow the brake discs to partially cool between
grooves in bore. and
stops.
The procedure will generate sufficient heat to cure the resins in the lining, but will not cause the material to become carburized due to excessive heat.
REMOVAL AND DISASSEMBLY (27-0001 THRU 27-0106). A. Remove left hand, lower firewall and exhaust cavity.
fuselage
skin aft of
hydraulic cylinder from pedal linkage. C. Disconnect and cap hydraulic lines. D. Disconnect hydraulic cylinder from bracket and remove cylinder.
(12)
disassemble
13
for
brake
cylinder
in
reverse
(refer
system
sequence of
to
SECTION
Cylinders
installed.
REMOVAL AND DISASSEMBLY (27-0107 THRU 27-TEA). A. Remove left hand, lower firewall and exhaust cavity. B.
Disconnect
hydraulic
fuselage
cylinder
skin aft of
from
pedal
linkage. C. Disconnect and cap
â&#x20AC;&#x2122;9
(27-0001 THRU 27-0106)
27-TEA)
hydraulic
lines.
5
\"6 7
4
t~
MASTER BRAKE CYLINDERS
20
(2)
SM32-19
10
7
15(27-01
32-40-04
Bleed
Master
11
14
springs
S/N 27-0107 and later A/C have larger capacity
87
15
return
NOTE
cylinder:
master
Disassemble piston rod assembly by roll pin (4), (spring guide (3) will be pushed
L
piston
max.). (13) Replace all faulty parts and all o-rings. (14) Reassemble in reverse sequence of disassembly. Immerse all parts in hydraulic brake fluid prior to reassembly.
G.
(3) Remove spacer (11) and o-ring packings, (10 12) from piston and assembly. (4)
Inspect
12-20-05).
(1) Unscrew and remove rod end clevis (15) and nut (14) from piston rod (9). (2) Remove snap ring (13) and lift out complete piston rod assembly, (items 3 thru 12).
removing
nicks
permanent set and proper length (3.670 in. min., 4.05
(Parker-Hannifin) (See Figure 32-19).
and
nicks
and scratches.
F. Reinstall master removal.
B. Disconnect
To
(9) Inspect piston (7) for damage, check for scratches (10) Inspect spacer (11) for damage. (11) Inspect push rod for scoring, grooves,
in.
3. MASTER CYLINDER
E.
MOONEY AIRCRAFT CORPORATION
out
(PARKER-HANNIFIN) 4-99
SMX32-19A
FIGURE 32-19
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION D. Disconnect remove
hydraulic cylinder
from bracket and
(4) Remove snap ring (5) from end of camshaft assembly (6). (5) Carefully remove camshaft assembly (6) from housing. (6) Inspect all components for damage, nicks,
cylinder.
E. To disassemble master cylinder: (Parker-Hannifin) (See Figure 32-19, S/N 27-0108 thru
27-TEA).
(1) Unscrew (16)
and washers
grooves, etc.
and remove rod end clevis (17), nut 8 15) from piston rod (13).
(14
(7) Clean all parts with cleaning solvent (Federal Specification No. PS-661). (8) Replace all o-rings (9). (9) Reassemble brake valve in reverse sequence of disassembly.
(2) Remove snap ring (11) from cylinder housing assembly; lift out complete piston rod assembly, (items 2 thru 13). Spring (12) can be removed at this time. (3) Remove assembly.
from end of
ring (2)
snap
SERVICE AND MAINTENANCE MANUAL
M20M
piston
(4) Remove bushing (3) and spring (4) from
rod
(10) Connect valve assembly
end
of
piston rod. (5) Remove piston assembly (5) and o-ring (7) from piston assembly and o-ring (6) from piston rod
with
hydraulic
(11) Bleed system; service hydraulic reservoir hydraulic fluid as described in SECTION 12-20-05.
5. Shuttle Valve
shaft.
(6) Remove end cap (8) and o-rings (9 [ID] and [ODI) from end cap assembly.
to the
lines.
A.
7
replace
Maintenance
No maintenance authorized. shuttle valve assembly.
Remove
and
(7) Clean all parts with cleaning solvent (Federal
Specification No. PS-661). (8) Inspect cylinder
for
cracks,
scoring,
or
grooves in bore.
(9) Inspect piston (5) for damage; check
for nicks
and scratches
(10) Inspect
end cap
(8)
(11) Inspect push rod
for
for
damage.
scoring,
grooves, nicks
and scratches.
(12) Inspect spring (4)
for free
height
.500 in.
+/-.030.
(13) Replace
all
faulty parts and
all
o-rings.
Reassemble in reverse sequence of disassembly. immerse all parts in hydraulic brake fluid
(14)
prior to reassembly.
(15) Check piston rod and return spring (12) for proper compression during stroke (9 Ibs., (initial) to 32 Ibs. 3/4 stroke)). F. Reinstall master removal.
G.
Bleed
brake
cylinder system
in
reverse
(refer
to
97
SECTION
12-20-05). 4.
5
sequence of
o
1
PARKING
BRAKE
VALVE
Removal
r6
O~I
~n9 ~-4
and
disassembly. A. Remove forward B. Disconnect brake valve arm.
fiberglass belly skin.
parking
C. Disconnect and cap D. Remove
parking
E. Disassemble
brake control at
parking
3 2
hydraulic lines.
brake valve.
parking
brake valve:
(Refer Figure
32-20). (1) Remove (7), springs (8) will
both
fittings (1)
come
from valve
out with the
housing
fittings.
(2) Remove poppet valves (2) and pins (3), from housing by bumping on table top. (3) Remove both fittings (4) from end of housing.
PARKING BRAKE VALVE
4-99
FIGURE 32-20
32-40-04 21
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
TROUBLE SHOOTING SYSTEM
3241-00 TROUBLE
Solid
pedal and
Spongy
no
brakes.
brake.
PROBABLE CAUSE
REMEDY
Brake lining worn allowable limit. Air in system.
Replace lining.
beyond
Bleed brake system.
Leak in brake system.
Pressure will not hold.
BRAKE
Visually check
entire
system for
evidence of leaks.
Parking
Air in system
brake will not hold.
or
leak in system
See remedies above.
(downstream of parking brake valve). Defective Brake
grabs.
brake valve.
neutral position,
Repair
bent disc.
Warped
or
Foreign
matter
locking
disc.
replace the valve.
disc.
Clean disc and
other
lining.
Check that shaft travels in and not binding in linkage.
straight
line
NOTE
-STEERING
Check 32-50-01
or
Replace
Master cylinder shaft or linkage misaligned.
Brake pedal will not return to
32-50-00
parking
NOSE GEAR STEERING SYSTEM
The nose gear steering system consists of a steering horn on the gear leg linked to the rudder pedals by push-pull tubes and bellcranks. Gear retraction automatically disengages the steering mechanism from the nose wheel. (SECt~ON 27-20-00 outlines the nose gear steering rigging.) A centering cam aligns the nose wheel for entry into the wheel well.
damage.
Twin limiter pads and adjustable stops (7), Fig. 32-21, are installed on the nose gear leg assembly (A) to Prevent towing/turning damage to the leg assembly. i. Every 100 hours remove cotter pin (1) (Figure 32-21) and retorque nut (2) to 450-500 inch Ibs. Check holes in leg assembly where pivot bolt (3) is located for any wear. If holes are worn, replace the leg assembly.
CAUTION (9) and (10) (Figure 32-21) must be installed as shown, from rear to front.
Bolt, washer,
TUBULAR STRUCTURE
j
gear leg assembly for towing Replace if any dent exceeds 1/32 inch. nose
8
2.
nut
Rod end bearing (4) (Figure 32-21) should be at least every 100 hours for any damage or
inspected bending.
3. Check the steering horn assembly (5) collars and spacers for looseness. Replace any bushings or spacers that are worn.
5
7
4. Adjust turn limiter stop bolts (7) to contact cross member (8) of truss assembly (.020 gap permissible) when rudder is at its extreme left and right travel
A
position. NOSE GEAR STEERING
32-50-02
GNIKCARTDNA
1. Level aircraft
2. Center
nose
as
described in
Chapter 8.
wheel.
3. Place plumb line over and forward of nose gear trunnion (see Figure 32-22) part number 540001-503. 4. Measure forward from aft edge of plumb line to axle center line. Modification relocating nose wheel should be accomplished if axle position, forward of plumb line, exceeds .06.
NOSE GEAR LEG ASSI.
5.
Add
SE
M20-202-3
spacer
under
collar
reposition the axle if required. NOSE WHEEL STEERING
32-41-00 22
NOTE Some collars have holes drilled off center and may be turned over to change axle position.
FIGURE 32-21
4-99
to
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
CAUTION When running gear up or down electrically DO NOT use circuit breaker as a switch. Partial retraction or extension may be accomplished electrically as follows: COLLAR
II
I GEAR TRUNNION
position.
2. Move gear switch to GEAR UP as
senoSPACER
PLUMB
1. Place Master Switch in OFF
or
GEAR DOWN
desired.
3. Momentarily actuate Master Switch until gear is in desired position.
LINE
LANDING GEAR WARNING SYSTEM
3260-02
landing gear warning system consists of: "GEAR Landino position lights: gear DOWN"-GREE~N light on annunciator and WHITE RED light indicator light on Roor "GEAR UNSAFE"
The 1.
SEE
"1*
on
CENTER LINE
UP-nolights.) 2. A warning
NOSE WHEEL LOCATION
6. Run gear through retraction/extension cycle. Check nose gear door and wheel well tire clearances. Re-rig if required.
POSITION AND WARNING
32-60-01
ELECTRIC GEAR SAFEN DEVICES
32-60-03
CAUTION
airspeed safety switch is designed to operate within a specified range during increasing airspeed only. Due to hysteresis of the switch/diaphragm assembly the switch MAY NOT deactivate the landing gear circuitry until approximately 49.5 KTS. This could allow the The
the gear in its retracted knob to its lower detent lowers the gear. The down limit switch will stop the gear actuating motor when the proper force is exerted to hold the gears in the down-and-locked position, Refer to SECtlON 32-30-02,7. for proper limit switch rigging. The gear down-and-locked position is indicated
landing gear to retract if the gear switch is inadvertently placed in the UP position during the landing roll. CAUTION
by:
During static system checks, pressure compensation on the pitot side of the switch diaphram must be considered or switch diaphram may rupture.
1. Illumination of the green gear down annunciator
The GEAR DOWN annunciator light is dimmed ever the Navigation Light Switch is ON.
warning
NOTE Refer to proper electrical schematic when replacing with switches from another manufacturer.
horn will not sound with the throttle
retarded within 1/4 inch of idle
position,
3. The indicator marks will be indicator.
aligned
on
AIRSPEED SAFETY SWITCH ADJUSTMENT
settings.
paragraph 32-60-03. up-limit switch will stop position. Moving the control
2. The
down; GEAR
The V.E.P. manufactured switches are field adjustable. They should close at 2.8 +1-.4 inches water. Adjust slotted screw head on center of switch to obtain correct
The
when
or
The airspeed safety switch, located inside the cabin, is mounted on the left side of the cockpit, forward of the pilots left knee. The airspeed safety switch is incorporated into the electrical system to prevent landing gear retraction while on th2~ ground and at airspeeds below 60 +/-5 )CTS. Additionally the RED gear unsafe light comes on and the warning horn is sounded when the gear control handle is placed in the gear UP position below 60 +/-5 KTS.
The gear switch operates the landing gear actuator relay. Pulling the wheel-shaped knob out and moving it to the upper detent raises the gear. However, an airspeed safety switch is incorporated into the electrical system to prevent landing gear retraction while on the ground. To allow gear retraction with the aircraft on jacks; attach a IrZ-inch length of 3/8 inch pliable rubber hose (surgical tubing) over the pitot head, and pinch the open end with a large cotter pin; roll the tubing with the cotter pin until the compressed air within the twisted tube actuates the airspeed pressure switch. Maintain pressure on the switch until retraction is complete. To adjust the airspeed switch refer to
light.
Gear is in transit, UP
horn in cabin is actuated by the throttle control when t~he gear control switch handle is UP and the throttle is less than 1/4 inch from idle position. Check warning horn for volume in Right periodically. Hom will sound if gear is not DOWN and LOCKED even if switch is in DOWN position or if airspeed is below 65 KIAS and gear switch is in UP position.
FIGURE 32-22
32-60-00
annunciator
the visual
gear-position
4-99
32-60-00 23
OLDWILLWAYNE
32-80-00
-MISCELLANEOUS
32-81-00
LANDING GEAR SHOCK DISC INSPECTION
1. Aircraft with full fuel load and
weight
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
on
iandingl
D
gear. A. Main gear shock discs.
(1) Remove dust shield. Check gap retaining collar (A) (Figure 32-23) and top plate (B). Allowable gap is 0.00 to 0.85 inches. (2) Replace discs when gap exceeds tolerance. Use a shock disc replacement tool (C), P/N GSE 030011, told P/N ME121), to remove and install main gear shock discs. Use removable pad from tool as a guide on top of shock link to align discs as theyl are being compressed. (3) Careful application of the shock disc( replacment tool is recommended during replacement main gear shock disc to keep from damaging
f~e 7
T
,F
fittings. PAD
NOTE Shock disc retention collar should be installed with the chamfer facing down and forward.
(4) Main landing gear leg assembly axle is to located to provide a minumum of.23 inches between tire and any component inside wheel well. Alternate collars, P/N 510049-001, -003, -005, -007, -009 or -011 can be substituted for basic dash no. to obtain this clearance. If any interference occurs between tire and other components during retract cycle, next higher dash number collar moves axle approximately .50 inches aft.
NOSE GEAR SHOCK DISC REPLACEMENT FIGURE 32-24
(2) Replace shock discs if gap is found. Use replacement tool (F), P/N GSE 030010, told P/N ME120), to remove and install nose gear shock discs. Use removable pad from tool as a guide on top of shock link to align discs as they are being compressed. shock disc
B. Nose Gear Shock
Discs.(See Figure 32-24) (1) Check for gap between retaining collar (D), (Figure 32-24) and top retaining plate (E). Top
NOTE Dimension O, (Figure 32´â&#x20AC;˘24), is critical to properly locate nose wheel position. Leg assemblies can vary, due to manufacturers tolerances. Dimension O in a no load fully extended position should be approximately 3.0 inches. Add spacer under collar( D) per SE M20-202, as needed. See (Figure 32-22), paragraph 30-50-02, for
A
B~
proper
AD
2. Raise aircraft
steering/tracking rigging. on
jacks
shocks
fully extended.
A. Inspect nose and main gear shocks for evidence of gap between retaining collar and retaining plate. The disc preload must be great enough to maintain complete wheel extension during retraction.
P
B.
Replace
C.
Inspect retaining collar
shock discs that have lost resilience. and bolt for deformation,
wear, and cracks.
D.
CAUTION Both collar and bolt must be replaced when or the other is defective.
MAIN GEAR SHOCK DISC REPLACEMENT FIGURE 32-23
32-80-00 24
Replace defective bolt and collar.
4-99
one
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
M20M
2. Main landing gear shock bisquits condition for compressed or extruded rubber. 3. Tail skid damage or damage to bulkhead that
NOTE For Nose Gear
Steering/Tracking see 32-50-02, (Figure 32-22).
SERVICE AND MAINTENANCE MANUAL
SECTION
attaches tail skid.
Propeller strikelmarks or other visual damage. 5. Engine or engine mount damage. 6. Nose landing gear leg assembly damage near steering lugs. 7. Pilot/Go-Pilotâ&#x20AC;&#x2122;s seat adjustment supports/tubes 4.
32-82-00
RECOMMENDED HARD
LANDING/OVERWEIGHT LANDING INSPECTION The following are areas recommended to be inspected when a "hard landing" or Overweight landing has occured. Since a "hard landing" is a relative term and an over weight landing may have occured, it is up to the owner/operator to advise maintenance personnel when the inspections are to be accomplished. However, since this may be overlooked during preliminary discussions, the mechanic/technician should inspect the aircraft for the following: 1. Mud Shield
main
landing
missing
or
damaged
on
either
or
bent from excessive G-loads. If any evidence of damage or abnormal visual observations are found, it is recommended that a thorough inspection of all the above areas be done and repairs be made as necessary. Contact FAA personnel for incident report requirements.
both
gear.
4-99
32-82-00 25
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
32-82-00 26
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
LIGHTS
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 33 LIGHTS
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT
33-00-00 33-20-00
33-21-00 33-21-01
33-21-02 33-21-00 33-21-01
33-21-02 33-22-00 33-22-01
33-23-00 33-23-01 33-40-00 33-40-01 33-41-00 33-41-01 33-41-02
33-41-03 33-42-00 33-42-01
33-43-00 33-43-01 33-43-02
SUBJECT
General
PAGE
Description and Operation Lights Maintenance Practices Cabin Lights Overhead Lights (27-0001 thru 27-0180, 27-0182, 27-0183) Light Bulb Replacement Cabin Light Switch Replacement Cabin Lights- Overhead Lights (27-0181,27-0184 ON) Light Bulb Replacement Cabin Light Switch Replacement Instrument/flight Panel and Glareshield Lights. Light Bulb Replacement Gear Down Indicator Light (Floorboard) Light Bulb Replacement Exterior Lights Maintenance Practices Trouble shooting Exterior Lights High Intensity, Strobe Lights-Maintenance Power Supply Unit Removal or Replacement Power Supply Unit Installation Strobe Light Replacement. Navigation/Position Lights Position Light Replacement Service LandingTTaxi Lights LandingTTaxi Light Adjustment Procedures LandingTTaxi Light Bulb Replacement
Interior
5 5 5 5 5 6
6 6 7 7 7 7 7 7
8 8
9
9 10 10 10 10 11
33-CONTENTS 4-99
3/48LANK
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 33
LIGHTS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT.
PAGE
DATE
1/28LANK 3/48LANK
4-99
33-00-00
5.
4-99
33-21-00
6.
4-99
33-22-00
7.
4-99
33-41-00
8.
4-99
33-41-02
9.
4-99
33-42-00
10
4-99
3343-02
11
4-99
33-43-02
12
4-99
33-8ffectivity 33-Contents.
4-99
33-EFFECTIVIN
1/28LANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 33-00-00
MOONEY AIRCRAFT CORPORATION
M20M
-GENERAL-DESCRIPTION AND OPERATION
of the
over head airvents on ovemead panel. The passenger compartment lights are located above rear seats in overhead panel and are activated by a similar three position switch located adjacent and aft of f0â&#x20AC;&#x2122;waâ&#x20AC;&#x2122;d cabin light switch.
High intensity strobe lights are standard equipment on M20M aircraft. The lights are located adjacent to the wing tip navigation Tights and incorporated in the taillight assembly. Separate power supplies are utilized for each strobe light and are located in each wing outboard section, mounted on inspection cover, and inside the tailcone adjacent to the left rear inspection cover. The system is actuated by a 10 amp circuit breaker/switch located on the instrument panel in front of the pilot. Navigation lights are located on each wing tip and, the aft facing navigation light (clear), located on each wing tip trailing edge. The lights are activated by a 7.5 amp circuit breaker/switch located on the instrument panel in front of the pilot. Landing/Taxi lights are located in leading edge of both wings. Two 110,000 candle power sealed beam bulbs are located in each wing. The lights are activated by two 25 amp split switches located on the upper left instrument panel in front of the pilot. The switches are taxi or either one, as used to illuminate both landing
NOTE These cabin
lights are connected directly to the battery through the rocker switches and will
illuminate with Master Switch OFF unless the optional door frame swithces are installed.
S/N 27-0053 thru 27-0107 aircraft MAY incorporate
optional switches on cabin and baggage door frames that will tum applicable interior lights ON when either door is opened. Forward cabin interior lights are ccnnected the cabin door switch and aft to cabin/baggage interior lights are connected to the baggage door switch. Rocker switches, located overhead, between pilot and cc-pilot, for cabin interior lights will turn selected set of lights ON, as desired. The rocker switch light circuits are routed through a timer and the MAStER switch and will go OFF when MASTER switch is tumed OFF, with the rocker switches left ON (doors closed). Lights will go OFF in approximately 90-120 seconds after door(s) are closed~ inrhen MASTER is OFF and rocker switch(es) are left ON. The lights will go OFF when door(s) are closed,(timer delay) if MASTER is ON or OFF and light rocker switch(es) are OFF.
needed. Two sets of interior lights are located on overhead panel. The forward cabin overhead lights are located between pilot and cc-pilot seats and are actuated by a three position switch, (dim, off, bright) located forward
BULB PART NUMBER
APPLICATIONS Glareshield Post Lights
GE GE GE GE GE
Lights
Map Light Cabin Interior Lights Trim Flap Indicator Gear Down Light (Floorboard GE 327 Tail Position Light (WHELEN) Wing Tip Position Light
W1290 W1290 GE 4596 01-0770303-00 ONhelen)
3340-00
INTERIOR LIGHTS-MAINTENANCE PRACTICES
33-21-00
-CABIN LIGHTS-OVERHEAD LIGHTS
33-21-02
2. Switches (5) are a press and snap in fit and may require bending of spring tabs to release for removal.
LIGHT BULB REPLACEMENT
3. Disconnect wire connections and switch. Check for proper operation.
light cover panel (2) (Figure 33-1A) from the headliner assembly (1) by removing four screws (3) from either panel. 1. Remove
rear
the 2.
Remove and
proper
NOTE bulbs
light
are
replaced
CABIN LIGHT SWITCH REPLACEMENT
1. Drop forward end of headliner assembly (1) by removing screws holding headliner in place (Figure 33-1A).
(27-0001 THRU 27-0180, 27-0182, 27-0183)
The front and
327 327 1818 327
Indicator)
Landing/Taxi Light Recognition Light (molded assy)
33-21-01
327
replace
with
new
4. Position headliner to proper location and secure.
in
same manner.
replace
the bulbs and check for
operation. 4-99
33-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
-CABIN LIGHTS-OVERHEAD LIGHTS
33-21-00
/FW~1MTEYIT*
ON)
(27-0181,27-0184
LIGHT BULB REPLACEMENT
33-21-01
Carefully slide smooth, flat sharp blade under lip of light assembly flange and pop light assembly out df mounting hole. 1.
r
Q
CABIN
2. Disconnect blade terminals from CABIN
i
DOOR
FWD LIGHT
4. Pull bulb from bulb holder and bulb. Reinstall bulb holder.
light assembly proper operation.
6. Check for
The front and
FWD
rear
NOTE bulbs
light
are
AFT
PILOTS
LIGHT
O
mounting hole.
replaced
1.
Remove
27-0184 8
ON)
cover
from
screws
arm
rest
holding
assembly by
cover
to arm rest
2. Switches are a snap fit and may be removed
pressiing
SMLM33-1
snap tabs and
pushing
FIGURE 33-1A -INTERIOR LIGHTS
~D
Reassemble switch assembly into cover by in from top side. Re-install cover into arm rest, secure with 2 each screws. 4.
27-0183)
27-0001 thru 27-0180, 27-0182
by through cover. replacae with new
switch
3. Disconnect wire terminals and switch. Check for porper operation.
snapping
‘i\
BAOOAOE
2PLCS)
UKIKNO
~WQT
JHOIWI~
B~I o
HUDUNER
(Hm
LOOKING
ASSY UP)
~HUOnT
F~p (HEI LODONO
FRAME ImK~No
PANEL OURGIKG)
7-0181,27-0
33-21-00
in
REAR SEAT PASSENGER’S SWITCHES.
removing 2 each (Figure 33-18).
j
(we~v
new
CABIN LIGHT SWITCH REPLACEMENT
(27-0181,
CABIN
(HCW
with
3
33-21-02
(S/N
replace
into
5. Re-assemble
r
light assembly.
3. Hold light assembly body and rotate blub holder counter-clock-wise to remove.
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CO-PILOT’s SWITCH
Go-pilot’s cabin light switch is located cabin door hinge above cc-pilot’s right knee. 1.
in front of
2. Remove 1 each screw above switch. Remove door frame cap. Pull panel away from velcro fastners to access switch. 3. Press snap tab 8
push
switch from
panel to
B. Post light bulbs are replaced by pulling hood out from post light base and then pulling bulb
St’aight
from this hooded C. Insert
D. Check for proper
27-0184 3
A. Remove outer
C. Screw outer
baggage top of hat rack opening. (Figure 33-1A)
door at front,
3. Press snap tabs and PUSH switch
light
terminals, replace reverse
housing
new
bulb.
back onto base.
operation.
A. Place wrench on fiat of metal housing on bulb assembly from receptacle. Unscrew and remove bulb.
through panel.
B.
Replace bulb;
screw on
bulb retainer and
tighten.
switch. 33-23-00
order.
GEAR DOWN INDICATOR LIGHT
(FLOORBOARD)
INSTRUMENT/FLIGHT PANEL AND
33-23-01
LIGHT BULB REPLACEMENT
1. Remove lower
LIGHT BULB REPLACEMENT
belly panel
to
gain
access
to
light
assembly.
1. INSTRUMENT PANEL LIGHTS.
2. Remove and
A. Internally liohted instruments considered in this in~ormation.
33-40-00 33-40-01
from
3. MAP LIGHT
GLARESHIELD LIGHTS 33-22-01
hood orientation.
housing by unscrewing
D. Check for proper
2. Remove 1 screw inboard of switch. Pull door frame down slightly from velcro fastners to access baggage compartment light switch.
33-22-00
operation and
B. Remove bulb and insert
ON)
1. Switch is located at rear of
5. Re-assemble in
hood back
assembly base.
BAGGAGE COMPARTMENT SWITCH
4. Disconnect
push
2. GLARESHIELD LIGHTS.
remove.
completed.
(27-0131,
bulb into hood and
post light base.
O"to
4. Re-assemble in reverse order when maintenance
action is
portion.
new
are
not
replace bulb. operation. Reinstall belly panel.
3. Check for proper
being
4.
UCTERIOR LIGHTS-MAINTENANCE PRACTICES TROUBLE SHOOTING UCTERIOR LIGHTS
TROUBLE
REMEDY
PROBABLE CAUSE
STROBE LIGHTS
Lights inoperative.
Circuit breaker/switch
tripped,
Check for short circuit Reset circuit breaker.
Loose connection.
Check and tighten electrical connections.
Battery defective.
Replace battery or
Circuit breaker switch defective.
Check
Faulty power supply. light.
Disconnect
Replace
Power
Replace.
Fixture not
LANDING
grounded.
wires to
identify faulty
bulb.
Check for good bonding between fixture and structure. Tighten mounting screws.
Loose connection.
Check all connections in circuit.
Defective fixture
Replace fixture.
LIGHTS, NAVIGATION LIGHTS
Lamp fails to light.
synch supply.
Bulb bumed out.
supply inoperative.
extemal power.
continuity through switch; replace if necessary.
power
One bulb does not
use
AND TAILLIGHT
Circuit breaker/switch
tripped,
Lamp burned
out. 4-99
Check for short circuit Reset circuit breaker.
Replace lamp. 33-22-00
OLDWILLWAYNE MOON EY AIRCRAFT CORPORATION TROUBLE
M20M
SERVICE AND MAINTENANCE MANUAL
PROBABLE CAUSE Loose connection defective wire.
REMEDY
Tighten connections and check wire circuit continuity. Replace or repair wire
or
if necessary. Circuit breaker/switch defective.
Check
continuity through Replace if necessary.
switch.
HIGH INTENSITY STROBE LIGHTS-MAINTENANCE
33-41-00
The strobe
light power supply requires a 28 VDC input the red and black wires. Red is positive and black is negative, or common. The voltage for the strobe light is supplied through Pin 1 and 3 of the power supply connector with Pin 2 as the trigger pulse, The strobe light assembly is a potted assembly and cannot be repaired.
o""FWD
across
go
2
O
The
power supplies synchronized by may be connecting each yellow wire together between all power supplies (Hoskins only).
TROUBLE SHOOTING AIDS When
no
lights are flashing:
1. Check circuit
breaker/switch.
2. To determine power supply or flashtube problems, first check the input Mnage to the power supply. The red and black line should have 28 VDC. If no voltage is present check for shorted power leads or tripped circuit breaker. If input voltage is present, then disconnect the yellow sync wires. This will allow unaffected units to flash. Determine defective light and proceed to "one light not flashing" below.
When
one
2. If voltage is present across Pin 1 and 3 of the power supply, connect a I<nown good flashtube to the power supply. If good Rashtube fails to operate, power supply is defective. If good RasMube operates, We old flashtube is defective. Replace Rashtube.
Be
sure
yellow
syne wire is
insulated and
STROBE LIGHT POWER SUPPLY WARNING
units in any way. Failure to observe these result in physical injury from electrical shock.
precautions may C.
supply
A. Gain access to wing bottom inspection cover (1)
tip
33-2). Power supply (2) is physically attached inspection cover, B. Disconnect and power supply. 33-41-00
wiring
screws
inspection panel
and
between
power
above).
securing the power supply remove
to
the unit.
2´• TAIL STROBE LIGHT POWER SUPPLY.
supply through wing tip (See Figure
power
near
Disconnect wiring harness and strobe light. (See warning
D. Remove the
1. WING TIP STROBE POWER SUPPLY.
FIGURE 33-2
High voltage is involved in the circuit between the power supply and strobe light assemblies. Although a bleed-off resistor is incorporated in the power supply circuit, turn the control switch for the strobe lights OFF and allow at least 20 minutes to elapse prior to disconnecting the cables at the power supply or strobe light assemblies before handling either of these
not
POWER SUPPLY UNIT-REMOVAL OR REPLACEMENT
POWER SUPPLY
VIEW LOOKING UP LEFT WING INSPECTION COVER TYPICAL LOCATION RIGHT WING
grounded. 3391-01
~Es
O
light not flashing:
1. To determine power supply or flashtube problems, first check the input voltage to the power supply. The red and black line should have 28 VDC. If no voltage is present then check for shorted power leads, blown inline fuses, or circuit breaker. If input voltage is present, then disconnect the connector to the flashtube. 400-500VDC should be present across Pin 1 and 3 of the power supply. If not, the power supply has no output and is defective. Turn off master switch.
3.
1
O
A. Gain access to this unit through the inspection the aft, left hand side of the tailcone. The power supply is physically mounted to this inspection
to this
cover on
cOve’.
connections between switch
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
B. Disconnect the wiring connections between the switch and the power supply.
navigation light bulb (7) plate/socket (9)
C. Steps B thru D, and Warning of paragraph 33-41-01, 1, apply for removal of this power supply
C. Remove three screws (8) from the mounting plate/socket assembly and pull away form tip rib..
unit.
pulled from mounting
WARNING POWER SUPPLY UNIT INSTALLATION
33-41-02
The installation of any of the power supplies is reverse sequence of the removal procedures.
a
CAUTION STROBE LIGHT WIRING An incorrect hook-up of the wires at either the power input or between the strobe light assemblies and the power supply unit will cause a reversal of polarity that results in serious component damage and failure. Care must be taken to ensure that the red wire is connected to positive power and the black wire to ground.
units in any way. Failure to observe these result in physical injury from electrical shock.
D. Flashtube assembly, as a unit, must be replaced if determined to be bad. E. Wiring harnes plug (10) is connected to wing inside wing tip. F. Electrical plug may be reached through front of wina tin opening when all light assemblies are Reach between wing tip rib and wing rib to disconnect plug. G. Extract pins from connector with appropriate
1.WING TIP STROBE LIGHT. A. Remove to
wing tip malfunctioning
lens (1) (Figure strobe light.
33-3)
to
High voltage is involved in the circuit between the power supply and strobe light assemblies. Although a bieed-off resistor is incorporated in the power supply circuit, turn the control switch for the strobe lights OFF and allow at least 20 minutes to elapse prior to disconnecting the cables at the power supply or strobe light assemblies and before handling either of these precautions may
STROBE LIGHT REPLACEMENT
33-41-03
access
to be
gain
B. Remove screw (2) holding the retainer (3) against navigation/position light lens/gasket (4) and strobe Remove both (5). light lens/gasket lens/gasketâ&#x20AC;&#x2122;s This will allow light assembly (6) and
tool.
H. Install new strobe sequence of removal.
light assembly
in
reverse
5
3
8
4~9 4
10
SM33-NAV WING TIP LIGHTS 4-99
FIGURE 33-3 33-41-02
OLDWILLWAYNE MOON EY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
2. TAIL STROBE REMOVAL.
C. Pull lens a"d
A. To gain access to wire harness and connections from power supply, rotate round access cover (1) on lower left side of empennage stinger (Figure 33-4).
F. Secure
light assembly with
light assembly
retainer and
new
lamp into base. light assembly in
E. Reassemble
reverse
sequence.
2. AFT POSITION LIGHT
A.
to
Remove two
(1)
that
screws
secure
wing tip (2) (Figure 33-5). B. Remove clear lens (3) 8 gasket light bulb (4). C. Pull light bulb (with special puller
cover
D. There is sufficient wire available to pull strobe light assembly out from rudder strobe light mounting hole. See (Figure 33-4). Disconnect light assembly pigtail (5) from connector at (6) and replace assembly if needed. E. Connect plug from the strobe hamess socket at (6).
(red or green) from mounting plate (5) lamp (8).
D. Install
B. Cut Ty-raps at harness coil (1) to allow slack for strobe light assembly and harness to be extended beyond rudder.
C. Remove two screws (3) that secure retainer and strobe light assembly to rudder (4) and pull light assembly out so it clears mounting hole.
â&#x20AC;&#x2122;emove
aluminum
to
to
if
gain
access
needed).
I:
to
2
screws.
G. Check for proper operation. H. Coil harness at I. Secure
(1)
to take up slack.
access covet on
I
empennage.
1
FWD VIEWI
LOOKING DOWN LEFT
WING
ON
TIP
S
SMX33-7
AFT POSITION LIGHT
FIGURE 33-5
D. Replace with new lamp 8 reassemble light assembly in reverse sequence of removal.
6
33-43-00
-LANDING/TAXI LIGHTS
3343-01
-LANDING/TAXI LIGHT ADJUSTMENT PROCEDURES
1. Position aircraft to face a vertical wall with front of wheel 7 ft. 6 in, from wall. Position UH 8 R/H main landing gear at exact distance from vertical wall, is. parallel to wall.
5
nose
2. Place four
target
crosses
on
vertical wall at the
following positions: A. 36.5 inches up vertical wall from is resting on.
same
ground
plane aircraft TAIL STROBE LIGHT ASSEMBLY 33-42-00
FIGURE 33-4
B. 9.85 feet left and
NAVIGATION/POSITION LIGHTS
3. Remove
33-42-01
light location
1.WING TIP POSITION LIGHTS.
wing tip
B. Remove two lens in place. 33-42-00 10
lens
screws
nose
wheel center line. on
both left 8
cover behind each landing/taxi wing lower surface. 4. Tum taxi lights ON, exit aircraft, turn adjusting screws until light beams are centered on outboard left and right. target crosses 5. Repeat Step 4 for landing lights, except center light beams on inboard target crosses, left 8 right. 6. Turn lights OFF, reinstall access covers.
POSITION LIGHT
REPLACEMENT/SERVICE
A. Remove
right of
C. 12.375 inches further outboard right side of Step B. target position.
(1) (Figure 33-3). (2) holding position light 4-99
access
on
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
NOTE DO NOT LOOSEN OR TURN SCREWS THAT ADJUST LIGHT BULB POSITIONING FOCUS IN MOUNTING BRACKETS.
LANDING/TAXI LIGHT BULB
3343-02
REPLACEMENT 1. Remove
2.
access cover.
Carefully
remove
See pam. 3 above.
electrical
plug connection
from 6.
bulb. 3. Loosen socket head retainer
mounting
screws
5. Pull retainer from
large
access
slotted
hole and
Pull bulb from hole.
plate assembly
and
threough
access
to
7.
remove.
4. Rotate retainer to retainer from bulb.
MOONEY AIRCRAFT CORPORATION
M20M
8´•
pull
Replace new bulb Verify adjustment
in
reverse
has not
order of removal.
changed
per SECTION
33-43-01. 9. Replace access cover and recheck landing/taxi light operation and focus adjustment.
hole.
4-99
33-43-02 11
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
BLANK
33-43-02 12
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
CHAPTER
NAVIGATION
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 34 NAVIGATION AND PITOT STATIC
TABLE OF CONTENTS
CHAPTER SECTION
34-00-00 34-10-00 34-10-01
PAGE
SUBJECT
SUBJECT
5
General
5
Pitot 8 Static Air Heated Pitot-Trouble
Shooting
5
Airspeed Indicator Airspeed Indicator-Trouble Shooting Vertical Speed Indicator RateOf-Climb Indicator Trouble Shooting (Vertical Speed Indicator)
6
34-1 3-00
Altimeter
6
34-13-01
7
34-20-01
Shooting Directional Gym Compass Directional Gyro-Trouble Shooting
34-21-00
Turn Coordinator.
8
34-11-00 34-11-01
34-1 2-00 34-12-01
34-20-00
34-21-01
Altimeter-Trouble
Turn Coordinator-Trouble
Shooting.
34-22-01
Magnetic Compass Compass-Trouble Shooting.
34-23-00
Artificial Horizon
34-22-00
34-23-01
34-90-00
Gym-Horizon-Trouble Shooting. Miscellaneous Instruments
6 6
6
7 7
8 8
9 9 9
10
34-90-01
Clock
10
34-90-02
Outside Air Temperature
10
SCCONTENTS 4-99
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OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 34 NAVIGATION AND PITOT STATIC
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SU&IECT.
PAGE
DATE
1/2BLANK 3/4BLANK
4-99
34-00-00.
5.
4-90
34-11-00.
6.
4-99
34-13-01.
7.
4-99
34-21 -00
3.
4-99
34-22-01.
9.
4-99
34-90-00
10
4-99
34-Effectivity 34-Contents.
4-99
34-EFFECTIVITY
1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 34-00-00
CAUTION Release the air pressure slowly by unrolling the rubber tubing, a sudden release of the air pressure may damage the airspeed indicator.
-GENERAL
the
All flight instruments are grouped on shock mounted panel directly in front of the pilot. Flight instruments are operated by: (1) filtered air drawn into an evacuated instrument case, (2) barometric pressure or barometric impact air pressure differences, (3) variations in electric current due to mechanically varied resistance, (4) reference to the earths magnetic field or (5) aircraft electrical power.
system hose inspections-After the pitot for leaks. inspect the hose sections checked is system for signs of deterioration. Check all tubing for brittleness, checks or cracks particularly at the bends or connecting points. When new hose is installed, recheck thesystem for leaks using the PITOT SYSTEM LEAK TEST procedure. 2.
The glareshield must be removed and plumbing disconnected on many of the Right instruments before they can be removed. Remove glareshield attaching screws, center post cover screws and carefully lift center post cover and glareshield from the panel, Disconnect the glareshield and compass lights. Reinstall the glareshield in reverse sequence. 34-10-00
PITOT 8( STATIC AIR PRESSURE SYSTEM
foreign
end of
a
short rubber hose
over
matter.
CAUTION NEVER BLOW AIR through the line TOWARD the INSTRUMENT panel; to do so will seriously damage the instruments. When blowing back through the line from the instrument panel, make sure that no air is blown into the instruments.
1. Pitot system leak test.-(Make sure Master switch is OFF and Gear Control is in DOWN position.)
Slip
Pitot
3. Static system cleaning.-8low low air pressure (10-25 PSI). through the lines from the disconnected line at the airspeed indicator to the static ports. Cover each static port separately when blowing to insure that each line is clear. Instrument error or possible damage may result if even one port is clogged with dirt or
Static pressure instruments are extremely sensitive to pressure changes; therefore, the pitot and static system must be kept free from moisture and obstructions. Drain the pitot and static systems after humid or wet weather. If instrument operation is erratic or inoperative after draining, perform the following:
A.
SERVICE AND MAINTENANCE MANUAL
M20M
4. Static system leak test.-The static system should be checked for leaks in accordance with the instructions in Federal Aviation Regulation 91.171.
pitot tube.
B. Close open end of hose; slowly roll up hose until airspeed indicator reads 150 MPH. C. Clamp hose and hold for one minute, D. If airspeed indicator falls more than 9 KIAS, within one minute, check system for leaks and tighten line fittings. E. Repeat steps B, C, and D until obtaining less than a 9 KIAS indicator reading drop.
CAUTION To avoid damaging either the airspeed indicator or the landing gear airspeed safety switch an equal pressure should be applied to the pitot side of the indicator while leak testing the static
system. 5. Altemate static source.-An altemate static source valve is provided to change the static air source from outside the aircraft to inside the cabin. The valve is located on the lower panel under the pilots control column. Airspeed indicator and altimeterreadings will be slightly affected when using the altemate static source.
34-10-01
HEATED PITOT TROUBLE SHOOTING
Tube does not heat itself of ice with switch on.
or
clear
Switch circuit breaker
Open
tripped.
Repair.
circuit.
Excessive voltage drop between and pitot head.
battery
Heating
Reset circuit breaker.
element burned out.
4-99
Check for bad connections in connectors and cables leading to the pitot head.
Replace pitot
head.
34-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
Registers airspeed in knots. Air pressure difference impact air, pitot tube, and static air (static ports on each side of the aircraft tailcone) operates the airspeed indicator. An electrically heated pitot head prevents ice obstruction in flight. The airspeed indicator dial markings are as follows: between
Yellow Are
174-195 KIAS
Green Are
65-174 KIAS
White Are
59-110 KIAS
NOTE See Section 27-95-00 for stall
warning systems.
AIRSPEED INDICATOR TROUBLE SHOOTING
34-11-01
REMEDY
PROBABLE CAUSE
TROUBLE Instrument pointer does not indicate properly.
pointer oscillates.
Check for leak and seal lines.
Leak in instrument Obstruction in
Instrument
195 KIAS
Radial Red Line
AIRSPEED INDICATOR
34-11-00
case or
static
Clean out obstruction.
pitot tube.
Leak in instrument
case or
in
Check for leak and seal lines.
pitot lines.
This instrument has a single needle and two adjoining scales that read from 0 to 2000 feet per minute, top side for ascent rate and bottom side for descent rate. The recessed, slotted screw at the lower left of the instrument case is used to "zero" the indicator when the aircraft is on the ground.
VERTICAL SPEED INDICATOR
34-12-00
Converts barometric pressure changes within the static port lines to aircraft ascent or descent rate; readings are in feet per minute.
RATE-OF-CLIMB INDICATOR TROUBLE SHOOTING.
34-12-01
(VERTICAL
Pointer does not set
on zero.
Aging of diaphragm.
Turn zero.
Pointer fails to
respond.
Obstruction in static line.
setting screw to reset pointer at Tap instrument while resetting.
Disconnect static line from instruments. low pressure air (10-25 PSI max.) to instrument end of static line. Check both static ports for air flow. Depress static drain valve and check for water. Keep depressed until air is free of moisture. Reconnect static line to instruments and leak check.
Apply
(Includes water)
Pointer oscillates.
INDICATOR)
REMEDY
PROBABLE CAUSE
TROUBLE
SPEED
Leaks in static line.
Disconnect all instruments connected to the static line. Check individual instruments and test installation for
leaks.
Defective mechanism.
34-1 3-00
Replace
instrument.
-ALTIMETER
The altimeter operates by absolute pressure and converts barometric pressure to altitude; reading is in feet above mean sea level. The altimeter has a fixed dial with three pointers to indicate hundreds, thousands, and tens of thousands of feet. Barometric pressure is sensed through the static vents. A knob adjusts a movable dial behind a small window in the face of the main dial to indicate local barometric pressure. This corrects the altimeter reading for prevailing conditions.
34-11-00
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
ALTIMETER TROUBLE SHOOTING
34-13-01
TROUBLE
PROBABLE CAUSE
Excess scale
REMEDY
Improper calibration adjustment.
Replace
instrument.
Defective mechanism.
Replace
instrument.
High reading.
Static pressure
Eliminate leak in static pressure system.
Setting
Wrong lubricant or lack of
Excessive
error.
pointer oscillation.
knob is hard to turn.
system leak.
Replace
instrument.
instrument.
lubrication. Inner reference marker fails to move when setting knob is rotated.
Marker out of engagement.
Replace
Setting missing.
Excessive vibration.
Tighten instrument screw if loose. Replace instrument if screw is missing.
Excessive vibration.
Replace
instrument.
Age.
Replace
instrument.
Barometric scale and reference markers are out of synchronization with pointers.
Shift in mechanism.
Reset
Barometric scale and reference markers are out of
Slippage
is loose or
Cracked Dull
or
or
loose
cover
glass.
discolored luminous
markings.
of
mating parts.
pointers.
Replace
instrument.
synchronization. DIRECTIONAL GYRO COMPASS
satisfactory operation is 4.25 +/-.2 to 5.5 +0.0/-.2. The vacuum system filters should be changed each 500 instrument indicates the vacuum-operated heading hours or at one year intervals, whichever occurs first. reference. The directional gym rotor is air driven and (See Trouble Shooting Chart, for maintenance with horizontal. The knob its axis is used rotates to spin i"structions.) reset basic directional heading. Vacuum pressure for DIRECTIONAL GYRO TROUBLE SHOOTING OIACUUM ONLY) 34-20-01 34-20-00
This
TROUBLE
PROBABLE CAUSE
REMEDY
Excessive drift in either direction.
Dirty air filter thigh indication).
Excessive vibration.
Test with vibrometer. If vibration amplitude is more than .004 inch, examine shock mountings to see if connections are pulling on instrument.
Insufficient
If vacuum indication is below 4.25 IN. Hg., check as follows:
Correct for insufficient follows:
1. Vacuum regulating improperly adjusted.
1.
Adjust vacuum regulating
2.
Repair
vacuum.
2.
vacuum
valve
Pump failure.
3. Vacuum line kinked, leaking, or too long for its diameter.
4-99
Inspect filter. Replace if
or
replace
necessary.
vacuum as
valve.
pump.
3. Locate and, if defective, replace or repair vacuum line. Check for collasped inner wall of flexible hose.
34-13-01
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
D/G TROUBLE SHOOTING (conâ&#x20AC;&#x2122;t.) TROUBLE
PROBABLE CAUSE
REMEDY
Defective mechanism (worn dirty pivots and bearings.) Dial spins direction.
continuously
in
one
Operating
or
limits have been
Replace instrument.
exceeded
Reset the instrument with the aircraft in level Right.
Defective mechanism.
Replace
instrument.
-TURN COORDINATOR
34-21-00
A gym instrument that indicates control coordination and rate of turn. This instrument is
electrically driven.
TURN COORDINATOR TROUBLE SHOOTING
34-21-01
TROUBLE Pointer fails to
PROBABLE CAUSE
respond.
Bar does not set level.
Foreign matter instrument.
lodged
REMEDY
in
Replace
instrument.
No electric current.
Check
Gimbal and rotor out of balance.
Replace
instrument.
Replace
instrument.
Fitted
or worn
assembly
pivots
or
voltage at
instrument.
bearings. In low temperature, bar fails to respond or responds sluggishly
Oil has become too thick.
Replace instrument.
Insufficient
Replace
and with insufficient deflection.
Bar sluggish in returning to level does not set on level when stationary.
Oil
or
bearing clearance.
dirt between damping and cylinders.
The
MAGNETIC COMPASS
magnetic compass dial, graduated in five-degree a liquid filled glass and metal
The unit mounts at the top of the glareshield. The compass should be swung and compensated at each annual inspection and whenever new equipment is installed. case.
To compensate for N-S deviation, adjust left screw; to compensate for E-W deviation, adjust right screw.
of the tubular structure may be required if limits. be compensated within Carefully go over the entire steel structure with degauser, from center to outboard of structure (Left Right), to remove residual magnetism. It is recommended that an Armature Growler be used to degause steel structure.
Degausing
cannot
NOTE Refer to S.B. M20-150A, Instruction Ill, for detailed degausing procedures.
34-21-00
Replace
instrument.
pivots. NOTE Check for outside magnetic influences if excessive compensation is required.
increments, is encased in
compass
Replace instrument.
pistons
Excessive clearance between rotor and rotor 34-22-00
instrument.
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
COMPASS TROUBLE SHOOTING
34-22-01
TROUBLE
PROBABLE CAUSE
Excessive card
error.
Excessive card oscillation.
card.
REMEDY
Compass not properly compensated.
Compensate instrument.
External
Locate magnetic interference and eliminate if possible.
magnetic interference.
Improper
instrument
Insufficient
Sluggish
SERVICE AND MAINTENANCE MANUAL
mounting.
Align
liquid.
Weak card magnets.
Excessive pivot friction broken jewel. Instrument too
or
heavily
instrument.
Replace
instrument.
Replace
instrument.
Replace
instrument.
Correct
excess
Tighten
screws.
compensation.
compensated.
Liquid leakage.
Loose bezel Broken
screws.
cover
Defective Discolored luminous markings discolored damping liquid.
Age
Defective
Burnt out circuit.
glass.
sealing gaskets.
Replace
instrument.
Replace
instrument.
Replace
instrument.
or
light.
34-23-00
lamp
or
broken
Check
or
wiring continuity.
ARTIFICIAL HORIZON
The vacuum-powered artificial horizon gym indicates aircraft attitude Maintenance is similar to that required for the directional gym compass. 34-23-01
lamp
relative to
straight
and
level
flight.
GYRO-HORIZON TROUBLE SHOOTING
TROUBLE Horizon bar does not
PROBABLE CAUSE
respond.
Dirty air filter thigh indication), Insufficient from the
vacuum
vacuum
Horizon bar does not settle.
Pump
Examine filter and clean
or
replace
if
necessary.
resulting
Correct insufficient
vacuum as
follows:
following:
1. Vacuum regulating improperly adjusted. 2.
REMEDY
valve
failure.
1.
Adjust valve.
2.
Repair or replace pump.
3. Vacuum line kinked, leaking, or too long for its diameter,
3. Locate and repair. Check for collapsed inner wall of flexible hose.
Defective mechanism.
Replace
Insufficient
Correct for insufficient outlined above.
vacuum.
4-99
instrument. vacuum as
34-22-01
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
GYRO HORIZON TROUBLE SHOOTING
(conâ&#x20AC;&#x2122;t.) REMEDY
PROBABLE CAUSE
TROUBLE
Test with vibrometer. If amplitude is more than .004 inch, examine installation to determine whether flexible hose connections are restricting movement of instrument.
Excessive vibration.
Horizon bar oscillates vibrates excessively.
or
Excessive vacuum from the following:
1.
resulting
Examine shock if necessary.
mountings and replace
Correct for excessive follows:
vacuum as
1. Examine filter and clean
Dirty air filter.
or
replace
if
necessary.
2. Vacuum
regulating valve improperly adjusted.
2.
Adjust valve.
3. Defective mechanism.
3.
Replace
4. Excessive vibration.
4. Test with vibrometer. If amplitude is more than .004 inch, examine installation to determine whether
instrument.
flexible hose connections are restricting movement of instrument. 5. Shock mounted panel is contacting structure
5. Examine shock
replace
mountings and
if necessary.
(inadequate clearance).
34-90-00
34-90-01
-MISCELLANEOUS INSTRUMENTS 34-90-02
CLOCK
Provides the
The digital clock is mounted in the upper left side of the instrument panel.
34-90-00 10
OUTSIDE AIR TEMPERATURE
pilot
with the free stream outside air
temperature in degrees centigrade.
4-99
OLDWILLWAYNE
CHAPTER
OXYGEN
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 35 OXYGEN
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT.
PAGE
DATE
1/2BLANK
4-99
35-00-00
3.
4-99
35-00-02
4.
4-99
35-00-02.
5.
4-99
35-00-02.
6.
4-99
35-EffectivitylContents
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT
SUBJECT
35-00-00
PAGE
3
General Procedures
35-00-01
Recharging
35-00-02
Maintenance Practices
4-99
3 4
35-EFF/CONTENTS 1/2BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
WARNING
-GENERAL
35-00-00
Plqper safety
The oxygen system is a standard installation for serial number 27-0001 and ON. The system consists of a 115.7 cubic ft. cylinder located in the tailcone immediately aft of the baggage compartment bulkhead,
while oxygen
measures must
be
employed
system maintenance is being
performed or a serious fire hazard will be created. Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of oxygen. Make sure
that your hands, tools, and
clothing
are
clean, particularly
with respect to oil or grease, for these will IGNITE upon contact with pure oxygen under
pressure.
8 3590-01 o
RECHARGING PROCEDURES
7
12
WARNING or other lubricants in contact with oxygen create a serious fire hazard, and such contact must be avoided when
11
Oil, grease
dod
6~1
handling
10
Ir
5’
\4~3
_
oxygen
refilling cylinder.
1.The oxygen cylinder should not be used to less than 100 P.S.I.; contamination may occur to the Icylinder and valve. The valve must be removed and the cylinder cleaned and inspected if this happens.
’12
2
1
equipment.
WARNING NO SMOKING when
~Og
U
AC~M\I
oxygen
‘13
cylinder with aviators No. Specification MIL-0-27210, through the Oxygen 2. Refill the
OXYGEN SYSTEM
FIGURE 35-1A
oxygen
A reducing valve and an altitude compensating valve are connected to the cylinder to regulate the oxygen flow for a given altitude. Lines the altitude valve distribute aviators oxygen to the pilot and passengers. The system is activated by the control knob rotated to open th~e reducing valve. A gauge, located on the pilots arm test adjacent to the control, indicates the pressure of the cylinder. When the cylinder is full the preossu\re will indicate 1850 P.S.I, at 210 C. (700 F.). The system is serviced through an access opening the aft of located baggage compartment door. Standard refill fittings are required to fill the cylinder with aviators oxygen. (Spec. No.
connected
9
to
compensating
8 o
8
13
12 11
10
Mll-0-27210). The
interior dictated slight for the oxygen system outlets. Refer to Figure 35-1A for S/N 27-0001 thru 27-0180, -0182, -0183 configuration and to Figure 35-18 for S/N 27-0181, 27-0184 ON configurations. new
changes
5’
13
OXYGEN SYSTEM 4-99
FIGURE 35-18 35-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
Servicing Access Door (1) (Figure 35-1A or -1B). No special f7ttings are required for this servicing, however several types of standard oxygen fittings are in use and
compatible fitting for the Scott Recharging Valve (2) must be used. Mooney P/N 870025-503 oxygen recharge hose assembly is recommended. 3. The cylinder contains 1850 P.S.I. at 210 C. (700 F.) when fully charged. Temperature has an affect on the correct charging pressure; See Section 12-10-04 and (Figure 12-1) for pressure vs. temperature charging pressure. a
35-00-02
MAINTENANCE PRACTICES
(Ref: AC 43.13-1A,chap. 8, pam. 363) 1. The control cable (3) is attached to an actuating arm (4) on reducing valve (5). This cable is routed through various bulkheads along left side panel to control (6) at pilots position. The control is a push-pull cable assembly that is activated by a rotating knob assembly. The supply gauge (7), located adjacent to this control, indicates pressure of oxygen available in
The following the system:
procedures
are
recommended to purge
A. Connect
recharge cart to filler valve (2). Set cart regulator to deliver 50 PSI to aircraft system. (9) Plug an oxygen mask into each outlet (8)
pressure
B. in aircraft cabin.
C. Open cabin door and place control knob (6) in half open position. D. Allow system to purge for one hour. If an offensive odor still lingers, continue purging system for an additional hour. If such odors still remain, replace supply cylinder. After aircraft system has been adequately purged, remove all masks from outlets (8) (9), place control knob (6) in closed position and service the system as described in 35-00-01. 6. Oxygen cylinder removal. The oxygen cylinder is located in the tailcone aft of the baggage compartment bulkhead. Access to the cylinder is obtained thru the door on the left side of the aircraft behind left
wing.
system.
WARNING
2. The pilot’s, cc-pilot’s and passenger outlets (8) (9) should be inspected for damage and cleanliness
Keep fire, cigarettes and sparks away from the vicinity of oxygen cylinder. Oil and grease will
during servicing. 3. Inspect all individual oxygen masks and fittings (14) for damage. 4. Oxygen system test ptocedures. Remove oxygen line from regulator and plug line. Cap open regulator port with a clean plastic cap to prevent contamination of the regulator. Conduct low pressure 10 PSI oxygen supply system leak test using a 70 plugged into one cabin outlet and a test gauge plugged into another outlet. Apply 70 10 PSI to the system,
IGNITE upon contact with oxygen under pressure. A. Place
pilots control knob (6)
B. Gain access to oxygen door.
to closed
position.
cylinder through
tailcone
access
C. Slowly loosen supply line fittings at cylinder valve (5), (reference Figure 35-1A or -1B), to relieve any pressure that may exist in supply lines (12) 8 (13). After pressure is relieved, remove lines at fittings.
allow 2 minutes for the system to stabilize, remove oxygen supply. The drop in pressure after 15 minutes shall not exceed five PSIG. Remove temporary plug and ensure that the cylinder is charged to capacity. Conduct high pressure test using cylinder pressure. Using supely gauge, on pilot’s side wail, note cylinder pressure. There shall be no pressure loss after 30 minutes. If leakage exists, apply MIL-L25567, leak test solution, to suspected areas. After test, wipe clean and dry. Make necessary repairs and retest.
