METRO III – ICAO ANNEX 8 PART B – STANDARD REFERENCE DATA CONTENTS ITEM
PAGE
Flyover Noise Levels ...........................................................................................................................4B-1 Fuel Venting and Exhaust Emissions .................................................................................................4B-1 Wind Component Chart.......................................................................................................................4B-2 Compressibility and Position Error Correction to Indicated OAT (IOAT) ............................................ 4B-3 Relationship of Outside Air Temperature to ISA Temperature ........................................................... 4B-4 Airspeed Calibration – Normal System Gear Up, Flaps Up .....................................................................................................................4B-5 Gear Up, Flaps 1/4 .....................................................................................................................4B-6 Gear Down, Flaps 1/4 ................................................................................................................4B-7 Gear Down, Flaps 1/2 ................................................................................................................4B-8 Gear Down, Flaps Down ............................................................................................................4B-9 Ground Operations ................................................................................................................... 4B-10 Altimeter Correction – Normal System Gear Up or Down, Flaps Up ..................................................................................................... 4B-11 Gear Up or Down, Flaps 1/4 .................................................................................................... 4B-11 Gear Down, Flaps 1/2 ..............................................................................................................4B-11 Gear Down, Flaps Down ..........................................................................................................4B-11 Airspeed Calibration – Alternate System Gear Up, Flaps Up ................................................................................................................... 4B-12 Gear Down, Flaps 1/2 or Down ................................................................................................ 4B-13 Altimeter Correction – Alternate System Gear Up, Flaps Up ................................................................................................................... 4B-14 Gear Down, Flaps 1/2 ..............................................................................................................4B-15 Gear Down, Flaps Down ..........................................................................................................4B-15 Zero Thrust Stall Speeds ..................................................................................................................4B-16 Tire Limitation Chart ..........................................................................................................................4B-17
FAA APPROVED: MAY 22/89 REVISED: DEC 06/91
PERFORMANCE
4B-i 4MC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4B-ii 4MC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
METRO III – ICAO ANNEX 8 FLYOVER NOISE LEVELS Flyover noise level measured in accordance with Appendix F to FAR 36 is 75.3 dB(A). NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable for operation at, into, or out of any airport. FUEL VENTING AND EXHAUST EMISSIONS This airplane complies with SFAR 27, "Fuel Venting and Exhaust Emissions Requirements for Turbine Engine Powered Airplanes", which is equivalent to FAR PART 34, effective September 10, 1990.
FAA APPROVED: MAY 22/89 REVISED: DEC 06/91
PERFORMANCE
4B-1 4MC
METRO III – ICAO ANNEX 8 WIND COMPONENT CHART EXAMPLE: GIVEN:
WIND VELOCITY = 25 KNOTS AT 40o OFF RUNWAY HEADING OBTAIN: HEADWIND COMPONENT = 19 KNOTS CROSSWIND COMPONENT = 16 KNOTS
30 o
35
20 o
10 o
NOTE DEMONSTRATED CROSSWIND COMPONENT IS 20 KNOTS.
30
35
25
o 50
30
20
E GL AY N A NW ) D IN RU ES W M RE O G FR (DE
25
o 60
20
15
o 70
15
HEADWIND COMPONENT (KNOTS)
D IN D W EE TS) SP NO (K
o 40
10
10
5
0 0
80o
5
5
10 15 20 25 CROSSWIND COMPONENT (KNOTS)
30
35
FIGURE 4B-1 4B-2 4MC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III - ICAO ANNEX 8 COMPRESSIBILITY AND POSITION ERROR OUTSIDE AIR TEMPERATURE (IOAT) TEMPERATURE PROBE RECOVERY FACTOR ASSUMES ZERO TEMPERATURE INDICATOR EXAMPLE: GIVEN: OBTAIN:
CORRECTION
.65 ERROR I
INDICATED AIRSPEED PRESSURE ALTITUDE IOAT = - 10°C AT - - 45°C OAT = IOAT + AT =- lO+ (-4.5) = - 14.5%
TO INDICATED
l
I 181 KIAS = 15,000 FEET
l
hlnl-l= I.-IL TEMPERATURE RISE IS SHOWN FOR STANDARD DAY AMBIENT TEMPERATURES. FOR AMBIENT TEMPERATURES WITHIN f40”C OF STANDARD, THE TEMPERATURE RISE MAY VARY BY AS MUCH AS f2.5”C FROM THAT SHOWN.
