Suplemnt when tpe331 10ua engine installed ocr

AIRESEARCH AVIATION COMPANY SPRINGFIELD. ILLINOIS FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR

SWEARINGEN SA226-TC REGISTRATION NO • .1/.2. c./rr11 L SERIAL NO.

Te

l-V T

This supplement must be attached to the FAA approved Airplane Flight Manual when the TPE331-10UA-51lG is installed in accordance with AiResearch Aviation STC SA344GL-D. The information contained herein supplements the information of the basic Airplane Flight Manual; for limitations, procedures, and performance information not contained in this supplement, consult the basic Airplane Flight Manual.

Springfield, Illinoia

62705

SEP 17 1982

Date

-----------------------

Revised

JUL 261985

---------------------

Page 1 of 26

Dec 01

05 04:42p

James W.

210 - ~11 - H1Ub

Leland

p ~ l

AFM Supplement for S~earingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, IL 62705

LOG OF REVISIONS Revised Pages

Rev. No. 1

5. 7. 14, 16. 23, 25

9. 10. 12

Description of Revisions Change engine model number, include present check list, and include % to torque figures.

02-15-83

pages Allow. EGT 96% Allow. EGT 100% Cont. Power

02-15-83

New Max Max Max

AiResearch Aviation Company DAS 1 GL

All pages renumbered 2

12.13,15, 16,18,22 24

17

Change ~n. RPM, over speed ck. Climb Power Bulked Landing, Air-APU Start & Definitions

03-15-84

-L2Yd/L/

New page Before Landing

w.

H. Cook AiResearch Avaiation Company DAS 1 GL

All pages renumbered

3

18

FAA-DAS Approved

Date

Change AWl operations

07-26-85

~~---W. H. Cook Garrett General Aviation Services Company DAS 1 GL

Note:

All changes are indicated by a black vertical line along the right margin.

FAA Approved:

DEC 01 , 2005 17 : 48

SEP 1 7 1982

SAN ANTONIO, TX

Page 2 of 26

210 341 9406

Page 1

Dec 01 OS 04:42p

James W.

210 - 341 - 9406

Leland

AiResearch Aviation Company Capital Airport Springfield. 1111nois

p.2

AFM Supplement for Swearingen SA226-TC Series

TABLE OF CONTENTS PAGE SECTION I

LIMITATIONS

SECTION II

NORMAL PROCEDURES

SECTION III

EMERGENCY PROCEDURES

20

SECTION IV

PERFORMANCE

23

SEP 1 7 1992 ___ FAA Approved: ______________

DEC 01 , 2005 17:49

SAN ANTONIO , TX

4 11

Page 3 of 26

210 341 9406

Page 2

Dec 01

05 04:42p

James W.

Leland

210-341-9406

AiResearch Aviation Company Capital Airport Springfield, Illinois

p.3

AFH Supplement for Swearingen SA226-TC Series

SECTION I LIMITATIONS

SEP 1 7 1982 _ FAA Approved: ________________

DEC 01,2005 17 :4 9

SAN ANTONIO , TX

Page 4 of 26

210 341 9406

Page 3

Dec 01

05 04:42p

James W.

AVlatlon ~ompany Capital Airport Springfield. Illinois

Leland

210 - 341 - 9406

p.4

:,uppJ.ement tor Swearingen SA226-TC Series

~Researcn

AN'

GENERAL This supplement presents information relative to the operation of the Garrett Turbine Engine Company TPE 331-10UA-511G turboprop engine in the Swearingen Metro SA226-TC aircraft. The performance contained in Section IV of the basic SA226-TC Airplane Flight Manual is applicable. Power is set according to the appropriate power chart for torque (foot-pound or %) as shown in the supplement.

Turbine temperature charts (EGT) include a margin for power deterioration so that when power is set by reference to torque on new and overhauled engines. the EGT should be less than the maximum allowable EGT. NOTE All reference to the ITT maximum limit in the basic Flight Manual and its supplements should be disregarded and only the EGT limit for the IOAT (Fig. 5 & 6) should be used.

POWER PLANT

Two AiResearch TPE 331-10UA-511G turboprop engines. rated at 840 maximum continuous shaft horsepower, are equipped with 102 inch diameter Hartzell TI0282HB full feathering, reversible, constant speed. three bladed propellers with hub model HC-B3TN-5().

PLACARDS

MAX EGT LIMITS °c

AWl FLUID

60-40% WATER I METHANOL ONLY ·

96% I OAT 605 600 590 580 570 560 550

540 535 530

50 40 30

20 10 0 ·10 -20 -30 -40

100% 605 595 585 575 565 560 555 550 545 540

FIGURE 1

SfP______________ 17 1982 _ FAA Approved: __~~ Revised:

DEC 01 , 2005 17:49

Page 5 of 26

FEB 1 5 1983 SAN ANTONIO, TX

210 341 9406

Page 4

Dec 01

05 04:43p

James W.

210-341-9406

Leland

p.5

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield. Illinois INSTRUMENT MARKINGS Red I\.od1&1 tnac.ruaaent

("111.)

~r.peed Indicator

(mou)

lIbice Are

Yellow Are

94 (1)

.

B6

o o o

!Fuel Pressure (psi)

15(2)

lou Pressure (ps1.)