D. Disconnect control cable (3) from ann (4) on ’educing valve (5). E. Cap all open lines (12) (13) and regulator openings (5) (10) with clean metal caps. F. Note relative position of regulator valves (5) 8 (10) and control arm (4) prior to removal. G. Loosen clamps (11) retaining cylinder while supporting cylinder. H. Carefully remove cylinder and regulator from its position. 7. Oxygen cylinder installation. A. Place new cylinder and regulators into position in clamps (11) and secure. The new cylinder should be positioned with regulator valves and control arm in same position as removed cylinder assembly
5. Oxygen system purging. Offensive odors may be removed from oxygen system by purging. The system should also be purged any time lines are left open and subject to contamination. Purging is accomplished by connecting a recharging cart into system and permitting oxygen to flow through all lines and outlets until any offensive odors have been carried
away.
components.
WARNING Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of the airplane when the outlets are in use. Inspect the filler connection for cleanliness befbre attaching it to the filler valve. Make sure that your hands, tools, and clothing are clean, particularly from grease and oil stains, for these contaminants will IGNITE upon contact with oxygen.
35-00-02
MOON EY AIRCRAFT CO RPORATION
B. Remove caps from lines (12) (13); carefully all connections for damage or any foreign substance before connection to new cylinder and valves.
inspect
C. Connect all lines connect control cable
(12) (3) to
(13) to proper fitting and (4) on reducer valve
arm
(5). D.
Charge cylinder, if required, to the see recharging table (Figure 35-2).
pressure,
4-99
correct
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION E.
Place
pilots
contol
knob
(6)
M2oM its
to
OPEN
NOTE
position.
Oxygen cylinders
F. Plug oxygen mask (14) into check for proper system operation.
pilots
outlet
G. Repeat this checkout procedure for (8)& (9). H. Test
SERVICE AND MAINTENANCE MANUAL
system for leaks per leak
paragraph 35-00-02,
(8)
hydrostatic tested in accordance with DOT Code of Federal
to
Regulations,Title 49,chap. 1, para. 173.34. (REFER TO SECTION 5-10-01 ALSO)
all outlets
test
NOTE All oxygen
cylinders must be replaced every 10,000 recharge cycles.
check,
D.
I. Reinstall tailcone
access
must be
NOTE
door.
Maximum life for
composite oxygen cylinders
is
15 years. NOTE
Maximum life for
light weight steel oxygen cylinders is 24 years.
Filling pressures will vary due to ambient temperature in the filling compression of the oxygen. Because of this, merely filling to 1850 Fill to pressures indicated
AMBIENT
on
FIG. 35-2 below for ambient temperatures.
FILLING PRESSURE
TEMPERATURE OF
and the rise of temperature resulting from PSIG will not result in a properly filled cylinder.
area
I
PSIG
O
1650
10
1700
20
1725
30
1775
40
1825
AMBIENT TEMPERATURE OF
FILLING PRESSURE PSIG
1 1
50 so
1925
1 1 1
70
1975
80
2000
90
2050
OXYGEN FILLING PRESSURES VS. TEMPERATURES
4-99
1875
FIGURE 35-2
35-00-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
35-00-02
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
VACUUM
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONfl AIRCRAFT CORPORATION
CHAPTER 37 VACUUM
TABLE OF CONTENTS CHAPTER
SECTiON SU&IECT
SUBJECT
37-00-00 57-10-00 37-11-00
General.
PAGE
5
Distribution
Dry AirP;md
5
5
37-11-01
Maintenance Practices.
5
37-11-02
Servicing
6
Removal
6
Reinstall
6
37-11-04
37-12-00
Vacuum
Regulator
6
37-12-01
Maintenance Practices.
37-12-02
Servicing
6
37-12-03
6
Removal
6
37-12-04
Reinstall
6
37-12-05
Adjustment.
7
37-1300
Filters
7
37-13-01
Maintenance Practices.
7
57-13-02
Servicing
7
37-13-03 37-1504 37-1400
Removal
7
Reinstall
7
Hoses
7
37-1401
Maintenance Practices.
7
37-1402
Servicing
7
57-14-05
Removal
7
37-1 404
Reinstall
7
57-20-00 57-21-00
Indicating Vacuum Switch
7
37-21-01
Description
8
37-21-02
Maintenance Practices.
8
57-21-03
Removal
8
37-21-04
Reinstall
8
37-21-05 37-30-00 37-30-01. 57-40-00 37-41-00
37-42-00
Adjustment. D~v Air Pump Repair Coupling Installation Stand-by Vacuum System Operational Procedures. Maintenance Practices
8 8 8 6 8 9
37-42-01
Removal
9
37-42-02
Installation
9
37-CONTEMS
3/4BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 37
VACUUM
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT.
37-Effectivity
PAGE
DATE
1/28LANK 3/4BLANK
4-99
37-00-00.
5.
4-99
37-11-02.
6.
4-99
37-12-05
7.
4-99
37-21-01.
8.
4-99
37-40-00
9.
4-99
37-42-02
10
4-99
37-Contents.
4-99
37-EFFECTIVITY
1/28 LANK 4-99
OLDWILLWAYNE 37-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CAUTION clean pump to filter line and replace filter between pump and firewall when replacing a failed pump to prevent particles from failed pump Deing ingested by the new
-GENERAL
Always
air vacuum pump supplies operated gyroscoplc flight instruments, Directional Gyro and Artificial Horizon. Air is passed through a filter before entering the instruments. A vacuum regulator valve is incorporated to maintain required operating vacuum throughout engine power range. Idle RPM settings will normally not provide adequate vacuum to satisfactorily operate An engine driven dry for suction vacuum
pump.
MAINTENANCE PRACTICES
37-11-01
Protection of pneumatic dry air pump when the engine compartment is very important.
instruments,
cleaning
A vacuum annunciator light will illuminate (RED) and flash when vacuum drops below the setting required to operate the instruments. The Vacuum Annunciator Light will illuminate steady (RED) when vacuum exceeds normal regulator settings.
WARNING Failure to protect the dry air pump from contamination by engine cleaning solvents may result in failure of the dry air pump within a short period of operation.
A stand-by vacuum system is standard for the M20M aircraft. This system is installed on the engine accessory pad through an electrically activated clutch assembly. The stand-by vacuum system should be activated manually when "HI/LO VAC" light flashes while on primary engine driven system. This is done by pushing STBY VAC switch, located on instrument panel, ON.
Prior to washing down engine compartment, the following precautions must betaken for better service life of the pneumatic dry air pump. i. Dâ&#x20AC;&#x2122;Y air pump coupling.
37-10-00 37-11-00
CAUTION Do not blast the air pump coupling area or other pneumatic system components with cleaning solvent under high pressure.
-DISTRIBUTION
Protect coupling area between the pump mounting flange and the pump housing by wrapping a protective
DRY AIR PUMP
covering around that area during engine cleaning.
A dry air pump (1) (Figure 37-1) requires no maintenance between replacement. Replacement is at engine overhaul. recommended at 500 hours
CAUTION Do not allow protective covering around the coupling or filters to become saturated with solvent.
NOTE
Always replace inoperative pump with
new
air
pump. ARTIFICIAL HORIZ(IN
STAND-BY VACUUM PUMP CHECK SYSTEM
k
ej VACUUM REGULATING VALVE
FILTERS
STAND-BY VACUUM PUMP
OYRO FILTER
OMRBOARD TUBES
(PRESSURE)
MAIN VACUUM PUMP
SMR37-1
VACUUM SYSTEM
4-99
FIGURE 37-1 37-00-00
OLDWILLWAYNE 7. Always replace ALL locking washers when installing a new pump. Tighten all four (4) mounting
housing behind coupling are foreign material such as dirt, dust and light fluid. However, fluid under high pressure can be forced past seals and enter pump. 2. Dry air pump fittings. Before washing engine off, check pump fittings for looseness of threaded fittings. Fluid can seep through loose threads and enter Seals in front frame of
designed
to
keep
out
90 to 110 in. Ibs.
nuts
8. Prior to reconnecting hoses, inspect inside of hose carefully to make sure it is clean and free of all debris, oils or solvents. Use vacuum or air pressure to clean all lines. Remove hoses from aircraft if necessary to clean.
pump.
When hose clearance is tight, making it difficult to reinstall onto pump fitting, spray fitting at hose end with silicone. LET IT DRY, then install hose by pushing it straight onto fitting.
air pump discharge hose (vacuum instrument end of hose or fitting and flag it with a RED "Remove Before Running Engine" tag, then clean 3.
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
Dry
system). Plug engine.
CAUTION
CAUTION Remove
plug prior
dry
parts
wiggle hose from side to side during placement. Wiggling could cause particles to Do not
running engine.
SERVICING
37-11-02
The
to
requires no servicing. self-lubricating and require NO ADDITIONAL
air pump
are
be cut from hose Ib. These particles would damage the pump.
The internal
lubricating.
done
-REMOVAL
37-11-03
1. Disconnect hoses from
dry
air pump.
mounting gasket and locking
vacuum regulator (2) (Figure 37-1) is a spring-controlled diaphragm valve for regulating vacuum for the aircraft pneumatic instrument system. The vacuum regulator is located on left-hand side of firewall, inside cabin, just under glareshield. Adjust vacuum regulator valve according to Section 37-12-05.
fittings
serviceable;
corners.
inspection. Check condition of the AND pad seal. If seal shows any signs of oil leakage, replace seal. Replace seal if there is any doubt as to its serviceability, 4.
Pad
37-12-01
20000
Check secure
(Main Never install
a
or
Stand-by)
No
CAUTION pump that has been
servicing replacement.
dropped.
37-12-03
Consult airframe manufacturerâ&#x20AC;&#x2122;s current Parts Catalog, Airborneâ&#x20AC;&#x2122;s Application List, or the PMA label on pump box to verify that pump is correct model for the engine and/or system application. 1.
2. Place pump
mounting flange
in
a
metal
or
jaw-protected
wood.
37-12-04
carbon rotor. thread with silicone and LET IT DRY. teflon tape, pipe dope or thread lube.
fittings in the pump. Hand tighten initially. 5. Use only a box wrench to tighten fittings to desired position. DO NOT make more than one and one half (1 1/2) turns beyond hand-tight position. 6. Install new pump mounting gasket (supplied with new pump). (NOTE: No gasket is required between stand-by pump/clutch assembly and its adapter plate mounting pad.) 4. Install
37-11-02
vacuum
REINSTALL
insert Inside aircraft mounting hole in firewall. 1.
Spray fitting use
REMOVAL
panel, remove both regulator; cap off to prevent foreign objects from entering them. hoses from 2. Engine compartment remove vacuum regulator; cap off to prevent foreign objects from entering. 3. Loosen and remove large nuts at firewall on vacuum regulator. 4. Pull regulator aft to remove from aircraft.
CAUTION
DO NOT
is required on regulator other than filter See Section 37-13-00 for details.
instrument lines from
Pump housing should never be placed directly in a vise, since clamping across the center housing will cause an internal failure of the 3.
SERVICING
1. Underneath the instrument
vise, with the drive coupling downward. Protect pump
mounting flange with soft
MAINTENANCE PRACTICES
general condition of regulator to insure it is and in airworthy condition.
37-12-02
INSTALLATION OF NEW PUMP
37-11-04
VACUUM REGULATOR
Th,
hardware.
from pump. Retain fittings if they clean thoroughly before reusing. Discard twisted fittings and any nuts with rounded 3. Remove
are
or
37-12-00
engine and discard
2. Remove main air pump from
old
CAUTION filters in the system. This must be pump warranty MAY BE VOIDED.
Change all
4-99
vacuum
regulator
thru
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
large nut on regulator and tighten. install hoses from 3. Engine compartment regulator and secure.
pump to
The hoses
regulator and
secure.
37-12-05
-ADJUSTMENT
of aircraft MIL-H-
CAUTION Remove
at a minimum of 1700 RPM. If is not set at 4.75 +/-0.25 In. Hg.,
Operate engine regulator
vacuum
bendlocking
screw.
Adjust
tab away from thumb
as
setting regulator, rebend tab adjusting screw.
All filters,
except the
back to lock
regulator
paper-pleated material design. a foam-garter design.
The
filter
vacuum
are
of
on
regulator
5-10-01) A. Vacuum
regulator, garter, filter
every 100 hours.
B. Gym instrument filters every 500 hours least once a year.
or
changed when
a new
particularly layers may
at
NOTE Do not wiggle hose from side to side. Wiggling could cause particles to be cut from hose ID. These particles could damage the pump.
2. All filters require routine inspection of condition of element and security of filter in system. 3. All filters must be
is
Where hose clearance is tight, making it difficult to reinstall it onto the pump fitting, spray the fitting at the hose end with silicone. LET DRY, then install hose by pushing it straight on.
(See Section
replacement intervals:
security
--REINSTALL
37-1 4-04
MAINTENANCE PRACTICES
Air filter
for
or brittle hose, the pump inlet. Sections of the inner separate, causing a pump failure.
Replace old, hard, cracked
filter is
37-13-01
clamps
-REMOVAL
37-14-03
vacuum
all
running engine.
Inspect inside of hose carefully to make sure it is clean and free of all debris, oils or solvents. Use vacuum or air pressure to clean lines. Remove the hoses from the aircraft if necessary to clean.
-FILTERS
37-13-00
of
to
-SERVICING
37-14-02
NOTE After
plug prior
Periodic check recommended.
adjustment required. Turning screw IN will increase vacuum; turning screw OUT will decrease vacuum. Adjust vacuum to read 4.75 +/-0.25 In. Hg.
then
type.
During engine cleaning, protect the discharge hose: 1. Plug end of hose and Rag it with a RED "Remove Before Running Engine" tag, then clean the engine.
a calibrated vacuum gauge into system, upstream of the regulator, (see Figure 37-1).
2.
xxx
MAINTENANCE PRACTICES
Tee
1.
1.
are
37-14-01
install both instrument lines to
Inside aircraft
-HOSES
37-14-00
2. Install
4.
SERVICE AND MAINTENANCE MANUAL
M20M
pump is
installed. -SERVICING
37-13-02
All filters
require
Make certain
Replace with new Optional instrument filters (if installed) should the same cleaning and replacement schedule. 1.
a low vacuum wamlng in annunciator, which Rashes (RED) when the vacuum is below 4.25 +/-.2 In. Hg. and a high vacuum warning light, HI/LO VAC in annunciator, which illuminates steady (RED) when the vacuum goes 5.5 (+.2-.0) In. Hg. or above.
Vacuum regulator garter filter is removed it over and off the regulator frame,
by
2. The Gyro instrument’s filter is mounted on a bracket under the instrument panel just fon~vard and to the right of the pilot’s right knee.
new
filter in
fitting
The
and
(7),Fig. 37-1, is located on either (3) or Directional Gyro (4). illuminating low and high light ADJUSTMENTS
The vacuum switch the Artificial Horizon
1. Prior to installing a new vacuum regulator filter, check the regulator to insure that it is clean from any foreign material. 2. Reinstall
VACUUM SWITCH
37-21-00
into the filter
-INSTALLATION
37-13-04
indicating system contains
light, HI/LO VAC
stretching
coming
connected to the correct to the
INDICATING
37-20-00 The
3. Disconnect the two hoses and remove it from the bracket.
are
follow
REMOVAL
37-13-03
hoses
fittings. Incorrect installation will cause damage gym system. Install clamps and secure.
service except routine inspections. current configuration filters.
no
are
done
on
the switch,
NOT
on
the annunciator
panel.
secure.
CAUTION Don’t
over
tighten; overtightening the rear housing.
will crack
4-99
37-12-05
OLDWILLWAYNE
The
7. Remove Calibrated gauge after verification.
DESCRIPTION
37-21-01 switch is unit.
low and
a
high
vacuum
sensing
Check for switch security in instrument and all wires
Remove i. vacuum pump accordance with maintenance 57-11-03.
secureatswitch.
-REMOVAL
Disconnect wires and
unscrew
from aff instrument
housing. 3781-04
-REINSTALL
Install switch in
housing
and
tighten.
Reconnect wires.
2. If coupling (1) has sheared, remove engine coupling drive gear (2) from engine gear housing.
4.
Push new drive drive gear (3).
1.Remove switch from instrument. Reinstall wires if removed. Attach poly-vinyl hose, "T" fitting and calibrated gauge to vacuum switch. Connect other end of hose to a vacuum source.
3.
The "Hl/low vac"
light
Apply vacuum and adjust source to 4.25 (+/-0.2) Adjust Low setting screw (connector end of
to illuminate the low annunciator panel.
vacuum
circuit
on
the
4. Increase vacuum source to 5.5 (+.2-.0) In. Hg. Punch a small jewelers screw driver through the poly-vinyl tube and into the fitting where the high setting screw is located and adjust until the "HI/LO VAC"â&#x20AC;&#x2DC;light on annunciator is illuminated, 5. After you have aircraft power off.
completed
switch
adjustment
turn
6. Remove switch from hose and gauge. 7. Reinstall switch in
Gym.
Reconnect wires.
CAUTION the electrical wires on vacuum switch wIll cause the annunciator lights to act in
Crossing
reverse.
31-22-00
27-0258 thru 27-TEA
1. See Figure potentiometer.
Gauge
2. Tee in calibrated Vacuum Vacuum Regulator. 3.
Apply
vacuum
4.
or
to aircraft
stand-by
hand
(2)
into
place
on
pump
check for correct rotation of
on engine Chapter37-11-04) 8. Make log book entry.
and test
run
(refer
37-40-00
STAND-BY VACUUM SYSTEM
3741-00
OPERATIONAL PROCEDURES
to
TheStand-by Vacuum Pumpassembly, incorporated on the M20hn, is either an engine mounted standard vacuum pump coupled to an electric clutch or a tailcone mounted, electrically driven, standard pump to allow operator selected ON/OFF operation as necessary.The Stand-by Vacuum system is to be used, only as needed, when the main vacuum pump malfunctions. The VAC annunciator light will iilumhate (RED) either flashing (low vacuum) or steady thigh vacuum) when this situation occurs. If annunciator flashing RED, push the STBY VAC switch ON and any flashing annunciator light should extinguish as the stand-by vacuum system takes over for all instrument operations. If annunciator light is steady RED, monitor flight instruments with "O"-vacuum gauges and continue Right if feasible, or land and have Vacuum System repaired. Check vacuum regulator for malfunction.
contamlnatron within
vacuum
by
system and
pump.
visible.
vacuum
Adjust regulator
to 4.8 in.
6. Verify aircraft calibrated gauge.
37-21-01
on
Operation of the engine driven, clutch actuated stand-by vacuum pump can be checked when engine is running by the following procedures: 1. Verify indicator RED button on C/B panel is
down stream of
system. Use separate
vacuum
place
stand-by vacuum pump/clutch assembly could be affected by the same cause.
adjustment
gauge potentiometer to read calibrated vacuum gauge.
Adjust
same as
5.
vacuum
supply
of
by
pump. 7. Reinstall pump
some
39-48 for location
into
WARNING Malfunction of main pump could be caused
GAUGE ADJUSTMENT
DIGITAL
coupling (1)
5. Push coupling drive gear drive coupling (1). 6. Tum
on.
manual,
coupling
-ADJUSTMENT
2. Turn aircraff power should Rash.
engine in Chapter
from
3. Use a screwdriver or similar tool, remove pump drive coupling (1) from coupling drive gear (2) and coupling drive gear (3) being careful not to damage drive pins.
CAUTION Do not over tighten. Over tightening will cause cracking of the aft instrument housrng.
37121-05
COUPLING INSPECTION AND REPLACEMENT
3730-01
-MAINTENANCE
3741-03
DRY AIR PUMP REPAIR
37-30-00
adjustable 37Q1-M
MOOND/ AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
2. Turn
Stand-by Vacuum Pump Switch -ON. stand-by VaCUU" pump is oeating properly. 4. Turn Stand-by Vacuum pumps switch OFF. 3. RED indicator button will not be visible if
Hg.
instrument
reads
same
as
499
OLDWILLWAYNE SERVICE AND MAIMENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
~iU
0‘0‘ O
~O
O
O
t, I, VACUUM
PUMPS MAY VARY,
BUT
COUP LING WILL BE SIMILAR
SMEAR
FOR
MOST VACUUM
PUMPS. SMX37-2
DRY AIR PUMP COUPLING
INSPECTION/REPLACEMENT
FIGURE 97-2
NOTE
complete check out and maintenance of the entire system is necessary if either pump experiences a malfunction. A
If during inspection, the AND 20000 pad seal shows signs of leaking, the adapter plate and drive extension must be removed to allow replacementof pad seal between drive extension and AND 20000 pad. A gadret le also required between drive extension and stanc~by pump/clutch adapter plate. No gasket Is required between stand~by pump/clutch assembly and adapter plate pad.
vacuum
It
Is
recommended
tall-cone mounted be turned ON prior t~hat the vacuum gauge (if
that
stand-by vacuum to engine start
the
to"v~Rsystem
equipped) indicates normal operating vacuum and that the gyros spin up and erect. When engine is started, the check valves closes and the stand-by vacuum pump system will not produce sufficient additional vacuum for any indication on the gauge (if equipped) 3742-00 The
stand-by
vacuum
pump/clutch assembly
the below approximately centered on 3742-01
REMOVAL-
Disconnect
hoses
main
engine
vacuum
accessory
new
stand-by vacuum pump/clutch assembly. No gasket is ’equired between stand-by pump/clutch assembly a"d 8dapter plate pad. 2. Replace stand-by vacuum pump/clutch assembly as a complete unit. 3. Replace all lockwashers. Tighten mounting nuts
is
pump case.
(CLUTCH DRIVEN) from stand-by vacuum
pump/clutch assembly. 2. Remove four (4) socket head cap screws attaching stand-by pump/dutch assembly and remove assembly from adapter plate pad. The adapter plate does not require removal. 3. Proceed with inspection of stand-by vacuum pump/clutch assembly per steps in Section 37-11-03, steps
INSTALLATION OF NEW STANDBY VACUUM PUMP ASSEMBLY
1. Refer to Section 37-11-04 for installation of
MAINTENANCE PRACTICES
mounted
1.
3742-02
to be noticible.
110 in. Ibs.
90
WARNING
adapter plate, to mount stand-by pump/clutch assembly, has been removed for any reason, It 271 on threads is necessary to apply loc-tlte, of flush head attaching screws (4 each) and
If
torque each
screw
to 70 Inch Ibs.
3 and 4.
4-99
37-42-00
OLDWILLWAYNE
TAIL CONE STANPBY VACUUM PUMP SYSTEM OPERATIONAL PROCEDURES
NOTE Refer to Airborne Service Letter, No. 34, for Inspection information on stand-by vacuum
pump/clutch assembly
drive
If installed, the stand-by Vacuum Pump system is located in the tailcone. Its location lis standard, but
coupling.
TAILCONE MOUNIED STANPBY VACUUM SYSTEM
can vary
installed
(If installed The
tailcone mounted stand-by vacuum pump assembly is to be a repaired/serviced in accordance with the particular vendor’s procedures. If no specific maintenance information is available from the manufacturer the following is recommended: 1. Inspect to verify hoses and wires are clear of any obstruction or interference with other components that may chafe hoses or wires.
2. and
3.
Inspect
hose
clamps
on
all
fittings
to
verify tight
secure.
100 hour/annual inspection in motor/air pump coupling for
Every
screws
inspect set tightness and
security. 4. A dry air pump requires no maintenance between replacement. Replacement is recommended at 500 hours operating time. It is recommended that stand-by vacuum system operating time be documented. 5. It is recommended that if the Stand-by Vacuum used regularly, that every 90 days the Stand-by Vacuum System should be turned on, in Right, for 20 30 minutes to get the pump and drive motor warm enough to dry out any condensation that may have accumulated. The exhaust port of the dry air pump is routed into the housing of the electric motor to assist in purging moisture and debris from the motor assembly.
System is not (approximately)
37-42-02 10
MOONP/ AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
499
slightly depending on
upon
optional equipment
aircraft.
The Stand-by pump is to be used only as needed when the main Vacuum pump malfunctions. The VAC annunciator light will illuminate (RED) either Rashing (low vacuum) or steady thigh vacuum) when this situation occurs. If annunciator light is flashing RED, push STBY VAC switch ON and annunciator light Should extinguish as stand-by vacuum system takes OV~’ fO’ all Instrument operations. If annunciator is steady RED, monitor Right instruments with non-vacuum gauges and continue with flight if feasible, or land and have vacuum system inspected and repaired. It is recommended that prior to aircraft engine start, the stand-by vacuum pump be turned ON to verify that the vacuum gauge (if equipped) indicates normal operating vacuum and that the gyms spin up end erect. When the engine starts, the check valve closes and the stand-by vacuum pump system will not produce sufficient additional vacuum for any ndication on the gauge (if equipped) to be noticeable.
OLDWILLWAYNE
CHAPTER
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M CHAPTER 39
ELECTRICAL PANELS AND COMPONENTS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT
DATE
PAGE
499
1 I2BLANK
39-EFF/CONTENTS. 39-00-00
3.
499
4.
4-99
39-11-01
5.
499
5911-01
6.
499
3911-02
7.
499
59-12-04
8.
4-99
59-21-00
10.
4-99
TABLE OF CONTENTS
CHAPTER SECTION
39-00-00
39-10-00 39-10-01 9910-02 39-11-00 39-11-01
3
General.
Flightlnstruments Equipment Engine Instruments and Flight Instrument Panel ClusterGauge
3 3
Avionics
Landing Landing
59-11-04
Clock
39-12-00
3
Instrument and Control Panels
3911-09
39-11-02
PAGE
SUBJECT
SUBJECT.
Circuit Breakers
Safety
7
8
Avionics/Radio Panel
8
39-12-02
Emergency
39-12-03
Instrument and Radio
Light
39-12-04
Cigar Lighter Electrical/Electronic Equipment
Rack
39-21-01
7 8
Annunciator Panel
39-21-00
5
Override Switch.
39-12-01
59-20-00
4
GearSwitch Gear
Locator Transmitter
(ELT)
Switch.
Control Box
499
System
8 9 9
Miscellaneous Maintenance Recomendations. Pitch Trim
4
Maintenance
9 9 9
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 39-00-00
-GENERAL
the disconnects for the glareshield the wires and lift the glareshield off.
The
instrument panel is divided into three basic groupings; (1) Flight Instruments, (2) Avionics/Radio Panel and (3) Engine Instruments and Circuit Breaker Panel. Theflight instrument panel is shock mounted. The radio/avionics panel generally, has individual racks for the components and are of the quick removal type. The circuit breaker panel is located in a quick removal panel, located at the far tight of cockpit.
C. Disconnect and
is
located
at
the
top
of
B.
39-10-01
-FLIGHT INSTRUMENTS
secure
C. Connect the post
the
mounting
panel.
to
screws
hold
lights.
D. Connect all plumbing and/or electrical connections to the instrument; perform pitot-static leak check. the E. Position glareshield connections can be made and secured.
glareshield
F. Secure
and
electrical
so
plate with
cover
screws.
-AVIONICS EQUIPMENT
39-10-02
Each avionics package installed is basically a customized package to meet the requirements of the customer. Wiring harness, any associated plumbing or mechanical mechanisms required for a particular avionics installation are well secured to prevent any interference with other components. Removal of these avionics components will require evaluation of each installation to determine the proper procedure or sequence to follow.
1. Removal.
A. Remove the and cover plate and
Insert and
on
instrumenttopanel.
Hardware Charts
INSTRUMENT AND CONTROL PANELS
the
it aft from the
A Place instrument into the proper location
A radio blower is incorporated to cool the avionics is turned on when Radio Master Switch is
39-10-00
securing
screws
2~ Installation.
avionics/radio panel.
System
any post lights.
by sliding
E. Remove the instrument
The panel illustration depicted in Figure 39-1 shows a typical installation. Model year improvements, technical improvements or various avionics installations dictate which instrument will be installed in a given location.
See Section 91 for Electrical and Schematics.
Disconnect
panel.
cluster
annunciator
remove
D. Remove the mounting instrument to the panel.
gauges, containing fuel quantity and engine operating gauges are located to the right of the flight and navigation instruments on the pilot’s instrument panel. The
lights.
B. Disconnect the plumbing and/or electrical connections from the flight instruments to be removed.
The circuit breaker/switches for the standard and/or optional accessories and equipment are located on upper/mid left and bottom of the flight instrument panel. The
SERVICE AND MAINTENANCE MANUAL
M20M
1. Removal.
attaching the glareshield carefully lift glareshield to expose screws
FLIGHT/ENGINE
INSTRUMENI
PVIONICS/RADiO
CIP~U T
PANE_
BREAKER
PANEL
PANEL
t~
´•´•´•´•g~l
osE ~g 5g g~g
(23:59] 99P
I
W~A 8~8
soo
II 59.a
In~ IbOLidi 110
0;1
gg
lso
06p=gCBOfi
losoa
I
o~ -Is n
00000000
Z
60
88~o.sooos
igBa
~I o
88888 U
-´•1
!~1
O
IIS!a~aaea
~3
BAl
oo
0~0
TYPICAL INSTRUMENTS AND CONTROL PANEL 4-99
n Q 27-0108
Be
ON
FIGURE 39-1 39-00-00
OLDWILLWAYNE D. Remove two screws (D) from underneath, near edge of the panel face. E. Remove the MS21919WDG() clamp (E) from the steel structure cross brace, underneath the panel, forward section, see (Figure 342). F. The panel should now be free to slide aft approximately 4-5 inches. This will allow access to the plumbing and electrical connections. Remove the plumbing or the electrical G.
Most individual avionics components are mounted in slide out chassis racks. Loosen the screw on the face of the component and slide the unit straight aft to
the
remove.
Some components are not mounted in slide out chassis. Removal of these units will require the same sequence as removal of flight instruments in Section 39-10-01. CAUTION Radio
2.
panel
must be stacked from the bottom to the top.
Install the repaired sequence of removal.
Installation.
reverse
39-10-03
or
new
unit
connections from the
In some instances components, other than the one to be removed, must be removed or at least some wiring, or plumbing disconnected to gain access to the desired one.
The circuit breaker panel is an assembly that can be pulled out as a unit for removal of any switch or circuit breaker,
H. Remove thin lexan glass insulation strip if required when removing components. i. Remove the circuit breakers by unscrewing nut
1. Removal.
refer to
glareshield
from stem on each circuit breaker and breaker forward through the panel.
Section
push
the
2. Installation.
B. Drill out 3 rivets on outside of the airplane (B) (Fig. 39-2). These are located forward of the cabin door hinge and above the cabin air inlet scoop approximately 4 inches below the windshield,
C. Remove two screws from the face of the at the upper left corner (C) (Figure 39-2).
component that will be removed. NOTE
in
CIRCUIT BREAKER PANEL
A. Remove the 39-10-01.
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
A. Installation of new instrument or circuit breaker panel is accomplished in reverse sequence of removal. into the
B. Insert the lexan insulator sheet location to prevent any short circuits.
panel
39-11-00
in
proper
FLIGHT INSTRUMENT PANEL
flight instrument panel is a shock mounted panel containing various flight instruments for a particular
The
3
group. These instruments vary slightly upon the avionics package installed. The panel contains circuit breakerlswitches, along with the Master Switch, which control most of the systems of the airplane. Refer to Figure 39-3). installation
depending
C B
CAUTION Care should be exercised when replacing wiring or switches to ensure proper alignment of terminal connections to prevent shorting between switches.
CIRCUIT BREAKER PANEL o
o
REMOVAL CIRCUIT BREAKER PANEL REMOVAL 39-10-03
Access for maintenance of the switches or related wiring is obtained by removing the two attachment screws and pushing the switch forward through the panel. There is a common bus bar on some of the switches that will require loosening or removal for switch replacement.
FIGURE 39-2 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
rr´•´•´•~441 a
OQ9(A~
660
8~8
(CIP~BDI P
X
O
o a LNO ILITE
e
i
fELEC.
99~
ROCKER/CIRCUIT BREAKER SWITCHES 39-11-01
FIGURE 393
To remove the entire cluster gauge the wiring harness can be disconnected at connector adjacent to duster gauge unit. The nuts on terminal studs need to be removed so wire terminals can be pulled from studs to remove the modules from the cluster gauge chassis.
CLUSTER GAUGE
The cluster gauges are located at the top/right of the flight panel.Access is obtained by removing the glareshield per Section 39-10-01. Cluster gauges have the capability of individual module replacement. Remove and replace the defective module as -foilows: Loosen the single screw to the point where it no longer is threaded into the chassis. Use the screw as the "handle" to pull the module from the cluster chassis. In some cases the adjacent, more centered, module may need to be removed before one of the edge modules will easily come out. 4-99
39-11-01
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
THIS ISSUSTRATION DEPICTS CONFIGURATION OF 27-0001 THRU 27-0052 ONLY. 27-0053 ON IS SLIGHTLY DIFFERENT.
~i ii L.FUEL 01Y.
li´•´•´•´•)I
ol a
~j
t~l
II~ R´• FUEL OM
B
QoB ALT.R.
BUS LOAD
O sae
8~8
n
~pem
I~BBSOI
Q O
I~o
VPCIU
QpslFCHTOAT’CF FUEL‘ ~PRESS
Ile~ ~p
O
O
ooclo~o
Q
OIL TEYP
CLUSTER GAUGE
MORITZ
DIGITAL
OIL PRESS
FIGURE 99-4A
INSTRUMENT ADJUSTMENT LOCATIONS
urr;pl
sBa’ a,
b
AaKmLIDn
;p~b c~ 2
~DJUNEICIFWYUCUUI
I
FOR UUNIFOU) PRESS. a OIL PRESS ~ROU HERE
MJUSTUENIS UN BE UADE WITH )IOWLE IN PANEL C DESIRED
ADJ. TO UNI DID OR 2010
SIADJ.CYERSPANRA)IGE
a LH Na FROU HERE
PRESS.
ADJUSNENTS CAN 8E klp9E ~lm UODULE IN PANEL IF
AOJUSTLM#TS CAN BE UAOE ONLV WITH )r(ODULE OUT OF PANEL
DESIRED CLARESHIEL)
UUST
~SUFPICIEM
>IC
BE
UOMD
UP TO REACH
ADJUSTLIENT
HARNESS LENGTH IS AVAILABLE TO SUM UOWLE FROU PANEL TO *OJUST.
POINTS IF WODULE IS NOT TO BE SLID OUT
PROCEDURES FOR ARIUSTLAEM: SEE SECTION 28-*5-03, OIWTAL FOR INITIAL SETUP.
FUEL
VACWM
)rU~IFOLD
YE SECTION 57-21-05. DK;ITAL PRESSURE SEE SECTION 77-10-02, DIGIT~L.
OIL PRESSURE
SEE
SECTION 79-50-01, MCITK.
MORITZ CLUSTER GAUGE ADJUSTMENT LOCATIONS 39-11-01
4~99
FIGURE 39-48
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
TROUBLE SHOOT1NG GUIDE FOR CLUSTERS
PRESSURE INSTRUMENTS
CHECK FOR THESE POSSIBIUTIES
GAUGE CONDITION
Gauge reads full scale with engine shut down.
Wire between sender and gauge disconnected or open.
Faulty sender. Faulty Elauge´•
Gauge reads is running.
Wire between sender and gauge
grounded.
Faulty sender. Faulty gauge.
zero
when
engine
TEMPERATURE INSTRUMENTS Gauge reads full scale with engine cool or cold.
Gauge
reads
zero
when
engine
is hot.
Wire between sender and gauge
grounded.
Defective gauge. Defective senaer.
Wire between sender and gauge is open or d~connected.
Defective gauge. Defective sender.
FUEL SVSTEM
Gauge
CHECK FOR THESE POSSIBIUTIES
GAUGE CONDITION
indicates empty in the
tank.
Gauge
CHECK FOR THESE POSSIBIUTIES
GAUGE CONDITION
indicates past full when
Grounded wire between sender and gauge.
Defective sender.
Open sender lead.
Open sender (open resistance element). Sender not property grounded to
Inoperative gauge.
tank is less than full.
airframe. Gauge off calibration. Note: Some clusters are equipped with fuel gauges that have trim pots and may need re-calibration.
~atUup indifate~ 1R when tank
On dual sender systems, the
The lead between the isolated sender and the grounded sender is grounded. Either sender defective. Gauge off calibration. O/B float stuck on bottom of tank.
isolated sender may be
grounded.
381192
LANDING GEAR SWITCH
The landing gear switch is a two position switch located at the top right side of the flight instrument panel. The wheel shaped knob must be Pulled aft prior to raising or lowering the switch to activate the landing gear actuator. The
access
will require removal to gain to switch for maintenance action (refer to
Section
59-10-01).
1.
$’Up; b’i~r
glareshield
2. Remove the wire connections from the back of the gear switch.
shaped
1
I
landing
3. Turn the wheel from stem.
I
s
aNI
knob counterclockwise to
remove
4. Remove the nut and washer from the face of the switch and push switch through the panel.
es,
I
FIGURE 39-5 3411-03
LANDING GEAR SAFETY OVERRIDE SWITCH
The
landing gear safety override switch is located landing gear switch. Proper operation of the lending gear safety system will not allow the gear to
above the
retract below 65 +7/-4 KIAS.
CAUTION Activation of the gear safety override switch while the aircraft is on the ground may cause the
landing
LANDING GEAR SWITCH 3 LANDING GEAR SAFETY OVERRIDE SWITCH
gear to retract. 499
39-11-02
OLDWILLWAYNE
1. Disconnect wire connectors, appm~dmately 6 inches from the switch, by cutting dth wire cutters or opening the knife disconnects, 2. Loosen me nuton the stem and hold the nut located inside the mounting bracket. The red lens may need to be removedto fully removetheswlch from the panel and bracket.
bulb, OE 327 removed by
can
be
a
or
39-1292
AvIONIW/RADIO
PANEL
order by Mooney Aircraft end other installed by othersouroes as the owner desires.The maintenance informationcontained inthis Service and Maintenance Manual describes me
sales
equipment
Mooney factory
installation
only.
The avionics/radio components are removed installed according to Section 39-10-02, 1 and 2.
and disconnect me
CIRCUIT
CDIIIBRATION.
paragraph 4.
EMERGENCY LOCATOR
(U7)
8WITCH
The remote ELT switch is located at the top of me circuit breaker panel. The ELT is located in thetallcone and is accessible by removing the radio access pnel on the left side of the aircraft tuselage. The ELT antenna is located on top of the tailcone undemeath the fiberglass dorsal fin. The unit has a three position switch "ON" "DFF" end "ARM". The conect position of this swiich is "ARM’. The remote switch ia connected in parallel to the ELT circuit and will operate correctly either in the "ARM" mode or the’ON" mode. Normal operation is in the "ARM´• position. Place me remote switch in the ’ON" position and tune me communication radio to 121.5 Mhr to verify that a warbling tone is heard. Place the remote swirch back to ’ARM" position for normal operation.
Theavionics/radio panel contains equipment installed pr
glareshield
TRANSMITTER
The digital clock can be set by using the procedures included in the POH/AFM, SECTION VII, INSTRUMENT PANEL.
30-12-00
Remove the
LOW FUEL WARNING Refer to Seoticn 2433-00
CLOCK
381144
The annunciator panel is located at the top of me center-most avionics/radio panel and is not mounted with a slide in type chassis. Remove this component by removing the two screws holding cover platein
position.
replaced nail
-ANNUNCIATOR PANEL
3812-01
electrical hamess from back side of the unit. Remove the screws holding unit in place on the pnel and remove frorn the back side ofthe panel.
after me similar rod 3/32" diameter) and pushing me red lens on to the front of the panel. Lips a small vacuum tube puller or soft nosed instrument to pull the bulb from ihe sooket.
The
MOONEYAIRCRAFTCORPOW\TION
M20M
SERVICE AND MAINTENANCE MANUAL
and
ORIGINAL As Received
By
ATP
e
w
ja.
s--
s;,
1~
ELECTRICA4ELECTRONICS 39-11-04
EOUIPMENT RACK 400
a
FIGURE 39-6
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
bottom
CAUTION
2. If ELT unit is found to be operating properly and the system still will not work correctly through the remote ELT switch, repair or replacement of the switch or wiring will be required, access
glareshield
will
decrease
illumination.
The
cigar lighter is located at the bottom of the radio panel immediately to the right of the co-pilots control column shaft. It Is a standard cigar lighter similar to
The
to the remote switch and wiring removal (refer to section
automotive type.
require
39-2090
B. Remove the switch retaining nut and washer and push switch through face of panel. Disconnect wires, remove and replace defective switch.
-ELECTR ICAUELECTRONIC EQUIPMENT RACK
The electnâ&#x20AC;&#x2122;cal equipment rack for the M20M aircraft iE located in the tailcone just aft of the baggage compartment bulkhead. Access is gained through the access door in the tailcone aft of the left wing edge. The batteries, auxiliary powerplug receptacle (if installed), and the various avionics black boxes are mounted on the electrical equipment rack. (See Figure 396) The ELT is mounted on an accessory rack further aft in the tailcone.
C. Reconnect wires and test switch for proper
operation.
glareshield.
NOTE Other switches located on avionrcs panel can be removed and replaced in similar manner, 3912-03
to
CIGAR LIGHTER
3812-04
39-10-01).
D. Reinstall
switch
Test malfunction of either switch with a multi-meter and replace as needed. Replace control box if ON control light malfunctioning. S/N 27-0108 intensity with two rheostat type switches. Rotate eit~er switch to obtain desired light intensity.
1. If the warbling tone is not heard replacement of the ELT battery or the unit may be necessary. Follow ELT manufactures instructions for battery replacement.
A. To gain
of
dimming function takes place in a control box located in the tailcone on aft cabin bulkhead.
of ELT should be conducted only during the first five (5) minutes after any hour and no longer than three (3) audible sweeps.
Testing
the
SERVICE AND MAINTENANCE MANUAL
M20M
INSTRUMENT/RADIO LIGHT GLARESHIELD DLMMER CONTROL
The dimmer controls for the instrument, radio and ~lareshield lights consists of two switches located on the lower portion of the avionics/radio panel on S/N 27-0001 thru 27-0107. Push the top of the switch to increase illumination of either lighi group and push
39-21-00
-MISCELLANEOUS MAINTENANCE
39-2191
-ELECTRIC TRIM SYSTEM
See Section 27-42-00 for
4-99
special
maintenance.
3912-03
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
39-21-01 10
499
MOONN AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
STANDARD PRACTI CES-
STRUCTURES
OLDWILLWAYNE MOONP/ AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 51 STRUCTURES
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
51-00-00
51-10-00 51-10-01
51-11-00 51-12-00
PAGE
SUBJECT
General Structural
5
Repair: General
5
Replacement
Fastener
5 7
Reserved
7
Fuselage
51-12-01
Tubular Structure
51-12-02
Tdhone
7
Repair
Repairs Gear 8 Retraction
system depair
51-13-07
Landing Flight Control System Repair. m,g Repair StringerRepair Main Spar Repair. Stub Spar Repair. Rear Spar Repair. Rib Repair Wing Tip Repair Wing Skin Panel Repair
51-14-00
Horizontal Stabilizer
51-12-03 51-12-04 51-13-00 51-13-01. 51-13-02 51-13-03 51-13-04 51-13-05
51-13-06
51-14-01
51-14-02 51-14-03 51-14-04
51-15-00
Vertical Fin
11
11 13 14
14 14 14
Repair.
Repair Leading Edge Spar Repair Outboard of STA.
16 16
9.00
16
Repair Remating Horizontal Stabilizer to Stinger Fiberglass Laminates, Repair Procedures
18
Rib
51-15-02
Non-Structural
51-15-03
Common Structural Laminate
Repair
(Metallnsert)
51-16-00
11
Main
Cracks, In Surface Areas.
51-15-05
10 11
Skin
51-15-01
51-15-04
10
Common Structural Laminate
Fiberglass Miscellaneous
REV. 4- 99
Delamination
18 18 19
Repair’ Rebair’
Repair.
19 20 21 22
22
51 ICONTENTS 3/4B LANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 51
STRUCTURES
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SU&IECT.
PAGE
DATE
1/2BLANK 3/4BLANK
4-99
51-00-00.
5.
4-99
51-10-01.
6.
4-99
51-11-00.
7.
4’99
51-12-01.
8.
4.99
51-Effectivity 51-Contents.
4-99
9´•
4’99
51-12-02
10
4-99
51-12-04
11
4-99
51-13-02
12
4-99
51-13-03
13
4-99
51-13-04
14
4-99
51-13-07
15
4-99
51-14-00
16
4-99
51-14-02
17
4-99
51-14-03
18
4-99
51-15-01
19
4-99
51-15-03
20
4-99
51-15-04
21
4-99
51-15-05
22
4-99
51-12-01.
S1/EFFECTIVITY IRBLANK REV. 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 51-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
the rear spat on both sides. The rudder is constructed of formed aluminum skins fastened to a spat extrusion at the leading edge and riveted together at the trailing edge.
GENERAL
The Mooney M20M is an all metal, low wing airplane. The fuselage cabin area is constructed ofa welded 4130 chrome-molybdenum steel tubular structure. The
the to
steel tubular structure is covered with non-structural aluminum skins fastened to the tubular structure by rivets, bolts and screws.
A three piece composite belly skin underside of the aircraft from the exhaust the tailcone.
The tailcone is of semi-monocoque type construction and is fastened to the tubular structure with structural bolts.
The front seats are installed on rails which are attached to the floorboard and structure beneath the Roorboard.
The wing is a tapered, laminar flow, one piece wing. It is constructed with a one piece, full length main spat. The spar is constructed from tapered cap strips (7075 aluminum) bolted (huck bolts) to webs (2024 aluminum). Aluminum ribs connect the main spar to the aft stub spat and the rear spat. Extruded stringers run the full length of the wing, spaced chordwise for strength and skin reinforcement. The skins are stretch formed, wrap around, 2024-T3 aluminum ranging in thickness from .025 at the tip to .050 at the fuel tanks.
The M20M has a split type rear seat, using seat cushions in molded wells over the wing spats and individually reclining rear seat backs. 51-10-00
The PRODUCT SUPPORT DEPARTMENT, Aircraft Corporation, Kenville, Texas, should be consulted for special repair procedures when repair status.
The empennage is of similar construction to the wing. A main spar spans the length of the stabilizer. Ribs connect the main spar to the stub and rear spat. A stretch formed skin wraps around the leading edge ribs and attaches to the rear spat on top and bottom. The elevators are constructed of formed aluminum skins fastened to a spat extrusion at the leading edge and riveted together at the trailing edge. The vertical stabilizer is constructed around a fabricated main spar assembly with ribs connecting the main and rear spat. A stretch formed, aluminum skin wraps around the leading edge ribs and is riveted to
R3001-T6 2L426H-T5
R3007-T6
GENERAL
specific to Mooney airplanes. All structural repair must be: in compliance with AC unless specific Mooneyfactory repairs 43.13-1( arerecommended, or with the specific approval of a Federal Aviation Administration representative which is the final authority in all repairs. This manual is for general guidance and has no authorized approval
transportation.
2LPH-T5
cavity aft
This section outlines structural repair procedures for the M20M airplane. It is intended to supplement FAA by showing repair methods Advisory AC 43.13-1(
The completed wing assembly is mated to the fuselage tubular structure during final assembly at the Mooney facility. Removal of the wing from the fuselage structure is essential for most over land type
ALPPH-TG
STRUCTURAL REPAIR
covers
Mooney
of damaged structure is not covered instructions. 51-10-01
by published
FASTENER REPLACEMENT
1. HUCKBOLT INSTALLATION. The Huck Lockbolt an interference fit fastener used in a rigid joint structure. A loose or slip fit Huckbolt is unacceptable. The recommended limits for Huckbolt holes are:
is
(.147 IN.) (.1695 IN.) No. 18 (.1695 IN.) No. 26 (.147 IN.) 3/16 (.187 IN.) No. 26
No. 18
No. 20
.161 to .1635 IN.
No. 13
.185 to .187 IN.
(.161 IN.) (.185 IN.) No. 13 (.185 IN.) No. 20 (.161 IN.) No. 7 (.201 IN.)
.185 to .187 IN. .161 to .1635 IN.
.2005 to .2025 IN
Corporation, Kerrville, Texas, for factory recommendations when the preceding instructions are inadequate to accomplish the repair.
Aircraft,
When the Huckbolt is enlarged beyond the above limits but is straight and round, the hole may be considered acceptable, provided that the Huckbolt cannot be pressed into the hole, with normal hand pressure, to a depth more than 50 percent of the heaviest material being secured. Check enlarged hole size at both ends. Select Huckbolts to fit the oversize holes.
T, compensate for material thickness tolerances, Huckbolt length may be increased by one dash number from the prescribed length. When aFluckboR pin of the proper length is not available, use a pin of the next
lo"ger length.
Oversize Huckbolt holes may be repaired by replacing 2LPH-T5 Huckbolts with ALPPH-TG Huckbolts or with NAS 623-2 screws and NAS 1021 No. 8 Hex-lock nuts (or equivalent), provided the pitch distance is greater than .56 inches and the edge distance is greater than .33 inches. Huckbolts ALPPH-TG and R3001-T6 may be replaced with R3007-T6 Huckbolts as necessary. Consult the Product Support Department, Mooney 4-99
51-00-00
OLDWILLWAYNE MOONN AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
percent of the fasteners in any pattern,
To adjust the grip length, install a cadmium-plated steel washer .065 inch thick (or a combination of not more than two washers .065 inch and .032 inch thick) under the Huckbolt collar. The combined thickness of any two washers shall not exceed .098 inch. Huckbolts or conical Keystone Lock blind rivet heads may be cocked no more than .004 inch. Not more than 20
Where
NAS 1465
HL20-5 Pin
or.
NAS 1466
HL20-6 Pin
or
NAS 1475
HL19-5 Pin
or.
Pin-Protruding Tension 160 KSI Ftu
(Hi-Shear)
Pin-Protruding Tension 160 KSI Ftu
Pin-100 D. Flush 95 KSI Fsu
(Hi-Shear)
HL94-5 Collar
R3014-T5 NAS 1476
(Hi-Shear)
HL86-6 Collar
R3001-T6
HL19-6 Pin
or.
Shear
Pin-100 D. Flush 95 KSI Fsu
(Hi-Shear)
Shear
HL94-6 Collar
R3014-T6
NOTE is limited or for the following substitution is
access
DESCRIPT1ON
HL86-5 Collar.
R3001-T5
NOTE HL2086-x-x and HL~99ex-x are P/Nâ&#x20AC;&#x2122;s which include pins and collars. Customer must diameter and grip data when ordering.
5
i
I
edge
8
I I
I 1
Gripinl/lBths" (8/18=.500)MAX (5/32 .156)
Nominal Dia. in 1132nds" Pin Part Number
(4) Dimpled Joint. If the edge distance is a minimum of two times the diameter of the original rivet, it will be permissible to drill for and install the next standard size larger diameter rivet of the same type and material as the original rivet. Do not redimple. After installation, mill the excess head height Rush with the surface. This method is subject to the same limitations as paragraph 2, A (3).
2. RIVET REMOVAL AND REPLACEMENT. A. REPLACEMENT-STANDARD SIZE RIVETS, HOLE OVERSIZE. This repair applies only to original aluminum alloy, steel, or monel rivets of 1/16, 3/32, 1/8, and 5/32 inch diameters. Such rivets may be replaced as noted and limited below and in the General Limitations, when the hole only is oversize.
B. REPLACEMENT-STANDARD SIZE RIVETS, HOLE AND COUNTERSINK OR DIMPLE OVERSIZE. This repair applies only to original countersunk head aluminum alloy rivets of 1/16, 3/32, 1/8, and 5/32 inch diameters. Such rivets may be replaced las noted and limited below) when the hole and countersink or dimple is oversize.
Head Joint. If the edge distance is a minimum of two times the diameter of the original rivet, it will be permissible to drill for and install the next standard size larger diameter rivet of the same type and material as the original rivet.
(1) Protruding
Machine Countersink Joint, Method I. If the distance is a minimum of two times the diameter of the next standard size larger diameter rivet and the sheet thicknesses involved are within the limits specified for machine countersinking for the next be it will standard size larger diameter rivet, permissible to drill and countersink for and install the next size rivet of the same type and material as the original rivet. The following are limits for machine
(2)
edge
(1) Machine Countersink Joint. If the edge distance is a minimum of two times the diameter of the next standard size larger diameter rivet and the countersink depth is not beyond the thickness of the countersunk sheet, it will be permissible to rework according to paragraph 2, A (3).
(2) Dimpled Joint. If the edge distance is a minimum of two times the diameter of the next standard size diameter rivet and all the parts are dimpled, it will be permissible to rework the smaller dimples to a
countersinking: RIVET SIZE
3/32 1/8 5/32 51-10-01
supply
(3) Machine Countersink Joint, Method II. If the distance is a minimum of two times the diameter of the original rivet, it will be permissible to drill for and install the next standard size larger diameter rivet of the same type and material as the original rivet. Donot â&#x20AC;&#x2122;e"achine the countersink. After installation, mill the excess head height flush with the surface.
PART NUMBER CODE
HL20
than
replacement/repair permissible.
P/N (VENDOR)
P/N.
nor more
three fasteners in succession, may be cocked.
MIN. GAUGE .025
,032 .040 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
size to match the oversize dimple and install the next standard size larger diameter rivet of the same type and material as the original rivet. Dimples in 75S-T6 must be hot formed when reworked.
(3) Combined Countersink and Dimpled Joint. If the edge distance is a minimum of two times the diameter of the next standard size larger diameter rivet, it will be permissible to rework the smaller countersink or dimple to a size to match the oversize dimple or countersink and install the next standard size larger rivet according to paragraph 2, A (4). Dimples in 75S-T6 must be hot formed when reworked. C. RIVET HEAD TOLERANCE.
or
or
AN426AD3 AN426AD4
#40 #30
D. RIVET HOLE TOLERANCE.
(1) An enlarged hole is defined as having an intemal diametric dimension in any direction which exceeds the sum of the drill diameter normally used plus ten percent of the diameter of the rivet shank. (2) The following table specifies the maximum acceptable diametric dimensions for the various rivet sizes that occur in multiple layer assemblies which are "drilled on assembly". DIAMETRIC DIMENSION .108 in. .141 in.
(.098 dia.) (.1285 dia.)
6. SPOT WELD REPAIR
(3) When a hole becomes enlarged beyond the acceptble diametric limit and the prescribed rivet cannot be used, the next larger diameter rivet may be used if (a) four-diameter (4D) rivet spacing is maintained and if (b) two-diameter (2D) edge distance is maintained. 3. BLIND RIVET INSTALLATION. Ordinarily, where rivet bucking is impossible, CherryLock (CR-2248 and CR-2249) ri~vets may be substituted for AD rivets to repair skins and structural members. However, consult the MAC Customer Support Department or a representative of the Federal Aviation Administration before using blind-type or hollow rivets in primary
or MS20426-AD4 rivets may replace double flush spotwelds, (1) per spotweld, head side function of requirements determined by form, fit assembly. Contact Mooney engineering department prior to beginning repair.
MS20470-AD4
51â&#x20AC;&#x2122;11-00
-RESERVED FUSELAGE REPAIR
51-12-00 51-12-01
-TUBULAR STRUCTURE REPAIR
Check tubular structure annually for corrosion and damage. Interior panels may require removal to gain access to areas which are difficult to inspect.
structure.
CAUTION of blind rivets normally require more frequent inspection of the area where used. Inspect for evidence of loosening of the rivet(s) or crack development that may cause deterioriation of structural integrity. Solid rivet replacement of blind rivets is recommended at earliest possible maintenance.
The
(1) A rivet head will be considered open if .001 feeler gauge can be inserted between the head of the Rush or protruding head rivet and the top skin. The top of a flush head rivet must not be below the skin in which it is installed by a dimension of more than .004.
MAX. ACCEPTABLE DRILL SIZE
NOMINAL RIVET SIZE AN470AD3 AN470AD4
SERVICE AND MAINTENANCE MANUAL
M20M
use
for tubular frame repair Refer to AC 43.13-1( Pâ&#x20AC;&#x2122;ocedures. Warped or bent tube members can often be straightened; however, ail surrounding welds should be dye checked for cracks after tube straightening. Use proper material when making weld repairs. Welding rod, meeting the requirement of specification MlL-R-5632, class 2, is recommended for oxyacetylene welding. Electrodes meeting the requirement of specification MIL-R-5632-A, class 2, MIL-E-23765/1C or AWS A5.18-69, class E70S-2 (IE. 65, Linde 32 or Page AS-35) are for non-heat treated parts, inert-gas shielded-are welding (Heliarc). Use AISI 4130 condition N steel for replacement and repair of tubes, and for making repair sleeves. Replacing a member or subassembly is often advantageous and more feasible than repair. All detail
Check existing rivet hole size before installing blind rivets. When hole is marginal, use the next larger size rivet to assure firm attachment. AND WASHER NUT "AN"4. BOLT, INSTALLATION. To compensate for material thickness tolerances, the length of AN bolts may be increased or decreased by one dash number from prescribed length. AN960 regular washers and AN960L thin washers may be used interchangeably for proper bolt and nut installation.
