16 f 8 performance standard reference parte g

METRO III – ICAO ANNEX 8 PART G – APPROACH AND LANDING PERFORMANCE CONTENTS ITEM

PAGE

Maximum Landing Weight Limitation Chart Bleed Air On .............................................................................................................................. 4G-2 Bleed Air Off .............................................................................................................................. 4G-3 Balked Landing Rate of Climb – Bleed Air On Dowty Rotol Propellers .............................................................................................................. 4G-4 McCauley Propellers ................................................................................................................. 5G-5 Two Engine Landing Distance Over 50 Foot Height .......................................................................... 4G-6 Landing Brake Energy Limits ............................................................................................................. 4G-7

FAA APPROVED: MAY 22/89

PERFORMANCE

4G-i 8AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4G-ii 8AC

PERFORMANCE

MANUFACTURER'S DATA ISSUED: MAY 22/89

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

MANUFACTURER'S DATA FAA APPROVED: MAY 22/89 ISSUED: MAY 22/89

PERFORMANCE

4G-1 8AC

METRO III -ICAO MAXIMUM ASSOCIATED

LANDING

WEIGHT

LIMITATION

CONDITIONS:

POWER .......... .... ............... ............ TAKEOFF (DRY) PROPELLER .. ..... ... ..... ...... ........... FEATHERED ON INOPERATIVE ENGINE GEN LOAD ...... ....................................... 300 AMPS BLEED AIR .. ..... ... ..... .. ..... ... ... .. .............. ..............ON ENG ANTI-ICE .. ...._....................OFF (SEE NOTE) CLIMB SPEEDS ..... SEE LANDING APPROACH SPEEDS (FIGURE 4G-5) GEAR ................. ........ ..... .. ... UP (APPROACH AND APPROACH CLIMB) FLAPS .. ........ ........................ l/4 (APPROACH AND APPROACH CLIMB)

CHART

ANNEX 8

- BLEED

EXAMPLE

AIR ON

:

GIVEN:

OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: MAX LANDING WEIGHT = 13,560 POUNDS

l

l

l

(6160 kg)

REDUCE MAXIMUM LANDING WEIGHT BY 1,200 POUNDS (544 kg) WITH ENGINE ANTI-ICE ON. MAXIMUM

OAT WITH ENGINE ANTI-ICE ON IS 5°C.

THIS WEIGHT RESULTS IN A MAXIMUM LANDING WEIGHT AT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER THAN 2.1% CAN BE MAINTAINED IN THE CONFIGURATION STATED ABOVE WITH ONE ENGINE INOPERATIVE. 17

16 7

FIGURE 4G-1 4G-2 8AC

PERFORMANCE

FAA APPROVED: MAY 22l89

METRO III -ICAO ANNEX 8 MAXIMUM

LANDING WEIGHT LIMITATION

ASSOCIATED

CONDITIONS:

CHART - BLEED AIR OFF EXAMPLE

POWER .. ........ ............................... TAKEOFF (DRY) PROPELLER .. .... ... ..... .................. FEATHERED ON INOPERATIVE ENGINE GEN LOAD ............................................. 300 AMPS BLEED AIR ................................. ....................... OFF ENG ANTI-ICE ...... .... .. .. ... .. ...... ..OFF (SEE NOTE) CLIMB SPEEDS ........ SEE LANDING APPROACH SPEEDS (FIGURE 4G-5) GEAR ...................... ....... ... ... UP (APPROACH AND APPROACH CLIMB) FLAPS .. .... .... .. ...................... 114 (APPROACH AND APPROACH CLIMB)

:

GIVEN:

OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: MAX LANDING WEIGHT = 14,490 POUNDS (6575 kg)

l

l

l

NOTE REDUCE MAXIMUM LANDING WEIGHT BY 1,050 POUNDS (475 kg) WITH ENGINE ANTI-ICE ON. MAXIMUM

OAT WITH ENGINE ANTI-ICE

ON IS 5°C.

THIS WEIGHT RESULTS IN A MAXIMUM LANDING WEIGHT AT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER THAN 2.1% CAN BE MAINTAINED IN THE CONFIGURATION STATED ABOVE WITH ONE ENGINE INOPERATIVE.

17

16

5

FIGURE 4G-2 FAA APPROVED: MAY 22l89

PERFORMANCE

4G-3 8AC

METRO Ill -ICAO ANNEX 8 BALKED LANDING RATE OF CLIMB - BLEED AIR ON DOWTY ROTOL PROPELLERS ASSOClATED

CONDITIONS:

POWER . . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . .. . . . . . . . . . . . . . . . . . . 3W AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE . . . . . . . OFF (SEE NOTE) CLIMB SPEED .._...... SEE SCHEDULE GEAR . . . . . . . _ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN FLAPS . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DDWN EXAMPLE: GIVEN: OBTAIN:

OAT - 10-C PRESSURE ALTITUDE - 4.C0J FEET GROSS WEIGHT - 14.500 POUNDS (6580 kg) CLIMB SPEED - 103 KIAS RATE OF CLIMB - 1.040 FEET PER MINUTE

NOTE - REDUCE RATE OF CLIMB BY 330 WITH ENGINE ANTCICE ON. * MAXIMUM

OAT BALKED

WITH

ENGINE

LANDING SCHEDULE

FEET

ANTCICE CLIMB (KIAS)

PER

MINUTE

ON IS 5°C.

