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 Takeoff Speed Schedules .................................................................................................................. 4D-4 Distance to Accelerate to V1 and Stop ............................................................................................. 4D-11 Single Engine Takeoff Distance to 35 Foot Height .......................................................................... 4D-12 Takeoff Flight Path Distance to 1500 Foot Height ........................................................................... 4D-14 Second Segment Climb Gradient ............................................................................................ 4D-18 Close In Obstacle Clearance .................................................................................................. 4D-19 Second Segment Acceleration Distance ................................................................................. 4D-20 Third Segment Climb Gradient ................................................................................................ 4D-22 Distant Obstacle Clearance .................................................................................................... 4D-23 Single Engine Takeoff Run Distance ............................................................................................... 4D-24 Two Engine Rate of Climb at V50. .................................................................................................... 4D-26
FAA APPROVED: MAY 22/89 REVISED: MAR 18/92
PERFORMANCE
4D-i 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-ii 8AC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
TAKEOFF
POWER
ASSOCIATED
CHECK
CHART
- DRY, BLEED
AIR OFF
EXAMPLE:
CONDITIONS:
GIVEN:
OAT = -5°C PRESSURE ALTITUDE = 3,000 FEET ENGINE ANTI-ICE SYSTEM - ON OBTAIN: ENGINE TORQUE = 92.2 PERCENT
POWER .. ........ ... TAKEOFF (DRY) RPM ................. .... ................. 100% MAX ALLOWABLE EGT ....65O”C GEN LOAD ... .............. 300 AMPS BLEED AIR . ..... ................... ... OFF ENG ANTI-ICE ...... .. SEE GRAPH SPEED ...................... ........ STATIC
l
MAXIMUM
OAT WITH ENGINE ANTI-ICE ON IS 5°C.
REFERENCE EGT IS THE EGT OBTAINED WHEN REQUIRED ENGINE TORQUE IS SET IN ACCORDANCE WITH THIS ,. 650°C.
L
80
60
40
-30
-20
-10
0
10 OAT (OC)
20
30
40
50
OFF ENGINE ANTI-ICE SYSTEM
ON
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-2 8AC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
METRO III -lCAO MAXIMUM
TAKEOFF
ASSOCIATED
WEIGHT
LIMITATION
CHART
ANNEX 8
- DRY, BLEED
CONDITIONS:
AIR OFF NOTE
POWER . . .. . . . . . . .. .._.............. TAKEOFF (DRY) GEN LOAD . . .. . . . . . . . .. . . . . . . .. . .. . . . . . . .. . 300 AMPS BLEED AIR . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) GEAR . . .. . . . . . . .. . . . . . . .. . .. . . . .. DOWN (TAKEOFF) UP (SECOND AND THIRD SEGMENT) FLAPS... . . . . . . . . . . . . . . . . . . .. . . . . . . .. . . . l/4 (TAKEOFF) UP (ENROUTE)
l
l
l
REDUCE TAKEOFF WEIGHT WITH ENGINE ANTI-ICE ON. MAXIMUM
OAT
WITH
ENGINE
BY
1,100
ANTI-ICE
POUNDS
ON
(500
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, .
