14 5 downty f 3 performance parte c

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 Distance to Accelerate to V1 and Stop B.F. Goodrich Single Rotor Brakes ........................................................................................... 4C-4 Goodyear Aerospace Dual Rotor Brakes .................................................................................. 4C-5 Single Engine Takeoff Distance to 35 Foot Height ............................................................................ 4C-6 Takeoff Flight Path Distance to 1500 Foot Height ............................................................................. 4C-8 Single Engine Climb Gradient at V2 ........................................................................................ 4C-10 Two Engine Rate of Climb at V35 .................................................................................................... 4C-11

FAA APPROVED: NOV 07/90

PERFORMANCE

4C-i 4AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4C-ii 4AC

PERFORMANCE

MANUFACTURER'S DATA ISSUED: NOV 07/90

TAKEOFF

POWER

ASSOCIATED

CHECK

CHART

- DRY, BLEED

CONDITIONS:

AIR ON

EXAMPLE:

RPM .. .... ....................... ... ... ... 100% MAX ALLOWABLE EGT ....65O”C GEN LOAD......0 TO 200 AMPS BLEED AIR .... ......... ............... ON ENG ANTI-ICE ........ SEE GRAPH SPEED ,.................0 TO 50 KIAS

GIVEN:

OAT = 0°C PRESSURE ALTITUDE = 2,000 FEET ENGINE ANTI-ICE SYSTEM - OFF OBTAIN: ENGINE TORQUE = 91.3 PERCENT

l

MAXIMUM

OAT WITH ENGINE ANTI-ICE ON IS 5°C.

z

REFERENCE EGT IS THE EGT OBTAINED WHEN REQUIRED ENGINE TORQUE IS SET IN ACCORDANCE WITH THIS Ij_rl*II1Xr_ 5; 660°C.

m -I Tlb 0

J

100

90

60

50

40

-30

-20

-10

10

0

OAT (OC)

20

30

40

50

OFF

ON ENGINE ANTI-ICE SYSTEM

7-

c)

D 0 D z 2 m x 00

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4C-2 4AC

PERFORMANCE

FAA APPROVED: NOV DATA 07/90 MANUFACTURER'S ISSUED: NOV 07/90

METRO III - ICAO ANNEX 8 MAXIMUM

TAKEOFF

ASSOCIATED

WEIGHT

LIMITATION

CHART

- DRY, BLEED

CONDITIONS:

POWER ...... ....................... TAKEOFF (DRY) GEN LOAD .................................. 200 AMPS BLEED AIR .. ........ ........... ......................... ON ENG ANTI-ICE ................ OFF (SEE NOTE) GEAR ............................. DOWN (TAKEOFF) UP (ENROUTE) FLAPS ...................... . . . . l/4 (TAKEOFF) UP (ENROUTE)

AIR ON NOTE

l

l

l

REDUCE TAKEOFF WEIGHT BY 1.060 POUNDS (475 kg) WITH ENGINE ANTI-ICE ON. MAXIMUM

OAT WITH ENGINE ANTI-ICE

ON IS 5°C.

THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE V1

EXAMPLE: GIVEN:

OAT = 2°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: TAKEOFF WEIGHT = 13,900 POUNDS 16305 kal DECREASE (ANTI-ICE ON) = -1iO60 POUNDS i-475 k;li NET TAKEOFF WEIGHT = 12,860 POUNDS (5630 kg)

7

8

FIGURE 4C-2 FAA APPROVED: NOV 07/90

PERFORMANCE

4AC

METRO III - 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 ..,...........................,... 200 AMPS BLEED AIR .............................................. ON ENG ANTI-ICE .. . ....... .OFF (SEE NOTE) RUNWAY ............... DRY, HARD SURFACE FLAPS .................................... ........ ... ........ 114 DECISION SPEED ... ..V , (FIGURE 4B-15) ANTI-SKID ................. ........ ....... ON OR OFF NOSE WHEEL STEERING ....ON OR OFF

GIVEN:

OAT = -10% PRESSURE ALTITUDE = 2,OCO FEET GROSS WEIGHT = 12.000 POUNDS (5440 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 2 PERCENT (UPHILL) OBTAIN: ACCELERATE -STOP DISTANCE = 2,630 FEET INCREASE (ANTI-ICE ON) = 165 FEET NET ACCELERATE -STOP DISTANCE = 3,015 FEET

l

MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4C2.

