METRO III – ICAO ANNEX 8 PART E – TAKEOFF PERFORMANCE WET CONTENTS ITEM
PAGE
Takeoff Power Check Chart ................................................................................................................4E-1 Maximum Takeoff Weight Limitation Chart ......................................................................................... 4E-3 Distance to Accelerate to V1 and Stop B.F. Goodrich Single Rotor Brakes ............................................................................................ 4E-4 Goodyear Aerospace Dual Rotor Brakes ................................................................................... 4E-5 Single Engine Takeoff Distance to 35 Foot Height ............................................................................. 4E-6 Takeoff Flight Path Distance to 1500 Foot Height .............................................................................. 4E-8 Single Engine Climb Gradient at V2 ......................................................................................... 4E-12 Two Engine Rate of Climb at V35 ..................................................................................................... 4E-14
FAA APPROVED: NOV 07/90
PERFORMANCE
4E-i 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4E-ii 4AC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: NOV 07/90
METRO III - ICAO ANNEX 8 TAKEOFF
POWER
ASSOCIATED
CHECK
CHART-WET EXAMPLE:
CONDITIONS:
GIVEN:
OAT = 27°C PRESSURE ALTITUDE = 3,000 FEET ENGINE ANTI-ICE SYSTEM - OFF OBTAIN: ENGINE TORQUE = 99 PERCENT
RPM ...... ........ ... ........ ...... ..... ...... 100% MAX ALLOWABLE EGT ........ 660°C GEN LOAD ...........0 TO 200 AMPS BLEED AIR ............................. ... OFF ENG ANTI-ICE .. .... ...... SEE GRAPH SPEED ._.._.................0 TO 60 KIAS
NOTE l
MAXIMUM
OAT WITH ENGINE ANTI-ICE ON IS 5°C.
l
MINIMUM OAT FOR WET POWER OPERATION
IS 4°C.
. REFERENCE EGT IS THE EGT OBTAINED WHEN REQUIRED ENGINE TORQUE IS SET IN ACCORDANCE WITH THIS CHART AND MUST NOT EXCEED 660°C. 120
80
-10
0
10
20
30
40
FIGURE NOV 07/90
OFF
ON ENGINE ANTI-ICE SYSTEM
OAT (OC)
FAA APPROVED:
50
4E-1
PERFORMANCE
4E-1 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4E-2 4AC
PERFORMANCE
FAA MANUFACTURER'S APPROVED: NOV DATA 07/90 ISSUED: NOV 07/90
METRO III - ICAO ANNEX 8 MAXIMUM ASSOCIATED
TAKEOFF
WEIGHT
LIMITATION
CHART
- WET NOTE
CONDITIONS: l
POWER ,,,,,..,,,,........,... TAKEOFF (WET) GEN LOAD .,,,,........,,............. 200 AMPS BLEED AIR .,,,,.,..,.,.,,...............,,,...... OFF ENG ANTI-ICE ... OFF (SEE NOTE) (TAKEOFF) GEAR .. . .. .. . . . . . . . . . . . . . . . . . DOWN UP (EN ROUTE) FLAPS .,,..,.,,..,,..........,,,,,. 114 (TAKEOFF) UP (EN ROUTE)
REDUCE TAKEOFF WEIGHT WITH ENGINE ANTI-ICE ON.
. MAXIMUM l
OAT
WITH
ENGINE
BY
985
ANTI-ICE
THIS WEIGHT IS THE MAXIMUM CAN BE CONTINUED AFTER AN RECOGNIZED AT OR ABOVE V1.
POUNDS
ON
(445
kg)
IS 5OC.
