METRO III – ICAO ANNEX 8 PART D – TAKEOFF PERFORMANCE DRY, BLEED AIR OFF CONTENTS ITEM
PAGE
Takeoff Power Check Chart ............................................................................................................... 4D-1 Maximum Takeoff Weight Limitation Chart ........................................................................................ 4D-3 Distance to Accelerate to V1 and Stop B.F. Goodrich Single Rotor Brakes ........................................................................................... 4D-4 Goodyear Aerospace Dual Rotor Brakes .................................................................................. 4D-5 Single Engine Takeoff Distance to 35 Foot Height ............................................................................ 4D-6 Takeoff Flight Path Distance to 1500 Foot Height ............................................................................. 4D-8 Single Engine Climb Gradient at V2 ........................................................................................ 4D-10 Two Engine Rate of Climb at V35 .................................................................................................... 4D-11
FAA APPROVED: NOV 07/90
PERFORMANCE
4D-i 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-ii 4AC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: NOV 07/90
k 0 a ;z
FIGURE 4D-1 PERFORMANCE
METRO III - ICAO ANNEX 8
FAA APPROVED: NOV 07/90
0
s ;r 8
4D-1 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-2 4AC
PERFORMANCE
FAA APPROVED: NOV DATA 07/90 MANUFACTURER'S ISSUED: NOV 07/90
METRO III - ICAO ANNEX 8 MAXIMUM
TAKEOFF
ASSOCIATED
WEIGHT
LIMITATION
CHART
- DRY, BLEED
CONDITIONS:
AIR OFF NOTE
l
POWER ... ... ...... . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . OFF ENG ANTI-ICE . . .._.......... OFF (SEE NOTE) GEAR . . .. . . . . . . . . . . . . . . . . . .. . . . . . . DOWN (TAKEOFF) UP (ENROUTE) FLAPS . .. . . . . . . . . . . . 114 (TAKEOFF) UP (ENROUTE)
l
l
REDUCE TAKEOFF WEIGHT WITH ENGINE ANTI-ICE ON. MAXIMUM
OAT
WITH
ENGINE
BY
1,050
ANTI-ICE
POUNDS
ON
(475
kg)
IS 5°C.
THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE V,
J
EXAMPLE: GIVEN: OBTAIN:
OAT = 4°C PRESSURE ALTITUDE = 8,000 FEET TAKEOFF WEIGHT = 13,825 DECREASE (ANTI-ICE ON) = -1,050 NET TAKEOFF WEIGHT = 12,775
POUNDS POUNDS POUNDS
(6270 (-475 (5795
FIGURE FAA APPROVED:
NOV 07/90
kg) l&j kg)
4D-2
PERFORMANCE
4D-3 4AC
METRO III - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO V, AND STOP B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
POWER ..,.__....................... TAKEOFF (DRY) GEN LOAD . . .. .._........................... 200 AMPS BLEED AIR . . .. . .. . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . .. .. . . . . . . . OFF (SEE NOTE) RUNWAY . . . . . . . . . . . . . . . DRY, HARD SURFACE FLAPS ..__................................................... l/4 4815) DECISION SPEED . . . . . V 1 (FIGURE ANTI-SKID ,.______........................ ON OR OFF NOSE WHEEL STEERING .. ..ON OR OFF
- DRY, BLEED
EXAMPLE: GIVEN:
OBTAIN:
OAT = -10°C PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 2 PERCENT (UPHILL) 3,500 ACCELERATE -STOP DISTANCE = INCREASE (ANTI-ICE ON) = 170 NET ACCELERATE -STOP DISTANCE = 3,670
l
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
EXCEED 4P2. GROSS
l
WEIGHT
FIGURE 4D-4 4AC
AIR OFF
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
(1000
WITH
- STOP ANTI-ICE ENGINE
DISTANCE ON.