SPEED

GROSS WEIGHT (kg) 7006 6500

RATE

OF CLIMB

(FEET

PER

MINUTE)

FIGURE 4G-3 4G-4 8AC

PERFORMANCE

FAA APPROVED: MAY 22l89

METRO III - ICAO ANNEX 8 BALKED LANDING RATE MCCAULEY PROPELLERS

OF CLIMB

-

BLEED

AIR ON ASSOCIATED

CONDITIONS:

(DRY) POWER . . . . ..__........_... TAKEOFF GEN LOAD _........___......._..... 300 AMPS BLEED AIR . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE _..... OFF (SEE NOTE) CLIME SPEED ._...... SEE SCHEDULE GEAR . . . . .. . . . . ..______....................... DOWN FLAPS .._.___.........____................... DOWN EXAMPLE: GIVEN:

OBTAIN:

OAT = 10°C PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT =14,500 POUNDS (6560 kg) CLIMB SPEED = 103 KIAS RATE OF CLIMB = 995 FEET PER MINUTE

l

REDUCE

l

MAXIMUM

PATE

OAT WITH BALKED

600

800 RATE

OF CLIMB

1,000

1,400

1,200

(FEET

PER

MAY 22189

1,600

2,000

BY 290

ENGINE

LANDING SCHEDULE

FEET

ANTI-ICE CUMB (KIAS)

PER

MINUTE

ON IS 5%.

SPEED

2,200

MINUTE)

FIGURE FAA APPROVED:

1,600

OF CLIMB

4G-4

PERFORMANCE

4G-5 8AC

4G-6 8AC

TWO ENGINE LANDING DISTANCE OVER 50 FOOT HEIGHT ASSOCIATED CONDITIONS:

EXAMPLE:

APPROACH SPEED ................ SEE CHART POWER .............................. 3o GLIDE PATH POWER AS REQUIRED GEN LOAD ........................... AS REQUIRED BLEED AIR ............................ AS REQUIRED ENG ANTI-ICE ....................................... OFF RUNWAY .................................. DRY, LEVEL, HARD SURFACE GEAR ................................................... DOWN FLAPS ................................................. DOWN BRAKING ......... HEAVY DURING ROLLOUT NOSE WHEEL STEERING ..... ON OR OFF

OAT = 18oC PRESSURE ALTITUDE = 7,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 15 KNOTS OBTAIN: APPROACH SPEED = 115 KIAS LANDING DISTANCE = 3,150 FEET (960 m)

CAUTION

GIVEN:

DETERMINE THAT THE BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED FROM FIGURE 4G-6.

NOTE • LANDING GROUND ROLL IS 67% OF LANDING DISTANCE.

7000

GROSS WEIGHT (KILOGRAMS) 6500 6000 5500

5000

D

ITU

1200

RE

U

SS

E PR

T AL

4,000

00

8,0

00 0

0 4,0

1000 ISA

00

2,0

EL

3,000

EV

AL

SE

ISA

IL

2,500

TA

FAA APPROVED: MAY 22/89 REVISED: MAR 26/95

0

–3

800

3,500

+40

6,0

2,000

600 HE

AD

118

116

114

112

110

108

106

104

102

100

1,500

APPROACH SPEED (KIAS) (ASSUMES NO INSTRUMENT ERROR)

400

–40

–20

0

20 OAT (oC)

40

60 16,000

15,000 14,000 13,000 12,000 GROSS WEIGHT (POUNDS)

11,000

10,000 0

1,000 10 20 30 WIND (KNOTS)

LANDING DISTANCE OVER 50 FOOT HEIGHT (FEET)

)

ET

FE E(

4,500

ISA

FIGURE 4G-5

PERFORMANCE

LANDING DISTANCE OVER 50 FOOT HEIGHT (METERS)

1400

REFERENCE LINE

REFERENCE LINE

5,000

METRO III – ICAO ANNEX 8

• IF APPLICABLE, SEE OPERATING RULES FOR FACTORS TO OBTAIN REQUIRED FIELD LENGTH.

FAA FAA APPROVED: APPROVED: MAY MAY 22/89 22/89 REVISED: MAR 26/95

LANDING BRAKE ENERGY LIMITS EXAMPLE: CAUTION

OAT = 18oC PRESSURE ALTITUDE = 7,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 15 KNOTS OBTAIN: MAXIMUM ALLOWABLE TAILWIND = 1.0 KNOT (BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED) GIVEN:

OPERATIONS WITH INSUFFICIENT HEADWINDS OR EXCESSIVE TAILWINDS WILL RESULT IN EXCEEDING THE BRAKE ENERGY LIMIT OF 2,820,000 FOOT POUNDS (3864000 Nm) PER BRAKE.

ET)

(FE

IS

(kg)

P

A

72 0( ,00 16

0(

68

60

05

)

)

50) (63

,00 15

(59

00)

000 14,

000

SS

13,

OUN

00 (

T, P WE

EL

LEV

ISA

GRO

SEA

12,0

A

IGH

IS

FIGURE 4G-6

0

–3

PERFORMANCE

0

2,00

0)

0

DS

+4

0

4,00

544

0

6,00

40

–30

–20

–10

0

10 OAT (oC)

20

30

40

50

60

–15

–10 0 10 20 MAXIMUM MINIMUM ALLOWABLE REQUIRED TAILWIND HEADWIND WIND (KNOTS)

METRO III – ICAO ANNEX 8

UDE LTIT A E 0 SUR 8,00 RES

4G-7 8AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4G-8 8AC

PERFORMANCE

MANUFACTURER'S FAA APPROVED: MAY DATA 22/89 ISSUED: MAY 22/89