AT WHICH TAKEOFF ENGINE FAILURE IS
EXAMPLE: GIVEN: OBTAIN:
OAT = 28OC PRESSURE ALTITUDE = 5,500 FEET TAKEOFF WEIGHT = 13,550 POUNDS
(6145
kg)
16
7
FIGURE FAA APPROVED: NOV 07/90 REVISED: NOV 18/97
4E-2
PERFORMANCE
4E-3 4AC
METRO III - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO VI AND STOP B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
EXAMPLE:
CONDITIONS:
TAKEOFF (WET) POWER ............................ 200 AMPS GEN LOAD ................................. BLEED AIR ............................................ OFF ENG ANTI-ICE.. ............. OFF (SEE NOTE) RUNWAY.. ............. DRY, HARD SURFACE FLAPS ....................................................... II4 ... V, (FIGURE 4B-15) DECISION SPEED.. ANTI-SKID ............................... ON OR OFF NOSE WHEEL STEERING.. ON OR OFF
1
-WET
GIVEN:
OAT = 25OC PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT = 12,000 POUNDS (5440 kg) TAILWIND = 5 KNOTS RUNWAY SLOPE = 2 PERCENT (UPHILL) ACCELERATE - STOP DISTANCE = 4,300 FEET
OBTAIN:
I
NOTE l
1 MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4E-2.
l
GROSS
WEIGHT
0
20
OAT (OC)
40
60
15
GROSS
14
13
WEIGHT
FIGURE 4E-4 4AC
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
(1000
6
-20
(1310
WITH
- STOP ANTI-ICE ENGINE
DISTANCE ON.
ANTI-ICE
BY
ON
IS 5OC.
2
4
2
kg)
5
12
11
(1,000
10 POUNDS)
9
0
10
WIND
20 (KNOTS)
30
0
6'
RUNWAY SLOPE (PERCENT)
4E-3
PERFORMANCE
FAA APPROVED: NOV 07/90 REVISED: NOV 18/97
METRO III - ICAO ANNEX 8 DISTANCE GOODYEAR
TO ACCELERATE TO VI AND STOP - WET AEROSPACE DUAL ROTOR BRAKES
ASSOCIATED
EXAMPLE:
CONDITIONS:
GIVEN:
POWER .,..,,....,,,............... TAKEOFF (WET) GEN LOAD . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . .. . 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . .. . .. . .. . . . . OFF ENG ANTI-ICE . . .. . . . . . OFF (SEE NOTE) RUNWAY . . . . . . . . DRY, HARD SURFACE FLAPS . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . l/4 1 DECISION SPEED .. . . V, (FIGURE 4B-15) NOSE WHEEL STEERING ON OR OFF
OAT = 25OC PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT = 12,000 POUNDS (5440kg) TAILWIND = 10 KNOTS RUNWAY SLOPE = 2 PERCENT (UPHILL) ACCELERATE -STOP DISTANCE = 4,900 FEET
OBTAIN:
NOTE
I l
1
MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4E-2.
l
GROSS
WEIGHT 6
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
WITH
m)
I
- STOP ANTI-ICE ENGINE
(1495
DISTANCE ON.
ANTI-ICE
ON
BY
2
IS 5’JC.
(1000 kg) 5 IO
9
OAT (OC)
GROSS
WEIGHT
(1,000
FIGURE FAA APPROVED: NOV 07/90 REVISED: NOV 18/97
POUNDS)
WIND
(KNOTS)
RUNWAY SLOPE (PERCENT)
4E-4
PERFORMANCE
4E-5 4AC
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
DISTANCE
TO 35 FOOT
ENGINE 0
HEIGHT
ANTI-ICE METERS 200
100
- WET
EFFECTS 300
400
8,000
F
6,000 9,000 (4090) 10,000 (4540) 11,000(5900) 12,000 (5440) 13,000 (5900) 14,000 (6350) 14,500 (6580)
!
LLI F3 a
4,000
0
1,000 (FEET) IN TAKEOFF DISTANCE ENGINE ANTI-ICE ON
500 INCREASE WITH
FIGURE 4E-6 4AC
1,500
4E-5
PERFORMANCE
FAA APPROVED:
NOV 07/90
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
ASSOCIATED
DISTANCE
TO 35 FOOT
HEIGHT
CONDITIONS:
- WET
EXAMPLE:
POWER . . .. . . . .. . .. .. . .. . .. . .. . . . .. . TAKEOFF (WET) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . .. . .. . .. . . . .. .. . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . . . . OFF (SEE GRAPH) RUNWAY . . . . . . . . . . . . . . . . DRY, HARD SURFACE V, SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4815 V2 SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4515 FLAPS . . . . . . . . . . . . .. . .. .. . . . . .. .. . . . . . . . . . .. . . . . . . . . . . . . . . . . . l/4 NOSE WHEEL STEERING . . ..ON OR OFF
GIVEN:
OAT = 30°C PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 TAILWIND = 4 KNOTS RUNWAY SLOPE = 2 PERCENT(DOWNHILL) V1 SPEED = 102 KIAS V2 SPEED = 111 KIAS TAKEOFF DISTANCE = 5,000 FEET (1525
OBTAIN:
kg)
m)
NOTE MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
FOR TAKEOFF FIELD LENGTH ENGINE TAKEOFF DISTANCES ENGINE TAKEOFF DISTANCES
EXCEED 4E-2.