IOAT NOTED ACCURATE.
WHEN
PARKED
OR TAXIING
220
240
MAY NOT BE
0
-1
-2
-3
-5
-6
-7
-8
-9 100
120
140
160 180 200 INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE FAA APPROVED:
MAY 22l89
260
4B-2
PERFORMANCE
4B-3 4MC
METRO III – ICAO ANNEX 8 RELATIONSHIP OF OUTSIDE AIR TEMPERATURE TO ISA TEMPERATURE 50
120
EXAMPLE: OAT = 15oC PRESSURE ALTITUDE = 10,000 FEET OBTAIN: CONDITION = ISA +20oC GIVEN:
40
110 100 90
30 80 70
20
60 50
10 IS
30
0o C
A
20
+2
A
+1
oC 0
IS
–10
+3
OAT (oF)
A
40 +4
0o C
IS
0
IS
OAT (oC)
A
10
0o C
A
IS
0
A
IS
–20
A
IS
oC 0
–1
–10 –20
oC 0 –2
A IS
–30
–3 A IS
oC 0
–30
–4
–40
oC 0
A
IS
–40
–5 oC 0
A
IS –6 oC 0
–50
–50 –60
MINIMUM OPERATING TEMPERATURE –60 S.L.
–70
5 10 15 20 25 PRESSURE ALTITUDE (THOUSANDS OF FEET)
30
FIGURE 4B-3 4B-4 4MC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III - ICAO ANNEX 8 AIRSPEED CALIBRATION GEAR UP, FLAPS UP
- NORMAL
SYSTEM
EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED = 150 KIAS GROSS \WEIGHT = ALL WEIGHTS CALIBRATED AIRSPEED = 151 KCAS
260
240
140
120
100
m-i --80
100
120
140
160
180
200
220
240
260
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE FAA APPROVED:
MAY 22189
4B-4
PERFORMANCE
4B-5 4MC
METRO III - ICAO ANNEX 8 AIRSPEED CALIBRATION GEAR UP, FLAPS 114
- NORMAL
SYSTEM
EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED = 158 KIAS GROSS WEIGHT = ALL WEIGHTS CALIBRATED AIRSPEED = 160 KCAS
180
160
80 )b”“““‘““““““““““““““‘-““““‘““‘“””-””””” 80 100
120
140
160
180
200
220
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-6 4MC
4B-5
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 AIRSPEED
CALIBRATION
- NORMAL
SYSTEM
GEAR DOWN, FLAPS l/4 EXAMPLE: GIVEN:
INDICATED AIRSPEED = 118 KIAS GROSS WEIGHT = 12,000 POUNDS (5440 kg) OBTAIN: CALIBRATED AIRSPEED = 118 KCAS
180
160
80 80
100
120
140
160
180
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-6 FAA APPROVED: MAY 22f89
PERFORMANCE
4B-7 4MC
METRO III - ICAO ANNEX 8 AIRSPEED
CALIBRATION
- NORMAL
SYSTEM
GEAR DOWN, FLAPS l/2 EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED= 125 KIAS GROSS WEIGHT = 13,000 POUNDS (5900 CALIBRATED AIRSPEED = 125 KCAS
kg)
18
160
60 60
80
100
120
140
160
180
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-7 4B-8 4MC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III - ICAO ANNEX 8 AIRSPEED CALIBRATION - NORMAL GEAR DOWN, FLAPS DOWN
SYSTEM
EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED = 100 KIAS GROSS WEIGHT = 12,000 POUNDS (5440 CALIBRATED AIRSPEED = 98 KCAS
kg)
180
160
80 /
60
80
100
120
140
160
180
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE FAA APPROVED:
MAY 22189
4B-8
PERFORMANCE
4B-9 4MC
METRO III - ICAO ANNEX 8 AIRSPEED
CALIBRATION
- FOR GROUND
OPERATION
- NORMAL
SYSTEM
GEAR DOWN, FLAPS l/4 EXAMPLE: GIVEN:
INDICATED AIRSPEED = 80 KIAS GROSS WEIGHT = ALL WEIGHTS OBTAIN: CALIBRATED AIRSPEED = 79 KCAS
140
130
