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 B.F. Goodrich Single Rotor Brakes ......................................................................................... 4D-12 Goodyear Aerospace Dual Rotor Brakes ................................................................................ 4D-13 Single Engine Takeoff Distance to 35 Foot Height .......................................................................... 4D-14 Takeoff Flight Path Distance to 1500 Foot Height ........................................................................... 4D-16 Second Segment Climb Gradient ............................................................................................ 4D-20 Close In Obstacle Clearance .................................................................................................. 4D-21 Second Segment Acceleration Distance ................................................................................. 4D-22 Third Segment Climb Gradient ................................................................................................ 4D-24 Distant Obstacle Clearance .................................................................................................... 4D-25 Two Engine Rate of Climb at V50. .................................................................................................... 4D-26
FAA APPROVED: MAY 22/89
PERFORMANCE
4D-i 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-ii 4MC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
TAKEOFF POWER CHECK CHART - DRY, BLEED AIR OFF ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER ............. TAKEOFF (DRY) RPM ...................................... 100% MAX ALLOWABLE EGT ....650% GEN LOAD .. ............... 300 AMPS BLEED AIR ..,.........................OFF ENG ANTI-ICE ........ SEE GRAPH SPEED .. .................. ........ ..STATIC
GIVEN:
OAT = -5°C PRESSURE ALTITUDE = 3,000 FEET ENGINE ANTI-ICE SYSTEM - ON OBTAIN: ENGINE TOROUE = 92.2 PERCENT
110
100
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 4MC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
METRO III - ICAO ANNEX 8 MAXIMUM
TAKEOFF
ASSOCIATED
WEIGHT
LIMITATION
CHART
- DRY, BLEED
AIR OFF
CONDITIONS: 1,010
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
MAXIMUM
OAT
WITH
ENGINE
ANTI-ICE
POUNDS
ON
(460
kg)
IS 5°C.
THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE VI.
EXAMPLE: GIVEN: OBTAIN:
.OAT = 26°C PRESSURE ALTITUDE = 5,500 FEET TAKEOFF WEIGHT = 12,650 POUNDS
(5740
kg)
16
FIGURE FAA APPROVED:
MAY 22/89
4D-2
PERFORMANCE
4D-3 4MC
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR OFF pziiz-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 CHART ARE PROVIDED FOR INTERPOLATION - REFER TO FIGURE
I
I
““TS’nr
n’R
TEMPERATURE
4lh2
FOR MAXIMUM
PERMISSISLE
S.L.
1’4500 111000 13500 13000 12500 12000 11500 11000 10500 10000
1 000
T
105 1011 102 101 101 102 102 103 103 103 I
108 105 102 101 101 102 102 103 103 103
11U 113 111 111 112 1111 116 118 120 121
125 121 123 123 125 127 129 132 1311 136 --
I 10000 I103 I103 I121 I135
105 IOU 102 101 100 101 102 103 103 103
108 105 103 101 100 101 102 103 103 103
1111 113 111 110 111 113 115 117 119 120
125 12Y 122 122 123 125 127 130 132 13’4 -
105 1011 102 101 100 101 101 102 103 103
109 106 103 101 100 101 101 102 103 103
1111 113 111 110 110 112 11Y 116 116 120
125 1211 122 121 122 1211 126 129 132 13U
105 1011 102 101 100 100 100 101 102 103
110 107 105 102 100 100 100 101 102 103
11U 113 .__
125 123 _--
110 111 113 115 117 119 11’4 113 111 109 109 110 111 113 115 118
I
YO
122 123 126 128 131 133
105 111 1011 106 _____ --100 101 100 100 100 100 100 100 101 101 102 102
1lY 113 111 109 109 109 110 112 1111 116
121 123 122 120 120 121 122 1211 126 129
105 1OY 102 101 100 100 100 100 100 100
1lU 112 109 107 105 105 1011 103 102 101
11U 123 113 122 111 120 109 119 109 119 109 119 109 120 109 120 109121100 110 121
1211 123 122 121 120 122 123 126 126 131
105 1OY 102 101 100 100 100 100 100 101
1111 113 111 109 109 109 109 110 112 114
12U 123 121 120 120 120 121 122 12Y 126
105 1011 102 101 100 100 100 100 100 100
115 113 110 106 106 105 105 1011 103 102
1111 113 111 109 109 109 109
---I-l----------
112 109 106 1011 102 101 100 100 100 101
WEIGHTS.