GROSS
WEIGHT 6
(1000 5
DETERMINATION, SINGLE ARE LONGER THAN TWO FACTORED BY 1.15.
kg) 13
12
11
10
9
6
7
6
5
4
3
2
1
-20
0
20 OAT (OC)
40
60
15 GROSS
FIGURE APPROVED:
NOV 07/90
14
13 WEIGHT
12
11
(1.000
10 POUNDS)
9
0
10
WIND
20 (KNOTS)
30
0
1
2
RUNWAY SLOPE (PERCENT)
4E-5 (continued)
PERFORMANCE
4E-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 4E-5 and 4E-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 4E-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 or 4E-6). Figure 4E-6 provides climb performance when Wet Takeoff Power is maintained during the climb. Note that if the V2 climb is to be conducted with Dry, Bleed Air Off Power (Figure 4D-6), the minimum required AWI fluid quantity is eight gallons when operating from airfield elevations up to 8,000 feet pressure altitude. Improved single engine climb performance and obstacle clearance can be achieved by using Wet Takeoff Power (five minute limit) during V2 climb. However, additional AWI fluid must be aboard in order to maintain Wet Takeoff Power during the climb. Figure 4E-6 presents the Single Engine Climb Gradient when using Wet Takeoff Power at V2 speed. Figure 4E-6 also shows the amount of AWI fluid which must be available before takeoff at various weight and altitude conditions in order to ensure ability to maintain Wet Power to 1,500 feet above the airport and through the level acceleration to VYSE.
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
ACCELERATE TO VYSE AND RETRACT FLAPS
VYSE
V2
LIFTOFF V1 SINGLE ENGINE TAKEOFF FLIGHT PATH TO 35 FOOT HEIGHT (FIGURE 4D–5)
4E-8 4AC
MAINTAIN V2 CLIMB WITH 1/4 FLAPS AND GEAR RETRACTED UNTIL OBSTACLE IS CLEARED
OBSTACLE CLEARANCE BUT NOT LESS THAN 400 FEET
V2 35 FT. SINGLE ENGINE CLIMB GRADIENT AT V2 (FIGURE 4D–6 OR 4E–6)
PERFORMANCE
SINGLE ENGINE CLIMB AT VYSE (FIGURE 4F–3)
FAA APPROVED: NOV 07/90
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) EXAMPLE: Given:
OAT = 20oC AIRFIELD PRESSURE ALTITUDE = 1,400 FEET GROSS WEIGHT = 12,900 POUNDS (5850 kg) WET POWER TAKEOFF AND V2 CLIMB
BLEED AIR OFF ENGINE ANTI-ICE OFF 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 = 4,000 FEET (1220 m) (FIGURE 4E-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 = 6.7 PERCENT (FIGURE 4E-6) d. DISTANCE =
(100) x (1,500 – 35) = 21,866 FEET (6665 m) 6.7
(3) TOTAL FLIGHT PATH DISTANCE = (1) + (2) = 25,866 FEET (7885 m) (4) MINIMUM AWI FLUID REQUIRED = 10.2 U.S. GALLONS (38.6 LITERS) (FIGURE 4E-6)
FAA APPROVED: NOV 07/90 REVISED: NOV 18/97
PERFORMANCE
4E-9 4AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4E-10 4AC
PERFORMANCE
FAA MANUFACTURER'S APPROVED: NOV DATA 07/90 ISSUED: NOV 07/90
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) Figures 4E-5 and 4E-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 On). • 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 – Wet 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 4E-2) and the flight paths constructed from Figures 4E-5 and 4D-6 or 4E-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
4E-11 4AC
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE SINGLE ENGINE CLIMB GRADIENT
TO 1500 FOOT AT V, - WET
HEIGHT
(continued)
MINIMUM AWI FLUID QUANTITY FOR WET CONTINUED WET V2 CLIMB TO OBSTACLE AND
ACCELERATION
TAKEOFF, HEIGHT,
TO VYSE. OBS;gLE
HEIGHT
(METE;5;) 290
70
50
S.L.
