METRO III ICAO ANNEX 8 PART H – PERFORMANCE WHEN ENCUMBERED BY ICE ACCUMULATIONS CONTENTS ITEM
PAGE
Effects of Ice Accumulations .............................................................................................................. 4H-1 Procedures When Encumbered By Ice .............................................................................................. 4H-2 Weight to Achieve 1.2% Single Engine Climb Gradient ..................................................................... 4H-3 Single Engine Rate of Climb .............................................................................................................. 4H-4 Weight to Achieve 3.3% Balked Landing Climb Gradient .................................................................. 4H-5 Balked Landing Rate of Climb ........................................................................................................... 4H-6 Landing Distance Over 50 Foot Height B.F. Goodrich Single Rotor Brakes ........................................................................................... 4H-7 Goodyear Aerospace Dual Rotor Brakes .................................................................................. 4H-8 Landing Brake Energy Limits B.F. Goodrich Single Rotor Brakes ........................................................................................... 4H-9 Goodyear Aerospace Dual Rotor Brakes ................................................................................ 4H-10 Weight to Achieve 2.1% Single Engine Approach Climb Gradient .................................................. 4H-11
FAA APPROVED: MAY 22/89
PERFORMANCE
4H-i 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4H-ii 4MC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
METRO III ICAO ANNEX 8 EFFECTS OF ICE ACCUMULATIONS Flights of the METRO III were conducted in dry air with simulated ice shapes installed on the unprotected leading edges of the inboard wing sections, vertical stabilizer, and landing lights. The shapes represented the ice predicted to form on unprotected aerodynamic surfaces while holding for 45 minutes in continuous maximum (stratiform) or intermittent maximum (cumuliform) clouds containing supercooled droplets. Minor changes occurred in flight characteristics and significant changes occurred in performance of the aircraft following accumulation of ice on its unprotected surfaces. The following are based on the results of those METRO III flight tests: 1.
Ice shapes caused light, continuous airplane vibration throughout the speed range of the airplane as well as heavier, intermittent vibration similar to that encountered when flying in light turbulence.
2.
Ice shapes caused the stall avoidance system warning horn and pusher speeds to be slightly higher than normal. However, increasing landing approach speeds by 5 KIAS will provide sufficient maneuvering margin to preclude inadvertent stall warning horn or pusher actuation during landing.
3.
The increased drag caused by ice shapes caused cruise, enroute single engine climb, and all-engine balked landing climb performance to be reduced.
FAA APPROVED: MAY 22/89
PERFORMANCE
4H-1 4MC
METRO III ICAO ANNEX 8 PROCEDURES WHEN ENCUMBERED BY ICE Both unshed ice accumulations and bleed air extraction to operate engine anti-icing or environmental control systems contribute to loss of performance when operating in icing conditions. The flight test results indicate that the encumbered performance shown in Figures 4H-1 through 4H-9 and the following procedures are appropriate. 1.
When planning flights into known icing conditions, be aware of the potential performance reductions caused by requirements to extract bleed air for engine anti-icing and by accumulations of ice on unprotected parts of the aircraft.
2.
Use high RPM to improve ice shedding characteristics of the propellers.
3.
Consider unpressurized flight with bleed air switches off when experiencing performance degradations caused by flight in icing conditions.
4.
Unless the pilot can determine that there are no ice accumulations on the unprotected surfaces of the aircraft, use the landing approach speeds shown in Figures 4H-5 and 4H-6. Those figures include increased approach speeds and show the landing distances resulting from that increase in approach speeds. NOTE If ambient temperature at the destination airport is 8°C (47°F), or warmer, retention of accumulated ice in the traffic pattern is considered to be unlikely and neither increased approach speeds nor Figures 4H-3 through 4H-9 apply.
