METRO III ICAO ANNEX 8 PART G – APPROACH AND LANDING PERFORMANCE CONTENTS ITEM
PAGE
Maximum Landing Weight Limitation Chart Bleed Air On .............................................................................................................................. 4G-2 Bleed Air Off .............................................................................................................................. 4G-3 Balked Landing Rate of Climb – Bleed Air On ................................................................................... 4G-4 Landing Distance Over 50 Foot Height B.F. Goodrich Single Rotor Brakes ........................................................................................... 4G-5 Goodyear Aerospace Dual Rotor Brakes .................................................................................. 4G-6 Landing Brake Energy Limits B.F. Goodrich Single Rotor Brakes ........................................................................................... 4G-7
FAA APPROVED: MAY 22/89
PERFORMANCE
4G-i 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-ii 4MC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
MANUFACTURER'S DATA FAA APPROVED: MAY 22/89 ISSUED: MAY 22/89
PERFORMANCE
4G-1 4MC
METRO III - ICAO ANNEX 8 MAXIMUM LANDING WEIGHT SINGLE ENGINE APPROACH ASSOCIATED
LIMITATION CHART CLIMB REQUIREMENT
EXAMPLE
CONDITIONS:
GIVEN:
POWER . . . .. . . . . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) PROPELLER .. . . . . . . .. . . .._................. FEATHERED ON INOPERATIVE ENGINE GEN LOAD . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . .. . . 300 AMPS BLEED AIR . . .. . . . .. . .. .. . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON . . . . . . . . . . . . . . . . . . . . . . . . . .. OFF (SEE NOTE) ENG ANTI-ICE CLIMB SPEEDS . . .. . . . . SEE LANDING APPROACH SPEEDS (FIGURE 4G4 OR 4G-5) AND GEAR . . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . UP (APPROACH APPROACH CLIMB) FLAPS . . . . . . . . . . . .. . . . . . . .. .. . . . . .. . . . . . l/4 (APPROACH AND APPROACH CLIMB)
OBTAIN:
AIR ON
: OAT = 7°C PRESSURE ALTITUDE MAX LANDING WEIGHT
= 5,600 FEET = 13,750 POUNDS
(6240
kg)
NOTE l
l
l
FIGURE 4G-2 4MC
- BLEED
REDUCE MAXIMUM LANDING (435 kg) WITH ENGINE ANTI-ICE
WEIGHT ON.
MAXIMUM
ANTI-ICE
OAT
WITH
ENGINE
BY 960
ON
POUNDS
IS 5°C.
THIS WEIGHT RESULTS IN A MAXIMUM LANDING WEIGHT AT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER THAN 2.1% CAN BE MAINTAINED IN THE CONFIGURATION STATED ABOVE WITH ONE ENGINE INOPERATIVE.
4G-1
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 MAXIMUM LANDING WEIGHT SINGLE ENGINE APPROACH ASSOCIATED
LIMITATION CHART CLIMB REQUIREMENT
CONDITIONS:
POWER ......................................... TAKEOFF (DRY) GEN LOAD.. ................... .200 AMPS (SEE NOTE) BLEED AIR ........................................................ OFF ENG ANTI-ICE . . . . . . . . . . .. . . . .. . .. . . . .. . . OFF (SEE NOTE) CLIMB SPEEDS . . . . . . . . SEE LANDING APPROACH SPEEDS (FIGURE 4G-4 OR 4G-5) GEAR . . . . . . . . . . . . . . . .. . . . . . . .. . . . . . . . . . . UP (APPROACH AND APPROACH CLIMB) !=LAPS . . . . . . . . . . . . . . . . . . .. . . .. . . . .. . . . . . 114 (APPROACH AND APPROACH CLIMB)
- BLEED
EXAMPLE GIVEN: OBTAIN:
AIR OFF
: OAT = 16°C PRESSURE ALTITUDE MAX LANDING WEIGHT
= 5,600 FEET = 13,700 POUNDS
(6210
kg)
NOTE l
l
l
REDUCE MAXIMUM LANDING (385 kg) WITH ENGINE ANTI-ICE
WEIGHT ON.
MAXIMUM
ANTI-ICE
OAT
WITH
ENGINE
BY 850
ON
POUNDS
IS 5°C.
THIS WEIGHT RESULTS IN A MAXIMUM LANDING WEIGHT AT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER THAN 2.1% CAN BE MAINTAINED IN THE CONFIGURATION STATED ABOVE WITH ONE ENGINE INOPERATIVE.
