METRO III ICAO ANNEX 8 PART C – TAKEOFF PERFORMANCE DRY, BLEED AIR ON CONTENTS ITEM
PAGE
Takeoff Power Check Chart ............................................................................................................... 4C-1 Maximum Takeoff Weight Limitation Chart ........................................................................................ 4C-3 Takeoff Speed Schedules .................................................................................................................. 4C-4 Distance to Accelerate to V1 and Stop B.F. Goodrich Single Rotor Brakes ......................................................................................... 4C-12 Goodyear Aerospace Dual Rotor Brakes ................................................................................ 4C-13 Single Engine Takeoff Distance to 35 Foot Height .......................................................................... 4C-14 Takeoff Flight Path Distance to 1500 Foot Height ........................................................................... 4C-16 Second Segment Climb Gradient ............................................................................................ 4C-20 Close In Obstacle Clearance .................................................................................................. 4C-21 Second Segment Acceleration Distance ................................................................................. 4C-22 Third Segment Climb Gradient ................................................................................................ 4C-24 Distant Obstacle Clearance .................................................................................................... 4C-25 Two Engine Rate of Climb at V50. .................................................................................................... 4C-26
FAA APPROVED: MAY 22/89
PERFORMANCE
4C-i 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-ii 4MC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
9
D
TAKEOFF POWER CHECK CHART - DRY, BLEED AIR ON ASSOClAiED
EXAMPLE:
CONDITIONS:
POWER ............. TAKEOFF (DRY) RPM ............ ...... .................... 100% MAX ALLOWABLE EGT ....66O”C GEN LOAD ................. 300 AMPS BLEED AIR ................ ......... ..... ON ENG ANTI-ICE ........SEE GRAPH SPEED ..................... ......... STATIC
GIVEN:
OAT = 0°C PRESSURE ALTITUDE = 2,000 FEET ENGINE ANTI-ICE SYSTEM - OFF OBTAIN: ENGINE TORQUE = 91.3 PERCENT
l
l
j_
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 %. 660%. 110
100
90
60
50
40 -40
-30
-20
-10
10
0 OAT (W)
20
30
40
50
OFF
ON ENGINE ANTI-ICE SYSTEM
m x
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-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 ON
CONDITIONS: REDUCE
POWER .. .. . . . . .. .. . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . .. . . . .. . .. . . . .. . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . .. . . . . . .. ON ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) GEAR . . . . . . .. . . . . . . .. . . . . . . . DOWN (TAKEOFF) UP (SECOND AND THIRD SEGMENT) FLAPS . . .. . . . . . . .. . .. . . . . . . . . . . . . . . . . . . . l/4 (TAKEOFF) UP (ENROUTE)
l
l
MAXIMUM
TAKEOFF
OAT
WEIGHT
WITH
ENGINE
BY
1,110
ANTI-ICE
POUNDS
ON
(505
kg)
IS 5°C.
THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE Vl
EXAMPLE: GIVEN: OBTAIN:
OAT = 10°C PRESSURE ALTITUDE = 5,000 FEET TAKEOFF WEIGHT = 13,700 POUNDS
(6210
kg)
I
16
15
APP. A, 6.(b) AND
FIGURE FAA APPROVED:
MAY 22189
4C-2
PERFORMANCE
4c-3 4MC
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR ON IPOUNDS . 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 ONLY. . REFER
TO FIGURE
4C-2
FOR MAXIMUM
PERMISSIBLE
TAKEOFF
WEIGHTS. I
PRES ALT (FT)
T-
-10
“1
“RI
105 1011 102 101
108 105 102 101 101 101 102 103 103 103
-
“21”5ol I I I
i# 102 103 103 103 -
I I
1111 113 111 111 112 1111 116 116 119 121
125 121 122 122 1211 126 128 131 133 135
I
%I
I
105 1OY 102 101 100 101 101 102 103 103
“RI
I I
109 106 103 101 100 101 101 102 103 103
105 i% 101 100 101 102 103 i-m 103 105 IOU i-07 101 100 101 101 102 103 103 -
iii/iir *
I I
OUTS1
IE RIR
0
“2l”so I I
11Y 113 111 110 110 112 1111 116 118 120
-
TEMPERRTURE
I-C) -?-
“1
“P
-
125 105 110 124 1011 ~ 122 102 105 121 101 102 122 100 12’4 100 iii? 127 100 100 129 101 101 132 102 i-z 13Y 102 102 105 1011 102 101 100 100 100 100 n-i 102 -
111 109 106 103 102 101 100 100 m-l 102 -
105 1011 iii2 101 100 100 100 QlJ 100 101
112 109 107 104 103 102 101 joJ 100 101
-r
“2
/
1111 113 111 109 109 109 109 110 iii 113 1111 113 111 109 109 109 109 111 113 115
12u 123 121 120 120 120 121 123 125 127
105 1011 102 101 100 100 100 100 100 100
113 110 108 105 1011 103 102 101 100 100
1111 113 111 109 % 109 109 i-iii 111 1111 i-z iii 109 109 i-m 109 109 109 110 -
3 m -I a 0 0 D 0 D z z
m x 00
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR ON . TAKEOFF IN TEMPERATURE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID. STEPPED LINE IS NOT APPROMD. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION - REFER
I
CJUTSIDE -10
105 1011 102 101 100 101
109 106 103 101 100 101
1111 113 111 109 110 112
0
“R
"50
~ "1
"R
"2
"SO
"1
125
~105 110 1011 107 102 1011 101 102 100 100 100 100 101 101 101 101 102 102 103 103
11q 113
12rl 123
105 10’4
111
111
122
102
109 109 110 112 1111 116 118
121 120 122 12U 126 129 131
101 100 100 100 100 101 101
% 103 102 iTi 100
11u 113 111 109 109 i-m 109
KY 101
Is 11u
112 110 i-m 104 103 m-2 101 100 100 101
1111 113 111 109 109 i-m 109 109 110 112
E 122 123 125 127 j3J 132 134 111500 lllDO0 13500 13000 12500 12000
I
125 123 122 121 122 i-z 100 100 101 102 125 123 122 121 121 i-23 125 128 130 133
100 100 101 102
110 112 11U 116
122 1211 126 129
100 100 100 101
113 111 108 105 1011 103 102 &l 100 100
RIR
TO FIGURE
TEHPERFITURE
4C-Z
FOR MAXIMUM
[‘Cl
PERMISSIBLE
TAKEOFF
WEIGHTS.
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-6 4MC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR ON ptz6-l
. 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 ONLY. - REFER
IYJTSIDE
I
I
-1
-1
--I
-1
I
I
I
I
I
I
RIR
I
I
TO FIGURE
4C-2
TEMPERFITURE
I
I
I
I
FOR MAXIMUM
PERMISSIBLE
TAKEOFF
[‘Cl
I
I
I
I
I
I
I
105 110 1111 121 105 112 1111 12U 1 I I I I ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ I I I I I I I I i~~nnlln~liflull t11i231tn311n71111 ll~~l~n2l~nsllll l~7nlto7l~~nl~~il~7oI 13000 101 102 109 121 101 105 109 120 101 106 109 119’101 106i1091119~101~109i109~118~ 1 1 1 1 6OOU 1 12500 100 100 109 120 100 103 109 119 100 105 109 119 100 1 07~109~119~100~108~109~116~ I I 12000 100 100 110 122 100 102 109 120 100 1011 109 119 100 l--061109111911001108110911181100110911091115l _---100 109 109 116 11500 100 100 111 123 100 102 109 120 100 103 109 120 100 105 109 119 100 109 109 117 11000 101 101 113 126 100 101 109 121 100 102 109 120 100 1011 109 120 11511~R~1001100~110~122~100i101~109~~21~100~103~109~120l100~105~109~120~100~109~109~116l 118~131~100~100~112~12U~100(1001110)1211100~102~1l0~121~100~10~~110~120 100~109~110~119 A”““”
.“L
.“.