ANTI-ICE
ON
FEET FEET FEET
BY
(1070 (50 (1120
m) m) m)
4.8
IS 5°C.
kg)
4D-3
PERFORMANCE
FAA APPROVED:
NOV 07/90
METRO III - ICAO ANNEX 8 DISTANCE
TO ACCELERATE
TO V, AND STOP
- DRY, BLEED
AIR OFF
GOODYEAR AEROSPACE DUAL ROTOR BRAKES ASSOCIATED
EXAMPLE:
CONDITIONS:
POWER . . . . . . . . . . . . . . . . . . . .. . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . .._.................... 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . . . . . .. . .. . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . OFF (SEE NOTE) RUNWAY .. . . . . .. . . . DRY, HARD SURFACE FLAPS . . .. .. . .. . .. . . . .. . .. . . . .. .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . l/4 DECISION SPEED . . . ..‘I. (FIGURE 4B-15) ANTI-SKID . . . . .. .. . . .. .. . . . .. . . . . . . . . . . . . . ON OR OFF NOSE WHEEL STEERING . . ..ON OR OFF
GIVEN:
OAT = -10°C PRESSURE ALTlTUDE = 4,000 FEET GROSS WEIGHT = 13.000 POUNDS (5900 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 2 PERCENT (DOWNHILL) ACCELERATE -STOP DISTANCE = 3,550 INCREASE (ANTI-ICE ON) = 160 NET ACCELERATE -STOP DISTANCE = 3,710
OBTAIN:
l
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
EXCEED 4P2.
l
L
:
L
GROSS
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
WEIGHT 6
40
-20
0
20 OAT (OC)
40
60
15
14
GROSS
13 WEIGHT
12
11 (1,000
(1000 5
kg)
10
9
POUNDS)
WITH
0 WIND
10
-STOP ANTI-ICE ENGINE
20 (KNOTS)
DISTANCE ON ANTI-ICE
30
FEET FEET FEET
0
m) m) m)
BY 4.5
ON
2
(1080 (50 (1130
IS5”C.
4
6
RUNWAY SLOPE (PERCENT)
FIGURE 4D-4 FAA APPROVED: NOV 07/90
PERFORMANCE
4D-5 4AC
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
DISTANCE
TO 35 FOOT
ENGINE 0
300
0
1,000
HEIGHT
ANTI-ICE METERS
- DRY, BLEED
AIR OFF
EFFECTS
600
900
8,000
6,000
S.L.
INCREASE WITH
2,000 (FEET) IN TAKEOFF DISTANCE ENGINE ANTI-ICE ON
FIGURE 4D-6 4AC
3,000
4D-5
PERFORMANCE
FAA APPROVED:
NOV 07/90
METRO III - ICAO ANNEX 8 SINGLE
ENGINE ASSOCIATED
TAKEOFF
DISTANCE
TO 35 FOOT
CONDITIONS:
HEIGHT
- DRY, BLEED
AIR OFF
EXAMPLE:
POWER .. . . . . . . . . . . . . . . . . . .. . . . . . . .. TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . .. .. . .. . . . .. . .. . . . OFF ENG ANTI-ICE . . . . . . . OFF (SEE GRAPH) RUNWAY . . . . . . . . . . . . .. . . DRY, HARD SURFACE V 1 SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4515 V2 SPEED . .._.__________...._........ FIGURE 4B15 FLAPS . . . . . . . . .. . . . . . . . . . . . .. . . . .. . .. . .. .. . . . . . . . . . . . . . . . . . . . 114 NOSE WHEEL STEERING . . ..ON OR OFF
GIVEN:
OAT = 0°C PRESSURE ALTITUDE = 3,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 13 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V1 SPEED = 102 KIAS V2 SPEED = 111 KIAS TAKEOFF DISTANCE = 4,900 FEET (1495 INCREASE (ATI-ICE ON) = 610 FEET (165 TOTAL TAKEOFF DISTANCE = 5,510 FEET (1660
OBTAIN:
m) m) m)
NOTE MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
FOR TAKEOFF FIELD LENGTH ENGINE TAKEOFF DISTANCES ENGINE TAKEOFF DISTANCES
EXCEED 4D-2. GROSS
WEIGHT
(1000 5
6
DETERMINATION, SINGLE ARE LONGER THAN TWO FACTORED BY 1.15.