120
110
60
50
60
70
80
90
100
110
120
130
140
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-9 4B-10 4MC
PERFORMANCE
FAA APPROVED: MAY 22189
METRO III - ICAO ANNEX 8 ALTIMETER
CORRECTION
- NORMAL SYSTEM
GEAR UP OR DOWN, FLAPS UP The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds and altitudes. GEAR UP OR DOWN, FLAPS l/4 The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds and for altitudes from sea level to 20,000 feet. GEAR DOWN, FLAPS l/2 The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds and for altitudes from sea level to 10,000 feet. GEAR DOWN, FLAPS DOWN EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED = 124 KNOTS INDICATED ALTITUDE = 5,000 FEET GROSS WEIGHT = 13,000 POUNDS CORRECTED ALTITUDE = (5,000 -21) = 4,979 FEET
(5900 kg)
a
-10
-20
-30
40
-50
70
80
90 (INDICATED
FAA APPROVED: MAY 22f89
100
110
120
130
INDICATED AIRSPEED (KNOTS) ALTITUDE AND AIRSPEED ASSUME NO INSTRUMENT
FIGURE 46-l 0 PERFORMANCE
140
150
160
ERROR)
48-l 1 4MC
METRO III - ICAO ANNEX 8 AIRSPEED CALIBRATION GEAR UP, FLAPS UP
- ALTERNATE
SYSTEM
EXAMPLE: GIVEN: OBTAIN:
INDICATED CALIBRATED
AIRSPEED AIRSPEED
= 172 KlAS = 170 KCAS l
THE
AIRSPEED
CORRECTION
GIVEN
IS
NOT
VALID
IF
NOTE THE NOT
COPILOT’S CONNECTED
STATIC PRESSURE TO THE ALTERNATE
INSTRUMENTS ARE STATIC SOURCE.
1
260
160
160
“” 60
100
120
140
160
160
,200
220
240
260
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-12 4MC
4B-11
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 AIRSPEED CALIBRATION - ALTERNATE GEAR DOWN, FLAPS l/2 OR DOWN
SYSTEM
EXAMPLE: GIVEN: INDICATED AIRSPEED = 114 KIAS OBTAIN: CALIBRATED AIRSPEED = 116 KCAS
l
DO NOT DUMP
l
THE AIRSPEED
PRESSURIZATION CORRECTION
WHEN USING THE
GIVEN IS NOT VALID
IF
THE COPILOT’S STATIC PRESSURE INSTRUMENTS ARE NOT CONNECTED TO THE ALTERNATE STATIC SOURCE.
180
160
80
60 60
80
100
120
.140
160
18(
INDICATED AIRSPEED (KNOTS) (ASSUMES NO INSTRUMENT ERROR)
FAA APPROVED: MAY 22189
FIGURE 4B-12 PERFORMANCE
4B-13 4MC
ALTIMETER CORRECTION GEAR UP, FLAPS UP
- ALTERNATE
SYSTEM
EXAMPLE:
1 CAUTION l
GIVEN:
INDICATED AIRSPEED = 165 KNOTS INDICATED ALTITUDE = 20,000 FEET OBTAIN: CORRECTED ALTITUDE = (20,000 - 120) = 19,880 FEET
l
1
DO NOT DUMP PRESSURIZATION THE ALTERNATE STATIC SOURCE.
WHEN
USING
THE AIRSPEED CORRECTION GIVEN IS NOT VALID IF THE DUMP VALVE IS OPEN.
THE COPILOl’S STATIC PRESSURE INSTRUMENTS ARE NOT CONNECTED TO THE ALTERNATE STATIC
rNoTE-l
zm -I a 0
c)
D 0 D z z
m x
3
D
% z 0
00
5. .
(INDICATED
ALTITUDE
INDICATED AIRSPEED (KNOTS) AND AIRSPEED ASSUME NO INSTRUMENT
ERROR)
METRO III - ICAO ANNEX 8 ALTIMETER CORRECTION GEAR DOWN, FLAPS l/2
- ALTERNATE
SYSTEM
The altimeter correction varies from plus 30 feet at 80 KIAS to minus 10 feet at 180 KIAS for altitudes from sea level to 10,000 feet. CAUTION . DO NOT DUMP PRESSURIZATION ALTERNATE STATIC SOURCE. l
THE ALTIMETER CORRECTION DUMP VALVE IS OPEN.