1..
.--
.“..
.“,
---
---
---
---
---
---
WEIGHTS.
__-,___,___,_-_
I
I
I
I
I
I
1
1
1
I
I
I
I
I
I
I I I I
111500 111000 13500 13000 7000 I 12,500 12000 11500 hllOOO 10500 10000
105 1OU 102 101 100 100 100 100 101 102
111 106 105 103 101 100 100 100 101 102
1111 113 111 109 109 109 110 111 113 116
12Y 123 122 120 120 121 122 123 126 128
105 1011 102 101 100 LOO 100 100 100 100
113 111 108 106 1OU 1OU 103 102 101 100
11’4 113 111 109 109 109 109 109 109 110
123 122 121 119 119 120 120 120 121 122
. .._^^
_-..
_^A
13500
102 101 100 100 100 100
106 1011 102 101 100 100
111 109 109 109 109 110
121 120 120 120 121 122
102 101 LOO 100 100 100
lo9 107 105 105 104 103
111 109 109 109 109 109
1% 119 119 119 120 120
101
101
1111 124 112 126
100 100
101 102
110 109
121
1~uuuI1u~I1uYIll~IlL~~~u~lll~lll~ll
13000
8OOCI 12500 12000 11500 11000
I
10000 10500
105 1011 102 101 100 100 100 100 100 100
I
lllllllllllllllllllI
115 112 110 107 106 105 1011 1011 103 102
1lU 113 111 109 109 109 109 109 109 110
I I 102/111l11111201
123 122 120 119 119 119 119 120 120 121
102 111 101109 100 107 tO0 107 100 106 100 105 100 1011 100 103
I
II
111 109 109 109 109 109 109 110
I
120 118 116 119 119 119 120 120
I
100 100 100 100 100 100
109 108 108 107 106 105
I
I
109 109 109 109 109 110
118 118 119 119 119 120
I
I
100 100 100 100
109 109 109 109
I
I
109 109 109 110
I
115 116 117 118
I
I
I
100 100 100 100
107 106 105 105
109 109 109 109
119 116 119 119 120
101 100 100 100 100
110 108 108 107 106
109 109 109 109 109
118 118 118 119 119
100 100 100
109 109 108
109 109 109
116 118 119
100
109
109
115
100
104 103
110 109
120
100
1011 109 105 110
120
100
106 107
110 109
119
100
109
110 109
117 116
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR ON lKlLoGRAMs1 . 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 ONLY. . REFER
TO FIGURE
4C-2
FOR MAXIMUM
PERMISSIBLE
TAKEOFF
WEIGHTS. I
II-
OUTSIDE
'RESS I GRbSS AL1
-10
-30
!
,
I
UT
IFf)
“1
“R
“2 “50
“1
“R
“2 “50
,0
“1
“R
RIR
TEMPERRTURE
(‘Cl
10 I
20
YO
I
“2 “50
“1
55
I
“R
“2 “50
“1
“R
“2 “50
“1
“R
“2
“50
“R
“2
“50
sm
II 111 0
S.