EXAMPLE: GIVEN: OBTAIN:
OAT = 26% PRESSURE ALTITUDE = 5,500 FEET TAKEOFF WEIGHT = 12,650 POUNDS
(5740
kg) 17
16
7
10
FIGURE FAA APPROVED:
MAY 22l89
4D-2
PERFORMANCE
4D-3 8AC
-
ob-Jolnomo~offlolno 0000000000000 Lolnlns~mmcunJ~-oo ------.-a------
vi
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FAA APPROVED: MAY 22189
0000000000000 olnomomomomoulo cDmuJSSmmNN--oO .e-d-dd+de.+e-e
ANNEX 8
omoLnolnolnoLnou7o 0000000000000 rnlrJmSSmmNN~~00 -4~--d-.-l~~d~d
METRO III -ICAO
f,ij 0 SL W-Ii=
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FtGURE 4D-3 PERFORMANCE
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METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-6 8AC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
k 0 a z
FAA APPROVED:
FIGURE
4D-3 (continued)
METRO III -lCAO
MAY 22l89
PERFORMANCE
ANNEX 8
4D-7 8AC
4D-8 8AC
wwz rrp
METRO III -lCAO
FIGURE 4D-3 (continued) PERFORMANCE
ANNEX 8
FAA APPROVED: MAY 22189
00 x W z z
a 0 a c)
811 LII L.11
011 601 601
601 601 601
001 001 001
611 611 611 811 811 811 LlI LII
011 601 601 601 601 601 601 011
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TAKEOFF
SPEED
SCHEDULE
0
(KIAS)
- DRY, BLEED
AIR OFF -1
[KILOGRAMS1
CAUTION
IPRESS
RLT IFTI
T I iRQSS WT IKG 1
7257 7000 6800 6600 6'400 6200 6000
6000
t-
OUTSIDE
V,
110 108 107 106
- -30 -vi 117 j&l
117 1111 112 110 i-m 105 103 101 100 100 101 101 102
5600~100
103
"50 119
112
110 1011 107 103 105 101 103 100 100 100 w 101 102 103 -
7000
I
L
118 116 115 113 112 110 +E 111 112 i-n 116 -118 119 118 116 115 113 112 110 109 109 110 112 113 u 117
vl
129
110
129 127 126 125 123 122 121 120 121 122 12u 126 128 130
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8000
5200~100
5000 4800 11600
t
101 101 102
115 113 111 108 106 104 101 101 i-m 100 !cJ 101 102 -
i-m 128 118 116 ii-5 113 m 110 109
-
127
126 121 123 122 121 120 120 B 121 110 122 112 121 1111 126 116 129
110 108 107 106 1011 103 101 100 100 100 100 100 100 100
0
I
-
RIR
I
REFER
TO FIGURE
4D-2
TEMPERRTURE 10
FOR MAXIMUM
TAKEOFF
WEIGHTS.
[‘Cl ED
I
PERMISSIBLE
40
I
I
zm
55
VP Vi
11s 127 108 11E 11Y 126 107 125 106 111 1211 1011 105 122 103 107 121 101 105 120 100 102 121 100 102 123 100 101 125 100 100 127 100 100 129 101 101 131 101 101 -
i-m
-10
-
1
* TAKEOFF IN TEMPERATURE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID, STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHARTARE PROVIDED FOR INTERPOLATION ONLY.
-
-I 31[1 0
11c 11E 11E 11: 11: i-i? 11c j&s 1oc 10s 10s i-it 112 Jl-Y
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119 120 120
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109
118
108
110
119
109
100
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112
120
119 -119 119
JO1 100 100 100
109 107 107 106
110 109 109 109
119 118 119 119
100 100 100
109 108 108
120 -120 120 121
100 100 100 100
105 105 1OY 103
109 109 109 110
119 120 120 120
100 100 100 100
107 106~109~119~100~109~109~117~ 106~109~119~100i109~10911181 1 I I !
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-
METRO III -ICAO DISTANCE
TO ACCELERATE
ASSOCIATED
TO V, AND STOP
ANNEX 8
- DRY, BLEED
CONDITIONS:
AIR OFF
EXAMPLE:
POWER . . .. . . . .. . . . . . . .. . . . . . . .. . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) RUNWAY . . . . . . . . . . . . . . . DRY, HARD SURFACE FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . II4 DECISION SPEED .. . . . . V1 (FIGURE 4D-3) NOSE WHEEL STEERING . ..ON OR OFF
GIVEN:
OBTAIN:
l
MAXIMUM TAKEOFF WEIGH+ MAY NOT THE WEIGHT DETERMINED FROM FIGURE
OAT = 15°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 15,000 POUNDS (6605 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V1 SPEED = 107 KIAS ACCELERATE - STOP DISTANCE = 4.100 FEET (1250 m)
EXCEED 4D-2.
l
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
WITH
- STOP ANTI-ICE ENGINE
DISTANCE ON.
