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Aviation > Boeing 737 Classic > Flashcards

Boeing 737 Classic Flashcards

0
Q

Vfe flaps 2

A

230 kts.

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1
Q

Vfe flaps 1

A

230 kts.

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2
Q

Vfe flaps 5

A

225 kts.

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3
Q

Vfe flaps 10

A

210 kts.

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4
Q

Vfe flaps 15

A

195 kts.

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5
Q

Vfe flaps 25

A

190 kts.

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6
Q

Vfe flaps 30

A

185 kts.

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7
Q

Vfe flaps 40

A

158 kts.

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8
Q

V Approach flaps 1

A

190 kts.

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9
Q

V Approach flaps 5

A

170 kts.

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10
Q

V Approach flaps 10

A

160 kts.

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11
Q

V Approach flaps 15

A

150 kts.

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12
Q

V Approach flaps 25

A

140 kts.

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13
Q

V Approach flaps 30/40

A

Vref + 5 kts.

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14
Q

VMO (max. operating speed)

A

340 kts.

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15
Q

MMO (max. Mach speed)

A

0.82 Mach

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16
Q

VA (PA 0’) (max. Airspeed full control deflection)

A

277 kts.

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17
Q

Vlo retract

A

235 kts.

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18
Q

Vlo extend

A

270 kts.

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19
Q

Vle

A

320 kts.

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20
Q

Mle

A

0.82 Mach

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21
Q

Limits below 10.000’

A
  • Speed 300 kts.

- max. V/S 3000’

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22
Q

Rough airspeed

A

280 kts. / 0.73 Mach

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23
Q

V window heat inop.

A

250 kts. below 10.000’

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24
Q

Max. Operating altitude

A

37.000’ P.A.

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25
Q

Max. Take-off and landing altitude

A

8.400’

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26
Q

Max. Operating latitudes

A
  • 73 degrees North

* 60 degrees South

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27
Q

Min. ambient temperature

A
  • 73 C
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28
Q

Do not reduced thrust for take-off if (5 items)

A
  • contaminated runway or low friction coefficient < 0,4
  • wind shear conditions exist
  • anti-skid inoperative
  • PMC is off
  • low visibility take-off
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29
Q

Altimeters requirements RVSM Airspace

A
  • difference on ground between capt. and F/O: 40’
  • difference on ground between any altimeter and A/P elev.: 75’
  • difference in flight between capt. and F/O: 200’
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30
Q

Max. N1 RPM

A

106 %

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31
Q

Max. N2 RPM

A

105%

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32
Q

Max take-off EGT

A

930 C

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33
Q

Max. Continuous EGT

A

895 C

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34
Q

Max. Start EGT

A

725 C

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35
Q

Max. Oil temperature

A

165 C

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36
Q

Min. Oil pressure

A

13 PSI

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37
Q

Minimum oil quantity

A
  • dep. from base: 75%

- dep. out station: 60 %

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38
Q

APU Versions

A
  • GTCP 85-129: green/red marking EGT indicator

- GTCP 36-280(B): APS 2000 indicator without colored marking

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39
Q

APU max. EGT temperature

A

GTCP 85-129

  • max. Start EGT: 760 C
  • max. Cont. EGT: 710 C
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40
Q

APU start attempts are not recommended above:

A

25.000’

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41
Q

No APU use for both:

  • Bleed air
  • Electrical load

Above:

A

10.000’

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42
Q

No APU bleed above

A

17.000’

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43
Q

No APU start above

A

35.000’

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44
Q

Max. APU altitude

A

37.000’

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45
Q

Automatic landing limitations (4 items)

A
  • max. Allowable wind speeds
  • max./min. glide slope of 3.25 respectively 2.5 degrees
  • only flaps 30 or 40 and both engines operative
  • both hydraulic and both electrical systems operative
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46
Q

Electrical power: max. generator drive oil temperature

A

157 C (in)

Rise difference: 20 C

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47
Q

Min. hydraulic fluid quantity

A

88 %

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48
Q

Min. Fuel for ground operation of elec. hydraulic pump cooling

A

760 kg.

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49
Q

No speed brake extension when (2 items)

A
  • below 1000’ R.A.

- flaps 15 or greater

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50
Q

Max. Flap operating altitude

A

20.000’

51
Q

Max. Differential pressure

A

8.65 psi

52
Q

Max. Cabin pressure differential for take-off and landing

A

0.125 psi

53
Q

Engine anti-ice on when:

A
  • Ground/flight operations: when icing conditions exist (OAT/TAT below 10 C)
  • Except in climb and cruise when SAT is -40 C
54
Q

Min. Time window heat operative prior take-off

A

10 minutes

55
Q

Left annunciator panel

A

FLT CONT ELEC

IRS APU

FUEL OVHT DET

56
Q

Right annunciator panel

A

ANTI ICE ENG

HYD OVERHEAD

DOORS AIR COND

57
Q

Max. tire speed

A

190 kts.