4H-2 4MC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III - ICAO ANNEX 8 WEIGHT TO ACHIEVE 1.2% SINGLE ENGINE WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CLIMB
GRADIENT
EXAMPLE:
CONDITIONS:
POWER .. .. ... .. ... .. ... .. .. MAX CONTINUOUS PROPELLER .... .. ... .. .. ... .. FEATHERED ON INOPERATIVE ENGINE GEN LOAD .. ... ... . .... .. ... .. ... .. ... .. .300 AMPS BLEED AIR .. .... . ... ... . .... ... .. .. ... .. ... .. .... ... .. ON ENG ANTI-ICE . ... .. ... .. ... ... .. .. ... ... ... .. ... ... ON CLIMB SPEED . .. .. V YSE (FIGURE 4H-2) GEAR .. .. .. ... .. ... .. ... ... ... . .... .. ... .. .. ... ... .. .... .. . UP FLAPS . .. .. ... .. ... .. ... ... .. .. ... ... . .... ... .. ... .. ... .. .. UP
GIVEN : OAT = -5°C PRESSURE ALTITUDE = 6,000 FEET OBTAIN : WEIGHT TO ACHIEVE 1.2% CLIMB GRADIENT = 13,060 POUNDS (5925 kg) VYSE CLIMB SPEED = 125 KIAS
15
6
9
)““1”“““““““““r’rrT’lr’T’l”“r’rlT’Tr’T’rTT”””””““l -40 -30 -50
8 -20
-10
0
10
20
OAT (OC) FIGURE 4H-1 FAA APPROVED:
MAY 22l89
PERFORMANCE
4H-3 4MC
METRO III - ICAO ANNEX 8 SINGLE ENGINE RATE OF CLIMB WHEN ENCUMBERED BY ICE ACCUMULA DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
T ‘IONS VYSE
CONDITIONS:
CLIMB
SPEED
SCHEDULE
(KIAS)
POWER .. .. . .. . .. .. . .. . .. MAX CONTINUOUS PROPELLER . . .. . .. . .. .. .. . FEATHERED ON INOPERATIVE ENGINE GEN LOAD . . .. . .. . .. .. . .. . .. . .. . .. . .. . 300 AMPS BLEED AIR . .. . .. . .. . .. .. . . .. .. .. . . .. . .. .. .. .. .. .. . . ON ENG ANTI-ICE .. . . .. . .. .. . .. . .. . .. .. .. . . .. . .. .. . . ON CLIMB SPEED . . .. . . .. .. . . SEE SCHEDULE GEAR . . .. . .. . .. . .. . .. .. . .. .. . . .. .. . .. . .. . .. .. . . .. .. . .. . . UP FLAPS .. . .. . .. .. . .. . .. . .. .. .. . . .. .. . .. . .. . .. . .. . .. . .. .. UP EXAMPLE: GIVEN:
OAT = -&C PRESSURE ALTITUDE = 13.000 FEET GROSS WEIGHT = 12,300 POUNDS (5550 CLIMB SPEED = 123 KIAS RATE OF CLIMB = 260 FEET PER MINUTE
OBTAIN:
kg)
NOTE
1
I
OBTAIN
OAT
FROM
IOAT
I (FIGURE
4B-2)
I
10
0
-10
s ;’ 8
-20
-30
40
-50
15
10 -1,000
-600
-600
400
-200
0 RATE
OF CLIMB
FIGURE 4H-4 4MC
200 (FEET
400
600
600
1,000
1,200
1,400
PER MINUTE)
4H-2
PERFORMANCE
FAA APPROVED:
MAY 22l89
METRO III - ICAO ANNEX 8 WEIGHT
TO ACHIEVE
3.3% BALKED
LANDING
CLIMB
GRADIENT
WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CONDITIONS:
POWER ...... ..... ... ... ...TAKEOFF (DRY) GEN LOAD ........................ 300 AMPS BLEED AIR .. ... ..... ..... ...................... ON ENG ANTI-ICE ............................... ON CLIMB SPEED ....SEE FIGURE 4H-4 GEAR ..................... .... ... .. ........... DOWN FLAPS ..................... ..... ... ... .... ... DOWN
EXAMPLE: GIVEN:
OAT = 6°C PRESSURE ALTITUDE = 6,800 FEET OBTAIN: GROSS WEIGHT = 13,080 POUNDS (5935 kg) CLIMB SPEED = 118 KIAS
FIGURE 4H-3 FAA APPROVED: MAY 22l89
PERFORMANCE
4H-5 4MC
METRO III - ICAO ANNEX 8 BALKED LANDING RATE OF CLIMB WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
EXAMPLE:
CONDITIONS:
GIVEN:
POWER . . .. . . ..._....... TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . .. . . 300 AMPS BLEED AIR _................................. ON ENG ANTI-ICE .. . . . . . . . . . . . . . . . . . . . . . . . . . . ON CLIMB SPEED . . . ..SEE SCHEDULE GEAR . . . . . . .. . . . . . . .. . . . .. . . . . . . . . . . . . . . . . . DOWN FLAPS . . . . . . . . . . . . . . .._................... DOWN BALKED GROSS
WEIGHT
OAT = -5°C PRESSURE ALTITUDE = 5,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 CLIMB SPEED = 118 KIAS RATE OF CLIMB = 910 FEET PER MINUTE
OBTAIN:
LANDING
CLIMB
SPEED
SCHEDULE
(KIAS) GROSS
(POUNDS)
kg)
WEIGHT
(kg)
14,000
13,000
12,000
11,000
10,000
6350
6000
5500
5000
4500
121
118
115
112
109
121
119
115
112
109
10
0
-
00
-10
r d
-20
-30
40
14
6
-200
0
200
400
600
800 RATE
OF CLIMB
FIGURE 4H-6 4MC
1,200
1,000 (FEET
1,400
1,600
1,800
2,000
2,200
PER MINUTE)
4H-4
PERFORMANCE
FAA APPROVED:
MAY 22189
LANDING DISTANCE OVER 50 FOOT HEIGHT WHEN ENCUMBERED BY ICE ACCUMULATIONS B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED
CONDITIONS:
EXAMPLE:
APPROACH SPEED . .._...._...._. SEE CHART POWER FLIGHT IDLE GEN LOAD . . . . . . . .. . . . . . . . . . . . . . . . AS REQUIRED BLEED AIR . . . . . . . . .. . . . . . . . . . . . . . . . . . ON OR OFF ENG ANTI-ICE . . . . . . . . . . . . .._........ ON OR OFF RUNWAY . . . . . . . . . . . . . . . . . . . . . . . . . . DRY, LEVEL, HARD SURFACE GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN BRAKING HEAVY DURING ROLLOUT ANTI-SKID . . ON OR OFF NOSE WHEEL STEERING . . ..ON OR OFF
GIVEN:
OBTAIN:
OAT = 0°C PRESSURE ALTITUDE = 6.000 F&ET GROSS WEIGHT = 12.600 POUNDS (5715 HEADWIND = 15 KNOTS APPROACH SPEED = 126 KIAS LANDING DISTANCE = 3.5M FEET (1075 ---j
kg)
m)
CAUTION]
DETERMINE THAT THE BRAKE ENERGY LIMIT NOT BE EXCEEDED FROM FIGURE 4H-7.
GROSS 6700
LANDING
-
SINGLE ENGINE LANDING DISTANCES ARE SHOWN AND, IN ALL CASES, ARE LONGER THAN TWO ENGINE LANDING DISTANCES.
*
IF APPLICABLE. SEE OPERATING RULES OBTAIN RECIUIRED FIELD LENGTH.
*
IF AMBIENT TEMPERATURE AT THE DESTINATION AIRPORT IS 6°C (47°F). OR WARMER, RETENTION OF ACCUMULATED ICE IS CONSIDERED UNLIKELY.
WILL
80,OO
WEIGHT 55po
GROUND
ROLL
NOTE IS 75%OF
.
LANDING
FOR
DISTANCE.
FACTORS
(kg) 50#00
45po
1600
TO
m -I =a 0
5.000
c)
2
D 0 D z z m x 00
800
9 4
600
40
-20
0
20 OAT
(OC)
40
60
14,000
13,000 GROSS
12,000 WEIGHT
11,000 (POUNDS)
10,000
0
10 WIND
20 (KNOTS)
30
LANDING DISTANCE OVER 50 FOOT HEIGHT WHEN ENCUMBERED BY ICE ACCUMULATIONS GOODYEAR AEROSPACE DUAL ROTOR BRAKES ASSOCIATED
EXAMPLE:
CONDITIONS:
APPROACH SPEED . . . . . . . . . . . . . . . . . SEE CHART POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3” GLIDE PATH POWER AS REQUIRED GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON OR OFF ENG ANTI-ICE ON OR OFF RUNWAY DRY, LEVEL, HARD SURFACE GEAR DOWN FLAPS . ..__._...._..............................,..... DOWN BRAKING HEAVY DURING ROLLOUT NOSE WHEEL STEERING . . . ..ON OR OFF
GIVEN:
OBTAIN:
OAT = 0°C PRESSURE ALTITUDE = 6.000 FEET GROSS WEIGHT = 12.600 POUNDS (5605 kg) HEADWIND = 15 KNOTS APPROACH SPEED = 127 KIAS LANDING DISTANCE = 2.9W FEET (665 m) -1
CAUTION
1
DETERMINE THAT THE BRAKE ENERGY LIMIT NOT BE EXCEEDED FROM FIGURE 4H-6.