40(2)

(OC)

to

248 54)

-40

15 to

20

20 to 70 to SO to

(2)

40 to 70 -40 to +55 (3)

o

ioxygen 10 4.4

~uctlon (in. ~ydraul1c

RR.) Pressl1re

10 to

1400 to 1700

(pai)

abin 01!ferent1.al Prusure (ps1)

12 to 4.4 to

&.d I\.od1&l

bd

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Are

Dot

248

540 to

605

60S

100 to

112

107 2363 101

2206 to 2468

770 (9)

112(8)

2468(8)

BO

70(4

19 4.8

1 700 to 2100

o

Duhee!

(M..:)

80

55 to llO t o )00 1600 to 1850

12

Rood

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!De1c.er Boot Pressure

(psi)

Arc

133 (5)

to 100 co 2206 96 to 100

orCll1e.eter (l) orQl1emeter (fL lb •• ) achometer (X JPM)

~U T~perature

Arc

to 153 97.5 to

xbal1at Ca. Temp . ("e)

tellov

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7.0

14 to

18

2.4 to

10

110 to

127(6)

UO 127

1850 to 2000 19 to

21

21 5.5

2100 to 2300(7)

2300 (12) 7.0 to 7 .25 (10) 7. :5

1.0 and ~~ 7.25 and u 10)

rep De1.c.er

iAmm,eter (aJaQs) ltot Heat.

lAmmeter (""'05) ~erato~ Loadmc~er

(11)

200

(amos)

FIGURE 2

(2) At 65% RPM (3) See Fig. 1-3 for minimum oil temperature for takeoff

(4) Above 23,000 feet, minimum oil pressure is 50 psi (5) Single engine best rate of climb speed (6) Ground operation only

(7) 3 minute limit during flight

(8) 2468 ft. lbs. or 112% torque is emergency water injection 5 minute limit (9) EGT limit during start

(10) With Swearingen pIN 26-84051-5 gauge installed (11) TC-222EE and subsequent (12) With Swearingen PIN 84253-1 gauge installed

FAA Approved

DEC 01 , 2005 17:50

:_S_E_P_l_7_19_'8_2_

SAN ANTONIO , TX

Page 6 of 26

210 341 9 406

Page 5

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ENGINE LIMITS FOR Al RESEARCH TPE 331-10UA-511G TURBOPROP ENGINES WITH REVERSING PROPELLERS

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5

2363 ft lbs

Maximum

EGT (OC)

RPM (X) 100% .. 2.000

Oil Pressure

Fuel Pressure

(2)

(psi)

(psi)

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z

Normal Takeoff

~ 1-1 o

107X (4)

70(8) to 120

20 to 80

70(8) to 120

20 to 80

55 to 110(9)

(1)

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5(3)

2468 ft lbs 112% (4)

(1)

55 to 110(9)

(5) r

Maximum Continuous Power

tD

2206 ft Ibe 100

70(8) to 120

20 to 80

55 to 110(9)

Flight Idle

96 to 100

70(8) to 120

20 to 80

55 to 110(9)

Ground Idle

65 or 97(7)

40 to 120

15 to 80

-40 to 127

100%

(1)

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770

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95.5 to 97

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o

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75 minimum Figure 3

70 to 120

15 to 80

-40 to 127

o I

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(1) Do not exceed maximum EGT limit for OAT.

.....

(2) Avoid operation between 18 and 28% RPM except for transients occurring during engine start and shutdown. 96% is minimum RPM during flight.

(3) 5 minutes of wet power is allowed for the engine. However. the two gallon emergency system will only provide 1 minutes of wet power. This power is authorized for single engine climb emergency.

(4) Static takeoff power should be limited ,to 2206 ft.-lh. or 100% to preclude over torque condition occurring due to ram effects on normal takeoff or water injection during single ENGINE emergency.

Normal dry takeoff power 1s shown in Figure 7 - continuous wet takeoff power is shown in Figure 8.

(5) Maximum EGT for emergency wet takeoff is the same as normal wet takeoff.

(6) 101% RPM for 5 minutes and 105% RPM for 5 second is allowed.

(7) Typical engine speeds for low and high speed lever positions.

(8) Above 23,000 feet, minimum 011 pressure 1s 50 psi.

(9) Takeoff is permitted with 011 temperature below 55°C provided the limitations shown in Figure 1-3 in the Basic Manual are observed.

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Dec 01

James W.

05 04:51p

210 - 341 -9 406

Leland

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Il11nois

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Leland

210-341-9406

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Illinois

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2 10 341 9406

Page 4

Dec 01

05 04:52p

James W.

Leland

210 - 341 - 9406

AiResearch Aviation Company Capital Ai rport Springfield. Illinois

p.5

AFM Supplement for Swearingen SA226-TC Series

SECTION I I

NORMAL OPERATING PROCEDURES

FAA

Approved: _SEP _ _1 _7_1982 _ __

DEC 01 , 2005 17:59

SAN ANTONIO , TX

Page 11 of 26

210 341 9406

Page 5

Dec 01 05 04:52p

James W.

Leland

210 - 341 - 9406

AiResearch Aviation Company Capital Airport Springfield. Il11nois

p.6

AFH Supplement for Swearingen SA226-TC Series BATTERY START

1.

Battery Switch/Switches .•.•...........•........................•..•...... ON

2.

Annunciator Panel and System Warning Lights ••••••••••••••••••• PRESS-TQ-TEST NOTE Press-to-test button must remain depressed until the wing overheat warning light starts flashing.