)2-S07-LIMdednemmocer
L~ee
tubes
One regular washer or one thin washer may be added to any bolt installation. Washers may be used under the bolthead and/or under the nut. AN365 and AN363 nuts may be used interchangeably. The AN363 nut is acceptable for higher operating temperature installations.
or
assemblies needed for replacement
can
be
purchased from SERVICE PARTS DEPARTMENT, Mooney Aircraft Corporation, Louis Schreiner Field, Kerrville, Texas 78028. 1. WELDED PATCH REPAIR OF LOCAL DAMAGE. Use a welded patch to repair dents, small holes, and cracks no longer than the outside diameter of the tube and covering a maximum of 1/4 of the tube
5. HI-SMEAR RIVET INSTALLATION. When a hi-shear rivet pin of the prescribed length is not available, the next longer length pin may be used with cadmium-plated steel washers to adjust the pin grip length. The combined washer thickness shall not exceed .096 inch.
circumference.
4-99
51-11-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
Drill out the crack, smooth the hole edges, weld the hole or dent, and file the repaired surface smooth. Form a patch that will cover twice the diameter of the tube around the edge of the damaged area and twice the circumferential area of damage as shown in
(Figure 51-1).
Weld
patch
in
´•MOONC/ AIRCRAFT CORPORATION
M20M
2. INNER SLEEVE SPLICING. Use an inner sleeve to partially replace a tube without increasing the
splice
outside diameter
(see Figure 51-2). 30-degree cut to remove
the damaged A. Make a portion of the tube; then, remove the burr from the remaining end. B. Cut a replacement tube of the same material (AISI 4130 steel, condition N), same diameter and the same wall thickness as the original tube.
place,
IF
OF TUBE CIRCUM, (MAX,>
NOT
GREATER
THAN
"A"
(DTAM,
OF
TUBE:,
1/4
2A
I,
Y
,I,
2A
,I,
I DAMAGE
WELDED PATCH -LOCAL DAMAGE REPAIR
II
;I
FIGURE 51-1
A
I
r
300
1
I --~-yrp
--r
Al
X
ORIGINAL TUBE
I SLEEVE REPAIR TUBE INSIDE
xC~
I
A L
--I--
ROSETTE WELD
C
1/2A
REPLACEMENT TUBE
LEAVE 1/8 IN, CAP FOR WELDING ROSETTE WELD
300
r SLEEVE REPAIR TUBE INSIDE
1/2A
1/2A 5A
INNER SLEEVE SPLICING 51-12-01
4-99
FIGURE 51-2
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
F. Install replacement tube over the inner sleeve allowing a 1/8inch gap for welding between the original and replacement tubes. G. Weld the inner sleeve to the tube stubs through
C. Select a tube with an outer diameter equal to the inner diameter of the tube to be repaired and with the same wall thickness, D. Cut tube to a lenath five times the outer diameter of the tube to be spj~ced.
the 1/8 inch gap,
forming
an
overlayed
bead
across
the
Sap´•
E. Install inner sleeve in tube to be repaired so that its outer end is one and one-half of the original tube diameter from the nearest end of the diagonalcut; secure in position with a rosette weld on each side at the one-half original tube diameter from the inner-sleeve end,
H. Rosette weld the replacement tube to the inner sleeve in two or more places. 3. SPLIT-SLEEVE SPLICING. Use the split-sleeve to repair a damaged tube when the parts on arated to each side of the damage cannot be sep insert an inner sleeve (see Figure 51-3).
splice
WELD HERE FIRST 4
ROSETTE WELDS
A
t´•´•´•M 1-1/2A
1/2C\
i-1/2A
SPLIT-SLEEVE SPLICE
B. Cut C tube at a 30 degree f’om bottom of tension fitting.
split sleeve from the same material 4130 steel, condition N) with at least the same gauge as the original tube. C. Form the
inches
E. Make an inner sleeve five inches long from 4130 steel tube, condition N, with outside diameter to match inside diameter of tube C and with a .085 inch wall thickness.
1/8 inch gap between sleeve halves for
welding. tube
through 1/8
F. Insert the inner sleeve in C tube and weld in as shown (Figure 51-4).
place
F. Weld center of each sleeve half to original tube with two rosette welds spaced one original tube diameter apart. 4. TENSION FITTING REPLACEMENT
seven
D. Drill four 114 inch holes for rosette welds 1.9 inches from center of 30 degree cut.
(AISI
original
angle
C. Cut a replacement C tube at a 30 degree angle and at an appropriate length to position the tension fitting. Weld tension fitting in proper position.
more.
E. Weld parallel edges of sleeve to inch gaps.
fitting
340034-7, -8 at welds.
B. Form the split sleeve from sheet steel when outside diameter of the original tube is one inch or
a
FIGURE 51-3 A. Cut A and B tubes loose from tension
A. Form the split sleeve from steel tube or sheet steel when outside diameter of original tube is less than one inch.
D. Allow
1/8 IN, CAP FOR WELDING
300
REPAIRS FOR WELDED ASSEMBLIES 5. General. This section does not apply to any control
system tubing
(see Figure
or
assemblies, engine mounts
treated steel components
(except
as
stated
or
heat
below).
51-4). 4-99
51-12-01
OLDWILLWAYNE MOONPI AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
TUBEJ
TUBE ,125
IN,
WELD GAP
A~
I B
UBE
300
YC~mh
Q
IC
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I SLEEVE TUBE INSIDE
2
340034-7
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TENSION FITTING REPLACEMENT A. Small holes up to a #20 drill may be closed inert gas shielded are method. are no
longer than
depth after cleanup may be smoothed out and reprimed. Nicks, holes, and cracks that will clean up with a #20 drill may be drilled and repaired per item A. C.
The
repair of weld beads
may be accomplished treatment within the following limits.
1/3 of total
length
3.
heat-treated without reheat
on
(2) Only one repair
The
skin
structure is
LANDING GEAR 3 RETACTION SYSTEM REPAIR
51-12-03
Replace
any
damaged landing gear
or
retraction
system component with a new part. Repairing landing retraction system components is not gear or recommended. After installing new components, check
-TAILCONE REPAIRS
1. LONGERON SPLICING. Use
procedure outlined for repairing and splicing tailcone 43.13-1( longerons. (Figure 51-5) shows acceptable methods for splicing longerons. Consult AC 43.13-1(A), Figures 2.28, 2.29 and 2.30 for fastener requirements. in AC
2. TAILCONE STRUCTURAL SKIN REPAIR. Repair minor tailcone skin damage as shown in AC 43.13-1(A), 4-99 51-12-02 10
REPAIR.
not restricted as to size or shape; however, appearance and possible vibration damage should be considered. Either a flush patch, a plate patch, or a plug patch may be used.
percent of the diameter of the tube in depth and are no longer than one-half the tube diameter are acceptable. 51-12-02
NONSTRUCTURAL SKIN
considered nonstructural. Patches in nonstructural skin
per weld bead is allowed.
7. DENTS. Small dents which do not exceed five
same as
are
will not exceed .375 in length of weld, whichever is the lesser.
6. REPAIR OF SPOT WELDS. Failed spot welds on aluminum may be repaired by installing an AD470-4 rivet through the weld if the damaged area will clean up with a #30 drill,
2.24. The rivet
covering the M20M aircraft tubular fuselage
(1) The repair bead or
FIGURE 51-4
shall be the
1/8" and do not exceed four percent of wall thickness i?
assemblies
F~ITTING
pattern for stressed skin repairs the rivet pattern in the skin joint immediately forward of the damaged area. Replace severely damaged structural skin panels. Install new skin panels to exactly match the original skin installation.
Figure
by
welding with the
B. Nicks and drill marks that
TENSION
gear and retraction system rigging as outlined in Section 32-20-02. Befbre returning the aircraft to service, perform a retraction test and operational check of the landing gear and retraction system per Section 32-30-01.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
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LONGERON SPLICING
51-12-04
51-13-02
FLIGHT CONTROL SYSTEM REPAIR
and rigging as outlined in Chapter 27 Before retuming the aircraft to service, flight test the aircraft for proper control system rigging, WING REPAIR
51-13-01
STRINGER REPAIR
MAIN SPAR REPAIR
The spar caps inboard of STA 103 are made of 7075-T6 high-strength aluminum. Replacement of the spar cap is preferable to repair. However, if a spar cap ’epair is thought necessary, an exact description of the damage showing location and extent should be sent to the PRODUCT SUPPORT DEPARTMENT, Mooney to obtain Ai’c’aft factory Corporation,
Replace any damaged primary control system component with a new part. Repairing primary control system components is not recommended. Use only hardware when installing new parts. After new installation of new parts, check control system travel
51-13-00
FIGURE 51-5
recommendations
prior to beginning the repair.
1. SPAR CAP REPLACEMENT. To replace a spar cap, remove the skin covering the area to be repaired. Before removing a large area of wing skin, attach temporary jigs or holding fixtures to the wing to prevent wing warpage. When attaching a new spar cap, assure proper interference fit of the replaced huckbolts. During installation of the new spar cap, all holes damaged by improper drilling or reaming should be reamed to the huckbolt for oversize recommended hole size installation. When installing oversize huckbolts, consult the Huck Fastener Standards Manual for proper tolerances. Use proper length huckbolts. If the bolt is too long, the collar will not swage properly; if the bolt is too short, the shank will not completely fill the hole.
Stringer splicing may require drilling new holes and adding rivets between existing rivets to obtain the required total number of rivets. Add extra rivets where the distance between existing rivets is the greatest. The pitch and edge distance must conform to AC 43.13-1() requirements (see Figure 516 below).
4-99
51-12-04
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
,750
.750
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MOOND/ AIRCRAFT CORPORATION
M20M
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FIGURE 51-6
SPLICE ANGLE MATERIALI 7075-T6 .875
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SMM51-7
SPAR CAP REPAIR
51-13-02 12
4-99
FIGURE 51-7
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
Repair scratches on spar caps that are not deeper than .003 inch by sanding with No. 400 abrasive paper. Remove no more than .005 inch of material. Inspect the sanded area; use dye penetrant to be sure that the scratch is completely removed. Clean and prime area where the protective coating has been removed. 2. SPAR CAP REPAIR. Spar caps outboard of STA 103 consist of sheet metal angles backed up with
RIVET CODES FOR REPAIRS
m4
MS20470AD4-xx
4~ 5
MSE10470AD5-xx
~P 4
aluminum extrusions from STA 103 to near STA 150. Replace or repair damaged extrusions. Do not allow splices in a repaired extrusion to coincide with a spar-web splice when avoidable. Splice sheet-metal angles with an extrusion of equal area, picking up existing fasteners. Add extra fasteners to bring the minimum number of fasteners to six AD-5 rivets per side in the vertical flange, and nine AD-4 (or six AD-5) rivets per side in the horizontal flange. (See Figure
~7 5
MS204;1~AD5-xx
~BP
CR516-xx
3´• SPAR WEB REPAIR. Repair all damage to spar webs in accordance with AC 43.13-( If there is extensive damage to a web that cannot be repaired as outlined in AC 43.13-( consult Mooney Aircraft
51-7).
Corporation, PRODUCT SUPPORT DEPARTMENT giving exact location and extent of damage. STUB SPAR REPAIR
51-13-03
(Stub spar splice at wing STA 34.5 3.0) (849 Figure 51-8). 1. Cut the stub spar halfway between existing rivets as required by the damage incurred.
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SIDE
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4-99
SPLICE
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CENTERLINE
I
SM51--B
FIGURE 51-8
51-13-03 13
OLDWILLWAYNE SERVICE AND
UAL
2. Smooth all to be spliced.
rough
or
sharp edges, and prime
3. Locate new outboard section and trim a maximum gap of .020 inch.
MOONEY AIRCRAFT CORPORATION
M20M
splice
area
to fit
with
o
4. Fabricate -501 angles to pick up 30 existing fastener holes (30 recommended, but 22 minimum), -503 angles to pick up 15 existing fastener holes (12 minimum), and -505 plate and-507 spacer. Figure 518). Prime angles, plate, and spacer. parts together using wet primer on all rivets.
RMTS
REAR SPAR REPAIR
51-13-04
The rear spar may be spliced between ribs accordance with AC 43.13-1( (see Figure 51-9).
in REPAIR rLARa
Ear a REAR PIECE
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RIB REPAIR
FIGURE 51-10
4. Rivet skin to rib at STA 193.5. 000
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0
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0
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5. Roll skin back on lower wing surface to gain to stringers for rivet bucking. Rivet skin to
access
upper
0000000000
Replace damage
51-13-07
FIGURE 51-9
ribs that are may be repaired
severely damaged. Minor shown (Figure 51-10).
as
To repair severe damage to the wing tip outboard of STA 193.5, it is advisable to replace the entire tip skin and rib. 1. Locate the new fip rib in the exact original tip rib position to prevent wing tip twisting. Use a temporary support or locator pins to maintain correct wing tip position. 2. Rivet
new
tip
rib to main and
rear
spars.
3. Locate new skin, and drill rivet holes through skin to match existing holes in ribs and stringers. 51-13-04 14
places extra
pair of
WING SKIN PANEL REPAIR
1. Damaged Dimple Repair Around Inspection Holes. Repair damaged dimples around inspection holes when (a) there are three or more cracked adjacent dimples, (b) the crack in one or more of the dimples extends beyond the radius of the dimple into the skin, a"d (c) when there are four or more cracked dimples around an inspection hole (see Figure 51-11).
WING TIP REPAIR
51-13-06
Buck
Repair wing skin panels as prescribed in AC 43.13-1( unless an entire skin panel is to be replaced. Install new skin panels to exactly match the original skin installation. Preformed skin panels may be obtained from the Mooney Service and Marketing Centers.
RIB REPAIR
51-13-05
leading edge.
7. Install cherrylock (CR-2248) blind rivets in inaccessable for rivet bucking. Add one countersunk blind rivet between every other cherrylock rivets.
rAo
REAR SPAR REPAIR
stringers.
6. Rivet skin to tip rib starting at rivets as far back as possible.
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
r
PI_I
7.5
e
EQUALLY SPACED RIVETS
d
e
TYPICAL~IL
I
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1
126
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ACCESS COVER REPAIR To
doubler from the repair damaged dimples (a) same material and gauge as the skin to be repaired, (b) drill and countersink 100-degree fastener holes in the doubler to match dimpled fastener holes in skin, and (cj install doubler around inspection hole. Use AN426-AD4 rivets when material is .040 inch thick or greater. Drill holes using a No. 30 (.123 IN.) drill as shown in the above illustration. Use AN426-AD3 rivets when material is .032 inch thick or less. Drill holes using a No. 40 (.098 IN.) drill. 2.
cut
Repair
of Cracks
Wholly
FIGURE 51-11 E. Prime
a
Within
MISTING
CRACKED DIMPLE
I I j I I j I I I i
II
Maintain four-diameter and (4D) spacing two-diameter(2D) edge distances. When original rivet pattern has rivets on only one or two sides of a dimple, only one or two rivets need be added (see Figure 51-12).
RIB STRINGER
I I I I -I
I I I I I I
~--´•oo MISnNG
~7P
Lcc~
U
1
SM51-12
drill crack with No. 60 bit. DIMPLE CRACKS REPAIR
B. Cut a doubler from the same material as the skin to be repaired. Allow for six rivets at iour-diameter rivet spacings with two-diameter edge distances in circular pattern around the cracked dimple.
D. Drill holes for six rivets (same size as those original rivet pattern), through doubler and area be repaired. Dimple 100 degree dimples in doubler,
FIGURE 51-12
4. Repair of Circumferentially Cracked Dimples. Circumferentially cracked dimples (dimples with cracks
a
that appear
as an
annular mark around the dimple)
can
be’epaired by installing a conical washer. A. Drill through dimple using a drill large enough to ’emove the damaged area. B. Install doubler as shown in Figure 51-14. Wet prime prior to assembly.
C. Round the comers of the doubler, and scarf the sandwiched edges to about .010 inch by .250 inch. the
and install doubler
I
I I I I 1 I
Dimple Radius.
out the crack. Cracks in dimples which do not extend beyond the dimple radius can be repaired by (a) stop drilling the crack with a No. 60 drill and (b) by adding rivets, the same size as those in the original pattem, to each side of the cracked dimple.
Stop
I I
~TB
repaired by sanding
A.
repaired
h?---~t
Surface cmd(s on inside (bearing) face of a dimple that do not extend through the material can be
3. Repair of Cracks Extending Beyond Dimple Radius. Cracks that extend through the face of the dimple into the surrounding skin can be repaired as follows: (see Figure 51-13).
to be
area
with wet primer.
in to
4-99
51-13-07
15
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
leading edge and close the access installing inspection cover P/N 913000-501.
stabilizer (SAME SIZE AS ORIGINAL FASTENER WITHâ&#x20AC;&#x2DC; CRACKED DIMPLE) 6 FASTENERS
hole
MAIN SPAR REPAIR OUTEOARD OF STA. 9.00
51-14-02
horizontal stabilizer main spar area and inspecting carefully forcracks. If cracks are formed, stop drill remove cracked area.
Repair damage to the
by it
straightening the damaged
a
a
by
a
or
Repair damage between STA 9.00 and STA 34.0 the spar upper flange, and between STA 9.00 and STA 40.0 on the spar lower flange with a splice angle formed from .070 AISI 4130 steel, condition N. The splice angle flanges must be as wide as the original spar flanges. The splice angle must be long enough to install 11 AD4 rivets through the skin and 11 rivets through the spar web on each side of the damaged 1.
a
on
a
a
oouelrR (SAME GAUGE AS SKIN)--SCARF EDGES TO APPROX..010 IN. DEEP AND .25 IN. WIDE; ROUND
DIMPLE
area
DIMPLE CRACKS
FIGURE 51-13
C. Countersink dimple hole in skin countersink to extend into substructure.
allowing
(see Figure 51-15).
Prime splice angle before riveting it to spar. Pick up five existing rivet holes and drill six new holes between existing rivet holes in the skin at each side of the damaged area. Install 22 AD4 rivets through splice angle and skin, and 22 AD4 rivets through splice angle and spar web. (See Figure 51-15).
SM51-13
the
2. Repair main spar cap damage between STA 34 and STA 48.5 by forming a splice angle from 3/4 inch by 3/4 inch .0502024-T3 sheet aluminum. Pick up five existing holes and drill six new rivet holes between
D. Install conical washer, use next oversize rivet size. Wet prime washer and adjacent skin and doubler surfaces prior to assembly. E. Drill remainder of the hole to allow installation of next larger diameter rivet than the rivets in the original
pattern. r.050
.070
100"
WET PRIMER
CONICAL WASHER
.75
SAUE LENCm AS ANGLE BaNG SWCOD
C
1 SKIN DOUBLER SPAR REPAIR
SUBSTRUCTURE
51-1 4-00
3. Repair main spar damage from STA 48.5 outboard by installing splice angles made from .040 2024-T3 material on both side Zrf web using 12 AD4 rivets (6 through skin and 6 through we6 on each side of damaged area).
FIGURE 51-14
HORIZONTAL STABILIZER 3
LEADING EDGE SKIN REPAIR
The horizontal stabilizer and vertical fin leading edge interiors are inaccessable near the tailcone. To repair damage in these areas, cut a standard (3.0 inches by 6.5 inches) access hole in the lower side of the
51-14-00 16
FIGURE 51-15
holes in the skin on each side of damaged Install 11 AD4 rivets through angle and skin and 10 AD4 rivets through angle and web on each side of the damaged area. (See Figure 51-15).
VERTICAL FIN REPAIR 51-14-01
OUTED.)
area.
SM51-14
OVERSIZE HOLE
9.0
existing
NEXT OVERSIZE RIVFT
SCARF EDGES
(STA.
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
Pick up three existing holes and drill three new holes between existing holes on each side of damaged area.
splice angle and web on each side of the damaged web area. The damaged web should be stop drilled or cracked area removed prior to splice angle installation. P’ime splice angle and deburr spar web and Range beiore installing splice (see Figure 51-17).
(See Figure 51-16). 4. Repair main spar web damage outboard of STA 34.0, top Range, and STA 48.5, lower Range by forming a splice angle from .050 2024-73 aluminum. The splice angle web flange should be cut to allow sufficient coverage of the damaged area of existing web and long enough to install 6 AD4 rivets on the Range on each side of the damaged area. Pick up 3 existing rivet holes on Range of spar and drill 3 new rivet holes between existing holes. Drill 10 rivet holes through
5. Spar webs outboard of STA 48.5 cracked more than 50% of the web height may be repaired (see Figure 51-18). Form a splice plate from .050 2024-73 aluminum to fit the inside dimensions of the web and Range at the damaged area. Pick up 3 existing rivet holes on top and bottom Range on each side of damaged area and drill 2 new AD4 rivet holes between
(4 MIN~ PER SIDE)
<3 MIN, PER SIDE)
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0
0
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SM51-16
SPAR REPAIR
~cp’ (10
EACH
(STA.
48.5
APPROX.)
SIDE OF
CRACK)
(6~
FIGURE 51-16
EACH SIDE OF
CRACK)
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STOP-DRILL (OR REMOVE CRACKED SPAR WEB AREA)
.050 2O24-T3 SM51-17
SPAR REPAIR
(OUTBD.
of STA.
4-99
34.0)
FIGURE 51-17
51-14-02 17
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
~4 (5 EACH SIDE)
.050
MOONEY AIRCRAFT CORPORATION
M20M
2024T-5
CLAD(
IIIII RIVET HUCK SUMP
GUN
COUAR
SWAGE SET
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FIGURE
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51-18SM51--18
B
these under
existing holes. Pick up all rivet holes on web splice plate and drill new rivet holes on equal spacing around the damaged area similar to that on Figure 51-18 rivets on each side of damaged area.
51-14-03
SET
deSWACE
REMATING HORIZONTAL STABILIZER TO STRINGER FIGURE 51-19 Alternates:
REMATING HORIZONTAL STABILIZER TO STINGER
Resin
#606 Patching Adhesive Resin United States Gypsum
Epoxical
repair necessitates removal from the stinger, remating can be facilitated by using huckbolt substitution information contained in Section 51-10-01. When mating stabilizer to stinger use bent rivet swage set #5 (See Figure 51-19). FIBERGLASS LAMINATES, REPAIR PROCEDURES
the fact that
Despite
~5
SM51-19
When stabilizer
51-15-00
BENT
RIB REPAIR
The repair of damaged stabilizer and fin ribs is not feasible in most cases. Damaged ribs should be replaced with new parts. 51-14-04
S~FWGHT
~5
fiberglass
to withstand considerable
laminates
are
Catalyst
#606
Patching Adhesive
Gypsum
OR Resin Ren Epoxy CG 1304 Ren PiastFcs Co.
designed
Lansing, Michigan
abuse, occasional repairs
will be necessary. It is difficult to covet dl the various repair techniques due to such limiting factors as accessibility and the extent of damage. The following outlines those steps which are used to make repairs of the more common type damage to a fiberglass laminate.
Catalyst
Ren Hardener CG 1304 Ren Plastics Co.
Lansing, Michigan Fire
retardation
Antimony
Trioxide
for
fire
retardation, 5% minimum; 10% maximum by Weight of
1. Materials used for repairs shall be as specified and compatible with the basic resin used in the
fiberglass laminate. Resin Aerospace Adhesive EA934 Hysol Division The Dexter Corporation
Epoxical
Hardner United States
Resin Content. Must be added to the base resin (cowling and air intake duct assemblies).
Part A
The manufacturerâ&#x20AC;&#x2122;s bulletins shall be followed for all mixing ratios and preparation prior to application. 2. General.
Catalyst
A. The configuration of repairs are shown for flat surface areas; for simplicity; however, the same techniques can be used for contoured surfaces. Contoured repairs will require additional considerations and the proper shaping of the backup plates used for clamping the laminates together during the curing
Aerospace Adhesive EA934 Part B HysolDivision
The Dexter
Corporation
cycle. 51-14-03 18
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
CAUTION
B. The degree of laminate chamfer and size will vary based on accessibility, shape of part and the extent of damage.
CRACKS, IN SURFACE AREAS
51´•15-01
drill
Stop procedure. 1.
all
cracks
standard
per
2. Remove any loose particles and strands from the cracked portion.
3.
Methyl Ethyl Ketone (M.E.K.) is a flammable liquid and should be used with proper ventilation and the prescribed safety equipment.
Prepare surface for repair
as
CAUTION
aircraft
Fiberglass components are attacked and deteriorated by the following products: Ketone, aliphatic eaters, chlorinated hydrocarbons, and slightly softened by aromatic hydrocarbons.
frayed fiberglass
shown in
(Figure
51-1,02
51-20, Figure 51-21, and Figure 51-22). 4. Prior to
Ref.
continuing the repair, repair must be cleaned
of the wiping the
area
area with by Methyl-EthylKetone.
a
NON-STRUCTURAL REPAIR
all surfaces in the of all contaminates clean cloth saturated with
1´•
Apply masking tape
Figure 51-20)
over
crack
on
finished surface
side. 2.
Apply
wet
coat
of
catalyzed
epoxy
resin
to
chamfered surface.
Apply one layer of #181 fiberglass cloth saturated catalyzed epoxy resin (A). 4. Add additional plys of #181 fiberglass cloth, saturated with epoxy resin (B) through (D) or as required to attain original laminate thickness.
3. with
STOP
0.5" I.................
DRILL
..........~rl
I CRACK I´•´•´•´•´•´•----´•´•-´•´• I
I´•-´•´•´•´•´•´•´•´•´•´•-´•´•
i
´•i
I
´•I
I.S---t-CRACK
AB
l.s^
--1
I´•s
---I~-
THICKNESS .02 TO
FINISHED SURFACE
OUTLINE OF CHAMFER AREA
I
CHAMFER 1.5* EACH SIDE OF CRACK
.04
C
_t
O
I
MASKING TAPE
FINISHED SURFACE
-r
THICKNESSLAMINATE SM51-20
NON-STRUCTURAL REPAIR
4-99
FIGURE 51-20
51-15-01 19
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 5. Apply one additional ply of #181 cloth total repaired area and bond in place.
bridging
the
INSERT) (Ref. Figure 1. Cut away laminate per
5. Place rigid aluminum plates on both sides of repair and cramp into place with "C" clamps. Permit laminated repair to cure.
area
COMMON STRUCTURAL LAMINATE REPAIR (METAL
51-15-03
MOONEY AIRCRAFT CORPORATION
M20M
8. After fiberglass repair has cured, remove clamps and install #3 AN426A rivets. Flush head to be on finished surface side. Number of rivets and spacing will be determined by size of repair.
51-21
sketch, roughen repair
area
sandpaper, clean repair area with M.E.K. apply a wet coat of catalyzed epoxy resin to surfaces. Then IMMEDIATELY proceed with steps 2 thru 5. 2. Install chemically cleaned .025 T-3 aluminum straps, perforated with #40 holes approximately .35 on with 240
7. Apply one additional overlapping layer of #181 fiberglass cloth on non-finished surface and bond in place. Should opposite side be a non-finished surface, an additional layer of fiberglass should be applied to
this side.
Upon completion of steps 1 thru 7, permit repair to before attempting further treatment of appearance surfaces, if required. 9´• Appearance surfaces will normally require application of a filler-sealer coating. The appearance area is to be wiped clean, using a clean cloth saturated with M.E.K. prior to applying filler-sealer coating. 8.
center all directions.
cure
Apply wet coat of epoxy resin to aluminum straps apply one or more layers of resin saturated #181 fiberglass cloth to equal the thickness of the original 3.
and
laminate. wax paper over both sides of the repaired while still wet. This prevents adhesion to the pressure clamp application (paragraph 5).
4.
Lay
area
#181
LlBERGLASS
CLOTH
.025 T-3 ALUM.
(i
.375*
(SEE
2.0"
51-1,-03,
I
2)
i LAMINATE 1
CRACK
.03" .025 T-3 ALUM. (SEE SECTION
2.75*
51-15-03,
#181 FIBERGLASS CLOTH
OVERLAP
(1)
LAYER FIBERGLASS
ALUM.
PLATES
LAMINATE FINISHED SURFACE
FLUSH FIBERGLASS
BOND IN
20
(MP.)
PLACE
OVERLAP (1) LAYER FlBERGLASS ONLY IF THIS SIDE IS A NON-FINISHED SURFACE.
COMMON STRUCT. LAMINATE REPAIR-METAL INSERT 51-15-03
RIVET
4-99
FIGURE 51-21
5
2)
OLDWILLWAYNE 6. Place rigid aluminum plates on both sides of repair and clamp into place with "C" clamps. Permit laminate repair to cure.
10. Mix epoxy resin and catalyst per manufacturers to appearance surface area. Care should be taken to assure as smooth as possible surface in this particular operation. Permit this surfacing coat to cure prior to any additional applications or further rework,
specifications and apply
11. area
area
7. After fiberglass repair has cured, remove clamps .,d install #3 AN426 rivets. Flush head to be on finished surface side. The number of rivets and spacing will be determined by the size of the repair.
sandpaper, sand and blend repaired surrounding surface. Steps 10 and 11 repeated to acquire a satisfactory surface
Using
#240
to match
may be finish. 51-15´•04
of steps 1 thru 7, allow the repair before attempting further treatment of the appearance surface. 8~
t,
Apply
wet coat
of
catalyzed
epoxy
resin
Upon completion
cure
9´• Appearance surfaces will normally require the application of a filler-sealer coating. The appearance area is to be wiped clean, using a clean cloth saturated with M.E.K. prior to applying a filler-sealer coating. 10. Mix epoxy resin and catalyst per manufacturer’s specifications and apply to the appearance surface
COMMON STRUCTURAL LAMINATE REPAIR (FIBERGLASS-RESIN
COMBINATION) (Ref. Figure 51-22) 1.
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
to
chamfered surface.
Apply one layer of #181 fiberglass cloth saturated catalyzed epo~ry resin. 3. Add additional plys of #181 fiberglass cloth saturated with epoxy resin to attain original laminate 2.
area.
with
Care should be taken to
assure as
smooth
as
possible surface in this particular operation. Permit this surfacing coat to cure prior to any additional application or further rework. 11. Using #240 sandpaper, sand and blend repaired area to match surrounding surface. Steps 10 and 11 may be repeated to acquire a satisfactory surface
thickness. 4. Apply one layer of #181 fiberglass cloth to the non-finished side of laminate, extending 1/2" each side of the chamfer and bond in place,
finish.
wax paper over both sides of the repaired while still wet. This prevents adhesion to the pressure clamp application (paragraph 6).
5.
Lay
area
O
1
STOP
0.5"
DRILL
’I
I.................
I
.I
I´•-´•´•-´•´•´•´•´•´•´•_,
i.
I
.7;...~ST;
CRACK
I-´•´•´•´•´•´•´•´•´•´•
´•-´•´•-´•--~´•I I´•-´•´•´•´•´•´•-´•´•´•´•´•´•´•
.I
I.....--........´•). i´•´•´•---´•´•´•-´•´•´•´•´•
CHAMFERED SURFACE
i
GLASS PATCH OUTLINE
I............´•.´•.\.
--t--15 ---I NON-FINISHED SURFACE CRACK 1
L-~--
FINISHED SURFACE
CHAMFER EACH SIDE
(TYP.)
THICKNESS .02 TO .04
;C-0~50
;c0.50
O (FIBERGLASS-RESIN COMBINATION) COMMON STRUCTURAL LAMINATE REPAIR-FIGERGLASS/RESIN-FIG.51
4-99
SM51-22
-22
51-15-04 21
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 51-15-05
M20M
is scratched, spotfaced, drilled, or in any way removed must be recoated with epoxy primer.
FIBERGLASS DELAMINATION REPAIR
coating
EXAMPLE: Part is Conversion Coated as detail part. During replacement the part is spotfaced to receive bolt and washer. This part must be primed after
Delamination or ply separation of a fiberglass product is usually a result of poor bonding of fiberglass layers. Generally, this condition is localized and can be readily repaired by carefully spreading apart plys in delamination, and removing loose particles by blowing clean compressed air into damaged area. 1.
spot-facing. 2. Low Pressure, Plastic, or Rubber Line Splices. Static system lines may be lengthened, shortened, or spliced to allow thereplacement of sections of damaged lines. The fittings are called out in the Parts Catalog text pages following the illustration depicting the assembly or component in question. If splices are made, the system must be checked for
2. Proceed by inserting catalyzed epoxy resin into delamination and then immediately clamp delamination together. Permit repair to cure a minimum of 8 hours before removing clamps.
3. Extensive delamination of a part will be reason for total rejection of part and shall be scrapped per
standard practices. 51-16-00 1. Protective
-MISCELLANEOUS
Coatings.
Parts with A. Conversion Coated
51-15-05 22
protective or
epoxy
coatings (such primer) on which
MOONEY AIRCRAFT CORPORATION
as
the
leaks. 3~ Shortening and Lengthening of Tubing, Hoses, manufactured Flexible and Ducting. Mooney assemblies of plumbing, tubing, hoses, and flexible ducting may be modified to allow the use of longer parts of the same size and material to be cut and used as replacements. When the manufactured ends of flexible ducting are removed, the raw edge must be taped with 3M aluminum foil tape.
4-99
I
OLDWILLWAYNE
C H A PT E R
DOORS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 52 DOOR
LIST OF EFFECTIVE PAGE
CHAPTER
SECTION SUBJECT.
PAGE
52-EFFICONTENTS
DATE
1/2BLANK
4-99
52-00-00.
3.
4-99
52-11-00.
4.
4-99
52-1 2-00.
5.
4-99
52-31-00.
6.
4-99
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT
52-00-00 52-10-00
SUBJECT
PAGE
General
3
Cabin Door-Maintenance Practices
52-11-00
Cabin Door
52-12-00
Cabin Door Seal
52-30-00 52-31-00
Rigging/Adjustment
3
Procedures
4
5
Baggage Compartment Door-Maintenance Practices Baggage Compartment Door-Latching Mechanism
4-99
5
6
~YEFF/CONTENTS 1/2BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 52-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
outer skin and the hinge and between the hinge and the mounting plate from the inside in order to break the sealant bond. During this procedure determination can be made where the locator rivets are positioned. Locate these rivets from the inside and drill the bucked head carefully. DO NOT DRILL THROUGH THE OUTER SKIN. Attempt to move the door and hinge aft and away from the attach point after each rivet stem is drilled out. The door and hinge should come free when all sealant bond and rivets are removed.
-GENERAL
The cabin door is constructed of an inner and outer aluminum shell fastened together by rivets. It is provided with a dual latching mechanism, 1) a lock pin extends into a mating receptacle in the lower door frame and 2) a jaw type latch clamps a special designed nut in the upper door frame to hold door securely in place. The door is hinged at the fon~vard edge by an extruded aluminum hinge. The inner handle and the outer handle are interconnected by tubes. This mechanism is spring loaded to an over center position in the latched position for positive security. Adjustment for each push pull tube is provided to accurately rig the latching pin and the jaw type latch. Adjustment to the special nut at the top of the door frame can be made for proper closure.
adjustable push pull
NOTE Some aircraft may have "AN" bolts instead of rivets. 2´• Door
The baggage compartment door is constructed of an inner and outer aluminum shell fastened together by rivets. It has dual pin latches that extend into receptacle fittings on both sides of the door frame when the exterior handle is closed properly.
B. Remove the interior door
auxiliary
before reinstallation of the door. A new door or hinge will require proper the door to obtain proper sealing. A.
new
hinge installed, into and the mounting
outer skin
inside the cabin. is
C. Dn’n the new holes in in place.
hinge carefully
while door
securely
replaced.
D. Remove the door, deburr holes and clean the the area.
shavings from
MAINTENANCE
NOTE The rivets and rivet holes originally used as locators do not have to be utilized when installing a new door or hinge if proper alignment can be obtained using another method.
Removal. The cabin door may be removed to replace or repair the door or to replace a damaged 1.
hinge.
panel
door, with
positioning of
B. When door is properly positioned mark the new hinge for mounting using existing holes, either from the outer skin locations or from the hinge mounting plate
A door lock is provided for both doors. A single key will operate either door rock. The interior panels require removal if the door locks are to be removed and
A. Remove the interior frame.
Place
position between the plate.
A hold open arm is attached on both doors to assist in holding the door open when desired.
CABIN DOOR PRACTICES
if necessary to
3. Installation. The old door can be relocated by using the existing holes. The mounting plate should be thoroughly cleaned of all sealant and foreign material
baggage
52-10-00
panel
repair the door assembly.
exit handle is located on the inside of the door. This handle can be operated only from the inside even if the outer handle is locked. A cam mechanism allows a clevis pin to bypass the outer handle latch groove and open the two latching pins which hold the ba~nage door closed. (Refer to POH/AFM Section III specific procedures to operate auxiliary exit handle.) This door is hinged at the top with an extruded piano type hinge. The
Repair.
A. The door should be repaired, if applicable, according to standard procedures in AC 43.13-1(
around the door
E. Apply sealant, PR1428-B, PR1403-G-B2, or equivalent, between outer skin and hinge support plate
B. Remove the hold open arm at the door frame. Remove the cotter pin and washers from the hold open arm shaft. Pull the shaft up from the doubler plate and clear of the door frame.
on
tubular structure.
F. Reinstall door hinge to mounting plate using the head screws removed earlier and three (3) flat head AD4 standard (AD5 oversize) rivets.
eight (8) Rat
C. Remove the eight (8) screws from outside the hold the front portion of the hinge in place. There are also three (3) flush rivets that will require removal at this location.
airplane that
D. Carefully drill center of rivet head with a 1/8th inch drill bit until head pops off and rivet stem can be punched out.
The original door assembly, with hinge attached, is assembled to the door frame prior to installation of the outer skin. The door is placed into position and the hinge held in place on its mounting plate by sealant and locator rivets. (The number of locator rivets may vary). These rivets will be underneath the outer skin. After removal of the outer rivets and screws work a putty knife or a thin piece of aluminum between the 4-99
52-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
G. Adjust door latching mechanism so door closes and seals during flight. (See door rigging procedures paragraph 52-11-00). H. Reinstall hold open arm with new cotter pin. I. Reinstall interior panels and interior trim to door and cabin. J. Paint door to match
airplane.
MOONEY AIRCRAFT CORPORATION CABIN DOOR RIGGING/ ADJUSTMENT PROCEDURES
52-11-00 The
cabin door latching mechanism has several adjustment points that may be utilized to obtain proper rigging. (See Figure 52-1). Removal of the interior door panel will be required to gain access to the adjustment points. 1. Adjust cabin door linkage to satisfy requirements
listed below.
7.
SLID LATCH
9.
JAWS
ADJUSTM POINT
COVER
PLATE
FWD
e
8.
2.
3.
ADJUSTMENT POINT
BELLCRANK ARM
VI EW- LOO f-( I NG CABIN DOOR
52-11-00
8
I
OUTBOARD AT RIGGING/ADJUSTMENT
4-99
SPRING
4.
HOUSING ASSEMBLY
5.
UPPER
LINK
~1. LOWER LINK
CABIN FIGURE 52-1
DOOR
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
H. Carefully place end of seal into position at bottom of door and continue around the door until the seal is firmly attached. Do not pull tight around comers. Cut off any excess seal.
A. Latching pin must contact striker plate on door frame the full circumference of pin when mechanism is in full latched position.
B.
opening
Latching pin must clear striker plate when or closing the door with latching mechanism in
I. When seal is properly attached the door should close with little effort.
full open position. C. As the lower link
(1)
and bellcrank
arm
52-1) travel over center, the spring (3), compressed to 1.000 +/-.030. NOTE Washers may be added between or
(2), (Fig.
NOTE Door contour can be altered slightly to conform with cabin contour, if needed, for proper fit and
be
is to
sealing. spring and link
PRACTICES
D. The lower link (1) and bellcrank arm (2), in full locked position, should be overcenter aminimum of.3
1. Removal. The baggage compartment door may be removed to replace or repair the door or to replace a
inches, (Figure 52-1).
damaged hinge. A. Remove the coat hanger and headliner panel located inside and directly under the baggage door
NOTE It is not necessary that the lower link (1) contact the upper link (5), (Figure 52-1).
hinge
position,
C. Center punch rivet heads to the fuselage.
the upper latch
jaws (6) (7) at the end See adjustment points (8) and (9),
must be closed and the latch slide cam
D. holes.
(Figure 52-1).
F.
NOTE cam
(7)
moves
position.
The cabin door seal is an extruded rubber seal filled with a soft foam. Unless deformed or torn, the seal will provide adequate sealing around the periphery of the door during Right conditions. 1. Cabin door seal
A. The seal adhesive. B. access
punch
hinge and baggage
Remove
door
If
repairs
are
is held to inner door frame with
to be made the interior trim
may
require
panel
removal.
3. Installation.
panel
to
gain
OLD HINGE A. Place repaired baggage door with old hinge into position and creco securely to assure fit of door; check
C. Pull the seal from the door frame. D. Clean the area with lacquer thinner to help Remove excess soften the remaining adhesive. adhesive.
latching operations. B. Remove door-assure attachment of old sealant.
CAUTION
C.
Care should be exercised to keep the lacquer thinner from dripping on the wing or any other portion of the airplane.
Apply
sealant,
area
PR1428 or between outer
hinge
and
oversize)
in all
(St.
D. Reinstall door assembly with old cleco hinge for proper placement.
of
(St.
E. Install rivets holes.
area
new
applications dry
seal with adhesive until
is clean
PR1403-G-B2,
to hinge attachment skin and inner frame.
equivalent,
area
E. Coat cleaned door frame with adhesive Clair #4587).
G. Let both
assembly
NOTE
replacement.
Remove the door inner trim to the door seal.
F. Coat bond Clair #4587).
rivets from
G. Clean hinge and hinge mounting area thoroughly of all sealant or foreign material. 2. Repair. The baggage door may be repaired per standard repair procedures in accordance with AC 43.13-1( Repairs may be made to the baggage door on the airplane if feasible.
CABIN DOOR SEAL
52-12-00
drill rivet heads and
Carefully
carefully.
1.13 in. from the full
latched to full open
holding the hinge half
E. Work a putty knife or thin piece of aluminum between outer skin and hinge and inner skin frame and hinge to break sealant bond.
G. In full open position the upper latch jaws must be open and slide cam at the end of its full travel. Slide
area.
B. Pull insulation back to clear rivet shanks.
E. The outside handle is to be Rush with outside skin when mechanism is in full latched position.
of its full travel.
BAGGAGE COIIIIPARTNIENT DOOR MAINTENANCE
52-3090
310294-501 housing assembly (4) to comply with items B and C, (Figure 52-1).
F. In full latched
SERVICE AND MAINTENANCE MANUAL
M20M
(AD4 standard,
AD5
tacky.
4-99
52-12-00
OLDWILLWAYNE NEW HINGE
A. Place old door assembly with door assembly and new hinge into the door in place.
Hinge
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
new hinge or new position and latch
i. Install rivets, (AD4 standard, AD5 oversize) in all holes. Remove clecoes as rivets are being installed to
keep
door
aligned. BAGGAGE COMPARTMENT DOOR LATCHING MECHANISM
52-31-00
NOTE mounting area should be oiean of old sealant and debris.
door has a direct that inserts two pins into hard points in the door frame. This latching mechanism can be locked from the outside. An auxiliary exit mechanism is incorporated into this mechanism which allows.the door to be in an emergency, from the inside even if outside handle is locked.
The
baggage
compartment
non-adjustable latching linkage
B. Push in on door assembly at top, while door is in the latched position to properly locate the door and seal in the door frame.
C. While door is held in place mark holes in new hinge using holes in outer skin as locators. D. Verify correct position of door prior to drilling holes in hinge. E. Center punch all holes and carefully drill the two end holes. Fasten clecoes in these and recheck door assembly fit, if satisfactory continue drilling all holes.
assembly. Deburr and clean the completely prior to reinstallation of door assembly. G. Apply sealant (PR 1403-G-B2 or equivalent) to mourrting and between wter skin and dmr F. Remove door
area
The outside handle has to be unlatched and fully opened to correctly reengage the latching mechanism after use of the inside auxiliary exit handle. (See
Figure 52-2). a spring attached to the clevis pin of the latch pin linkage. This ensures a positive re-engagement of the clevis pin into the cam slot of the outside handle for proper actuation of the outside latching mechanism (see Figure 52-2). There is
NOTE Follow the
procedures In the Pilots Operating
HandbooklAirplane Flight Manual (P6H/AFNI) H. Reinstall door
assembly
and cleco
securely
for re-engagement of the mechanism for proper outside handle operation.
in
place.
CLIP/PIN
ASSY
HITCH
CR3213-4-2 RIVET PLC)
LANYARD ([IRIENTATION
NOT
CRITICAL)
HANDLE
PIN
CR321â&#x20AC;&#x2DC;3-4-3 RIVET AN960-4 WASHER (2> (1 UNDER RIVET HEAD &1 I7N BACK SIDE OF HANDLE,) MS20470-4
RIVET
S M 5 â&#x20AC;&#x2122;1 BAGGAGE DOOR LATCH MECHANISM
52-31-00
4-99
FIGURE 52-2
(OPT>
OLDWILLWAYNE
CHAPTER
FUSE LAG E
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 53
FUSELAGE
LIST OF EFFECTIVE PAGES
CHAPTER SECTION DATE
PAGE
SUBJECT.
1/2BLANK
4-99
53-00-00.
3.
4-99
53-30-00.
4.
4-99
53-30-00.
5.
6-89
53-40-00
6.
4-99
53-40-03
7.
4-99
53-40-04.
8.
4-99
53-Effectivity/Contents
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT
SUBJECT
53-00-00 53-1 0-00
PAGE
3
General
3
Mainframe
53-10-01
Tubular Structure Frame
3
53-10-02
Tailcone Structure
3
53-20-00
Firewall
3
53-30-00
PlateslSkins
3
53-40-00
Attach
53-40-01 53-40-02 53-40-03 53-40-04
Fittings Wing Attach Empennage Attach Fittings Main Landing GearAttach Points Engine Mount Attach Points
Fittings:
6
6 6 6 8
53-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION 53-00-00
53-16-02
GENERAL
The Mooney M20M forward fuselage is constructed from 4130 chrome molybdenum tubular steel. The tubular steel sub-assemblies are heliarc welded in fixtures, inspected and then assembled into the main cabin fixture and heliarc welded into a cabin enclosure. The assembled steel structure is sand blasted and epoxy primed for corrosion protection, The tailcone bulkheads, formers, etc., are formed from sheet aluminum on a hydro press or drop hammer at Mooney Aircraft Corporation. These components, along with stringers, clips, brackets, etc., are assembled together on a fixture and built into the aft fuselage assembly. All air ducts, control brackets, electrical harnesses and antennas are assembled into the tailcone during this manufacturing stage. The forward cabin enclosure and the tailcone are mated and this fuselage assembly advances down the production line to the point of mating with the wing
assembly. 53-10-00 53-10-01
SERVICE AND MAINTENANCE MANUAL TAILCONE STRUCTURE
The tailcone is of semi-monocoque construction. The internal structure is shown on (Figure 53-2). The forward cabin structure (1) is bolted to the tailcone with structural bolts. The tailcone skin (2) is an integral load bearing portion of the assembly. The avionics equipment shelf (3) spans the tailcone wic~th to provide rigidity and space for avionics components. The batteries are located in this area also. The hat rack shelf (4) provides rigidi~ as well as storage space. The empennage attach points (6) are attached to the rear bulkhead (7) with tabs (8) extended forward and attached to the tailcone structure. 53-20-00
FIREWALL
The firewall is .016 stainless steel attached to forward tubular steel structure. Insulation is placed between restrict to interior cabin and firewall engine All noise. engine holes are sealed tight to prevent fire and smoke in cabin. reference Section 71-30-00 for sealing.
comparbment
heat
compartment/cabin MAIN FRAME TUBULAR STRUCTURE FRAME
The basic cabin enclosure is shown in
(Figure 53-1).
53-30-00
The
fuselage
and
access
PLATES/SKINS tubular
structure
is
covered with aluminum after skins mating to the tailcone. The skins are and riveted to bolted
support angles, forners and brackets. These skins non
are
structural
coverings
II
to
the
Ilform outside
of contour forward the
fuselage section. skins
The
covering the tailcone
are
an
integral
part
of
the
structure. or Repair replacement
these of skins should be according to AC 43.13
-1()Section SMi´â&#x20AC;˘1R53-1
TUBULAR STRUCTURE FRAME 4-99
FIGURE 53-1 53-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
Ljy/ IWZd~
2,
rl
i"
7
SMMR53-2
TAILCONE CONSTRUCTION The
fuselage assembly
and tailcone have panels, doors at various locations to provide access to the interior for inspection or maintenance purposes.
The
FIGURE 53-2
belly
skins
are
removable to
provide
access
to all
covers or
components and control systems located below the
(See Figure 53-3).
ffoorboard. See (Figure 53-3) and table component location and identification.
following
for
NOTE PR1766-B2 sealant should be used
on
all
fuselage lap joints to provide
a
good
electrical
ground plane for
electrical
systems. TABLE FOR FIGURE 53-3
COMPONENT IDENTIFICATION
1. Cabin Door.
13.
Landing
Gear Retract Tubes,
Flap
Indicator
Cable. 2. 3. 4.
5.
Engine Compartment, Turbocharger. Baggage Door. Elevator/Rudder Control Stops. Empennage Attachment.
14. Electric
Flap Actuator.
15. Stabilizer Trim Screw and
Stops.
16. Elevator/Rudder/Aileron
Control
Elevator/Rudder/Aileron
Control
17.
System System
Bellcranks 6. Avionics Blackboxes, ELT
18., Control System/Landing Gear Rod End
6A
Nose Wheel Controls
Bearings. Battery Access.
19.
7. Stabilizer Trim Jack Screw.
8.
20. Rudder
Steering System,
Cowl
Flap
Torque Tube.
Empennage Attachment.
9. Elevator/Rudder
Controls, Rod End Bearings
Gear Retraction Tubes.
21.
Landing
10. Rudder Controls, Elevators 3 Rudder Bellcranks.
22.
11. Brake Master
23.
Tail-Light Harness Connections. Empennage Attachment, Trim Jack Screw.
8 Travel
Stops
Tube, Electric 12.
Cylinders, Rudder Torque Fuel Pump.
Gear Actuator, Fuel Selector Valve.
Landing
53-30-00
Gascolator,
24. Oil Access
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
10
24
1
~-zr"
II
Il
22
6,6A
Q
21 12 11 20 0
13
14
O
3
15 19
16,17,18
~-[lj
ill
1
6A 5
2 SMR53-3 INSPECTION PANELS AND COVERS 4-99
FIGURE 53-3 53-30-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 53-40-00
MOONEY AIRCRAFT CORPORATION
M20M
-ATTACH FITnNGS
Figure
5340-01
WING ATTACH FITTINGS
locations). Various type of fittings (3) properly distribute the load between the fuselage.
53-4 for
used to wing and the are
wing assembly (1) is attached to the fuselage assembly (2) using structural hardware (4); (see
The
3(TYPICAL
LH
a 3
RH)
(TYPICAL
LH
4(TYPICAL
a
iH
RH)
a
RH)
FWD
G3
i""~â&#x20AC;&#x2122;F" (TYPICAL
LH
iH
RH)
~RH)
SMMR53-4
WING/FUSELAGE ATTACH FITTINGS 53-40-02
EMPENNAGE ATTACH FITnNGS
5340-03
assembly is manufactured as a unit (1), (Figure 53-5) with the vertical fin and the horizontal stabilizer using common components. This unit attaches to the tailcone empennage attach points (1) (Figure 53-6), using two structural bolts (2) (F5gure The empennage
MAIN LANDING GEAR ATTACH POINTS
The main landing gear assembly is a welded heat treated 4130 chrome molybdenum steel assembly. The leg assembly (1), Figure 53-7, is supported at the forward end py the tension strap fitting (2) attached to the wing man spar assembly (3) and provides one of the hard points for the main landing gear assembly. The leg assembly (1) is supported at the rear by a bracket (4) attached to the stub spar assembly (5). This is the rear hard point. The main landing gear truss assembly (6) also attaches to the tension strap fitting (2) on the main spar. The brass bearing (7) should be inspected at any scheduled maintenance action for
53-5) asssng through two top hinges (3) (Figure 53-5). The bottom attach point (4) (Figure 53-5) on the empennage assembly secures the stabilizer trim jack screw (5) (Figure 53-5) and (4) (Figure 53-6). Lateral stability of the empennage assembly is controlled with a~iculated hinge assembly (2) (Figure 53-6) an attached to the rear bulkhead (3) (Figure 53-6) of the tailcone. The hinge attach pin (6) (Figure 53-5) is held in place with a cotter pin at each end.
53-40-00
FIGURE 53-4
wear.
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
3
3 2
4
5
6
sm3-5
EMPENNAGE ASSEMBLY ATTACH FITTINGS
4-99
FIGURE 53-5
53-40-03 7
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ENGINE MOUNT ATTACH POINTS
53-40-04
The engine mount is attached to hard points built into the forward portion of the tubular structure. The upper and outboard hard points (1) 8 (2) (Figure 53-8) are for NAS1304 bolts installed for tension loads. The lower hard points (3) are for shear loads. AN6 bolts are used on lower forward attach points in
conjuction
with
nose
landing gear truss assembly.
1.
sns3-6
TAILCONE/EMPENNAGE ATTACH POINTS FIGURE 53-6 Grease fittings (8) are installed at pivot points of the main landing gear assembly for lubrication per Section 5. (Reference Figure 53-7).
;2 4
3
S~IR53-8
2 ENGINE MOUNT ATTACH POINTS
3
(r
L
45d 8
6 1
SMX53-7 MAIN LANDING GEAR ASSEMBLY ATTACH POINTS FIGURE 53-7
53-40-04
4-99
FIGURE 53-8
OLDWILLWAYNE
C H A PT E R
STA B I LIZ E RS
OLDWILLWAYNE M20M
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SERVICE AND MAINTENANCE MANUAL
CHAPTER 55 STABILIZERS
LIST OF EFFECTIVE PAGES CHAPTER
SECTION SUBJECT
PAGE
DATE
1/2BLANK
4-99
55-00-00
3
4-99
55-20-01
4
4-99
5530-01
5
4-99
55-40-02
6
4-99
S5-EFF/CONTENTS
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
PAGE
Horizontal Stabilizer
3
SUBJECT
55-00-00 55-1 0-00 55-1 0-01
55-1 0-02 55-20-00 55-20-01 55-20-02 55-30-00
55-30-01 55-30-02
55-40-00
3
General
Horizontal Stabilizer- Removal
Horizontal Stabilzer- Installation Elevator Elevator- Removal Elevator- Installation Vertical Stabilizer. Vertical Stabilizer- Removal Vertical Stabilizer- Installation
Rudder
3
3 3 4 4 4
5 5 5
55-40-01
Rudder- Removal
5
55-40-02
Rudder- Installation
5
55-EFF/CONTENTS 1Iâ&#x20AC;&#x2122;LBAAN( 4-99
OLDWILLWAYNE SC-00-00
-OENERAL
The M20M empennage assembly is a variable incidence tail-plane consisting of a horizontal and vertical stabilizer bulk as a un~. (Refer to Chapter 53 for the attachment of the empennage to the fuselage.) The horizontal and vertical stabilizer am constructed of formed sheet metal ribs attached to a forward and aft spat assembly covered with stretch formed skins. The horizontal stabilizer has a stub spat that spans a portion of the stabilizer. The elevator and rudder are constructed from an e~druded leading edge spat assembly covered with formed skins. The elevators have a fixed tab between the skins that run the full length of the trailing edge. The elevators and the rudder have balance weights permanently installed for stabilization during flight. 55-1000
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
The aft vertical fin spat (11) is attached to the horizontal stabilizer structure through a brad(et (12) which is fastened securely to the stabilizer rear spar
Bssembly O. (Reference Figure ~-1). SC-1 001
HORIZONTAL STABILIZER REMOVAL
on the tailcone, covering the gap between the tailcone and empennage assembly, will require removal to gain access to empennage attaching hardware. SECTION 53-40-02 describes the attaching points for the empennage assembly. Refer to this section for the removal of the empennage assembly from the airplane.
The fairing located
5~-1002
HORIZONTAL STABILIZER INSTALLATION
Refer to SECTION 53-40-02 for installation.