BY 3.3
ANTI-ICE
ON
30
0
IS5”C.
5
GROSS 7
-40
-20
0
20
OAT (OC)
40
60
16 GROSS
FIGURE FAA APPROVED:
MAY 22189
15
WEIGHT 6
14 WEIGHT
13
(1000
12 (1,000
kg) 5
11 POUNDS)
10
0 WIND
10
20 (KNOTS)
1
2
RUNWAY SLOPE (PERCENT)
4D-4
PERFORMANCE
4D-11 8AC
METRO SINGLE
ENGINE
TAKEOFF
III -ICAO
DISTANCE
TO 35 FOOT
ANNEX HEIGHT
- DRY, BLEED
8 AIR OFF
ENGINE ANTI-ICE EFFECTS 0
50
100
(METERS) 150
200
250
300
8,000
6,000
i= 5.000
4 .,ooo
0
200
400
600
800
I 1,000
(FEET) INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4D-12 8AC
4D-5
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO Ill -lCAO SINGLE
ENGINE ASSOCIATED
TAKEOFF
DISTANCE
TO 35 FOOT
CONDITIONS:
ANNEX 8
HEIGHT
- DRY,
BLEED
AIR OFF
EXAMPLE:
POWER .. ........ ................... TAKEOFF (DRY) GEN LOAD ...... .... .... ... ................ 300 AMPS BLEED AIR ...... ........ ... .. ...... .................. . OFF ENG ANTI-ICE ............ OFF (SEE GRAPH) RUNWAY ............... DRY, HARD SURFACE V , SPEED .. ........ ..... .. .... .... ... FIGURE 4D-3 V R SPEED ................. ...... ... .. FIGURE 4D-3 V 2 SPEED ............................ FIGURE 4D-3 FLAPS .. .. ...._..............................................114 NOSE WHEEL STEERING ...ON OR OFF
OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) OBTAIN: V1 SPEED = 107 KIAS VR SPEED = 113 KIAS V2 SPEED = 116 KIAS TAKEOFF DISTANCE = 7,250 FEET (2210 m)
MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FlGURE4D-2.
FOR TAKEOFF FIELD LENGTH DETERMINATION, SINGLE ENGINE TAKEOFF DISTANCES ARE LONGER THAN TWO ENGINE TAKEOFF DISTANCES FACTORED BY 1 .15.
GIVEN:
NOTE
GROSS
WEIGHT
7
(1000
6
kg) 5. 12
11
OAT (OC)
GROSS
WEIGHT
(1,000
POUNDS)
WIND
(KNOTS)
RUNWAY SLOPE (PERCENT)
FIGURE 4D-5 (continued) FAA APPROVED: MAY 22f89
PERFORMANCE
4D-13 8AC
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF
TWO ENGINE TAKEOFF WITH ENGINE FAILURE RECOGNIZED AT V 1 , FLAPS 1/4
AFTER TAKEOFF, GEAR IS RETRACTED
MAINTAIN V 2 CLIMB TO 400 FEET WITH 1/4 FLAPS
ACCELERATE TO V YSE YSE , RETRACT FLAPS AT V 22 +5 KNOTS AND FEATHER INOPERATIVE PROPELLER
VYSE
V2
400 FT
V2 VR
SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4D-5)
REDUCE POWER TO MCP AND CONTINUE CLIMB TO 1,500 FEET
END OF FLIGHT PATH
START OF TAKEOFF ROLL
An estimate of the horizontal distance required to clear an obstacle up to 1,500 feet above the runway, or the required climb gradient to clear an obstacle along the takeoff flight path, may be obtained by using Figures 4D-5 through 4D-10. The takeoff flight path is as follows:
1,500 FEET
35 FT SECOND SEGMENT CLIMB (FIGURES 4D-6 AND 4D-7)
SECOND SEGMENT ACCELERATION (FIGURE 4D-8)
THIRD SEGMENT CLIMB (FIGURES 4D-9 AND 4D-10)
The takeoff flight path consists of four phases defined as follows: 1. SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4D-5). Both engines are assumed to operate normally to speed V1 where one engine is recognized as failed and the takeoff is continued on one engine. This phase ends when the airplane reaches 35 feet above the runway surface at V2. 2. SECOND SEGMENT CLIMB (FIGURES 4D-6 and 4D-7). The second segment climb is a constant V2 climb starting at a height of 35 feet above the runway surface and ends at a height of 400 feet above the runway. The landing gear is fully retracted at the start of this phase, flaps remain at 1/4, and the propeller on the inoperative engine is windmilling in the NTS mode. Figures 4D-6 and 4D-7 present net climb gradient.