WHEN
USING
THE
GIVEN IS NOT VALID IF THE
NOTE The copilot’s static pressure instruments are not connected to the alternate static source. GEAR DOWN, FLAPS DOWN EXAMPLE: GIVEN: OBTAIN:
INDICATED AIRSPEED = 142 KNOTS INDICATED ALTITUDE = 10,000 FEET CORRECTED ALTITUDE = (10,000 - 35) = 9,965 FEET
50
0
-50
-100
-150
-!mo
-------“--‘---‘--‘----‘--“‘-“-”
~-““-““““‘-“‘““““-“-‘“‘-““-‘.--’
(INDICATED
FAA APPROVED: MAY 22189
ALTITUDE
INDICATED AIRSPEED (KNOTS) AND AIRSPEED ASSUME NO INSTRUMENT
FIGURE 4B-14 PERFORMANCE
ERROR)
4B-15 4MC
METRO III - ICAO ANNEX 8 ZERO
THRUST
STALL
SPEEDS NOTE
EXAMPLE: GIVEN:
OBTAIN:
. GROSS WEIGHT = 14,000 (6350 kg) FLAPS = 114 BANK ANGLE = 20” STALL SPEED = 96 KIAS
POUNDS l
l
THE CENTER OF GRAVITY ABLE AT EACH WEIGHT. GEAR
IS UP
THE
GEAR
IS DOWN
FOR
MAXIMUM ALTITUDE IDLE POWER STALL 800 FEET.
LOSS PER
l
WITH BOTH DEFLATED.
PROPELLERS
SAS PUSHER IS SET AT FLIGHT IDLE POWER TO THE THRUST STALL SPEEDS WITH -0. +4 KIAS TOLERANCE.
. THE l
l
SPEEDS ARE BASED ON TESTS FEATHERED AND DEICE BOOTS
MAXIMUM ALTITUDE POWER 10” AND
OR
IS THE
DOWN
FOR FLAPS
MOST
FLAPS l/2
AND
FORWARD
UP
AND
ZERO
ALLOW-
l/4.
DOWN.
DURING RECOVERY FROM FLIGHT FAR 23.201 IS APPROXIMATELY
NOSE DOWN PITCH ATTITUDE LOSS DURING RECOVERY FROM ON STALLS PER FAR 23.205 ARE 390 FEET, RESPECTIVELY.
CHANGE AND SINGLE ENGINE, APPROXIMATELY
L
GROSS 6000
WEIGHT (KILOGRAMS) 5000
4000
130
120
100
90
p h ul i 2 ~JJ
00
70
60 LOO0
14,000
13,000 GROSS
in,000 WEIGHT
11,000 (POUNDS)
10,000
FIGURE 4B-16 4MC
9.000
0
20 BANK ANGLE
40 (DEGREES)
60
4B-15
PERFORMANCE
FAA APPROVED:
MAY 22189
TIRE LIMITATION CHART - MAIN GEAR TIRE B.F. GOODRICH P/N 021-335-l ASSOCIATED
CONDITIONS:
POWER ....TAKEOFF (WET OR DRY) GEN LOAD .... ..... .. .... .... .... .. 300 AMPS BLEED AIR ... ..... ...... .... ... ON OR OFF ENG ANTI-ICE ... .... ..I..... ON OR OFF SPEED . .... .... VR (FIGURE 4C-3.4D3. 4E-3 OR 4E4) GEAR . ...... ..... ..... .... ..... ...... ... .... ... WWN FLAPS .,,,,....................,..................... IN
EXAMPLE: GIVEN:
OBTAIN:
TAKEOFF WEIGHT . 14,Mx) POWER - TAKEOFF (WET) ENG ANTI-ICE - OFF OAT - 5°C
POUNDS
(S35Ok@
~~~~~~~‘,~~~~~~‘~~~~~~~ KIAS TAILWIND - 5 KNOTS MAXIMUM ALLOWABLE TAILWIND . 10 KNOTS (TIRE SPEED WILL NOT BE EXCEEDED)
OPERATIONS WITH INSUFFICIENT HEADWINDS OR EXCESSIVE TAlLWINDS AS DETERMINED FROM FIGURE 4B-16 WILL RESULT IN EXCEEDING THE TIRE SPEED c-1
1 0
D 0 D Z Z
MAXIMUM ALLOWABLE TAILWIND
MINIMUM REQUlkED HEADWIND WIND
(KNOTS)
m x 00
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4B-18 4MC
PERFORMANCE
FAA APPROVED: MAY DATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89