kg)
13
12
40
-20
0
20
40
60
15
OAT (OC)
GROSS
FIGURE FAA APPROVED:
NOV 07/90
14
13 WEIGHT
12
11 (1,000
10
9
POUNDS)
0
10 WIND
20 (KNOTS)
30
0
1
2
RUNWAY SLOPE (PERCENT)
4D-5 (continued)
PERFORMANCE
4D-7 4AC
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF An estimate of the horizontal distance required to clear an obstacle up to 1,500 feet above the runway may be obtained by using Figures 4D-5 and 4D-6. The takeoff path is considered in two phases, as follows: (1) The distance from the start of the takeoff roll to 35 feet above the runway (Figure 4D-5). Both engines are assumed to operate normally to V1 speed, where one engine fails and the takeoff is continued on one engine. This phase is concluded when the airplane reaches 35 foot height at V2. (2) Single Engine Climb at V2 (Figure 4D-6).
AIRCRAFT ROTATION
START OF TAKEOFF ROLL
TWO ENGINE TAKEOFF WITH ENGINE FAILURE AT V1, FLAPS 1/4
AFTER POSITIVE CLIMB IS ESTABLISHED, GEAR IS RETRACTED AND INOPERATIVE PROPELLER IS FEATHERED
MAINTAIN V2 CLIMB WITH 1/4 FLAPS AND GEAR RETRACTED UNTIL OBSTACLE IS CLEARED
ACCELERATE TO VYSE AND RETRACT FLAPS
VYSE
V2
LIFTOFF V1 SINGLE ENGINE TAKEOFF FLIGHT PATH TO 35 FOOT HEIGHT (FIGURE 4D–5)
OBSTACLE CLEARANCE BUT NOT LESS THAN 400 FEET
V2 35 FT. SINGLE ENGINE CLIMB GRADIENT AT V2 (FIGURE 4D–6)
SINGLE ENGINE CLIMB AT VYSE (FIGURE 4F–3)
EXAMPLE: Given:
OAT= 20oC AIRFIELD PRESSURE ALTITUDE = 1,400 FEET GROSS WEIGHT = 12,600 POUNDS (5715 kg) BLEED AIR OFF
ENGINE ANTI-ICE OFF DRY POWER NO WIND LEVEL RUNWAY
Desired: TAKEOFF FLIGHT PATH DISTANCE TO 1,500 FOOT HEIGHT AFTER ENGINE FAILURE AT V1 Obtain:
(1) TAKEOFF DISTANCE TO 35 FOOT HEIGHT = 4,650 FEET (1415 m) (FIGURE 4D-5) (2) CLIMB DISTANCE: a. AVG HEIGHT = FIELD ELEVATION + HEIGHT INCREASE = 2,150 FEET (655 m) 2 b. ESTIMATED TEMPERATURE = 18oC (AT 2oC PER 1,000 FEET) c. NET CLIMB GRADIENT = 4.6 PERCENT (FIGURE 4D-6) d. DISTANCE = (100) x (1,500 - 35) = 31,848 FEET (9710 m) 4.6 (3) TOTAL FLIGHT PATH DISTANCE = (1) + (2) = 36,498 FEET (11125 m)
4D-8 4AC
PERFORMANCE
FAA APPROVED: NOV 07/90
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) Figures 4D-5 and 4D-6 depend upon the following variable conditions. The appropriate charts must be used to ensure accuracy. VARIABLE CONDITIONS: • Engine Anti-Ice – Off or On (Adjust distances as indicated by anti-ice effects graphs or notes for anti-ice Off). • V1 and V2 Speeds – From Figure 4B-15. • Wind and Runway Gradient Effect on Takeoff Distance to 35 feet. The charts are also based on the following common conditions: COMMON CONDITIONS: • • • • • •
Power – Dry with Bleed Air Off Generator Load – 200 AMPS total. Runway – Dry, Hard Surface. No wind effect on V2 Climb Gradient. Flaps – 1/4 until after reaching 400 feet AGL and clearing obstacles at V2; then up. Propeller on inoperative engine – Windmilling in the NTS mode until it is feathered after attaining V2 speed. NOTE The maximum takeoff weight (Figure 4D-2) and the flight paths constructed from Figures 4D-5 and 4D-6, can be realized using the following procedures:
1. At V1, rotate to takeoff attitude (approximately 10o nose up). 2. Once airborne, establish 5o of bank into operating engine. 3. After a positive rate of climb is indicated on the vertical speed indicator and the altimeter, retract the landing gear. This will occur at approximately 15 to 20 feet above the ground. 4. Climb and accelerate to the scheduled V2 speed. 5. Feather the propeller on the inoperative engine. 6. Maintain V2 speed to 400 feet AGL minimum or until obstacle clearance is assured. 7. Retract flaps and accelerate to best rate of climb speed.
