16 f 5 performance standard reference parte d

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

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FAA APPROVED: MAY 22189

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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

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SPEED

SCHEDULE

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AIR OFF -1

[KILOGRAMS1

CAUTION

IPRESS

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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

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55

VP Vi

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* 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.

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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