58
Q

Hydraulic system A (PLINGA)

A
  • Auto Pilot A
  • ailerons
  • rudder
  • elevator (feel)
  • thrust reverser eng. # 1
  • Power Transfer Unit
  • Landing gear
  • Inboard spoilers
  • Nose wheel steering
  • Ground Spoilers
  • Alternate Brake
59
Q

Hydraulic system B ( LANAL TOY)

A
  • Auto Pilot B
  • Ailerons
  • Rudder
  • Elevator (feel)
  • Thrust reverser eng. #2
  • Landing Gear Transfer Unit
  • Auto slats
  • Normal and auto brake
  • Alternate Nose Wheel Steering
  • Leading edge flaps & slats
  • Trailing edge flaps
  • Outboard Spoilers
  • Yaw Damper
60
Q

Standby hydraulic systems provides back-up for (RET):

A
  • Rudder
  • Extension of Leading edge devices
  • Thrust reversers
  • Yaw Damper ( NG)
61
Q

Landing Gear Transfer Unit activates when (4 items):

A
  • Airborne
  • # 1 engine drops below limit value
  • Landing gear lever is in UP position
  • Either main landing gear is NOT up and locked
62
Q

Power Transfer Unit activates when (3 items)

A
  • Airborne
  • System B Engine driven pump hydraulic pressure drops below limits
  • Flaps 15 or less but not up
63
Q

Min. Flight crew oxygen pressure

A

1200 PSI

64
Q

Volume fresh potable water tanks

A

30 US Gallons ( installed in aft. Cargo compartment)

65
Q

Fresh water can be pressurized by:

A
  • Bleed air engine #1 or APU

- 115 V AC air compressor

66
Q

Emergency exit light battery packs operating time

A

20 minutes

To recharge:

  • AC power must be available
  • Switch must be in OFF or Armed position
67
Q

Passenger Oxygen mask automatically deploys when:

A
  • Cabin altitude exceeds 14.000’

- PASS OXYGEN switch must be ON

68
Q

Passenger oxygen duration

A

12 minutes

69
Q

Power Transfer Unit purpose

A

Supplies additional hydraulic fluid needed to operated the:

  • Autoslats
  • leading edge flaps and slats

When system B engine driven hydraulic pump is lost

70
Q

Landing Gear Transfer Unit purpose

A

Supplies volume of hydraulic fluid to raise the landing gear when system A eng. driven pump volume is lost

71
Q

Hydraulic leak system A:

  • leak in engine-driven pump
A

The reservoir quantity displayed indicates approximately 20 % full.

System A hydraulic pressure is maintained by the electrical- driven pump

72
Q

Hydraulic leak system A:

  • leak in electrical-driven pump (or both pumps)
A

Quantity in the reservoirs steadily decreases to zero and all system pressure is lost.

73
Q

Hydraulic leak system B:

  • Leak in engine-driven pump and/ or electrical-driven pump
A
  • If a leak develops in either pump, line or component of system B, the quantity decreases until it indicates approximately zero and system B pressure is lost.
  • Fluid remaining in system B reservoir is sufficient for Power Transfer Unit
  • A leak in system B does not affect the operation of the stand-by hydraulic system.
74
Q

Hydraulic leak standby system

A
  • If a leak occurs in the standby system, the standby reservoir decreases to zero.
  • System B reservoir fluid level indication decreases and stabilizes at approximately 72 % full.
75
Q

Changeover (C/O) switch

A
  • Changes IAS/MACH display (MCP)

- Automatic changeover occurs at +/- FL 260

76
Q

Normal hydraulic pressure (all systems)

A

3000 PSI

77
Q

Normal brake pressure

A

3000 PSI

78
Q

What does the hydraulic quantity indications show if hydraulic fluid quantity is too low?

A

RF (refill)

79
Q

Automatic operation hydraulic standby system during take-off and landing (3 items)

A
  • airborne or wheel spees >60 kts
  • hydraulic pressure system A or system B is low
  • flaps are NOT up

(Standby system operates until flaps are up)

80
Q

CAT I minima

A

DH: not lower than 200 ft.

RVR: not less than 550 m.

Visibility: not less than 800 m

81
Q

CAT II minima

A

DH: between 100 ft. and 200 ft.

RVR: not less than 350 m.

82
Q

CAT IIIA minima

A

DH: between 0 ft. and 100 ft.

RVR: not less than 200 m

83
Q

CAT IIIB minima

A

DH: between 0 ft. and 50 ft.

RVR: between 50 m. and 200 m.

84
Q

CAT IIIC minima

A

DH: no DH

RVR: no RVR limitation

85
Q

FMA Annunciator modes (4 items):

A

A/T PITCH ROLL A/P

86
Q

FMA engaged modes A/T (7 items)

A
  • N1
  • GA
  • RETARD
  • FMC SPD
  • MCP SPD
  • THR HLD
  • ARM
87
Q

FMA engaged modes PITCH (9 items)

A
  • TO / GA
  • V/S
  • ALT ACQ
  • ALT HOLD
  • VNAV SPD
  • VNAV PTH
  • MCP SPD
  • G/S
  • FLARE
88
Q

FMA engaged modes ROLL (3 items)

A
  • HDG SEL
  • VOR/ LOC
  • LNAV
89
Q

FMA engaged modes A/P (4 items)

A
  • CMD
  • FD
  • CWS P
  • CWS R
90
Q

Max. Fuel imbalance

A

453 kg.