I ‘Cl I
lU500 105 107 11U 125 105 108 1111 125 105 108 11U 125 105 109 111000 1OY 1011 113 12Y 1OY 105 113 1211 1011 105 113 l2Y 1011 106 ,13500,1021102i1121123110211021111112211021103111111221102110U1111112211021105 13000 101 101 111 123 101 101 111 122 1011101111011~2110i1101I1nsl171l1n1lin~ -12500 101 101 113 126 101 101 112 12Y 100 100 111 123 100 100 12000 102 102 115 128 101 101 1lU 126 101 101 113 125 100 100 11500 103 103 117 130 102 102 116 128 102 102 115 127 101 101 11000 103 103 119 132 103 103 118 131 102 102 117 130 102-102 10500 103 103 120 1311 103 103 119 133 103 103 119 132 103 103 10000 103 103 122 136 103 103 121 135 103 103 120 1311 103 103
TAKEOFF
55
102 101 100 100 100 100 100
111 109 108 108 107 106 105 IOU
111 109 109 109’ 109 109 109 110
119 118 118 18 :,9 119 120 120
123 121 120 119 119 119 119
IO1 100 loo 100
110 109 108 108
109 109 lo9 109
117 118 118 119
109
120
100
107
109
119
109 110
120 121
100 100
106 105
109 110
119 120
-
i
D z z
m x 00
FIGURE 4D-3 (continued) PERFORMANCE
METRO III - ICAO ANNEX 8
FAA APPROVED: MAY 22189
4D-5 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-6 4MC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
FIGURE 4D-3 (continued) PERFORMANCE
METRO III - ICAO ANNEX 8
FAA APPROVED: MAY 22189
4D-7 4MC
4D-8 4MC
f cn
-I
0000000000 ~0000000000 ~NOww~luOww lDwuJu-llnlnln3~ zw
4D-3 (continued)
z 0
00000000000 woooo 000000 “~~c$“~~co~~~ co In
t?i
=:
FAA APPROVED:
00000000000 woooooooooo LnSNoww~wOoJ* lDwwwlJlmuJlnms~
METRO III - ICAO ANNEX 8
-
z Ol-63 651s
E&I &
%I--
FIGURE
PERFORMANCE
MAY 22189
FIGURE 4D-3 (continued) PERFORMANCE
METRO III - ICAO ANNEX 8
FAA APPROVED: MAY 22189
4D-9 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4D-10 4MC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
FAA APPROVED:
4D-3 (continued)
PERFORMANCE
FIGURE
METRO III - ICAO ANNEX 8
MAY 22/89
4D-11 4MC
METRO III - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO V, AND STOP B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
l
WEIGHT
DETERMINED
DOWNWIND
AIR OFF
EXAMPLE:
POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . .. . .. . . . .. . . . . . . . . . 300 AMPS BLEED AIR . . . . . . .. . . . . .. .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) RUNWAY . . . . . . . . . . . . . . . DRY, HARD SURFACE FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . .. .. . . . . . . . . . 114 DECISION SPEED . . . . ..Vl (FIGURE 4D-3) ANTI-SKID . . . . . . . . . . . . . . . . . . . . . . .. . . . .. . . ON OR OFF NOSE WHEEL STEERING . ..ON OR OFF
THE
- DRY, BLEED
TAKEOFFS
FROM
GIVEN:
OBTAIN:
FIGURE
PROHIBITED
OAT = 15% PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V 1 SPEED = 104 KIAS ACCELERATE -STOP DISTANCE = 4,000 FEET (1220 m)
4P2 AT
PERCENT
WITH
MAXIMUM
OAT
ENGINE
ANTI-ICE
ON.