3. Fire Extinguisher System (TC398 and up) ••••••••••••••••••••••••.•.••••• TEST 4. Inverter (Check No. 2~ then No. 1) •••••••••••••••.•••.•••••••.....••••... ON 5. Fuel Quantity .•••.•••••••••••••••••••.• CHECK (500 POUNDS MAXIMUM IMBALANCE) Start right engine first.

6. Boost pumps ••••••.•••••••••••••••...•.•••••••••••••.•.•••.• CHECK/ AS DESIRED 7. Propellers ••••••..•••••••••••••.••..•.••••••.•••••..•••.•••• UNFEATHER/CLEAR 8. NTS Check During Start (First flight of day. See Page 11-24 Basic Flight Manual) .••••••••••. CHECK 9. Start Mode Switch (when installed) •••..••••••••••••.••••••••••••• AS DESIRED 10. Start Button •.•••••••••••••••••••••••••.•••••••••••.•••••.. DEPRESS AND HOLD 11.

RPM ••••••••••••••••••••••••••••••••••••••••••••••••••••••.•••••••••• 10%-12%

12.

Observe ignition as indicated by rising EGT (and illumination of IGN light, when installed.) Release start button when EGT rises.

CAUTION IF IGNITION 10% RPM, OR PULL ENGINE SECOND WITH

IS NOT OBTAINED WITHIN 10 SECOND AFTER REACHING BEFORE ATIAINING 20% RPM, PRESS STOP BUTTON AND STOP AND FEATHER CONTROL. CLEAR ENGINE FOR 10 STARTER TEST SWITCH. NOTE

The TPE 331-10UA-SllG is equipped with a Start Fuel Enrichment (SFE) system, actuated by the engine start button. The use of SFE to promote smooth engine acceleration between initial combustion (approximately 10-12% RPM) and idle (MINIMUM 65% RPM) will normally be required.

Modulate Start Fuel Enrichment (ON-OFF-oN-OFF) as necessary to maintain approximately 650°C EGT, ± ISoC during engine acceleration to idle RPM. 13.

14.

15.

EGT ••••••••••••••••••••••••••••••.••.••••••••••••••• MONITOR (770°C MAXIMUM) RPM ••••••••••••••••••••.•••••••..••••••••••••••••••••••••••••••• MINIMUM 65% Fuel and Oil Pressure ••••••••••.••••••••••••••••••••••• YELLOW OR GREEN ARCS

16.

Generator .••••••••••. - ••••••••.•.••.•..•••.••••••••••.••••••••••••• RESET/ON

NOTE Check for absence of air flow through the open cooling air "eye balls" prior to turning on either bleed air system.

FAA Approval: Revised:

DEC 01 , 2 005 17 : 59

SEP 1 7 1982

MAR 1 5 1984

SAN ANTONIO , TX

Page 12 of 26

210 341 9406

Page 6

Dec 01

05 04:S2p

James W.

Leland

210 - 341 - 9406

p.?

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Illinois

Battery Start (Continued)

17.

18.

19.

20.

Bleed Air Switch (right engine) •••••••••••••••••••.•••••.•••.••• NORMAL (ON) Start Mode Switch (when installed) •••••••••••••••.•••••.••.••••.••• PARALLEL Repeat Step 6 through Step 16 for left engine.

Bleed Air Switch (left engine) ••••••••••••••••••••••••••...•••.. NORMAL (ON) NOTE Verify operation of each bleed air system by selectively operating right and left systems.

21.

22.

23.

Air Conditioning Controls ••.•••.••.••••••••••.••••••...•••••••.. AS REQUIRED

Cabin Dump Switch •••••••.••••••••••••.•••.•••.•..••••...••.••....••••.• NORM Boos t Pumps •••••••••••••••.•••••.•••••••.•.•.•••.•••••..•••••..••......•• ON APU START CAUTIONS USE ONLY NEGATIVELY GROUNDED TYPE AUXILIARY POWER SOURCES. DUE TO THE POSSIBILITY OF EXCESSIVELY HIGH CURRENT SURGE DURING ENGINE START. IT IS RECOMMENDED THAT THE MAXIMUM STARTING CURRENT FROM AN EXTERNAL POWER SOURCE BE LIMITED TO 1.000 AMPS.

_ 1.

2• 3.

4.

5.

6.

Battery Switch/Switches •••.••••..•••••.•••••••.••••.•••••••••.•• ~ ••••••• OFF APU ••••••.•••••••••••.••••••.•••••••••••••••••••••••••••••••••••• ENGAGED / ON Right Engine ••••••••.•••...••.•••••.•••.•• START BY BATTERY START PROCEDURES Left Engine •••••••.••••••••••.•••••••••••• START BY BATTERY START PROCEDURES APU •••••••••••••.•.•••••••••..•••••••••••••.•••••••••••.••••• OFF /D ISENGAGED Left and Right Generators ••••.••.••••.••••••••••••.•••••.•...•••••• RESET/ON BEFORE TAXI

1.

2.

3.

4.

5.

6.

Generator Volt/Ammeters ••••••••.•••••••.•••••••••••... CHECK (APPROXIMATELY) 28.5/EVEN LOAD SHARING) Battery Disconnect System and Overheat Llghts ••.•••.••••••••••...••••• CHECK Battery Switch/SWitches .••.••.•••••••••••••••••••• OFF (FIRST FLIGHT OF DAY) Left Generator ..•••••••••••••••••••.••.•.••••••••• OFF (FIRST FLIGHT OF DAY) Stabilizer Trim System •••••••.•••.••.•••••••••••.•.••••• CHECK ALL FUNCTIONS Batter Switch/Switches ••.••••.•.•••••••••••••••••••••••••••.••••••••••••• ON

7.

