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Challenger CL604/605 renamed > CL605 Limitations > Flashcards

CL605 Limitations Flashcards

1
Q

Max take off weight

A

48200 lbs

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2
Q

Max ramp/taxi weight

A

48300 lbs

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3
Q

Max landing weight

A

38000 lbs

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4
Q

Max zero-fuel weight

A

32000 lbs

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5
Q

Max airport pressure altitude for take-off and landing

A

10,000 feet

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6
Q

Max operating altitude

A

41,000 feet

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7
Q

Max OAT for take-off and landing

A

ISA +35

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8
Q

Min OAT for take-off

A

-40º C

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9
Q

Max tailwind for take-off and landing

A

10 knots

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10
Q

Max crosswind to use reverse thrust

A

24 knots

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11
Q

Max Flaps-up load factors

A

-1.0 G to +2.5 G

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12
Q

Max flaps-down load factors

A

0.0 G to 2.0 G

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13
Q

Max glide-path angle at or below 1500 feet above touch-down zone elevation

A

4.49º

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14
Q

Max altitude for flaps use

A

15,500 feet

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15
Q

Max gear extend or retract speed (VLO)

A

197 knots / M0.6

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16
Q

Max speed with gear down and locked

A

250 knots / M0.7

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17
Q

Max gear-down altitude

A

20,000 feet

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18
Q

Tyre speed limit

A

182 knots

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19
Q

Turbulence penetration speed

A

280 knots / M0.75

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20
Q

Max RVSM speed

A

M0.83

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21
Q

Flap 20º limiting speed

A

231 knots

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22
Q

Flap 30º limiting speed

A

197 knots

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23
Q

Flaps 45º limiting speed

A

189 knots

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24
Q

Max runway slope

A

± 2%

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25
Q

Fuel quantity - main tanks

A

4860 lbs each

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26
Q

Fuel quantity - Aux tank

A

7168

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27
Q

Fuel quantity - Tail tank

A

3112 lbs

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28
Q

Max fuel imbalance between wing tanks - cruise

A

800 lbs

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29
Q

Max fuel imbalance between wing tanks - Taxi / take-off / landing

A

400 lbs

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30
Q

Take-off with <500 lbs of fuel in the Aux tank. How much must there be in the Main tanks and Tail tank?

A

1500 lbs in each Main tank and nothing in the Tail tank.

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31
Q

Flap setting and conditions for fuel jettison

A

0º, No lightning.

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32
Q

Min bulk fuel temperature for take-off

A

5º C

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33
Q

Min autopilot use altitude - Take-off

A

320 feet

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34
Q

Min autopilot altitude for visual/non-precision approach

A

320 feet

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35
Q

Min autopilot altitude use for a precision approach - Glide-path 3.5º or less

A

80 feet

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36
Q

Min autopilot altitude for a precision approach with a glide-path of 3.6º-4.49º

A

160 feet

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37
Q

Aircraft max relief differential pressure

A

9.2 psi

38
Q

Aircraft max negative differential pressure

A

-0.5 psi

39
Q

Max aircraft differential pressure - taxi / take-off / landing

A

0.2 psi

40
Q

Altitude above which one ACU or cowl anti-ice must be selected on for each engine

A

40,000 feet

41
Q

Max AC main generator loading: 0 - 35,000 feet

A

30 kva

42
Q

Max main AC generator load: > 35,000 feet

A

25 kva

43
Q

Max APU generator load up to 20,000 feet

A

30 kva

44
Q

Max load on TRUs

A

100 amps

45
Q

Limitations for flight spoiler use in flight

A

No use below 300 feetNo use below Vref + 10

46
Q

Taxi light limitation when aircraft stationary

A

Off after 10 minutes

47
Q

APU Max EGT on start

A

974º C

48
Q

Max APU EGT

A

731º C

49
Q

APU max RPM

A

110 %

50
Q

rpm that APU auto-shut down occurs

A

107 %

51
Q

Min temp for APU start

A

-40º C

52
Q

Max alt for APU start

A

20,000 feet

53
Q

Max speed for APU start

A

290 knots

54
Q

Max altitude for APU bleed air extraction

A

15,000 feet

55
Q

Max altitude for in-flight engine start with APU (double engine failure only)

A

15,000 feet

56
Q

If both engines started with APU: Max rpm for operating engine

A

70 % N2

57
Q

APU start cycles using APU battery

A

3 attempts of 30 seconds cranking, then 20 minutes rest. 2 further attempts of 30 seconds cranking, then 35 minutes rest before further attempts