HORIZONTAL STABILIZER
The main spat assembly (1) 55-1) is formed from aluminum sheet into a Angle doublers (2, 3 and 4) are formed and riveted to the spar through the web section. The stub spat (5) is a channel formed from aluminum sheet reinforced with a joggled channel (6) at the center section. The rear spat O is an e>drusion attaching to the aff end of the ribs and contains the hinge fittings (8) for the elevators, The ribs (9) are assembled in sedions to the front and rear face of each spar assembly to form the air foil. Stretch formed skins (10) are fastened to the ribs, spats and doublers toform the complete horizontal stabilizer structure.
SS-20-00
-ELEVATOR
The elevators on the M20M consist of a lee and right hand assembly attached through ball bearing fittings (1) to the rear spar of the horizontal stabilizer
(reference Figure 56-2 The elevator control horn (2) is connected to the inboard leading edge of each elevator (R.H. and L.H.). Both control hems are then connected to the elevator flight control bellcrank. The full length trim tab (3) may not be adjusted from the factory installed configuration.
This is factory set at 7 The elevator skins
degrees down. are
stretch formed for the
s s
DETAIL A
a
s
s
s
8
to
A
1
sacs~-i
HORIZONTAL STABILIZER 4-99
FIGURE 55-1 55-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
7
1
I
SERVICE AND MAINTENANCE MANUAL
M20M
r4 3
1
5
2
L1
Lt
DETAIL A
A~
55-2
and lower surface of the elevator. There are no ribs in the elevator between the inboard and the outboard ribs. The skins are attached to the leading edge extrusion (5) and the ribs (6) with blind rivets. Each formed corrogation is matched on top and bottom skins and rivets are installed for strength and rigidity through each corrogation. A lead balance weight (7) is installed in each elevator tip with iron rivets (8). (Reference Figure 55-2). See SECTION 27-91-00 for balancing procedures on the elevators. 55-20-01
ELEVATOR
REMOVAL
Remove the AN3 bolts from each control horn and push-pull tube bearing, then remove the AN3 bolts and hardware from each hinge fitting on both elevators. 55-20-02
-ELEVATOR- INSTALLATION CAUTION
Each new,
or repainted elevator should be checked for balance per SECTION 27-91-00. The elevators are installed in reverse order of removal. Nominal torque values for AN3 bolts are to be used (see SECTION 5-20-01 for torque
repaired
table.)
55-30-00
VERTICAL STABILIZER
The main spar assembly (1) (Ref. Figure 55-3) is formed from aluminum sheet. Formed angle doublers 55-20-01 4-99
nested inside the main spar channel and riveted rear spar (3) is an extrusion used to attach the aft end of the sectioned ribs (4). The stub soar (5) is also formed from sheet aluminum. A doubler channel (6) is attached to the vertical stabilizer stub and the stub scar of the horizontal stabilizer. This attach channel is securely bolted to stinger bulkhead brackets. The main spar doublers and angles 7, 8 and 9 provide attach points for the stinger and the horizontal stabilizer spar. (Refer to Figure 55-3). Skins (10) are stretch formed in 2 sections and riveted to the ribs and soar.
(2)
are
to the web. The
Rudder attach fittings (11) are mounted to the rear spar extrusion to attach rudder (12). Lead weights (13) are added for dampening.
OLDWILLWAYNE MOONEY AIRCRAFT CORPO RATION
SERVICE AND MAINTENANCE MANUAL
M20M
12
10
o
VERTICAL STABILIZER
55-30-01
VERTICAL STABILIZER REMOVAL
the 0"
The upper hinge fitting (12) is attached to the rear ffange of the front spar just under the top rib assembly (13) and the balance weight (14), (refer to Figure 55-4). The balance weight (14) is installed with four screws (15). See SECTION 27-91-00 for balancing procedures on the rudder. Balance weight (16) is installed with bolts.
VERTICAL STABILIZER INSTALLATION
Refer to SECTION 53-40-02 for installation. 5540-00
the lower rib assembly (10). A brace the hom assembly is attached to a fitting (11) the lower rib (10).
junction of
arm on
The vertical and horizontal stabilizer are removed as a unit with the stinger assembly. Remove the fairing located on the tailcone which covers the gap between 53-40-02 SECTION and tailcone empennage. describes the attaching points for the complete empennage assembly. Refer to this section for removal of the empennage assembly from the airplane, 55-30-02
FIGURE 55-3
5590-01
-RUDDER
The rudder on the M20M is constructed the same as the elevator with stretch formed skins (1) (Ref. Figure 55-4) riveted to an extruded leading edge (2) and riveted together at the trailing edge. The rudder lower skins (3) are drop hammer formed left and right halves riveted to the upper skins, a rib assembly (4) and at the leading and trailing edge. A stiffener (5) is to support the lower rudder ball bearing hinge fitting (6). A weather seal (7) is included in the assembly. The rudder control horn (8) is attached with the center hinge fitting (9) to the rear flange of the front spar at
4-99
RUDDER
REMOVAL
Remove the AN3 bolt from the control horn and push-pull tube bearing, then remove the three AN3 bolts and hardware from each hinge fitting. Disconnect electrical connections per paragraph 33-41-03,2,A thru E´â&#x20AC;˘
55-40-02
RUDDER INSTALLATION
CAUTION Each new, repaired or repainted rudder should be checked for balance per section 27-91-00 prior to installation.
55-30-01
OLDWILLWAYNE
1,4
2~,´•’ 10
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
:513
1
s,~b
12 1
9 16
7~
4
5
7
5 RUDDER
FIGURE 55-4
The rudder is installed in reverse order of removal. Nominal torque valves for AN3 bolts are to be used. (See SECTIC)N 5-20-01 for torque table).
55-40-02
j
\2 o
4-99
OLDWILLWAYNE
CHAPTER
VVINDOVVS
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 56 WINDOWS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
PAGE
SUBJ ECT
DATE
1/2BLANK
4-99
56-00-00.
3.
4-99
256-22-00
4.
4-99
5660-00
5.
4-99
56-50-00
6.
4-99
56-Effectivity
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
56-00-00 56-00-01 56-20-00 56-21-00
56-21-01 56-21-02 56-22-00
General
PAGE
3
deaningâ&#x20AC;&#x2122;Acrylic:
Windshield and Cabin Windows Windshield
3 3 3
Windshield Removal
3
Windshield-lnstallation
3
Cabin Windows
4
56-22-01
Cabin Windows-Removal
4
56-22-02
Cabin Windows-installation
4
56-23-00 5660-00
Storm Windows.
Acrylic Drilling
4
5
56-EFF/CONTENTS 1/28LANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION GENERAL
56-00-00
A putty knife or thin aluminum strip will be necessary to work underneath the top skin (4) and the side post skin (5) to break the sealant bond between the acrylic and
The windshield for the M20M is .187 inch thick acrylic heat formed to contour. The pilots side window is also .187 inch thick acrylic with a hole cut out to accommodate the .312 inch thick storm window. The storm window is milled to fit the hole and to be Rush with outside of pilots window surface when closed. The other three side windows are .125 inch thick acrylic. All windows are single pane windows. All windows in heated auto-dave to are an approximately 3000 F and placed on a plaster mold to cool while maintaining the correct shape. The windows are tinted for visual comfort, ultra-violet filteration and cooling effect for the cabin. The windows are all sealed to the outside skin with PR1403-G-82 or PR1428 (8) sealant. Retainers and clips are used on the frame to hold windows in place.
the skins. CAUTION
during this operation to avoid scratching the acrylic. Considerable effort may be required to break the bond. Exercise
When windshield is removed all residual sealant must be removed prior to installation of the replacement windshield. Careful scrapeing with putty knife and the application of M.E.K. will assist in removing the excess sealant. 56-21-02
commercial cleaning solution manufactured for acrylic may be used to clean routine grit and grime from the windows. Follow the instructions on the commercial cleaner used. If no commercial cleaner is available these procedures should be followed: Flush windows with water
prior
wiping
to
with
WINDSHIELD-INSTALLATION
is removed, brush M.E.K. or solvent in the cavity (8) where new windshield will be located (refer to Figure 56-1
When
A
1.
care
Carefully pull the windshield away from its location starting at the lower portion and work it loose as the sealant bond is broken around the edge of acrylic.
CLEANING ACRYLIC
56-00-01
SERVICE AND MAINTENANCE MANUAL
M20M
old
sealant
equivalent cleaning
a
clean, soft cloth soaked in kerosene. Never
CAUTION windows when
wipe
Flush with kerosene.
2.
water
after
dry.
cleaning
with
CAUTION Never
gasoline, benezene, carbon tetrachloride, acetone, lacquer thinner, deicer fluid, house hold cleaning fluid or any other questionable fluid to clean acrylic windows. These solvents will use
soften
or cr~ue
2 8
the surface.
NOTE Minor scratches or abrasions may be polished out by using acrylic
resurfacing kits, ie., Micro-Mesh, available from aviation accessory
suppliers. 56-20-00
WINDSHIELD AND CABIN WINDOWS
I
The removal and installation of windshield and windows are accomplished in the
1
-WINDSHIELD
56-21-01
-WINDSHIELDREMOVAL
\2
/6~3
following paragraphs. 56-21-00
6
ofl
The aluminum retainer (1) at bdtom windshield (2) must be removed by drilling out the rivets attaching it to the cowl deck
5
A
~u/ WINDSHIELD INSTALLATION
1
SMX56-1 FIGURE 56-1
(3), (reference Figure 56-1). 4-99
56-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
NOTE Exercise care with application of these solvents. Damage may result if drops of solvents come in contact with either the exterior paint, interior trim or
~9-´• 1
2
plexiglass. Apply sealant, (B),
PR14281/C~
PR1 403-G-82
or
PRC1321-B-2, into the until (8) cavity approximately half filled. Apply a bead of sealant recessed the along
56-1).(6)
of the
(3),
The
new
2
2
cowl(referencel
2
windshield
1
4
being forced into the cavity between the outer skin (4) and the interior retainer (7) will extrude sealant. After the windshield is in place wipe the excess sealant ofi with a damp clean
i’
2
4
8
5
excess
7 6
SMX56-2
cloth. to Prior riveting the WINDOW INSTALLATION FIGURE 56-2 retainer aluminum (1) into position coat retainer CABIN WINDOWS 56-22-02 with a uniform thickness of either sealant. A positive -INSTALLATION bond will be made as the retainer is riveted into place. Use CR1312-5-2 cherry rivets to reattach the retainer Remove all old sealant and clean skin area with M.E.K. (1) to cowl deck (3), (reference Figure 56-1). Place window (1) into position to assure proper fit. Trim a After the sealant cures the excess may be removed necessary (See Figure 56-2) with a sharp razor knife. Aoolv a thick, unifon thickness of PR1428 (8), PR’1~03-G´• or PRC1321-8-2 sealant to both the Check for water leaks. window and skin areas where window (1) will be located. Sufficient sealant should be used so excess sealant is Repaint retainer and rivets to match aircraft. e~ctruded from all edges of windows, both inside and CABIN WINDOWS 56-22-00 outside, (approximately 5, 3.5 oz. tubes for 4 windows). 56-22-01
CABIN WINDOWS
Force window (1) into place with retainers (2) or clips (3). Secure cllips and retainers with Avex 1601-410 blind rivets or existing screws and hardware (4). The sealant will be forcedout and seal the window to the outside skin. Carefully wipe excess sealant off acrylic before it sets up. After sealant cures the excess can be cut off with a sharp razor knife.
REMOVAL
Remove interior trim from the window (1) to be replaced. Remove the retainers (2) or clips (3) which hold the window in position from the inside, (reference Figure 56-2). NOTE Some retainers are held in place with and some with rivets. Drill out rivets
The cabin window installation configuration for S/N 27-0181, 27-0184 8 ON will be slightly different from earlier aircraft, however, the proper application of sealant and fasteners will still apply.
(4) carefully.
screws
The window will be bonded to the outside skin with sealant. Considerable effort may be required to break the bond between the acrylic and the outer skin. Care should be exercised to keep window from twisting and
Check replaced window for leaks. Reinstall interior trim panels. STORM WINDOW
possibly cracking.
56-23-00
Remove the window and clean all remaining sealant from the skin. Use M.E.K. and a scraper to remove the sealant,
The storm window
56-22-00
(5) is mounted with two aluminum hinges (6), attaching hardware (7) and held closed by a latch (8). A gasket (9) is bonded to the storm window
4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL for
sealing purposes (reference Figure 56-2).
75:
56-50-00
1" NEGATIVE RAK
when
closed,
ACRYLIC DRILLING
Drill bits for
acrylic should be ground per (Figure 56-3). A slow turning drill bit with light pressures is desirable.
(,03 FLAT WIDTH)
5"
CLEARANCE
STOVE BURNER TYPE BIT (NO FLUTE RELIEF)
JOBBER FLUTE LENGTH a JI]BBER LENGTH OVERALL
DRILL DIAMETER TOLERANCE TOTAL INDICATED RUNDUT ACRYLIC DRILL BIT
+,0000 ,0000
,0002
JSM56-31
FIGURE 56-3
4-99
56-50-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
BLANK
56-50-00
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
CHAPTER
VVINGS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONflAIRCRAFT CORPORATION
M20M CHAPTER 57 WINGS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
DATE
PAGE
57-EFF/CONTENTS
1/28LANK
4-99
57-00-00.
3.
4-99
57-00-02
4.
4-99
57-20-00
5.
4-99
57-20-00
6.
4-99
57-40-00.
7.
4-99
57-50-11.
8.
4-99
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
57-00-00 57-00-01 57-00-02
PAGE
SUBJECT
General
3
Wingâ&#x20AC;&#x2122;Removal and Installation Stall
Strip
Installation
3 4
57-1 0-00
Mainframe
4
57-20-00
Auxiliary Structures
5
57-20-01
Jack Points
6
57-20-02
Wing Tips
6
5750-00
Plates-Skin
57-40-00
Attach
57-50-00
Flight Surfaces Flaps Flap Removal
5760-10 57-50-11 5760-20 57-50-21
6 7
Fittings
7
7
and Installation
Ailerons Aileron Removal and Installation
8 8 8
57-EFF/CONTENTS 1/28LANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
Fuel is contained in wet wing type fuel cells between the main spar and baffles fbrward of the spar. The tanks are sealed during manufacturing with current technology sealant. (See SECTION 28 for fuel system
GENERAL
57-00-00
The all metal wing is a one piece assembly attached to the fuselage at structural hard points with structural hardware. (See SECTION 53-40-01). The full span main spar assembly is connected to the stub spar and rear spar assembly by ribs, doublers and skins. The attach assembly is an main landing gear fon,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,n,~rd integral part of the main spar and the rear fitting is bolted to the stub spar assembly. The spar caps are 7075-T6 aluminum and the webs, ribs and doublers are 2024-T3, T4 or T42 aluminum. Repair of these components is covered in SECTION 51-13-00. The wing tips are fabricated from the navigation and strobe lights.
I
SHRI_ S101J&7 310131-1 3101SC11 31O13C1J 51O1JC15
BOLT
I
~V(CIU ANCSA A3UaA ANCBA ANCBI
I
I
SERVICE AND MAINTENANCE MANUAL
M20M
fiberglass
details). 57-00-01
WING REMOVAL AND INSTALLATION
major subassemblies of the wing may be removed individually, or the wing m~y be removed as a unit. To remove a wing, a tuselage supporting cradle is
The
needed.
and house
SEE TABLE FOR LENGTHS. IF NECESSARY, INSTALL SHIMS BETWEEN SMEAR mnN~S AND NOT UNDER BOLT HEAD OR NUT.
mrr
WASHER AHOBO~1L
I
1 ~WWO-118 ANOBO~1(1
I
LI 8 d
I
Z
I
ANI-4A BOLT (4) AN960-416 WA;S~ER AN363-428 NUT (4)
I~NJ65-)211 I AN585-4~1
1 ARDEMlsL
(4)
BOTH S16ES--ACCESSIBLE INSIDE
IANS(L3-~
CABIN).
SMEAR ANC1OA BOLT (5)-ACCESSIBLE THRU WHEEL WELL AN960-~16 WASHER (3) Nm (2)-ACCESSIBLE INSIDE CABIN
AN6-)6A BOLT~ALT)ANG-17A AN980-616 WASi´•lai AN3C~ 624 NUT 110001-3 OR -5 SPACER (AR) (MPICAL BOTH SIDES-ACCESSIBLE INSIDE CABIN)
(P(PICAL
II~
~Ne15A BOLi
BOTH
SIDES)
INSIDE CABIN AN960-416L WASHER AN960-416 WASHER (5)~ AN363-428 NUT (5)--ACCESSI8LE BY RMOVING TOP WING FAIRING OYPICAL BOTH SIDES)
O
NCIT br BOLT
8
TORQUE VKUE
ACCESSIBLE AN960-416 AN363-428 ACCESSIBLE
AN 3
UNDER REAR SEATS WASHER (2) NUT (2)-THRU WING BOTTOM
ACCESS PANE~ SHIM AS NECESSARY AN3-4A BOLT--ACCESSIBLE BY REMOVING TOP WING FAIRING AN960-10 WASHER (8) AN363-1032 NUT (8) ~ACCESSIBLE THROUGH WHEOLWELL CMPICAL BOTH SIDES)
AN7H-17A BOLT--ACCESSIBLE THROUGH ACCESS COVER UNDER REAR 600. SAFEIY WIRE BOLT HEAD TO ADJACENT SPAR-WEB SIIFFENER, AN960-716L WASHER (TYPICAL BOTH SIDES)
WING ATTACHING HARDWARE
4-99
FIGURE 57-1
57-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
Wing removal: wing-root fairings access panels.
M20M
1.
A. Remove
MOONEY AIRCRAFT CORPORATION
1. Adjust stall strips so that, during stall recovery, normal use of the controls should prevent:
fuselage
A. More than 15
B. Drain ail fuel from tanks. C.
Drain brake lines and resenroir. lines at wing main spar.
B. More than
Disconnect
hydraulic
C. More than
D. Remove front and rear seats. Remove the two under rear seat area.
E. Jack aircraft per SECTION 7-10-00.
(a)
or remove
Two
the
landing (b) Aileron control tubes (c)
gear assist
following: springs.
The
integral fuel cells, shaded area (1) start at wing station 24.5 and continue to the rib at station 88.75 on both wings. (Reference Figure 57-3). Sealer is applied to all joints on ribs, spar and baffle plates. (See SECTION 28-11-00 for resealing procedures).
Trim control tube at station 59.3 and 94.5.
Elevator control tube.
The wing is manufactured in three sections; the center section (2), the left outboard section (3) and an opposite right outboard section (not shown) (Figure 57-3). These three section’s are then assembled into one full span wing assembly as the skins are installed.
(g) Elevator and rudder push-pull tubes, (h) Floorboards at rear attach points. (i) Belly
skin
stringer splice angles,
(j) Airspeed indicator line, pitot lines, (if installed),
and
A spares
pitot
heater wires
(k) Hardware shown Have
fuselage
in
CAUTION suitable cradle ready to carry the before removing all mating hardware.
a
FT
WING
GHT
configuration, wing tip assembly
is available,
which includes completed section from wing station 103.50 and outboard. The assembly includes the stringers (4) required to complete the splice to the old center section. A spar splice plate is required to reinforce the spar (5) at it’s attachment location. These components, with instructions, are available through your Mooney Service Centers.
(Figure 57-1).
2. Wing installation: Installation of the is direct reversal of removal.
MAIN FRAME
57-10-00
at inboard bellcranks.
(d) Main gear retraction tubes. (e) Rudder control tubes.
(f)
degree roll. 15 degree yaw. 30 degree pitch below Right level. strips on leading edge at stations
2. Place stall shown on Figure 57-2, attach securely with duct tape for test flights. Adjust stall strips until aircraft flies to criteria in paragraph 57-00-02, 1, A, B and C. Secure stall strip per installation instructions in (Figure 57-2).
inspection plates
F. Disconnect
STALL STRIP INSTALLATION
57-00-02
and bottom
wing assembly
AUXILIARY STRUCTURES
57-20-00
SHOWN
WING
OPP.
STA.
43.5
RIB
RIVET
LINE
1 FWD
~2.0 )jA
SKIN
C’BORE STRIP
STALL
WING
SKIN
.406"
.06/.10"
DEEP
AN520-6-7 STALL
STRIP
AN345-6 AiV960-6
SCREW NUT WASHER
FW D
AN515-6R10 SCREW USE LOCKTITE TYPE CV
DRILL .189/.193 DIA USE A6-75 RIVNUT
FW D --sP~
NOTE: FILL
SCREW HEAD HOLES WITH FEATHERFILL; SAND SMOOTH 8c PAINT
A TYPICAL
ALL
II\ISTL.
To
MATCH
WING.
STALL 5iR P
A
STALL STRIP INSTALLATION -FIGURE 57-2
57-00-02
4-99
ALTERIUATE
I~ISTL.
OLDWILLWAYNE
WS WS WS "s WS
’"7.’5
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION 103.5
118.25
133.0
4
I
1
163.0
178.25 WS
5 4
193.5
1
WS
24.5
43.5
WS WS
WS
I--WS
118.~5WS
59.25
74.0
cS
88.75
103.5
C SMMRS57-3
WING STRUCTURE
FIGURE 57-3
4
7
3 8
SMX57-4 WING TIP ASSEMBLY 4-99
FIGURE 57-4 57-20-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
JACK POINTS
57-20-01
NOTE
The strobe from wing
located on the under side of both Wing jack points wings. The threaded wing tie down eyebolt fittings are designed to accept the non threaded jack points. These are located outboard of each main gear. The nose jack point is located aft of the left hand cowl 8ap at Fus. Sta. -5.51. See SECTION 7-10-00 for complete are
Wing tip
2~
M20M
are non-structural fiberglass riveted to the upper and lower final assembly of the wing structure.
wing tips
components. They skins
removing 4 screws wing tip (3) (see Figure 57-4). B. Drill out rivets (4) holding tip to upper and lower wing skin (5). Remove all rivet shanks with a punch. C. Carefully pull wing tip away from wing rib (6) and skins (5). Disconnect strobe and navigation light hamesses at disconnect plug (8) prior to completely removing wing tip.
I
7
7 7 7
C. Use Avex 1604-0412 blind rivets to attach the
5750-00
-PLATES- SKIN
The
wing access and inspection covers shown in (Figure 57-5) provide maintenance access to components, plumbing and control bellcranks enclosed within the wing. They are Rush mounted covers and when installed continue the aerodynamic contour of the wing.
9--7
I,n
o
171
0
1~ 7
20
17
7 0
----t-F1 11
e~t-- 7
-E3
o
Oo
19--c~ 16 19
4
13
o
5
14
SMivlRS57-5
WING SKINS AND INSPECTION COVERS 57-20-01
10 1
18
6
place.
wing tip to the top and bottom skins. D. Repaint to match the aircraft.
19
5
in
sure
3
7 7
repaired wing tip
NOTE Connect strobe and navigation light connectors prior to final attachment of the tip.
strobe light lens (1) by and washers (2) that retain lens to
navigation
1
new or
8. Secure wing tip and drill holes to match wing skins. Cleco as holes are drilled into tip. When all holes are drilled remove wing tip assembly and deburr.
are
wing during 1.Wing tip removal. A. Remove the
installation.
CAUTION aileron and aileron balance weights are not restricted in movement either direction.
Be
WING TIPS
57-20-02
The
tip
A. Place the
jacking procedures.
can be removed either before or after its removal from wing.
navigation lights
or
4-99
0
FIGURE 57-5
-P- 6
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
1. 2.
3. 4.
5.
6.
Wing Wing Wing Wing Wing Wing
skin
.050 thickness
skin
.040 thickness
skin
.040 thickness.
skin
.040 thickness
SERVICE AND MAINTENANCE MANUAL
M20M
(Fuel Tank). (Fuel Tank).
LEGEND FOR FIGURE 57-5 11. OAT probe,
right wing only. guide blocks. Pitot post left wing only. Strobe light power supply.
12. Control tube 13.
(Fuel Tank).
14.
skin
.025 thickness.
15. Aileron bellcrank and control rods.
skin
.025 thickness.
16. Auto
7. Fuel tank access
panels.
17.
Gym
pilot servos. compass flux valve
(left wing only). bungee. controls rod end bearings,
8. Fuel tank filler.
18. Main
9. Control tube
19. Elevator and rudder bellcranks. 20. Descent Rate Control
10.
guide blocks. Wing fuselage attach points,
NOTE Access covers on bottom of wing that require removal for inspection intervals are secured with screws. Any access covers that are riveted in place are required for manufacturing only and NOT for routine inspections. 57-40-00
57-00-01
for
(If installed)
FLIGHT SURFACES
57-50-00
Refer to SECTION 27-90-00 for
Right
control surface
balancing procedures. FLAPS
57-50-10
Refer to SECTION 27-50-00 for maintenance and
rigging procedures.
-A~TACH FITTINGS
Refer to SECTION attachment.
landing
gear assist
wing
fuselage
76
8
3
5
FLAP ASSEMBLY 4-99
FIGURE 57-6 57-40-00
OLDWILLWAYNE Refer’to SECTION 27-10-00 for maintenance and
The flap actuator jack shaft is connected by a push-pull rod end bearing to the actuator bracket (1) located just inboard of theinboard hinge (2). All three hinges (2) and (3) are faired (4) to reduce drag (Figure 57-6).
rigging procedures. The ailerons
Internal structure of the flaps consists of a leading extrusion (5), trailing edge stiffener (6), ribs (7) and top and bottom skins (8). These components are riveted together into a left hand and right hand flap
assembly. FLAP REMOVAL AND
INSTALLATION Refer to installation 57-50-20
SECTION
27-50-00
of all metal construction. The main
AILERON REMOVAL AND INSTALLATION
57-50-21
removal
for
are
(1), (Figure 57-7), is attached to the rear soar (2) through ribs (3). These components are riveted together and a top and bottom skin (4) and (5) riveted to this sub-assembly. To complete the control surface, hinges (6) and balance weights (7) are installed. The weights (7) are bolted bolted (10) through an outboard rib (8) and bracket (9) on each aileron assembly. soar
edge
57-50-11
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
and
procedures.
Refer to SECTION 27-10-00 for removal, installation 8
balancing procedures.
-AILERONS
3
3
‘Qg~
5
6
~2
1
4~1
ob
3"
gl
6
DETAIL A
7
Be
~C 4
1 91
8 6
la~4
(B 7
DETAIL C
DETAIL B
SMX57-7 AILERON ASSEMBLY 57-50-11
4-99
FIGURE 57-7
8
OLDWILLWAYNE
CHAPTER
STANDARD
PRACTICES
(PROP/ROTOR)
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 60 STANDARD PRACTICES-PROPELLER
LIST OF EFFECTIVE PAGES
CHAPTER SECTION PAGE
SUBJECT.
DATE
1/2BLANK
4-99
60-00-00.
3.
4-99
60-00-00
4.
4-99
60-Effectivity/Contents
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
60-00-00
General
PAGE
3
60-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 60-00-00
M20M
-GENERAL
The standard M20M aircraft has a McCauley Propeller, controlled by a governor for constant RPM settings at the pilots discretion.
SERVICE AND MAINTENANCE MANUAL
Repairs may be made to metal propellers in accordance with AC 43.13-1(3) and in conjunction with the definitions of FAR 43. CAUTION
TEXTRON-Lycoming maintenance publications for engine inspection procedures after a propeller strike. Refer to
4-99
60-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
60-00-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
PROPELLERS/
PRO PU LSO RS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 61 PROPELLERS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION DATE
PAGE
SUBJECT.
1/2BLANK
4-99
61-00-00.
3.
4-99
61-00-20.
4.
4-99
61-20-90.
5.
4-99
61-40-00.
6.
4-99
61-40-00.
7.
4-99
sl-Effectivity
TABLE OF CONTENTS
CHAPTER SECTION
61-00-00 61-00-10
61-00-20 61-10-00 61-10-10 61-20-00
General
spinner boms ad Propeller RdmoMI Propeller Installation Propeller Assembly Minor Propeller Blade Repair Propeller Controlling
61-20-20
Governor Installation Propeller Governor Control
61-20-30
Govemor
61-20-10
61-20-90 61-40-00
DATE
SUBJECT.
SUBJECT
Adjustment
kissins
Propeller Governor iroubleshd,ti, Dynamic Propeller Balancing
3
3 4 4
4 4 4
5 5
5 7
61-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE 61-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
NOTE It is not necessary to remove
-GENERAL
The propeller is a constant speed type which operates by oil pressure opposing natural centrifugal twisting moment of rotating blades and force of a spring tin McCauiey propellers) to obtain correct pitch for the selected engine load. Engine lubricating oil is supplied to a power piston in propeller hub through the propeller shaft. The amount and pressure of oil supplied (0-300 PSI) is controlled byan engine driven govemor. Govmor oil pressure acting on a piston land spring) increase propeller blade pitch, thus decreasing engine RPM. As govemor oil pressure is reduced, centrifugal twisting moments and spring force on propeller blades decrease propeller blade pitch and increase RPM.
spinner when removing propeller assembly.
A. Remove 15 screws and fiber washers (1) from aft spinner bulkhead assembly (2) and 5 screws (3) from each doubler plate (4). (Reference Figure 61-1).
plates from behind propeller. Carefully pull spinner dome (5) forward to propeller blades and hub (6). B. PUII doubler C.
clear
Spinner support is shimmed for snug fit on spinner dome with shims (12), las required); quantity of shims installed for use when re-installing spinner dome. Spinner must fit bulkhead D.
inside of note the
snug at each re-installation.
Propeller overhaul shall coincide with engine overhaul, but interval between overhauls shall not exceed 1500 hours. Refer to propeller manufacturersâ&#x20AC;&#x2122; ovemaul manual for complete maintenance action.
CAUTION
propeller/spinner installation is dynamically balanced during manufacturing. It is mandatory that the spinner be re-installed in exact position as removed unless all weights are removed and a complete rebalancing procedure is accomplished. The
NOTE
Approved propeller shops ONLY are authorized for overhaul or major repairs to these propellers. Refer to Federal Aviation Regulations, Part 43, (FAR 43) and Federal Aviation Agency Advisory Circular No. 43.13( [AC 43.13( )Ifor the definition of major or minor repairs or alternations and who may accomplish them.
2.
Propeller removal.
safety wire and discard. Loosen stud/nut (8) attaching propeller to engine crankshaft propeller fiange (9) about 114 inch and pull propeller
A. Cut assemblies
forward. 61-00-10 1.
SPINNER DOME AND PROPELLER REMOVAL
Spinner dome
removal
(if necessary).
h
~8
10 11
I
5
13
SMMR~11 10 SPINNER DOME AND PROPELLER REMOVAL 4-99
FIGURE 61-1 61-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
7. Install spinner dome making installed under all screw heads
NOTE
are
Propeller studlnut assemblies will have to be backed off evenly so that the propeller may be pulled forward (approximately 1/4 inch at a time until all stud/nutassemblies are disengaged from the propeller flange. As the propeller is separated from the engine crankshaft, oil will drain from the propeller and engine crankshaft cavities.
(12)
spinner support (7)
No
propeller
on
PROPELLER ASSEMBLY
61-10-00
is required on the M20M propellers. PreRight inspection should be accomplished prior to each flight to determine: if blades have been damaged,
external
lubrication
if any abnormal looseness is evident between hub and blades or if there is any evidence of oil leakage.
CAUTION Remove the
propeller de-ice boot connections (if installed) prior to removing the aft bulkhead from the propeller assembly.
1.
fiber washers
8. Conduct operational and leak check i"stallation prior to flight.
C. If necessary to remove the aft spinner bulkhead (2) (Figure 61-1), the spinner dome (5) must be removed, refer to 61-00-10. Remove cap screws, and washers (10) which attach bulkhead to propeller hub flange. Remove aff bulkhead from propeller flange.
was
sure
(1).
NOTE should be shimmed to ensure that it fits snug on spinner dome as dome is being installed.
The
B. Pull propeller from engine crankshaft (9). Use clean rags to cover cavity in crankshaft and hub.
61-00-20
MOONEY AIRCRAFT CORPORATION
M20M
MINOR PROPELLER BLADE REPAIR
61-10-10
i. Minor nicks, dents and gouges may be dressed out by approved personnel. Blend any nicks or gouges
-PROPELLER INSTALLATION
If aff
spinner
bulkhead
removed, re-install, using
cap screws and washets (10) in reverse order of removal. 2. Clean propeller hub cavly and mating surfaces of propeller hub.
3.
Lightly lubricate
a
A
new
I
O-Rins (11), (Figure 61-1), and
Install
O-Ring
in
the
propeller hub. CAUTION Remove all rags or plugs placed in crankshaft or hub during propeller
DRESSED
S~I-r
A-A
removal.
4. Rotate engine to No. 1 cylinder TDC.
5.
Position
hub/spinner
propeller assembly with
PROPELLER BLADE MINOR REPAIRS
FIGURE 61-2
Number 1 blade DOWN. Blade numbers are marked propeller hub. An "O" is etched on mating surface of both the propeller hub flange and engine starter ring gear flywheel. These "O"’s should align for installation.
into the leading edge with smooth curves or generous radii as shown in (Figure 61-2). Repaint area to reduce corrosive action.
6. Align propeller hub holes with proper bushings in engine crankshaft flange; slide propeller carefully over bushings until stud/nut assemblies (8) can be started. If bushings should need to be removed for maintenance, refer to Lycoming S.I. No. 1098D or subsequent
61-20-00
on
revisions for correct re-installation. CAUTION
propeller hub must be aligned with proper bushings and holes on the crankshaft fiange.
Tighten stud/nut assemblies (8) evenly and work propeller aff on crankshaft flange. Tighten bolts to 55-65 ft. pounds.
61-00-20
´•1.Clean
GOVERNOR INSTALLATION
mounting pad and
bottom of governor.
2. Coat new gasket with Dow Coming #7 compound release agent or equivalent before installation.
4. Position governor on mounting studs, aligning governor splines and splines of accessory drive.
5.
Safety
6190-10
3. Install new gasket on mounting studs. Insure gasket has raised surface of gasket screen toward governor.
The
6.
PROPELLER CONTROLLING
5. Install all
with .032 wire.
mounting
hardware.
Torque
nuts.
6 Connect governor control to governor and 4-99
rig.
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
NOTE All rigging to match governor arm location. Do not adjust governor high RPM stop to match
CAUTION Recheck
safety wire, security and thread engagement on all engine controls after adjustment rigging or assembly.
rigging. 61-20-20
NOTE Vernier controls friction can be adjusted by loosening the lock nut on back side of panel and either tighten the nut on front of panel to increase friction or loosen the nut to decrease friction. Retighten the lock nut on back side to secure cable to the panel.
PROPELLER GOVERNOR CONTROL RIGGING
i. Disconnect
propeller governor control rod. A. Remove cotter pin, nut, bolt and washers from rod end at propeller governor control arm. B. Disconnect control rod from governor control arm.
61-2030
2. Adjust control arm spring to minimum tension which will return control arm to maximum RPM.
NOTE No adjustment can be done before a test flight is done to obtain maximum governor RPM.
3. Push propeller control in cockpit full forward. Pull control back approximately 1/8 inch and lock in this
position. 4. Place governor control
arm
against high
RPM
2. Remove govemor.
stop
screw.
Adjust propeller control the governor arm position. 5.
6. Attach
replace
control
cotter
rod
3. Loosen
rod end to coincide with
end to
governor
arm
-GOVERNOR ADJUSTMENT
i. Fly aircraft and record maximum RPM at takeoff or cruise flight at full power.
upper
high
RPM
engine screw
cowl
jam
access
to
nut.
4. Turn screw in (CW) or out (CCW) to match RPM recorded during governor test flight. One full tum of screw equals approximately 25 RPM.
and
pin.
5.
7. Operate the propeller control from cockpit to verify full travel of control arm in both directions, high RPM to
Tighten jam
adjustments 6.
Re-rig
as
nut and make propeller control linkage necessary to maintain full travel.
disconnected controls and reinstall
cowling. 7. Perform propeller and govemor operational tests. Fly aircraft and repeat governor test flight and record maximum RPM in flight at maximum power. Repeat this process until proper maximum RPM setting is
minimum RPM stop. NOTE When propeller control rigging is complete, check controls in cockpit to be sure there is .03 to .06 inch cushion between control knob and adjustment nut on instrument panel. The control should not bottom out when pushed full forward.
achieved.
NOTE When
installing a governor, insure that oil system is purged of all air by cycling propeller several times before
61-2080
for
flight.
PROPELLER GOVERNOR TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
REMEDY
Leakage: Between control shaft and head. Between head and body. Between relief valve
plug
and
body. Between
body
and base.
Between governor base and
engine mounting pad,
Inability to attain proper RPM during static ground run:
Damaged O-Ring. head and
Replace
with new
bodygasket.
Replace gasket.
Damaged relief valve plug gasket. Damaged body and base gasket.
Replace gasket.
Damaged governor mounting gasket. Loose governor attaching nuts.
Replace gasket.
Warped engine mounting pad.
Consult
Wrong high-RPM governor setting.
adjustment screw.
Incorrect system
Adjust
Damaged
rigging.
4-99
O-Ring.
Replace gasket.
Retighten
nuts.
engine manual.
Reset governor external
high
RPM
control system.
61-20-20
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
PROPELLER GOVERNOR TROUBLE SHOOTING
TROUBLE
(CONâ&#x20AC;&#x2122;T.) REM EDY
PROBABLE CAUSE
NOTE: Takeoff RPM should not be attained during static ground run. RPM should be approximately 2525 RPM.
Low
engine
Consult
power.
Erroneous reading tachometer manifold pressure gauge.
or
Sticky pilot valve.
engine
Calibrate
or
manual.
replace
instruments.
Remove head and clean pilot valve with cloth. Maintain sharp pilot valve land comers. Check for straightness of pilot valve; if bent, replace valve. crocus
RPM will not stabilize:
Sludgein or
governor relief valve.
Burrs
on
pilot valve
pilot valve
Disassemble and clean.
lands.
Disassemble and clean with cloth.
Backlash in governor control
crocus
adjust control system.
Re-rig
or
Re-rig
control system.
system. Short control lever making fine speed adjustment impossible.
Sticky
relief valve.
Erroneous
reading
Inspect for burrs, tachometer.
Excessive oil leakage in transfer bearing.
engine
High propeller friction. Governor function upset
Calibrate
or
and clean.
replace
instrument.
Refer to
engine
Refer to
propeller overhaul
manual.
manual.
Repair engine for smooth operation.
by
malfunctioning engine. Air
trapped
in
Cycle propeller from
MIN to MAX several times to purge air.
propeller.
Sticky pilot valve.
pitch
Remove head and pilot valve. Clean sludge and vamish. Check speeder spring ends for proper settings.
away Bent
pilot valve.
Excessive intemal
Excessive
over-speeding:
leakage
in
Remove head and
replace pilot valve.
Check
make necessary
governor.
rigging and replacements.
Wrong governor setting.
Reset governor. Use test
Too
Advance throttle
rapid throttle opening.
Damaged or wrong gasket between governor base and
Install correct
part
rig if available.
evenly and slowly.
new
gasket.
engine mounting pad.
Sticky governor pilot or
relief
Disassemble, clean, and check for
valve.
burrs. Replace bent
Erroneous reading tachometer manifold pressure gauge.
Inabilityto pitch:
attain
positive high
or
Nigh-RPM screw adjusted too far IN, causing restricted arm travel,
Calibrate
61-20-30
Excessive friction.
propeller/bladeseat
4-99
replace
instrument.
Remove control arm and rotate one serration clockwise. Back out high-RPM screw to required maximum RPM.(One tum
Surging:
or
pilot valves.
equals
Examine friction.
27
RPM.)
propeller hub for cause of
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 61-40-00
propeller/spinner dynamically balanced by Mooney process maintenance
component of these
PROPELLER BALANCING
The
action
to
is
combination assembly during the manufacturing Aircraft Corporation. Any be
accomplished
SERVICE AND MAINTENANCE MANUAL
M20M
on
two assemblies should take this in
to consideration.
There
are
Balancing operation
many different models of Dynamic Propeller Equipment, therefore details of proper
and manuals of the being used.
any
4-99
procedures should be taken from specific Manufacturer for the equipment
61-40-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
61-40-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
POVVERPLANT
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 71
POWERPLANT
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
71-00-00
PAGE
SUBJECT
5
General Removal
5
71-20-00
Engine Engine Inspection 8 Repair. Enginelnstaliation Engine Ground Operation Checkout EngineSetUp Procedure Fuel Injector Idle Speed 8 Mixture Adjustments Engine Set Up Requirements Engine Control Rigging Fuel Injection system Maintenance. Starter System Maintenance Engine Mixture Control Rigging. StarterTrouble Shooting Cowling Removal Top Cowling Bottom Cowling Cowling Installation Bottom Cowling Top Cowling Engine Cowl Flaps Cowl Flap Rigging Cowl Flap Indicator Adjustment Mounts Engine
71-30-00
Fireseals
12
Airlntakes
12
71-00-10 71-00-20 71-00-30 71-00-40 71-00-50
71-00-51 71-00-52
71-00-60 71-00-70 71-00-80 71-00-90 71-10-00 71-10-01 71-10-02 71-11-00 71-11-01
71-11-02
71-12-00 71-13-00 71-13-01
71-60-00 71-61-00
Air Intake Duct
71-62-00
Alternate Air Door
71-63-00
Intercooler intake Air duct
Replacement Rigging.
Replacement/Removal
5 5
6 6 6 7
8
9 9 9
10 10 10 10 10 10 10 10 10 11
11
12 12 11
71-CONTENTS
3/4BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 71 POWERPLANT
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
SUBJECT.
PAGE
DATE
1/28LANK 3/48LANK
4-99
71-00-00
5´•
4-99
71-00-40
6.
4-99
71-00-52.
7.
4-99
71-00-52.
8´•
4-99
71-00-60
9´•
4-99
71-00-90
10
4-99
71-13-01
11
4-99
71-30-00
12
4-99
71-Effectivity 71-Contents.
4-99
71-EFFECTIVITY 4-99
1/2BLANK
OLDWILLWAYNE
Garrett-Airesearch variable injected engine level wastegate turbocharger installed to give power capability up to 20,000 feet density altitude and high altitude performance up to 25,000 feet. has
a
instructions, consult engine manufacturerâ&#x20AC;&#x2122;s ovemaul manual and service instructions.
Reverse the i.
cockpit switches
are
OFF.
Remove
and
engine cowling
removal
procedure for installation.
Engine installation torque values are as follows: Spark plugs-300 to 420 inch Ibs. B. Hose clamps-i 5 to 25 inch Ibs. C. Engine shock mount bolts-450 to 500 inch Ibs. D. 1/4 inch upper engine mount to fuselage
boltsb(0 to 70 inch Ibs.
2. Turn fuel selector valve OFF.
3.
engine
A.
To assist in installation, identify and tag each part as it is removed. Plug or cap all lines, hoses, and fittings as they are disconnected. i. Make sure that all
-ENGINE INSTALLATION
71 60-30
ENGINE REMOVAL
71-00-10
overhaul
and
inspection
engine
specific
For
The M20M (S/N 27-0001 thru 27-TEA) have either a TEXTRON-L ning TIO-540-AF1A or -AF1B series engine instEilled. fhis six cylinder, 270 H.P., fuel
REPAIR
ENGINE INSPECTION
71-00-20
-GENERAL
71-00-00
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
baffles
(See
SECTION 71-10-00).
E. #10-32 lower engine mount attach block to fuselage-20 to 25 inch Ibs; 1/4 inch lower mount bolt torque is 50-70 inch Ibs.
battery ground cable. propeller (refer to SECTION 61-00-10).
4. Disconnect
5. Remove
6. Drain
engine
NOTE
engine shock mounts in same position as they were originally installed. Refer to paragraph 71-20-00 for sequence of assembly.
Reinstall
oil sump.
7. Disconnect the
following:
A. Vacuum lines. B. Cabin heat ducts C. Fuel vent lines
(at engine).
2.
A.
D. Oil temperature bulb. E. Oil pressure line. F. Manifold pressure line.
G.
Cylinder head temperature
Re-inspect to
and
plugs
control
Spark plugs properly installed. G. Magneto ground
linkage:
A. Throttle control.
B.
Propeller
ignition
tightened
are
and safetied.
quarts. and
tight
wires
ignition
are
H. Oil
plug
Cylinder head temperature wiring is
secure.
M. Exhaust system is
secure.
L. Altemator
points.
is safetied.
connection is
K. Starter cable connection is
WARNING Ground magneto breaker
ii. Disconnect
Row
wires
from
fuel
flow
O. Fuel connections
engine ground strap.
Q. Oil checked.
12. Disconnect alternator and starter wires.
13. Disconnect heater muff and exhaust tail 14. Disconnect fuel line at
engine
R.
pipe.
fuel pump.
16. Attach hoist to lifting eye at Slightly lift engine to relieve mounts. Remove engine mounting 17.
Slowly
tight
raise engine. Be free.
sure
injection
are
are
lines
are
S. Oil filter is installed and T. Induction manifolds
U. All anchored.
top of crankcase. from
Fuel
pressure
lines
are secure.
and pressure checked.
tight.
tight
and
pressure
tight
and
pressure
checked.
15. Shore up fuselage at tail skid using shoring stand to prevent tail from dropping after engineis removed.
and wires
are
P. Manifold pressure lines
secure.
secure.
N. Vacuum lines and connections
fuel
installed
properly
temperature bulb is tight and safetied.
I. Oil pressure relief valve
switch wires from magnetos.
J.
in. Disconnect transducer.
hamess is
and safetied.
governor control.
C. Mixture control. 9. Disconnect
are
are
E. Oil sump is filled to ten
F.
following
spinner
Propeller Engine mounting
D. Oil drain
bulb.
H. Breather hose. 3. Disconnect the
that:
see
properly torqued. bolts are properly torqued. B. C. Engine controls are properly rigged and safetied. (Recheck rod-ends for proper threadgrip length.)
(at firewall).
engine
lines,
hoses,
secure.
are secure.
and
wires
V. Induction air filter is installed and
are
properly
secure.
that all lines, hoses,
are
4-99
71-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL W. X.
M20M
Engine area is free of loose objects, tools, etc. Cowling is installed and secure (See SECTION
RPM of each
usually
Rap
control rods
are
connected.
Prestarting procedure (with aircraft headed into wind): ignition switch OFF. B. Check magneto ground connections. C. Check engine oil level. D. Check fuel quantity. E. Operate all controls through full range to check binding. F. Check baffles and cowling for security. G. Open cowl flaps; check operation. H. Drain fuel sumps and gascolator; check for
Starting procedure: Set A. propeller FWD.(HIGH RPM).
rotating propeller during engine FUEL INJECTOR IDLE SPEED MIXTURE ADJUSTMENT
71-00-51 1. For
operation
in normal
or
low ambient
conditions, adjust idle and mixture
as
temperature
follows:
Check magnetos; if magneto drop is normal,
brake.
proceed
ad~ustment.
A. IDLE SPEED ADJUSTMENT
(1) Start engine and warm up at 1500 to 1800 RPM until oil pressure, oil temperature and cylinder head temperature indications are in the normal operating ranges (GREEN).
FULL
B. Turn fuel valve ON.
(2) Reduce engine RPM and stabilize between 700 to 750 RPM using aircraft tachometer.
C. Set mixture control: FULL RICH. D. Open throttle FULL. Push boost pump switch for 10-25 seconds until positive indication of fuel Row is obtained. Retard to 1/4 open.
E. Clear
propeller area.
F. Start engine. Check oil pressure. If no oil pressure isindicated within 30 seconds, shutdown engine and trouble shoot oil system. Refer to T~XTRON-Lycoming maintenance publications for procedures. G. Set throttle for idle at 900 to 1000 RPM for one minute; then, advance throttle slowly to 1200 RPM for engine warmup. 3. Ground run and warmup. Always head the aircraftinto the wind during warmup. Always select the high RPM blade-angle setting when ground running the engine.hlevet idle for extended periods at low RPM (low RPM will foul spark plugs). Always operate with the mixture control at FULL RICH, and maintain RPM in the 1000 RPM range during warmup
and
ground
Cwl
Ja~´•ctor
AL V(LD
run.
A. Warmup engine until temperature indications are normal. Monitor cylinder head and oil temperature instruments for over
;3
Pn#
temperature. Check magnetos at 2000 RPM with at high RPM blade angle. Switch ignition-starter switch from BOTH to LEFT to check mag drop. Switch back to BOTH until RPM returns to normal. Switch from BOTH to RIGHT and check mag drop.Return switch to BOTH. Mag drop should not exceed 150 RPM on either magneto (drop should be within 50 B.
propeller
71-00-40
-AF1B
adjustment.
2.
governor
or
CAUTION
with idle
control:
ENGINE SET UP PROCEDURE
Watch for
sediment and water.
parking
broken P-leads.
It is recommended that the TIO-540-AF1A
A. Turn
I. Place wheel chocks and set
or
engine installed on the Mooney M20M aircraft be set up according to the following instructions and in conjunction with TEXTRON-Lycoming’s TIO-540-AF1A -AF1B or Operator’s Manual and appropriate TEXTRON-Lycoming Service Bulletins.
1.
for
other). A smooth drop off past normal is sign of too lean or too rich mixture. If no drop
71-00-50
ENGINE GROUND OPERATION CHECKOUT
71-00-40
a
in RPM, check for open
71-11). Y. Cowl
MOONEY AIRCRAFT CORPORATION
u
FUEL INJECTOR ADJUSTMENTS 4-99
FIGURE 71-1
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
(3) Adjust the contact is made 71-1.
idle
SERVICE AND MAINTENANCE MANUAL
M20M
speed adjusting screw until arm stop. See Figure
wit~ the throttle
measured. There is now additional and the reference pdnt is retained.
adjustment
range
(5) Each time an adjustment is changed, clear the engine by running it up to approximately 2000 RPM before making a mixture or idle RPM check.
NOTE Fuel flow will vary with temperature changes. Temperature variations from NACA STANDARD DAY temperature causes approximately .7 Ibs./hr. fuel flow change with each 1 degree C. variation (minus if hotter, plus if cold~er).
(6) Recheck as required to insure the idle mixture is adjusted within limits specified above. Allowance should be made for weather and field altitude when adjusting idle mixture.
If RPM changes appreciably after making idle mixture adjustment during the succeeding steps, readjust as
NOTE
procedures do not result in stabilized idle speed, check idle linkage for looseness.
If above
necessary, B. IDLE MIXTURE ADJUSTMENTS
71-00-52
Stabilize idle speed; slowly, but positively, mixture control from full rich toward IDLE move CUT-OFF. Engine speed should increase 25 to 50 RPM before beginning to drop toward zero.
(1)
(2) Observe tachometer for any change during the leaning process. If engine RPM increase is less than 25 RPM, adjust idle mixture adjustment (Figure 71-1) to enrich the mixture. If engine RPM increase is more than 50 RPM, adjust idle mixture to lean the mixture. An immediate decrease in RPM (not preceded by a momentary increase) indicates the idle mixture is on the LEAN side of best power.
ENGINE SET-UP REQUIREMENTS
1. Check all fuel lines, reference lines, gauge lines and electrical connections for proper routing and
security of fittings. Remove the 7/16-20 plug located at the left hand port of induction air duct downstream of the injector (Ref. Figure 71-2). Install Mooney P/N GSE050012-501, Temperature Probe Assembly into this port (Lycoming SI 1187(G) altemate method). Route wiring back along aircraft, through pilotâ&#x20AC;&#x2122;s storm window; place readout indicator inside cockpit where it will be secure and easily read. Secure wiring to prevent damage by propeller wash.
CAUTION Return the mixture control to FULL RICH position before RPM drops to a point where the
engine quits.
(3) Adjust
idle
mixture to rise of 25 to 50 RPM during the above leaning exerci~e. This adjustment is made by obtain
a
or lengthening (richening) shortening (leaning) of the linkage
Propeller Governor Adjustment (High RPM Stop>
between the throttle lever and idle valve lever tone or two tums at a time is recommended). For easy consider reference, only the coarse thread end. When it is tumed OUT of its block, thel( linkage becomes LONGER and a RICHER mixture is provided. When it is tumed INTO its block, the linkage is SHORTENED and a LEANER mixture is provided
(Ref.
Figure71-1). (4) Additional adjustment
available
for
use
when
\\ln\~w\\n RIâ&#x20AC;&#x2122;""
is
the
screw bottoms out on either side of the blocks and the not idle is adjustment Measure the satisfactory. distance between the two blocks; disconnect spring from the most accessible linkage pin and remove the pin. Tum the block and adjustment screw until the adjusting wheel is centered and the distance between block
center
is
exactly
as
previously
Dens;ty
Controller 7/16 20 P~ug CPort for Temp. Measurement of Intercooler Out Induction Air~
ENGINE ADJUSTMENTS 4-99
FIGURE 71-2 71-00-52
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL A. CHECK AND ADJUST ENGINE CONTROL
assembly cushion
RIGGING control through full range of travel; check that it operates smoothly and contacts the stops at each end of travel. each control at the instrument panel for inch cushion with the control pushed full
(2) Check
Do not force vernier controls
by turning
knobs.
NOTE
Any vernier control which tends to creep can be tightened by loosening the housing nut on the back of the panel and tightening the face nut on the pilot sideof the panel. (3) Adjust controls by adjusting rod end on the forward end of the control. If additional adjustment is required, the control arm may be repositioned to adjust the throttle or mixture, screws
and
resafety,
at
firewall.
if
required.
B. FUEL LINE PURGE
Disconnect
approximately
fuel
line
Pump
out
quart of fuel using the auxiliary fuel Select the opposite tank and repeat. one
in
Step 71-00-52, A, (2)
(3) Run engine until 170 to 1800 oil temperature is obtained. Slowly apply full throttle (propeller and mixture full forward). Observe the GSi~:0j0012-501* readout indicator and allow the intercooler out induction air temperature to stabilize. Lycoming SI 1187(G) Alternate Method)
(5) The dens~ controller is mounted on the left aft side of the intercooler (ref. Figure 71-2). Remove lockwire from the adjusting fitting and by means of a small wrench, turnthe square head of the fitting clockwise or counterclockwise to accomplish the adjustment. Turning the screw inward, or clockwise will increase manifold pressure; tuming it counterclockwise will decrease manifold pressure. Be careful when reinstalling safety wire to avoid turning the adjustment fitting.
boost pump. Reconnect fuel line.
CAUTION
C. FUEL BOOST PUMP THROTTLE SWITCH RIGGING
Turning the adjusting fitting 1/16 turn will change the manifold pressure approximately 2 inches; therefore, CARE MUST BE U(ERCISED
Turn ignition switch OFF, manual fuel boost pump switch OFF, mixture at idle cutoff and aircraft electrical power ON. Push throttle full NVD (FULL POWER POSITION); verify that throttle activated fuel boost pump switch is engaged and boost pump stays ON while the throttle is pulled, toward idle, until 0.38 to 0.5 inches from the full MID position.
(1)
to turn the screw in VERY SMALL increments until correct adjustment is obtained.
If
discrepancies in the controller settings ground set up and actual flight become evident, then the following procedure shall be accomplished. Shut the engine down after the initial (6)
between
to obtain
warm-up for 4 to 5 minutes to allow proper heat soak of
(3) Verify that BOOST PUMP annunciator (BLUE
engine components. To insure that temperatures have stabilized, readings and adjustments MUST BE made with the aircraft cowling installed. Restart engine and run (minimum 2 minutes) until induction air temperature has stabilized.
(2) Reposition switch and
actuator
arm
the above criteria,
light)
specified
(4) Note the stabilized intercoo\er out induction air temperature on GSE050012601 indicator and the stabilized manifold pressure on a calibrated manifold pressure gauge and compare with chart (Figure 71-3). If manifold pressure at the observed intercooler out induction air temperature falls within the limits indicated in the chart no adjustment of the density controller is required. However, if the manifold pressure is not within the limits shown in Figure 71-3, the density controller must be adjusted as described in Step (5) below until it falls within the required band.
CAUTION
(4) Tighten all
as
above and SECTION 61-20-00.
(1) Operate each engine
i~tard:06
MOONEY AIRCRAFT CORPORATION
M20M
is illuminated.
(4) Verify that fuel pressure on aircraft gauge does not exceed 55 PSI and does not drop below 45 PSI. Adjust or replace fuel pump as required.
(7) Recheck all idle and full power adjustments to they meet this specification and readjust if necessary. Verify that all screws are tightened and resafety if required.
insure that
D. IDLE ADJUSTMENT Refer to
paragraph 71-00-51,
A. and B. above.
E. FULL POWER ADJUSTMENTS F. CLEAN UP
(1) Engine running, temperatures and pressures apply full throttle FORWARD).
in normal range (GREEN) slowly (propeller and mixture controls FULL
After any flight checks and adjustments conduct a leak check of all connections.