c) 1000
2000 ',
6560 6YOO 6200 6000 se00 5690 SKI0 5,200 5000 IL800 ‘4600 6580 6UOO 6200 6000 5800 5600 5400 5200 5000 U800 4600
106 1011 103 101 101 101 102 102 103 103 103
107 105 103 101 101 101 102 102 103 103 103
1111 113 112 111 112 113 115 117 116 120 121
106 1011 103 101 100 101 102 102 103 103 103
108 106 103 101 100 101 102 102 103 103 103
1111 113 112 111 111 113 1111 116 118 119 120
III
125 12’4 123 123 121 126 126 130 132 133 135
106 1011 103 101 100 101 101 102 102 103 103
108 106 1011 101 100 101 101 102 102 103 103
125 12Y 123 122 123 125 127 129 131 133 135
106 loll 103 101 100 100 101 101 102 103 103
109 107 1011 102 100 100 101 101 102 103 103
III
1111 113 112 110 110 112 113 115 117 118 120
I
1111 113 112 110 109 110 112 1111 115 117 119
I
125 12Y 123 122 122 12Y 126 128 130 132 1311 125 1211 123 121 121 122 1211 126 128 131 133
I
106 1011 103 101 100 100 100 101 101 102 103 106 1OY 103 101 100 100 100 100 101 101 102
I
110 107 105 103 100 100 100 101 101 102 103 110 108 106 1011 101 101 100 100 101 101 102
I
1111 113 112 110 109 109 111 112 1lY 116 118 1111 113 112 110 109 109 109 110 112 11Y 116
125 123 122 121 120 121 123 129 126 129 131
106 1011 103 101 100 100 100 100 100 101 101
111 109 107 1011 102 101 101 100 100 101 101
32Y 123 122 121 120 120 121 122 12Y 126 128
106 1OY 103 101 100 100 100 100 100 100 101
112 110 108 105 103 102 102 101 100 100 101
III
1111 113 112 110 109 109 109 109 111 112 114
12Y 123 122 121 120 120 120 121 123 125 127
106 1011 103 101 100 100 100 100 100 100 100
1111 113 112 110 109 109 109 109 109 110 112
12Y 123 122 120 119 120 120 121 121 lZ2 121
106 1011 103 101 100 100 100 100 100 100 100
III
113 111 109 106 1011 103 103 102 101 100 100
I
114 112 110 107 105 1011 10’4 103 102 101 100
I
1lY 113 112 110 109 109 109 109 109 109 110 1111 113 112 110 109 109 109 109 109 IO9 110
I
12Y 106 122 1OY 121 103 12OllOl 119 119 120 120 100 121 100 121 100 122 100
I
123 122 121 120 119 119 120 120 120 121 121
1011 103 101 100 100 100 100 100 100 100
I
115 1111 112 110
1111 113 112 110
121 120 120 119
106 106 105 1011
109 109 109 110
119 119 120 120
100 100 100 100 100
109 109 109 108 108
109 109 109 109 110
117 118 116 119 119
119 119 118 118 118 118 119 119 119 120
100 100 100 100
109 109 109 109
109 109 109 110
117 117 118 119
1111 112 110 109 108 108 107 107 106 105
I
113 112 110 109 109 109 109 109 109 110
I
D 0 D z z m x 00
FIGURE 4C-3 (continued) PERFORMANCE
METRO III - ICAO ANNEX 8
FAA APPROVED: MAY 22l89
4c-9 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-10 4MC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
FAA APPROVED:
PERFORMANCE
METRO III - ICAO ANNEX 8
MAY 22l89
4c-11 4MC
METRO Ill - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO V, AND STOP B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
- DRY, BLEED
EXAMPLE:
POWER . . . .. . .. . . . .. . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . .. . . . .. . . .. . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . . .. . . . . . . .. . . ON ENG ANTI-ICE . . . . . . . . . . . . . . OFF (SEE NOTE) RUNWAY . . . . .. . .. . . . . . . DRY, HARD SURFACE FLAPS .. . .. . .. .. . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. .. It4 DECISION SPEED . . . . ..V 1 (FIGURE 4C-3) ANTI-SKID . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . ON OR OFF NOSE WHEEL STEERING . ..ON OR OFF
GIVEN:
OBTAIN:
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 = 4,050 FEET (1235 m)
l
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
EXCEED 4C-2.
l
GROSS 7
40
-20
0
20 OAT (OC)
40
60
15 GROSS
INCREASE PERCENT
ACCELERATE-STOP DISTANCE WITH ENGINE ANTI-ICE ON.
