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 Dowty Rotol Propellers .............................................................................................................. 4G-4 McCauley Propellers ................................................................................................................. 5G-5 Two Engine Landing Distance Over 50 Foot Height .......................................................................... 4G-6 Landing Brake Energy Limits ............................................................................................................. 4G-7
FAA APPROVED: MAY 22/89
PERFORMANCE
4G-i 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-ii 8AC
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 8AC
METRO III -ICAO MAXIMUM ASSOCIATED
LANDING
WEIGHT
LIMITATION
CONDITIONS:
POWER .......... .... ............... ............ TAKEOFF (DRY) PROPELLER .. ..... ... ..... ...... ........... FEATHERED ON INOPERATIVE ENGINE GEN LOAD ...... ....................................... 300 AMPS BLEED AIR .. ..... ... ..... .. ..... ... ... .. .............. ..............ON ENG ANTI-ICE .. ...._....................OFF (SEE NOTE) CLIMB SPEEDS ..... SEE LANDING APPROACH SPEEDS (FIGURE 4G-5) GEAR ................. ........ ..... .. ... UP (APPROACH AND APPROACH CLIMB) FLAPS .. ........ ........................ l/4 (APPROACH AND APPROACH CLIMB)
CHART
ANNEX 8
- BLEED
EXAMPLE
AIR ON
:
GIVEN:
OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: MAX LANDING WEIGHT = 13,560 POUNDS
l
l
l
(6160 kg)
REDUCE MAXIMUM LANDING WEIGHT BY 1,200 POUNDS (544 kg) WITH ENGINE ANTI-ICE ON. MAXIMUM
OAT WITH ENGINE ANTI-ICE ON 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. 17
16 7
FIGURE 4G-1 4G-2 8AC
PERFORMANCE
FAA APPROVED: MAY 22l89
METRO III -ICAO ANNEX 8 MAXIMUM
LANDING WEIGHT LIMITATION
ASSOCIATED
CONDITIONS:
CHART - BLEED AIR OFF EXAMPLE
POWER .. ........ ............................... TAKEOFF (DRY) PROPELLER .. .... ... ..... .................. FEATHERED ON INOPERATIVE ENGINE GEN LOAD ............................................. 300 AMPS BLEED AIR ................................. ....................... OFF ENG ANTI-ICE ...... .... .. .. ... .. ...... ..OFF (SEE NOTE) CLIMB SPEEDS ........ SEE LANDING APPROACH SPEEDS (FIGURE 4G-5) GEAR ...................... ....... ... ... UP (APPROACH AND APPROACH CLIMB) FLAPS .. .... .... .. ...................... 114 (APPROACH AND APPROACH CLIMB)
:
GIVEN:
OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: MAX LANDING WEIGHT = 14,490 POUNDS (6575 kg)
l
l
l
NOTE REDUCE MAXIMUM LANDING WEIGHT BY 1,050 POUNDS (475 kg) WITH ENGINE ANTI-ICE ON. MAXIMUM
OAT WITH ENGINE ANTI-ICE
ON 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.
17
16
5
FIGURE 4G-2 FAA APPROVED: MAY 22l89
PERFORMANCE
4G-3 8AC
METRO Ill -ICAO ANNEX 8 BALKED LANDING RATE OF CLIMB - BLEED AIR ON DOWTY ROTOL PROPELLERS ASSOClATED
CONDITIONS:
POWER . . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . .. . . . . . . . . . . . . . . . . . . 3W AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE . . . . . . . OFF (SEE NOTE) CLIMB SPEED .._...... SEE SCHEDULE GEAR . . . . . . . _ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN FLAPS . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DDWN EXAMPLE: GIVEN: OBTAIN:
OAT - 10-C PRESSURE ALTITUDE - 4.C0J FEET GROSS WEIGHT - 14.500 POUNDS (6580 kg) CLIMB SPEED - 103 KIAS RATE OF CLIMB - 1.040 FEET PER MINUTE
NOTE - REDUCE RATE OF CLIMB BY 330 WITH ENGINE ANTCICE ON. * MAXIMUM
OAT BALKED
WITH
ENGINE
LANDING SCHEDULE
FEET
ANTCICE CLIMB (KIAS)
PER
MINUTE
ON IS 5°C.
SPEED
GROSS WEIGHT (kg) 7006 6500
RATE
OF CLIMB
(FEET
PER
MINUTE)
FIGURE 4G-3 4G-4 8AC
PERFORMANCE
FAA APPROVED: MAY 22l89
METRO III - ICAO ANNEX 8 BALKED LANDING RATE MCCAULEY PROPELLERS
OF CLIMB
-
BLEED
AIR ON ASSOCIATED
CONDITIONS:
(DRY) POWER . . . . ..__........_... TAKEOFF GEN LOAD _........___......._..... 300 AMPS BLEED AIR . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE _..... OFF (SEE NOTE) CLIME SPEED ._...... SEE SCHEDULE GEAR . . . . .. . . . . ..______....................... DOWN FLAPS .._.___.........____................... DOWN EXAMPLE: GIVEN:
OBTAIN:
OAT = 10°C PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT =14,500 POUNDS (6560 kg) CLIMB SPEED = 103 KIAS RATE OF CLIMB = 995 FEET PER MINUTE
l
REDUCE
l
MAXIMUM
PATE
OAT WITH BALKED
600
800 RATE
OF CLIMB
1,000
1,400
1,200
(FEET
PER
MAY 22189
1,600
2,000
BY 290
ENGINE
LANDING SCHEDULE
FEET
ANTI-ICE CUMB (KIAS)
PER
MINUTE
ON IS 5%.
