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 Dowty Rotol Propellers .............................................................................................................. 4H-5 McCauley Propellers ................................................................................................................. 4H-6 Weight to Achieve 2.1% Single Engine Approach Climb Gradient .................................................... 4H-7 Balked Landing Rate of Climb Dowty Rotol Propellers .............................................................................................................. 4H-8 McCauley Propellers ................................................................................................................. 4H-9 Two Engine Landing Distance Over 50 Foot Height ........................................................................ 4H-10 Landing Brake Energy Limits ........................................................................................................... 4H-11
FAA APPROVED: MAY 22/89
PERFORMANCE
4H-i 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4H-ii 8AC
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 occured 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, using the landing approach speeds shown in Figure 4H-8 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 allengine balked landing climb performance to be reduced.
FAA APPROVED: MAY 22/89
PERFORMANCE
4H-1 8AC
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 Figure 4H-8. This figure includes increased approach speeds and shows 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 8AC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III -ICAO WEIGHT TO ACHIEVE 1.2% SINGLE ENGINE WHE’N ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CLIMB
CONDITIONS:
ANNEX 8
GRADIENT
EXAMPLE:
POWER .. .. ... .. ... .... .. ... MAX CONTINUOUS PROPELLER .. .. .. ... .. .... .. . FEATHERED ON INOPERATIVE ENGINE GEN LOAD . ... .. ... .. .. .... ... .. ... ... .. .300 AMPS BLEED AIR . ... .. ... .. .... ... .. ... .. ... .. .. ... .... ... .. ON ENG ANTI-ICE ... ... ... .. .. ... ... ... .. .... .. .. ... ... ON CLIMB SPEED .. ...VySE (FIGURE 4H-2) GEAR .. .. .. ... .. ... .. .... .. ... .. ... .. ... .. ... .. .... ... .. .. . UP FLAPS ... .. ... .. ... .. ... ... .. ... ... .. ... .. ... ... ... . .... .. . UP
GIVEN
: OAT = -5OC PRESSURE ALTITUDE = 6,000 FEET OBTAIN : WEIGHT TO ACHIEVE 1.2% CLIMB GRADIENT = 13,060 POUNDS (5925 kg) VySE CLIMB SPEED = 126 KIAS
'16
6
-50
40
-30
-20 OAT (OC)
FIGURE FAA APPROVED:
MAY 22f89
-10
0
10
4H-1
PERFORMANCE
4H-3 8AC
METRO SINGLE
ENGINE
RATE
III -LAO
ANNEX
8
OF CLIMB
WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CONDITIONS:
VYSE
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
CLIMB
SPEED
SCHEDULE
(KIAS)
~!
EXAMPLE: GIVEN: OBTAIN:
OAT = -5°C PRESSURE ALTlTUDE = 6,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) CLIMB SPEED = 132 KIAS RATE OF CLIMB = -120 FEET PER MINUTE OBTAIN
NOTE OAT FROM IOAT
(FIGURE
48-2)
10
0
” ;r 5
-20
-50
10 -1,200