Lef t Generator ••••••....•.•.......•••...•••.•••.•••••••...•...••••••....• ON

8.

9.

SAS ••••••••••••••••••••••••••.••••••••••••••••••••• CHECK ALL TEST FUNCTIONS Windshield Heat •••••••••••••••••••••••••••••••••••••••••••••••••••• ON (LOW)

10.

Avionics ......•.••••••••.•..•..•.••...•••..••.•••.••••••..••• ONI AS REQUIRED

11.

12.

13.

14.

Overspeed Governors •••••••••••••••••••••••••••••• (II-25 BASIC MANUAL) CHECK Propeller Start Locks •.••••••••••••••••••••••••••••••••••••••••••••• RELEASE External and Internal Lights ••••.•••.•••••••••••••••••••.••••••• AS REQUIRED Environmental Control System ••..•••••••••••••••••••••••••••••••• AS REQUIRED

FAA Approved:

SEP 1 7 1982

Revised: _ _M_A_R_l_5_19_8_4__

DEC 01 , 2005 18 : 00

SAN ANTONIO , TX

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AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Illinois

TAXI "

1.

2.

Nose Wheel Steering Arm Switch ••••••.••••••••••••••••••••••••••....• ARMED Parking Brake .................................................................................................. RELEASE

NOTE Apply pressure to the brake pedals while pushing the parking brake control full forward to ensure complete release of the wheel brakes.

*

*

3.

Powe r Leve rs •••••••••••••.•..•••..••.••••..••.••.••••••••..••. AS REQUIRED

4.

Brakes .................................................................................................................. CHECK

5.

NWS Power Lever Bu t ton •••.•••••••••••••••••••••••••••••••••••..••• DEPRESS Nose Wheel Steering System .••••.••••.••..••••••••••••••••••••..••••.• TEST

6.

BEFORE TAKEOFF 1.

*

Cont.rols ................................................................................................................ FREE

2.

Stabilizer. Rudder. and Aileron Trim ••..•••••••.•••••••••••••..•.•••• SET

3.

Flaps ....••••••.....••....•••...........•..•••••..•.••..•......•.•.... UP

4.

5.

Propeller Synchronizer ••...•••...••••••.•••••••••••.••• TAKEOFF - LANDING Flight Instruments ••••••••••••••••••••••••••••••.•••••••••• CHECK AND SET

6..

7.

Engine Instruments ...................................................................................... CH.ECK. Annunciator Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK.

8.

9.

Vacuum and Deicer Pressure ••.•••.••...••••••••••••••••••••••.•••••. CHECK Takeoff Power. VMC ' VI' V50 ••••••••·•··•••·••••• •• • •••••• ••··• ... CONFIRM

10.

AWl System ........•.....•.•.....•............•...•................ . CHECK

11.

12.

(See Figure 7 for minimum dry takeoff power - Figure 8 for continuous wet takeoff power. See basic AFM Figure 4-16 for dry and AWl armed airspeeds and supplement 13 for continuous wet power airspeeds) Ice Protection Systems ••••••••••••••.•••••••••••••••••• CHECK/AS REQUIRED Maximum Flow Switches (when installed) •••••••••••••••••••••••••••• NORHAL

13.

Bleed Air Switches •.•.....•....••.......•......•••...............•... OFF

14.

15.

16.

Pltot and SAS Heat •••••••••••.•••••••••••••••••••••••••••.••• AS REQUIRED Fuel Crossflow Switch •••••••.••••••.•••••••••••••••••••••••••.•••• CLOSED Takeoff EGT ••••••••••• SET REFERENCE RING RED LINE TO PLACARDED KGT LIMIT

Airplanes equipped with variable nose wheel steering.

SEP 1 7 1982 _ FAA Approved: ________________

DEC 01 , 2 005 18 : 00

SAN ANTONIO , TX

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AFH Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield. Illinois

TAKEOFF 1. Speed Lever s ...................................................................... HIGH

2. Engine Speed •••••••••••••••••••••••••••••••••••••••••••.•••••• CHECK 96%-97% 3. Ignition Mode Switches (if installed) ••••••••••••••...•.•••••••• AS REQUIRED 4. Power Levers ••.•••••••••.••.•••••••••••••.••• SET MINIMUM DRY TAKEOFF TORQUE FROM FIG. 7. SET CONTINUOUS WET TAKEOFF TORQUE FROM FIG. 8. (DO NOT EXCEED EGT OR TORQUE LIMITS) 5. Engine Speed ••••••.•••••••••.••••••••••••••••.••••••••••••••••••• CHECK 100% 6. AWl Arm Switch •••••••••••••••••.•.•••••.•••.•.••••.••••••••• ARM/IF REQUIRED (ABOVE 550 FT. LBS. OR 25% TORQUE) 7. Brakes ........................................................................................... RELEASE

*

8. AWl Arm Light {after power lever switches are closed) •.••.••.•••••• CHECK ON 9. NWS Power Lever Button •.•••••••••.•.•..••••.•••..•••••..• DEPRESS/AS DESIRED 10. V1 Speed .••.•••••••••.••••••••••••••..•••••••••••••.•••••••..••••.. ROTATE 11. Landing Gear (after liftoff) ••••••••..••••..••••..•••••..••••.••••.• RETRACT NOTES Sidearm control nose wheel steering, when installed. may be used on the initial part of takeoff roll, if desired.

