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FCOM Flashcards

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1
Q
  1. PSEU light, what does it monitor?
A

TALL
Take off configuration warning
Air/Ground sensing
Landing configuration warning
Landing gear

FCOM 15.20.6

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2
Q
  1. When do the leading edge slats go from
    extend to fully extend?
A

When the Flap lever is moved beyond the 25 position

FCOM 9.20.17

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3
Q
  1. What do the flight control switches do?
A

STBY RUD- activates STANDBY HYDRAULIC system pump and OPENS standby rudder shutoff valve to PRESURISE STANDBY RUDDER POWER CONTROL unit.

FCOM 9.10.1

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4
Q
  1. What does the Yaw damper switch do
A

During normal operation the MAIN yaw damper uses SYS B HYD pressure to prevent dutch roll, gust damping and turn cordination.

During manual reversion (loss of system A and B) it engages the standby yaw damper

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5
Q
  1. What does the FEEL DIFF pressure light indicate? Are there any further considerations?
A

Either HYD SYSTEM A or
HYD SYSTEM B or
ELEVATOR FEEL PITOT system fails.

DO NOT ATTEMPT AN AUTO LAND

FCOM 9.20.6

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6
Q
  1. When could the speed trim be activated?
A

Between 100kts-0.68M
More that 10 seconds after takeoff
More than 5 seconds after releasing the the trim switch
Autopilot not engaged (STS uses AP stab trim controller)
Sensing out of trim

FCOM 9.20.8

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7
Q
  1. What causes the engine fuel valve closed light to illuminate bright blue?
A

The valve is in transit or the valve position and the engine start lever disagree

FCOM 12.10.1

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8
Q
  1. What fuel tank is the fuel temperature
    measured from?
A

A sensor in the No. 1 tank using AC power

FCOM 12.20.3

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9
Q
  1. What is the max fuel temp?
A

49 degrees

FCOM 1.10.10

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10
Q
  1. What causes the fuel FILTER BYPASS light
    to illuminate?
A

An impending fuel filter bypass due to a contaminated filter.

FCOM 12.10.2

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11
Q
  1. when does the LOW indication illuminate?
A

When fuel quantity is less than 907kg in the related main tank.

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12
Q

13.When does the fuel CONFIG light illuminate?

A

If there is more than 726kg in the center tank and the pumps are off.

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13
Q
  1. When must the wing tanks be full?
A

Main tanks 1 and 2 must be full if the center tank contains more than 453kgs

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14
Q
  1. When does the fuel wing IMBAL illuminate?
A

When main tanks differ by more than 453kgs.

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15
Q

Which bus normally powers the left IRS?

A

AC STANDBY BUS

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16
Q

Which bus normally powers the right IRS?

A

AC TRANSFER BUS 2

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17
Q

When will the IRS operate on DC power?

A

If AC power is not normal, either or both systems automatically switch to backup DC power from the SWITCHED HOT BATTERY BUS

18
Q

When the IRS is operating on DC power on the ground, will there be any indication outside?

A

YES, If AC power is removed, the IRS will continue to be supplied by the SWITCHED HOT BATTERY BUS, the ON DC light will illuminate and the ground call warning horn in the nose wheel well will sound.

19
Q

What causes the ALIGN lights to illuminate, steady? and Flashing?

A

The ALIGN light will illuminate steady when the alignment process begins, 5-7 min
The FLASHING ALIGN light indicates the position entered doesn’t agree with the last stored position.

20
Q

What causes the BAT DISCHARGE light to illuminate?

A

Battery switch on and excessive battery discharge detected.

21
Q

What causes the TR unit light to illuminate

A

On the ground…..Any TR unit has failed

In flight…TR 1 or TR 2 and 3 have failed.

(do not use the AFDS mode during an ILS or GLS approach)

22
Q

What causes the ELEC light to illuminate?

A

A standby power or DC system fault occurs

Will only operate on the ground.

DO NOT TAKEOFF

23
Q

What causes the STANDBY PWR OFF light to illuminate?

A

One or more of the following busses are unpowered

-AC standby bus

-DC standby bus

-Battery bus

24
Q

What causes the DRIVE light to illuminate?