2,000 AIRPORT
4,000 PRESSURE
6,000 ALTITUDE
6,000
1,500
FIGURE 4E-12 4AC
1300 OBSTACLE
(FEET)
1,100 HEIGHT
900
700
500
(FEET)
4E-6
PERFORMANCE
FAA APPROVED:
NOV 07/90
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE SINGLE ENGINE CLIMB GRADIENT ASSOCIATED
TO 1500 FOOT AT V2 -WET
CONDITIONS:
.
REDUCE CLIMB GRADIENT BY 1.0 PERCENT WITH ENGINE ANT!-ICE ON.
-
MAXIMUM
.
FOR FLIGHT PATH DETERMINATION GRADIENT BY 0.8 PERCENT GRADIENT.
ENGINE
ANTLICE
(continued)
EXAMPLE:
POWER . . . . . . . TAKEOFF (WET) PROPELLER . . . . . . . . FEATHERED ON INOPERATIVE ENGINE GEN LOAD . . . . . . . . . . . . . . . xx) AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . OFF (SEE NOTE) V2 SPEED _..___..._._..__..FIGURE 48-15 GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . l/4
OAT WITH
HEIGHT
GIVEN:
OBTAIN:
OAT - 0% PRESSURE ALTITUDE - 2.Mx) FEET GROSS WElGHT - 11.000 POUNDS (4990 kg) V2 SPEED - 103 KIAS MINIMUM AWI FLUID = 8.0 U.S. GALLONS (30.3 GROSS CLIME GRADIENT 11.6 PERCENT DECREASE (ANTI-ICE ON) -1 .O PERCENT GROSS CLIMB GRADIENT 10.6 PERCENT FLIGHT PATH DETERMINATION I -0.6 PERCENT NET CLIMB GRADIENT 9.6 PERCENT
LITERS)
GRADlENT
ON Is 5°C. I REDUCE
CLIMB I
-
DETER)INE FIGURE 4E-6.
I
YlNlWlJY
AWI
FLUID
QUANTITY
FROM
60
50
40
30
20
10
0
12
4
5
6 GROSS
7 CLIMB
NET CLIMB GRADIENT MINUS 0.6 PERCENT.
FIGURE FAA APPROVED:
NOV 07/90
9
10
GRADIENT (PERCENT) NOTE EOUALS GROSS CLIMB
6
GRADIENT
11
12
13
4E-6 (continued)
PERFORMANCE
4E-13 4AC
METRO III - ICAO ANNEX 8 TWO ENGINE
RATE
ASSOCIATED
OF CLIMB
AT V, -WET EXAMPLE:
CONDITIONS:
GIVEN:
POWER ..................... TAKEOFF (WET) GEN LOAD ........................ ,200 AMPS BLEED AIR .................................... OFF ENG ANTI-ICE ....... OFF (SEE NOTE) V35 SPEED ................. FIGURE 48-15 GEAR ................................................ UP FLAPS ............................................... l/4
OBTAIN:
I
OAT I 0% PRESSURE ALTITUDE - 6.ooO FEET GROSS WElGHT I ll.MM POUNDS (4990 lq) 155 SPEED - 112 KIAS RATE OF CLIMB 3,760 FEET PER MINUTE DECREASE (ANTI-ICE ON) I -340 FEET PER MINUTE NET RATE OF CLIMB I 3.420 FEET PER MINUTE
NOTE * REDUCE RATE OF CLIMB BY 340 FEET PER MINUTE WITH ENGINE ANTCICE ON. . MAXIMUM
OAT WITH
(FEET
MINUTE)
ENGINE
ANTCICE
ON IS 5°C.
I
60
50
40
10
0
-10
15
RATE
OF CLIMB
PER
FIGURE 4E-7 4E-14 4AC
PERFORMANCE
FAA APPROVED: NOV 07/90