-1,000
-800
-600
400
-200 RATE OF CLIMB
0
200
400
600
BOO
1,000
1,200
(FEET PER MINUTE)
FIGURE 4H-2 4H-4 8AC
PERFORMANCE
FAA APPROVED: MAY 22l89
METRO III -lCAO
ANNEX 8
WEIGHT TO ACHIEVE 3.3% BALKED LANDING CLIMB GRADIENT WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON DOWTY ROTOL PROPELLERS ASSOCIATED
CONDITIONS:
POWER .................... TAKEOFF (DRY) GEN LOAD ........................300 AMPS BLEED AIR ..................................... ON ENG ANTI-ICE ............................... ON CLIMB SPEED.. ..SE E FIGURE 4H-6 GEAR.. ....................................... DOWN FLAPS ....................................... DOWN
EXAMPLE: GIVEN:
OAT = 6°C PRESSURE ALTITUDE = 6,600 FEET OBTAIN: GROSS WEIGHT = 13,200 POUNDS (5990 kg) CLIMB SPEED = 116 KIAS
16
FIGURE 4H-3 FAA APPROVED: MAY 22/89
PERFORMANCE
4H-5 8AC
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 MCCAULEY PROPELLERS ASSOCIATED
CONDITIONS:
POWER . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . .. . . . . . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE .. . .. . . . .. . . . . . . . . . . . . . . . . . . . . . ON CLIMB SPEED . . ..SEE FIGURE 4H-7 GEAR . . . .. . . . . . . .. . .._.._..................... DOWN FLAPS . . . . . . . . . . . . . . . .._..................... DOWN
EXAMPLE: GIVEN: OBTAIN:
OAT = 6°C PRESSURE ALTITUDE = 6,800 FEET GROSS WEIGHT = 13,000 POUNDS (5900 CLIMB SPEED = 118 KIAS
kg)
16
4H-6 8AC
FIGURE 4H-4 PERFORMANCE
FAA APPROVED: MAY 22189
METRO III -ICAO WEIGHT TO ACHIEVE 2.1% SINGLE ENGINE WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON ASSOCIATED
CONDITIONS:
APPROACH
EXAMPLE
POWER . . . . . . . . . . . . . . . . . .. . . . . . . .. . . . .. . .. . .. .. . TAKEOFF (DRY) PROPELLER . . . . . . .. . . . . . . .. . .. . . . .. . .. . . . .. FEATHERED ON INOPERATIVE ENGINE GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . .. . . . 300 AMPS BLEED AIR . . .. . .. . . . .. . .. . . . .. . . . . . . .. . . . . . . . . . .. . .. . . . . . .. . . . . . . .. ON ENG ANTI-ICE . . . . . . .. . . . .. . .. . . . .. . .. . . . .. . .. . . . . . . .. . .. .. . . . . .. .. ON APPROACH CLIMB SPEEDS . . . . .. .. SEE LANDING SPEEDS (FIGURE 4H-81 GEAR . . . . . . . . . . . . . . . . . . . . . .. . . . . .. .. . . . . UP (AP‘PROACH ANd APPROACH CLIMB) FLAPS . . . . . . . .. . .. . . . .. . .. . . . .. . . . . . . . . . l/4 (APPROACH AND APPROACH CLIMB)
ANNEX 8
GIVEN: OBTAIN:
CLIMB
GRADIENT
: OAT = 3°C PRESSURE ALTITUDE = 6,600 FEET GROSS WEIGHT = 10,540 POUNDS (4780 CLIMB SPEED = 119 KIAS
kg)
NOTE
1
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.
16
FIGURE FAA APPROVED:
MAY 22/89
4H-5
PERFORMANCE
4H-7 8AC
METRO III -ICAO
ANNEX 8
BALKED LANDING RATE OF CLIMB WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON DOWTY ROTOL PROPELLERS ASSOCIATED
EXAMPLE:
CONDITIONS:
POWER . . .. . . . .. . .. . . . .. TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG ANTI-ICE CLIMB SPEED . . . ..SEE SCHEDULE GEAR . . . . . . . . . . . .. . . . . . . .. .. . . . . . . . . . . . . . . . DOWN FLAPS . . . . . . . . . . . . . . . . . .. . . . .. . .. . . . .. . . . . DOWN BALKED GROSS 15,500 125