However, adequate directional control can be obtained with the rudder at airspeeds above 60 knots.

On airplanes equipped with the variable authority nose wheel steering system, normal authority steering is available until deactivated by the landing gear squat switches at liftoff.

If required engine torque per Figure 7 or 8 is not obtained at or before 80 knots abort takeoff.

On aircraft equipped with variable nose wheel steering 8ystem~ i.e •• those aircraft which have been modified in accordance with Fairchild Swearingen Service Bulletin 32-037, normal authority steering 1s available until deactivated by landing gear retraction.

*

Airplane equipped with variable authority nose wheel steering.

FAA Approved: Revised:

DEC 01 , 2005 18 : 01

SEP 1 7 1982 MAR 1 5 1984

SAN ANTONIO , TX

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p. 1

AFM Supplement for Swearingen SA226-TC Series

CLIMB

1. Climb Speed •••••••••••••••••••••.••••. PER PAGE IV-23 OF BASIC FLIGHT MANUAL 2. AWl Arm Switch •.••••.••••••••.•••••••••••••••••••••••••••••••••••••••••• OFF 3. Climb Power ••••••••••••••••.•.••••••••• FOR NORMAL TWO ENGINE CLIMB MAINTAIN TAKEOFF TORQUE FROM FIGURE 7 OR lO°C BELOW MAX EGT LIMIT FOR IOAT WHICHEVER COMES FIRST. FOR MAXIMUM CLIMB PERFORMANCE SET 100% TORQUE OR MAX EGT LIMIT WHICHEVER COMES FIRST. 4. Propeller Synchronizer •••••••••...••••••••••••••••••••••••• CLIMB AND CRUISE S. Ice Protection Systems ••••.•..••.•••••••••.••••••••••••••••••••• AS REQUIRED 6. Bleed Air Switches ••••••••••...••.••.•••••••••••••••••••••••••••. AS DESIRED 7. Cabin Pressure Scheduling ••..••..•••••••••••••••••••••••••.•••••••••.• CHECK 8. No Smoking-Fasten Seat Belt Signs .••.••.•.••••••.••••••••••••••• AS REQUIRED * 9. Nose Wheel Steering Arm Switch ••......•.•..••••••••••••••••••••••••••••• OFF 10. Ignition Mode Switches (if installed) ..•..•.••••••...•••••••.•••••••••. NORM CRUISE 1. Cruise Power ••••••••••••••••••• FOR NORMAL CRUISE SET EGT 20°C OR MORE BELOW MAX EGT LIMIT. FOR MAX CRUISE DO NOT EXCEED MAX EGT LIMIT, DO NOT EXCEED MAX TORQUE 2. Cabin Pressurization •••••••••••••••••••••••••••••••.••••••••••••• AS DESIRED DESCENT 1. Power •..•••.•.••..•.••••••••.••.••••••••••••••••••..•.•••••••••• AS REQUIRED 2. Altimeters ................................................................................................. SET

3. Cabin Pressure Contro11er ••••••••••••••••••••••••• SET (TO ASSURE ZERO CABIN DIFFERENTIAL AT TOUCHDOWN) 4. Cabin Rate Control •••••••••••••••••••••••••••••••••.••••••••••••• AS DESIRED 5. No Smoking-Fasten Seat Belt Signs ••••••••.••••••••••••••••••.••• AS REQUIRED 6. Fuel Quantity and Balance •••••••••••••• CHECK (500 POUNDS MAXIMUM IMBALANCE) 7. Fuel Crossflow Switch •••••••••••••••••••••••••••••••••••••••••••••••• CLOSED

*

Airplane equipped with variable authority nose wheel steering.

FAA Approved :_S_E_P_l_7_19_8_2_ Rev1 sed : _ _ _~...;;.fA...;;.R.:....;1=--=-5-!:19~8LJ4,---_

DEC 01 , 2005 18 : 01

SAN ANTONIO , TX

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p.2

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Illinois

BEFORE LANDING 1. No Smoking-Fasten Seat Belt Signs ••••...••••••••••••••••••••••••••••.•••. ON 2. Speed Levers ••••••••••••••••••••••••••••••••••••••••••••••••••••••• HIGH RPM

3. Landing EGT •••••••••••••• SET REFERENCE RING RED LINE TO PLACARDED EGT LIMIT CAUTION ATTEMPTED REVERSE WITH THE SPEED LEVERS IN THE LOW RPM POSITION MAY RESULT IN AN ENGINE OVER TEMPERATURE CONDITION. 4.

5.

6.

7.

8.

9.

*

Propeller Synchronizer •••...•..•••.••.•.••••••..•.••...••••• TAKEOFF-LANDING Landing Gear ••.••••••••••••••..•••.•••••••.••••..•••.•••••••••••••••••• DOWN Flaps ••••••••••••••••••..•••••..••••.•.••...••..•.••...•••••.••• AS REQUIRED Cabin Differential Pressure •••.••••••••••••.••..•••••••.••••.•... CHECK ZERO Nose Wheel Steering Arm SWitcb •••••••.••••••••.•••••.••••••••••••••••• ARMED Ignition Mode Switches (if installed) ••••.•.•••••••••.•••••••••• AS REQUIRED

Airplanes equipped with variable authority nose wheel steering.

FAA Approved :_M_A_R_l_5_19_84 __

DEC 01 , 2005 18 : 02

SAN ANTONIO , TX

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p.3

AFH Supplement for Swearingen SA226-TC Series

BALKED LANDINGS 1.