GROSS l
GROSS 7
WEIGHT 6
WITH
ENGINE
ANTI-ICE
ON
IS 5°C.
(1000 kg) 5
11
3
-40
-20
0 OAT (OC)
20
40
60
15 GROSS
14
FIGURE 4D-12 4MC
13
WEIGHT
12 (1,000
11
10
POUNDS)
0 WIND
10
20 (KNOTS)
,30
0
1
2
RUNWAY SLOPE (PERCENT)
4D-4
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 DISTANCE GOODYEAR
TO ACCELERATE TO V, AND STOP - DRY, AEROSPACE DUAL ROTOR BRAKES
ASSOCIATED
GIVEN:
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
EXCEED 4D2.
l
I GROSS 7
0
20
OAT (“C)
40
60
15
GROSS
FIGURE FAA APPROVED:
MAY 22l89
OAT = 15°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V 1 SPEED = 104 KIAS ACCELERATE - STOP DISTANCE = 4,120 FEET (1255 m)
OBTAIN:
l
-20
AIR OFF
EXAMPLE:
CONDITIONS:
............................. TAKEOFF POWER (DRY) GEN LOAD ................................ .300 AMPS BLEED AIR ............................................ OFF ENG ANTI-ICE ............... OFF (SEE NOTE) RUNWAY ............... DRY, HARD SURFACE FLAPS ....................................................... l/4 DECISION SPEED ...... V 1 (FIGURE 4D-3) NOSE WHEEL STEERING. ..O N OR OFF
40
BLEED
14
INCREASE PERCENT
ACCELERATE WITH ENGINE
MAXIMUM
OAT
WEIGHT
ENGINE
DISTANCE ON.
ANTI-ICE
ON
BY 3.6
IS 5°C.
(1000 kg)
6
5
13
10 12 11 (1,000 POUNDS)
WEIGHT
WITH
- STOP ANTI-ICE
0 10 20 ?I) WIND (KNOTS)
0
1 2 RUNWAY SLOPE (PERCENT)
4D-5
PERFORMANCE
4D-13 4MC
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
DISTANCE MAXIMUM
TO 35 FOOT
NOTE OAT WITH ENGINE ENGINE
0
50
ANTI-ICE
HEIGHT ANTI-ICE
- DRY, BLEED ON IS 5°C.
AIR OFF
1
EFFECTS
(METERS) 100 150
200
250
8,000
6,000
200 (FEET)
INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4D-14
4MC
4D-6
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 SINGLE
ENGINE ASSOCIATED
TAKEOFF
DISTANCE
TO 35 FOOT
HEIGHT
CONDITIONS:
- 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 ....................................................... If4 NOSE WHEEL STEERING. ..O N OR OFF
GIVEN:
OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) OBTAIN: V1 SPEED = 101 KIAS VR SPEED = 103 KIAS V 2 SPEED = 109 KIAS TAKEOFF DISTANCE = 4,550 FEET (1385 m)
I
NOTE I F6R TAKEOFF FIELD LENGTH DETERMINATION.
SINGLE ENGINE TAKEOFF DISTANCES ARE LONGER Tl-iAN TWO ENGINE TAKEOFF DISTANCES FACTORED BY 1.15.
MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4D-2. GROSS 7
WEIGHT 6
(1000 kg) 5
14
4
13
12
4
40
-20
0 20 OAT (“C)
40
60
15 GROSS
14 13 WEIGHT
12 11 10 (1,000 POUNDS)
FIGURE 4D-6 (continued) FAA APPROVED: MAY 22189
PERFORMANCE
0 10 20 30 WIND (KNOTS)
0
1 RUNWAY SLOPE (PERCENT)
2
4D-15 4MC
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 V1 , FLAPS 1/4
AFTER TAKEOFF, GEAR IS RETRACTED
MAINTAIN V 2 CLIMB TO 400 FEET WITH 1/4 FLAPS
ACCELERATE TO V YSE , RETRACT FLAPS AT V 2 +5 KNOTS AND FEATHER INOPERATIVE PROPELLER
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-6 through 4D-11. The takeoff flight path is as follows:
VYSE
V2
400 FT (120 m) V2 VR
SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4D-6)
1,500 FEET (457 m)
35 FT (10.7 m) SECOND SEGMENT CLIMB (FIGURES 4D-7 AND 4D-8)
SECOND SEGMENT ACCELERATION (FIGURE 4D-9)
THIRD SEGMENT CLIMB (FIGURES 4D-10 AND 4D-11)
The takeoff flight path consists of four phases defined as follows: 1. SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4D-6). 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-7 and 4D-8). 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-7 and 4D-8 present net climb gradient.
4D-16 4MC
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-9). 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-10 and 4D-11). 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-10 and 4D-11 present net climb gradient. The following are three examples to illustrate the use of the flight path data charts. EXAMPLE 1 Ð DETERMINATION OF TOTAL DISTANCE TO 1500 FEET Given:
OAT = 10oC Airport Pressure Altitude = 2000 feet Gross Weight = 13,000 pounds (5900 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-6) = 4,550 feet (1385 meters). 2. Second Segment Climb Gradient (Figure 4D-7) = 6.1%. 3. Enter Figure 4D-8 at 400 feet and proceed to 6.1%. Obtain 5,950 feet (1815 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4D-9) = 3,150 feet (960 meters) to accelerate from V2 to VYSE. 5. Third Segment Climb Gradient (Figure 4D-10) = 5.9%. 6. Enter Figure 4D-11 at 1500 feet and proceed to 5.9%. Obtain 18,758 feet (5715 meters) to climb from 400 feet to 1500 feet. 7. Total Distance is: 4,550 feet (1385 meters) 5,950 feet (1815 meters) 3,150 feet (960 meters) 18,750 feet (5715 meters) 32,400 feet (9875 meters)
FAA APPROVED: MAY 22/89
to 35 feet to 400 feet to accelerate to VYSE to 1500 feet (5.33 nautical miles)
PERFORMANCE
4D-17 4MC
METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF (continued) EXAMPLE 2 Ð CLOSE IN OBSTACLE CLEARANCE Given:
OAT = 10oC Airport Pressure Altitude = 2,000 feet Gross Weight = 13,000 pounds (5900 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 350 feet* (107 meters) Obstacle Distance From Brake Release = 18,550 feet (5655 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4D-6) = 4,550 feet (1385 meters). 2. Obstacle horizontal distance from the 35 foot height point equals the total obstacle distance minus the distance to 35 feet height. 18,550 Ð 4,550 = 14,000 feet (4265 meters). 3. Second Segment Climb Gradient (Figure 4D-7) = 6.1%. 4. To obtain the required climb gradient to clear the close in obstacle, enter Figure 4D-8 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, 6.1%, 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-8.
4D-18 4MC
PERFORMANCE
FAA APPROVED: APPROVED: MAY MAY 22/89 22/89 FAA REVISED: OCT 17/94
METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR OFF (continued) EXAMPLE 3 Ð DISTANT OBSTACLE CLEARANCE Given:
OAT = 10°C Airport Pressure Altitude = 2000 feet Gross Weight = 13,000 pounds (5900 kg) Headwind = 20 knots Runway slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 700 feet* (213 meters) Obstacle Distance from Brake Release = 28,650 feet (8730 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4D-6) = 4,550 feet (1385 meters). 2. Second Segment Climb Gradient (Figure 4D-7) = 6.1%. 3. Enter Figure 4D-8 at 400 feet and proceed to 6.1%. Obtain 5,950 feet (1815 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4D-9) = 3,150 feet (960 meters) to accelerate from V2 to VYSE. 5. The horizontal distance from the end of the second segment acceleration to the obstacle equals 28,650 Ð 4,550 Ð 5,950 Ð 3,150 = 15,000 feet (4570 meters). 6. Enter Figure 4D-11 at 700 feet* height and 15,000 feet distance. Obtain required gradient of 2.0%. 7. The Third Segment Climb Gradient (Figure 4D-10) = 5.9%. 8. Since the required gradient, 2.0%, is less than the actual gradient of 5.9%, 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-11.