GROSS

-40

-20

0

20 OAT (‘X)

AIR ON

40

60

l

WEIGHT

14 13 12 GROSS WEIGHT

INCREASE ACCELERATE - STOP DISTANCE PERCENT WITH ENGINE ANTI-ICE ON. MAXIMUM

(1000

11 (1,000

4c-4 4AC

BY 6.5

OAT WITH ENGINE ANTI-ICE ON IS 5°C.

kg)

10 9 POUNDS)

10 0 TAIL WIND

FIGURE

(865 m) (55 m) (920 m)

10 20 HEAD (KNOTS)

24

-6

-4 -2 0 2 UPHILL DOWNHILL RUNWAY SLOPE (PERCENT)

4

4C-3

PERFORMANCE

FAA APPROVED:

NOV 07/90

METRO III - ICAO ANNEX 8 DISTANCE GOODYEAR

TO ACCELERATE TO V, AND STOP - DRY, BLEED AEROSPACE DUAL ROTOR BRAKES

ASSOCIATED

AIR ON

EXAMPLE:

CONDITIONS:

POWER .. . . . . . . .. . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 AMPS BLEED AIR . . . . . . . .. . . . . . . . .._...........................

ON ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) RUNWAY . . . .. . .. . . . .. . .. DRY, HARD SURFACE FLAPS . . .. . . . .. . .. . . . .. . .. . . . .. .. . . .. . . . . . . .. . . . . . . . . . . . . . . . . l/4 DECISION SPEED . . . ..Vl (FIGURE 4B-15) NOSE WHEEL STEERING .. ..ON OR OFF

GIVEN:

OAT = -10°C PRESSURE ALTITUDE = 2,ooO FEET GROSS WEIGHT = 12,000 POUNDS (5440 kg) HEADWIND = 10 KNOTS RUNWAY SLOPE = 2 PERCENT (UPHILL) ACCELERATE -STOP DISTANCE = 3,000 INCREASE (ANTI-ICE ON) = 150 NET ACCELERATE -STOP DISTANCE = 3,150

OBTAIN:

l

l

GROSS

(915 (45 (960

NOTE

I

MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4C2.

FEET FEET FEET

INCREASE PERCENT

ACCELERATE WITH ENGINE

MAXIMUM

OAT

WEIGHT

(1000

WITH

m) ml m)

I

- STOP ANTI-ICE ENGINE

DISTANCE ON.

ANTI-ICE

BY

ON

5

IS5”C.

kg) 11

10 3

2

-40

-20

0

20 OAT (OC)

40

60

15 GROSS

14

13

FIGURE FAA APPROVED:

NOV 07/90

12

WEIGHT

11 (1.000

10

9

POUNDS)

0 WIND

10

20 (KNOTS)

30

0

2

4

6

RUNWAY SLOPE (PERCENT)

4C-4

PERFORMANCE

4c-5 4AC

-L

0 “0 8

N “0 8

“0 8

m x 00

0 b z z

c)

I

METRO III - ICAO ANNEX 8 SINGLE

ENGINE

TAKEOFF

ASSOCIATED

DISTANCE

TO 35 FOOT

CONDITIONS:

HEIGHT

- DRY, BLEED

AIR ON

EXAMPLE:

POWER ............................. TAKEOFF (DRY) GEN LOAD ..................................200 AMPS BLEED AIR ..............................................ON ENG ANTI-ICE .............OFF (SEE GRAPH) RUNWAY.. ..............DRY, HARD SURFACE V 1 SPEED.. ......................... FIGURE 4B15 V 2 SPEED.. ......................... FIGURE 4515 FLAPS ....................................................... 114 NOSE WHEEL STEERING.. ..O N OR OFF

GIVEN:

OAT = -10% PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 10,000 POUNDS (4540 kg) TAILWIND = 8 KNOTS RUNWAY SLOPE = 2 PERCENT (DOWNHILL) OBTAIN: VI SPEED = 98 KIAS V2 SPEED = 99 KIAS TAKEOFF DISTANCE = 2,400 FEET (730 m) INCREASE (ANTI-ICE ON) = 230 FEET (70 m) TOTAL TAKEOFF DISTANCE = 2,830 FEET (800 m)

NOTE FOR TAKEOFF FIELD LENGTH DETERMINATION, SINGLE ENGINE TAKEOFF DISTANCES ARE LONGER THAN TWO ENGINE TAKEOFF DISTANCES FACTORED BY 1.15.

MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FlGURE4G2.

GROSS

WEIGHT

(1000

ka) 14

13

12

11

40

-20

0

20 OAT (OC)

40

60

15

FIGURE FAA APPROVED:

NOV 07/90

14

GROSS

13

12

WEIGHT

11 (1,000

10 9 POUNDS)

4C-5 (continued)

PERFORMANCE

0

10 20 30 WIND (KNOTS)

0

1

2

RUNWAY SLOPE (PERCENT)

4c-7 4AC

METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON An estimate of the horizontal distance required to clear an obstacle up to 1,500 feet above the runway may be obtained by using Figures 4C-5 and 4C-6. The takeoff path is considered in two phases, as follows: (1) The distance from the start of the takeoff roll to 35 feet above the runway (Figure 4C-5). Both engines are assumed to operate normally to V1 speed, where one engine fails and the takeoff is continued on one engine. This phase is concluded when the airplane reaches 35 foot height at V2.

(2) Single Engine Climb at V2 (Figure 4C-6).

AIRCRAFT ROTATION

START OF TAKEOFF ROLL

TWO ENGINE TAKEOFF WITH ENGINE FAILURE AT V1, FLAPS 1/4

AFTER POSITIVE CLIMB IS ESTABLISHED, GEAR IS RETRACTED AND INOPERATIVE PROPELLER IS FEATHERED

MAINTAIN V2 CLIMB WITH 1/4 FLAPS AND GEAR RETRACTED UNTIL OBSTACLE IS CLEARED

ACCELERATE TO VYSE AND RETRACT FLAPS

VYSE

V2

LIFTOFF V1 SINGLE ENGINE TAKEOFF FLIGHT PATH TO 35 FOOT HEIGHT (FIGURE 4C–5)

OBSTACLE CLEARANCE BUT NOT LESS THAN 400 FEET

V2 35 FT. SINGLE ENGINE CLIMB GRADIENT AT V2 (FIGURE 4C–6)

SINGLE ENGINE CLIMB AT VYSE (FIGURE 4F–2)

EXAMPLE: Given:

OAT = 20oC AIRFIELD PRESSURE ALTITUDE = 1.400 FEET GROSS WEIGHT = 12,600 POUNDS (5715 kg) BLEED AIR ON

ENGINE ANTI-ICE OFF DRY POWER NO WIND LEVEL RUNWAY

Desired: TAKEOFF FLIGHT PATH DISTANCE TO 1,500 FOOT HEIGHT AFTER ENGINE FAILURE AT V1 Obtain:

(1) TAKEOFF DISTANCE TO 35 FOOT HEIGHT = 5,600 FEET (1705 m) (FIGURE 4C-5) (2) CLIMB DISTANCE: a. AVG HEIGHT = FIELD ELEVATION + HEIGHT INCREASE = 2,150 FEET (655 m) 2 b. ESTIMATED TEMPERATURE = 18oC (AT 2oC PER 1,000 FEET) c. NET CLIMB GRADIENT = 3.6 PERCENT (FIGURE 4C-6) d. DISTANCE = (100) x (1,500 – 35) = 40,695 FEET (12405 m) 3.6 (3) TOTAL FLIGHT PATH DISTANCE = (1) + (2) = 46,295 FEET (14110 m)

4C-8 4AC

PERFORMANCE

FAA APPROVED: NOV 07/90

METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT (continued) Figures 4C-5 and 4C-6 depend upon the following variable conditions. The appropriate charts must be used to ensure accuracy.

VARIABLE CONDITIONS: • Engine Anti-Ice – Off or On (Adjust distances as indicated by anti-ice effects graphs or notes for anti-ice On).

• V1 and V2 Speeds – From Figure 4B-15.

• Wind and Runway Gradient Effect on Takeoff Distance to 35 feet.

The charts are also based on the following common conditions: COMMON CONDITIONS: • • • • • •

Power – Dry with Bleed Air On Generator Load – 200 AMPS total.

Runway – Dry, Hard Surface.

No wind effect on V2 Climb Gradient.

Flaps – 1/4 until after reaching 400 feet AGL and clearing obstacles at V2; then up.

Propeller on inoperative engine – Windmilling in the NTS mode until it is feathered after attaining V2 speed.