4D-14 8AC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF (continued) 3. SECOND SEGMENT ACCELERATION (FIGURE 4D-8). This phase is an acceleration at 400 feet height from V2 to VYSE. The flaps are retracted at V2 +5 knots, the propeller on the inoperative engine is feathered, and takeoff power is maintained until VYSE is obtained. 4. THIRD SEGMENT CLIMB (FIGURE 4D-9 and 4D-10). The third segment climb is at VYSE with maximum continuous power set. It starts at 400 feet and is completed at 1500 feet above the runway surface. Figures 4D-9 and 4D-10 present net climb gradient. The following are three examples to illustrate the use of the flight path data charts. EXAMPLE 1 – DETERMINATION OF TOTAL DISTANCE TO 1500 FEET Given:
OAT = 10°C Airport Pressure Altitude = 2,000 feet Gross Weight = 15,000 pounds (6805 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4D-5) = 7,250 feet (2210 meters). 2. Second Segment Climb Gradient (Figure 4D-6) = 3.1%. 3. Enter Figure 4D-7 at 400 feet and proceed to 3.1%. Obtain 11,800 feet (3600 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4D-8) = 7,600 feet (2315 meters) to accelerate from V2 to VYSE. 5. Third Segment Climb Gradient (Figure 4D-9) = 3.3%. 6. Enter Figure 4D-10 at 1500 feet and proceed to 3.3%. Obtain 33,500 feet (10210 meters) to climb from 400 feet to 1500 feet. 7. Total Distance is: 7,250 feet (2210 11,800 feet (3600 7,600 feet (2315 33,500 feet (10210 60,150 feet (18335
FAA APPROVED: MAY 22/89
meters) to 35 feet meters) to 400 feet meters) to accelerate to VYSE meters) to 1500 feet meters) (9.90 nautical miles)
PERFORMANCE
4D-15 8AC
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF (continued) EXAMPLE 2 – CLOSE IN OBSTACLE CLEARANCE Given:
OAT = 10°C Airport Pressure Altitude = 2,000 feet Gross Weight = 15,000 pounds (6805 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 350 feet* (107 meters) Obstacle Distance From Brake Release = 21,250 feet (6475 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4D-5) = 7,250 feet (2210 meters). 2. Obstacle horizontal distance from the 35 foot height point equals the total obstacle distance minus the distance to 35 feet height. 21,250 – 7,250 = 14,000 feet (4265 meters). 3. Second Segment Climb Gradient (Figure 4D-6) = 3.1%. 4. To obtain the required climb gradient to clear the close in obstacle, enter Figure 4D-7 at 350 feet* and at 14,000 feet distance. Obtain required climb gradient of 2.25%. 5. Since the required gradient, 2.25%, is less than the actual gradient, 3.1%, this obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 350 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4D-7.
