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: NOV 07/90
PERFORMANCE
4G-i 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-ii 4AC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: NOV 07/90
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
FAA APPROVED: NOV 07/90 MANUFACTURER'S DATA ISSUED: NOV 07/90
PERFORMANCE
4G-1 4AC
MA~~~~~~~
LANDING
WEIGHT
LIMITATION
CHART
- BLEED
ASSOCIA I Fb I:OND~TIONS:
EXAMPLE
(DRY) POWER . .. .. . .. .. .. . .. . .. .. .. . .. . .. .. .. . .. . .. .. . .. . TAKEOFF GEN LOAD . .. . .. . .. .. .. . .. . .. .. .. . . 200 AMPS (SEE NOTE) BLEED AIR .. .. . .. .. . .. .. . .. .. .. . .. . .. .. . .. .. . .. . .. .. . . ... . .. . .. . .. .. . .. ON ENG ANTI-ICE . .. . .. . .. .. .. . .. . .. .. .. . .. .. . . OFF (SEE NOTE) CLIMB SPEEDS . . .. . .. .. .. SEE LANDING APPROACH SPEEDS (FIGURE 4G-4 OR 4G-5) AND GEAR .. .. . . .. .. . .. . . . .. .. . . .. UP (APPROACH APPROACH CLIMB) DOWN (LANDING) AND FLAPS .. . .. .. .. .. . . .. . .. . .. .. . . .. . . . 114 (APPROACH APPROACH CLIMB) DOWN (LANDING)
GIVEN: OBTAIN:
AIR ON
: OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET MAX LANDING WEIGHT = 13,900 POUNDS
(6395 kg)
NOTE . REDUCE MAXIMUM LANDING WEIGHT 495 kg) WITH ENGINE ANTI-ICE ON. * MAXIMUM
OAT WITH ENGINE
ANTI-ICE
BY 1,090 POUNDS
ON IS 5°C.
. DECREASE MAXIMUM LANDING WEIGHT BY 8 POUNDS (3.6 kg) FOR EACH 10 AMPS ABOVE 200 AMPS GENERATOR LOAD. * 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.
METRO III - ICAO ANNEX 8 MAXIMUM ASSOCIATED
LANDING
WEIGHT
LIMITATION
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) AND GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP (APPROACH APPROACH CUMB) DOWN (LANDING) FLAPS .. ... .. .. . . . . . . l/4 (APPROACH AND APPROACH CLIMB) DOWN (LANDING)
CHART EXAMPLE GIVEN: OBTAIN:
- BLEED AIR OFF : OAT = 3°C PRESSURE ALTlTUDE MAX LANDING WEIGHT
= 8,000 FEET = 13,900 POUNDS
(6305
ka)
NOTE l
l
l
l
REDUCE MAXIMUM LANDING (430 kg) WITH ENGINE ANTI-ICE
WEIGHT ON.
BY 950
MAXIMUM
ANTI-ICE
ON
OAT
WITH
ENGINE
POUNDS
IS 5°C.
DECREASEMAXIMUM LANDING WEIGHT BY 8 POUNDS(3.6 kg) FOR EACH 10 AMPS ABOVE 200AMPS GENER-ATOR LOAD. THISWEIGHTRESULTSINAMAXIMUMIANDINGWEIGHTAT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER 2,1%CANBEMAlNTAlNED INTHECONFIGURATIONSTATED ABOVE WITH ONE ENGINE INOPERATIVE.
THAN
15
FAA APPROVED: NOV 07/90
FIGURE 4G-2 PERFORMANCE
4G-3 4AC
METRO Ill - ICAO ANNEX 8 BALKED
LANDING
RATE OF CLIMB - BLEED AIR ON ASSOCLATED
CONDITIONS:
POWER.. .............. MAX CONTINUOUS GEN LOAD.. ................ AS REQUIRED BLEED AIR ....................................... ON ENG ANTI-ICE ....... OFF (SEE NOTE) CLIMB SPEED ......... SEE SCHEDULE GEAR ......... _. .............................. DOWN FLAPS ....... .._..................- ......... WWN EXAMPLE: GIVEN:
OBTAIN:
OAT - -5°C PRESSURE ALTITUDE - 4,wO FEET GROSS WEIGHT - ~Z$XIO POUNDS (5440 kg) CLIMB SPEED I 92 KIAS RATE OF CLIMB 1.900 FEET PER MINUTE DECREASE (ANTI-ICE ON)-360 FEET PER MINUTE NET RATE OF CLIMB 1.550 FEET PER MINUTE
REDUCE
* MAXIMUM
RATE OF CLIMB
OAT
WITH
BALKED
400
800
1,200 RATE
1,600 OF CLIMB
2,000 (FEET
PER
2,400
3,200
ENGINE
LANDING SCHEDULE
ANT!-ICE CLIMB (KIAS)
ON
WITH
IS 5°C.