MAXIMUM
OAT
WEIGHT 6
14
13
WEIGHT
FIGURE 4C-12 4MC
AIR ON
WITH
ENGINE
ANTI-ICE
BY 4.4
ON
IS 5°C.
(1000 kg) 5
12 (1,000
11
10
POUNDS)
0
10
WIND
20
30
(KNOTS)
0
1
2
RUNWAY SLOPE (PERCENT)
4C-4
PERFORMANCE
FAA APPROVED:
MAY 22189
METRO III - ICAO ANNEX 8 DISTANCE GOODYEAR
TO ACCELERATE TO V, AND STOP - DRY, BLEED AEROSPACE DUAL ROTOR BRAKES
ASSOCIATED
AIR ON
EXAMPLE:
CONDITIONS:
GIVEN:
POWER ............................. TAKEOFF (DRY) GEN LOAD ................................ .300 AMPS BLEED AIR .............................................. ON ENG ANTI-ICE ............... OFF (SEE NOTE) RUNWAY ............... DRY, HARD SURFACE FLAPS ....................................................... If4 DECISION SPEED ...... V1 (FIGURE 4C-3) NOSE WHEEL STEERING. ..O N OR OFF
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 = 4,200 FEET (1280 m)
OBTAIN:
7 1 WARNING
I
I
1.
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
EXCEED 4G2.
NOTE
I
. INCREASE I PERCENT
I
I
GROSS 7
l
ACCELERATE WITH ENGINE
MAXIMUM
WEIGHT 6
OAT
WITH
- STOP ANTI-ICE ENGINE
DISTANCE ON.
ANTI-ICE
BY 4.2
ON
1
IS5”C.
(1000 kg) 5 12
11
c ::
2 6d
8
40
-20
0
20 OAT (“C)
40
60
15 GROSS
14
FIGURE FAA APPROVED:
MAY 22109
13
WEIGHT
12 (1,000
11
10
POUNDS)
0
10
WIND
20 (KNOTS)
30
0
1
2
RUNWAY SLOPE (PERCENT)
4C-5
PERFORMANCE
4c-13 4MC
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
DISTANCE
1 MAXIMUM
TO 35 FOOT
OAT WITH ENGINE ENGINE
0
HEIGHT
50
100
NoTE’
ANTI-ICE
ANTI-ICE
EFFECTS
(METERS) 150
- DRY, BLEED
AIR ON
ON IS 5°C.
200
250
300
8,000
6,000
S.L. 0
200
400
600
800
1,000
(FEET) INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4c-14 4MC
4C-6
PERFORMANCE
FAA APPROVED:
MAY 22169
METRO III - ICAO ANNEX 8 SINGLE
ENGINE ASSOCIATED
TAKEOFF
DISTANCE
TO 35 FOOT
CONDITIONS:
HEIGHT
- DRY, BLEED
AIR ON
EXAMPLE:
POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD .. .. . . . . .. . . . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . .. . . . .. . .. . . . .. . .. . . . .. . . ON ENG ANTI-ICE .. .. . . . . .. . . OFF (SEE GRAPH) RUNWAY . . . . . . . . . . . . . . . DRY, HARD SURFACE V , SPEED . . . . . . . . . . . . . . . . . . . . . .. . . . . . FIGURE 4C-3 V R SPEED . . . . . . . . . . . . . . . . . . . . . .. . . . . . FIGURE 4C-3 V 2 SPEED . . . . . . . . . . . . . . . . . . . . . .. . . . . . FIGURE 4C-3 FLAPS . . . .. . .. . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114 NOSE WHEEL STEERING ...ON OR OFF
GIVEN:
OAT = 10% PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) VI SPEED = 101 KIAS VR SPEED = 104 KIAS V2 SPEED = 109 KIAS TAKEOFF DISTANCE = 4,975 FEET (1515 m)
OBTAIN:
NOTE FOR TAKEOFF FIELD LENGTH ENGINE TAKEOFF DISTANCES ENGINE TAKEOFF DISTANCES
MAXltiUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FlGURE4C-2.