4D-16 8AC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF (continued) EXAMPLE 3 – DISTANT OBSTACLE CLEARANCE Given:
OAT = 10°C Airport Pressure Altitude = 2000 feet Gross Weight = 15,000 pounds (6805 kg) Headwind = 20 knots Runway slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 700 feet* (213 meters) Obstacle Distance from Brake Release = 41,650 feet (12695 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4D-5) = 7,250 feet (2210 meters). 2. Second Segment Climb Gradient (Figure 4D-6) = 3.1%. 3. Enter Figure 4D-7 at 400 feet and proceed to 3.1%. Obtain 11,800 feet (3600 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4D-8) = 7,600 feet (2315 meters) to accelerate from V2 to VYSE. 5. The horizontal distance from the end of the second segment acceleration to the obstacle equals 41,650 – 7,250 – 11,800 – 7,600 = 15,000 feet (4570 meters). 6. Enter Figure 4D-10 at 700 feet* height and 15,000 feet distance. Obtain required gradient of 2.0%. 7. The Third Segment Climb Gradient (Figure 4D-9) = 3.3%. 8. Since the required gradient, 2.0%, is less than the actual gradient of 3.3%, the obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 700 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4D-10.
FAA APPROVED: MAY 22/89
PERFORMANCE
4D-17 8AC
METRO III -lCAO TAKEOFF SECOND
-6
FLIGHT SEGMENT
-4
PATH DISTANCE TO 1500 FOOT HEIGHT (continued) CLIMB GRADIENT - DRY, BLEED AIR OFF
-2
0
2 NET CLIMB
4D-18 8AC
ANNEX 8
4 GRADIENT
6 (PERCENT)
FIGURE
4D-6
PERFORMANCE
0
10
12
FAA APPROVED:
14
MAY 22189
T ‘AKEOFF FLIGHT PATH DISTANCE C:LOSE IN OBSTACLE CLEARANCE ASSOCIATED
TO 1500 FOOT HEIGHT - DRY, BLEED AIR OFF EXAMPLE:
CONDITIONS:
POWER .. .... ................ TAKEOFF (DRY) GEN LOAD .. .. ...... ..... .......... 300 AMPS BLEED AIR .. ..................................... ON ENG ANTI-ICE ... .. ...... ... ON OR OFF CLIMB SPEED......V2 (FIGURE 4D-3) GEAR ...... .. . . ................... .... .. .. .... .... . UP FLAPS .. ......................... ... ... .. ... ..... . . l/4
GIVEN:
OBSTACLE HEIGHT ABOVE THE RUNWAY SURFACE OBSTACLE HORIZONTAL DISTANCE FROM 35 FOOT POINT = 14,000 FEET (4265 m) OBTAIN: REQUIRED GRADIENT = 2.25 PERCENT
HORIZONTAL 500
0
(continued)
1000
DISTANCE
1500
FROM
35 FOOT
HEIGHT
2500
2000
POINT
= 350 FEET (107 m)
(METERS)
3000
3500
4000
4500
400
350
300
60 250
200
60
150
100
50
n “0
2,000
I 0
I 0.2
I
4,000
I 0.4
I
I 0.6
6,000 HORIZONTAL
I
I 0.6
I
6,000 FROM
DISTANCE
I
I
I
1 .o 1.2 HORIZONTAL DISTANCE
35 FOOT
I
HEIGHT
10,000 POINT
I
I
1.4 (NAUTICAL
1.6 MILES)
14,000
12,000
16,00C
(FEET)
I 1.6
I
I 2.0
I
I 2.2
I
I 2.4
I 2.6
METRO III -LAO TAKEOFF SECOND
FLIGHT SEGMENT
PATH DISTANCE ACCELERATION MAXIMUM
ANNEX 8
TO 1500 FOOT HEIGHT (continued) DISTANCE - DRY, BLEED AIR OFF OAT WITH ENGINE
NOTE ENGINE
ANTI-ICE
ANTI-ICE
EFFECTS
ON IS 5°C.