CAUTION Do not exceed 38.0 In. Hg. and 2600 RPM under any circumstances during the full power
adjustment process. (2) Verify that propeller governor will allow the engine to operate at proper static RPM to obtain 2575 RPM during T/O roll. Refer to SECTION 61-20-30 for propeller governor adjustment. Recheck control cable 71-00-52
4-99
are
complete,
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
RPM H.P.--2575 270 TIO--540--AF1A or B LW-10682 TA0413
CONTROL CHART MODEL DENSIN CONTROLLER TURBOCHARGER POWER ENGINE
CONDITIONS 2575 RPM. Full Throttle Normal Operating Oil Temp. and Pr-essure.
’1 80
’1 70 ’1 60 ,G
150
Ir
~140 Ir w
Z~ t;’120 _I
lr
~’100 o w 7,
90 80
60
54
MANIFOLD
37
56
35
PRESSURE
INTERCOOLER OUT INDUCTION AIR TEMP
vs
IN.
38
HG.
MANIFOLD PRESSURE
FIGURE 71-3
71-00-60
For
CAUTION Do not operate starter in excess of 30 seconds; allow cooling time before re-engaging.
FUEL INJECTION SYSTEM MAINTENANCE
specific injection system inspection
71-00-80
and overhaul
1´• Disconnect mixture control.
instructions, consult engine manufacturer’s overhaul manual and service instructions.
71-00-70
Inspect and
A. Remove cotter
key.
B. Remove nut, bolt, and two washers from clevis and mixture control arm.
STARTER SYSTEM MAINTENANCE service starter per
ENGINE MIXTURE CONTROL RIGGING
TEXTRON-Lycoming’s
Service Instructions. 4-99
71-00-60
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 2. Reconnect mixture control. A. Reverse mixture control. 3.
disconnect
Adjustment of mixture
to
reconnect
control arm.
A. Loosen locknut on control rod end and control arm rod as required.
adjust
grip,
D. Secure locknut.
STARTER TROUBLE SHOOTING
See SECTION 243404 for procedure. TDC~RONLycormgS MAINTENANCE AND OPERATORS MANUAL should be consul;ed.
71-10-00
COWLING REMOVAL
71-~001
TOP COWLING
1. Remove two (2) screws from top cowling on each inboard side of engine cooling air intakes. 2. Remove (1) screw from each side of top cowling, forward and outboard. Then unlatch seven cam locks along each side. 3. Unlatch
cowling just 4.
locks on the aft ahead of windshield. seven cam
Carefully
lift top
cowling
edge
A cowl flap position indicator is located on the lower console adjacent to the cowl flap switch. This indicator is operated electrically thru a potentiometer which is connected to cowl flap actuator shaft. See SECTION 71-1 3-01 for Cowl Flap Indicator rigging procedures. -COWL FLAP RIGGING
´•11-13-00 The cowl the cowl
rigged for a flush contour between flaps flap’s trailing edges and lower cowl and fuselage when in the closed position (See Figure are
71-4).
of the top
off.
BOTTOM COWLING
71-10-02
The cowl flaps are activated OPEN and CLOSED by an idler arm which is connected by a push-pull rod to the actuator arm on the geared motor.A cowl flap switch, located on the cockpit console directly under the mixture control, activates the geared motor. The switch has three positions: a center (CLOSED) and may be (OPEN) position. The positioned at any angle by selecting the switch either up or down until the desired position, as shown on the position indicator, has been reached. Then retum the switch to the center (OFF) position. Limit switches, which are not adjustable, prevent the cowl flap from exceeding the full open or full closed position.
spalfa
B. Check for full travel.
71-00-00
ENGINE COWL FLAPS
71-12-00
procedure
C. Check for proper thread
MOONEY AIRCRAFT CORPORATION
M20M
i. Unlatch seven cam locks located on bottom of cowling, forward and between the cowl flaps.
A
Adjusting Rod
B
Cowl
flap
flush with
engine cowling
2. Unlatch twelve cam locks around NACA duct on lower, right, forward end of lower cowl. 3. Unlatch eight cam locks around induction air inlet duct at forward center of lower cowl. 4. Unlatch six cam locks on aft sides of bottom cowling while supporting the cowl. 5. and
Carefully lower cowling remove
71-11-00
clear of
I
spinner
from aircraft.
-COWLING INSTALLATION
NOTE Check condition of tape on firewall flange where cowling will rest. A polyethylene tape, P~ 5421(UHNIW) (3M)1 in. wide is recommended. This will decrease streaking during wet weather operations. 71-11-01
BOTTOM COWLING
1. The bottom reverse
cowling is installed "firsP in sequence of removal.
71-11-02 1. The top of removal.
71-00-90 10
TOP COWLING
cowling
is installed in reverse sequence
COWL FLAP RIGGING 4-99
FIGURE 71-4
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
1. With the cowi flaps open, adjust linkage rods irom idler shaft arm of each cowl flap to their maximum
.2.h tgnel flaps
Open decreasing 3.
K81
PIN
Close cowl and measure the distance between the cowl flapâ&#x20AC;&#x2122;s trailing edges and fuselage lower forward skin line.
I
R8
z
F
PIN
cowl flaps and readjust the linkage rod, the length by the measured amount.
t
O
r, o
4. Close cowl flaps and ensure that cowl flaps are not outside the fusdage contour nor that the cowl flaps are
preloaded. Readjust
71-13-01
as
o
required.
-COWL FLAP INDICATOR ADJUSTMENT
1. Position cowl
Raps
in closed
IN
position.
B
0 13 R1 1200-07FG-58 COWL FLAP IND. ADJUST.
INSULATOR
FIGURE 71-6
MOONEY M20M ENGINE MOUNT INSTALLATION The rubber shock mounts are installed in a specific sequence for proper dampening of engine and
01,
propeller power pulses. manufacturers make the engine isolators, it is necessary to know which (Lord or Barry) installed or being replaced. Lord Mfg. part numbers shown in normal print; Barry Mfg. part rtumbers 8hown in italics.
Two are are are
The following observed. It is not
~W
SET SCREWS
sequence
assembly
of
permissable to
must
be
mix manufacturers
components.
POTENTIOIIETER
All
assembly sequences
are
listed from aft to forward.
1. UPPER MOUNT SEQUENCE
(LEFT
AND
RIGHT)
(LORD I[BARRYI) ISOLATOR KIT-J-9613-82 contains the components below except mounting hardware.
snwl-e
COWL FLAP INDICATOR RIGGING 2. Adjust cowl flap potentiometer illuminate top bar in display.
3. Position cowl
flaps
to OPEN
on
aircraft,
Adjust
B. NAS1307-50-BOLT
to
Figure 71-6) display.
D.
if
E. TIO-540-AF1A
Repeat steps 2 through 4, until no further adjustment is required. 6. Cycle cowl flap system to insure proper movement
F. J-7763-53
or
-AF1B
MOUNT i
ENGINE
BONDED MOUNT I
[MOLDED ASSY] [98-907~CI0] WASHER,LARGE O/D
G. J-221&61 1
of the indicator.
The M20M
[00-11900-35] BONDED [IMOLDED ASSY] J-10931-5/ [00-12171-01]- SPACER
C. J-ss12-46
5.
71-20-00
A. ENGINE MOUNT, WELDED ASSEMBLY
position.
R1 on A/D board (see necessary, to illuminate bottom bar on 4.
FIGURE 71-5
H. AN960-716- WASHER ENGINE MOUNTS
engine
mount is
a
welded
I. AN363-720- NUT
dyna-focal type
of chrome-moly, 4130 steel. Refinish by sandblasting and paint with 2 coats of Krylon High 1614 (Sherwin-Wiiliams Co.) Heat Black Enamel, mount
assembly
4-99
71-13-01
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 2.
LOWER
RIGHT)
MOUNT
SEQUENCE
ISOLATOR KITJ-9613-82 contains the components below except mounting hardware, special washer (item C.) and heat shield. A. ENGINE MOUNT, WELDED ASSEMBLY
*Optional thickness
ALTERNATE AIR DOOR RIGGING
will allow maximum travel of alternate air door lever assembly. Ref. Figure 71-7,
[MOLDED ASSY] [00-12171-01] -SPACER
2. The alternate air lever assembly should be rigged .06 to .13 gap remains when the alternate air box
F. J-10931-5/
-AF1B
H. J-961 2-46/[00-11900-35]
so
3. The annunciator
BONDED MOUNT/
i. 600394-003 HEAT SHIELD "NOTE: INSTALL H. ON LOWER LEFT MOUNT ONLY
J. J-2218-61 i
[98-9074-10]
K. AN363-720
NUT
magnetic catch assembly. light switch is mounted on the alternate air box and should be rigged to extinguish the light with bottom of door .25 in. (max.) from full closed. door is held closed with the
ENGINE
[MOLDED ASSY]
WASHER, LARGE
O/D
4. Check opening force of door. It should take between 4.5 and 7.5 pounds to open the door. Take readings at approximate location of the magnetic catch assembly.
71-63-00
TORQUE NUTS TO 520-530 INCH LBS 71-30-00
-FIRESEALS
Firewall fireseals and grommets, if removed and replaced for any reason, should be re-sealed after routing the cable or wire assembly from the engine compartment into the cockpit area. After installation cover cable or wire and grommet undemeath the 8reseal with Coast Pro-Seal 700 on engine side of firewail.
INTER-COOLER INTAKE AIR DUCT REPLACEMENT/REMOVAL
When the inter-cooler duct is removed/replaced for any reason it is essential that it be securely fastened to the inter-cooler flanges and positioned so the cam lock fasteners will easily attach when lower cowling is installed.
I
FWD OUTB OARD
71 60-00
-AIRINTAKES
The
air intakes and exits for optimum cooling minimum and drag.
are
engine cooling calculated
requirements Normal engine operating temperatures are at the optimum to facilitate engine
efficiency. engine induction air intake is al fiberglass duct that picks up impact air and routes it through the air filter to the turbocharger housing and eventually to the engine. The
The air alternate
intake system includes an air intake system that is automatically operated. A manual operation control is provided on the aircraft also. The ALT AIR amber light will illuminate on the annunciator panel when the alternate air door is open. 71-61-00
INDUCTION AIR DUCT REPLACEMENT
When the induction air duct must be
replaced it is essential that the duct be
securely fastened to the air filter Ranges to prevent interference with cowl ing.
REO’D. TO ALLOW FOR MAX. TRAVEL OF LEVER ASSY. VY
Sealant some
to seal
front
,06 1,, .13 In,
t
;13 In,
&1D
GAP REQ’D. BETWEEN ACTUATOR ROD DOOR ASSY. WITH CONTROL KNOB IN CLOSED POSITION
can
the ALTERNATE AIR DOOR RIGGING
71-30-00 12
on
Clamp housing of alternate air intake control assembly at the bracket on alternate air box so housing extends only .13 inches beyond clamp. This
BONDED MOUNT/
or
been removed and is to be re-installed induction air assembly,
1.
C. AN960-716- WASHER
G. TIO-540-AF1A
Apply continuous bead of sealant approximately .06 in. high to all sealing flanges of induction air assembly when air filter can has
7182-00
B. NAS1307-50- BOLT
D. 600364-"- SPACER
NOTE
(LEFT´•AND
(LORDI[BARRYI)
E. J-7763-53
MOON EY AIRCRAFT CORPORATION
M20M
4-99
FIGURE 71-7
OLDWILLWAYNE
C H A PT E R
ENGINES
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 72 ENGINE
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
PAGE
SUBJECT.
72-EFF/CONTENTS
DATE
1/2BLANK
4-99
72-00-00.
3.
4-99
72-00-00
4.
4-99
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
72-00-00
General
PAGE
3
72-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 72-00-00
Refer to
M20M
SERVICE AND MAINTENANCE MANUAL
-GENERAL
TEMRON-Lycoming Operators
Manual and Overhaul and Maintenance Manual for detailed information.
4-99
72-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
72-00-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
ENGINE FUEL AND CONTROL
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 73 ENGINE FUEL SYSTEMS
LIST OF EFFECTIVE PAGES CHAPTER
SECTION DATE
PAGE
SUBJECT.
4-99
1/2BLANK
73-Effectivity/Contents 73-00-00.
3´•
4’99
73-31-01.
4.
4-99
73-31-02.
5.
4-99
73-31-02.
6.
4‘99
73-31-03.
7.
4-99
73-40-00.
8.
4-99
73-60-00.
9.
4’99
73-60-00
10
4-99
TABLE OF CONTENTS CHAPTER
SECTION
3
73-00-00
General
73-20-00
Fuel Pressure
73-20-01
3
Fuel Pressure
3
System
Low Fuel Pressure
73-21-00 7330-00
PAGE
SUBJECT
SUBJECT
Warning-
3
Fuel Flow
7331-00 73-31-01. 73-31-02 73-81-03 73-31-04 73-31-05
3
Annunciator
Indicating. System .GBnBTBISyStem
Descrrption
3
Panel Mounted Instrument. Fuel Flow Transducer
3
General Operating Procedures Test Function
7
TroubleshootingSDI (HaskinsjFuel Management Systems Injector-General
5
7
7 8
73-40-00
Fuel
7360-00
Transducer Test Procedures.
8
73-60-00
Fuel
Pump- Information
9
73-EFFECTIVIN 4-99
112BLANK
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION -GENERAL
73-00-00
The
M20M
The system consists of
engine and its accessories
certificated under TEXTRON-Lycoming Type Certificate. Refer to TEXTRON-Lycoming Operators or Overhaul Manual for specific instructions. are
73-20-00
-FUEL PRESSURE
73-20-01
-FUEL PRESSURE SYSTEM DESCRIPTION
pressure transducer, installed between fuel injector and fuel pressure indicator on instrument pa?el, provides electrical signal to indicate operating fuel pressure. A fuel boost pump is installed, in series with engine driven fuel pump, to provide starting pressure and backup fuel pressure during take off.
when fuel pressure goes below 24 PSI (top of yellow are on fuel pressure gauge). The fuel pressure gauge has a ground contact (Pin 8) that sends signal to annunciator panel. The gauge is adiusted by the manufacturer and can only be readjusted by an instrument
73-30-00
73-31-00
designed for use in all single engine fuel aircraft having no more than 60 GAUHR continuous consumption or 78 GAUHR Intermittent consumption. CTake off power). injected
PANEL MOUNTED INSTRUMENT
The panel mounted instrument contains all system electronics and may be divided into groups. FT-101
seven
The display uses one mini lamp and segment incandescent digits that are fully
sunlight
readable and dim automatically during night light flight conditions. 2. MICROPROCESSOR The microprocessor in the FT-101 contains a crystal controlled oscillator that CO"t’Ob all timing and computing functions for precise fuel Row and totalizing computations. 3. POWER SUPPLY The FT-101 power supply is a high speed switching regulator type for optimum efficiency and the lowest possible power drain on the 4~
the and
FT-101
microprocessor
the totalized fuel quantity in a random access memory chip. The Total Fuel Used quantity is retained during aircraft shut down byconnecting the FT-101 memory wire to the aircraft battery through a memory switch. The drain on the aircraft battery is small due to the low power CMOS memory chip which uses only 3.5 milliamps at 24 VDC.
-INDICATING
indicator
system.
MEMORY
continuously
matching
(HOSKINS) SYSTEM
1. DISPLAY
four
aircraft electrical
shop.
A turbine type transducer and installed in the M20M.
The system is
a"d low
-LOW FUEL PRESSURE WARNING
Aircraft, S/N 27-0001 thru 27-0052 (excluding 27-0020) have a low fuel pressure warnig light located in the annunciator panel. This annunciator light will come ON
approved
a panel mounted instrument a"d a fuel Row transducer which is installed in the ai’c’aft engine fuel line.
73-31-01
A fuel
73-21-00
SERVICE AND MAINTENANCE MANUAL
are
FUEL FLOW SYSTEM GENERAL SYSTEM DESCRIPTION
stores
updates
INTERNAL SWITCH ARRANGEMENT The switch block (see Figure 73-2) located inside the FT-101 panel mounted unit has several arranaements to change data readout if desired. Switdhes S1 and S2 (see Figure 73-1) should not be changed unless the transducer "K" factor of a replacement transducer differs from the original unit’s "iC’ factor (see SECTION 73-31-02, 3, for "i<" factor 5.
The Fuel Flow Totalizer
system, utilizes the latest in microcomputer technology products. The fuel Row system is designed to maximize the efficiency of fuel fuel the by displaying system management consumption rate (fuel flow) of the engine and the precise amount of fuel the engine has consumed. This information may be displayed in one of the following formats, US Gallons, Pounds, or Liters depending on switch or contact arrangement, see (Figure 73-1 and Figure 73-2).
programming
description). Switches S3 thru S7 can be positioned in various arrangements to change fuel Row readout to gallons, pounds or liters as the situation may require, (see Figure 73-1).
FT-101 SWITCH ARRANGEMENT
K-FACTOR
SWITCH ARRANGEMENT
SWITCH#
L. M H HH......... Table is continued
on
following
S1 82 ON ON ON OFF OFF ON .......OFF........~O
page.
4-99
73-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
FT-101 SWITCH ARRANGEMENT FUNCTION
(con’t.)
SWITCH ARRANGEMENT
SWITCH
GALLONS
S3 ON OFF OFF
POUNDS LITERS
S4 OFF ON OFF
S5 OFF OFF ON
S6
S7
NA NA NA
NA NA NA
S5 X. X.
S6
X. X.
X U X E X
S7 N X T X S X D
FT-101 TRUTH TABLE FIGURE 73-1 FT-101 A
(HOSKINS)
1. Basically same as Ft-lOl. 2. Refer to Hoskins Operators
3.See
Figure
or Maintenance Manual for 73-1A for FT-1O1A Switch arrangement.
SYSTEM
specific data.
K-FACTOR ADJUSTMENT SWITCH NUMBERS (1111) LOW LOW LOW (2222) LOW LOW. (3333) LOW. (4444) MEDIUM i5555j HIGH (5335) HIGH HIGH (7777) HIGH HIGH HIGH FUNCTIONS
GALLONS LITERS. POUNDS
S1
OPEN: OPEN’ OPEN: X. X. X.
S2 CLOSED. CLOSED. CLOSED OPEN CLOSED. CLOSED CLOSED
FT 101A
S3 34 OPEN OPEN OPEN X. CLOSED. OPEN. CLOSED X. OPEN. CLOSED CLOSED X. CLOSED CLOSED
X. X. X.
X.
OPEN OPEN CLOSED. OPEN OPEN CLOSED
X
X.
-101ASWITCH ARRANGEMENT
SHADIN SYSTEM
X. X. X.
X
O
X X X
X
CLOSED OPEN OPEN
FIGURE 73-1
The -L
option is a fuel management system designed provide information relative to actual flight conditions without any manual data entry, except for initial fuel on board. It is connected to engine fuel flow transducer for fuel Row data and the Loran-C (or GPS) receiver for navigation data. The system provides: Specific Range: NM/gal. or NM/10 Ib. of fuel
to
burned. Optimum cruise speed can be obtained by selecting power setting which yields highest NM/gal. Fuel to Destination: System calculates fuel
necessary to reach destination as selected Loran-C (GPS) receiver by multiplying Fuel Flow ETE to destination. Fuel Rese~va: SCREW
UNrr
7
System
on
by
ca~oulates amount of fuel
whiCh will be available onboard when aircraft reaches destination, as indicated on Loran-C (GPS) receiver waypoint. This feature provides pilot with necessary data to evaluate reserve fuel situation based on accurate data early enough to take necessary action. Endurance: System calculates time left to fly in hours and minutes based on fuel on board and~fuel
SECURIM SEAL
HOUSING
consumption.
*Z
SWITCH BLOCK
FT-101 SWITCH ARRANGEMENT
73-31-01
FIGURE 73-2
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
Remaining: System keeps track of fuel remaining on board. Fuel Used: System keeps track of fuel used since last fuel entry. Not enough Fuel: System will flash display digits when rotary switch is in Fuel to Destination position and fuel to destination is more than fuel remaining. Fuel remaining display digits will show a negative sign followed by amount of fuel short to reach Fuel
SHADIN SYSTEM MEMORY
System includes a non-volatile memory for retaining basic settings and Fuel Remaining and Fuel Used
during power shut
TEST FUNCTIONS AND ERROR MESSAGES Press "TEST" button. Program checks hardware and If test is successful, "good" is displayed; if not, "bad" is displayed and system is to be considered unserviceable until corrective action is taken.
display.
destination.
When "test routine" is completed, system will display the following:
Fuel Reserve will be Used: System will flash display digits when rotary switch is in either Fuel to Destination or Reserve Fuel. This warning is intended to alert piiot that prevailing conditions will require use of the 45 minute Fuel Reserve or part of it.
i. Software basic number
2. K-factor setting in flow window (pulse count per This number MUST match pulse count stamped on fuel flow transducer, otherwise errors will occur. 3. Display units internal settings.
SHADIN SYSTEM COMPONENTS
(Gal.,
system)
-Interface
-Display -Display Controls
checking
of either flow transducer or display unit must have new units set to same K-factor as old unit. Transducers are pre-set by manufacturer and display unit must be set to agree with transducer setting. Refer to table below:
Indicator Setting
K-Factor
Aerosonic Transducer
3
Flowscan Transducer
L
82000
M
85000
H
87000
(85000 pulses/gal.)
1.Remove can from indicator. 2. Locate switch "O". (Ref. Figure 73-3) 3. Set switch to one of the following positions: K-Factor
SulLt~
Disolav will read
K-O K-l 1<-2 K-3 K-4 K-5 K-6 1<-7 K-8 K-9
B A 9 8 7 6 5 4 3 2
88.0 87.0 86.0 85.0 84.0
3
or
85000
hour. In addition, the transducer is accurate down to 0.6 gallons per hour.
change K-Factor in Shadin Miniflo display unit:
2. Transducer supplies the Fuel Flow Totalizer with a pulse signal from a self contained opto-electronic pickup. A neutrally buoyant rotor spins with liquid between V-jewel bearings. Rotor movement is sensed when notches in rotor interrupt an infra-red light beam between a light emitting diode and a photo-transistor. 3. Transducer design is fail safe; complete rotor blockage cannot interrupt fuel flow. Transducer life expectancy is 1500 hours.
83.0 82.0
NOTE Transducers are categorized by number of pulses per second output for a given GPH flow rate ("K Factor)". This will be noted as: L, M, H, or HH scribed on the end of Serial No. For accurate readings, replacement transducers should have same "K" factor as units being replaced. Specify "K" factor code when ordering new transducers.
81.0 80.0 79.0
FUEL FLOW TRANSDUCER
turbine flow transducer, mounted in the engine fuel line, measures flow of fuel. The transducer is rated for a continuous operation to 60 gallons per i.
of
Replacement
Transducer Confiauation
73-31-02
5.8), part
REPLACEMENT OF SHADIN SYSTEM COMPONENTS
-Micropressor
To
LB.
4. Loran-C (GPS) distances as shown on Loran-C (GPS) receiver to check Data Interface Integrity. If system is not capable of reading Loran-C (GPS) data, the word "LbAd" will be displayed.
of three basic units:
i. Fuel Flow Transducer 2. Loran-C (GPS) receiver (not part of Shadin 3. Indicator: (which includes)
and revision level.
gallon).
Fuel Flow: System provides digital readout of fuel flow per hour to one/tenth of a gallon.
System consists
down.
The
4-99
73-31-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
I
74HC373 7~HC373
74HC244 74HC244
)DS1Z10
S1210
O
SW2 28C17
I
I
RN2
/74HC138
74HC244
i~ II I
U2
RN1
I
I HD1I IHD21
U1555
I
i
27CXXX
I
J1
SM73-SHA SHADIN FUEL FLOW CIRCUIT
4. Fuel flow transducer removal.
F. Loosen nuts on inlet outlet tube and at fittings transducer prior to loosening nuts on transducaer attaching bolts. G. Loosen and remove nuts, washers and bolts from transducer and bracket.
8. Remove safety wire from firesleeve around turbine transducer and unwrap firesleeve to expose transducer.
H. Disconnect flare nuts from transducer fittings. Transducer should now be free for removal. Note position of fittings on old transducer prior to removal.
C. Cut and remove ty-raps from insulator sleeves knife disconnects of electrical wires (see Figure
i.
73-4).
sleeving
up
on
FIGURE 73-3
on
A. Remove top and bottom cowling from aircraft, See SECTION 71-10-00 for procedures.
D. Slide insulation harness.
61XX
U10
-I~3-
on
I
Bj
U7
r
HD3
U9
80C318H
U374HC74 )74HC74 I B
I
SWITCH
8
~74HtlJ8 U4
O
SW3
U8
U5
O
MOONEY AIRCRAFT CORPORATION
M20M
electrical wire
Cap
all lines to prevent contamination.
5. Fuel flow transducer
(replacement)
installation.
NOTE The "K" factor of the replacement transducer should match the "K" factor of replaced unit. Refer to "NOTE" following
E. Disconnect knife disconnects.
FIREWALL
3ECTION73-31-02,
paragraph 3 for detailed explanation, A. Note position of fittings old transducer and place them in similar position on new transducer.
s9
on
I
A
I
B. Connect nuts of inlet outlet lines to fittings, leave them snug, not tight.
C. Connect transducer to bracket bolts, washers and nuts.
Oo
DETAIL
A
CAUTION the lines are not being put into a bind or twist when securing transducer to bracket.
Make TURBINE
FUEL
FLOW TRANSDUCER
S~M73-3
TURBINE FUEL FLOW TRANSDUCER 73-31-02
new
using
FIGURE 73-4 4-99
sure
OLDWILLWAYNE D. Tighten transducer.
all
fuel
lines
and
bolts
to
secure
over
insulating sleeving with ty-raps. connections by pressurizing
connections. Secure
F. Leak check all fuel fuel lines with boost pump.
Correct any leaks
or
discrepancies. G. Wrap firesleeving position with safety wire.
over
transducer;
secure
into
NOTE Installation of new transducer may affect engine fuel flow adjustment. It is recommended that procedures of SECTION 71-00-50 be followed to assure engine is set up for proper
H. When all adjustments have been made and all connections checked for security, install cowling per SECTION 71-11-00. GENERAL OPERATING PROCEDURES
stop flashing and read fuel flow.
starting the aircraft engine, the FT-101 will continuously display fuel flow. Total Fuel Used may be displayed by pressing and holding the USEDTTEST
the right of the instrument. Total Fuel Used displayed as long as the USEDTTEST button is depressed (or for 2 seconds), whichever comes first. This number may be reset to zero (0.0) by depressing and holding the RESET button for at least 1 second. on
2. The totalizer function may be used as a single Right totalizer or as a long term totalizer. Both methods are explained below.
A. SINGLE FLIGHT TOTALIZER. The aircraft should be topped with fuel before each flight so the total usablefuel will be known. Turn the aircraft MASTER switch ON. Push and hold the reset button, located on the left of instrument, for at least 1 second. The RESET button has a one half second delay to prevent accidental reset. On starting the engine, the FT-101 will begin displaying fuel Row. Total fuel used may be checked by depressing the USEDTTEST button. B. LONG TERM TOTALIZER. Tum the aircraft MASTER switch ON. On activating the aircraft electrical system, the FT-101 will Rash zero (000.0) fuel Row. Depress and hold the USED/TEST button. The FT-101 will display the total fuel used from previous Rights. DO NOT push the RESET button! On starting the engine, the FT-101 will display fuel Row and continue counting fuel used up to 999.9 gallons, 9999 pounds, or 9999 liters depending on the intemal setting. TEST FUNCTION
A test function is
may
verify
that all
provided
digits
the pilot prior to each
in the FT-1OI,
are
functioning
Troubleshooting any Hoskins fuel management systems should be approached in a systematic manner. All problems can be put in one to five categories: Improper operation due to lack of knowledge about the system. Inoperative computer or main instrument. Inoperative transducer.
Improper transducer
installation.
1. MEMORY LOSS
A. Loses memory when Master switch is tumed OFF.
so
switch ON.
If switch is ON, check clock for
operation. (3) If clock inoperative, replace fuse at battery. (4) If no problem found, remove connector from unit, check Pin 9 for bus voltage. (5) If voltage present, replace FT-101. B. Memory scrambles when engine starts. (2)
After
73-31-04
TROUBLESHOOTING SDI (Hoskins) FUEL MANAGEMENT SYSTEMS
73-31-05
(1) Check "Fuel Flow Memory"
1. Turn aircraft Master Switch ON. When the aircraft electrical system is activated, the FT-101 display will Rash zeros (000.0). This flashing is a reminder for the pilot to reset or check the fuel used by pressing either the RESET or USEDTTEST button. Once the RESET or USED/TEST button is depressed, the display will
button will be
use
Improper wiring.
operation.
73-31-03
the test function, depress and hold the button two times within one second and the FT-101 will display all eights (888.8).
flight. To
USED/TEST
E. Connect I(nife disconnects and slide
sleeving
SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
Exchange FT-101 for modified
unit.
2´• DOES NOT INDICATE
A. No
display.
(1) Remove connector from indicator. Check Pin 1 of harness connector for bus voltage. Check Pin 8 for airframe ground. If OK, change indicator. Displays zeros (with engine running) (1) Remove cowling for access to transducer. Remove insulating sleeving from connections on all wires. Check BLACK wire for IVF ground. Check RED wire for bUS vORage. Check WHITE wire for 25 volts with no fuel flow and increasing to near bus voltage at full flow. B.
(2) If no increase in voltage is seen on WHITE wire as Row increases or if too high a voltage indication is seen with no flow, change transducer. (3) If RED wire does not have bus voltage, check wiring from transducer to Pin 3 of indicator. (4) If BLACK wire is not grounded, check wiring f,, transducer to Pin 6 of indicator. 3. ERRATIC INDICATIONS
A. Check wiring for loose connections. B. Check
wiring for
intermittent shorts.
C. Check transducer for foreign D. If all checks
OK, replace
particles.
transducer.
4. INACCURATE READINGS
A.
The letter K-factor. transducer Check or "HH" inscribed after the serial number.
"L’,"M","H",
B. Remove indicator from instrument panel and Check switch settings and correct to match transducer. 73-31-03 4-99 case.
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
compartment, by disconnecting the transducer electrical connector and test box in its place.
NOTE
setting changes reading by If settings are OK, replace approximately 2 Each switch
appropriate Druck connecting the the
transducer. NOTE For Kulite, Patriot transducers an adapter harness will be required. Contact MAC Service Parts for harness information.
CAUTION Whenever transducer or indicator is replaced, care must be taken to set indicator switches to match transducer. If after making these checks you still do not isolate the problem or do not find a problem, contact the Product Support Department, Mooney Aircraft Company, (830)
Push aircraft Master Switch ON (insure engine gauge circuit breakers are in) and adjust box to approximate pressure desired. The engine gauge should read this approximate pressure.
896-6000, ext.2920, for further assistance. 73-40-00
FUEL INJECTOR-GENERAL
if pressure
The Bendix RSA-B fuel injector is supplied with the engine from TEXTRON-Lycoming. Bendix Operation and Service Manual No. FORM 15-338-D,ECD-JAN 85-700 or subsequent revision should be used for operation, installation or adjustment of the fuel injector.
is correct:
1. Verify Fuel pressure to transducer with mechanical p’essu’e gauge. a.
If
correct--probable failure
b. If incorrect-troubleshoot
(Reference Figure 73-5) 73-50-00
reading
If pressure reads
TRANSDUCER TEST BOX
(DRUCK,KULITE, PATRIOT)
i.
CAUTION
incorrectly,
is transducer.
fuel system.
zero or
SigmaTek gauge, --S/N
pegged
condition:
27-0001 thru 27-0257.
2. Mori~ gauge, --S/N 27-0258 thru 27-TEA.
This unit is for troubleshooting only. DO NOT ATTEMPT TO CALIBRATE WITH THIS UNIT.
a. Check wiring for continunity between engine compartment connector and cluster.
The Transducer Test Box, P/N GSE 030036, can be used to simulate fuel and oil pressures in the Mooney Model M20M.
b. If wiring is correct--probable failure is in gauge module or cluster.
To use the unit for troubleshooting, the box is connected to the aircraft harness in the engine
O i
I
~eae
r’
il\
I
1
BYSO LYCOMINCi D(VI~IC)N
BENDIX RSA-5 FUEL INJECTOR SCHEMATIC 73-40-00 8
FIGURE 73-5
4-99 AI,SO
SEE FICJ~JRE AS HORIZONTAL
(NEXT1
OLDWILLWAYNE
´•otUIr ~O*L CII nu
U ~Coc nAACAll mt U´•
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II
II II II
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BENDIX RSA-5 FUEL INJECTOR SCHEMATIC
FIGURE 73-5
WOUI´•I
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 7360-00
Refer to 1446 for
-FUEL PUMP
M20M
SERVICE AND MAINTENANCE MANUAL
INFORMATION
Textron-Lycoming Service Instruction No. inspection of engine driven fuel pump for
ruptured diaphram.
4-99
7360-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
73-60-00 10
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
IGNITION
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 74 IGNITION
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT
DATE
PAGE
1/2BLANK
4-99
74-00-00
3.
4-99
74-30-00.
4.
4-99
74-EFF/CONTENTs
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT
74-00-00 74-1 0-00
74-10-01 74-20-00 7450-00
PAGE
3
General Electrical Power
Ignition system TroubleahoDtins
Engine Firing Switching.
Order
4-99
3 3
3 3
74-EFF/CONTENTS 1/2BLANK
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ENGINE FIRING ORDER
74-20-00
GENERAL
74-00-00
SERVICE AND MAINTENANCE MANUAL
The TIO 540-AF1A/-AF1B series engines are equipped with Slick 6200 Series, magnetos. The left magneto incorporate an impulse coupling that retards the spark 35 degrees for starting. When the engine starts, counter weights hold the latch pawls away from stop pins. The magneto then will fire at its advanced firing
position. magneto/starter switch combines both ignition and starting functions. Turn the key clockwise through R, L and BOTH to START position; push forward on key
The
while in START and the starter relay is energized. Release of the key, after engine starts, will return the switch to the BOTH position where both magnetos are
Engine firing order is 1-4-5-2-3-6 (Figure 74-1). position of the No. 1 cable terminal in the magneto outlet plate in relation to the magneto case. Observe
As viewed from the distributor end, magneto rotor turns counterclockwise, passing in succession the terminals of spark plug cables in engine firing order. Cables are connected to the magnetos so that the right magneto fires the upper plugs on the right side and lower plugs on the left. The left magneto fires the upper plugs on the left and the lower plugs on the right. The magneto cases, spark plugs, cables and connections are Shielded to prevent radio interference.
NOTE
operative.
It is recommended that all
-SWITCHING
7450-00
IGNITION SYSTEM TROUBLE SHOOTING
74-10-01 1. Hard
The
starting.
A. Assure that the
impulse coupling
is
operating
properly. a. Check 2.
magneto timing
to
engine.
Engine roughness. new spark plugs, B. Check plug leads for deterioration. C. Check magneto points for wear
A. Install
or
be
reinstalled in the same cylinder but in a different spark plug hole every 100 hrs. Replace spark plugs after 400 Hrs. of operation.
ELECTRICAL POWER
74-10-00
spark plugs
removed, inspected, cleaned, reagapped and
In the OFF position both magnetos are grounded. At the R position the left magneto is grounded and at the L position the right magneto is grounded.
switch
Magneto/Starter
is
connected
the
to
magneto grounding wires ("P" leads) of both magnetos. Tuming this switch from "BOTH" to "OFF or from "R" to "L" to "OFFâ&#x20AC;&#x2122; will ground out both or either magneto.
(See Section 74-0060
grounding sequence.) RELIABLIITY: With proper installation and compliance maintenance with procedures Slick prescribed Magnetos should last the life of the engine before ove~rhaul or replacement is required. for
improper
setting.
Magneto drop out of limits. A. Check magneto-to-enginel timing. service I and B. Inspect 3.
magnetos
TEXTRON-Lycoming
UPPER
per maintenance
information.
I
I
IGNITION
4
C. leads. 4.
Check
spark plugs
Check
pressurization
magneto I hoses
LEFT
and I and
I
SPARK
I
I
I
I
I
I
PLUGS
SWITCHES RIGHT a
I
~hi
5
RIGHT
LEFT
I
MAG,
connections. NOTE Aircraft which are flown at higher altitudes during normal
1
flight operations require more frequent maintenance on ignition components than aircraft flown at lower altitudes.
2
3
I
LOWER
ENGINE
SPARK
FIRING ORDER
PLUGS
1
4
IGNITION WIRING DIAGRAM 4-99
5
2
3-6
FIGURE 74-1 74-00-00
OLDWILLWAYNE
I SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
74-30-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
ENGINE
CONTROLS
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
CHAPTER 76 ENGINE CONTROLS
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
76-EFF/CONTENTS
DATE
PAGE
4-99
1/2BLANK
76-00-00.
3.
4-99
76-1 0-00.
4.
4-99
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
76-00-00 76-10-00
PAGE
SUBJECT
Engine Controls Engine Controls
digging:
3 3
76-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY A\RCRA~T CORPORATION
M20M
76-00-00
ENGINE CONTROLS
76-10-00
ENGINE CONTROLS RIGGING
See
Section
71-00-52
for
Engine
SERVICE AND MAINTENANCE MANUAL
Controls
Rigging/Adjustments
4-99
76-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
76-10-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
C H A PT E R
ENGINE
INDICATING
OLDWILLWAYNE M20M
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
CHAPTER 77 ENGINE INDICATING
LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT
PAGE
DATE
1/28LANK
4-99
77-00-00.
3.
4-99
77-10-02.
4´•
4-99
77-EffectivitylContents
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
77-00-00 77-00-01 77-1 0-00
PAGE
3
General
Ranges Power Indicating
3
3
77-1 0-01
Tachometer.
3
77-10-02
Manifold Pressure
4
77-10-03
77-20-00 77-20-01 77-20-02 77-20-03 7730-00
Fuel Flow Indicating System Temperature indicating
TITlnstrument
Cylinder Head Temperature Oil Temperature. Pressure Indicating
4 4 4 4 4 4
77-30-01
FuelPressure
4
7750-02
Oil Pressure.
4
77-EFF/CONTENTS 4-99
1~BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION GENERAL
77-00-00
7. Turbine inlet
Engine indicating instruments and their sending units, transducers, probes, etc., must be operating properly to prevent engine damage. It is recommended that all engine indicating components be checked at each 100 hour or annual inspection to verify proper operation. Calibrated instruments may be Teeâ&#x20AC;&#x2122;d into the particular systems for a comparison check between them and the aircraftâ&#x20AC;&#x2122;s instruments.
1.BUS LOAD meter. A.
Range-O to
-150
temperature gauge.
A. Green are--100 to B. Red
lin~-2450
2450
F
F.
3. OIL PRESSURE gauge.
A. Green are--55 to 95 PSI B. Yellow
arcs:
(1) Cold (2)
Idle
rang~25 to 55 PSI. MIN.(idle only),
115 PSI MAX.
NOTE The oil pressure relief valve seat may be honed to improve low idle oil pressure. 5. Tachometer.
A. Green
are
"200 to 2575 RPM.
B. Red line 6.
--1300
17500
F.
--17500 F.
8. Red line
A. Normal range
--10.0 to 38.0 Inches
B. Red line
--38 Inches
Hg.
Hg
POWER INDICATING -TACHOMETER
The tachometer indicating system is a fully solid state electronic system that senses engine RPM by magneto rotation speed. A Hall- effect sensor is installed on the magneto bleed source. This sensor is excited by 12 volts DC provided by the tachometer indicator. The "Hall-effect" sensor incorporates a switching transistor that is actuated by north to south pole switching of the main rotor magnet within the magneto. The switch HIGH (+5 VDC) to switch LOW(GRD) creates a square wave frequency output from 0 to 75 HERTZ which is monitored by the electronic tachometer. Because the sensor does not rely on magneto output pulses for generating signals. The magneto may be disabled and still maintain signal output from the hall effect sensor.
The electronic tachometer is a micro-processor controlled stepper motor. The micro-processor receives the square wave frequency signal from the Hall-effect sensor and computes the relative position of the pointer. The micro-processor then generates pulsed signals to drive the stepper to its precomputed position. A DC activated solenoid engages the gear train drive to locate the pointer in its respective position. Upon loss of the +28 VDC input, the solenoid then deactivates and disengages the drive train, thus returning the pointer to below 500 RPM.
start--95 to 115 PSI.
C. Red line--25 PSI
temperature CTIT).
are
8. Manifold pressure gauge.
77-1 0-01
Power plant instruments operate: l)electrically through variations in resistance caused by pressure or temperature changes, 2) by variations In current output caused by varying engine RPM or alternator output, or 3) by pressure from engine induction system,
2. OIL
A. Green
77-10-00
-RANGES
77-00-01
SERVICE AND MAINTENANCE MANUAL
M20M
Power for the tachometer
"575 RPM
indicating system
is
provided
to Pin A of the tachometer. Power requirement is 28 VDC with a typical current drain requirement of 250
Cylinder head temperature gauge (CHT). --~50 to 5000 F. are J;000 F. B. Red line
milliamps.
A. Green
TACHOMETER TROUBLE SHOOTING.
TROUBLE
PROBABLE CAUSE
No permanent or intermittent indicator reading.
C/B out (IGN/CIG LTR)
Reset C/B.
Broken wire
Check
repair wiring.
Replace
instrument.
Faulty Pointer Oscillates
excessively.
REM EDY
instrument.
Mag. timing
too wide between
Retime magnetos.
mags. Isolation resistors at mag. switch increased in resistance value.
4-99
Replace
resistors.
77-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL MANIFOLD PRESSURE
77-10-02
MOONEY AIRCRAFT CORPORATION
M20M
reduce power to 38 In.
Manifold pressure is an indication of engine power affected primarily by throttle setting. The instrument is calibrated in inches of mercury (Hg) and indicates the pressure in the induction air manifold. The RED line of 38 inches Hg.can be exceeded during cold or high humidity weather conditions. Observe the manifold pressure gauge during power settings when weather conditions and encountering these type
Hg.. Manifold
pressure varies
somewhat with pitch attitude in flight and therefore Small oscillations may tuâ&#x20AC;&#x2122;bulent air.
in
occur
flight, particularly
in
CAUTION Do not over boost the engine during any normal operation. (Do not exceed 38 inches manifold pressure).
MANIFOLD PRESSURE TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
Excessive error at existing barometric pressure. Excessive
error
when
engine
is
REMEDY
Pointer shifted.
Replace
Line leaking.
Tighten
Improper damping adjustment.
Adjust damping
Vibration
Replace glass and
instrument.
line connection.
running.
Sluggish
or
jerky pointer
screw.
movement.
Broken
Dull
or
or
loose
cover
glass.
discolored luminous
or
excessive pressure.
Age.
Replace
reseat
case.
instrument.
markings. Incorrect
Moisture
reading.
77-10-03
or
oil in line.
FUEL FLOW INDICATING SYSTEM
Textron
-TEMPERATURE INDICATING
77-20-01
-TIT INSTRUMENT/PROBE
Lycoming
SI
No.
1422A
77-20-02
CYLINDER HEAD TEMPERATURE
The
The turbine inlet temperature ~IT) instrument depicts the temperature of the exhaust gases as they enter the turbocharaer. This temperature is controlled by power setting, aPM and the fuel air ratio entering the combustion chamber of the engine cylinders. The TIT should never exceed 17500 F. continuous operation. The TIT probe is installed at the inlet to the
turbocharger.
cylinder head temperature (CHT) instrument provides the operator with an indication of how hot or cool the cylinders are operating during flight. A resistance type temperature probe is installed in the number 5 cylinder. An optional system provides a probe in each cylinder to provide monitoring of each cylinderâ&#x20AC;&#x2122;s temperature. 77-20-03
sensing probe should be removed, and inspected for proper calibration at the recommended 50 hour inspections.
-O1L TEMPERATURE
Refer to SECTION 79-30-02 77-30-00
NOTE The TIT gauge and
-FUEL PRESSURE
Refer to SECTION 73-20-00 77-30-02
-O1L PRESSURE
Refer to SECTION 79-30-01
The TIT probe should be re-installed to the proper depth in accordance with instructions providedin
77-10-02
(or subsequent
instruction).
Refer to Section 73-30-00 for this data. 77-20-00
Disconnect lines and purge with air.
4-99
OLDWILLWAYNE
CHAPTER
EXHAUST
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
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CHAPTER 78 EXHAUST
LIST OF EFFECTIVE PAGES
CHAPTER SECTION SUBJECT.
DATE
PAGE
78-EFF/CONTENTS
1/28LANK
4-99
78-00-00.
3.
4-99
78-00-00
4.
4-99
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT
78-00-00 78-10-00 78-30-00
78-40-00
PAGE
SUBJECT
General
3
Exhaust
Installation
System System Servicing Periodic ReplacementComponents Exhaust
3
3 4
78-EFF/CONTENTS 1/28LANK 4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
A. Spray engine exhaust system components with suitable solvent (Stoddard Solvent), allow to drain and wipe dry with clean cloth.
GENERAL
78-00-00
The exhaust
a
pipes system’s headers, turbocharger interface components are manufactured by Textron-Lycoming. The turbocharger is manufactured by Garrett-Airesearch (See SECTION 81) Inspections for cracks, burns, etc, are required during each maintenance activity and recommended before each flight. exhaust
and
WARNING Never use
B. Place RH header
exhaust
position
on
LH
procedures:
pipe
This
crossover
pipe
into
NOTE should be conducted when engine is cool.
inspection
Remove all muffler shrouds/shields to
position.
D. Place LH header pipe, fwd 2 cylinders, into on engine exhaust fianges. Ensure that the exhaust gaskets remain in proper position on each
Examine surfaces LOOK FOR LEAKS to exhaust system components for signs of exhaust soot. Look for gray, red or black gas stains at welds, clamps, flanges, etc. Inspect exhaust system for chaffing by cowling, engine mount, cables or any airframe components. Inspect exhaust stacks for burned areas, cracks and looseness.
A.
B.
CAUTION hour inspection is recommended for exhaust system and TIT probe and gauge. Ref. Lycoming SI 1422A.
LOOSE CONNECTIONS Inspect exhaust looseness and proper security.
clamps for cracks,
NOTE
During inspection, particular attention should be given to condition and security of flanges, spot welds, slip joints, and welded areas. C. INTERNAL EROSION
spots for thinning
Examine bends and low
pitting. D. STANDOFFS (PINS) AND HEAT TRANSFER FINS Look for missing or damaged heat transfer pins
or
or
fins. Look for holes at these locations. E.
bulging
METAL FATIQUE Inspect all surfaces for and distrotion and for groups of small cracks.
CAUTION DO NOT mark any surface with lead pencils any carbon-containing markers.
or
F. BAFFLE BREAKDOWN Look inside muffler for broken baffles or tubes. These can restrict the outlet, causing power loss.
EXHAUST SYSTEM SERVICING
repetitive 50
visual
adjacent
cylinder exhaust flange. E. Position exhaust/turbocharger transition pipe assembly onto engine exhaust Range loosely. F. Position 2.0 inch V-Band gasket and 2.0 inch V-Band header and ~nsition pipe. coupling onto LH G. Secure all nuts on exhaust flanges. H. Place exhaust manifold retaining cable in position and attach to clamp adjacent to center ring of crossover pipe. Adjust slack out of retaining cable so crossover pipe is held securely. Cabin heat shroud will be placed into position and secured i. Position Turbocharger onto mounting pad of exhaust transition pipe. Secure bolts and nuts of turbochargerltransition pipe mount. J. Position Bypass valve on to transition pipe with 2.25 inch V-Band gasket and 2.25 inch V-Band clamp. K. Position bypass pipe onto bypass valve at same time tailpipe is attached to turbocharger. L. Secure tailpipe V-Band clamp and bypass pipe. lines to bypass valve from M. Attach oil turbocharger controller, wastegatel etc, and oil and drain lines to turbocharger. Secure all connections. N. Position and secure TIT probe land any other temperature probe connections, if installed). 78-30-00
permit full
inspection.
position
A
use a
flange.
C. Position
engine
A thorough inspection of engine exhaust system will detect any breaks or cracks causing leaks which might result in loss of efficiency, loss of engine power or engine compartment fire. Inspect per following
into position on engine exhaust flanges. Ensure that the exhaust remain in proper position on each cylinder
cylinder gaskets
on
2´• VISUAL INSPECTION OF COMPLETE SYSTEM
(or
1. EXHAUST PIPE HEADERS TO ENGINE
A. Place new exhaust gaskets in engine exhaust flange studs.
solvents exhaust systems.
pencils.
Reference Lycoming Service Instruction No. 1422A later revision) for inspection and installation.
RH
highly flammable
WARNING wire brush or abrasives to clean exhaust systems or mark on system with lead
Never
EXHAUST SYSTEM INSTALLATION
78-10-00
MOONEY AIRCRAFT CORPORATION
M20M
G. HIDDEN DAMAGE internal surfaces that lie
gussets, stiffners, etc. (A borescope t,inspect intemal conditions) H. INSTALLATION TIPS
all under external is recommended
Carefully inspect hidden
only correct parts. DO NOT FORCE FIT any component. Properly align connecting components. Do not reuse gaskets. Insure that attach bolts are properly torqued Exhaust flange stud nuts are to be torqued to 100-110 inch Ibs.
1. CLEANING
To properly inspect exhaust system, components must be clean and free of oil, grease, etc. Clean as follows:
4-99
Install
78-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 7890-00
M20M
However, thorough inspection of all components should be made any time exhaust system is removed from engine for component replacement. The inspection should be made in the interest of preventive maintenance.
PERIODIC REPLACEMENT COMPONENTS
recommended that all exhaust system pipes, and miscellaneous mounting hardware be replaced at engine overhaul time (2000 Hours). It is
clamps
78-40-00
SERVICE AND MAINTENANCE MANUAL
4-99
OLDWILLWAYNE
CHAPTER
OIL
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 79 OIL
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION PAGE
SUBJECT
1/2BLAN K
79-Effectivity/Contents
DATE
4-99
79-00-00
3.
4-99
79-20-00
4.
4-99
79-30-00
5.
4-99
79-30-00
6.
4-99
79-40-00
7.
4-99
79-40-00
8.
4-99
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT
SUBJECT
79-00-00
PAGE
3
General.
79-00-01
Oil Filter Removal
3
79-00-02
Oil Filter Installation
3
79-20-00
Distribution
79-30-00
Indicating
4
79-30-01.
Oil Pressure
6
79-30-02
Oil
7
79-40-00
Temperature
Transducer Test Procedures
7
79-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
-GENERAL
79-00-00
NOTE A new, remanufactured or newly overhauled engine should have oil and filter changed at 25 and 50 hours of operation, then begin the 100 hour ail change interval.
The oil system is a wet sump, pressure type system. The engine sump has a 10 quart (U.S.) capacity, Servicing of the oil quantity is provided through an access door located on top of the engine cowling. The
aircraft
is
delivered
with
the
proper ashless
NOTE Refer to SECTION 5-20-07 for
dispersant oil (Mll-L-22851 or SAE J1899). This oil should be changed at 25 hours or when oil consumption has stabilired. Replacement oil should conform to TEMRON-Lycoming Specifications (Ref. Lycoming SI 1014(*). The routine oil change interval is 100 hours, however if operating in a dusty environment the interval should be more often. C current or subsequent revision) SPLASH Or TO ROQQR VKVE 5mil*
approved
oil
products. OIL FILTER REMOVAL
79-00-01
The engine oil filter, should be replaced each 50 hours and at every oil change (refer to Figure 79-4 for
location).
RoaaFR ~w Bsm0S
oaTn or n~u slrrao Tars
DRAIN
OIL TO SUMP TNRu OIL DRAIN TUBES
PIIIP. QN. a QOHR I81 Na U91e QIIWIWOR
OOMRNOR IOLER SUFT
PUSC(
RODS
PUSH ROO SQC(QIS QN. JPUPH QL 10 SPWH
OIL TO
PISTONS,
P1STON
PINS,
CAMS.
ETC. or
CUE~UFT Me
NoaZ IOPRIP MB
MO M. 1
m.2 BURINO
Rrrm SoPBS
1Y).
KIS eEARINO
BURINO OILWWLR--R~T
MIwM ~VIIHO ASJY.
RPH Mo 3mQlS
MO.RYD WODRVE
TP~PPETS BANK
â&#x20AC;&#x2122;YC NEL RYIP PUSH
RODS
UCUY Ma UOORM
ND
ROCIW LIY
BQIYiS
s~
R
C~ZA OIL PRESSURE UNE
O~YHIY Q MRU 41ROU)TUas
TOEAcHCYLHD. o
at RuP
awDP
TO COOL VALvE
~HWOCNmC
olull a.
WLlh
8180 ~ume
IIRBO ORU( rme
Wm~
OO0O 00
mnn~M omna.
svcme saroc
9C*KWOE RIP
a COQLR
QLSUP
mOeE aa
LUBRICATION DIAGRAM 1.
Remove top and bottom
cowling (see
Section
3.
71-10-00). 2. Cut and
spin
Tighten
safety wire on
filter.
wire filter.
off oil filter and
new
filter
on
prior to flight.
5. Reinstall lower and upper 71-1 1-00).
remove.
6. Connect and connections.
OIL FILTER INSTALLATION
79-00-02
1. Position
Safety
4. Perform leak check remove
3. Loosen the
2.
FIGURE 79-1
secure
cowling (see Section
all electrical and mechanical
adapter.
per instructions
on
filter. 4-99
79-00-00
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 79-20-00
M20M
-DISTRIBUTION
~MOONEY AIRCRAFT CORPORATION
back to the enaine
The oil system on the TIO 540-AF1A engine is internal within the engine (See Figure 79-1) except for turbocharger lubrication, oil cooler routing, and oil pressure transducer plumbing. The turbocharger portion of the system contains pressure hoses, fiteings and check valves to route oil through the turbocharger
case for cooling; (refer to Figure 73-4. The -AF1B engine has a Tee pressure hose to each cylinder head to
79-2, 793 and
fitting
to route
a
oil cool the valve
guides.
ac w
wl
u,
zz
4u
a
L,,,,,
"T
u,
w rr
_JI
dir
~a
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v, w L1! a
i
cnw
cnu
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a\
u
dz
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TURBOCHARGER LUBRICATION SCHEMATIC 79-20-00 4
FIGURE 79-2
4-99 ALSO SEE FIQIRE AS HORIZONTAL
!NEXTI
P
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~1
-1
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(L)
2´•$
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a
8 HIGH PRESSURE OIL PUMP (ACCESSORY HSG>
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a a
m
~p--
Ijj3ro
B C
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m
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1
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7
EoPs
a
C,
E
o~n
o
P
E m
a n
a~ a=s"
OIL TANK
j
p
b
o ~Z u,
r ru o
o
r
I m
9’ CnNTRMIER
(3
za3o DIF~ERENTIAL CONTROLLER
r)
5
SCAVENGE
SP~ n~p’
PUHP (IICCESS. HSG)
S
n c a m
Illr
IIC
2~
DUMPS DIRECTLY INTO ENGINE
r;
cD
3 P, (O 3
K o o
hIgi ~31cP 5
e.
SMM79-2
mS
PRESSURE SCAVENCE<L~W PRESSURE>
R B 7
VENT
3´•n,
8
a
-~’OE s~a
B
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
´•r
"CONTROL LINE"
LEADS TO ii DENSITY
HIGH PRESSURE
(FROM
COWTROLLER,~_ W~
ENGINE OIL
PUMP)
CO~OLLER
WPISTEGATE ncrunToR
CONTROLLER/
URAIN/VENT LINE
OR
(LEADS
"EXHIUST EYPASS
TO ENGINE
CRANKCISE 8
VALVE PISSEMBLY"
SEPARATOR)
TURBOCHARGER LUBRICATION
e9s
FIGURE 79-3
79-2000
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 79-30-00 79-30-01
M20M
MOONEY AIRCRAFT CORPORATION
INDICATING
DIGITAL GAUGES
OIL PRESSURE
Ref.
Oil pressure indicating is provided through a pressure transducer plumbed into the engine oil system, see (Figure 79-1). Pressure variations change the resistance within the transducer and this signal drives the oil pressure gauge located within the cluster
Figure
(27-0258 THRU 27-TEA) adjustment location.
39-48 for OP
1´• Tee in calibrated OP gauge
upstream of transducer.
Adjust Z (zero) and S (span) of Moritz gauge face to concure with value on calibrated gauge. 2.
3. Disconnect leaks.
CalibratedOP gauge.
and check for
gauge.
OIL
TEMP,
TRANSDUCER OIL
FILTER
~r
vAcUuM PUMP
C3IL
PRESS~
Ij
TRANSDUCER
OIL
PRESS,
LINE
TO
TURBOCHARGER WAS TEGATE
DETAIL
A
FWD TOP
OIL PRESSURE TRANSDUCER
79-30-00
4-99
VIEW
FIGURE 79-4
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION 79-30-02
OIL TEMPERATURE
The oil temperature gauge is an electric unit receiving its signal from a temperature bulb in the engine case, located between the oil cooler and the case. The probe resistance changes as the oil temperature changes and this varies the readout on the instrument.
