4d_AFM

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