Power Levers ••••••••••••••••••••••••••.••••••• MAXIMUM EGT LIMIT FOR IOAT OR 100% TORQUE WHICHEVER COMES FIRST

2.

Climb Speed ...................................................................................................... 96 KIAS (98 WHEN ABOVE 12,500 LBS.) Engine .Anit-Ice .................................................................................................................. OFF

3..

4.

Rate of Climb •••••••••••••••••••••••.•••.•• ESTABLISH POSITIVE RATE OF CLIMB

5 ..

6.

Landi ng Gea r ................................................................................................................ RETRA.CT Flaps ••••••••••••••.••••••••••••••••••••••••••••••••••••••••••• RETRA.CT TO ~

7.

Airspeed •.••••••••••••••••••••.•••••••••••••••••••••• ACCELERATE TO 120 KIAS

8..

Flaps .............................................................................................................................. RETRACT

9.

Ignition Mode Switches (if installed) •••••••••••••••••.•.•••••••••••••. NORM NOTE When required for obstacle clearance, this procedure is used to obtain the climb performance depicted in Figure 4-26 of the Basic Flight Manual.

SPECLAL SYSTEMS OPERATIONS AND CHECKS AWl SYSTEM OPERATIONS

After the AWl control switch is placed in the arm position, an AWl arm light will not be obtained until the power levers are advanced beyond the 50% power lever position. Retarding the power levers aft of the 50% pOSition will automatically disarm the system. In the event that an engine 1s lost on takeoff or initial climb, the armed system will sense the lower torque of the failed engine and automatically fire the water alcohol mixture into the compressor inlet of the operative engine, providing a minimum of 45 seconds of augmented power during the "clean-up" stages of the takeoff. Maximum allowable EGT for AWl system operations is the same as for dry takeoff power as shown on the placard on the instrument panel and Figure 1. Takeoff Power Torque (wet) is shown in Figure 7 and is the same as Figure 1 Supplement 13 for Continuous Wet Takeoff Minimum Power Check Chart. Do not exceed 2468 Foot-pound or 112% emergency torque limit (denoted by a dashed red radial). When the AWl tank runs dry, a decrease in torque will be observed.

CONTINUOUS IGNITION (Wben installed in accordance with Swearingen Drawing 27-82001 or Swearingen Service Bulletin 74-001.) This system was installed in production aircraft SiN TC-219 and subsequent.

Provisions for continuous engine ignition are installed for use during periods when excessive water, slush, or ice ingestion might cause engine flame-out. A lever-lock switch independently controls the ignition mode selection for each engine. These modes are available:

SEP 1 7 1982 _ FAA Approved!________________ Revised: _ _J_U_l_2_6_'98_S_ _

DEC 01 , 2005 18 : 02

SAN ANTONIO , TX

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p.4

AFM Supplement for Swearingen SA226-TC Series

Continuous Ignition (Continued) NORM:

Ignition is only supplied to the engine during the automatic start cycle. between 10% and 50% RPM. This mode is provided for ground use during normal operations.

AUTO/CONT:

Ignition is supplied to the engine continuously as long as the main landing gear squat switches are in the ground position.

This mode is provided for use during takeoff or landing on wet or slush covered .runways when ingestion is possible. Ignition is automatically supplied to the engine in flight at approximately 90% RPM if a flame-out should occur due to ingestion of ice of an excessive amount of water.

OVRD:

Ignition Is supplied to the engine continuously. regardless of landing gear squat switch position. This mode is provided for use in the event of inadvertent icing encounters during flight. See Page 111-23 of the basic Flight Manual.

An amber light. adjacent to each EGT indicator. is provided for each engine to indicate that power is being supplied to the igniter. Power for the system is provided via a 5 ampere circuit breaker marked (LH or RH) CONT IGN. Note that excessive operation of this system in the CONT or OVRD mode will reduce igniter plug life.

ELECTRICAL SYSTEM A.C. POWER Two 115 volt. 400 HZ, single phase inverters supply A.C. power for the fuel pressure gauges. oil pressure gauges, fuel quantity gauges, and for avionic A.C. requirements. The number one inverter is powered by the left essential bus; the number two inverter is powered by the right essential bus.

NOTE Installation of the Garrett TPE 31-10UA-S11G engines requires that torque and EGT gauges operate from the 28.5 VDC left and right essential bus.

SEP 1 7 1982 _ FAA Approved: ________________

DEC 01 , 2005 18:03

SAN ANTONIO , TX

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A1Research Aviation Company

AFM Supplement for

Capital Airport Springfield. Illinois

Swearingen SA226-TC Series

SECTION III EMERGENCY OPERATING PROCEDURES

SEP 1 7 1982 ___ FAA Approved: ________________

DEC 01 , 2005 18:03

SAN ANTONIO , TX

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p.6

AFK Supplement for Swearingen SA226-TC Series

ENGINE FAILURE DURING TAKEOFF-TAKEOFF CONTINUED AT OR ABOVE VL CAUTION THE AIRPLANE SHOULD BE FLOWN OFF IN A NORMAL ALTITUDE. WHEN LIFTOFF IS ASSURED, THE AIRPLANE ALTITUDE SHOULD

BE STABILIZED WITH MINIMUM LANDING GEAR CLEARANCE REQUIRED (DO NOT EXCEED APPROXIMATELY 8-10 FEET). NO ATTEMPT SHOULD BE MADE TO CLIMB TO A HIGHER ALTITUDE UNTIL GEAR RETRACTION IS COMPLETE. MINIMUM ALTITUDE FOR OBSTACLE CLEARANCE SHOULD BE MAINTAINED UNTIL SINGLE ENGINE BEST RATE OF CLIMB SPEED IS ATTAINED. THIS IS ESPECIALLY IMPORTANT WHEN AWl AUGMENTED POWER IS REQUIRED BY FIGURE 4-20.