7940-00
To use the unit for troubleshooting, the box is connected to the aircraft harness in the engine compartment, by disconnecting the appropriate transducer electrical connector and connecting the the test hox in its place. Push aircraft Master Switch ON (insure engine gauge circuit breakers are in) and adjust box to approximate pressure desired. The engine gauge should read this
approximate pressure. If pressure reading is correct: 1. Verify Oil pressure to transducer with
TRANSDUCER TEST PROCEDURES CAUTION
This unit is for troubleshooting only. DO NOT ATTEMPT TO CALIBRATE WITH THIS UNIT.
The Transducer Test Box, P/N GSE 030036, used to simulate fuel and oil pressures in the M20M.
can
mechanical
pressure gauge. a.
be
ledoMyenooM
must be used on GSE 6301036 Transducer Test Box when Kulite or Partriot transducers are installed. Contact MAC Service Parts for status of these adapters.
If
correct--probable
failure is transducer.
b. If incorrect-troubleshoot If pressure condition:
NOTE
An
SERVICE AND MAINTENANCE MANUAL
M20M
1.
appropriate wiring adapter
reads
incorrectly,
Sigma Tek gauge -S/N
2. Moritz gauge a.
Check
compartment
oil system. zero
or
pegged
27-0001 thru 27-0257.
S/N 27-0258 thru 27-TEA.
wiring
for
continunity
between
engine
connector and cluster.
b. If wiring is correct--probable failure is in gauge module or cluster.
4-99
7930-02
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
BLANK
79-40-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
STARTING
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
CHAPTER 80
STARTING
LIST OF EFFECTIVE PAGES
CHAPTER SECTION
PAGE
SUBJ ECT
DATE
1/2BLANK
4-99
80-00-00
3.
4-99
80-1 0-00.
4.
4-99
80-Effectivity/Contents
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
80-00-00
PAGE
3
General
Troudleshwting:
3
80-00-01
starter
80-00-02
Starter Maintenance
80-00-03
Starter Removal.
3
80-00-04
Starter Installation
3
80-00-05
Starter Brushes
3
80-10-00
3
3
Cranking
80-EFF/CONTENTS 4-99
1/2BLANK
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION -GENERAL
80-00-00
the
ignition
switch
placed in the "start" supplied through the main bus to
position, current is energize the starter solenoid battery to the starter.
is
which in tum connects the
1. Before
from
8.
STARTER MAINTENANCE
and Inspect TEXTRON-Lycoming
No lubrication is 2. Lubrication starter motor except at overhaul.
per and
required
on
the
CAUTION Do not clean the starter in any degreasing tank or grease dissolving solvents. Avoid excessive lubrication. Use only kerosene or Varsol.
cowling land
2. Disconnect electrical
wiring
lower if
desired),(See
from starter terminals.
3. Remove nut and washer from studs
on
O-ring
from
STARTER BRUSHES
The starter brushes should slide freely in the holder and make full contact on the commutator. The brushes should be replaced when they have wom to 1/4 inch in length. Brush tension should be 32 to 40 ounces as measured with a spring scale hooked under the brush spring and pulled in a straight line opposite the force exerted by the spring. Read the tension just as the spring leaves the brush. 80-10-00
adapter
mounting pad. 4. Remove starter and
ground straps connections for tightness. O-ring on starter flange. starter on mounting pad.
CRANKING
The starter solenoid is located on the cabin side of the firewall. The solenoid is energized by placing the ignitionlmagneto switch in the start position. Battery current is then directed to the starter. The aircraft are equipped with a "START POWER" annunciator light. This light illuminates "RED" when the starter switch is in start position or when the starter switch or starter solenoid has malfunctioned and the starter is engaged while the engine is running. This malfunction should be corrected before the engine is started again.
STARTER REMOVAL
1. Remove upper SECTION 71-10).
dirt
attaching nuts and washers. Torque nuts 220.0 to 260.0 inch Ibs. Connect electrical wiring to starter terminals. Install cowling.
80-00-05
service starter Service Information
Overhaul Manual.
80-00-03
or
new
4. Position
7.
f.
rust corrosion
surface of starter motor.
2. Check all
3. Install
6.
1. Refer to SECTION 24-39-04.
80-00-02
installation, clean any
mounting
5. Install
STARTER TROUBLESHOOTING
80-00-01
-STARTER INSTALLATION
80-00-04
The airplane is equipped with a 24 volt starter supplied with the engine package. The starter is located on the engine case at the front of the engine.
When
SERVICE AND MAINTENANCE MANUAL
M20M
adapter,
4-99
80-00-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
BLANK
4-99
80-10-00
OLDWILLWAYNE
C H A PT E R
TURBINES
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
CHAPTER 81 TURBINES
LIST OF EFFECTIVE PAGES
CHAPTER SECTION DATE
PAGE
SUBJECT.
1/2BLANK
4-99
81-00-00
3.
4-99
81-10-02.
4.
4-99
81-30-00.
5.
4-99
81-40-00
6.
4-99
81-EFF/CONTENTS
TABLE OF CONTENTS CHAPTER
SECTION
81-00-00 81-10-00
81-10-01
81-10-02 81-20-00 81-30-00 8130-01 81-40-00
PAGE
SUBJECT
SUBJECT
3
General Control
Turbocharger Turborcharger Control System (Airesearch) Altemate Air System-Turt~ocharger Operation Turbocharger Troubleshooting Exhaust System Servicing Inspection -’V’ Band Clamp Periodic Replacement Components
3 3 4 4
5 5 5
81-EFF/CONTENTS 1/2BLANK 4-99
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
81-10-00
-TURBOCHARGER CONTROL
81-10-01
-TURBOCHARGER CONTROL
GENERAL
81-00-00
TURBOCHARGER OPERATION
turbocharger increases the power output and efficiency of the engine by supplying compressed air to the intake manifold. The engine exhaust is routed to the turbine wheel of the turbocharger assembly. The
SERVICE AND MAINTENANCE MANUAL
SYSTEU--(AIRESEARCH) turbocharger output is controlled coordinated action of the Density/Differential Controller system when set up properly.
The
Th,
amount of exhaust gas passing over the turbine wheel is controlled by a waste gate assembly. Exhaust gas passing over the turbine wheel causes the compressor, mounted on the same shaft, to rotate. Ambient ram air, supplied through an air intake on the lower cowling, is filtered and routed to the compressor where it is compressed and delivered to the engine. As engine power is increased, the Row of exhaust over the turbine wheel also increases, resulting in a proportionate increase in the speed of the rotating assemblies and
through Pressure
CAUTION
mandatory that the turbocharger system properly adjusted prior to operation. See SECTION 71-00-52 for engine set up procedures,
It is
be
TURBOCHARGER OVERBOOST PROTECTION The engine incorporates overboost protection within the pressure controller. See SECTION 71-00-52.
turbocharger output.
Refer to Airesearch and TUCTRON-Lycoming Service and Maintenance Manuals for detailed maintenance data.
aWllln Y~WIRU
mucur m~u uur lue~r
numr~
coauml RI#UI( 11II DIOI~EUU*
ol~n
C~Y
II(LIIUROLO
I
’1 OIL lN
ENGIM~ Rmrm un e~MI
~UUYII
W YUIO wm ~I*
,mu VUVE conn# rtmun
I ’P- i,,,,, ´•IKWI~I
s~
IIHn I´•IWOL´• ~IIIY´•(l
ocL 1~ ~o ´•´•u~´• (CICIU
UUY´•LI
uuur~
Turbocharger and DensitylDifferential Control System
TURBOCHARGER SCHEMATIC
4-99
FIGURE 81-1 81-00-00
OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL
81-10-02
M20M
ALTERNATE AIR SYSTEM TURBOCHARGER OPERATION
than primary air so less power will be available at normal throttle settings.
The turbocharger system will continue to operate when the primary air source is obstructed. An engine automatic alternate air system is provided to allow air from inside the cowling to pass through the compressor and into the engine. This air is wanner
81-20-00
NOTE
Inspection of the induction system and turbocharger assembly should be conducted after any obstruction of the primary air source prior to the next engine operation.
TURBOCHARGER TROUBLESHOOTING
TROUBLE
PROBABLE CAUSE
Excessive noise
Engine will
MOON EY AIRCRAFT CORPORATION
or
vibration.
not deliver rated
REMEDY
Improper bearing lubrication.
Supply required oil pressure. Clean or replace oil line. If trouble continues, remove turbocharger and return to approved overhaul station for overhaul or repair.
Leak in engine intake manifold,
Tighten
Clogged
or
exhaust
manifold system.
loose connections, or replace manifold gaskets as necessary.
Clean all
ducting.
power.
Foreign material lodged in compressor impeller or turbine.
Remove turbocharger and return to approved overhaul station for overhaul or repair.
Excessive dirt
Service engine induction air filter and check for leakage. Remove turbocharger a~d retum to approved overhaul station for overhaul or repair.
buildup
in
compressor.
Leak in engine intake of exhaust manifold.
Tighten
Rotating assembly bearing seizure.
Remove turbocharger and return to approved overhaul station for overhaul or repair.
Compressor blades chipped, bent or missing.
Remove turbocharger and return to approved overhaul station for overhaul
loose connections, or replace manifold gaskets as necessary.
or
Impeller binding
Induction leaks.
or
or
frozen.
exhaust system
Compressor blades chipped, bent or missing,
Engine surges
or
smokes.
Oil leaking into turbine wheel chamber,
Clogged
81-10-02
breather.
4-99
repair.
Remove turbocharger and return to approved overhaul station for overhaul or repair. Perform leak checks. Remove turbocharger and return to approved overhaul station for overhaul or repair. Remove
turbocharger and
approved overhaul or repair.
return to station for overhaul
Check breather for restriction to air flow.
MOONP/ AIRCRAFT CORPORATION
81-30-00
OLDWILLWAYNE M20M
EXHAUST SYSTEM SERVICING
TORQUE PROCEDURES
Torque V-Band coupling to 40 Lb.-ln. Tap coupling lightly around circumference with a non-metallic hammer to equalite band tension. Re-torque coupling to 60 Lb.-ln. and tap band again. Re-torque to a final value of 55 to 65
1. REFER TO SECTION 78-30-00 2. VISUAL INSPECTION OF COMPLETE SYSTEM
A thorough inspection of the engine exhaust system will detect any breaks or cracks causing leaks which might result in the loss of optimum turbocharger
efficiency and engine power. per SECTION 78-30-00. 81-30-01
Inspect
SERVICE AND MAINTENANCE MANUAL
Lb.-ln.
exhaust system
81-40-00
INSPECTION MULTI-SEGMENT "V" BAND CLAMP
PERIODIC REPLACEMENT COMPONENTS
It is recommended that all e~haust system pipes, clamps and miscellaneous mounting hardware be replaced at engine overhaul time (2000 Hours). However, a thorough inspection of all components should be made any time the exhaust system is removed from the engine for component replacement. The inspection should be made in the interest of preventive maintenance.
1. Using crocus cloth, clean outer band of the multisegment’V" band clamp. Pay particular attention to the spot weld areas on the clamp. 2. With clamp in place and properly torqued:
A. Inspect outer band in the area of the spot welds for cracks (See Figure 81-2). If cracks are found, replace clamp with new multi-segment ’Y" band clamp.
NOTE When replacement is required, install new "V" band clamp over the exhaust flanges and
torque according
t
following procedures.
IYPICAL
SPOT WELD AREAS
"V" BAND CLAMP SPOT WELD AREA CHECK
FIGURE 81 -2
4-99
81-30-00
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
BLANK
81-40-00
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
CHAPTER
CHARTS
OLDWILLWAYNE MOONE/ AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
CHAPTER 91 ELECTRICAL WIRING DIAGRAMS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION SUBJECT.
DATE
PAGE
1 RBLANK
91-Effectivity/Contents
.......699
91-00-00.
3.
699
91-00-02.
4.
4-99
91-00-02.
5.
.......699
91-20-00.
6.
699
91-20-00.
7.
.....699
91-20-00.
8.
4-99
91-20-01.
9 thru 26
4-99
91-20-02
27 thru 40
4-99
91-20-03
41 thru 54
4-99
91-30-00
55
699
TABLE OF CONTENTS
CHAPTER SECTION
SUBJECT
´•91-00-00 91-00-01
91-00-02 91-00-03
91-20-00
91-20-01
SUBJECT
General
Ele$icai Systems I;otes Identification
System Wiring List Abbreviations-Equipment Electrical System Hardware Charts
PAGE
3 3 4 5 6
27-0002thnl 27-0052
9
27-0053thru 27-0107
9
91-20-02
27-0001, 27-0108 thru 27-0239
27
91-20-03
27-0240thN 27-TEA
41
91-30-00
Electrical System Schematics
55
91-EFF/CONTENTS 1RBLANK 4-99
OLDWILLWAYNE -Electrical
GENERAL
91-00-00
The electrical system hardware lists and related schematics are sequenced in this section by serial number effectivity. The chapter is divided into the following sections: 91-00-01
ELECTRICAL SYSTEMS SCHEMATICS NOTES
1. All electrical wiring, assemblies, and installtions must be in accord with FAR 43 and AC 43.13-1( 2.
All
splices
be
must
â&#x20AC;&#x2122;1AMP"
disconnect
or
equivalent. 3. All circuit breakers
are
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
Systems
Schematic Notes
-Wiring Identification System -Electrical System Hardware Charts (By Effectivity) -Eiectrical Schematics (By Effectivity) 9. Wires denoted by twisted counter clockwise with wraps per foot.
a
symbols to be minimum of three (3)
ground through frame (no wires). 11. All knife disconnect splices to be insulated with PVC105 and securely string tied with airtex no. 417 10. "Fâ&#x20AC;&#x2122; denotes
cord.
trip-free.
Spec. MS25036 (or equivalent or they must be soldered.) 5. All terminals must be preinsulated or must be insulated with "Ampsulation" (or equivalent), 6. Wires without dash numbers are furnished by the manufacturer and are included with the equipment.
12. All wire sizes
4. All terminals are
are
minimum sizes
acceptable.
necessary for various manufacture and changes configuration interconnecting bus using no. 2170 tubular braid covered with PVC105/5/16" (both Alpha Wire Co.) and terminated with AMP terminals of appropriate sizes. 13. Use 913127 bus bars
as
indicates a knife disconnect. symbol Optional equipment may be installed as required.
7. The 6.
35108 PVC
105/
Terminal 5/16"
170
Tuk>uCar
o 327218 AmpsLilat;on 3 ~1 9 F~ Terminal
EXAMPLE
FIGURE 91-1
4-99
91-00-00
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
WIRING IDENTIFICATION SYSTEM
9190-02
Mooney Aircraft Corporation wiringlequipment system originally depicted a typical Wire Identification Number M-PA03A18. This g-character number, app\icab\e to 800310 drawing only, is composed of five functional groups, each of which communicates certain specific information. These functional groups are as follows:
The
I
as
Aircraft Type (M20M) M- first letter and depict Circuit Function PA first two letters Wire Sequence 03 second set of numerals A- single letter in the series Configuration Wire Size 18 last two numerals in the series
CODE/COMPONENT
or
SYSTEM
(CIRCUIT FUNCTION)
MA/Miscellaneous MB/Miscellaneous MC/Miscellaneous MO/Miscellaneous ME/Miscellaneous MIG/Miscellaneous MM/Miscellaneous MP/Miscellaneous
CB/Defroster Blower CC/Cowl Flaps Electric Rudder Stablizer CV/Stand-by Vacuum
CF/Wing Flaps
CR/Trim CT/Trim
Ammeter Tum Coordinator Cylinder Head Temperature Outside Air Temperature Carburetor Air Temperature DF/lnstruments Fuel Quantity DG/lnstruments Cluster Gauge DH/lnstruments Oil Temperature DJ/lnstruments Oil Pressure DWlnstruments- Fuel Pressure DUlnstruments- Tachometer DM/lnstruments Hour Meter DN/lnstruments- Pressurization DP/lnstruments Pitot Heat DR/lnstruments- Turbine Inlet Temperature
DA/lnstrumentsDB/lnstrumentsDC/lnstruments DD/lnstruments DE/instruments
DS/lnstruments DT/lnstruments DU/lnstrumentsDV/lnstruments DW/instruments
NF/Fuel NP/Fuel
PS/Power
SE/Speed
Cigar Lighter Clock Light Electric Clock
Microphone Marker Beacon Propeller De-ice
Fuel Pump Primer
Starter
(Input
Control)
Brake
SP~Speaker
Compressor Discharge Temperature Exhaust Gas Temperature
VB/Vent Air Blower
Manifold Pressure
WANVarning System WE/Warning Engine WE/Warning System WF/Warning System WVWarning System WN/Warning System WSIWarning System WT/Warning System WV/Warning System WW/Warning System WD/Warning System
Fuel Flow VSI
Locator Transmitter
FON/Phones
JM/lgnition Magneto
LB/Lighting Rotating Beacon (Anticollision Light) LC/Lighting CabinLights LULighting Landing Lights LN/Lighting Navigation Lights LP/Lighting Instrument Placard Lights LR/Lighting Recognition Lights LS/Lighting Instrument Strobe Lights LT/Lighting -Taxi Lights
91-00-02
Plug
RE/Radio Blower
Gear Controls Electroluminescence
ELT/Emergency
Power Radio Circuits
Auxiliary
PAIPower Alternator (output Control) PB/Power Battery (Output Control) PG/Power Generator (Output Control)
EG/Electric Gear
EULighting
800310 DRAWING
4-99
Alternator Voltage Warning Boost Gear Position Warning Fuel Pressure
Landing Light Pressurization
StallWarning Press-to-Test Vacuum Warning Alternate Air Starter Power
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
The Mooney Aircraft Corporation wiring/equipments identification system used in current production aircraft deletes the Model Number annotation. The purpose of this is to standardize the identification of a system functionlcomponent for all model of aircraft. The functional groups are basically the same as earlier identification numbers. These follows:
new
functional groups
apply
CR
First two/three letters
04
First set of numerals
to master schematic
drawing
800304. The
new
functional groups
are as
Circuit Function Wire
Sequence
letter in series Configuration Wire Size Last two numerals in series
Single
A 20
CODE/COMPONENT ACT/SWITCH ACTUATOR BS/RELAY BASE BUS/BUSS BARS C/CAPACITORS CB/DEFROSTER BLOWER CC/COWL FLAPS, ELECTRIC cFnnrlNe FLAPS CL/CLAMPS CM/CURRENT MONITOR CR/RUDDER TRIM CT/STABILIZER TRIM CV/STANDBY VACUUM D/DIODES DA/AMMETER DB/TURN COORDINATOR DC/CHT DD/OAT
DF/FUEL QUANTITY DG/ENGINE INSTRUMENTS DH/OIL TEMPERATURE DJ/OIL PRESSURE DWFUEL PRESSURE
or
SYSTEM
(CIRCUIT FUNCTION)
800304 SCHEMATIC DRAWING
DUELECTRIC TACHOMETER DM/HOUR METER DP/PITOT HEAT DR/TIT DT/EGT DV/FUEL FLOW
DO/LANDING. GEAR, ELEC. ELT/ELT F/FUSES FH/FUSEHOLDER FON/PHONE JM/IGNITION, MAGNETO ULIGHT BULBS LB/BEACON LENS/ANNUNCIATOR LENS LH/LAMP HOLDER LVLANDING LIGHTS
LN/NAVIGATION LIGHTS LP/PANEL LIGHTS
LR/RECOGNITION LIGHTS LS/STROBE LIGHTS
PUPLUGS, ELECTRICAL PS/START POWER R/RESISTORS RE/RADIO BLOWER RC/RECEPTACLES, ELECTRICAL RURELAYS SB/SPEEDBRAKE SPKRISPEAKER SW/SWITCHES VR/VARISTOR WS/STALL WARNING WTIANNUNCIATOR WARNING
LT/TAXI LIGHTS
CODE/COMPONENT OR SYSTEM CIRCUIT FUNCTION LEGEND AC-AIR CONDITIONER AH-ARTIFICIAL HORIZON AT-ACTUATOR, SWITCH AV-AVIONICS
800383 SCHEMATIC DRAWING
DF-INSTRUMENTS FUEL QUANTITY DG-INSTRUMENTS ENGINE DH-INSTRUMENTS OIL TEMPERATURE DI-DIODES DJ-INSTRUMENTS OIL PRESSURE DK-INSTRUMENTS FUEL PRESSURE Dr-INSTRUMENTS TACHOMETER, ELECTRIC DM-INSTRUMENTS HOUR METER DN-INSTRUMENTS- PRESSURIZATION DP-INSTRUMENTS PITOT HEAT DR-INSTRUMENTS -T I T DS-INSTRUMENTS COMPRESSOR DISCHARGE
BR-CIRCUIT BREAKERS BS-RELAY BASE BU-BUS BARS
CA-CAPACITORS CB-DEFROSTER BLOWER CC-COWL FLAPS CD-PC DUMP CF-WING FLAPS CL-CLAMPS CR-RUDDER TRIM CT-ELEVATOR TRIM CV-STAND-BY VACUUM DA-INSTRUMENTSDB-INSTRUMENTS DC-INSTRUMENTS DD-INSTRUMENTS DE-INSTRUMENTS
MA/AUXILIARY POWER MB/AVIONICS MASTER MC/CIGAR LIGHTER ME/CLOCK MI/MICROPHONE MP/PROPELLER DE-ICE NF/BOOST PUMP PA/ALTERNATOR POWER PB/BATTERY POWER
DT-INSTRUMENTS DU-INSTRUMENTSDV-INSTRUMENTS DW-INSTRUMENTS
TEMP. E G T MANIFOLD PRESSURE FUEL FLOW ENGINE VACUUM
EG-GEAR, ELECTRIC
AMMETER TURN COORDINATOR CYLINDER HEAD TEMP. OUTSIDE AIR TEMP. CARBURETOR AIR TEMP.
EL-ELECTROLUMINESCENCE ET-EMERGENCY LOCATOR BEACON
4-99
91-00-02
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
CODE/COMPONENT OR SYSTEM CIRCUIT FUNCTION LEGEND FA-ALT-EMER (FRENCH) FH-FUSE HOLDERS FN-PHONES FU-FUSES FW-ALT-EMER FIELD (FRENCH)
800383 SCHEMATIC DRAWING
(conâ&#x20AC;&#x2122;t.)
NE-FURL ENRICHMENT NF-FUEL PUMP NP-FUEL PRIMER NS-FUEL COLD START
GD-GROUND
PA-POWER, ALTERNATOR PB-POWER, BATTERY PG-POWER, GEN. (OUTPUT
HS-HORIZNTAL SITUATION INDICATORO
PL-PLUGS
CONTROL)
PS-POWER, START
JE-IGNITION, ELECTONIC JM-IGNITION, MAGNETO JV-GNITION, VIKBRATOR
RE-BLOWER, RADIO RC-RECEPTACLES RL-RELAYS RS-RESISTORS
LA-LIGHT BULBS LB-BEACON, ROTATING LC-LIGHT, CABIN LE-LENS, ANNUNCIATOR LG-LIGHTS, LOGO LH-LAMP HOLDER LI-LIGHT, ICE LL-LIGHT, LANDING LN-LIGHTS, NAVIGATION LP-LIGHTS, PANEL LR-LIGHTS, RECOGNITION LS-LIGHTS, STROBE LT-LIGHTS, TAXI
SA-STAND-BY ALTERNATOR SB-SPEEDBRAKE SP-SPEAKER SW-SWITCHES
VB-VENT, AIR BLOWER VC-VOLTAGE CONVERTER VR-VARISTOR WA-WARNING, ALTERNATOR WE-WARNING, BOOST PUMP WC-WARNING, PROP DE-ICE WD-WARNING, POWER START WE-WARNING, ELECTRIC GEAR WF-WARNING, FUEL QUANTITY
MA-AUXILIARY POWER MB-RADIO, MASTER MC-CIGAR LIGHTER ME-CLOCK, ELECTRIC MH-MISCELLANEOUS, ANTI-ICE MJ-MISCELLANEOUS, JUNCTION BOX MK-MICROPHONE MM-MISCELLANEOUS, MARKER BEACON MO-PROP OVERSPEED MP-PROP DE-ICE MS-MISCELLANEOUS, RADIO-SPEAKER MW-MISCELLANEOUS, RADIO-WARNING
ABBREVIATIONS
91-00-03
The abbreviations to the electrical the computer.
WG-WARNING,
TACHOMETER
WH-WARNINGI CHIP DETECTOR
WK-WARNING, FUEL PRESSURE WL-WARNING, CANOPY LOCK WM-WARNING, MASTER WN-WARNING, PRESSURIZATION WP-WARNING, PITOT HEAT
WS-WARNING,
STALL
WT-WARNING, ANNUNCITOR WV-WARNING, VACUUM WW-WARNING, ALTERNATE AIR
EQUIPMENT LIST
system hardware charts
are
necessary due to space limitations in the fields of
Airspeed- A/S
Glareshield- Glrshld
Remote- Rem
Alternate- Altn
Landing- Ldg
Resistor- Res
Left
Rheostat
Circuit Breaker
CM. Bkr.
or
L
Rheo
C/B Console- Cnsl
Lights-
Control- Cntrl
Panel- Pnl
Safety- Sfty
Coordinator- Coordtr
Pilot- Pit
Selector- Sel
Cylinder- Cyl
Placard- Plod
Switch- Sw
Down- Dn
Radio- Rad
Transducer- XDCR
Electric- flee
Receptacle- Recpt
Transmitter- XMTR
Flight-
Regulator- Regltr
Transistor- XSTR
Fit
Lts
Right-R
Warning- Wrn 91-00-03
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
9190´•00
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL SYSTEM HARDWARE CHARTS
Refer to the Electrical Schematic (located in the envelopes at the back of this manual) that depicts the Serial Number configuration of the aircraft being senAced. The S/N’s vs. applicable master schematics are shown below: AIC SERIAL NUMBER DRAWING NUMBER (SCHEMATKC NUMBER) 27-0002 thru 27-0052
800310
(M1) (G)
27-0053 thru 27-0107
800310
(M2) (H)
27-0001,27-01 08 THRU 27-0137
800304
(Mi) (Revision E)’ (2 Sheets)
27-0138 THRU 27-0141 (Sheet 1 of2) (Sheet 2 of 2)
800304 800304
(MZ)(Revision (M2) (Revision
27-0142 THRU 27-0180, 27-0182, 27-0183 (Sheet 1 of 2) (Page 3.1.1.3) (Sheet 2 of 2) (Page 3.1.2.3)
800304 800304
(M3) (Revision G) (M3) (Revision H)
1) (Page 3.1.1.4)
800304
(M4) (Revision W)´•
27-0193 THRU 27-0208 (Sheet 1 of 1) (Page 3.1.1.5)
800304
(M5) (Revision W)’
27-0209 THRU 27-0215 (Sheet i of 1) (Page 3.1.1.6)
800304
(M6) (Revision X)’
27-0216 THRU 27-0220 (Sheet 1 of 1) (Page 3.1.1.7)
800304
(M7) (Revision 2)"
27-0221 THRU 27-0231 (Sheet 1 of 1)(Page 3.1.1.8)
800304
(M8) (Revision 2)"
27-0232 THRU 27-0239 (Sheet 1 of 1) (Page 3.1.1.9)
800304
(M9) (Revision AA)’
27-0240 THRU 27-0246 (Sheet 1 of 1) (Page 3.1.1.1)
800383
(M1) (Revision G’
27-0247 THRU 27-0257 (Sheet 1 of 1) (Page 3.1.1.2)
800383
(M2) (Revision H)*
27-0258 THRU 27-TEA (Sheet i of 1) (Page 3.1.1.3)
800383
(M3) (Revision M)*
27-0181, 27-0184 THRU 27-0192
(Sheet
i of
These schematics address different serial numbered aircraft. Make sure the for the S/N aircraft being serviced.
applicable
schematic is
being
used
The correct Vendor and/or Part Number will be depicted where the applicable electrical equipment identifier is shown on the following hardware charts. Order replacement or repair Part Numbers for electrical components from the following Electrical System hardware charts that are applicable to the aircraft model SM being worked on. 91-20-01
ELECTRICAL SYSTEM HARDWARE CHART
800310 SCHEMATICS
91-20-02
ELECTRICAL SYSTEM HARDWARE CHART
91-20-03
ELECTRICAL SYSTEM HARDWARE CHARTS NOTE 800305 drawing. included in the S 8 M manual due to the
System Schematics
are
depicted
on
4-99
Pages
9 thru 26.
800304 SCHEMATICS
Pages 2’1 thru 40.
800383 SCHEMATIC
Pages 41 thN 54.
They are "A" size drawings and quantity of pages required.
ate
not
91-20-00
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
BLANK
91-20-00
4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION M20M SERVICE AND MAINTENANCE MANUAL ELECTRICAL EQUIPMENT CHART 91-20-01
-ELECTRICAL EQUIPMENT HARDWARE CHART
S/N 27-0001 THRU 27-0052, SCHEMATIC DRAWING NO. 800310 -(MI) S/N 27-0053 THRU 27-0107 SCHEMATIC DRAWING NO. 800310 (M2)
CODE NOTES
DESCRIPTION
VENDOR
M-CB1O1A M-CB1OPA M-CB103A M-CB104A
C/B, DEFROST BLOWER SWITCH, BLOWER MOTOR MOTOR, BLOWER PLUG,PPIN /SOCKETS RECPT, 2 PIN.
KLIXON CHERRY. MOONCI.
M-CBlOjA
AMP AMP AMP AMP
/PINS M-CC1O1A M-CC102A M-CC103A M-CC104A
M-CClOjA
M-CClOiSA M-CdlOjA M-CC108A M-CC1OSA M-CC11OA
M-CClliA
M-CClliA
SWITCH,
COWL FLAP ACTUATOR, COWL FLAP
SWITCH, OPEN LIMIT IACTUATOR
SWITCH, CLOSE
ilMiT
IACTUATOR PLUG,SPIN ICLAMP RECEPTACLE, 9 PIN: ICLAM P C/B, COWL FLAP IND INDICATOR, COWL FLAP PLUG,4PIN /CLAMP RECEPTACLE, 4 PIN: /CLAMP POT., COWL FLAP POSITION
VARISTOR
M-CF1O1A M-CF1 02A M-CF103A
C/B, TRIM/FLAP IND INDICATOR, TRIM/FLAP PLUG, INDICATOR /CLAMP /LOCK RETAINER POTENTIOMETER,
M-CFlOjA
RECEPTACLE,
4
/CLAMP
C/B, FLAP ACTUATOR
M-CF108A M-CF1OSA M-CF11OA
FLAP SWITCH FLAP ACTUATOR SWITCH, UP LIMIT
M-CFlliA
/ACTUATOR SWITCH, DOWN /ACTUATOR
4-99
E51-50B 640317-501 1-480318-0 60619-1 1-480319-0 60620-1 7277-2-5 880052-517 880050-501 1SE1-T JE-5 1SE1T JE-5 206708-1 206966-1 206705-2 206966-1 7277-2-1 800242-505 206060-1 206062-1 206153-1 206062-1
KLIXON MOONN.
7277-2-1 800242-501 DAl 5S DA5121 0-1 DA51220-1 WA2-G056S502UA 206060-1
CUTLER HAMMER MOONEY. MICRO SWITCH MICRO SWITCH MICRO SWITCH MICRO SWITCH
ilMli
7277-2-5
WA2-G056S502UA
AMP. AMP AMP. AMP. KLIXON
PIN:
PART NO.
ALLEN-BRADLEY AMPHENOL AMPHENOL GE
ALiEN:sRADiCI’
FLAP’ P6SIT’ION
PLUG,4PIN /CLAMP
M-CF1OGA
AMP.
RECEPTACLE, 9 PIN. PLUG,SPIN
M-CC113A M-CC114A M-CC1ISA
M-CF1 04A M-CF105A
KLIXON MOONDI. MOONEY. MICROSWITCH MICRO SWITCH MICRO SWITCH MICRO SWITCH AMP. AMP. AMP. AMP KLIXON MOONN. AMP AMP AMP.
C/B, COWL FLAP
1~
126-219 126-222 V47ZA05
206062-1 206153-1 206062-1 7277-2-5
8906K3149 750105-501 V3-1 JV-5 V3-1 JV-5
91-20-01
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
M-CR1O1A
C/B, RUDDER TRIM SWITCH, RUDDER TRIM.
KLIXON MOONEY. AMP
M-CR1OPA M-CR103A M-CR104A
M-CfilOjA M-CR1OGA
M-CdlOjA
M-CR108A M-CR1OSA
M-CRlljlA M-CRlliA
M-CRlliA M-CR113A M-CR114A M-CR115A M-CR1IGA M-CT1O1A M-CT102A
PLUG,3PIN
AMP AMP AMP
/SOCKETS RECEPTACLE, 3 PIN. /PINS SWITCH, ilMli /ACTUATOR PLUG,2PIN /SOCKETS RECEPTACLE, 2 PIN: /PINS
MICRO MICRO AMP AMP AMP
AMP MOONEY. MICRO MICRO AMP. AMP. AMP. AMP. ALLEN BkAbLEY KLIXON MOONEY. AMPHENOL AMPHENOL
MOTOR, RUDDER TRIM SWITCH, LIMIT /ACTUATOR PLUG,4PIN ICLAMP RECEPTACLE, 4 PIN: /CLAMP POTENTIOMETER, RUDDER TRIM C/B, RUDDER TRIM INDICATOR INDICATOR, RUDDER TRIM RECEPTACLE, 9 PIN. PLUG,SPIN
POTENTIOMETER, TRIM POSITION PLUG,4PIN /CVAMP
ALLEN-BRADLN AMP. AMP AMP. AMP
C/B, STANDBY VACUUM. CLUTCH, STANDBYVACUUM
MOONEY. AIRBORNE
/CLAMP M-CT103A M-CV1O1A M-CV1OPA M-CV103A M-DA1O1A M-DA102A M-DA103A M-DA104A M-DA104B M-DA105A M-DA1OGA M-DA107A M-DA108A M-DA1OSA M-DA1IOA M-DA111A M-DB1O1A M-DB102A
M-DB103A
RECEPTACLE,
4 PIN.
10
7277-2-5 880052-519 1-408303-0 6061 9-1 1-480305-0 60620-1 V3-1
JV-26 1-48031 8-0
60619-1 1-480319-0 60620-1
880050-503 V3-1 JV-26 206060-1 206062-1 206153-1 206062-1
WA2-G056S502UA 7277-2-1
800242-503 126-219 126-222
WA2-G056S502UA 206060-1 206062-1 206153-1 206062-1 930023-247
28C21 4CW 1 N2483/1 N5060
DIODE ALT
GE
SHUNT, RIGHTALTERNATOR
EMPRO KLIXON KLIXON EMPRO EMPRO KLIXON KLIXON EMPRO KLIXON KLIXON KLIXON KLIXON
RIGHT ALT SHUNT C/B RIGHT ALT SHUNT C/B LOAD SHUNT. LOAD SHUNT (OPT) LOAD SHUNT C/B LOAD SHUNT C/B SHUNT LEFT LEFT ALTERNATOR C/B. LEFT ALTERNATOR C/B C/B, AMMETER C/B, AMMETER
ALTERNAT’OR’(OPT)
C/B, TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR TURN COORDINATOR
KLIXON UNITED INSTRUMENTS ASTRONAUTICS ELECTRO GYRO CORP
(ALT) (ALT)
PLUG.
/CABLE CLAMP
91-20-01
PART NO.
4-99
37-20-GE MLA-70A-1 OOMV 7277-2-1 7277-2-1 MCA-~05A-100MV MLB-210A-100MV 7277-2-1 7277-2-1 MLA-70A-100MV 7277-2-1 7277-2-1 7277-2-1 7277-2-1 7277-2-2 9013 CODE N.5 303990-028MSC
1394T100-32 MS3106A-1 0SL-3S MS3507-4A OR (-48)
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONN AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
M-DC1O1A
SWITCH
M-DdlOiA
/KNOB. PLUG, 28 /CLAMP
M-DC103A
(OPT),
CYL HEAD TEMP.
GRAYHILL RAYTHEON AMP. AMP.
PIN:
RECEPTACLE, 28 PIN
AMP. AMP
/CLAMP M-DC104A M-DC1OSA
M-DC1OGA M-DC107A M-DC1OBA M-DC1OSA
PART NO.
VENDOR
CYLINDER CYLINDER CYLINDER CYLINDER CYLINDER PROBE, CYLINDER
PROBE, PROBE, PROBE, PROBE, PROBE,
#1 #2 #3 #4 #5 #6
71AD30-02-2-AJN 50-3-1G 205839-3 206070-1
MS24482-i MS24482-1 MS24482-1 MS24482-1 MS24482-1 MS24482-1
(OPT) (OPT) (OPT) (OPT) (OPT)
205152-1 206070-1
OR AN5546-1* OR AN5546-1* OR AN5546-1* OR AN5546-1* OR AN5546-1* OR AN5546-1*
*USE AN4076-1 ADAPTER.
M-DD1O1A M-DD1OPA
M-DDlOjA
O.A.T. PROBE
PLUG,2PIN /SOCKETS RECEPTACLE, /PINS
261N:
M-DF1O1A M-DF102A M-DF103A M-DF104A
FUEL TRANSMITTER, LEFT I/B FUEL TRANSMITTER, LEFT O/B FUEL TRANSMITTER, RIGHT I/B
M-DG1O1A M-DG102A
C/B, INSTRUMENT MODULE #1 IND, INSTRUMENT MODULE #1 IND, INSTRUMENT MODULE#1(ALT)
M-DG1d2B: M-DG103A
M-D~103B
KLIXON MOONEY. MOONEY. MOONEY. AMP.
INDICATOR, INSTR, MODULE #1 PLUG, 28 PIN
AMP AMP
/CLAMP
PLUG,SPIN
/CLAMP
AMP. KLIXON MOONEY. AMP. AMP.
PROBE, OIL TEMP PROBE, OIL TEMP
MboNE‘j
/CLAMP C/B, INSTRUMENT MODULE #2
M-DG105A M-DG10GA
IND, INSTRUMENT MODULE #2. PLUG, 28 PIN
27-0 i
MOONEY MOONEY MOONEY MOONEY
FUELTRANSMITTER, RIGHTO/B
M-Ddl04A
M-DH1O1A
MOONEY. AMP AMP AMP AMP
PLUG,
M-DJ’102A
M-Dj103A
/ALTERNATE
PLUG,4PIN /CLAMP 4 PIN
/CLAMP M-DK1O1A M-DK102A
M-DK103A
TRANSDUCER, FUELPRESSURE PLUG,4PIN ICLAMP
RECEPTACLE,
7277-2-1 880059-501 880059-503 880059-513 205839-3 206070-1 206060-1 206062-1 7277-2-1 880059-505 205839-3 206070-1
(27-0001 thru 27-0052) (probe w/ plug only)
TRANSDUCER, OIL PRESSURE.
RECEPTACLE,
610242-3 610242-5 610242-3 61 0242-5
MS3057-4A
2 PIN
W/CLAMP M-DJ1O1A
1-480319-0 60620-1
MS28034-1 (w/ plug) 880061-501 (knife disconnects) (27-0053 thru 27-0107 8 all Spares thru
07j
M-DH1OPA
880004-501 1-480318-0 60619-1
DRUCK KULITE AMP. AMP AMP. AMP.
PDCR 821-0662-100 APT-201-1 000-1 OOG 206060-1 206062-1 206153-1 206062-1
DRUCK AMP AMP.
PDCR 920-U143 50 PSID 206060-1 206062-1
AMP. AMP.
4 PIN.
/CLAMP
4-99
206153-1 206062-1
91-20-01
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
M-DL1O1A M-DL102A M-DL103A
C/B, TACHOMETER
KLIXON MOONEY.
INDICATOR, TACHOMETER. PLUG, 25 PIN
M-DL1 05A M-DL1 O$A
M-DLlOjA
M-DilOi3A
TACHSENSOR TACH SENSOR
PLUG,4PIN /CLAM P
RECEPTACLE, /CLAMP RECEPTACLE, /PINS PLUG, iPI’N /SOCKETS
M-DL1OSA
LIGHT TRAY
M-DM1O1A M-DM102A
HOUR METER
M-DM103A
B&DINSTRUMENTS B 8 D INSTRUMENTS AMP. AMP AMP AMP AMP AMP AMP AMP D INSTRUMENTS B
(ALT)
461N: 2
f;lN:
M-DP1O3A M-DF;104A
0402-102 0402-104 206060-1 206062-1 2061 53-1 206062-1 1-4803199-0 60620-1 1-48031 8-0 6061 9-1 0221-128
MOONEY. AMP. AMP AMP. AMP
880035-505 206153-1 206062-1 206060-1 206062-1
C/B, PITOT HEAT.
MOONEY.
HEATEDPITOT HEATED PITOT PLUG
AERO INSTRUMENT
930023-205 PH502-24 AN5812-1 AN3115-1
RECEPTACLE, /CLAM P PLUG, 4 PI’N
4 PIN.
/CLAM P M-DP1O1A M-DP1OPA
7277-2-1 880039-519
MS3106A-14S-5S MS3057-6A/B
/CLAM P M-DL104A
PART NO.
/SOCKETS PLUG, 2 PIN /SOCKETS RECEPTACLE,
(ALT)
AMP
AN3116-1 1-480318-0 6061 9-1 1-480319-0 60620-1
/PIN
AMP AMP AMP
M-DR1O1A
PROBE,TIT PROBE, TIT (ALT)
MOONEY. MOONEY.
M-DU1O1A
PLUG,PPIN /SOCKETS RECEPTACLE, 2 PIN. /PINS
AMP AMP AMP AMP
FUEL FLOW, C/B INDICATOR, FUEL FLOW INDICATOR, FUEL INDICATOR, FUEL FLOW
INDICATOR, F/F (GALS) (OPT) INDICATOR, F/F (LBS) (OPT) INDICATOR, F/F (GALS)(OPT)
KLIXON MOONEY. MOONEY. MOONEY. SHADIN SHADIN SHADIN
INDICATOR, F/F (LBS)(OPT).
SHADIN
912043
INDICATOR, F/F (LITERS)(OPT)
SHADIN
912047
INDICATOR, F/F (GALS)(OPT)
SHADIN
91 2081
INDICATOR, F/F (LBS)(OPT).
SHAD\N
912083
INDICATOR, F/F (LITERS)(OPT)
SHADIN
91 2087
M-DP1OSA
M-DljlOiA M-DV1OIA M-DV102A
M-D\ilOiB
M-DV103A
91-20-01 12
2
PIN:
880055-503 880055-501 1-48031 8-0 6061 9-1 i -480319-0 60620-1 7277-2-1 880034-501 880034-503 880034-505 912021 912023 912041
DE-SS DE-24657 D-51224-1
PLUG, 9 PIN /CLAM P /LATCH ASSY (2 EA) 4-99
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
M-DV103B
M-DV104a
M-D\ilO´•iB M-DV105A
M-D\ilO(iA M-DVlOjA M-DV108A
DESCRIPTION
VENDOR
PLUG, 9 PIN /CLAMP /LATCH ASSY (2 EA)
Mborj,v.
TRANSDUCER, FUEL FLOW.
/CLAMP
MOONP/. MOONEY. SHADIN AMP. AMP. AMP. AMP. C AND K AMP. AMP. AMP. AMP.
INDICATOR, VERTICAL SPEED PLUG,3PIN
UNITED INSTRUMENTS BENDIX
TRANSDUCER, FUEL FLOW TRANSDUCER, F/F PLUG,4PIN /CLAMP
RECEPTACLE,
4 PIN.
/CLAMP
SWITCH, FUEL FLOW PLUG,4PIN /CLAMP
M-DV1OSA M-DW1OIA M-DW102A
M-D\jVlOiA M-D~iV162A
RECEPTACLE,
4 PIN.
/CLAMP
PLUG,
3 PIN
/CLAMP
PLUG,
3 PIN
CANNON
(ALT)
(ALT)’.
/CLAMP M-EG1O1A M-EG1OPA M-EG103A
C/B, GEARACTUATOR SWITCH, GEAR UP/DOWN
KLIXON CUTLER CUTLER CUTLER CUTLER CUTLER
GEAdUd
HAMMER HAMMER HAMMER HAMMER HAMMER GENERAL ELECTRIC MOONEY. KLIXON MICRO SWITCH MICRO SWITCH MICRO SWITCH SAINT SWITCH AMP. AMP AMP. AMP. CUTLER HAMMER
GEAd DOWN
CUTLE’R HAMMEk
SWITCH, GEAR OVERRIDE /LOCKING RING /LOCK WASHER /HU< NUT (2 EA) /LAMP (28V)
M-EG104A M-EG1OSA M-EG1OGA
M-EdlOjA M-EG107B M-EG108A
SWITCH, AIRSPEED, GEAR SAFETY C/B, GEAR RELAYS SWITCH, GEAR UP LIMIT /ACTUATOR
SWITCH, GEAR DOWN LiMli SWITCH, GEAR DOWN LIMIT PLUG, 4 PIN
(ALT):
/CLAMP M-EG1OSA
RECEPTACLE, /CLAMP
M-EG11OA M-EG111A M-EG112A M-EG113A M-EG114A MELT1O1A
MELTlOj B MELT102A MELT102B
RELAY, DIODE
RELAY,
4 PIN
DIODE
ACTUATOR, GEAR ACTUATOR, GEAR (ALT)
MdONEY.
SWITCH, REMOTE SWITCH, REMOTE (/iLT): SWITCH, REMOTE TRANSMITTER, ELT TRANSMITTER, ELT
DORNE 8 MARGOLIN CAND K ARTU( DORNE 8 MARGOLIN. ARTU(
MOONEY.
4-99
PART NO.
DE-SS DE-24657 D110278 880030-501 880030-503 880030-505 6805018 206060-1 206062-1 206153-1 206062-1 7101K 206060-1 206062-1 206153-1 206062-1 7000 CODE C.83
PT06E-8-3S MS3057-3A OR B KPT06E-8-3S MS3057-3A OR B MS3116-8-38 MS3057-3A OR B 7277-2-7.5
89061(2875 SB1DDX492-2 29-761 16-886 15-966-6 388 880013-507 7277-2-2
DT-2R-A7 MCD-2711 1CH116-6 ML1116 206060-1 206062-1 206153-1 206062-1
6041H-105A 1 N2483 6041H-105A 1 N2483 560254-503 880037-507
DM-U65-1 7101K 1 10-416 DM-ELT8 ELT11O-4
91-20-01 13
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
MELT103A
PLUG, 12 PIN ISOCKET
MOLU( MOLU( MOLU( MOLU( AMP. AMP. AMP. AMP AMP. AMP. AMP. AMP.
MELTiO4A MELT105A MELT1OGA
MELTlOjA MELT108A
PLUG,SPIN /SOCKET PLUG,8PIN /CLAMP RECPT.,8 PIN: /CLAM P
PLUG,BPIN ICIP1MP
RECPT,
861N:
/CLAMP MFON1O1A
PHONE JACK.
SWITCHCRAFT SWITCHCRAFT.
/WASHERS
M-JM1 OiA
SWITCH, MAGNETO /P14CARD MAGNETO, LEFT:
M-JM102A
MAGNETO,
M-LB1O1A M-LB102A
MOONEY C/B, ROTATING BEACON WHELEN LIGHT, ROTATING BEACON. WHELEN. IADAPTER WHELEN LIGHT, ANTI-COLLISION (RED)(ALT) LIGHT, ANTI-COLLISION (WHITE)(ALT)WHELEN AMP PLUG,3PIN AMP /SOCKETS AMP RECEPTACLE, 3 PIN. AMP /PINS
MJM1O1A
M-LB’1 OiB
M-LB’1 OjA
M-LB’lOdA
RIGHT
M-LC1O1A
FUSE HOLDER
M-LClOiA
/FUSE (SA-3AG-SLO-BLO) SWITCH (FRONT), CABIN LIGH’I: RESISTOR (20 Oi-IM 10W), DIM
M-LC103A M-LC104A
hn-idlO$A
M-LC10$A
M-LCjlOjA M-L610~A M-LC1OSA M-LC1 10A
M-L611 iA
BENDIX SCINTILLA BENDIX SCINTILLA SLICK SLICK
LITTLE FUSE LITTLE FUSE CARLING. DALE H.H.SMITH G.E. H.H. ~MITH G.E. H.H. SMITH G.E. H.H. SMITH G.E. CARLING. DALE H.H.SMITH G.E. H.H. SMITH G.E.
LAMP HOLDER
/LAMP LAMP HOLDER
/LAMP LAMP HOLDER
/LAMP LAMP HOLDER
/LAMP
SWITCH (REAR), CABIN iIGHT RESISTOR (20 OHM 10W), DIM LAMP HOLDER
/LAMP LAMP HOLDER
/LAMP M-LC112A
M-LClljA M-L6114A
LAMP HOLDER
H.H.SMITH G.E. H.H. SMITH G.E. H.H. SMITH G.E.
/LAMP LAMP HOLDER
/LAMP LAMP HOLDER
/LAMP
91-20-01 14
4-99
PART NO.
03-06-2122 02-06-11 03 03-06-2092 02-06-11 03 205838-1 206062-1 205841-2 206062-1 205838-1 206062-1 205841-2 206062-1 C-l 1 S-1028 AND S-1029 10-357210-9 10-187-468 6261 6260 930023-243 WRML-24 WRM-65 90033-19 90033-20 1-380303-0 6061 9-1 1-480305-0 60620-1 155020 OR 155120 313005
TILC64-i S-WH-FN RH-10-20 OHM 1930
1818 1930 1818 1930 1818 1930 1818
TILC64-IS-WH-FN RH-10-20 OHM i 930 1818 1930 1818
1930 1818 1930 1818 1930
1818
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONN AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
M-LC115A
Ni-LC11$A M-LC117A M-LC118A
M-L611~B M-LC119A M-LC1 24A
DESCRIPTION
VENDOR
LAMP HOLDER
H.H.SMITH G.E.
/LAMP
PART NO.
1930 1818
800268-501 DE-1S DE2457
MOONEY.
MODULE, LT., AUTO-OFF PLUG, 9 PIN /CLAMP /LATCH RECEPT, SHORTI’NG’ ICLAMP /LOCKING POST
DE51224-1 DESP DE24657 206514-1 1 N2483/1N5060
DIODE
3720-GE
GE
DIODE, (ALT)
1
DIODE
N2483/1N5060 3720-GE
M-LC128A
/PIN PLUG, i PI’N /SOCKFT
GE AMP AMP AMP AMP NMIARK NEWARK AMP AMP AMP AMP
M-LL1O1A M-LL102A M-LL103A M-LL104A
C/B, LANDING LIGHT. SWITCH, LANDING LIGHT LANDING LIGHT, RIGHT. LANDING LIGHT, LEFT
KLIXON. MOONC(. G.E. G.E.
7277-2-25 880052-521 4596 4596
M-LN1O1A M-LN 1016 M-LN 102A
C/B,NAVIGATION LIGHTS
930023-201 930023-251
/CLAM P
MOONEY MOONEY. MOONEY MOONEY. AMP AMP AMP. AMP. AMP AMP AMP. AMP. AMP AMP AMP. AMP. AMP AMP AMP. AMP
C/B, GLARESHIELD LIGHTS. C/B, PANEL LIGHTS CONTROL BOX, DIMMER CONTROL BOX, DIMMER
KLIXON KLIXON IAl IAl
M-LC12jA M-LC1 24A
M-LC125A M-LC126A M-LC127A
M-LN103A M-LN 104A
M-Lrjl04B M-LN105A
M-LNlOjB M-LN106A M-LN 10$B
M-LNlOjA M-LNlOjB M-LP1OIA M-LP102A M-LP103A M-LP103B
DIODE, (ALT) RECPT, 2 PIN. /PINS
PLUG,2PIN /SOCKET SWITCH, CABIN
dOdR
SWITCH, BAGGAGE DOOR PLUG,2PIN
C/B, NAV LTS.
NAV iAli LIGHT ASSY (LT LIGHT ASSY (RT WING) NAV TAIL
WING),
PLUG, 2 PIN (RT WING) ISOCKETS RECPT, 9 PIN. ICLAMP RECEPTACLE, 2 PIN (RIGHT WING) /PIN
PLUG, 9 PIN ICLAMP PLUG, 2 PIN (LEFT WING) /SOCKETS
RECPT, 9 PIN. /CLAMP
RECEPTACLE, 2 PIN (LEFT WING) /PIN
PLUG, 9
PI’N
4-99
1-480319-0 60620-1 1-480318-0 6061 9-1 89F5544
89F5544 1-480319-0 60620-1 1-480318-0 6061 9-1
800051-501 800051-501 1-480318-0 6061 9-1 206705-1 206966-1 1-480319-0 60620-1 206708-1 206966-1 1-480318-0 6061 9-1 206705-1 206966-1 1-480319-0 60620-1 206708-1 206966-1 7277-2-7.5 7277-2-7.5
950D0307-000 9500307-001
91-20-01 15
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
M-LP104A
PLUG, DIMMER CONTROL.
M-LP105A
/CLAMP /LOCK RETAINER /RECEPTACLES (2 EA) DIMMER SWITCH, G/SHIELD LTS
M-LP1OGA M-LP107A
SWITCH, PLUG,4PIN
M-LP108A
/CLAMP RECEPTACLE, 4 /CLAM P
M-LP1OS9A M-LP11OA M-LP111A M-LP112A M-LP113A
M-LP114A
M-LP115A M-LP11GA
M-LP’11 jA M-LP118A
M-LP119A M-LP12dA M-LP121A M-LP122A
M-LP12jA M-LP124A M-LP125A M-LP135A
M-LP’~ 38A M-LP’1 3jA M-LP’1 38A
DIMMER
C AND’ K C AND K AMP. AMP AMP. AMP DEANS DEANS G.E.. G.E. MOONEY G.E. SLOAN G.E.
PANEL LIGHTS
PIN:
RECEPTACLE, COMPASS LIGHT PLUG, COMPASS LIGHT. COMPASS LIGHT. GLARESHIELD LIGHTS FLAP SWITCH LIGHT
(14 EA)
/LAMP COWL FLAP SWITCH, LIGHT
/LAMP. CONSOLE SWITCH
LiGHi
PLUG, 16 PIN /CLAM P /CLAMP
PLUG,8PIN CLAMP
RECEPTACLE, 8 PIN. /CLAMP
PLUG, 20 PIN RECEPTACLE,
MALE HALF DEA90020 FEMALE HALF DEA90020 327 OR 327 AVIATION RED 327 130285-3 327 855S-0-Ufk
6o-F;ILCjT
GE. SLOAN
OXYGEN LIGHT
/LAMP LIGHTING TRAY LIGHTING TRAY
(O.A:T.).
(VOLT/AMP) POTENTIOMETER, MAP LT, PILOT /KNOB.
POT., MAP LT, GO-PILOT
LT, MAP,
206060-1 206062-1 206153-1 206062-1
PILOT
OXYGEN LIGHT
/LAMP
7105-J1-Z-Q
MOONEY. MOONEY. SLOAN G.E. SLOAN G.E. B AND D INSTRUMENTS B AND D INSTRUMENTS NEWARK NEWARK NEWARK NEWARK SLOAN
20 PIN
/LAMP.
/KNOB. LT, MAP,
DBM1M/2S DB51212 DB51221-1 DM53744-7 7105-J1-Z-Q
AMP. AMP AMP. AMP. AMP. AMP. AMP. AMP.
1BPlhj
RECEPTACLE,
PART NO.
/LAMP
327
206037-1 206070-1 206036-3 206070-1 205838-1 206062-1 205841-2 206062-1 930021-501 930021-502
855S-0-U*X 327 855S-0-Ufk 327 0221-128 0221-128 09F981 57F2368 09F981
57F2368 855S-0-U 327
855S-0-U
GE.
327
fkUSE 1 EA. hn835334121 OR M2898 (ALLEN-BRADLEY) INTERNAL TOOTH LOCICWASHER WITH EACH LIGHT IF NOT SUPPLIED BY SLOAN. M-LR1O1A
C/B, RECOGNITION LIGHT
M-LR102A M-LR1 03A
RECOGNITION LIGHT
M-LR104A M-LR105A M-LR1 O$A
MOONEY MOONEY. AMP AMP DALE.
(LT WING)
PLUG,2PIN /SOCKETS RESISTOR
RECEPTACLE, /PIN
PLUG,
2 PIN.
AMP AMP AMP AMP
iPI’N
/SOCKETS
91-20-01 16
4-99
930023-231 880049-501 1-48031 8-0 6061 9-1
RH-50-7.5 OHM 1-480319-0 60620-1 1-48031 8-0 6061 9-1
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
M-LR107A M-LR108A
RECOGNITION LIGHT PLUG, 2 PIN SOCKETS. RESISTOR
(RT WG)
VENDOR
PART NO.