FAA APPROVED: MAY 22/89
PERFORMANCE
4D-19 4MC
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) SECOND SEGMENT CLIMB GRADIENT - DRY, BLEED AIR OFF
‘ERCENT
IIENT :.
7
5
4
-2
0
2
4
6
NET CLIMB
GRADIENT
8
10
12
14
16
(PERCENT)
FIGURE 4D-7 4D-20 4MC
PERFORMANCE
FAA APPROVED: MAY 22189
TO 1500 FOOT HEIGHT -DRY, BLEED AIR OFF
TAKEOFF FLIGHT PATH DISTANCE CLOSE IN OBSTACLE CLEARANCE ASSOCIATED
CONDITIONS:
EXAMPLE:
(DRY) POWER TAKEOFF GEN LOAD . . . . . . . . . . . . . . .. . . 300 AMPS BLEED AIR . . .. . . . . . . . . . . . . . . . . . . . . . .. . .. .. OFF ENG ANTI-ICE . . . . . . . . . . . . . . ON OR OFF CLIMB SPEED ...V2 (FIGURE 4D-3) GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . .. .. . . . . . . . . . l/4
GIVEN:
OBSTACLE OBSTACLE 35 FOOT REQUIRED
OBTAIN:
HORIZONTAL 500
0
1500
1000
1
I 0.2
I
I 0.4
1
I 0.6
I
I 0.6
HEIGHT ABOVE THE RUNWAY HORIZONTAL DISTANCE FROM POINT = 14,000 FEET (4265 m) GRADIENT = 2.25 PERCENT
DISTANCE
FROM 35 FOOT HEIGHT 2500 .
2000
HORIZONTAL I 0
(continued)
I
I
DISTANCE
I
1.0
I 1.2
HORIZONTAL
DISTANCE
I 1.4 (NAUTICAL
= 350
FEET
(107
m)
POINT (METERS) 3000 I
FROM 35 FOOT HEIGHT
I
SURFACE’
..a..
3500
.I
4500
4000
POINT (FEET)
4
I 1.6 MILES)
I
I 1.6
I
I 2.0
I
1 2.2
I
I 2.4
I
I 2.6
METRO - III - ICAO ANNEX 8 TAKEOFF SECOND
FLIGHT SEGMENT
PATH DISTANCE ACCELERATION I MAXIMUM
TO 1500 FOOT HEIGHT (continued) DISTANCE - DRY, BLEED AIR OFF OAT WITH ENGINE NoTE ENGINE
ANTI-ICE
ANTI-ICE
ON IS 5°C.
EFFECTS
(METERS) 0
600
1200
1800
2400
12,000
3600
8,000
2400
; 6,000 !5
1800
b-
El ii z.