15
FIGURE FAA APPROVED:
MAY 22189
4G-2
PERFORMANCE
4G-3 4MC
METRO III - ICAO ANNEX 8 BALKED LANDING RATE OF CLIMB - BLEED AIR ON 60
ASSOC!ATED
CONDITIONS:
POWER . . . . . . . . . .._......... TAKEOFF (DRY) GEN LOAD . . . . . . . . .. . . . . . . . . . . . . . . . 3M) AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE . . . . . . . OFF (SEE NOTE) CLIMB SPEED . . . . . . . . . SEE SCHEDULE GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN FLAPS . . . . . . . ..I............................. WWN EXAMPLE: GIVEN:
OBTAIN:
OAT - 10% PRESSURE ALTITUDE - 4.ooO FEET GROSS WEIGHT - 11$X POUNDS (5215 k9) CLIMB SPEED - 97 KIAS RATE OF CLIMB - 1.560 FEET PER MINUTE
. REDUCE RATE OF CLIMB BY 290 WITH ENGINE ANTCICE ON. * MAXIMUM
OAT
WITH
BALKED
ENGINE
LANDING SCHEDULE
ANTCICE CLIME (KIAS)
GROSS WEIGHT (POUNDS)
CLIMB SPEED (KIAS)
14,ca
102 100 97 96
12.m 10,003
FEET
PER
MINUTE
ON IS 5-C.
SPEED GROSS
WEIGHT w 6350 Ez 4500
6
500
1,000
1,500
2,000
2,500
3,000
3,500
RATE OF CLIMB (FEET PER MINUTE)
FIGURE 4G-4 4MC
4G-3
PERFORMANCE
FAA APPROVED:
MAY 22/89
LANDING DISTANCE OVER 50 FOOT HEIGHT B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
APPROACH SPEED . . . . . . . SEE CHART POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLIGHT IDLE GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON OR OFF ENG ANTI-ICE . . . . . . . . . . . . . . . . . . . . ON OR OFF RUNWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRY, LEVEL, HARD SURFACE GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN FLAPS . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN BRAKING . . . .._ I-lEAVY DURING ROLLOUT ANTI-SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON OR OFF NOSE WHEEL STEERlNG....ON OR OFF
EXAMPLE: GIVEN:
OBTAIN:
OAT = 18°C PRESSURE ALTITUDE = 7.000 FEET GROSS WEIGHT - 11,900 POUNDS (5400 kg) HEADWIND = 15 KNOTS APPROACH SPEED = 106 KIAS LANDING DISTANCE = 2,775 FEET (945 m)
LANDING
*
SINGLE ENGINE LANDING DISTANCES ARE SHOWN ALL CASES, ARE LONGER THAN TWO ENGINE DISTANCES.
-
IF APPLICABLE, SEE OPERATING OBTAIN REQUIRED FIELD LENGTH.
(1 DETERMINE THAT THE BRAKE ENERGY LIMIT NOT BE EXCEEDED FROM FIGURE 4G-6.
WILL
GROSS SO,00
WEIGHT 5500
GROUND
ROLL
NOTE IS 72%OF
*
LANDING
RULES
FOR
DISTANCE. AND, IN LANDING
FACTORS
TO
m -I 310 0
(kg) 5000
45po
4,000
12ot
z 8$
3,500 1000
E 3,000
-
g I.? 2 s* ii LA.
2.500
6 6 8 f ii E 4 9aJ
i2 cc F 0 Y
2,000
600
1,500 400
1,000
500 OAT (OC)
GROSS
WEIGHT
(POUNDS)
WIND
(KNOTS)
2 IE cl
P 53
-I c) D
0
D z z m X
00
$8 O&
LANDING DISTANCE OVER 50 FOOT HEIGHT GOODYEAR AEROSPACE DUAL ROTOR BRAKES ASSOCIATED
CONDITIONS:
APPROACH POWER
EXAMPLE:
SPEED . . .
. . . . . . . . SEE CHART 3” GLIDE PATH POWER AS REQUIRED GEN LOAD ,...........,..,.,_........ AS REQUIRED BLEED AIR . . . . . . . . . . . . ON OR OFF ENG ANTI-ICE . .._......_....... ON OR OFF RUNWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DRY, LEVEL, HARD SURFACE
GIVEN:
OBTAIN:
OAT = 19°C PRESSURE ALTITUDE = 7.000 FEET GROSS WEIGHT = 13.000 POUNDS (5900 kg) HEADWIND = 17.5 KNOTS APPROACH SPEED = 109 KIAS LANDING DISTANCE = 2.993 FEET (980 m)
FLAPS . . . . .._..__..__.__.............................. DOWN BRAKING HEAVY DURING ROLLOUT NOSE WHEEL STEERING . . . ..ON OR OFF
LANDING
*
TWO ENGINE LANDING DISTANCES CREASE LANDING DISTANCE BY 72% OPERATION.
-
IF APPLICABLE. SEE OPERATING OBTAIN REQUIRED FIELD LENGTH.
GROSS 65.00
6000
WEIGHT 5500
GROUND
ROLL
NOTE IS 62%OF
*
LANDING
RULES
DISTANCE.
ARE SHOWN. INFOR SINGLE ENGINE
FOR
FACTORS
TO
(kg) 5000
4500
600
-40
-20
0
20 OAT (OC)
40
60
14,000
13,000 GROSS
12,000 WEIGHT
11,000 (POUNDS)
10,000
0
10 WIND
(KNOTS)
20
-“-
FAA APPROVED:
4G-6 PERFORMANCE
FIGURE
METRO III - ICAO ANNEX 8
MAY 22189
4G-7 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-8 4MC
PERFORMANCE
MANUFACTURER'S FAA APPROVED: MAY DATA 22/89 ISSUED: MAY 22/89