1.

Power Lever (operating engine) •.•.•••••.•••.•••••.•••••••• SET TAKEOFF POWER NOTES Set dry takeoff power not to exceed 2363 foot pound or 107% torque or the EGT limit for IOAT. If torque limit is not being developed and bleed air is on, increased power may be obtained by selecting bleed air off.

Set wet takeoff power not to exceed 2468 foot pound or L12% torque or the EGT limit for IOAT. AIRSTART PROCEDURE CAUTION IF AN ENGINE HAS BEEN SauT DOWN BECAUSE OF AN OBVIOUS FAILURE. AS INDICATED BY THE ENGINE INSTRUMENTS OR EXCESSIVE VIBRATION, AN AIRSTART SHOULD NOT BE MADE.

NOTE Satisfactory airs tarts have been demonstrated up to 20,000 feet pressure altitude with the fuel boost pumps operating and up to 12,000 feet pressure altitude without the boost pumps operating.

SEP 1 7 1982

FAA Approved: _________________

DEC 01 , 2005 18 : 03

SAN ANTONIO , TX

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James W.

Leland

210 - 341 - 9406

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield, Illinois )

Airstart Procedure (Continued) I.

Speed Lever ••••••••••••••••••••••••••••••••••••••••••••••••••••••••• LOW RPM

2.

3.

4.

5.

6.

7.

8.

9.

Power Lever ••••••••••••••••••• APPROXlMATELY ONE INCH FORWARD OF FLIGHT IDLE EGT ••••.••.•••••••••••••••••••••.••••••••••••••••• BELOy 200°C (IF FEASIBLE)

10.

II.

12.

13.

14.

IS. 16.

17.

18.

19.

-

p.?

20.

'RPM ••••.••••••••••••••..•..••••.•••••••••••••••••••••••••••••••. 10% OR LESS Altitude ••.•••••••••••.••••••.•••••••••••••••••••••.•••• 20.000 FEET MAXIMUM Airspeed •••••••••••••••••••••••••••••••••••••••.••••••• 100 KIAS ,TO 180 KIAS

Engine Stop and Feather Control ••••••••••••••••••.••••••••••..•••••• FORWARD Fuel Shutoff Switch ••.•••••••••••••••••••••••••••••••••••••••.•.••..••• OPEN Hydralic Shutoff Switch •••••••••••••••••••••••••••••••.••••••.•..••••.• OPEN Fuel Boost Pump Switch ••••••••••.••••••.•••••••••••••••••••••..•••••••••• ON Generator Switch ....................................................... . OFF

Bleed Air Switch ••••••••••••••••••••••••.•••••••••••••.••••••..••••••.•• OFF Engine Start Button .•••••••••••••••••••••.••.•.••••.••••••• DEPRESS AND HOLD Propeller ••••••••••.••••••••••••••••••••••••••••••••••• OBSERVE UNFEATHERING Fue 1 Flow •••••••••••••••••••••••••.••••••••.•••••••• SHOULD START AT 10% RPM EGT ••••••••••••••••••••••••••• SHOULD INDICATE COMBUSTION AT 10% TO 207. RPM. IF COMBUSTION NOT INDICATED BY 25% RPM. ABORT START BY PRESSING STOP BUTTON AND PULLING ENGINE STOP BUTTON AND PULLING Start Fuel Enrichment (SFE) .••••••••••••• USE AS REQUIRED TO MAINTAIN PROPER ENGINE ACCELERATION DURING START Fuel and Oil Pressure •••••.••••••••••••.•••••••••••••••••••••••••. GREEN ARC Generator Switch ••.•••••••••.•••••••.•.•••••••.••••••••••••••••.•.. RESET ION Bleed Air Swi tch ••••••••••••••••••••••••••.•..•••••..••••••••... NORMAL (ON) INADVERTENT ICING ENCOUNTER

If icing is encountered with the ice protection systems OFF. the following procedure is recommended: 1.

2.

Left Ignition Mode Switch (if installed) ••••••••••••••••••••••••••••••• OVRD Engine and Prop Anti-Ice Switch {left engine) •••••••••••••••••••••••••••• ON NOTE EGT will increase slightly and torque will decrease when engine and prop heat is selected. Power lever adjustment may be required.

3.

4.

5.

6.

7.

8.

9.

Left Ignition Mode Switch (when continued engine operation' is assured) •••••••••••••••••••••••••.•••••••••••••••••••••••• NORM Pitot Heat/SAS Heat ••••••••••••••••••.•••••••••.•.•••••••••••••••••••••.• ON Windshield Heat ..•••••••••••••••••••••••••••••••••••••••••••••.•.•••••• HIGH Deicer Boots •••••••.•••••••••••••••••••••••••••••••••••••••••.•• AS REQUIRED Right Ignition Mode Switch (if installed} •••••••••.•••••••••••••••••••• OVRD Engine and Prop Anti-Ice Switch (right engine) •••••••••••••.•.•••••••.•.• ON Right Ignition Mode Switch (when continued engine operation is assured) ••.•...•....•..•••••.•••••••.•.••.•..••........•.. NO'RH

Observe ignition duty cycles. igniter plug life.