600
0 lniiiiiiiiiiiiii’iiiiiiiiiiiiiiiiiiiiiiil 0 2,000 ACCELERATION
0 4,000 (FEET) DISTANCE,
FIGURE 4D-22 4MC
6,000 ENGINE
ANTI-ICE
8,000 OFF
4D-9
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) SECOND SEGMENT ACCELERATION DISTANCE - DRY, BLEED AIR OFF ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER ............................. TAKEOFF (DRY) GEN LOAD ................................ .300 AMPS BLEED AIR ............................................ OFF ENG ANTI-ICE ............ OFF (SEE GRAPH) ACCELERATE TO VYSE ... ..FlGUR E 4F-2 GEAR ........................................................ UP FLAPS ............................... 114 (SEE NOTE)
GIVEN:
AIRPORT OAT = 10°C AIRPORT PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS VYSE CLIMB SPEED = 126 KIAS SECOND SEGMENT ACCELERATION DISTANCE = 3,150 FEET (960 m)
OBTAIN:
1EA”l ACCELERATE
GROSS 7
TO
WEIGHT
THE
(1000
LESSER
OF
V2
+5
KIAS
OR
kg)
6
5
E
1
-40
-20
0
AIRPORT
20
OAT (OC)
FAA APPROVED: MAY 22189
40
60
15
14
13
GROSS
WEIGHT
12
(1,000
FIGURE 4D-9 (continued) PERFORMANCE
11 POUNDS)
10
0
10
WIND
20
30
(KNOTS)
4D-23 4MC
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT THIRD SEGMENT
PATH CLIMB
DISTANCE GRADIENT
TO 1500 FOOT HEIGHT (continued) - DRY, BLEED AIR OFF
60
ASSOCIATED
CONDITIONS:
POWER . . . . . . . . . . . . . . . . . . MAX CONTINUOUS GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . OFF (SEE NOTE) CLIMB SPEED....VySE (FIGURE 4F-2) GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . .._...................................... UP
GIVEN:
OBTAIN:
*
-2
0
2
4 NET CLIMB
6 GRADIENT
FIGURE 4D-24 4MC
8 (PERCENT)
AIRPORT OAT - 10% AIRPORT PRESSURE ALTITUDE I 2.000 FEET GROSS WEIGHT - 13.00l POUNDS (5900 Icg) HEADWIND - 20 KNOTS V,‘SE CLIMB SPEED - 126 KIAS THIRD SEGMENT CLIMB GRADIENT - 5.9 PERCENT
MAXIMUM
10
OAT
WITH
ENGINE
12
ANTCICE
14
ON
IS 5°C.
16
4D-10
PERFORMANCE
FAA APPROVED:
MAY 22189
TAKEOFF DISTANT
FLIGHT PATH DISTANCE OBSTACLE CLEARANCE
ASSOCIATED
CONDITIONS:
TO 1500 FOOT HEIGHT - DRY, BLEED AIR OFF
(continued)
EXAMPLE:
POWER ................... MAX CONTINUOUS GEN LOAD ............................. 300 AMPS BLEED AIR .......................................... ON ENG ANTI-ICE.. .................. ON OR OFF CLIMB SPEED.. 4F-2) .. . YSE (FIGURE GEAR .................................................... UP FLAPS .................................................. UP
GIVEN:
OBTAIN:
HORIZONTAL
DISTANCE
FROM
OBSTACLE OBSTACLE SECOND REQUIRED
END
HEIGHT ABOVE THE RUNWAY SURFACE HORIZONTAL DISTANCE FROM END OF SEGMENT ACCELERATION = 15,000 FEET GRADIENT = 2.0 PERCENT
OF SECOND
SEGMENT
ACCELERATION
POINT
= 700 (4570
FEET
(213
m)
m)
=
(METERS)
420
380
m II 3 0 --
’I 0
D
0
D z z
m x 00
0
10.000
20.000
30.000 HORliONTAL
I 0
I 1
I 2
I 3
I 4
DISTANCE
40,000 FROM
I 5
END
OF SECOND
50.000 ACCELERATION
I 7
I 6 HORIZONTAL
SEGMENT
DISTANCE
(NAUTICAL
I 6 MILES)
POINT
(FEET) I 9
I 10
I 11
I 12
I 13
METRO III - ICAO ANNEX 8 TWO ENGINE
RATE
OF CLIMB
AT V,, - DRY, BLEED
AIR OFF
60
40 :5= 30
C)
MINUTE
i PER
MINUTE
20 ON IS 5%.
s 2 0
10
0
-10
-20
40
10 0
500
1,000
1,500
2,000 RATE
2,500
OF CLIMB
(FEET
FIGURE 4D-26 4MC
3,000
3,500
4,000
4,500
5,000
PER MINUTE)
4D-12
PERFORMANCE
FAA APPROVED:
MAY 22189