GROSS 7
WEIGHT
(1000 kg)
(i
5
DETERMINATION, SINGLE ARE LONGER THAN TWO FACTORED BY 1 .15.
. 12
11
OAT (OC)
GROSS
WEIGHT
(1.000
POUNDS)
WIND
(KNOTS)
RUNWAY SLOPE (PERCENT)
FIGURE 4C-6 (continued) FAA APPROVED: MAY 22/89
PERFORMANCE
4c-15 4MC
METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON
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
VYSE
V2
400 FT (120 m)
V2 VR
SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4C-6)
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 4C-6 through 4C-11. The takeoff flight path is as follows:
1,500 FEET (457 m)
35 FT (10.7 m) SECOND SEGMENT CLIMB (FIGURES 4C-7 AND 4C-8)
SECOND SEGMENT ACCELERATION (FIGURE 4C-9)
THIRD SEGMENT CLIMB (FIGURES 4C-10 AND 4C-11)
The takeoff flight path consists of four phases defined as follows: 1. SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4C-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 4C-7 and 4C-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 4C-7 and 4C-8 present net climb gradient.
4C-16 4MC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON (continued) 3. SECOND SEGMENT ACCELERATION (FIGURE 4C-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 4C-10 and 4C-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 4C-10 and 4C-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 4C-6) = 4,975 feet (1515 meters). 2. Second Segment Climb Gradient (Figure 4C-7) = 4.9%. 3. Enter Figure 4C-8 at 400 feet and proceed to 4.9%. Obtain 7,450 feet (2270 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4C-9) = 3,750 feet (1145 meters) to accelerate from V2 to VYSE. 5. Third Segment Climb Gradient (Figure 4C-10) = 4.9%. 6. Enter Figure 4C-11 at 1500 feet and proceed to 4.9%. Obtain 22,500 feet (6860 meters) to climb from 400 feet to 1500 feet. 7. Total Distance is: 4,975 feet (1515 meters) 7,450 feet (2270 meters) 3,750 feet (1145 meters) 22,500 feet (6860 meters) 38,675 feet (11790 meters)
FAA APPROVED: MAY 22/89
to 35 feet to 400 feet to accelerate to VYSE to 1500 feet (6.37 nautical miles)
PERFORMANCE
4C-17 4MC
METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON (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 = 18,975 feet (5785 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4C-6) = 4,975 feet (1515 meters). 2. Obstacle horizontal distance from the 35 foot height point equals the total obstacle distance minus the distance to 35 feet height. 18,975 Ð 4,975 = 14,000 feet (4265 meters). 3. Second Segment Climb Gradient (Figure 4C-7) = 4.9%. 4. To obtain the required climb gradient to clear the close in obstacle, enter Figure 4C-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, 4.9%, 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 4C-8.
4C-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 ON (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 = 31,175 feet (9500 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4C-6) = 4,975 feet (1515 meters). 2. Second Segment Climb Gradient (Figure 4C-7) = 4.9%. 3. Enter Figure 4C-8 at 400 feet and proceed to 4.9%. Obtain 7,450 feet (2270 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4C-9) = 3,750 feet (1145 meters) to accelerate from V2 to VYSE. 5. The horizontal distance from the end of the second segment acceleration to the obstacle equals 31,175 Ð 4,975 Ð 7,450 Ð 3,750 = 15,000 feet (4570 meters). 6. Enter Figure 4C-11 at 700 feet* height and 15,000 feet distance. Obtain required gradient of 2.0%. 7. The Third Segment Climb Gradient (Figure 4C-10) = 4.9%. 8. Since the required gradient, 2.0%, is less than the actual gradient of 4.9%, 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 4C-11.