14,500 122
WEIGHT 13,500 119
GIVEN:
OAT = -5°C PRESSURE ALTITUDE = 5,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 CLIMB SPEED = 124 KIAS RATE OF CLIMB = 570 FEET PER MINUTE
OBTAIN:
LANDING
CLIMB
SPEED
SCHEDULE
116
(KIAS) WEIGHT
(kg)
7000
6500
GROSS
6000
5500
5000
4500
125
122
119
115
112
109
(POUNDS) 12,500
11,500
10,500O
113
kg)
110
16 7
RATE
OF CLIMB
FIGURE 4H-8 8AC
(FEET
PER MINUTE)
4H-6
PERFORMANCE
FAA APPROVED:
MAY 22/89
METRO III -ICAO
ANNEX 8
BALKED LANDING RATE OF CLIMB WHEN ENCUMBERED BY ICE ACCUMULATIONS DRY, BLEED AIR ON, ANTI-ICE ON MCCAULEY PROPELLERS ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER .......... .. .. ... TAKEOFF (DRY) GIVEN: OAT = -5°C GEN LOAD ..... ................ 300 AMPS PRESSURE ALTITUDE = 5,000 FEET BLEED AIR ......_...........................ON GROSS WEIGHT = 15,000 POUNDS (6805 kg) ENG ANTI-ICE ... ....... .... ... .... .. .....ON OBTAIN: CLIMB SPEED = 124 KIAS CLIMB SPEED .....SEE SCHEDULE RATE OF CLIMB = 530 FEET PER MINUTE GEAR ................................ ..... . DOWN FLAPS ...... .............................. DOWN BALKED LANDING CLIMB SPEED SCHEDULE (KIAS) 15,500 125
GROSS WEIGHT (POUNDS) 14,500 13,500 12,500 11,500 122 119 116 113
lo,5000 110
7000 125
GROSS WEIGHT (kg) 6500 6000 5500 122 119 115
5000 112
4500 109
10
16 7 15
14
-200
0
200
FAA APPROVED: MAY 22i89
400
600 800 1,000 1,200 RATE OF CLIMB (FEET PER MINUTE)
FIGURE 4H-7 PERFORMANCE
1,400
1,600
1,800
2,000
4H-9 8AC
TWO ENGINE LANDING DISTANCE OVER 50 FOOT HEIGHT WHEN ENCUMBERED BY ICE ACCUMULATIONS ASSOCIA~D
EXAMPLE:
CONDITIONS:
APPROACH SPEED .. .... ...... .... . SEE CHART POWER .,............................. 3” GLIDE PATH POWER AS REQUIRED GEN LOAD . .... .... .. .... .... .... .... AS REQUIRED BLEED AIR . .... .... .. .... .... .... .... AS REQUIRED ENG ANTI-ICE .. .... ..... .... ..... .... .... ..... ..... .... ON 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,ooO FEET GROSS WEIGHT - 15.000 POUNDS (6605 k9) HEADWIND - 15 KNOTS APPROACH SPEED I 134 KIAS LANDING DISTANCE - 3,900 FEET (1190 m) {CAUTION
zm
1
DETERMINE THAT THE BRAKE ENERGY LIMIT WILL NOT SE EXCEEDED FROM FIGURE 4H-9.
7000
6500
GROSS WEIGHT 6000
(k9) 5500
-I za 0
5000
0 D
Z Z
m x 00
OAT (“C,
GROSS
WEIGHT
(POUNDS)
WIND
(KNOTS)
LANDING
BRAKE
ENERGY
WHEN ENCUMBERED
LIMITS
BY ICE ACCUMULATIONS
EXAMPLE: GIVEN:
OAT = 0°C PRESSURE ALTITUDE = 6,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 15 KNOTS OBTAIN: MINIMUM REQUIRED HEADWIND = 16 KNOTS (BRAKE ENERGY LIMIT WILL BE EXCEEDED. REDUCE LANDING WEIGHT TO AVOID EXCEEDING BRAKE ENERGY LIMIT.)
EXCESSIVE TAILWINDS WILL RESULT IN EXCEEDING THE BRAKE ENERGY LIMIT OF 2,850,OOO FOOT POUNDS
xm
II =a 0 -I 0
0 D z z m x 00 -30
-20
-10
0 OAT (OC)
10
20
30
10 MAXIMUM ALLOWABLE TAILWIND
0
10
MINIMUM REQUIRED HEADWIND WIND (KNOTS)
20
METRO III – ICAO ANNEX 8
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4H-12 8AC
PERFORMANCE
MANUFACTURER'S FAA APPROVED: MAY DATA 22/89 ISSUED: MAY 22/89