MOONEY
880049-501 1-480318-0 6061 9-1 RH-50-7.5 OHM 1-480319-0 60620-1
/PIN
AMP AMP DALE. AMP AMP
M-LR111A
PLUG,2PIN /SOCKETS
AMP AMP
M-LS1O1A M-LS102A M-LS103A
C/B, STROBE LIGHT
MOONEY. WHELEN AMP AMP AMP AMP AMP AMP WHELEN
M-LR1OSA M-LR11OA
M-LS104A M-LS’lOjA
RECEPTACLE,
2
PIN:
POWER SUPPLY (LEFT WING) RECEPTACLE, POWER SUPPLY
/PINS
RECEPTACLE, POWER SUPPLY /PINS
M-LS108A
PLUG, STROBE LIGHT ASSY /SOCKETS STROBE/NAV LIGHT ASSY (L WG)
M-LS107A M-LS108A
POWER SUPPLY (RIGHT WING) RECEPTACLE, POWER SUPPLY
M-LS109A
/PINS RECEPTACLE, POWER SUPPLY /PINS
M-LS’lldA
PLUG, STROBE LIGHT ASSY
M-LS’111’A
STdoB’E/NI4V LIGHT ASSY (dT WG)
M-LS112A M-LS113A
POWER SUPPLY TTAIL)
M-LS114A M-LS115A
M-LS’11$A M-LS’11 jA M-LS118A M-LS11SA
M-LS’1 2dA
M-LS121 M-LT1O1A
M-LT102A M-LT103A M-LT104A M-MA1O1A M-MA102A M-MA103A M-MA104A
WHELEN AMP AMP AMP AMP AMP
RECEPTACLE, P6WEd /PINS
RECEPTACLE, /PINS
PLUG,
4
AMP WHELEN WHELEN AMP AMP AMP AMP AMP. AMP AMP. AMP. AMP AMP MOONEY. AMP AMP AMP AMP AMP AMP
SUPbL\i
PdWiR SUPbl\j
PI’N
/CLAM P
RECEPTACLE, 4 PIN. /CLAMP
PLUG, STROBE LIGHT ASSY /SOCKETS STROBE LIGHT ASSY, TAIL RECEPTACLE, 3 PIN. /PINS RECEPTACLE, 3 I;IN /PINS RECEPTACLE, 3 PIN: /PINS C/B, TAXI LIGHT SWITCH, TAXI LIGHT
KLIXON. MOONEY. G.E.
TAXI LIGHT(RIGHT) TAXI LIGHT (LEFT)
G.E.
RECEPTACLE, AUX POWER RELAY, AUX POWER
CUTLE’R H’AM’MER SARKES TARZIAN
DIODE. DIODE
4-99
1-48031 8-0 606191 930023-237 01-077032990 1 -480305-0 60620-1 1-480305-0 60620-1 1-480303-0 6061 9-1
A650-PR-D-M 01-0770329-00 1-480305-0 60620-1 1-480305-0 60620-1 1-480303-0 60619-1 A650-PG-D-M 01-0770329-00 1-480305-0 60620-1 1-480305-0 60620-1 206060-1 206062-1 206153-1 206062-1 1-480303-0 6061 9-1 470013-501 1-480305-0 60620-1 1-480305-0 60620-1 1-480305-0 60620-1 7277-2-25 880052-523 4596 4596
AN2552-3A 6041H-105A 10H3P 1N2483
91-20-01 17
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
M20M
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
PART NO.
M-MB1O1A M-MB1OPA M-MB1 03A. M-MB104A M-MB1OSA M-MB1OGA M-MB107A M-MB108A M-MB1OSA M-MB11OA M-MB111A M-MB112A M-MB113A M-MB114A M-MB115A M-MB11GA M-MB117A M-MB118A M-MB1ISA M-MB120A M-MB121A M-MB122A M-MB123A
C/B SWITCH, AVIONICS MASTER
MOONEY
930023-213
D16DE RELAY, AVIONICS
MASTER’.
KIS’SLING’
AVI’ONI’CS’BUS BkR#l AVIONICS BUS BAR AVIONICS BUS BAR AVIONICS BUS BAR AVIONICS BUS BAR AVIONICS BUS BAR AVIONICS BUS BAR C/B, COM 1 CIRCUIT BREAKER, C/B, AUDIO C/B, COM 2 C/B, NAV 2
MObNEY
iN2483 26.64.01
’91j127-67
#2 #3 #4
MOONEY 913127-67 MOONEY 913127-67 MOONEY 913127-67 #5 MOONEY 913127-67 #6 MOONEY 913127-67 #7 MOONEY 913127-67 7277-2-1 Om KLIXON NAV 1 KLIXON 7277-2-7.5**X KLIXON 7277-2-7.5XCA KLIXON 7277-2-10+** KLIXON 7277-2-7.5kA* KLIXON 7277-2-7.5*k* C/B,PHONE KLIXON 7277-2-7.5M* C/B, TRANSPONDER. KLIXON 7277-2-7.5m C/B,ENCODER KLIXON. 7277-2-7.5*f* C/B, RAD BLOWER M-MB124A KLIXON 7277-2-7.5m C/B,ADF M-MB125A KLIXON 7277-2-7.5m C/B, DME M-MB126A KLIXON 7277-2-7.5"" C/B, R/NAV M-MB127A KLIXON 7277-2-7.5*k* C/B, STORMSCOPE M-MB127B KLIXON 7277-2-7.5m C/B,RMI M-MB129A KLIXON 7277-2-7.5" C/B,LORAN M-MB130A KLIXON 7277-2-7.5*** C/B, STEREO M-MB131A KLIXON 7277-2-7.5f** C/B, TELEPHONE M-MB132A KLIXON 7277-2-7.5" C/B, VME M-MB133A KLIXON 7277-2-1 OMR C/B, AUTOPILOTTTRIM M-MB134A KLIXON 7277-2-7.5MR C/B, YAW DAMP M-MB135A KLIXON 7277-2-7.5m C/B, INVERTER M-MB136A KLIXON 7277-2-2Xk* C/B, HSI M-MB137A KLIXON 7277-2-2" C/B, ART HORIZON M-MB138A KLIXON 7277-2-7.5C** C/B, A/P ALERT "MAXIMUM CIRCUIT BREAKER RATING IS SHOWN. AMPERAGE OF INSTALLED CIRCUIT BREAKER IS DETERMINED BY PARTICULAR UNIT INSTALLED. M-MC1O1A CIRCUIT BREAKER KLIXON. 7277-2-10 M-MC1OPA CIGAR LIGHTER MOONEY. 800336-503 CASCO /ALTERNATE 208292 M-ME1O1A CLOCK PORSCH E 944.641 .213.00 M-ME1O1B MID-CONT. MD-89 CLOCK(ALT) R1 1500HM3WATT M-ME102A CLAROSTAT VC3D R1 150 OHM 3 WATT (ALT) OHMITE 23J M-ME1O$A R2 3.9K OHM 112 WATT. M-ME104A R3 3.OK OHM 1/2 WATT. ~oksdH E’ 944.iii 2:21 j.OO M-ME105A CONN, 4 PIN PORSCH E /PIN 999.652.351 .1 2 M-MEIOSB MID-CONT 6016177 CONN, 4 PiN MID-CONT /PIN 6016125
(ALT)
MMIC1O1A MMICl d2A
MICROPHONE JACK.
MIASHERS
SWITCH,MIKE KEY,
SWITCHCRAFT SWITCHCRAFT ALCO CUTLER-HAMMER ALCO CUTLER-HAMMER
PILOT
(AL77
MMIC103A
91-20-01 18
SWliC H, M I KE, KEY, GO-PI LOT (ALT) 4-99
C-128
S-1028,S-1029 MPE-106F-C-22-9 SAIRV20 MPE:l 06F-C-22-9 SAl RV20
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOON EY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
M-MP1O1A M-MP102A M-MPlOSA M-MP104A
C/B, PROP DE-ICE TIMER, PROP DE-ICE CURRENT MONITOR, PROP DE-ICE. PLUG,SPIN
930023-245
M-MP105A
/CLAMP TERMINAL BLOCK
MOONEY. B.F. GOODRICH MOONCIâ&#x20AC;&#x2122; AMP. AMP. MC CAULEY. MOONN. WELDON AMP AMP AMP. AMP. KLIXON. MICRO SWITCH MICRO SWITCH AMP. AMP.
930023-211 A10051-D 206060-1 206062-1 206153-1 206062-1 7277-2-10 1SE1-T JE-5 206060-1 206062-1 206153-1 206062-1
M-NF1O1A M-NF102A M-NF103A
M-NF1OLiA
C/B, BOOSTPUMP BOOST PUMP
PLUG,4PIN /CLAMP
RECEPTACLE,
4
PIN:
/CLAMP M-NF1 05A M-NF1OGA
M-NFlOjA M-NFlO8A
M-PA1OIA M-PA102A M-PAlOSA M-PA103B M-PA104A M-PA105A
M-PA1 06A
M-PAlOjA M-PA1 08A M-PA1OSA M-PA11OA M-PA111A M-PA112A M-PA113A
M-PA114A
C/B, BOOSTPUMP THROTTLE SWITCH, BOOST PUMP /ACTUATOR
PLUG,4PIN /CLAMP RECEPTACLE, /CLAMP
4
PIN:
AMP.
AMP
C/B, ALTERNATOR, RIGHT C/B, FIELD, RIGHT ALTERNATOk SWITCH, ALTERNATOR FIELD (OPT). SWITCH, ALTERNATOR FIELD (STD) VOLTAGE REGULATOR RECEPTACLE, 9 PIN.
(RIGHT)
/CLAMP
PLUG,SPIN /CLAMP ALTERNATOR (RIGHT) /INSTALL KIT (REF 600180) FI LTER
CAPACITOR CIRCUIT BREAKER CIRCUIT BREAKER VOLTAGE REGULATOR RECEPTACLE, 9 PIN.
/CLAMP
PLUG,SPIN /CLAMP
M-PA115A
M-PA11QA M-PA117A M-PA118A M-PA11SA M-PA1POA
ALTERNATOR (OPT)
/INSTALL KIT
(REF 6001~0)
FILTER CAPACITOR MONITOR, CURRENT MONITOR, CURRENT DIODE. /MICA WASHER (2 EACH)
/TEFLON BUSHING /FLAT WASHER /STEEL LOCK WASHER /HU( NUT
4-99
PART NO.
3E1899-1 800221-505 206708-1 206966-1 C-40521
ETA KLIXON MOONEY MOONEY ELECTRODELTA AMP. AMP AMP AMP ELECTRO SYSTEMS LYCOMING MOONEY. MALLORY ETA KLIXON ELECTRODELTA. AMP. AMP AMP AMP
41-3-S34-LN2-041 800
ELECTRO SYSTEMS LYCOMING MOONEY. MALLORY MICRO SW. MICRO SW. SARKES TARZIAN MOTO ROLA. MOTO ROLA. MOTO ROLA. MOTO ROLA. MOTOROLA.
ES 4009 05K-21066 880014-501
7277-2-5 880052-525 880052-503
VR-802 206708-1 206966-1 206705-2 206966-1 CS 4009
05K-21065 88001 4-501
CGS302U-050R2C 41-3-S34-LN2-041800 7277-2-5
VR-802 206708-1 206966-1 206705-2 206966-1
CGS302U-050R2C CSLA1GE CSLA1GE 10H3P 852600F001 851 547F01 2 851 567F009 851 566F020 851 568F015
91-20-01 19
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
ELECTRICAL EQUIPMENT CHART
CODE NOTES
M-PA121A
M-PA1PiA
M-PA123A
DESCRIPTION
VENDOR
DIODE.
SARKES TARZIAN MOTOROLA. MOTOROLA. MOTOROLA. MOTOROLA. MOTOROLA. SARKES TARZIAN MOTOROLA. MOTOROLA. MOTOROLA. MOTOROLA. MOTOROLA. SARKES TARZIAN MOTOROLA. MOTOROLA MOTOROLA. MOTOROLA. MOTOROLA. L’ITEL FUSE LITTEL FUSE CUTLER HAMMER CUTLER HAMMER CUTLER HAMMER CUTLER HAMMER GENERAL ELECTRIC
/MICA WASHER (2 EACH) TTEFLON BUSHING /FLAT WASHER /STEEL LOCK WASHER /HEX NUT DIODE.
/MICA WASHER (2 EACH) /TEFLON BUSHING /FLAT WASHER /STEEL LOCK WASHER /HU( NUT DIODE.
/MICA WASHER TTEFLON /FLAT WASHER /STEEL LOCK WASHER /HE( NUT
BUSHI~2,E4C-
M-PA124A
M-PA12jA
M-PA12$A M-PA12jA
FUSEHOLDER
/5A FUSE
SWITCH, EMERGENCYFIELD /LOCKINGRING /LOCK WASHER /HEX NUT (2 EACH) /LAMP (28V) DIODE
Gi
(ALT) DIODE
GE
BAfiERY-
M-PB1OPA M-PB103A M-PB104A M-PB1OBA M-PB1OGA M-PB107A M-PB108A M-PB1OSA M-PB11OA M-PB111A
RELAY, BATTERY
M-PB113A M-PB114A M-PB115A M-PB11GA M-PB117A M-PB118A M-PB11SA M-PB1POA M-PB1P1A M-PB122A M-PB123A M-PB124A
91-20-01
20
#1
GILL CUTLER HAMMER
DIODE
MOONEY.
SWITCH, MASTER C/B, BATTERY C/B, LOAD
ETA ETA ETA ETA MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY
C/B, LEFT AUX C/B, RIGHT AUX BUSBAR#1 BUSBAR#2 BUSBAR#3 8USBAR#4 BUSBAR#5 BUSBAR#6 8USBAR#7
ivlObNiY
8USBAR#9 BUS BAR #10. BUS BAR #11
MOONEY MOONEY MOONEY. GILL CUTLER HAMMER.
GROUND/DIMMER BOX BATTERY- #2 MASTER RELAY#2 DIODE
RESISTOR,
851547F012
851567F009 851566F020 851 568F015 10H3P
B52600F001B51547F012 B51567F009 851566F020 851 568F015 155020 OR 155120 313005
SB1DDX492-2 29-761 16-886 15-966-6 388 1 N2483/1 N5060
3720-GE 3720-GE
GE
DIODE (ALT)
M-PB1O1’A
M-PB112A
10H3P B52600F001 851547F012 851567F009 851566F020 851568F015 10H3P 852600F001
1N2483/1N5060
(ALT) M-PA128A
PART NO.
1
OHM
25
W’A~
DALE
4-99
1
N2483/1 N5060
3720-GE 6-243 6041H-105A iN2483 880052-501 41-3-S34-LN2-041 800 41-3-S34-LN2-041 800 41-3-S34-LN2-40A 41-3-S34-LN2-40A 913127-69 913127-19 913127-19 913127-19 913127-19 913127-19 913127-67
’91j127-53 913127-73
913127-65 800220-501 G-243 8041H-202 OR 202A 1N2483 RH-25-1-25W
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
M-PB125A
M-PB128A
M-Ptil2jA M-PL201A
M-Pi202´•A M-Pi20jA M-Pi20LiA M-PL204B M-PL205A
M-Pi208A M-PL207A M-PL208A M-PL209A
M-Pi21dA
M-Pi211’A M-PL212A M-PL213A
M-PLilBA M-PLi1jA M-Pi218A M-Pi219’A
M-Pi224A M-Pi221’A M-Pi22~A M-Pi22jA
M-Pi224A
M-Pi22jA
DESCRIPTION
VENDOR
DIODE.
SARKES TARZIAN MOTOROLA MOTOROLA. SARKES TARZIAN MOTOROLA MOTOROLA. MOONEY.
/NYLON BUSHING /MICA WASHER DIODE.
/NYLON BUSHING /MICA WASHER BATTERY SELECT SWITCH PLUG 37 PIN
AMP. AMP AMP AMP. AMP AMP.
/CLAMP PLUG
/FLANGE PLUG
/CLAMP PLUG 20 PIN PLUG, 26 PIN PLUG 28 PIN
MOONEY. MOONEY. AMP. AMP MOONEY. MOONEY.
/CLAMP
PLUG, 34 PIN. PLUG, 20 PIN. PLUG 14 PIN
MOONEY AMP AMP AMP. AMP. MOONEY. MOONEY. AMP. AMP AMP. AMP. AMP. AMP AMP. AMP. AMP. AMP. AMP. AMP AMP. AMP. AMP AMP. MATRIX SCIENCE MATRIX SCIENCE. MATRIX SCIENCE MATRIX SCIENCE MATRIX SCIENCE MATRIX SCIENCE. MATRIX SCIENCE MATRIX SCIENCE MATRIX SCIENCE MATRIX SCIENCE. MATRIX SCIENCE MATRIX SCIENCE
PLUG,SPIN ICLAMP PLUG, 9 PI’N /CLAMP PLUG, 26 PIN PLUG, 34 PIN PLUG,SPIN /CLAMP PLUG, 16 PIN /CLAMP PLUG, 16 PIN ICLAM P PLUG, 16 PIN /CLAMP PLUG, 28 PIN ICLAMP PLUG, 4 PI’N ICLAMP PLUG, 4 PI’N /CLAMP PLUG,4P\N /CLAMP PLUG, 32 PINhC-* ICLAM P /SOCKET /SOCKET PLUG, 32 FIN"" /CLAM P /SOCKET /SOCKET
PLUG, 32 PINfM* ICLAMP /SOCKET /SOCKET
4-99
PART NO.
10H3P 85147F012 852600F001 10H3P 85147F012 852600F001 880052-527 206150-1 2061 38-1 2061 50-1 207299-4 206037-2 206070-1 930021-501 930021-505 205839-3 206070-1 930021-507 930021-501 930021-1 206708-1 206966-1 206708-1 206966-1 930021-505 930021-507 2061708-1 206966-1 206037-1 206070-1 206037-1 206070-1 206037-1 206070-1 205839-3
206070-1 206060-1 206062-1 206060-1 206062-1 206060-1 206062-1
M83723/86R2232N M85049/52-1 -22N 5100-00f-0012 5100-001-0020
M83723/86R2232N M85049/52-1 -22N 5100-001-0012 51 00-001-0020
M83723/86R2232N M85049/52-1-22N 5100-001-0012 5100-001-0020
91-20-01 21
OLDWILLWAYNE MOONEY AIRCRAFT CORPORATION
CODE NOTES
M-PL226A
SERVICE AND MAINTENANCE MANUAL M20M ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PLUG, 32 PINX*kX
MATRIX MATRIX MATRIX MATRIX *kk*USE MS3420-14 OR -16 BOOT WITH CONNECTOR. M-PL227A MATRIX PLUG,GPIN MATRIX /CLAMP MATRIX /SOCKET MATRIX /SOCKET
/CLAMP /SOCKET /SOCKET
SCIENCE SCIENCE SCIENCE SCIENCE
M83723/86R2232N
SCIENCE. SCIENCE SCIENCE
MS3106A-28-225 MS3057-16B OR A 5100-001-0012
SCIENCE
M-PL228A
PLUG, 20 PIN
MOONEY.
M-PL229A
PLUG, 16 PIN
AMP. AMP. MOONEY AMP. AMP. MOONFV
M-Pi23dA M-PL231A
M-Pi232A
ICLAMP
PLUG, PLUG,
14 PIN 16 PIN
/CLAMP
PLUG,
14 PIN
M-PS1O1A M-PS102A M-PS103A M-PS104A
C/B, STARTERSOLENOID SOLENOID, STARTER
KLIXON CUTLER HAMMER.
DIODE STARTER
BAND’C.
M-RB102A M-RB1OPB M-RB1OSA
BLOWER, RADIO. BLOWER, RADIO.
M-RB104A
PLUG,PPIN /SOCKET
M-RCPO1A M-RC202A
RECEPTACLE, RECEPTACLE,
M-RdaOjA M-RdaO~jA M-RC204B M-RC205A
M-Rd206A M-RC207A M-RC208A M-RC209A M-RC210A
M-RC21iA M-RC212A M-RC213A
M-Rd214A
M-Rd21jA M-Rd22i)A M-RC22iA
91-20-01 22
FILTER FILTER
TRW
(ALTEkNA;TEj 37 PIN 37 PIN
/CLAMP
RECEPTACLE, 3 PIN. /CLAM P
RECEPTACLE, RECPT, 26 PIN RECEPTACLE,
20 PIN 28 PIN
RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, /CLAMP RECEPTACLE, /CLAMP RECEPTACLE, RECEPTACLE, RECEPTACLE, /CLAM P RECEPTACLE, ICLAMP RECEPTACLE,
34 PIN 20 PIN 14 PIN 9 PIN... 9
14PIFj
CLAM P
RECEPTACLE, ICLAMP RECEPTACLE, ICLAMP
4
PIN:
4
F;IN:
4-99
930021-501 206037-1 206070-2 930021-1 206037-1 206070-1 930021 7277-2-5
6041H-202 OR 202A 1 N2483 BSC206-149
206151-2 206151-2 206070-1 206207-1 206070-1 930021-502 930021-506 206152-1
AMP.
14’ PIN
5100-001-0020
AMP. AMP. AMP AMP. AMP MOONEY. MOONEY. AMP.
AMP AMP. AMP. MOONEY. MOONEY. AMP. AMP AMP AMP AMP AMP AMP. AMP. AMP. AMP.
26 PIN 34 PIN 9 PIN.
5100-001-0012 5100-001-0020
19/1\2790 071-4037-01 273-103 5JX51 04A 03-06-1 023 02-06-11 03
MOONEY. MOONEY. MOONEY
IjlN:
M85049-52-1-22N
KING ARCHER SPRAGUE MOLEX MOLEX
AMP.
ICLAMP
PART NO.
206070-1
930021-508 930021-502 930021-2 206705-2 206966-1 208705-2 206966-1 930021-506 930021-508 206705-2 206966-1 206044-1 206070-1 206044-1
206070-1 206153-1 206062-1 206153-1 206062-1
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
M-RC222A
M-Rd22jA
DESCRIPTION
RECEPTACLE,
VENDOR
4 PIN.
AMP AMP. MATRIX SCIENCE.
/CLAMP
RECEPTACLE,
32 PIN
MATRIX SCIENCE /PINS
M-Rd224A
/BOOT.
RECEPTACLE,
32 PIN
/BOOT. RECEPTACLE, /PINS
32
Plrj
RECEPTACLE,
M-Rd23ilA M-Rd232A
/CLAMP RECEPTACLE,
M-SB1O$A M-SB106A
M-SBlOjA
14’ Plr;1
KLIXON PRECISEFLT AMP AMP AMP AMP PRECISEFLT
RELAY,ST;DBRK: DIODE
M-SB111’A M-SB112A M-SB113A M-SB114A M-SB115A
M-SB11GA
M83723/83K2232N 5000-054-0020 5000-054-0012 MS3420-14 OR 16
MS3100K-28-2P MS3100KE-28-2P MS3057-12BORA 930021-2 206036-1 206070- 1 930021-2 7277-2-2 01265 1-380303-0 60619-1 1-380305-0 60620-1 01384 1 N2483/1 N5060
PLUG,4PIN
APAP. AMP
3720-GE 206060-1 206062-1
AMP. AMP. AMP. AMP. AMP. AMP PRECISEFLT PRECISEFLT PRECISEFLT PRECISE FLT AMP. AMP. AMP. AMP AMP AMP. AMP AMP
206153-1 206062-1 205838-1 206062-1 205841-2 206062-1 01532 01505 01505 01678 205838-1 206062-1 205841-2 206062-1 205838-1 206062-1 205841-2 206062-1
RECPT, PLUG,
8
RECPT,
4 PIN.
PI’N
861N:
/CLAMP
MOTOR, LEFT SWITCH, DEPLOY LIMIT. SWITCH, RETRACT LIMIT SOLENOID, CLUTCH. PLUG,8PIN /CLAMP RECPT, 8 PIN:
PLUG,8PIN /CLAMP
M-SB118A
5000-054-0020 5000-054-0012 MS3420-14 OR 16
G~
/CLAM P M-SB117A
MS3420-140R16
(ALT)
/CLAMP M-SB11OA
M83723/83K2232N
MdON’EY’
C/B, SPEED BRAKE SWITCH, SPEED BRAKE. PLUG,3PIN /SOCKET RECPT, 361N: /PIN
/CLAMP M-SB1OSA
MATRIX SCIENCE
AMP. AMP. MOONEY
/CLAMP M-SB108A
5000-054-0020 5000-054-0012
or
RECEPTACLE, 14 PIN RECEPTACLE, 16 PIN
M-SB104A
M83723/83K2232N
MATRIX SCIENCE MATRIX SCIENCE
/BOOT. RECEPTACLE, 6 PIN
M-RC231A
M-SB1O1A M-SB102A M-SB103A
MAiRlj( SCIENCE
MATRIX SCIENCE MATRIX SCIENCE
li=LAhnP’
M83723/83K2232N 5000-054-0020 5000-054-0012 MS3420-14 OR 16
iylAiRlj( SCIENCE
32 PIN
/PINS /PINS
M-Rd22jA
or
MATRIX SCIENCE MATRIX SCIENCE
/PINS /BOOT. M-RC226A
206153 206062-1 MS3100K-22-14P
MATRIX SCIENCE
/PINS /PINS M-RC225A
PART NO.
RECPT, 861N: /CLAM P
4-99
91-20-01
23
OLDWILLWAYNE
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
M20M
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
MOTOR,RIGHT SWITCH, DEPLOY LIMIT. SWITCH, RETRACT LIMIT SOLENOID, CLUTCH. PLUG,8PIN /CLAM P RECPT, 8 PIN: /CLAMP
PRECISEFLT PRECISEFLT PRECISEFLT PRECISEFLT AMP AMP AMP. AMP.
SPEAKER, CABIN PLUG,2PIN
ARCHER AMP AMP AMP AMP
PART NO.
NOTES
M-SB11SA M-S8120A M-SB121A M-SB122A M-SB123A
M-SB124A MSPK1OIA MSPK102A MSPK1 d3A
M-WC1O1A
/SOCKET
RECPT, 2 /PIN
PIN:
FUSE HOLDER
LITTEL FUSE LITTEL FUSE LITTEL FUSE LITTEL FUSE KLIXON SLOAN G.E. MICRO MICRO
/1A FUSE M-WD1O1A
M-WE1O’1A
FUSE HOLDER
/1A FUSE
M-WE102A
C/B, GEAR WARNING LIGHT, GEAR DOWN.
M-WElOjA
iHROiTLti, SWITCH:
M-WE10;1´•A M-WE105A M-WE1OGA
M-WElOjA
/ACTUATOR DIODE DIODE
PLUG,
4
PiN
AMb.
/CLAMP
RECEPTACLE,
4
AMP. AMP. AMP.
PIN:
/CLAMP M-WP1O1A M-WP102A
M-WPlOjA
CURRENT MONITOR, PITOT HEAT. PLUG 9 PIN
MOONEY. AMP. AMP LITTEL FUSE LITTEL FUSE
/CLAM P FUSEHOLDER
/FUSE (5A-3AG-SLO-BLO) M-WS1OIA M-WS102A M-WS103A
M-WS1d4A:
C/B, STALL WARNING ALERT, STALL WARN/GEAR WARN PLUG, 25 PIN
KLIXON IAl
/CLAMP /LOCK RETAINER SWITCH, STALL WARNING
’SAFE FLIGHT’
(ALT) M-WS105A M-WS1OGA M-WS1 068
M-W~jlOjA
RECEPTACLE, /CLAMP
RECPT, /CLAM P
PLUG,
4
/CLAMP M-WS1OjB
M-WSlOi3A M-WS1OSA
M-W~llbA
91-20-01 24
MOONEY. AMP. AMP. AMP. AMP. AMP. AMP AMP. AMP AMP. AMP ARCHER AMP AMP AMP AMP
PLUG, 4 PIN /CLAMP
PLUG, 9 /CLAMP
4 PIN.
961N: PI’N PI’N
SPEAKER, ALERT PLUG,PPIN /SOCKETS RECEPTACLE, /PIN
261N:
4-99
01532 01505 01505 01678 205838-1 206062-1 205841-2 206062-1 12-1703 1-48031 8-0 60619-1 1-480319-0 60620-1
155020
155’020
155120 313001 or 155120 313001 727/-2-1 or
855S-0-U 327 1SE1-T JE-17 1 N2483 1 N2483 206060-1 206062-1 206153-1 206062-1
800221-505 206705-2 206966-1 155020 OR 155120 313008 7277-2-1
950D0309-000 DB25S D851212 DB51221-1 C46001 800366-501 206060-1 206062-1 206153-1 206062-1 206705-2 206966-1 206060-1 206062-1 206708-1 206966-1 40-1 333C 1-48031 8-0 6061 9-1 1-480319-0 60620-1
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
M-WT1O1A M-VVT102A
CIRCUIT BREAKER ANNUNCIATOR
KLIXON IAl IAl IAl IAl IAl IAl
/LEGEND, ANNUNCIATOR-US /LEGEND, ANNUNCIATOR -FRENCH ANNUNCIATOR
M-VVil03A
/LEGEND,ANNUN,-US /LEGEND, ANNUN.-FRENCH PLUG, 25 PIN /CLAMP /LOCK RETAINER
M-WV1OIA M-WV102A M-WV103A M-V~104A M-WW1O1A.
PART NO.
7277-2-2
9501)031 6-000 40000059-000 40080059-001 9500326000 9500330000 9500330001 DB25S 0851212 D851221-1
C/B, VACUUM WARNING SWITCH, VACUUM WARNING RECEPTACLE, 4 PIN.
KLIXON MOONEY. AMP.
/CLAMP ICLAMP
AMP. AMP. AMP.
SWITCH, ALTERNATEAIR
CHERRY SWITCH
PLUG,4PIN
4-99
7277-2-2 880012-501 206153-1 206062-1 206060-1 206062-1
E51-50B
91-20-01 25
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
M20M SERVICE AND MAINTENANCE MANUAL ELECTRICAL EQUIPMENT CHART
NOTES:
1. SHADIN MODEL NO. INTERFACE WITH ii MORROW
SYSTEMS.
APOLLO, ARNAV AND NORTHSTAR LORAN
2. SHADIN MODEL NO. INTERFACE WITH BENDIX/KING KLN-88.
91-20-01 26
4-99
MOONEY AIRCRAFT CORPORATION
91-20-02
OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL M20M CHART ELECTRICAL EQUIPMENT
ELECTRICAL EQUIPMENT HARDWARE CHART
28 VOLT SYSTEM
800304 27-0001, 27-0108 THRU 27-0231, MOONEY DRAWING NUMBER REVISION LEVEL WILL VARY WITH EFFECTIVITY; REFER TO ENVELOPES
SERIAL NUMBER’s
PART NO.
CODE NOTES
DESCRIPTION
VENDOR
ACT1 ACT2
ACTUATOR ACTUATOR ACTUATOR ACTUATOR ACTUATOR ACTUATOR
MICRO MICRO MICRO MICRO MICRO MICRO
AIR1O1A AIR1 02A AIR1 03A AIR1 038 AIR104A AIR105A
SWITCH, AIC COMPRESSOR, AIC
MOONEY. MOONEY MOONEY. MOONEY. MOONN. MOONEY.
880067-501 770028-1 770002-501 770002-503 770016-501 770029-501
BL1
BULB HOLDER FOR BL1 BULB HOLDER FOR BL2 BULB (NAV-T/L) BULB (NAV-T/L) BULB (CONSOLE)
GE HH SMITH GE HH SMITH WHELEN WHELEN GE. GE. GE GE. CHI. MiN. CHI. MIN.
1818 1930 1816 1930
ACT3 ACT4 ACT5 ACTG
B’L2 B’L3 BL4 BL5
B’L6
EVAP. BLWR (FRT) EVAP. BLWR, (REAR) CONDENSER BLWR SWITCH, AIC PRESS.
(ALT)
BL7 BL8 BL9
(COMPASS) (POST LIGHT) BVLB (ANNUNCIATOR) BULB (ANNUNCIATOR)
BR1 BR2. BR3. BR5. BR7.5 BR10
CIRCUIT CIRCUIT CIRCUIT CIRCUIT CIRCUIT CIRCUIT
BR15 BR20 BR25 BR30 BR35 BR40 BR50 BR70
BRSW3 BRSW7.5 BRSW8 BRSW10 BRSW15 BRSW25
BULB BULB
SWITCH SWITCH SWITCH SWITCH SW\TCH SWITCH
BREAKER (10A) CIRCUIT BREAKER (15A) CIRCUIT BREAKER (20A) CIRCUIT BREAKER ~5A) CIRCUIT BREAKER (30) CIRCUIT BREAKER (35A) CIRCUIT BREAKER (40A) CIRCUIT BREAKER (50A) CIRCUIT BREAKER (70A)
KLIXON KLIXON KLIXON KLIXON KLIXON KLIXON. KLIXON. MECH PROD MECH PROD MECH PROD ETA ETA ETA ETA
C/B-SWITCH C/B-SWITCH C/B-SWITCH C/B-SWITCH C/B-SWITCH C/B-SWITCH
KLIXON KLIXON KLIXON KLIXON. KLIXON. KLIXON.
BREAKER (1A) BREAKER (2A) BREAKER (3A) BREAKER (5A) BREAKER (7.5A)
4-99
JE-5 JV-5 JV-26 MCD-2711 JE-17 JV-82
34-022-8030-85 34-021-2030-85 327 385
327(AV RED) 330
CM’7-n30
CM7-7327
7277-2-1 7277-2-2 7277-2-3 7277-2-5 7277-2-7.5 7277-2-10 7277-2-15 4200-002-20 4200-002-25 700-001-30
41-2-S14-LN2-35A 41-3-S34-LN2-40A 41-2-S34-LN2-50A 41-3-S14-LN2-70A 7270-5-3 7270-5-7.5 7270-5-8 7270-5-10 7270-5-15 7270-5-25
91-20-02 27
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART PART NO.
CODE NOTES
DESCRIPTION
VENDOR
BS1.
RELAY, BASE.
MAGNACRAFT
BUSPA BUS2B BUS2C BUS3A BUS3B BUSSC BUS4A BUS4B BUS4C BUS5A BUSSB BUSSC BUS5D BUSGA BussB BUS7A BUS8A BUS8B
BUSS BAR (2 BUSS BAR (2 BUSS BAR( BUSS BAR (3 BUSS BAR (3 BUSS BAR (3 BUSS BAR (4 BUSS BAR (4 BUSS BAR (4 BUSS BAR (5 BUSS BAR (5 BUSS BAR (5 BUSS BAR (5 BUSS BAR (6 BUSS BAR (6 BUSS BAR (7 BUSS BAR (8 BUSS BAR (8
PLC)
MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY.
PLC)
MOONEY.
PLP\
MOONEY. MOONEY.
913127-069 913127-089 913127-005 913127-093 913127-077 913127-085 913127-019 913127-035 913127-079 913127-081 913127-095 913127-083
C1
CAPACITOR
MALLORY
CGS302V-050R2C
CAP1 CAPP CAP3
CAP,WHITE CAP,BLACK CAP, DUST
WI\CROSW ALCO SW MATRIX SCIENCE.
CB1O1A.
BLOWER, DEFROST.
MOONEY.
64031 7-503
CC1O1A. CC1O2A. CC1O3A. CC1O38. CC103C.
MOTOR, COWL FLAP INDICATOR, COWL FLAP SWITCH, COWL FLAP SWITCH, COWL FLAP (M20J) SWITCH, COWL FLAP
MOONEY. MOONEY. MOONEY. MICRO-SWITCH MOONEY.
880050-505 880242-505 880052-517 12TW1-~0 880052-117
CF1OIA. CF1 02A. CF1 03A. CF1 08A.
ACTUATOR, FLAP INDICATOR, TRIM/FLAP INDICATOR, FLAP SWITCH, FLAP
MOONEY. MOONEY. MOONEY. C-H
750105-501 800242-501 800242-505 89061(3149
CLO3A CLO3B CL03C
CLAMP, 3/14/16/28 PIN CLAMP, 3 PIN. CLAMP, 3 P\N
AMP. AMP
CL04A
CLAMP, 4j8 PiN CLAMP, 5 PIN CLAMP, 6 PIN CLAMP, 9 PIN, Li. C6NTROi CLAMP, 9 PIN. CLAMP, 9 PIN ILOCK RETAINER /LOCK RETAINER (ALT) CLAMP, 9 PIN /LOCY RETAINER
CLO5A
CLOGA CLOSA CLOSE CLOSC
CLOSD
91-20-02 28
PLC) PLC)
PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC)
PLi
(ALT)
AMP.
70-303 913127-033
913127-097 913127-099 913127-087 913127-059 913127-073
15PA90-8W C-22
M83723/60-122RC
206070-1 M85O49-41-4A MS3057-4A MS3O57-48 206062-1
MS3057-6A/B MS3057-16AIB
sbx
AMP. AMP
206966-1
P/O 126-222 DE-24657 DE-51224-1 D11O278
DE-19977-5 DE-51224-1
4-99
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
CL1SA
CLAMP, 15 PIN /LOCK, RETAINER
DA51210-1 DA51 220-1
CL17A
CLAMP, 17 PIN /LOCK, RETAINER
DB51212 DB51221-1
CL25A
CLAMP, 25 PIN /LOCK, RETAINER CLAMP, 25 PIN /LOCK, RETAINER CLAMP, 25 PIN /LOCK, RETAINER CLAMP, 32 PIN CLAMP, BOOT
DB51212 DB51221-1 DB19977-2 DB51221-1 DB-24659 D-2041 8-2
CL258
CL25C CL32A CL328
dL3jA
VENDOR
PART NO.
M85049/52-1-22N MS3420-14 MS3420-16
(ALT)
CL37B
CLAMP, 3j PIN CLAMP,37PIN /LOCK, RETAINER
CM1.
CURRENT MONITOR.
MOONEY.
800221-505
CR1O1A. CR1O1B. CR102A. CR103A.
SWITCH, RUDDER TRIM. SWITCH, RUDDER TRIM. MOTOR, RUDDER TRIM INDICATOR, RUDDER TRIM
MOONEY. MOONEY. MOONEY. MOONEY.
880052-519 880052-119 880050-503 800242-503
CT1O1A. CT102A. CT103A. CT104A.
SWITCH, ELEV TRIM. INDICATOR, ELEV TRIM MOTOR, ELEV TRIM INTERFACE, TRIM
MOONEY. MOONEY. S-TEC MOONEY.
930023-233 800242-519
CV1O1A. CV1O1B. CV102A.
C/B-SW, STAND-BY VACUUM C/B-SW, STAND-BY VAC. PUMP, STAND-BY VACUUM.
CV103A. CV104A. CV104B. CV105A.
PUMP, STAND-BY VACUUM. C/B-SW, STAND-BY VAC. C/B-SW, STAND-BY VAC. PUMP/CLUTCH, STAND-BY VAC
MOONEY MOONEY AEROSAFE AEROSAFE MOONEY. MOONEY. AIRBORNE
D1
DIODE
206138-1
DC19977-3 DC51 222-1
(ALT) (ALT) D2
GE SARKES-TARZIAN ECG NTE FAGOR FAGOR
DIODE.
(ALT) (ALT) D4 D5
DIODEBRIDGE DIODEBRIDGE
DA1OIA.
AMMETER SHUNT
DAldlB:
EMPRO JANCO EMPRO JANCO
(ALT) AMMETER SHUNT
(ALT) DB1O1A.
TURN TURN TURN TURN
COORDINATOR COORDINATOR (ALT) COORDINATOR COORDINATOR
UNITED INSTRUMENTS ASTRONAUTICS ELECTROGYRO CORP UNITEDINST.
(ALT) (ALT)
4-99
01165-0-T14 80031 3-501
930023-233 930023-343 820904-2 820904-1 930023-247 930023-344
28C214CW-2 1N2483 1N5060 3720GE 10H3P 5854 5854
FB5001 FB5006
MLA-70A-100MV 8406-70
MLA-150A-100MV 8406-150 9013 CODE N.5
303990-028MSC 1394T100-32 9114 CODE N.21
91-20-02 29
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
VENDOR
DB102A.
TURN COORDINATOR
UNITED INST.
DC1OIA.
PROBE, CYLINDER#1
(ALT)
PART NO.
9112 CODE N.9
MS24482-1 AN5546-1*
USE ANOj6-1 ’ADAPT’ER:
DD102A. DD1OSA.
INDICATOR, O.A.T. O.A.T. PROBE SOCKET, 4 PIN
MOONEY. MOONEY. CINCH-JONES
880059-159 880004-501
DF1OIA DF102A. DF103A. DF104A.
FUELXMTR, LH/RH I/B FUEL XMTR, LH O/B FUEL XMTR, RH O/B FUEL XMTR, LH/RH O/B
MOONEY MOONEY. MOONEY.
610242-003 610243-003 610243-001
MOONEY.
610242-005
DG1O1A. DG102A. DG103A. DG104A. DG105A. DG1OGA.
IND, INSTRUMENT MODULE IND., INSTRUMENT, MODULE IND., INSTRUMENT MODULE #1 IND., INSTRUMENT MODULE #2 IND., INSTRUMENT MODULE IND., INSTRUMENT MODULE
MOONEY MOONEY. MOONEY. MOONEY. MOONEY. MOONEY.
880059-507 880059-511 880059-513 880059-505 880059-517 880059-519
DH1O1A. DH102A.
PROBE, Oil TEMP PROBE, OILTEMP
MOONEY.
880061-501 MS28034-1
DJ1O1A
TRANSDUCER, OIL PRESSURE.
DRUCK KULITE KULITE
PDCR 821-0662-100 APT-201 -1 000-1 OOG APT-1 54-1 000-1 00PSIG
DRUCK KULITE
APT-1 53-1 000-30PSIG
DRUCK KULITE
PDCR 920-U143 50 PSID APT-1 55-1 000-50D
DD1O1A.
(ALT) (M20M) (ALT) (M20J, K, DK1O1A.
R)’
TRANSDUCER, FUEL PRESSURE
(ALT) DK102A.
TRANSDUCER, FUELPRESSURE
(ALT) DL1O1A.
IND., TACH
DLld2A:
(OPTIONAL) SENSOR,TACH IND., TACH
MOONEY. B&D B&D MOONEY. B&D
TACH SENSOR TACH SENSOR TACH SENSOR INDICATOR, TACHOMETER INDICATOR, TACHOMETER.
B&D B&D. B&D MOONEY. MOONEY.
DL103A.
DLlObA:
dL144B dLld5A: DL1OGA.
S-304-CCT
PDCR-821-0662-30
880039-515 0520-003 0400-004 880039-517 0520-006 (SLICK MAGS) 0402-102 0406-003 *(NOTE 3) (BENDIX MAGS) 0402-104 0406-004 (NOTE 3) 880039-519 880039-523
INSTALLED ON 10 550 ENGINE BY TELEDYNE CONTINENTAL MOTORS.
DM1O1A DM102A DM103A
HOUR METER HOUR METER HOUR METER
oM164n.
H~kiVIEiEd
MOONEY. MOONfl. HOBBS DATCON HOBBS HOBBS
(ALT)
91-20-02 30
4-99
880035-507 880035-505 15006 SG-70 85000 15000
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
VENDOR
DP1O1A. DP1O1B. DP102A.
C/B, PITOT HEAT. C/B, PITOT HEAT.
MOONEY. MOONEY. AEROINSTR
930023-205 930023-305 PH502-24 AN581 2-1
AEROINSTR
PH502-12 AN5812
HEATEDPITOT
(ALT) DP103A.
PITOT, HEATED
(ALT) DP104A. DP105A. DR1OIA.
PLUG, 2 PIN
AN3115-1 AN3116-1
SOCKET
PROBE,TIT /ALTERNATE
DT1OIA. DT1O1B. DT102A. DT1 03A.
IND., EGT IND., EGT SWITCH, EGT, PROBE, EGT
DT1 d4A: DT105A.
IALTERNATE /ALTERNATE TRAY, LIGHT (28VDC) TRAY, LIGHT (14V)
DV1OIA.
DVldlB:
INDICATOR, INDICATOR, INDICATOR, INDICATOR, INDICATOR, INDICATOR,
PART NO.
4
FjoSjTldN
FUEL FLOW FUEL FLOW FUEL FLOW
(OPT).
(OPT). F/F(GALS) F/F (LBS) (OPT) F/F (GALS)(OPT)
MOONEY. MOONEY.
880055-503 880055-505
ALCOR ALCOR ALCOR MOONEY. MOONEY. ALCOR ALCOR ALCOR
46361 OEM-46161 OEM-80825 660110-000 880055-505 86255
MOONEY MOONEY. MOONEY. SHADIN SHADIN SHADIN
880034-501 880034-503 880034-505 91 2021 91 2023 91 2041
41338 41337
INDICATOR, F/F (LBS)(OPT).
SHADIN
912043
INDICATOR, F/F (LITERS)(OPT)
SHADIN
912047
INDICATOR, F/F (GALS)(OPT)
SHADIN
912081
TRANSDUCER, FUEL FLOW.
MOONEY. MOONEY. SHADIN
880030-501 880030-503
EG104A.
ACTUATOR, LbG GR: SWITCH, LDG GR. AIS SAFETY
MOONEY. MOONEY. MOONEY. MOONEY. MOONEY. MOONEY.
880037-507 560254-503 880037-501 560254-501 560254-505 880013-507
ELT1OIA ELT1 02A
SWITCH, ELT PANEL. TRANSMITTER, ELT
ARTU( ARTU(
110-416 453-0150
Fl F2 F3 F4
FUSE, 1 AMP FUSE, 5 AMP-3AG-SLO-BLO. FUSE, 10 AMP SLO-BLO. FUSE, 5 AMP
LITTEL LITTEL LITTEL
31 3001 313005 313010
FH1.
HOLDER,FUSE
DV102A.
(OPTIONAL)
Dvl d2B:
TRANSDUCER, F/F
EG1O1A.
ACTUATOR, LDG GR.
EG1 j~2A: EG1 03A:
(ALT) ACTUATOR, LDG GR.
(ALT)
(ALT) FH2
HOLDER,
FUSE
4-99
680501B
McGRAW-EDISON
FMO1-5A
LITTEL LITTEL McGRAW-EDISON
155020 155120 FHN42W
91-20-02 31
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PHONE JACK.
/WASHER /WASHER
SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT
JE1OIA
IGNITION CONTROL CABLE
LASAR LASAR
JM1O1A.
JM161B
SWITCH, MAGNETO /PLACARD /TERMINAL LUG SWITCH, MAG. ONICONN.)
JM102A.
MAGNETO
JMld3A:
(ALT) (ALT) PLUG,
BEND\X SCINTILLA BENDIX SCINTILLA BENDIX SCINTILLA JANCO BENDIX SCINTILLA BENDIX SCINTILLA LYCOMING BENDIX SCINTILLA
CODE NOTES
FON1
MIASHER /WASHER FONi
JM104A. JM105A. JM1OGA. JM107A.
JM108A. JM1OSA. JM11OA. JM111A.
JM112A. JM112A. JM JM
PHONE JACK.
MAGNETO
MAGNETO, LEFT: MAGNETO, RIGHT SWITCH, IGNITION MAGNETO, LH MAGNETO, RH IGNITION, PULSAR MAGNETO, VR MAGNETO, LH MAGNETO, RH MAGNETO, LH MAGNETO, RH BULB, 28V BULB, 14V
L5 L6 L7 L8 L9 L10
BULB BULB BULB BULB BULB BULB (28V) BULB BULB
L11 L12
SLICK SLICK SLICK TCM SLICK SLICK MOONC/. BENDIX
MAGNETO
L1 L2 L3 L4
BULB
BULB,
(SLICK)
SLICK(LASAR) SLICK(LASAR) SLICK ON10 LASAR) SLICK ON/O LASAR) GE GE GE. GE. CHI. MINI. CHI. MINI.
i4V’
GE. GE GE GE. GE GE
PART NO.
C-l 1 S-1028 S-l 029 C-l 12B S-l 028 S-1029 CD-1001-02 CH1001-XX 10-357210-9 10-187-468 10-126656 97-2273-1
D-4LN2021 D4LN-3000 LW-682555-11 10-382698 6244 6261 6260 10-357240-1 6393
6350 80031 5-501 S6RN-25-10 CD-4771 CD-4770 4372 (Rev. 4370 (Rev. 464-T-3 114 168-T-3 1/4 385 330
’CM7-7330 CM7-7327 370 1816
327
(AV RED) 327 1818 1495
LB102C
C/B, BEACON, ROTATING C/B, BEACON, ROTATING LIGHT, ROTATING BEACON. /ADAPTER LIGHT, ANTI-COLLISION (RE’D) LIGHT, ANTI-COLLISION (WHITE)
WHELEN WHELEN WHELEN WHELEN
930023-243 930023-343 WRML-24 WRML-65 90033-19 90033-20
LENS1 LENSP LENS3
ANNUNC. LENS (US). ANNUNCIATOR LENS ANNUNCIATOR LENS
MOONEY. MOONEY. MOONEY.
880048-613 880048-615 880048-617
LB1O1A LB1O1B. LB102A.
LBld2B
91-20-02 32
MOONEY MOONEY.
(FRAN) (US)
4-99
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
LENS4 LENS5 LENSG
ANNUNCIATOR LENS ANNUNCIATOR LENS ANNUNCIATOR LENS
LG1O1A. LG102A. LH1 LH2 LH3 LH4
LH5 LH6 LH7 LH8
PART NO.
VENDOR
MOONEY MOONEY. MOONEY.
880048-619 880048-621 880048-623
C/B, LOGO LIGHT LIGHT, LOGO.
MOONEY. WHELEN
930023-357 A730-1-28
LAMP HOLDER
MOONEY DIALIGHT WHELEN SLOAN
914083-1 270-1 930-01 71-702
(FRANCE)
LAMP,HOLDER IAMP HOLDER LAMP HOLDER
MIASHER, LOCK, INi. TOOTH IWASHER, LOCK, INT. TOOTH LAMP LAMP LAMP LAMP
ALLEN skAdLEY INSTRUMENTS. INSTRUMENTS SIGMATEC HH SMITH LEECRAFT ALLIED SPC NEWARK HH SMITH
HOLDER HOLDER HOLDER HOLDER
(ALT) (ALT) (ALT) (ALT) LH9
LAMP HOLDER
LH10 LH11
LAMP HOLDER LAMP HOLDER, COCKPIT
A-350-CN-CL-BK-SH-28 8555-0-U MS35334-21 M2898 0211-128 BA28-24-BW3 1V-192-971
WHELEN TEK-LITE
UTILITY).
(ALT)
1930 7-05
931-3103) LSL-11-128U
81N2561) 1925 01-0770437-00
LC-28-5 MS1 745-51 A 01-077-0142-04
LH12
LAMP
LL1O1A LL1O1B LL102A LL103A
SWITCH, LANDING LT SWITCH, LANDING LT LIGHT, TAXI/LANDING, LH/RH (i8Vj LIGHT, TAXI/LANDING, LH/RH (14V)
MOONEY. MOONEY. GE GE
880052-521 880052-121 4596 4509
LN1O1A. LN1O1B. LN 102A
C/B, NAV LIGHTS. C/B,NAV LIGHTS LIGHT ASSY, WING,
MOONEY. MOONEY. MOONEY.
930023-251 930023-351 800051-501
LP1O1A LP102A LP103A LP104A LP105A
DIMMER CONTROL BOX (28V/14v) DIMMER CONTROL BOX(28V) DIMMER CONTROL BOX(14V) SWITCH, LIGHT ASSY INVERTER, PLACARD
MOONEY (ELECTRONIC) MOONEY (RHEOSTAT). MOONEY (RHEOSTAT). MOONEY. ERG
800299-501 800299-503 800299-505 150085-501
LPS28-3-3P
LR1OIA. LR1O1B. LR102A.
C/B, RECOGNITION LIGHT C/B, RECOGNITION LIGHT
MOONEY MOONEY. MOONEY.
930023-231 930023-331 880049-501
LS1OIA. LS1O1B LS102A LS102B. LS103A LS104A LS105A LS1OGA
C/B, STROBE LIGHT C/B, LIGHTS, STROBE POWER SUPPLY, STROBE POWER SUPPLY, STROBE STROBE/NAV LIGHT ASSY (LH/WG) STROBE/NAV LIGHT ASSY (RH/WG) STROBE/TAIL LIGHT ASSY
MOONEY. MOONEY. WHELEN WHELEN WHELEN WHELEN MOONEY. WHELEN
930023-237 930023-337 01-0770329-00 01-0770329-01 01-0770054-12 01-0770054-13 470013-501
HOLDER, BAGGAGE LT
WHELEN
NAV-TP~IL
(d/H)
RECOGNITION LIGHT
POWER SUPPLY
CTAIL)
4-99
A413A,HDA,DF-28
91-20-02 33
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
VENDOR
LT1O1A LT1O1B LT102A
SWITCH, TAXI LIGHT SWITCH, TAXI LIGHT
MOONEY. MOONEY. G.E.
MA1OIA.
RECEPTACLE, AUX POWER
MB1O1A. MB1O1B.
C/B-SWITCH, AVIONICS MASTER C/B-SWITCH, RADIO MASTER
MOONEY MOONEY.
930023-213 930023-313
MC1O1A
CIGAR LIGHTER
MOONEY.
800336-503
ME1O1A.
CLOCK
MID-CONT PORSCHE MID-CONT MID-CONT PORSCHE PORSCHE
TAXI LIGHT LT/RT
CONN, 4 PIN (ALT) PIN
CONN,4PIN PIN
MIC1
MICROPHONE JACK.
SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT
/WASHER /WASHER MP1O1A. MP1O1B. MP102A. MP102B. MP103A.
C/B-SW, PROP DE-ICE C/B-SW., PROP. DE-ICE TIMER, PROP DE-ICE TIMER, PROP DE-ICE
NF1O1A. NF1O1B. NF102A.
C/B-SW, LOW-BOOST PUMP C/B-SW., BOOST PUMP PUMP, BOOST
NFld3A:
P’UM~,
TERMINAL BLOCK
(ALT~
BOOST
NFld4A: NF105A NF1OGA. NF108A. NF1OSA.
PUMP, BOOST PUMP, BOOST REGULATOR, FUEL BOOST PUMP C/B-SW, HI-BOOST PUMP
PA1OIA.
REGULATOR, VOLTAGE.
PA1 62A:
SWITCH, ALT ’FL6 (DUAL) SWITCH, ALT FLD (SINGLE).
PA103A. PA1 04A.
ALTERNATOR
PA1 d5A:
ALTERNATOR
PA1 66A:
ALTERNATOR
91-20-02 34
MOONEY MOONEY. WELDON WELDON WELDON WELDON WELDON WELDON
930023-211 930023-311 A81 638
MOONEY. AMERICAN PROD. ELECTRODELTA MOONEY. MOONEY. LYCOMING PRESTOLITE LYCOMING PRESTOLITE TCM TCM TCM ELECTRO SYSTEMS LYCOMING
(ALT) \GEAR ASSEMBLY ALTERNATOR /INSTALL KIT (REF 600180)
4-99
C-128 S-1028 S-l 029 930029-245 930023-345 3E1899-1 8-45018 C-40521
MASSEY MOONEY.
(ALT)
MD-89 944.641.213.00 6016177 601 6125 944.612.21 7.00 999.652.351.12
MOONEY. MOONEY. B.F. GOODRICH McCAULEY McCAULEY
WELDON
(ALT)
PAld7A:
880052-523 880052-123 4596 AN2552-3A
(ALT) ME102A.
PART NO.
81638 8163A A81 63A 100548 Al 0051D A8152-B VR536 930023-219 800270-501 DGR-2 VR-802 880052-525 880052-503 LW-14367 ALU-6421 -LS LW1 5404 ALY-8420 649280 649172 649123 ES 4009-LS 05K-21065
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE M20M SERVICE AND MAINTENANCE MANUAL ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
PA1 08A.
FILTER
MOONEY. MOONEY. MICRO SW. MOONEY. KLIXON KUXON TCM
880014-501 800307-501 CSLA1GE 800270-503
(ALT~
PAldSA:
SENSOR,
PA11OA. PA111A.
REGULATOR, VOLTAGE. SENSOR, CURRENT (110 A). SENSOR, CURRENT (175 A).
CURRENT.
PART NO.
7235-1-110 7236-1-175 649304
PA111B. PA112A.
ALTERNATOR
PB1OIA. PB102A. PB102B. PB103A. PB103B PB1 05A.