NOTE The maximum takeoff weight (Figure 4C-2) and the flight paths constructed from Figures 4C-5 and 4C-6, can be realized using the following procedures:

1. At V1, rotate to takeoff attitude (approximately 10o nose up).

2. Once airborne, establish 5o of bank into operating engine.

3. After a positive rate of climb is indicated on the vertical speed indicator and the altimeter, retract the landing gear. This will occur at approximately 15 to 20 feet above the ground.

4. Climb and accelerate to the scheduled V2 speed.

5. Feather the propeller on the inoperative engine.

6. Maintain V2 speed to 400 feet AGL minimum or until obstacle clearance is assured.

7. Retract flaps and accelerate to best rate of climb speed.

FAA APPROVED: NOV 07/90

PERFORMANCE

4C-9 4AC

METRO Ill - ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE SINGLE ENGINE CLIMB GRADIENT

TO 1500 FOOT HEIGHT (continued) AT V, - DRY, BLEED AIR ON ASSOCLATED

CONDITIONS:

POWER ......... _. .... MAX CONTlNUWS PROPELLER ....... .._. FEATHERED ON INOPERATIVE ENGINE GEN LOAD ....... .._ .............. 2~ AMPS BLEED AIR ....... .._ ........................... ON ..... OFF (SEE NOTE) ENG ANTCICE..

V2 SPEED ....... ..I ....... FIGURE 48-15 GEAR ....... .._..................- ................. UP FLAPS. ........ I. ............... .._ ................ l/4 EXAMPLE: GIVEN:

OAT - 0% PRESSURE ALTINDE - 2.030 FEET GROSS WEIGHT - ll.WO POUNDS (4990 kg) OBTAIN: V2 SPEED - 103 KIAS GROSS CLIMB GRADIENT II 9.2 PERCENT DECREASE (ANTI-ICE ON) I -1.5 PERCENT GROSS CLIMB GRADIENT 7.7 PERCENT FLIGHT PATH DETERMINATION - -0.6 PERCENT NET CLIMB GRADIENT 6.9 PERCENT NOTE . REDUCE CLIMB GRADIENT BY 1.5 PERCENT GRADIENT WITH ENGINE ANTCICE ON.

s 20

. MAXIMUM

OAT

WITH

ENGINE

ANTI-ICE

* FOR FLIGHT PATH DETERMINATION GRADIENT BY 0.8 PERCENT GRADIENT.

GROSS

CLIMB

GRADIENT

GRADIENT

EQUALS

FIGURE 4c-10 4AC

IS 5%.

REDUCE

CLIMB

(PERCENT)

GNoTEy NET CLIMB

ON

GROSS

CLIMB

GRADIENT

4C-6

PERFORMANCE

FAA APPROVED:

NOV 07/90

METRO III - ICAO ANNEX 8 TWO

ENGINE

RATE

OF CIMB

AT V, - DRY, BLEED

AIR ON ASSOCIATED

CONDITIONS:

POWER . .._..... _ . . . . . . . . .._ TAKEOFF (DRY) GEN LOAD . . . . . I . . . . . . . .._.._.200 AMPS BLEED AIR . . . . . . _ . . . . . . . . . ..__.....I . . . . . . . ON ENG ANTI-ICE . . .._.. OFF (SEE NOTE) Vs SPEED . . . . . . . .._..... FIGURE 48-15 GEAR . . . . . . . .._.....................................

UP FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l/4

50

40 EXAMPLE: GIVEN:

30 OBTAIN:

20

OAT I -144: PRESSURE ALTITUDE I &Cal FEET GROSS WEIGHT I ll.WO POUNDS (4630 I@ Vs SPEED = 112 KIAS RATE OF CLIMB 2.700 FEET PER MINUTE DECREASE (ANTI-ICE ON) 460 FEET PER MINUUTE NET RATE OF CLIMB 2.660 FEET PER MINNUTE

* REDUCE RATE OF CLIMB BY 460 WITH ENGINE ANTCICE ON. .’ MAXIMUM

OAT

WITH

ENGINE

FEET

ANTCICE

PER

MINUTE

ON IS 5°C.

10

1,500 RATE

2,000

2,500

OF CLIMB

(FEET

3,000 PER

FIGURE FAA APPROVED:

NOV 07/90

3,500

4,000

4,500

5.001

MINUTE)

4C-7

PERFORMANCE

4c-11 4AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4C-12 4AC

PERFORMANCE

FAA APPROVED: NOV DATA 07/90 MANUFACTURER'S ISSUED: NOV 07/90