A

IDG low oil pressure caused by one of the following:

-IDG failure

-engine shutdown

-IDG automatic disconnect due to high oil temperature

-IDG disconnected through generator drive disconnect switch

25
Q

What occurs when the standby power switch is placed in battery?

A

-AC standby bus is powered by battery through static inverter

-DC standby bus and battery bus are powered directly by battery

26
Q

What causes the APU MAINT light to illuminate?

A

APU maintenance problem exists, however APU may still be operated.

27
Q

What are the APU limitations for bleed and electrical load?

A

BLEED + ELECTRICAL= 10,000
BLEED = 17,000
ELECTRICAL = 41,000

28
Q

When is F/D Go-Around armed

A
  • inflight below 2000ft RA
  • inflight above 2000ft RA with flaps up or GS captured
  • not in takeoff mode
  • if the TO/GA switches are activated after touchdown (wheel spin up)
29
Q

What happens with the first push of TO/GA (F/D go-around)

A
  • A/T (if armed) engages in GA and advances thrust toward a reduced N1 to produce 1000-2000ftm
  • Autopilot (if engaged) disengages
  • pitch mode engages in TO/GA
  • F/D commands 15 degrees nose up until a programed rate of climb is reached. Then Pitch commands target airspeed for each FLAP setting based on MTOW
  • F/D roll commands CURRENT GROUND TRACK until 50ft then LNAV will engage
  • IAS display blanks

NB engaging an Autopilot changes pitch mode from TO/GA to LVL CHG

30
Q

What is the normal sequence for a F/D takeoff

A
  • push TOGA, both FDs ON, N1, roll mode blank,TOGA
  • 60kts F/D pitch 15 degrees NU (starts 10 degrees ND)
  • 84 kts THR HLD
  • 88 kts RTO function if thrust lever moved to idle
  • Lift off, pitch bar 15 degrees NU until sufficent RoC the MCP speed + 20tks. Roll bar continues to command wings level
  • at 50ft RA LNAV ( if armed) engages
  • 400ft AGL VNAV (if armed) engages
31
Q

HYD SYS A

A
  • ground spoilers
  • alternate brakes
  • nose wheel steering
  • landing gear
  • ## PTU
  • ailerons
  • rudder
  • elevator and elevator feel
  • flight spoilers (2 each wing)
  • No 1 thrust reverser
  • autopilot A
32
Q

HYD SYS B

A
  • LE flaps and slats
  • brakes
  • alternate NWS
  • landing gear transfer unit
  • autoslats
  • yaw damper
  • ## TE flaps
  • ailerons
  • rudder
  • elevator and elevator feel
  • flight spoilers ( 2 each wing)
  • No. 2 thrust reverser
  • autopilot B
33
Q

selected FLT ALT = differential pressure

at or below 28000
28000 - 37000
above 37000

A

7.45 psid
7.8 psid
8.35 psid

34
Q

conditions that will trigger AUTO FAIL light

A
  • Loss of DC power
  • Controller fault
  • Outflow valve control fault
  • Excessive differential pressure, more 8.75 psi
  • More the 2,000fpm cabin pressure change
  • Cabin alt above 15,800
35
Q

How many flight spoilers are located on each wing?

A

4, HYD system A powers 2 on each wing and HYD system B powers 2 on each wing

36
Q

Autothrottle engaged modes (FMAs?)

A
  • N1
  • GA
  • Retard
  • FMC SPD
  • MCP SPD
  • THR HLD
  • ARM (white)
37
Q

Roll modes (FMAs?)

A

Engaged (GREEN)
- HDG SEL
- LNAV
- VOR/LOC

Armed modes (white)
- VOR/LOC
-LNAV VOR/LOC

38
Q

Pitch modes (FMAs?)

A

Engaged (GREEN)
- TO/GA
- V/S
- MCP SPD
- ALT/ACQ
- ALT HOLD
- G/S
- VNAV SPD
- VNAV PTH
- FLARE

39
Q

What conditions must be satisfied to introduce fuel prior to 25% N2 during engine start

A

N2 must be above 20% and
Max motoring, less than 1% N2 within 5 seconds

40
Q

NSD includes?

A

one FMC
one MCDU
one PFD and ND
one F/D

41
Q

Crosswind limitations ( dry and wet)

A

Dry
Takeoff 33kts landing 37kts

Wet
Takeoff 25kts landing 37kts

101 (10 decks)

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