BATTERY SWITCH, MASTER SWITCH, MASTER SWITCH, BATTERYSELECT SWITCH, BATTERY SELECT BATTERY
GILL MOONEY. MOONEY. MOONEY. MOON EY. CONCORDE
G-243 880052601 880052-101 880052-527 880052-1 27 RG24-11M
PLUG,2PIN PLUG,2PIN PLUG, 2 PIN(FEMALE) PLUG, 2 PIN. PLUG, 3 PIN PLUG,3PIN PLUG, 3 PIN PLUG, 3 PIN. PLUG, 4 PIN PLUG, 4 PIN PLUG, 5 PIN PLUG, 6 PIN PLUG,8PIN PLUG,SPIN PLUG,SPIN PLUG, 9 PIN PLUG, 9 PIN PLUG,SPIN PLUG, 14 PIN PLUG, 14 PIN PLUG, 14 PIN PLUG, 15 PIN PLUG, 16 PIN PLUG, 17 PIN PLUG, 20 PIN PLUG, 25 PIN PLUT, 15 PIN PLUG, 26 PIN PLUG, 28 PIN PLUG, 32 PIN
AMP MOLE( DEAN.
1-48031&0 03-06-1 023 DEA900020
PLOPA PL02B PLOPC PL02D PL03A PL03B PU)3C PL03D PL04A PL04B PLOSA PLOGA PL08A PLOSA PLOSB PLOSC PLOSD PLOSE PL14A PL14B PL14C PL15A PL1GA PL17A .PL20A PL25A PL25B PL26A PL28A PL32A m*
(100A)
AMP AMP.
MS3106A-24-9S 1380303-0 206037-2
MS3106A-10SL-3S MS3106A-28-6P AMp.
iAAiRR>X S61EN’CE: AMP. AMP. AMPHENOL
MOiu<’ AMP.
MOONEY MOONEY. AMP.
AMP.
MOONEY:
206060-1
MS3106A-32-17S MS3106A-14S-5S MS3106A-28-22S 205838-1 206708-1 126-222
DE-SS 03-06-2092 206485-1 930021-1 930021-513 206043-3
DA15S 206037-1 DBM 17W2S 930021-501
DB25S AMP. MOONEY. AMP. MATRIX SCIENCE
205208-1 930021-505 2058343
M83723/86R2232N
USE MS3420-14 OR -16 BOOT WITH CONNECTOR.
PL34A PL34B
PLUG, 34 PIN PLUG, 34 PIN
MOONEY. MOONEY.
PL37A PL37B
PLUG, PLUG,
AMP.
PS1OIA. PS102A.
C/B, STARTERSOLENOID C/B, STARTERSOLENOID
37 PIN 37 PIN
930021-507 930021-515 206150-1
DC37S KLIXON KLIXON
4-99
7277-2-10 7277-2-5
91-20-02 35
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART CODE NOTES
DESCRIPTION
VENDOR
PS1 03A.
STARTER
PRESTOLITE LYCOMING TCM TCM B&C SPECIALITY
(ALT)
PS1 64A:
STARTER
PSld5A:
STARTER
R1 R2 R3 R4 R5 R6 R7
RESISTOR (20 OHM/1OW) RESISTOR (5 OHM/1OW).
(ALT)
R8
RESISTORâ&#x20AC;&#x2122; (150 dHMkVlj)
R9 R10 R11. R12 R13
RESISTOR (3.9K OHMI 1/2W) RESISTOR (3.OK OHMI 1/2W) RESISTOR (1 OHM/25W). RESISTOR (70 OHM/1OW) RESISTOR (10.OK OHM/1W)
DALE DALE NEWARK. NEWARK DALE. ALLEN-BRADLEY ALLEN BRADLEY SELECTROL BOURNS NEWARK. CLAROSTAT OHMITE OHMITE OHMITE DALE DALE OHMITE
RB1O1A.
BLOWER, RADIO
KING.
RC02A RCOPC RCOPD RC03A RCOSB RC03C RC03D RC04A RC04B RCOGA RC08A RCOSA RCOSB RCOSC RCOSE
RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE,
RESISTOR,MAPLIGHT (5000HM) RESISTOR (100 OHM) RESISTOR (7.5 OHM) RESISTOR (1K OHMI~LW) RESISTOR (5K OHM).
(ALT) (ALT) (ALT) (ALT)
RC1PA RC14A RC14B RC14C RC1GA RC1GB
RCPOA RC26B RC28A RC32A RC34A RC34B RC37A
91-20-02
36
2 2 2 3 3 3
AMP
PIN.
DEAN.
PIN (MALE) PIN. PIN. PIN. PIN. 3 PIN. 4 PIN. 4 PIN 6 PIN. 8 PIN. 9 PIN. 9 PIN. 9 PIN 9 PIN 12 PIN 14 PIN 14 PIN 14 PIN 16 PIN 16 PIN 20 PIN 26 PIN 28 PIN 32 PIN 34 PIN 34 PIN 37 PIN
AMP AMP. AMP.
AMP.
MATdIX SCIENCE. AMP. AMP. AMP.
AMP: MOLEX MOONEY AMP. AMP. AMP. AMP. MOONEY. MOONEY. AMP. MATRIX SCIENCE MOONEY. AMP. AMP.
4-99
PART NO.
MHJ-4016 LW-1 5572 646275 637847 BSC206-149
RH-10-20 OHM RH-10-5 OHM 919029-501
09F976 RH-50-7.5 OHM RC42-GF1MJ WA2-G056S502UA 149-11-502 3862C-282-502A 12F9905R 5.OK VC3D 23J
N/A N/A
RH:25:1 OHM RH-10-70 OHM
N/A 071-4037-01 1-480319-0
DEA900020 MS3100-24-9P 1-480305-0 206036-2 206207-1
MS3100-28-68 206153-1 MS3100-32-17P MS3100C-28-22P 205841-2 206705-2 206905-1 DESP 205486-1 03-06-2122 930021-2 203540-1 206044-1 206037-1 206036-1 930021-502 930021-506 206152-1
M83723/83K2232N 930021-508 204814-1 206151-1
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART PART NO.
CODE NOTES
DESCRIPTION
VENDOR
RL1.
RELAY, BATT. (28V/200A)
RELAY RELAY RELAY SOCKET TERMINAL
C-H C-H KISSLING KISSLING C-H KISSLING KISSLING C-H KISSLING MOON EY. C-H C-H MAGNACRAFT KISSLING P&B. P&B P&B B&C B&C B&C B C.
BC41 0-1
SA162A:
ALTERNATOR, STAND-BY HOUSING, CONNECTOR TERMINAL (1/4") CONTROLLER, STBY. ALT.
SB1OIA. SB102A. SB1 03A.
C/B, SPEEDBRAKE SWITCH, CONTROL WHL RELAY, SPEEDBRAKE
KLIXON PRECISEFLT PRECISEFLT
7277-2-3 01265 01384
SB1 04A.
DIODE
1~:Tj RL2 RL3 RL4 RL5
(ALT) RELAY,
BATT.’ (14V/2bOAj
RELAY RELAY
LdG. i28V/50;4)
RELAY,
(ALT) /BRACKET (2 EA) RL6 RL7 RL8 RL9 R10
SA1OIA.
SB165A: SB1 06A.
RELAY
(28V/100A)
RELAY, (14V/200A)
MOTOR, SPEEDBRAKE SWITCH, SPEEDBRAKE SOLENOID, CLUTCH
SPK1 SPK2 SPK3
SPEAKER, ALERT SPEAKER, CABIN
SW1. SW2 SW3. SW4. SW5.
SWITCH
Sws. SW7. SW8. SW9.
Swlb SW11 SW12
26.57.01 26.57.02 6041H-1 05A 26.64.01 26.64.21 6041 H-220 26.72.03 800375-001 6041 H-53 6041 H-105R
W67RCSX-3 28.08.01 VF4-1 5-H11 VCF4-1 002 26A1 348C
12-003 14-026
BC203-2
1 N2483 1N5060
(ALT) (ALT)
SB1 07A. SB108A.
6041 H-202 6041H-202A
INTERFACE, SPEEDBRAKE
SONALERT
SWITCH, DEF: BLWR: SWITCH, LIMIT, RUD.TRIM SWITCH,UP LIMIT, LDG SWITCH, DN LIMIT, LDG. (ALT) SWITCH, CAsI’N LTS: SWITCH
SWITCH, LDG: SWITCH, MIG-KEY
GE PRECISEFLT PRECISEFLT
3720-GE
PRECISEFLT MOONEY.
01678 800314-501
ARCHER ARCHER MALLORY
40-1 333(3 40-1 325 SC628
MICRO CHERRY. MICRO MICRO O~r0 MICRO CARLING MOONEY. C-H ALCO
1SE1-T E51-50B
C-H GRAYHILL. C-H CARLING.
(ALT)
SWITCH, CHT: SWITCH, FLAP SWITCH, CABIN LTS(MASTER)
4-99
01532 01505
V3-1
dT-2R-47 P6-24014 1 CH116-6
RCSI1-VBBOW 88001 3-507 8906K2875
’MPE-106F-C-22-9
SA1 RV20 71AD30-02-2-AJN 89061(4731 RAS11-VBBOW
91-20-02 37
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20M
ELECTRICAL EQUIPMENT CHART
CODE NOTES
DESCRIPTION
VENDOR
SWITCH (ALT)
/CAP, WHITE
MICRO MICRO
swlk
(ALT) SWITCH,
C&K
SW15
SWITCH, LDG, OVERRIDE
SWl 3
FIF: MEM.
swli;
/SWITCH (ALT) /LOCKRING /LOCKWASHER /HEX NUT (2 EA) SWITCH,VAC.HI/LO.
SW1 7
SWITCH
C-H. C-H. C-H MOONEY. CARLING TSCHUDIN TSCHUDIN TSCHUDIN MOONEY. CARLING
s’wls
LENS BULB SWITCH SWITCH
7101K
EA) (NKK)
C-H
SW(ALT)
12TW1-10 15PA90-8W MS27753-38
DLB241-W01-L3C/ AT506M/AT503MB
NKK
lsljTTbNliodK dlNCilLdCK’ WASH’EWHEX NUT i2
PART NO.
SB1 DDX492-2 29-761 16-886 15-966-6 880012-501 TILC64-1 S-WH FN 504202 464415 590002 880062-501 TIGM64-1 S-WHFN
SW19 SW20 SW21 SW22 SW23 SW25 SW35
SWITCH SWITCH,MIKEKEY SWITCH, SPDBRK SWITCH SWITCH SWITCH
CROUZET ALCO NKK. NKK.
VR1.
VARISTOR
GE
WM1O1A WM102A
MASTER WARNING MASTER WARNING
MICRO SWITCH MICRO SWITCH.
WS1OIA WS103A
ALERT, STALL WARN/GEAR WARN SWITCH, STALL WARNING
IAl. MOONEY.
950D0309-000 800364-507
WT1OIA
ANNUNCIATOR ANNUNCIATOR ANNUNCIATOR ANNUNCIATOR
MOONEY. MOONEY. MOONEY. MOONEY.
880048-501 880048603 880048-507 880048-509
WT1 02A VI~T103A WT1 04A
CkoljZEi
MS35058-22 83-450-001 83-452-504 MPE1OGF
MB2085SBiW01-EA MB2085SB1W01-EA V47ZA05 DSK-104-GYR DSB-11-RRRR-LRP
NOTES:
1. SHADIN MODEL NO. INTERFACE WITH II MORROW
APOLLO, ARNAV AND NORTHSTAR LORAN
SYSTEMS. 2. SHADIN MODEL NO. INTERFACE WITH BENDIX/KING KLN-88 OR KLNS0 SERIES.
3. B 8 D TACH SENSOR’S P/N 0406-004 \S 9/16 DIAMETER FOR SLICK MAGNETOS
91-20-02 38
DIAMETER FOR BENDIX MAGNETOS. 0406-003 IS 11/16
4-99
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE M20M
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
4-99
91-20-02 39
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPOW~TION
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
91-20-02 40
4-99
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART 91-20-03
ELECTRICAL SYSTEM HARDWARE CHART
28 VOLT
S/N 27-0240 THRU 27-0246, SCHEMATIC NO. 800383 (M1) (REV. G) S/N 27-0247 THRU 27-0257, SCHEMATIC NO. 800383 (M2) (REV. H) S/N 27-0258 THRU 27-TEA, SCHEMATIC NO. 800383 (M3) (REV. M) CODE
DESCRIPTION
VENDOR
PART NO.
AC1O1A AC102A AC103A AC103B AC104A AC105A AC1OGA
SWITCH, AIR COND. COMPRESSOR, AIR COND. BLOWER, EVAP. (FRONT) BLOWER, EVAP. (REAR) BLOWER, CONDENSOR SWITCH, AIR COND. PRESS CONNECTOR, AIR COND
MOONEY MOONP/ MOONEY MOONEY MOONEY MOONEY GORY COMP. GORY COMP.
880067-501 770028-1
CONTACTS SWITCH SWITCH SWITCH SWITCH SWITCH SWITCH
AT102A AT103A AT104A AT105A AT1OGA
ACTUATOR, ACTUATOR, ACTUATOR, ACTUATOR, ACTUATOR, ACTUATOR,
BR1
CIRCUIT BREAKER
AT1O1A
MICRO MICRO MICRO MICRO MICRO MICRO
SWITCH SWITCH SWITCH SWITCH SWITCH SWITCH
770002-501 770002-503 77001 6-501
770029-501 CSLT-P1 PA
CB017-5S JE-5 JV-5 JV-26 MCD-2711 JE-17 JV-82 4200-002-1 7277-2-1 4200-002-2 7277-2-2
BR50 B270
CIRCUIT BREAKER (50A) CIRCUIT BREAKER (70A)
MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. KLIXON MECH PROD. MECH PROD. MECH PROD. ETA ETA MECH. PROD. ETA ETA
BS1OIA
BASE, RELAY
MAGNACRAFT
70-303
BU2A BUeB BU2C BU2D BU2E BU3A BU3B BU3C BU4A BU4B BU4C BU4D BU5A BU5B
BUS BUS BuS BUS BUS BUS BUS BUS BUS BUS BUS BUS BUS BuS
MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY
913127-33 913127-97 913127-99 913127-75 913127-65
(1A)
(ALT) BR2
CIRCUIT BREAKER
(2A)
(ALT) (3A)
BR3
CIRCUIT BREAKER
BR5
CIRCUIT BREAKER (5A)
(ALT) (ALT) BR7.5
CIRCUIT BREAKER (7.5A)
(ALT) BR10
CIRCUIT BREAKER
(10A)
(ALT) BR15
CIRCUIT BREAKER
(15A)
(ALT) BR20 BR25 BR30 BR35 BR40
CIRCUIT CIRCUIT CIRCUIT CIRCUIT CIRCUIT
BREAKER BREAKER BREAKER BREAKER BREAKER
(20A) (25A) (30A) (35A) (40A)
(ALT)
BAR BAR BAR BAR BAR BAR BAR BAR BAR BAR BAR BAR BAR BAR
(2 (2 (2 (2 (2 (3 (3 (3 (4 (4 (4 (4 (5 (5
PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC) PLC)
PLC) PLC)
4-99
NOTES
4200-002-3 7277-2-3 4200-002-5 7277-2-5 4200-002-7.5 7277-2-7.5 4200-002-10 7277-2-10 4200-002-15 7277-2-15 4200-002-20 4200-002-25 4200-002-30 41-2-S34-LN2-35A
41-3-S34-LN2-40A 700-001 -40
41-2-S34-LN2-50A 41-3-S34-UJ2-70A
913127-87 913127-59 913127-73 913127-69 913127-89 913127-5 913127-53 913127-93 913127-77 91-20-03 41
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
BUSC
BUS BAR
CODE
MOONEY
913127-85
DESCRIPTION
VENDOR
PART NO.
BUSD BUGA BUGB BUâ&#x20AC;&#x2122;IA BUSA
BUS BUS BUS BUS BUS
MOONEY MOONEY MOONEY MOONEY MOONEY
913127-19 913127-35 913127-79 913127-81 913127-95
BW3 BW7.5 BW1O BW15 BW25
SWITCH, SWITCH, SWITCH, SWITCH, SWITCH,
KLIXON KLIXON KLIXON KLIXON KLIXON
7270-5-3 7270-5-7.5
CA1OIA CA1O2A
CAPACITOR CAPACITOR (1000 PF)
MALLORY NEWARK
CGS3O2V050R2C 18F2711 TYPE 5GAD1O
CB1O1A
BLOWER, DEFROSTER
MOONEY
64031 7-503
CC1OIA CC1O2A CC1O3A CC103B CC1O3C
MOTOR, COWL FLAP INDICATOR, COWL FLAP SWITCH, COWL FLAP SWITCH, COWL FLAP (J) SWITCH, COWL FLAP
MOONEY MOONEY MOONEY MOONEY MOONEY
880050-505 800242-505 880052-517 12TW1-10 880052-117
CF1OIA CF1O2A CF1 03A CF1O4A
ACTUATOR, INDICATOR, INDICATOR, INDICATOR,
MOONEY MOONEY MOONEY MOONEY
7501 05-501 800242-501 800376-501 800391-502
CLO3A CLOSE CLOSC
CLAMP, 3,14,16,28 PIN
AMP
206070-1
CLAMP, CLAMP,
CLO4A CL04D CLO5A
CLAMP, 4, 8 PIN CLAMP, 4 PIN CLAMP, 5 PIN
(5 PLC)
BAR (5 BAR (6 BAR (6 BAR (7 BAR (8
PLC) PLC) PLC) PLC) PLC)
C/B C/B C/B C/B C/B
(3A) (7.5A) (10A) (15A) (25A)
FLAP
TRIM/FLAP TRIM/FLAP TRIM/FLAP
3 PIN
(ALT)
CLOGA CLO7A CLOSA CLOSE CLOSC
(ALT) CLAMP, 6 PIN (ALT) CLAMP, 7 PIN CLAMP, 9 PIN CLAMP, 9 PIN CLAMP, 9 PIN RETAINER, LOCK
AMP
BENDIX
CL15A
CL17A
CL25A CL25B CL25C 91-20-03 42
7270-5-25
206062-1 10-101971-8-3 MS3057-6A
MS3O57-6B MS3057-16A MS3O57-168 MS3O57-12B AMP AMP
206966-1 P/O 126-222
DE-24657 DE 51224-1 D11O278 D-2041 9-16
RET. LOCK RET. LOCK CLAMP, 9 PIN RETAINER, LOCK CLAMP, 15 PIN LOCK RETAINER CLAMP, 15 PIN (ALT) CLAMP, 17 PIN LOCK RETAINER CLAMP, 25 PIN LOCK RETAINER CLAMP, 25 PIN LOCK RETAINER CLAMP, 25 PIN
(ALT) (ALT)
CLOSD
7270-5-10 7270-5-15
M8O49-41-4A MS3O57-4A MS3O57-4B
3 PIN
DE-19977-5
DE-51224-1 DA51210-1 DA51220-1 DA19977-1
DB51212 DB51221-1 DB51212 DB51221-1 DB1SS77-2 DB51221-1 DB24659 4-99
NOTES
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART LOCK RETAINER
D-20418-2
CL32A
CLAMP, 32 PIN
M85049/52-1-22N
CODE
DESCRIPTION
CL32B
CLAMP/BOOT
VENDOR
CL37B
CLAMP, 37 PIN CLAMP, 37 PIN LOCK RETAINER
CM1O1A
CURRENT MONITOR
CR1O1A CR1O1B CR102A CR1 03A
SWITCH, RUDDER TRIM (WHITE) MOONEY SWITCH, RUDDER TRIM (BLACK) MOONEY MOONEY MOTOR, RUDDER TRIM MOONEY INDICATOR, RUDDER
880052-519 880052-119 880050-503 800242-503
CT1O1A CT1 02A CT1 03A CT104A CT1 05A
SWITCH, TRIM INDICATOR, ELEV. TRIM MOTOR, ELEV. TRIM
930023-233 800242-519
TRIM INTERFACE INDICATOR, ELEV. TRIM
CV1O1A CV1O1B CV102A CV103A CV104A CV104B CV105A
CIRCUIT BREAKER/SWITCH MOONEY CIRCUIT BREAKER/SWITCH MOONEY AEROSAFE PUMP, STAND-BY VACUUM AEROSAFE PUMP, STAND-BY VACUUM SWITCH/C-B, STAND-BY VACUUM MOONEY SWITCH/C-B, STAND-BY VACUUM MOONEY PUMP/CLUTCH ASSY, STDEY VAC. AIRBORNE
930023-233 930023-333 820904-2
DA1O1A
SHUNT, AMMETER
EMPRO JANCO EMPRO JANCO
MLA-70A-1 OOMV 8406-70
UI ASTRONAUTICS ELEC. GYRO CORP.
UI UI
9013 CODE N.5 303990-028MSC 1394T100-32 9114 CODE N.21 9112 CODE N.9
(ALT)
NORWICH
MS24482-1 AN5546-1 102-00007
DD1OIA DD1 02A DD103A
INDICATOR, OAT PROBE, OAT SOCKET, 4 PIN
MOONEY
DF1O1A DF1 02A DF1 03A DF1 04A DF1 05A DF1 06A DF107A DF1 08A DF1OSA DF11OA DF111A
XMTR, FUEL, INBD, LH/RH XMTR, FUEL, OUTED, LH XMTR, FUEL, OUTED, RH XMTR, FUEL, OUTED, LH/RH XMTR, FUEL FLOAT/ARM, RH I/B FLOAT/ARM, RH O/B FLOAT/ARM, LH I/B FLOAT/ARM, LH O/E
(ALT) DA1O1B
SHUNT, AMMETER
(ALT) DB1O1A
TURN COORDINATOR
(ALT) (ALT) (ALT) DB102A
TURN COORDINATOR
DCIOIA
PROBE, CHT (ALT)
TRANSDUCER PROCESSOR
NOTES
MS3420-14 MS3420-16 206138-1 DC19977-3 DC51222-1
(ALT) CL37A
PART NO.
MOONEY
Mll-S-9419 MOONEY S-TEC MOONEY MOONEY
MOONEY CINCH-JONES MOONEY MOONEY MOONEY MOONEY AVAQ AVAQ AVAQ AVAQ AVAQ AVAQ AVAQ 4-99
800221-505
01165-0-T14 80031 3-501 800391 -501
820904-1 930023-247 930023-347 28C214-CW-2
MLA-150A-100MV 8406-150
880059-159 880004-501
S-304-CCT 610242-3 610243-3 61 0243-1 610242-5 9450563001 94005631 02
9400563104 9400563101 9400563103 9450563002 9450563303 91-20-03 43
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
DG1O1A DG102A DG1 03A DG1 04A DG1 05A DG1 06A DG1 07A DG1 08A DG1OSA DG11OA DG111A DG112A DG113A DG114A DG115A
MODULE, MODULE, MODULE, MODULE, MODULE,
MODULE, INSTRUMENT MODULE, INSTRUMENT, #1 MODULE, INSTRUMENT, #2 MODULE, INSTRUMENT CLUSTER, D/A CLUSTER, D/A CLUSTER, DIGITAL CLUSTER, DIGITAL CLUSTER, D/A CLUSTER, DIGITAL
DH1O1A DH102A
PROBE, OIL TEMP PROBE, OIL TEMP
DI1O1A
DIODE
INSTRUMENT INSTRUMENT
INSTRUMENT, #1 INSTRUMENT, #2 INSTRUMENT
DJ1O1A
XDCR, OIL PRESS
(ALT) (M20J) (ALT) DJ1O1B
XDCR, OIL PRESS (M20M)
DK1OIA
XDCR, FUEL PRESS
(ALT) XDCR, FUEL PRESS
(ALT) (ALT) TACHOMETER
(OPTIONAL) DL102A DL1 03A
SENSOR, TACH TACHOMETER
DL1 04A DL104B DL1 04C DL1 04D DL1 05A DL1OGA DL1 07A DL108A
SENSOR, SENSOR, SENSOR, SENSOR,
DM1O1A DM102A DM 103A
HOUR METER HOUR METER HOUR METER
DM104A
HOUR METER
(CPTIONAL) TACH TACH TACH TACH TACHOMETER TACHOMETER SENSOR, TACH SENSOR, TACH
(ALT) (ALT) 91-20-03
MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY
880059-511 880059-513 880059-515 880059-517 880059-519 880059-523 880059-525 880059-521 880093-501 880093-503 880093-505 880093-507 880093-509 880093-511
MOONEY
880061-501
MS28034-1
ECG NTE FAGOR FAGOR
BRIDGE, DIODE BRIDGE, DIODE
44
880059-507
DIODE
D1104A D1105A
DL1O1A
MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY
NOTES
1 N2483/1 N5060
(ALT) (ALT)
DK102A
PART NO.
GE
(ALT) D1102A
VENDOR
(SLICK) (BENDIX) (BENDIX) (SLICK)
(SLICK) (BENDIX)
3720-GE 10H3P 5854 5854
1=85001 FB5006
DRUCK KULITE PATRIOT KULITE
PDCR 821-0662-100 APT-1 54-1 000-1 00PSIG KA21-014-1 OOG
DRUCK KULITE DRUCK KULITE PATRIOT
PDCR-821-0662-30 APT-153-1000-30 PSIG PDCR-920-U 143-50 PSID APT-1 55-1 000-50D KA2 1 -01 6-50D
MOONEY B&D B&D MOONEY B&D B&D B&D B&D B&D MOONEY MOONEY J-P INSTR. J-P INSTR.
880039-515 0520-003 0400-004 880039-517 0520-006 0402-102 0402-104
MOONEY MOONEY HOBBS DATCON HOBBS HOBBS
880035-507 880035-505 15006
4-99
APT-201-1000-100G
0406-004 0406-003 880039-519
880039623 420809 420807
SG-70 85000 15000
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE
DESCRIPTION
VENDOR
PART NO.
DP1O1A DP1O1B DP1O1C DP1OPA
C/B C/B C/B
MOONEY MOONEY
930023-205
PITOT, HEATED
AERO INSTR
MOONEY
(ALT) DP103A
PITOT, HEATED
AERO INSTR
(ALT)
930023-305 930023-353 PH502-12 AN5812 PH502-12 AN5812 AN3115-1 AN3116-1
DP104A DP105A
PLUG SOCKET
DR1O1A DR1O1B
PROBE, TIT PROBE, TIT
MOONEY MOONEY
880055-503 880055-505
DT1OIA DT1O1B DT102A DT1 03A
INDICATOR, EGT INDICATOR, EGT SWITCH, EGT (4 POSITION) PROBE, EGT
ALCOR ALCOR ALCOR MOONEY MOONEY ALCOR ALCOR ALCOR
46361
KULITE PATRIOT PATRIOT
APT-231-1000-25A KA21-015-25A SP1 00-110-25A
MOONEY MOONEY MOONEY SHADIN MOONEY MOONEY SHADIN
880034-501 880034-503
MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY MOONEY
880037-507 560254-503 560254-507 880037-501
(ALT.) (ALT) DT104A DT105A
LIGHT TRAY LIGHT TRAY
DU105A
TRANSDUCER, MAP
(28V) (14V)
(ALT) (ALT) DV1OIA
INDICATOR, FUEL FLOW
(OPTIONAL) (OPTIONAL) DV102A
INDICATOR, FUEL FLOW TRANSDUCER, FUEL FLOW
DV102B
TRANSDUCER, FUEL FLOW
EG1O1A
ACTUATOR, LDG
DV1O1B
(OPTIONAL)
(ALT) (ALT) EG1 02A
ACTUATOR, LDG
EG103A EG1 04A
ACTUATOR, LDG SWITCH, AIRSPEED
ET1O1A ET1 02A ET103A ET104A
SWITCH, ELT PANEL TRANSMITTER, ELT CABLE ASSY, REMOTE
(ALT)
REMOTE UNIT ASSY
(OPTIONAL) ET105A
MAIN UNIT ASSY.
FH1O1A
FUSE HOLDER
(ALT) FH102A
FUSE HOLDER
FN1O1A
JACK, PHONE
FN102A
WASHERS JACK, PHONE WASHERS
OEM-46161 OEM-80825 660110-000 880005-505 86225 41338 41337
880034-505 912041TD 880030-501
1
880030-503
6805018
560254-501 560254-505 88001 3-507
ARTU( ARTEX AMERI-KING AMERI-KING AMERI-KING AMERI-KING
110-416 453-0150
LITTEL FUSE LITTEL FUSE McGRAW EDISON
155020 155120 FHN42W
SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT
C-l 1
4-99
NOTES
4500041 450004
450004-1\1/-1H AK-450
S-1028/S-1029 C-112B
S-1028/S-1029
91-20-03 45
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
FU1O1A FU102A FU103A FU104A FU105A FU1OGA
FUSE (1 AMP) FUSE (5AMP-3AG-SLO-BLO) FUSE (10 AMP, SLO-BLO) FUSE (5 AMP) FUSE (0.5 AMP) FUSE (2 A MP)
LITTEL LITTEL LITTEL McGRAW-EDISON McGRAW-EDISON LITTEL
313001
JElOtA JE1 02A JE103A JE104A
CONTROL, IGNITION
LASAR (SLICK) LASAR (SLICK) SLICK (LASAR) SLICK (LAZAR)
JM1O1A
BENDIX SCINTILLA SWITCH, IGNITION BENDIX SCINTILLA /PLACARD BENDIX SCINTILLA /LUG, TERMINAL SWITCH, IGNITION (INCL CONN.) JANCO
JM1O1B JM102A
CABLE
MAGNETO, LEFT MAGNETO, RIGHT
MAGNETO
(ALT) (ALT) JM103A JM104A JM105A JM1OGA JM107A JM108A JM1OSA JM11OA JM111A JM113A
LA1O1A LA102A LA103A LA104A LA105A LA1OGA LA107A LA108A LA1OSA LA11OA LA111A LA112A LA113A LA114A
PLUG, MAGNETO MAGNETO
MAGNETO, LEFT MAGNETO, RIGHT SWITCH, IGNITION MAGNETO, LEFT MAGNETO, RIGHT IGNITION, PULSAR MAGNETO, L&R MAGNETO, L&R MAGNETO, L&R(OPT.) LIGHT BULB, 28V LIGHT BULB, 14V
LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT LIGHT
BULB BULB BULB BULB BULB BULB BULB BULB BULB BULB BULB BULB
LA115A
LIGHT LED
LB1O1A LB1O1B LB1 02A
C/B-SW, BEACON, WHITE C/B-SW, BEACON, BLACK BEACON, ROTATING /ADAPTER
BENDIX SCINTILLA BENDIX SCINTILLA LYCOMING BENDIX SCINTILLA SLICK SLICK SLICK BENDIX-SCINTILLA SLICK SLICK MOONEY
TCM/BENDIX TCM BENDIX GE GE GE GE CHICAGO MINI CHICAGO MINI GE GE GE GE GE GE GE PACIFIC PREC. PROD MOUSER
MOONEY MOONEY WHELEN WHELEN
LB1 028 LB1 02C
LIGHT, ANTI-COLLISION (RED) WHELEN LIGHT, ANTI-COLLISION (WHITE) WHELEN
LC1OIA
CONTROL BOX, LIGHT
91-20-03 46
MOONEY
4-99
313005 313010
FMO1-5A FM01-.50A
CD-1001-02 CH-1 001-XX CD-4771 CD4770 10557210-9 10-187-468 10-126656 97-2273-1 D4LN2021 D4LN3000 LW-682555-11 10-382698 6224 6261 6260 10-357240-1 6393 6350 80031 5-501 10-79020-10 640896-1 10-79020-1 20 400
168-T-3 114 385 330
CM7-7330 CM7-7327 370 1816 AVIA. RED, 327 327 1818 1495 4596 P28028 351-0003 930023-243 930023-343 WRML-28 WRML-65 90033-19 90033-20 800268-509
NOTES
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
VENDOR
CODE
DESCRIPTION
LE1O1A LE1 02A LE1 03A LE1 04A LE1 05A LE1 06A LE1 07A LE1 08A LE1 09A LE11OA LE111A LE11 2A LE113A LE114A LE115A LE11GA LE117A LE11SA
LENS, LENS, LENS, LENS, LENS, LENS, LENS, LENS, LENS,
LG1O1A LG102A
CIRCUIT BREAKER, LOGO LIGHT MOONN WHELEN LIGHT, LOGO
LH1O1A LH102A LH103A LH104A LH105A LH1OGA
LAMP LAMP LAMP LAMP LAMP LAMP LAMP
LH107A LH 108A
LENS, LENS, LENS, LENS,
LENS, LENS, LENS, LENS, LENS,
ANNUNC. ANNUNC. ANNUNC.
ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC.
MOONEY (US) (M20J) (FRANCE) (M20J) MOONEY MOONEY (US) (M20M) (FRANCE) (M20M) MOONN MOONEY (M20T) MOONEY (M20T) MOONEY (US) (M20J) (FRANCE) (M20J) MOONN MOONEY (US) (M20R) (FRANCE) (M20R) MOONEY MOONEY (US) (M20R) (FRANCE) (M20R) MOONEY MOONEY (US) (M20K) MOONEY (US) (M20K) MOONEY (M20K)
ANNUNC. ANNUNC. ANNUNC. ANNUNC. ANNUNC. (M20J) MASTER WARN
HOLDER HOLDER HOLDER HOLDER HOLDER
HOLDER HOLDER LAMP HOLDER
(ALT) (ALT) (ALT) (ALT)
SLOANE MOONN MOONEY
MOONEY DIALIGHT WHELEN SLOAN INSTRUMENTS INSTRUMENTS SIGMA-TEC HH SMITH LEECRAFT ALLIED SPC NEWARK HH SMITH WHELEN TEK-LITE
PART NO. 880048-613
880048-615 880048-617
880048-619 880048-621
880048-623 880044-633 880044-635 880048-625 880048-627
880048-629 880048-631 880048-605 880048-607 880089-001 855-SE-C
880089-003 150080-6097 930023-357 A730-1 -28 914083-1 270-1930-0171-702
A-350-CN-CL-BK-SH-28 855S-0-U BA28-24-BW3 1\/-192-971 1930 7-05
931-3103 LSL-11-128U 81 N2561
LH1OSA LH11OA LH111A LH112A LH113A
LAMP HOLDER LAMP HOLDER
WHELEN
1925 01-0770437-00 LC-28-5 MS1745-51A 01-077-0142-04
MOUSER
351-0003
LL1O1A LL1O1B LL1 02A LL1 03A
SWITCH, LDG LIGHT SWITCH, LDG LIGHT BULB, LIGHT, LOG/TAXI BULB, LIGHT, LDG/TAXI
MOONEY MOONEY GE GE
880052-521 880052-121
LN1O1A LN 101B LN1 02A LN1 02A
CIRCUIT BREAKER
C/B LIGHT, NAV. CTAIL) LIGHT, NAV. CTAIL)
MOONEY MOONEY MOONEY MOONEY
930023-251 930023-351 800051-501 800051-509
LP1O1A LP102A LP103A LP104A LP105A
DIMMER, BOX DIMMER, CONTROL BOX DIMMER, CONTROL BOX SWITCH, O/H LIGHT ASSY INVERTER, E-L PLACARD
MOONEY MOONEY MOONEY MOONEY ERG
800299-501 800299-503 800299-505 150085-005 LPS28-3-3P
4-99
2
0211-128
LAMP HOLDER LAMP HOLDER LAMP HOLDER
(ALT)
NOTES
4596
4509
91-20-03 47
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
LR1O1A LR1O1B LR1 02A
C/B C/B LIGHT, RECOGNITION
MOONEY MOONEY MOONEY
930023-231 930023-331 880049-501
LS1O1A LS1O1B LS102A LS102B LS103A LS104A LS105A LS1 06A
CIRCUIT BREAKER CIRCUIT BREAKER POWER SUPPLY, STROBE POWER SUPPLY, STROBE LIGHT, STROBE-LT WING LIGHT, STROBE-RT WING LIGHT, STROBE, TAIL LIGHT, STROBE, DUAL
MOONEY MOONEY WHELEN WHELEN WHELEN WHELEN MOONEY WHELEN
930023-237 930023-337
01-0770054-12 01-0770054-13 47001 3-501 A41 3A-H DA-CF
LT1OIA LT1O1B LT102A
SWITCH, TAXI LIGHT SWITCH, TAXI LIGHT BULB, LIGHT, TAXI, LH 8 RH
MOONEY MOONEY GE
880052-523 880052-123 4596
MA1OIA
RECEPTACLE, AUX. POWER
01-0770329-00
01-0770329-01
(ALT)
AN2552-3A MS3503-1
MB1O1A MB1O1B
ClSSWITCH, RADIO MASTER tJVH~ MOONEY C~SWITCH, RADIO MASTER(BU~ MOONEY
930023-213 930023-313
MC1 01A MC102A MC1 03A
LIGHTER, CIGAR CAP
MOONEY CASCO CASCO CASCO
800336-503 216550 216510 200402
MID-CONT. PORSCHE MID-CONT MID-CONT PORSCHE PORSCHE
MD-89 944.641.213.00 6016177 6016125 944.612.21 7.00
SWITCHCRAFT SWITCHCRAFT SWITCHCRAFT
C-12B S-l 028 S-l 029
TETHER LIGHTER, SOCKET
(ALT) wlWIRE ME1O1A
CLOCK
(ALT) ME1OPA
CONNECTOR,
4 PIN
PINS
(OPT) (OPT)
PINS
MK1O1A
JACK, MICROPHONE WASHERS WASHERS
MP1O1A MP1O1B MP102A MP102B MP103A
C/B-SW, PROP DE-ICE OIVHITE) MOONEY MOONEY C/B-SW, PROP DE-ICE (BLK) BF GOODRICH TIMER, PROP DE-ICE McCAULEY TIMER, PROP DE-ICE TERMINAL 8LOCK
NF1O1A NF1O1B NF102A
SW/C-B, LOW BOOST FUEL PUMP MOONEY MOONEY SW/C-B WELDON PUMP, FUEL BOOST
McCAULEY
WELDON WELDON WELDON (ALT) WELDON PUMP, FUEL BOOST (M20K) WELDON PUMP, FUEL BOOST WELDON PUMP, FUEL BOOST MASSEY (ALT) MOONEY REGULATOR, FUEL PUMP SW/C-B, HI-BOOST FUEL PUMP MOONEY GUARD ASSY, HI-BOOST SW. MOONEY
(ALT)
NF103A NF104A NF105A NF1OGA NF108A NF108B NF1OSA NF11OA
91-20-03 48
PUMP, FUEL BOOST
4-99
999.652.351.12
930023-245 930023-345
3E1899-1 8-45018 C-40521 930023-211 930023-311 A8163B 81 638 8163A A81 63A 100548 A10051-D A8152-8 VR536 800270-523A 930023-219 930028-501
NOTES
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
VENDOR
PART NO.
REGULATOR, VOLTAGE
MOONEY
800270-501
(ALT) (ALT)
AM.PROD/PRECISE FLT AUXILEC~ELK/TODELTA
DGR-O VR-802
CODE
DESCRIPTION
PA1OIA
SWITCH, ALT’NTR FIELD (DUAL) MOONEY SWITCH, ALT’NTR. FIELD(SING~R MOONC/
PA102A PA103A PA1 04A
ALTERNATOR
PA1OSA
ALTERNATOR
(ALT) (ALT) PA1 06A
ALTERNATOR, RIGHT
(ALT) PA107A
GEAR ASSY ALTERNATOR KIT, INSTALL
PA1 08A
FILTER
LYCOMING PRESTOLITE LYCOMING PRESTOUTE TCM TCM TCM ELECTRO SYSTEMS LYCOMING
NOTES
880052-525
880052603 LW-14367 ALU-6421-LS
LW-15404 ALY-8420 649719
649280 649123
ES-4009-LS 05K-21 065
(REFERENCE 600180) (ALT) PA1OSA PA11OA PA111A PA111B PA112A PA113A PA114A
SENSOR, CURRENT REGULATOR, VOLTAGE SENSOR, CURRENT (110A) SENSOR, CURRENT (175A) ALTERNATOR MONITOR, CURRENT ALTERNATOR, LEFT
(ALT) PB1OIA PB1 02A PB1 028 PB1 03A PB1 03B PB1 05A PB1 058 PLO1A PLOPA PL02B PL02C PL02D PL03A PL03B PLOSC PL03D PL03E
BA~TERY
SWITCH, MASTER SWITCH, MASTER SWITCH, BAT 1-2 SWITCH, BAT 1-2 BA~TERY, 24V BATTERY, 24V PLUG, 1 PIN PLUG, 2 PIN
PLUG, 2 PLUG, 2 PLUG, 2 PLUG, 3 PLUG, 3 PLUG, 3 PLUG, 3 PLUG, 3 SOCKET SOCKET
PIN
PIN PIN PIN PIN PIN
PIN PIN
(ALUMEL) (ALUMEL)
PL05B PLOGA PL07A
PLUG, 4 PIN PLUG, 4 PIN PLUG, 4 PIN PLUG, 4 PIN PLUG, 5 PIN PLUG, 5 PIN PLUG, 6 PIN PLUG, 7 PIN
PL08A
PLUG, 8 PIN
PL04A PL04B PL04C PL04D PL05A
(FEMALE)
MOONEY MOONEY MICRO SWITCH MOONEY KLIXON KLIXON TCM MOONEY TCM TCM
88001 4-501 800307-501 CSLA1GE 800270-503
7235-1-110 7235-1-175 649304 800287-501 6491 72 649283
GILL MOONEY MOONEY MOONEY MOONEY CONCORDE CONCORDE
G-243 880052-501
AMP AMP MOLEX DEAN
1-480349-0 1-480318-0 03-06-1023 7021
880052-101 880052-527 880052-127
RG24-11M RG24-15
4
MS3106A-24-9S AMP AMP
ARRAY CDI CDI AMP
1-380303-0 206037-2
MS3106A-10SL-3S MS3106A-28-6P PWF06F08-33B 01-2020-245 01-2020-244 206060-1
MS3106A-32-17S AMP ARRAY CONN
1-480424-0
DEUTSCH MATRIX SCIENT.
PW06F8-4S MS310~A-14S-5S BVD06E0205SN MS3106A-28-22S MS3106A-20-15S MS3106R-20-15S
AMP
205838-1
(ALT)
4-99
91-20-03 49
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART CODE
DESCRIPTION
PLOSA PLOSB PLOSC PLOSD PLOSE
PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG, PLUG,
PL14A PL14B PL14C
PL15A PL1GA PL17A PL20A PL20B PL20C PL25A PL25B PL26A PL28A PL32A PL34A PL34B PL37A PL37B PL50 PL104A PS1O1A PS102A PS1 03A
VENDOR
PART NO.
9 PIN
AMP
9 PIN
AMP
206708-1 126-222
9 PIN 9 PIN 9 PIN 14 PIN 14 PIN 14 PIN 15 PIN 16 PIN 17 PIN 20 PIN
DESS
25 PIN 25 PIN 26 PIN 28 PIN 32 PIN 34 PIN 34 PIN 37 PIN 37 PIN 50 PIN
03-06-2092 206485-1 930021-1 930021-513 206043-3 DA15S
AMP
206037-1
MOONEY POSITRONICS POSITRONICS
930021-501
AMP MOONEY AMP
CC148-003-0.00 CC 149-003-0.00 DB25S 205208-1 930021-505 205839-3
M83723/86R2232N MOONEY MOONEY AMP MOONEY POSITRONICS
104 PIN
C/B, START POWER C/B, START POWER
(M20J)
(ALT) PS104A
MOLEX AMP MOONEY MOONEY AMP
DBM1M12S
20 PIN 20 PIN
STARTER
STARTER (M20K
M20R)
(ALT) PS1 05A
STARTER
RB1O1A RB102A
BLOWER, RADIO BLOWER RADIO
RCO1A RC02A
(M20M)
KLIXON KLIXON PRESTOLITE LYCOMING TCM TCM B&C
930021-507
930021-515 206150-1 DC37S 930021-511 GMCT104FOTH000 7277-2-10 7277-2-5
MHB4016 LW-1 5572 646275 637847
BSC206-1 49
KING GLOBE
071-4037-01 19A2790
AMP AMP
1-480351-0 1-480319-0 7022
RC03C RC03D
RECEPTACLE, 1 RECEPTACLE, 2 RECEPTACLE, 2 RECEPTACLE, 2 RECEPTACLE, 2 RECEPTACLE, 3 RECEPTACLE, 3 RECEPTACLE, 3 RECEPTACLE, 3
RC04A RC04B RC04C RC04D RCOSB RCOGA RC08A RCOSA RCOSB RCOSC
RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE, RECEPTACLE,
RCOSE RC12A RC14A
RECEPTACLE, RECEPTACLE, RECEPTACLE,
RCOPC RCOPD RC02E RC03A RC03B
91-20-03 50
NOTES
PIN PIN PIN (MALE) PIN PIN PIN PIN PIN PIN 4 PIN 4 PIN 4 PIN 4 PIN 5 PIN 6 PIN 8 PIN 9 PIN 9 PIN 9 PIN 9 PIN 12 PIN 14 PIN
DEAN
MS3100-24-9P MOLEX
03-06-2023
AMP AMP
1-480305-0 206036-2
AMP
206207-1
AMP
206153-1
MS3100-28-68
AMP ARRAY DEUTSCH MATRIX SCIENCE AMP AMP AMP AMP MOLEX MOONEY 4-99
M3100-32-17P 1-480426-0 PW01F8-04P BVD04E0205PN MS3100C-28-22P 205841-2 206705-2 206705-1 DESP 205486-1
03-06-2122 930021-2
4
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE
DESCRIPTION
RC14B
RECEPTACLE,
RC14C RC1GA RC1GB RCPOA RC20B RC26A RC28A RC32A RC34A RC34B
14 PIN
RL1 04A RL105A
AMP AMP AMP MOONEY
206044-1
POSITRONICS MOONEY AMP MATRIX SCIENCE MOONEY
GMCT2MOE100JO
AMP POSITRONIC AMP
204814-1
RECEPTACLE, 16 RECEPTACLE, 20 RECEPTACLE, 20 RECEPTACLE, 26 RECEPTACLE, 28
PIN PIN PIN PIN
PIN
RECEPTACLE, 32 PIN RECEPTACLE, 34 PIN RECEPTACLE, 34 PIN RECEPTACLE, 37 PIN RECEPTACLE, 104 PIN RECEPTACLE, 170 PIN
(22GA) (20-18 GA) (20-14GA)
RELAY, 28V/200A
RELAY, 14V/200A RELAY RELAY
RELAY, 28V/50A (2 REQâ&#x20AC;&#x2122;D.)
BRACKET
(ALT) RL1 06A RL1 07A RL1 08A RL1 09A RL11OA
RELAY, 28V/100A RELAY 14V/200A RELAY RELAY RELAY SOCKET TERMINAL
RS1O1A RS102A RS103A RS104A RS105A RS1OGA RS107A RS108A
RESISTOR, RESISTOR, RESISTOR, RESISTOR, RESISTOR, RESISTOR, RESISTOR, RESISTOR,
RS1 09A RS11OA RS111A RS112A RS113A RS114A RS115A
RESISTOR RESISTOR
20-OHM/10W 5 OHM/1OW
500 OHM 100 OHM
7.5-OHM 1K OHM/2W 5K OHM 150
OHM/3W
(ALT)
RS11GA SA1O1A
203540-1 G14000H000-1 265.0
RECEPTACLE, 14 PIN RECEPTACLE, 16 PIN
(ALT) (ALT) (OBSOLETE) RL1 02A RL1 03A
AMP
POSITRONIC
SOCKETS SOCKETS SOCKETS RL1OIA
PART NO.
(ALT)
(ALT) RC37A RC104A RC170A
VENDOR
RESISTOR, RESISTOR,
1
OHM/25W OHM/1OW
70
RESISTOR
RESISTOR, DUAL, 5.OK OHM RESISTOR RESISTOR
POSITRONICS HYPERTRONICS HYPERTRONICS HYPERTRONICS HYPERTRONICS KISSLING KISSLING C-H C-H KISSUNG KISSUNG KISSLING MOONEY C-H C-H C-H MAGNACRAFT KISSLING P&B P&B P&B
DALE DALE MOONEY NEWARK DALE ALLEN BRADLEY SPECTROL CLAROSTAT OHMITE OHMITE OHMITE DALE DALE OHMITE ALLIED OHMITE OHMITE
B&C ALTERNATOR, STAND-BY HOUSING, PLASTIC CONNECTOR B&C B&C TERMINAL, 1/4 INCH 4-99
NOTES
206036-2 206036-1 930021-502 930021-506 206152-1
M83723/83K2232N 930021-508 SK2114 206151-1 GMCT104MOOOOZO NEBV23-077 YSK006-011 YSK006-089 YSK015-025AH 26.57.01 26.57.02 6041 H-202/202A 6041H-1 05A 26.64.01 26.64.21
26.72.03 800375-1 6041 H-220 6041 H-53 6041 H-l 05R W67RCSX-3 28.08.01 VF4-1 5-H11 VCF4-1 002 26A1348C RH-10-20 OHM
RH-10-5 OHM 919029-501 09F976 RH-50-7.5 OHM RC42-GF102J 149-11-502 VC3D 23J 3.9K OH M/1 /2W 3.OK OHM/1 12W RH-25-1 OHM RH-10-70 OHM 15.OK OHM/1/4W 753-8059 1.6K OHM/1/2W 1.0 OHM/118W
3
BC410-1 12-003 14-026
91-20-03 51
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
SA102A SA103A
CONTROLLER, STBY ALTERNATOR B&C SWITCH, STBY ALT./EMERG BUS MOONEY
8(=203-2 880052-531
SB1OIA SB102A SB103A SB1 04A
KLIXON C/B, SPEEDBRAKE SWITCH, SPEEDBRAKE, YOKE PRECISE FLT PRECISE FLT RELAY, SPEEDBRAKE DIODE, SPEEDBRAKE GE (ALT) PRECISE FLT MOTOR, SPEEDBRAKE PRECISE FLT SWITCH, SPEEDBRAKE SOLENOID, CLUTCH, SPEEDBRK PRECISE FLT
7277-2-3 01265 01384 1 N2483/1 N5060
SB105A SB1OGA
VENDOR
PART NO.
CODE
3720-GE
S/B INTERFACE
MOONEY
01532 01505 01678 80031 4-501
SP1 02A
SPEAKER, ALERT SPEAKER, CABIN
SP103A
SONALERT
ARCHER ARCHER BLAUPUNKT MALLORY
40-1 333(= 40-1 325 PCx352 SC628
SW1 01A
SWITCH
MICRO
(ALT)
SAINT
CHERRY MICRO MICRO SAINT MICRO OTTO CONT. CARLING MOONEY C-H C-H ALCO GRAYHILL C-H CARLING MICRO MICRO
1SE1-T ZS-1009 E51-50B V3-1 DT-2R-47 ML-1409 1CH116-6 P6-24014 RCSI1-VBBOW 88001 3-507 8906K2875 SA1 RV20 MPE-1 06F-C-22-9 71AD30-02-2-AJN 8906K4731
SB107A SB108A
SP1OIA
(ALT)
SW102A
SWITCH, DEFROSTER BLWR
SW1 03A SW1 04A
SWITCH
SW1 05A
SWITCH, DN-LIMIT
SW1 06A SW1 07A SW1 08A SW1 09A
SWITCH SWITCH SWITCH SWITCH
SW11OA SW111A SW112A SW113A
SWITCH SWITCH SWITCH SWITCH
SWITCH, UP-LIMIT
(ALT) (ALT)
(ALT)
SWITCH, WHITE CAP
(AKT) SW114A SW115A
SW11GA SW1 1 7A SW118A SW11SA SW1 20A SW121A SW1 22A
SW1 23A SW1 24A
SW1 25A SW1 26A 91-20-03 52
C&K SWITCH NKK SWITCH INCLUDES- BUTTON, LOCKRING, LOCKWASHER, HEX NUT (2) C-H (ALT) C-H LOCK RING C-H LOCK WASHER C-H HEX NUT (2) TSCHUDIN (ALT) LENS TSCHUDIN BULB TSCHUDIN SWITCH MOONEY CARLING SWITCH SWITCH MOONEY CARLING SWITCH SWITCH CROUZET SWITCH SWITCH CROUZET ALCO SWITCH SWITCH NKK SWITCH EATON SWITCH 4-99
NOTES
RAS11-VBBOW 12TW-10 15PA90-8W MS27753-38 7101K DLB241-WO 1-L3C/ AT506M/AT503MB SB1 DDX492-2 29-761 16-886 15-966-6 504102 464415 590002 88001 2-501 TILC64-1 S-WH FN 880062-501 TIGM64-1 S-WHEN MS35058-22 83-450-001 83-452-504 MPEI 06F
MB2085SB1W01-EA 1501-11E
5
OLDWILLWAYNE M20M
MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART CODE
DESCRIPTION
VENDOR
PART NO.
SW127A
SWITCH, MASTER WARN
OMRON OMRON
A3BA-7011-1 A3BA-500R
OMRON OMRON NKK
A3BA-5202 A38-028
SW. SW. SW1 35A
(W/ LENS) (W1 LEGEND) (W/ BULB)
SW. SWITCH
NOTES
MB2085SB1W01-EA
VC1OIA
VOLTAGE CONVERTER, 28-14 TERRA TERRA (ALT)
MLC28-5 C28-5
VR1O1A
VARISTOR
GE
V47ZA05
WM1O1A WM1 02A
WARNING, MASTER WARNING, MASTER
MICRO MICRO
DSK-1 04-GYR DSB-11-RRRR-LRP
WS1O1A
ALERT, STALL/GEAR WARN
950D309-000 950D51 9-000
880048-501 880090-XXX 880048-503 880048-507 880048-509
WS103A
SWITCH, STALL WARN
IAl IAl MOONEY
WT1OIA WT1 01B WT102A WT103A WT104A
ANNUNCIATOR ANNUNCIATOR ANNUNCIATOR ANNUNCIATOR ANNUNCIATOR
MOONEY MOONEY MOONEY MOONEY MOONEY
(ALT)
800364-509
6
NOTES: 1. ALL P/N’s ARE ACCEPTABLE. SEE VENDOR INFORMATION FOR APPLICABLE CONFIGURATION. 2. 1 EACH MS35334-21 OR M2898
(ALLEN BRADLEY) INTERNAL TOOTH LOCKWASHER, REQUIRED
WITH EACH LIGHT, IF NOT SUPPIED BY SLOAN 3. SEAL BACK OF POTENTIOMETER WITH DOW CORNING #738 ELECTRICAL SEALANT AFTER
WIRES ARE SOLDERED TO TERMINALS. 4.
PL02C 8 RCOPC MAY BE PURCHASED FROM DEAN AS P/N 7020.
5. SEAL BACK OF SWITCH WITH DOW CORNING #738 ELECTRICAL SEALANT AFTER
WIRES ARE SOLDERED TO TERMINALS WHEN USED AS ’7HROTTLE SWITCH-GEAR WARNING". 6. ANNUCIATOR P/N WILL BE DETERMINED BY OPTIONS INSTALLED. REF. DRAWING
4-99
880090.
91-20-03 53
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL
M20M
MOON EY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
91-20-03 54
4-99
OLDWILLWAYNE SERVICE AND MAINTENANCE MANUAL 913000
M20M
MOONEY AIRCRAFT CORPORATION
ELECTRICAL SVSTEM SCHEMATICS
(SEE ENVELOPES)
CAUTION USE SCHEMATIC APPLICABLE TO SERIAL NUMBER OF THE AIRCRAFT BEING SERVICED.
4-99
91-30-00 55
OLDWILLWAYNE
ELECTRICAL SYSTEM SCHEMATICS
SCHEMATIC
M20R EFFECTIVITY
BLOW-UP FICHE NO.
ITEM NO.
800310
(M1)
27-0002 thru 27-0052
AMOB345
A
800310
(M2)
27-0053 thru 27-0107
AMOB345
E
800304
(M1) (sheet 1 of 2)
27-0001, 27-0108 thru 27-0137
AMOB345
800304
(M1) (sheet 2 of 2)
27-0001, 27-0108 thru 27-0137
AMOB345
M
800304
(M2) (sheet 2)
27-0~ 38 thru 27-0141
AMOB345
Q
800304
(M2) (sheet 2 of 2)
27-0138 thru 27-0141
AMOB345
U
(M3) (sheet 1 of 2)
27-0142 thru 27-01 80,
27-0182,
AMOB346
A
800304
(M3) (sheet 2)
2710142 thru 27-0180, 27-0182, 27-0183
AMOB346
E
800304
(M4)
27-0181,
AMOB346
800304
(M5)
27-0193 thru 27-0208
AMOB346
M
800304
(M6)
27-0209 thru 27-0215
AMOB346
Q
800304
(M7)
27-0216 thru 27-0220
AMOB346
U
800304
(M8)
27-0221 thru 27-0231
AMOB347
A
800304
(M9)
27-0232 thru 27-0239
AMOB347
E
800383
(M1)
27-0240 thru 27-0246
AMOB347
800383
(M2)
27-0247 thru 27-0257
AMOB347
M
800383
(M3)
27-0258 thru 27-0279
AMOB347
Q
800383
(M4)
27-0280 thru 27-TEA
AMOB347
U
1 of
800304
2 of
27-0183
thru 27-0192