Excessive use of override mode will reduce

FAA Approved: __ S_E_P_l_7_1_98_2_

Revised : _ _M_A_R....;,:1...,.;5:-:..;:19.::..84..:.....-_

DEC 01 , 2005 18 : 04

SAN ANTONIO , TX

Page 22 of 26

210 341 9406

Page 7

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05 04:56p

James W.

Leland

210-341-9406

AiResearch Aviation Company Capital Airport Springfield. Illinois

p.8

AFM Supplement for Swearingen SA226-TC Series

SECTION IV PERFORMANCE

-

SEP 17 1982 __ FAA Approved: ______________

DEC 01 , 2005 18:04

SAN ANTONIO , TX

Page 23 of 26

210 341 9406

Page 8

Dec 01

05 04:56p

James W.

Leland

210 - 341 - 9406

p.9

AFM Supplement for Swearingen SA226-TC Series

AiResearch Aviation Company Capital Airport Springfield. Illinois

DEFINITION OF TERMS

/

-

Hp

Pressure altitude. Determined with the altimeter set at 29.92 inches Hg. Assumes no instrument error.

ISA

International Standard Atmosphere (15°C at seal level with approximately 2°C/I,OOO feet lapse rate).

IOAT

Indicated outside air temperature.

OAT

Outside air temperature. Indicated outside air temperature corrected for compressability and pickup position error.

EGT

Exhaust Gas Temperature.

KIAS

Indicated airspeed in knots.

KCAS

Calibrated airspeed in knots. tion error.

KTAS

True airspeed in knots.

MCP

Maximum continuous power. Defined as 100% RPM 2,206 footpound or 100% torque not to exceed EGT limits for IOAT.

TOP

Takeoff power. Defined as torque from Figure 7 for airport pressure altitude and oat not to exceed 100% torque (2206 ft. lbs.) static dry power or 107% torque (2313 ft.-Ibs.) with ram effect, not to exceed EGT limits for IOAT.

VMC

Minimum control speed. Assumes one engine in negative torque sensing mode (NTS) and the other engine at takeoff power.

VR

Rotate speed.

VS1

Stall speed in a specified configuration.

Vx

Best angle of climb speed.

Vy

Best rate of climb speed.

VI

Takeoff Decision Speed in knots (Fig. 4-16 Basic Flight Manual). VI is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue to discontinue the takeoff.

V50

Takeoff speed at 50 foot height.

FAA Approved:

Assumes no instrument error.

Assumes no instrument error.

Indicated airspeed corrected for posi-

SEP 1 7 1982

aevised: _ _M_A_R_l_5_19_84 ___

DEC 01 , 2005 18 : 05

SAN ANTONIO, TX

Page 24 of 26

210 341 9406

Page 9

Dec 01

05 04:57p

James W.

A1Kesearcn AV~a~~gu ~uwvauy Capital Airport Springfield, Illinois

210 - 341 - 9406

Leland

~n

~upp~emen~

Lor

p. 10

Swearingen SA226-TC Series

TAKEOFF POWER CHECK CHART DO NOT EXCEED BGT LIMIT FOR IOAT RPM-lOOI Example:

Obtain:

lOAT-IO°C

Obtain:

Pressure altitude-4,OOO feet Engine Torque-l,960 foot-pound-89%

Obtain:

89% Torque From Fig. 4 this Supplement

TAKEOFF POWER PER ENGINE 0- 50 KTAS

60 BLEED AIR OFF

50

40

~(,

,S~

30

/?J

0

z =>

0

20

a..

I

r-

10

0 0

u..

0

<0

0

-10

N N

-20

r-

II

~

-'

-30

w

=>

0

-40

0::

0

-50 -60 1,000 46%

r-

TEMPERATURE LIMIT -

c

54 C

1,200

1,400

1,600

1,800

2,000

2,200

54%

64%

73%

827-

91%

100%

FIGURE 7

SEP 17 1982 FAA Approved:, _ _ __ __ __

Page 25 of 26

Revised: _ _F_E_B_l_5_19_8_3

DEC 01 , 2005 18 : 05

SAN ANTONIO , TX

210 341 9406

Page 10

Dec 01

James W.

05 04:57p

210 - 341 - 9406

Leland

AiResearch Aviation Company Capital Airport Springfield, Illinois

p. 11

AFM Supplement for Swearingen SA226-TC Series

CONTINUOUS WET TAKEOFF MINIMUM POWER CHECK CHART

RPM

C>

Example: Given: IOAT = +10°C Pressure Altitude = 4,000 feet Obtain: Engine Torque = 2,234 foot-pound or 102%

100%

BLEED AIR OFF INLET ANTI-ICE OFF

NOTE To avoid exceeding 107% wet torque, select continuous AWl while dry torque is less than 91% torque.

TAKEOFF POWER PER ENGINE 0-50 KTAS

_2011T.!IEM! pIEIR!AITluIRIEilLI Ml iT~=~_!1!5!~cl~ : I~I!:lil 1:1~,lIlIlIlIlIiI!ili ..

1,500 1,600 1,700 68%

73%

1,800 1,900

77%

82%

87%

2,000 2,100 2,200

91%

96%

100%

2,300 2,400 105%

107%

FIGURE 8

SEP 1 7 1982 _ FAA Approved: ______________ Revised: DEC 01 , 2005 18 : 06

rra

Page 26 of 26

151983

SAN ANTONIO , TX

210 341 9406

Page 11