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220 Course > Limitations > Flashcards

Limitations Flashcards

(62 cards)

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1
Q

Certified to fly into icing up to

A

35000 ft

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2
Q

Maximum Ramp Weight (MRW) 101-124

A

68 039kgs

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3
Q

Maximum Takeoff Weight (MTOW) 101-124

A

67585

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4
Q
A
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5
Q

Maximum Landing Weight (MLW) 101-124

A

57833

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6
Q

Maximum Zero Fuel Weight (MZFW) 101-124

A

55111

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7
Q

Minimum Flight Weight (MFW) 101-124

A

36 287

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8
Q

Maximum Ramp Weight (MRW) 125-135

A

70 307

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9
Q

Maximum Takeoff Weight (MTOW) 125-135

A

69853

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10
Q
A
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11
Q

Maximum Landing Weight (MLW) 125-135

A

57833

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12
Q

Maximum Landing Weight (MLW) 125-135

A

55111

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13
Q

Flaps vfe

A

• FLAP 1: 230 KIAS
• FLAP 2: 210 KIAS
• FLAP 3: 210 KIAS
• FLAP 4: 190 KIAS
• FLAP 5: 170 KIAS

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14
Q

MAXIMUM LANDING GEAR OPERATING SPEED (VLO)

A

The maximum speed for landing gear extension is 250 KIAS.
The maximum speed for landing gear retraction is 220 KIAS

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15
Q

Turbulence Penetration Speed (VRA)

A

Maximum recommended airspeed for turbulence penetration in moderate to severe
turbulence is 265 KIAS (10000 feet and below) or 280 KIAS (above 10000 feet) or
0.75 Mach, whichever is lower.

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16
Q

Windshield Wiper Operation

A

250

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17
Q

Tire Limit Speed

A

195

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18
Q
A
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19
Q

Maximum airport pressure altitude for take-off and landing

A

10 000

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20
Q

Maximum operating altitude is

A

41000

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21
Q

Maximum/min ambient temperature approved for take-off and landing is

A

-54 to 52.5

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22
Q
A
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23
Q

Maneuvering Limit Load Factors

A

Flaps up: -1.0 g to 2.5 g
• Flaps down: 0.0 g to 2.0 g

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24
Q

Engine ice shedding (ground)

A

Engine ice shedding must be performed when the OAT is 3°C or below and
visible moisture in any form is present. Engine run-ups must be performed,
momentarily, to a minimum of 60% N1 and at intervals of not more than 30
minutes. The first run-up during taxi-out must be done as soon as practical.

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25
Engine ice shedding (in flight)
When operating for extended periods in icing conditions, engine vibrations may be encountered, even with the anti-ice on. A momentary increase in thrust, up to CLB thrust, should stop undesirable vibrations
26
Speed corrections for approach and landing in icing conditions with FLAP 5
During an approach and landing in icing conditions, or if there is evidence of ice accretion, VREF, VAC and VGA speeds must be increased by 5 KIAS
27
Runway Slopes
+/- 2%
28
Tail wind
The maximum tailwind component approved for takeoff is 15 knots. For tailwind components above 10 knots, refer to Standard Operating Procedures, Take-off, High Wind Procedure. The maximum tailwind component approved for landing is 15 knots. For tailwind components above 10 knots, refer to AOM 1.05.00, Take-Off and Landing with Tailwind Components Greater Than 10 Knots.
29
Pressurization Differential
The maximum positive differential pressure is 8.8 psid. The maximum negative differential pressure is -0.5 psid. During initial landing (at touchdown) the pressure differential must not exceed 1.0 psid.
30
Air-Conditioning
The doors should not be closed for more than 15 minutes when passengers are on board and the packs are off and no ground ventilation (LPGC), except for deicing operations, during which time with the packs off should be kept to a minimum. When OAT is above 40°C (104°F) operation without ECS or external cooling (LPGC) is limited to 30 minutes
31
Autopilot Engagement
The minimum height for engagement of autopilot is 400 feet AGL. The minimum height for use of autopilot is 80 feet AGL
32
Autothrottle
During an approach and landing with autothrottle, the approach speed must be increased by 5 kts.
33
Data Link FANS-1/A+ Use of the ALTITUDE selection on the WHEN CAN WE page
Prohibited
34
Maximum altitude with slats/flaps extended is
20000 ft
35
Flight Spoilers
Minimum height with flight spoilers manually extended is 500 ft AGL. Minimum speed with flight spoilers manually extended is VREF + 10 KIAS.
36
The maximum permissible fuel imbalance between the contents of the left and right tank is
454kg
37
The minimum fuel quantity for go-around
442 kg per wing a maximum airplane climb attitude of 10 degrees nose up
38
39
Main tank volume
3770 L or 3050 kgs
40
Centre tank volume
13968 L or 11300 kgs
41
Total fuel volume
21508L 17400kgs
42
The maximum allowable brake temperature (BTMS) for take-off
6 units
43
Maximum brake temperature (BTMS) for gear retraction is
13 units
44
FMS navigation at latitudes
north of 73°N and south of 60°S is prohibited
45
Operation using QFE altimeter setting is
Prohibited
46
Reduced Vertical Separation Minima (RVSM
Autopilot Must be operational Altitude alerting system Must be operational Altitude reporting transponder One (1) must be operational Air data computers Two (2) must be operational
47
Takeoff and Landing Awareness Function (TLAF)
When proceeding onto the departure runway do not exceed 35 knots ground speed or 55% N1 until within 10 degrees of the runway heading.
48
APU Type
Honeywell 131-9(C)
49
APU Start
The minimum oil temperature for an APU start is −40°C. Do not perform more than three starts / start attempts in one hour. A two-minute delay must be observed between start attempts
50
The altitude limit for APU bleed air extraction is
23000ft
51
Maximum wind for passenger and cargo door operation
The maximum wind speed for door operation (opening/closing) is 40 kts. The maximum wind speed for the door held in the open position is 65 kts
52
Engines
PurePower™ PW1524G-3
53
-20 to -40
If turnaround time exceeds 120 minutes, the thrust reversers must be cycled two times before take-off on contaminated runways: take-off must be initiated within 5 minutes after the last thrust reverser cycle. If the take-off is not initiated within 5 minutes after the last thrust reverser cycle, the two thrust reverser cycles must be repeated
54
Less than −40°C
If turnaround time exceeds 120 minutes, the thrust reversers must be cycled before take-off on contaminated runways until the last deployment cycle time is equal to or less than 2.5 seconds. [2] Take-off must be initiated within 2 minutes after the last thrust reverser cycle. If the take-off is not initiated within 2 minutes after the last thrust reverser cycle, the thrust reverser cycles must be repeated.
55
Engine Start
After three start attempts, or after four minutes continuous cranking, a 30-minute cooling period is required. Do not engage the starter on ground if indicated N2 rpm exceeds 20%
56
Engine Shutdown
Engine Shutdown The engine must be operated at or near idle for a minimum 3 minutes (cumulative) (5 minutes recommended) before shutdown. Taxi time may be counted when thrust is at or near idle. This does not apply to non-normal shutdowns. Near idle is defined as up to 40% N1. An additional period equal to or greater than the time spent above 40% N1 must be accounted fo
57
Starting on ground crosswind limits
Maximum crosswind component 43kts Maximum tailwind component 18kts (Same for 60 % ice shedding
58
59
Oil consumption
.38 L/h
60
Above 29100 feet, the maximum N1 i
95.2%
61
When the HMU is inoperative, any exceedance of more than
40 seconds must be reported
62
Ground fog limit
-18 c

220 Course (4 decks)

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