(METERS) 490
690
890
lOQ0
12po
1490
8,000:'
6,000
B
0
4,000 3,000 (FEET) INCREASE IN ACCELERATION DISTANCE WITH ENGINE ANTI-ICE ON
1,000
2,000
FIGURE 4D-20 8AC
5,000
4D-8
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III -ICAO ANNEX 8 TAKEOFF
FLIGHT
PATH
DISTANCE
ASSOCIATED
HEIGHT (continued) DISTANCE - DRY, BLEED AIR OFF
TO 1500 FOOT
SECOND SEGMENT ACCELERATION CONDITIONS:
EXAMPLE:
POWER .. .... ....................... TAKEOFF (DRY) GEN LOAD ................................. 300 AMPS BLEED AIR ...... .... .... ....... ...... .. ... .. .. .... .... OFF ENG ANTI-ICE .. .... .... ..OFF (SEE GRAPH) ACCELERATE TO V YSE .. ... FIGURE 4F-2 GEAR ........................................................ UP FLAPS .............. ... .. ...... .... .. l/4 (SEE NOTE)
GIVEN:
AIRPORT OAT = 10°C AIRPORT PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 20 KNOTS OBTAIN: VYSE CLIMB SPEED = 133 KIAS SECOND SEGMENT ACCELERATION DISTANCE = 7,600 FEET (2315 m)
NOTE ACCELERATE. TO THE LESSER OF V2 +5 KIAS OR VYSE PRIOR TO RAISING FLAPS.
7000
GROSS 6500
WEIGHT 6000
(KILOGRAMS) 5500
5000
11
IO
3
-20
0 AIRPORT
20 OAT (OC)
40
60
16.000
15,000
14.000 GROSS
13,000 WEIGHT
12,000 ( POUNDS)
11,000
10,000
0 WIND
10
20
30
(KNOTS)
FIGURE 4D-8 (continued) FAA APPROVED: MAY 22189
PERFORMANCE
4D-21 8AC
METRO III -lCAO
ANNEX 8
TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) THIRD SEGMENT CLIMB GRADIENT - DRY, BLEED AIR OFF 60
ASSOC!ATED
CONDITIONS:
POWER .... .... .... .... .. MAX CONTINUOUS GEN LOAD ... ... ...... .... .... ... .... . 300 AMPS BLEED AIR . .... .... ..... ... .... ... .... ..... .... .. OFF ENG ANTI-ICE . ... .... .. OFF (SEE NOTE) CLIMB SPEED....VYSE (FIGURE 4F-2) GEAR .. .... ...... ... .... .... ... ..... ... .... ..... .. ...... UP FLAPS . ... ..... .... .... .... ... .... ...... .. ..... .. ..... . UP EXAMPLE: GIVEN:
OBTAIN:
II
AIRPORT OAT - 10% AIRFORT PRESSURE ALTITUDE = 2.01X FEET GROSS WEIGHT - 15,000 POUNDS (6605 kg) HEADWIND - 20 KNOTS VYSE CLIMB SPEED I 133 KIAS THIRD SEGMENT CLIMB GRADIENT - 3.3 PERCENT
* REDUCE CLIMB GRADIENT BY 1.7 PERCENT WITH ENGINE ANTCICE ON. . MAXIMUM
OAT WITH ENGINE
ANTCICE
GRADIENT
ON IS 5%.
16 7 15
6
-4
-2
0
2
4 NET CLIMB
6 GRADIENT
6 (PERCENT)
10
12
14
16
FIGURE 4D-9 4D-22 8AC
PERFORMANCE
FAA APPROVED: MAY 22189
I 1
TAKEOFF DISTANT
FLIGHT PATH DISTANCE OBSTACLE CLEARANCE
ASSOCIATED
TO 1500 FOOT HEIGHT - DRY, BLEED AIR OFF
CONDITIONS:
EXAMPLE:
POWER ...................... MAX CONTINUOUS GEN LOAD ...............................,300 AMPS BLEED AIR ..........................................OFF ENG ANTI-ICE ......................ON OR OFF CLIMB SPEED.. ...... VYSE (FIGURE 4F-2) GEAR ......................................................UP FLAPS .....................................................UP HORIZONTAL 0
2500
(continued)
5000
DISTANCE 7500
GIVEN:
OBSTACLE OBSTACLE SECOND OBTAIN: REQUIRED
FROM END OF SECOND SEGMENT 10000 12500
HEIGHT ABOVE THE RUNWAY SURFACE = 700 FEET (213 m) HORIZONTAL DISTANCE FROM END OF SEGMENT ACCELERATION = 15,000 FEET (4570 m) GRADIENT = 2.0 PERCENT
ACCELERATION
POINT (METERS)
15000
17500
2oow
1,500
1,400
1,300
c)
D 0 D 2 z m x 00
,
HORIZONTAL
ad RQ _..
