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Vol 1 > Section 1 Limitations > Flashcards

Section 1 Limitations Flashcards

1
Q

Runway slope

A

±2%

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2
Q

Maximum takeoff and landing tailwind component:

A
  • 10 knots (HP-1369 and HP-1370)

* 15 knots

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3
Q

TAKEOFF with tailwind component over 10 kts to 15 kts are permitted with the following restrictions:

A 
TAKEOFF (Dispatch Requirements):
Runway is clear and dry.
Antiskid and thrust reversers are fully operational.
Max Takeoff rated thrust is used.
Auto spoilers are used.
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4
Q

LANDING with tailwind component over 10 kts to 15 kts are permitted with the following restrictions:

A

LANDING (Dispatch Requirements):
Antiskid and thrust reversers are fully operational.
Landing Flaps 30/40.
Auto spoilers are used (unless correction is taken).
Braking action reported at least Good.

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5
Q

Maximum operating altitude:

A

41,000 ft.

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6
Q

Maximum takeoff/landing altitude:

A

10,000 ft.

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7
Q

Maximum flight operating latitude:

A

82° North and 82° South

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8
Q

If landing weight exceeds the chart value in the Maximum Quick Turn Around Weight Limits chart, Section 4, wait at least:

A
  • 700 (steel brakes) 62 Minutes
  • 800 (steel brakes) 67 Minutes
  • 700/-800 (carbon brakes) 48 Minutes
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9
Q

-700 Maximum Taxi Weight:

A

155,000 lbs.

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10
Q

-800 Maximum Taxi Weight:

A

174,700 lbs.

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11
Q

-700 Maximum Takeoff Weight:

A

154,500 lbs.

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12
Q

-800 Maximum Takeoff Weight:

A

174,200 lbs.

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13
Q

-700 Maximum Landing Weight:

A

129,200 lbs.

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14
Q

-800 Maximum Landing Weight:

A

146,300 lbs.

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15
Q

-700 Maximum Zero Fuel Weight:

A

120,500 lbs.

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16
Q

-800 Maximum Zero Fuel Weight:

A

138,300 lbs

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17
Q

System safety relief differential pressure:

A

Maximum 9.1 psi

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18
Q

Maximum cabin differential for takeoff/landing:

A

.125 psi

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19
Q

Minimum altitude for autopilot engagement (climb and cruise) is

A

1,000 ft. AGL.

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20
Q

For coupled single channel approaches with electronic glideslope, the autopilot shall not remain engaged below

A

50 ft. AGL.

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21
Q

Use of Aileron Trim with the Autopilot engaged

A

is prohibited.

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22
Q

Autopilot use prohibited below 100’ RA at airport pressure altitudes

A

above 8400 feet.

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23
Q

The autoland capability may only be used with

A

flaps 30 and 40 with both

engines operative

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24
Q

Max allowable winds for autoland:

A
  • Headwind – 25 knots
  • Tailwind – 15 knots
  • Crosswind – 20 knots
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25
Q

Maximum and minimum glideslope angles for autoland are

A

3.25 degrees and 2.5 degrees respectively.

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26
Q

APU bleed and electrical maximum altitude:

A

10,000 ft.

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27
Q

APU bleed maximum altitude:

A

17,000 ft.

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28
Q

APU electrical load maximum altitude:

A

41,000 ft.

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29
Q

Do not use VHF-3 for ATC communications with

A

ACARS operational, or if audio entertainment system is in use.

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30
Q

Do not use VHF COMM #2 or VHF COMM #3 on

A

120.00 MHZ as a primary means of communication. If frequency 120.00 MHZ is required use VHF COMM #1.

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31
Q

When placard installed use VHF-2 for

A

primary ATC COMM on ground.

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32
Q

The following HF frequencies are prohibited:

A

Listed in MHZ: 11.133 22.434 22.683 22.766

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33
Q

Maximum single engine drive generator load (ground operations):

A

75KVA – 215 amps

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34
Q

Maximum flap extension altitude:

A

20,000 ft.

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35
Q

Holding in icing conditions with flaps extended

A

is prohibited.