SPEED
3,60
MINUTE)
FIGURE 4G-4 4AC
2,800
BY 360 FEET PER MINUTE
4G-3
PERFORMANCE
FAA APPROVED:
NOV 07/90
LANDING DISTANCE OVER 50 FOOT HEIGHT B. F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
EXAMPLE:
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.. ...... HEAVY DURING ROLLOUT ANTI-SKID ..... ....... ..... .... ...... . .. ON OR OFF NOSE WHEEL STEERlNG....ON OR OFF
GIVEN:
OAT - 18°C PRESSURE ALTITUDE - 7,ooO FEET GROSS WEIGHT I 11.w POUNDS (5400 KG) HEADWIND = 15 KNOTS OBTAIN: APPROACH SPEED - 106 KIAS LANDING DISTANCE = 2.775 FEET (845 m) 1 CAUTION
I
. LANDING
GROUND
ROLL
NOTE IS 72%
OF LANDING
DISTANCE.
. SINGLE ENGINE LANDING DISTANCES ARE SHOWN ALL CASES, ARE LONGER THAN TWO ENGINE DISTANCES.
AND, IN LANDING
) . IF APPLICABLE. SEE OPERATING RULES OBTAIN REQUIRED FIELD LENGTH.
DETERMINE THAT ME BRAKE ENERGY LIMIT WILL NOT SE EXCEEDED FROM FIGURE 4G-6.
GROSS 6000
WEIGHT 5500
FOR FACTORS
TO
( kg) 5qoo
1200
3,500
g k 5
3,000
isI i IL 0
2.500
40
-20
0
20
OAT (“C)
40
60
14,000
13,000
GROSS
12,000
WEIGHT
11,000
( POUNDS)
10,000
0
10
WIND (KNOTS)
20
---
,” F 0
D z z m x 00
LANDING DISTANCE OVER 50 FOOT HEIGHT GOODYEAR AEROSPACE DUAL ROTOR BRAKES ASSOCIATED
CONDITIONS:
EXAMPLE:
APPROACH SPEED . ...... .. ... .. SEE CHART POWER ...... ...... .. .... ..... .. ..... 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 GEAR ....... ........ .... .. .. .. ........ ...... ....... ... DOWN FLAPS ..... ....... ..... ...... ........ ....... ....... ... DOWN BRAKING . ....... HEAW DURING ROLLOUT NOSE WHEEL STEERlNG....ON OR OFF
GIVEN:
OAT - 19°C PRESSURE ALTITUDE - 7.ooO FEET GROSS WEIGHT - 13,DCO POUNDS (5900 KGI HEADWIND - 7.5 KNOTS OBTAIN: APPROACH SPEED - 109 KIAS LANDING DISTANCE = 2.890 FEET (990 m)
NOTE
* LANDING
GROUND
ROLL
IS 62% OF LANDING
* TWO ENGINE LANDING DISTANCES ARE SHOWN, INCREASE LANDING DISTANCE BY 72% FOR SINGLE ENGINE OPERATION. . IF APPLICABLE, SEE OPERATING RULES OBTAIN REQUIRED FIELD LENGTH.
GROSS 6000
DISTANCE.
WEIGHT
5500
FOR FACTORS
TO
( kg) 5000
0 D z z m x 00
-40
-20
0
20
OAT (OC)
40
60
14,000
13,000
12,000
GROSS
WEIGHT
11,000 ( POUNDS)
10,000
9,000
0
IO WIND
(KNOTS)
20
FAA APPROVED:
4G-6 PERFORMANCE
FIGURE
METRO III - ICAO ANNEX 8
NOV 07190
4G-7 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-8 4AC
PERFORMANCE
FAA APPROVED: NOV DATA 07/90 MANUFACTURER'S ISSUED: NOV 07/90