FAA APPROVED: NOV 07/90
PERFORMANCE
4D-9 4AC
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE SINGLE ENGINE CLIMB GRADIENT
TO 1500 FOOT HEIGHT (continued) AT V, - DRY, BLEED AIR OFF ASSOClATED
CONDITIONS:
POWER .._......_...... MAX CONTINUOUS PROPELLER . . . . . . . . . . . FEATHERED ON INOPERATIVE ENGINE GEN LOAD ....... .._ .............. 200 AMPS BLEED AIR .................................... OFF ENG ANTI-ICE ....... OFF (SEE NOTE) Vs SPEED ................... FIGURE 48-15 GZAR ....... ..- ...... ............................... UP FLAPS ........................... ..” ................ 114 EXAMPLE: GIVEN:
OBTAIN:
OAT - 0% PRESSURE ALTITUDE - l.ooO FEET GROSS WElGHT - ll.M)o POUNDS (4993 kg) VP SPEED - 103 KIAS GROSS CLIMB GRADIENT 10.70 PERCENT DECREASE (ANTI-ICE ON) -1.35 PERCENT GROSS CLIMB GRADIENT 9.35 PERCENT FLffiHT PATH DETERMINATION = -0.8 PERCENT NET CLIMB GRADIENT 8.55 PERCENT
* REDUCE CLIMB GRADIENT BY 1.35 PERCENT WITH ENGINE ANTClCE ON. . MAXIMUM
OAT
WITH
ENGINE
ANT!-ICE
. FOR FLIGHT PATH DETERMINATION GRADIENT BY 0.8 PERCENT GRADIENT.
-1
0
1
2
3
4 GROSS
5
6 CLIMB
7 GRADIENT
8
9
10
11
13
14
15
CLIMB
GRADIENT
ON IS 5°C. REDUCE
CLIMB
(PERCENT)
NET CLIMB GRADIENT /.INUSOBPERCENT.NoTE/
EQUALS
FIGURE 4D-10 4AC
12
GRADIENT
GROSS
4D-6
PERFORMANCE
FAA APPROVED:
NOV 07/90
II- ICAO ANNEX 8 Ilm m
-METRO TWO
ENGINE
RATE
OF CLIMB
AT V, - DRY, EBLEED AIR OFF ASSOC!ATED
CONDITIONS:
60 POWER ...................... TAKEOFF (DRY) GEN LOAD ........................ .2M) AMPS BLEED AIR .................................... OFF ENG ANTI-ICE ....... OFF (SEE NOTE) V 35 SPEED ................ FIGURE 48-15 GEAR ................................................ UP FLAPS ....... .._ .................................... 114 EXAMPLE: GIVEN:
OAT - -54: PRESSURE ALTITUDE = 6,CXlO FEET GROSS WEIGHT = ll.COO POUNDS (4990 kal V35 SPEED = 112 KliS RATE OF CLIMB I 3.175 FEET PER MINUTE DECREASE (ANTI-ICE ON) = 405 FEET PER MINUTE NET RATE OF CLIMB 2.770 FEET PER MINUTE “,
OBTAIN:
OAT
WITH
ENGINE
ANTI-ICE
ON IS 5-C.
-
-10
-20
-30
6
RATE
OF CLIMB
(FEET
PER
MINUTE)
FIGURE FAA APPROVED:
NOV 07/90
4D-7
PERFORMANCE
4D-11 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-12 4AC
PERFORMANCE
FAA APPROVED: NOV DATA 07/90 MANUFACTURER'S ISSUED: NOV 07/90