91
Q

Max. Fuel quantity

A
  • each wing main tank: 4.827 kg (2x)
  • centre tank: 7.448 kg
  • total: 17.102 kg
92
Q

Max. Fuel temperature

A

+ 49 C

93
Q

Min. Fuel temperature

A
  • fuel freezing point + 3 C
  • -47 C

Whichever is higher

94
Q

Do not engage A/P during take-off below:

A

1000’ AGL

95
Q

Lowest height for single channel ILS app. A/P engaged

A

50’ AGL

96
Q

Lowest height A/P engaged in V/S mode

A

300’ AGL

97
Q

(TMD) Thrust Mode Display annunciations

A
  • TO
  • R-TO
  • CLB
  • R-CLB
  • CRZ
  • G/A
  • CON
98
Q

EADI

A

Electronic Attitude Director Indicator (artificial horizon display)

99
Q

Illuminated switch at MCP means:

A

Mode can be deselected by pushing switch again

100
Q

When FMA shows N1…

A

A/T sets power according Thrust Mode Display

101
Q

At 64 kts (or 84 kts?) N1 (in FMA) change into

A

THR HLD (Throttle Hold)

A/T servomotor disconnects so A/T cannot change THR positions. However manual adjustment is possible.

102
Q

After 60 kts g/s F/D will point how many degrees nose up?

A

15 degrees nose up

until a v/s of 600’ p/m is obtained
Thereafter climb rate between 600 and 1200 fpm
(Pitch command is pitch/speed function)

103
Q

Max. Roll limitations until 400’ RA

A

4 degrees bank angle

104
Q

Above v/s of 1200 fpm the F/D command bar sets pitch to obtain:

A

V2 speed + 20 kts.

With maximum of 25 degrees nose up

105
Q

THR HLD changes in ARM (FMA) when:

A
  • 18 seconds after liftoff

And

  • above 400’ RA
106
Q

At 1500’ after T/O, A/T will change “ARM” into

A
  • Thrust reduction to N1 climb limit
  • N1 in FMA
  • CLB in TMD
107
Q

Vertical speed range (MCP)

A

+ 6000 fpm

  • 7900 fpm
108
Q

FD TO/GA mode on ground is only available if

A

Both F/D switches are in “on” position

109
Q

LNAV engage mode criteria

A
  • less than 3 NM off track

OR (!)

  • Intercept angle less than 90 degrees
110
Q

RTO active above:

A

90 kts.

111
Q

A/T does not arm when which FMC related item is missing

A

OAT (Outside Air Temperature)

112
Q

N1 in FMA means:

A

A/T have set the maximum possible power as indicated in the TMD (thrust mode display)

113
Q

When FMC commands speed, the IAS/Mach display is:

A

Blank

114
Q

You loose 1 generator (blue GEN OFF BUS light and amber (BUS OFF) light, in APP mode ABOVE 800’ RA. The F/D bar at the effected will disappear.
How can you recover the F/D guidance bar?

A

Switch of the F/D switch at the unaffected side and F/D will appear again.

Above 800’ RA: 1 GEN = only 1 F/D

115
Q

You loose 1 generator (blue GEN OFF BUS light and amber (BUS OFF) light, below 800’ RA. What is the effect on your F/D (bar) guidance?

A

No effect. Below 800’ RA all F/D modes are available on both sides in case you loose a generator.

116
Q

Go Around mode is available between which altitudes?

A

Between 2000’ RA and touchdown.

Activated by TO/GA switches
With or without F/D switches in on position

117
Q

Difference between pressing 1 and 2 time(s) TO/GA switch

A

Once –> Reduced GA power (A/T FMA = GA)

Twice –> Full GA power (A/T FMA = N1)

(Available till 2000’ RA)

118
Q

By pressing TO/GA switch for GA, the FD bar initiates 15 degrees nose up, thereafter FD will pitch for go around target speed. This speeds depends on:

A

Actual flap setting

119
Q

How can you deselect the APP mode at the MCP?

A
  • Both F/D switches to off
  • Change ILS frequency
  • Press TO/GA and perform a Go Around
  • disengaging A/P
  • overriding the control wheel column
120
Q

In APP mode:

  • F/D “V” bar disappear and;
  • No guidance will be available for flare/landing

Passing which altitude?

A

Passing 50’ RA

121
Q

G/A mode:

When can you select any other pitch or roll mode?

After passing…

A

400’ RA

Below this altitude TO/GA mode maintains:

  • last (ground) track when G/A was initiated
  • pitch for 15 degrees nose-up
122
Q

G/A mode:

When reached G/A altitude, which roll mode will automatically appear on MCP and in FMA

A

HDG SEL

123
Q

Standard bank angle airBaltic

A

25 degrees

124
Q

CWS Pitch (P)

A

Pitch is set manually by yoke and pitch will be maintained when yoke is released

125
Q

CWS Roll (R)

A

Roll is initiated manually by yoke and bank angle will be maintained when yoke is released.

Only available when roll is greater than 6 degrees

Aviation (1 decks)

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