WILL
GROSS
65,OO
60?0
WEIGHT
55clo
GROUND
ROLL
NOTE IS 71%OF
*
LANDING
LANDING
DISTANCE.
*
TWO ENGINE LANDING DISTANCES CREASE LANDING DISTANCE BY 72% OPERATION.
.
IF APPLICABLE, SEE OPERATINGRULES OBTAIN REQUIRED FIELD LENGTH.
-
IF AMBIENT TEMPERATURE AT THE DESTINATION AIRPORT IS 6°C (47°F). OR WARMER, RETENTION OF ACCUMULATED ICE IS CONSIDERED UNLIKELY.
ARE SHOWN. INFOR SINGLE ENGINE FOR
FACTORS
TO
(kg)
5qoo
45po
1600 5.000
0
3,000
2,500
600
OAT (OC)
GROSS
WEIGHT
(POUNDS)
WIND
(KNOTS)
8 5
& 6 4 z 4
D 0 D z z m x 00
LANDING BRAKE ENERGY LIMITS WHEN ENCUMBERED BY ICE ACCUMULATIONS B.F. GOODRICH SINGLE ROTOR BRAKES EXAMPLE: GIVEN:
OBTAIN:
OAT = -5°C PRESSURE ALTITUDE = 6,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 5 KNOTS MINIMUM REQUIRED HEADWIND = 3.5 KNOTS (BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED)
OPERATIONS EXCESSIVE THE BRAKE
WITH INSUFFICIENT HEADWINDS OR TAILWINDS WILL RESULT IN EXCEEDING ENERGY LIMIT OF 2,520,OOO FOOT POUNDS
c)
D 0 D z z
m x 00 OAT (OC)
MAXIMUM MINIMUM ALLOWABLE REQUIRED HEADWIND TAILWIND WIND (KNOTS)
LANDING BRAKE ENERGY LIMITS WHEN ENCUMBERED BY ICE ACCUMULATIONS GOODYEAR AEROSPACE DUAL ROTOR BRAKES EXAMPLE: GIVEN:
OBTAIN:
OAT = 0°C PRESSURE ALTITUDE = 6,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 5 KNOTS MAXIMUM ALLOWABLE TAILWIND = 2.5 KNOTS (BRAKE ENERGY LIMIT WILL NOT BE EXCEEDED)
OPERATIONS EXCESSIVE THE BRAKE
WITH INSUFFICIENT HEADWINDS OR TAILWINDS WILL RESULT IN EXCEEDING ENERGY LIMIT OF 2,8$0,000 FOOT POUNDS
3 m -I 3 0 0 D
0
D z z
m x 00
-40
30
20
10
0 OAT (OC)
-10
-20
-30
10
0
MAXIMUM ALLOWABLE TAILWIND
10 MINIMUM REQUIRED HEADWIND
WIND (KNOTS)
20
METRO III - ICAO ANNEX 8 WEIGHT TO ACHIEVE 2.1% SINGLE ENGINE APPROACH WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CONDITIONS:
POWER .................. ... ....... ........ ..... TAKEOFF (DRY) PROPELLER .. ... ..... ...................... FEATHERED ON INOPERATIVE ENGINE GEN LOAD ......................... ....... .... .... ... ..300 AMPS BLEED AIR ...... ..._................................................ON ENG ANTI-ICE ..............._.....................................ON CLIMB SPEEDS ........ SEE LANDING APPROACH SPEEDS (FIGURE 4H-5 OR 4H-6) GEAR .............. ... .... ........ ...... UP (APPROACH AND APPROACH CLIMB) FLAPS ................_.................l/4 (APPROACH AND APPROACH CLIMB)
EXAMPLE
CLIMB GRADIENT
:
GIVEN:
OAT = 5°C PRESSURE ALTITUDE = 5,500 FEET OBTAIN: GROSS WEIGHT = 10,900 POUNDS (4945 kg) CLIMB SPEED = 120 KIAS
AT WHICH A CLIMB GRADIENT EQUAL TO OR GREATER THAN 2.1% CAN BE MAINTAINED IN THE CONFIGURATION STATED ABOVE WITH ONE ENGINE INOPERATIVE.
14
13
12
11
10
9
FAA APPROVED: MAY 22/89
FIGURE 4H-9 PERFORMANCE
4H-11 4MC
METRO III ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4H-12 4MC
PERFORMANCE
FAA APPROVED: MAY DATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89