SPEED
2,200
MINUTE)
FIGURE FAA APPROVED:
1,600
OF CLIMB
4G-4
PERFORMANCE
4G-5 8AC
4G-6 8AC
TWO ENGINE LANDING DISTANCE OVER 50 FOOT HEIGHT ASSOCIATED CONDITIONS:
EXAMPLE:
APPROACH SPEED ................ SEE CHART POWER .............................. 3o GLIDE PATH POWER AS REQUIRED GEN LOAD ........................... AS REQUIRED BLEED AIR ............................ AS REQUIRED ENG ANTI-ICE ....................................... OFF RUNWAY .................................. DRY, LEVEL, HARD SURFACE GEAR ................................................... DOWN FLAPS ................................................. DOWN BRAKING ......... HEAVY DURING ROLLOUT NOSE WHEEL STEERING ..... ON OR OFF
OAT = 18oC PRESSURE ALTITUDE = 7,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 15 KNOTS OBTAIN: APPROACH SPEED = 115 KIAS LANDING DISTANCE = 3,150 FEET (960 m)
CAUTION
GIVEN:
DETERMINE THAT THE BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED FROM FIGURE 4G-6.
NOTE • LANDING GROUND ROLL IS 67% OF LANDING DISTANCE.
7000
GROSS WEIGHT (KILOGRAMS) 6500 6000 5500
5000
D
ITU
1200
RE
U
SS
E PR
T AL
4,000
00
8,0
00 0
0 4,0
1000 ISA
00
2,0
EL
3,000
EV
AL
SE
ISA
IL
2,500
TA
FAA APPROVED: MAY 22/89 REVISED: MAR 26/95
0
–3
800
3,500
+40
6,0
2,000
600 HE
AD
118
116
114
112
110
108
106
104
102
100
1,500
APPROACH SPEED (KIAS) (ASSUMES NO INSTRUMENT ERROR)
400
–40
–20
0
20 OAT (oC)
40
60 16,000
15,000 14,000 13,000 12,000 GROSS WEIGHT (POUNDS)
11,000
10,000 0
1,000 10 20 30 WIND (KNOTS)
LANDING DISTANCE OVER 50 FOOT HEIGHT (FEET)
)
ET
FE E(
4,500
ISA
FIGURE 4G-5
PERFORMANCE
LANDING DISTANCE OVER 50 FOOT HEIGHT (METERS)
1400
REFERENCE LINE
REFERENCE LINE
5,000
METRO III – ICAO ANNEX 8
• IF APPLICABLE, SEE OPERATING RULES FOR FACTORS TO OBTAIN REQUIRED FIELD LENGTH.
FAA FAA APPROVED: APPROVED: MAY MAY 22/89 22/89 REVISED: MAR 26/95
LANDING BRAKE ENERGY LIMITS EXAMPLE: CAUTION
OAT = 18oC PRESSURE ALTITUDE = 7,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 15 KNOTS OBTAIN: MAXIMUM ALLOWABLE TAILWIND = 1.0 KNOT (BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED) GIVEN:
OPERATIONS WITH INSUFFICIENT HEADWINDS OR EXCESSIVE TAILWINDS WILL RESULT IN EXCEEDING THE BRAKE ENERGY LIMIT OF 2,820,000 FOOT POUNDS (3864000 Nm) PER BRAKE.
ET)
(FE
IS
(kg)
P
A
72 0( ,00 16
0(
68
60
05
)
)
50) (63
,00 15
(59
00)
000 14,
000
SS
13,
OUN
00 (
T, P WE
EL
LEV
ISA
GRO
SEA
12,0
A
IGH
IS
FIGURE 4G-6
0
–3
PERFORMANCE
0
2,00
0)
0
DS
+4
0
4,00
544
0
6,00
40
–30
–20
–10
0
10 OAT (oC)
20
30
40
50
60
–15
–10 0 10 20 MAXIMUM MINIMUM ALLOWABLE REQUIRED TAILWIND HEADWIND WIND (KNOTS)
METRO III – ICAO ANNEX 8
UDE LTIT A E 0 SUR 8,00 RES
4G-7 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4G-8 8AC
PERFORMANCE
MANUFACTURER'S FAA APPROVED: MAY DATA 22/89 ISSUED: MAY 22/89