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36
Q

-700 Flap limit speeds (IAS):

1

A

230 knots

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37
Q

-700 Flap limit speeds (IAS):

2

A

230 knots

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38
Q

-700 Flap limit speeds (IAS):

5

A

225 knots

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39
Q

-700 Flap limit speeds (IAS):

10

A

210 knots

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40
Q

-700 Flap limit speeds (IAS):

15

A

195 knots

41
Q

-700 Flap limit speeds (IAS):

25

A

170 knots

42
Q

-700 Flap limit speeds (IAS):

30

A

165 knots

43
Q

-700 Flap limit speeds (IAS):

40

A

156 knots

44
Q

-800 Flap limit speeds (IAS):

1

A

230 knots

45
Q

-800 Flap limit speeds (IAS):

2

A

230 knots

46
Q

-800 Flap limit speeds (IAS):

5

A

225 knots

47
Q

-800 Flap limit speeds (IAS):

10

A

210 knots

48
Q

-800 Flap limit speeds (IAS):

15

A

200 knots

49
Q

-800 Flap limit speeds (IAS):

25

A

190 knots

50
Q

-800 Flap limit speeds (IAS):

30

A

175 knots

51
Q

-800 Flap limit speeds (IAS):

40

A

162 knots

52
Q

Maximum tank fuel temperature:

A

49°C.

53
Q

Inflight tank fuel temperature must be maintained at least

A

3°C above the freezing point of the fuel being used or -43°C, whichever is higher.

54
Q

Lateral fuel imbalance between wing tanks 1 and 2 must be scheduled to be zero. Random fuel imbalance

A

must not exceed 1000 lbs.

55
Q

Main wing tanks 1 and 2 must be scheduled to be full if the center tank contains more than

A

1000 lbs. of fuel.

56
Q

With XXXX lbs. of center tank fuel or less, partial wing tank fuel may be loaded provided the effects of
balance have been considered.

A

1000

57
Q

Fuel crossfeed valve must be closed for

A

takeoff and landing.

58
Q

For ground operation, center tank fuel pump switches must not be positioned to ON

A

unless the center tank fuel quantity exceeds 1000 pounds (453 kilograms), except when defueling or transferring fuel.

59
Q

Center tank fuel pump switches must be positioned to OFF

A

when both center tank fuel pump low pressure lights illuminate.

60
Q

Center tank fuel pumps must not be ON unless personnel are available

A

in the flight deck to monitor low pressure lights.

61
Q

The center tank fuel pump switch(es) must be turned OFF at the first indication of fuel pump low pressure any time during the flight.

A

This includes LOW PRESSURE indication that may occur as a result of pitch attitude changes.

62
Q

Takeoff and Initial Climb

Both center tank fuel pump switches must be OFF for takeoff if center tank fuel is less than

A

5000 pounds with the aircraft readied for initial

taxi.

63
Q

Takeoff and Initial Climb

Both center tank fuel pumps should be repositioned ON above

A

10,000 feet or after the pitch attitude has been reduced to begin acceleration to a climb speed of 250 knots or greater, if more than 2000 pounds remain in the center tank.

64
Q

Climb and Cruise

When fuel reduces to approximately

A

2000 lbs, turn LEFT center tank fuel pump switch OFF and OPEN fuel crossfeed valve to minimize fuel imbalance.

65
Q

Climb and Cruise
When the Master Caution, FUEL system annunciator and
fuel pump LOW PRESSURE illuminate

A

turn the RIGHT center tank fuel pump switch OFF without delay and close the fuel crossfeed valve.

66
Q

Descent

Turn LEFT center tank fuel pump switch OFF at the beginning of the descent if

A

less than 3000 pounds of fuel remain in the center tank. Open the crossfeed valve to minimize fuel imbalance.

67
Q

The CONFIG indicator will annunciate if center tank fuel exceeds

A

1600 pounds and the center tank fuel pump switches are OFF or are producing low pressure.

68
Q

If one center tank fuel pump fails with fuel in the center tank, turn the failed pump switch OFF

A

Turn the operational pump ON, if previously turned OFF. Open the fuel crossfeed valve to prevent a fuel imbalance.

69
Q

In a low fuel non-normal situation,

A

both center tank fuel pumps may be selected ON and all center tank fuel may be used regardless of the amount of fuel remaining in the tank.