I 0
..
I 1
I 2
-- -- -.-- .-.-
I 3
DISTANCE
I 4
FROM END OF SECOND SEGMENT
I 5 HORIZONTAL
I
I
6 7 DISTANCE (NAUTICAL
ACCELEPATION
I 6 MILES)
“,““”
--,---
POINT (FEETI
I
I
I
I
I
9
10
11
12
13
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
RUN DISTANCE
I
MAXIMUM
0
- DRY, BLEED
AIR OFF
NoTE------l
OAT WITH ENGINE
ANTI-ICE
ON IS 5°C.
ENGINE ANTI-ICE EFFECTS (METERS) 50 100 150
200
6,000
S.L. 0
200
400
600
800
(FEET) INCREASE IN TAKEOFF RUN DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4D-24 8AC
4D-11
PERFORMANCE
FAA APPROVED: MAY 22189 REVISED: MAR 18/92
METRO III - ICAO ANNEX 8 SINGLE
ENGINE ASSOCIATED
TAKEOFF
RUN DISTANCE
- DRY, BLEED
CONDITIONS:
AIR OFF
EXAMPLE:
POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD .. .. . . . . .. .. . . . . .. . . . .. . . . . . . . . . . . 300 AMPS BLEED AIR .. .. . . . . .. .. . . . . . . .. . .. . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . .. . . . . OFF (SEE GRAPH) RUNWAY . . . . . . . . . . . .. . .. DRY, HARD SURFACE V 1 SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . .. FIGURE 4D-3 VR SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4D-3 V2 SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4D-3 FLAPS . . . . . . . . . . . . . . . .. . . . . . . .. . .. . .. . . . .. . .. . . . . . . . . . . . . . . . . 114 NOSE WHEEL STEERING . . ..ON OR OFF
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
GIVEN:
OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 15,000 POUNDS (6605 HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V1 SPEED = 107KlAS V R SPEED = 113 KIAS V 2 SPEED = 116 KIAS TAKEOFF RUN = 6,100 FEET (1660 m)
OBTAIN:
kg)
EXCEED 4D-2. GROSS
WEIGHT
7
(1000
6
kg) 5 12
11
10 3
1 3
OAT (OC)
GROSS
WEIGHT
(1,000
POUNDS)
WIND
(KNOTS)
RUNWAY SLOPE (PERCENT)
FIGURE 4D-11 (continued) FAA APPROVED: MAR 18/92
PERFORMANCE
4D-25 8AC
METRO III - ICAO ANNEX 8 TWO ENGINE
RATE
OF CLIMB
AT V,, - DRY, BLEED
AIR OFF NOTE . REDUCE RATE OF CLIMB BY 465 WITH ENGINE ANTI-ICE ON.
EXAMPLE: POWER .................... MAX CONTINUOUS GEN LOAD ............................ .300 AMPS RI FED AIR ........................................ OFF ........... OFF (SEE NOTE) ENG ANTI-ICE CLIN1B SPEED.. .. ..V, (FIGURE 4D3) UP GEAR .................................................... FLAPS ................................................... 114
-----
GIVEN:
....
600
OBTAIN:
800
OAT = 12% PRESSURE ALTITUDE - 5,000 FEET (6305 Q) GROSS WEIGHT - 13.900 POUNDS Vm CLIMB SPEED - 122 KIAS RATE OF CLIMB = 1,960 FEET PER MINUTE
1,000
1,200 RATE
I
4D-26 8AC
1,400 OF CLIMB
1,600 (FEET
FIGURE
1,800
I
2,000
. MAXIMUM
2,200
OAT WITH
2,400
ENGINE
FEET
ANTI-ICE
2,600
PER
MINUTE
ON IS 5-C.
I
2.800
PER MINUTE)
4D-12
PERFORMANCE
FAA APPROVED:
MAR 18192