FAA APPROVED: MAY 22/89
PERFORMANCE
4C-19 4MC
METRO III - ICAO ANNEX 8 TAK :EOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) SEC :OND SEGMENT CLIMB GRADIENT - DRY. BLEED AIR ON 60
40
20
0
-20
40 15
14
13
12
‘11
10
0 IO 20 30 -4
-2
0
2
4 NET CLIMB
FIGURE 4C-20 4MC
6 GRADIENT
8 (PERCENT)
10
‘?
14
16
4C-7
PERFORMANCE
FAA APPROVED:
MAY 22/89
TAKEOFF FLIGHT PATH DISTANCE CLOSE IN OBSTACLE CLEARANCE ASSOCIATED
TO 1500 FOOT HEIGHT - DRY, BLEED AIR ON
(continued)
EXAMPLE:
CONDITIONS:
GIVEN:
POWER ,.,.........,....._ TAKEOFF (DRY) GEN LOAD . .._...,........,...... 300 AMPS BLEED AIR ..,,.,,......,...................... ON ENG ANTI-ICE . . . . . . . . . . . . . . ON OR OFF CLIMB SPEED . ..V2 (FIGURE 4C-3) GEAR . . . . . . .._.....................,.....,........, UP FLAPS . . . . .. . .. . . . ..._..__......................... II4
OBSTACLE OBSTACLE 35 FOOT REQUIRED
OBTAIN:
HEIGHT ABOVE THE RUNWAY HORIZONTAL DISTANCE FROM POINT = 14,000 FEET (4265 m) GRADIENT = 2.25 PERCENT
SURFACE
= 350
FEET
(107
m)
zm 120
-I 3 0 -
i 0 D 0 D z z m X 00 I
0
1
I 0.2
I
I 0.4
I
I 0.6
,
I 0.6
I
I 1.0
I HORIZONTAL
I 1.2
1 DISTANCE
I 1.4 (NAUTICAL
1
I 1.6 MILES)
8
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
FLIGHT
PATH
DISTANCE
TO 1500 FOOT
SECOND SEGMENT ACCELERATION / MAXIMUM
200
(continued)
OAT WITH ENGINE
NoTEI ANTI-ICE
ENGINE 0
HEIGHT
DISTANCE - DRY, BLEED AIR ON
400
ANTI-ICE
ON IS 5°C.
EFFECTS
(METERS) 600 800
1000
1200
1400
8,000
6,000
(FEET) INCREASE IN ACCELERATION WITH ENGINE ANTI-ICE
DISTANCE ON
FIGURE 4C-9 4C-22 4MC
PERFORMANCE
FAA APPROVED: MAY 22189
METRO III - ICAO ANNEX 8 TAKEOFF
FLIGHT
PATH
DISTANCE
TO 1500 FOOT
SECOND SEGMENT ACCELERATION ASSOCIATED
HEIGHT
(continued)
DISTANCE - DRY, BLEED AIR ON
CONDITIONS:
EXAMPLE:
POWER .............. ... .... .... .... TAKEOFF (DRY) GEN LOAD .. ............................... 300 AMPS BLEED AIR .. .. .......................................... ON ENG ANTI-ICE ............ OFF (SEE GRAPH) TO V YSE ... FIGURE 4F-1 ACCELERATE GEAR .............. ... ....................................... UP FLAPS .._............................l/4 (SEE NOTE)
GIVEN:
AIRPORT OAT = 10°C AIRPORT PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS OBTAIN: VYSE CLIMB SPEED = 126 KIAS SECOND SEGMENT ACCELERATION DISTANCE = 3,750 FEET (1145 m)
NOTE ACCELERATE TO THE LESSER OF Vp +5 KIAS OR V YSE PRIOR TO RAISING FLAPS. GROSS WEIGHT (1000 kg) 7
12
11
10
2
3
2
-40
-20
0
20
AIRPORT OAT (OC)
40
60
15
12 11 14 13 GROSS WEIGHT (1,000 POUNDS)