70
Q

When the main tanks are not full, the zero fuel gross weight of the aircraft plus the weight of center tank fuel may exceed the maximum zero fuel weight

A

by up to 5000 pounds for takeoff, climb and cruise, and up to 3000 pounds for descent and landing, provided the effects of balance (CG) have been considered.

71
Q

Prior to transferring fuel or defueling,

A

conduct a lamp test of the respective fuel pump LOW PRESSURE lights.

72
Q

When transferring fuel or defueling from either the center or main wing tanks, monitor the fuel pump LOW PRESSURE lights

A

and turn the fuel pumps OFF at the first

indication of fuel pump low pressure.

73
Q

Fuel may be transferred from tankto tank or the aircraft may be defueled with passengers on board,

A

provided the fuel quantity in the tank from which fuel is being taken is maintained at not less than 2000 pounds.

74
Q

Deplane all passengers and non-essential crew when defueling or transferring fuel from a tank that has a fuel quantity

A

less than 2000 pounds. Wait until the process has been completed and the respective fuel pumps turned OFF before reloading non-essential crew and passengers.

75
Q

Icing conditions exist when OAT (ground) - TAT (airborne) is 10 C / 50 F or below and:

A
  • Visible moisture (clouds, fog with visibility less than one mile, rain, snow, sleet, ice crystals, and so on) is present, or
  • Standing water, ice, slush or surface snow is present on the ramps, taxiways, or runways which may be ingested by the engines or freeze on engines or nacelles
76
Q

If the aircraft has been deiced:

The control column will

A

be smoothly and slowly cycled from the full aft to the full forward position a minimum of three times to minimize the residual fluids in the balance bay during flight.

77
Q

Engine anti-ice:

Must be ON (1)

A

during all ground operations, including after landing, when icing conditions exist or are anticipated.

78
Q

Engine anti-ice:

Must be ON (2)

A

during all flight operations when icing conditions exist or are anticipated, except during climb and cruise when the temperature is below –40 C SAT.

79
Q

Engine anti-ice:

Must be ON (3)

A

prior to and during descent in all icing conditions, including temperatures below -40 C SAT.

80
Q

Wing anti-ice:

Must be ON

A

during all ground operations between engine start and takeoff when icing conditions exist or are anticipated, except when the airplane is or will be protected by the application of the Type II or Type
IV fluid in compliance with an approved ground de-icing program.

81
Q

Do not operate wing anti-ice on the ground

A

when the OAT is above 10 C/50 F.

82
Q

Do not use wing anti-ice as a substitute

A

for ground de-icing/anti-icing.

83
Q

The maximum allowable in-flight difference between Captain and First Officer altitude displays for RVSM operations is

A

200 feet.

84
Q

The maximum allowable on-the-ground display differences for RVSM operations are: SL to 5000 ft CAP & FO

A

50 Feet

85
Q

The maximum allowable on-the-ground display differences for RVSM operations are: SL to 5,001 to 10,000 ft CAP & FO

A

60 Feet

86
Q

The maximum allowable on-the-ground display differences for RVSM operations are: SL to 10.000 ft Max Difference Between Captain or F/O & Field Elevation

A

75 Feet

87
Q

Do not move the airplane until integrated Standby Flight Display (ISFD)

A

alignment is complete.

88
Q

Landing gear placard speeds:
A. Retract
B. Extend
C. Extended

A

235 knots
270 knots/.82M
320 knots/.82M

89
Q

Do not apply brakes

A

until after touchdown.

90
Q

Reverse thrust for ground use only,

A

Intentional use of reverse thrust in flight is prohibited.

91
Q

Ignition must be on for:

A
  • Takeoff
  • Landing
  • Engine Anti-Ice Operation
  • Heavy Rain
92
Q

Maximum and Minimum Engine Limits

A

are red.

93
Q

Caution Limits

A

are amber.

94
Q

Normal Engine operating range

A

is white.

95
Q

Oil Temperature must be greater than

A

-10 C before advancing thrust levers to takeoff thrust.

96
Q

Maximum N1:

A

104.0%

97
Q

Maximum N2:

A

105.0%

98
Q

Maximum EGT:
Takeoff (5 min):
Maximum Continuous:
Start:

A

950°C
925°C
725°C

Vol 1 (2 decks)

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