58
Q

APU start cycles using ground power

A

2 attempts of 15 seconds cranking, then 20 minutes rest. 2 further attempts of 15 seconds cranking, then 35 minutes rest before further attempts

59
Q

APU hung start definition

A

not more than 30 % rpm within 60 seconds

60
Q

Cold soaked aircraft > 8 hours: first flight of the day if temp is < -30º C

A
  1. Motor engines for 60 seconds and confirm N1 rotation before start. 2. Reversers must be actuated until the deploy and stow cycles are less than 5 seconds
61
Q

Engine oil max consumption

A

0.2 quarts or 0.05 US gallons per hour

62
Q

Max engine oil refill before dry motoring is necessary

A

2 quarts

63
Q

Min steady state oil pressure

A

25 psi

64
Q

Min oil pressure at take-off power

A

45 psi

65
Q

Max continuous engine oil pressure

A

115 psi

66
Q

Max transient engine oil pressure after a cold start

A

156 psi (130 psi at idle - max 10 mins). AFM 02-05-2

67
Q

Min oil temp for engine start

A

-40º C

68
Q

Max continuous oil temp

A

+155º C

69
Q

Max permissible oil temp

A

+163º C (15 mins)

70
Q

Engine start: fuel introduction limitations - ground start

A

ITT < 120º C and N2 > 20%

71
Q

Engine starter cranking cycle limits (ground and air)

A

Starter not to be used if N2 is above 55% 3 consecutive start cycles, then 5 minutes cooling between additional cycles

72
Q

Engine start: fuel introduction limitations - starting in the air using starter

A

ITT < 90º CN2 <55%N2 >28%

73
Q

Engine start: fuel introduction limitations - windmill start below 10,000 feet

A

N2 greater than 10%

74
Q

Engine start: fuel introduction limitations - windmill start above 10,000 feet

A

N2 greater than 12%

75
Q

Dry motoring limitations (ignition off, thrust levers at shut-off)

A

First cycle - 90 seconds max, then 5 minutes off. Subsequent cycles - 30 seconds max, than 5 minutes off.

76
Q

Icing conditions on the ground: Cowl anti-ice limitations

A

OAT is below +10º C and visible moisture/ contaminated surface

77
Q

Icing conditions on the ground: Wing anti-ice limitations

A

Wing anti-ice on for final taxi before take-off if OAT below +5º C regardless of conditions unless anti-ice fluids applied. Wing anti-ice on for take-off when OAT is below +5º C and visible moisture below 400 feet AGL. (Wing tactile check if OAT below +5º C or wing fuel below 0º C)

78
Q

Icing conditions in the air: Cowl and Wing anti-ice limitations

A

Must be on when: 1. Ice detection system detects ice. 2. below 22,000 feet and in icing conditions (TAT below +10º C and visible moisture) 3. Above 22,000 feet and in icing conditions when ice detector has failed

79
Q

Min fuel quantity for go-around and subsequent rotation limit

A

500 lbs per main tank with max 10º nose-up

80
Q

Reduction in max fuel quantity in Aux and Main tanks for gravity refuling

A

7%

81
Q

Max Speed with ADG deployed

A

250 KIASIf necessary: up to 330 KIAS for 12 minutes; up to 348 KIAS for 4 minutes (215 KIAS for flight testing)

82
Q

Electrical load at which generators overload

A

34.5 kva

83
Q

Cabin altitude at which CABIN PRESSURE aural warning triggered

A

10,000 feet (14,500 high alt airfield ops)

84
Q

ITT limit for all ground starts

A

120º C

85
Q

ITT limit for all air starts

A

90º C

86
Q

Ground operation of electrical/avionics equipment: temp and time limitations

A

At temps above +40º C, avionics/electrical system use restricted to 30 mins unless one pack is on and the main door closed.

87
Q

Max N1 RPM

A

98.5% N1

88
Q

Maximum engine ITT

A

899ºC

89
Q

Maximum engine N2 RPM

A

99.2% N2

90
Q

Digital FAN VIB amber indication on N1 gauge.

A

N1 = 2.7 MILS or greater

91
Q

Amber VIB indication on N2 gauge

A

N2 = 1.7 MILS or greater

Challenger CL604/605 renamed (8 decks)

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