10
0 10 20 30 WIND (KNOTS)
FIGURE 4C-9 (continued) FAA APPROVED: MAY 22189
PERFORMANCE
4C-23 4MC
METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) THIRD SEGMENT CLIMB GRADIENT - DRY, BLEED AIR ON 60
ASSOCIATED
CONDITIONS:
POWER . . . . . . . . . . . . . . . . . . MAX CONTINUOUS GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE . . . . . . . . . . OFF (SEE NOTE) CLIMB SPEED . . . . VYSE (FIGURE 4F-1) GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP EXAMPLE: GIVEN:
OBTAIN:
AIRPORT OAT - 10% AIRPORT PRESSURE ALTITUDE I 2,CUO FEET GROSS WEIGHT - 13,OCO POUNDS (5900 $) HEADWIND = 20 KNOTS VYSE CLIMB SPEED - 126 KIAS THIRD SEGMENT CLIMB GRADIENT - 4.9 PERCENT I.“IL
.
REDUCE CLIMB GRADIENT BY 2.1 PERCENT WITH ENGINE ANTCICE ON.
*
MAXIMUM
OAT
WITH
ENGINE
ANTCICE
GRADIENT
ON IS 5°C.
7 15
14
6 13
12
11
10
0 6 5
‘10
B g 5
20 30 NET CLIMB
GRADIENT
(PERCENT)
FIGURE 4C-10 4C-24 4MC
PERFORMANCE
FAA APPROVED: MAY 22189
TAKEOFF DISTANT
FLIGHT PATH DISTANCE OBSTACLE CLEARANCE
ASSOCIATED
CONDITIONS:
TO 1500 FOOT HEIGHT - DRY, BLEED AIR ON
(continued)
EXAMPLE:
POWER ................... MAX CONTINUOUS GEN LOAD ............................. 300 AMPS BLEED AIR .......................................... ON ENG ANTI-ICE.. .................. ON OR OFF CLIMB SPEED.. ..VYS E (FIGURE 4F-1) GEAR .................................................... UP FLAPS .................................................. UP
GIVEN:
OBTAIN:
HORIZONTAL
DISTANCE
OBSTACLE OBSTACLE SECOND REQUIRED
FROM
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)
D z z m x 00
I 0
I 1
I 2
I 3
I 4
I 5
I 6 HORIZONTAL
I 7 DISTANCE
(NAUTICAL
I 6 MILES)
I 9
I IO
1
t
11
12
I 13
METRO III - ICAO ANNEX 8 TWO ENGINE
RATE
OF CLIMB
AT V,, - DRY, BLEED
AIR ON
60 ASSOClATED
CONDITIONS:
POWER . . . . . . . . . . . . . . . . MAX CONTINUOUS GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . 3UO AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE . . . . . . . OFF (SEE NOTE) CLIMB SPEED . Vm (FIGURE 4C3) GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114 EXAMPLE: GIVEN: OBTAIN:
-
OAT = 10% PRESSURE ALTITUDE - 6,ooO FEET GROSS WEIGHT - 13,OCO POUNDS (5900 $) VW CLIMB SPEED - 119 KIAS RATE OF CLIMB - 1.990 FEET PER MINUTE
MAXIMUM
OAT
WITH
ENGINE
ANTCICE
ON IS 5-C.
-30
40
15
g
14
f i? g
13
t I’ P
12
z ii g
11
10 0
l.,OOO
1.500 RATE
2,000 OF CLIMB
2,500 (FEET
3,000
FIGURE 4C-26 4MC
3,500
4,000
4,500
5,000
PER MINUTE)
4C-12
PERFORMANCE
FAA APPROVED:
MAY 22189