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AB's Dreamliner Study > Engines > Flashcards

Engines Flashcards

1
Q

Each engine is controlled by a(n) ____ which monitors autothrottle and flight crew inputs through the thrust levers to automatically control the engines.

PMG

EEC

TCP

CDU

A

EEC

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2
Q

Primary and secondary engine indications can be displayed simultaneously on both the Captain and FO’s inboard MFD window.

True

False

A

False

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3
Q

The primary engine indications are displayed full-time on the EICAS display. The primary engine indications are…

N1 and N2.

N1 and fuel flow.

N1 and EGT.

N1 and oil pressure.

A

N1 and EGT

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4
Q

The Electronic Engine Control (EEC) has two control modes…

  • primary and secondary.
  • direct and alternate.
  • controlling and bypass.
  • normal and alternate
A

normal and alternate

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5
Q

The autothrottles will disconnect if the EECs automatically switch to the Alternate mode.

True

False

A

False

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6
Q

Simultaneous engine start is only allowed when the APU is running and both APU starter generators are operational.

True

False

A

True

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7
Q

Each engine has two ignitors. The EEC automatically selects the appropriate ignitor(s) for successive engine ground starts. Dual ignitors are always used for in-flight starts. The normal power source for ignition is…

aircraft supplied 28 Vdc power with standby power as backup.

235 Vac with 115 Vac as backup.

235 Vac with 28 Vdc as backup.

115 Vac with 28 Vdc as backup.

A

aircraft supplied 28 Vdc power with standby power as backup

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8
Q

The engines can only be started using the autostart system.

True

False

A

True

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9
Q

In the air, the EEC does not limit autostart attempts. On the ground, autostart attempts per start sequence are limited to…

1.

2.

3.

4.

A

3

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10
Q

Each engine has a _______________ actuated fan air thrust reverser.

electrically

hydraulically

fuel

bleed air

A

hydraulically

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11
Q

When is X-START (magenta) displayed under the N2 RPM display?

When current altitude and/or airspeed are outside the windmilling start envelope

When within the airspeed range necessary for an in-flight start at the current flight level

When the In-Flight Start Envelope information is displayed

When engine N1 is below idle

A

When current altitude and/or airspeed are outside the windmilling start envelope

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12
Q

How is low engine oil quantity displayed on the secondary engine display?

LO message displayed in white, oil quantity displayed in as black number on white background, i.e. reversed from normal

LO displayed in amber, quantity shown inside amber box

OIL LO displayed in amber

Oil quantity displayed same as normal quantity is displayed (white number on black background), LO message displayed in amber

A

LO message displayed in white, oil quantity displayed in as black number on white background, i.e. reversed from normal

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13
Q

When the fuel control switch is in the RUN position and the engine is at or above idle, the green RUNNING indication blanks on the secondary engine display after…

10 seconds.

15 seconds.

20 seconds.

30 seconds.

A

30 seconds

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14
Q

If starting the APU from an unpowered airplane (battery switch recently moved to ON), what does the APU controller (APUC) wait for before proceeding with the APU start?

The availability of the common core system (CCS) applications

Fuel pressure from the right fuel manifold

Battery voltage of the main battery

APU inlet door position

A

The availability of the common core system (CCS) applications

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15
Q

If the required signals are not available to operate in the normal mode, the EEC automatically uses the alternate mode. Which of the following is correct regarding EEC Alternate Mode?

Thrust protection is not provided in the alternate mode and maximum rated thrust is reached at a thrust lever position less than full forward.

Automatic reversion or manual selection to the alternate mode is indicated by the EICAS advisory message ENG LIMIT PROT (L, R).

The autothrottles disconnect whenever the EEC automatically switches to the alternate mode.

The alternate mode schedule (N1 schedule) provides somewhat less thrust than the normal mode for the same thrust lever position.

A

Thrust protection is not provided in the alternate mode and maximum rated thrust is reached at a thrust lever position less than full forward.

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16
Q

The APU operates in either attended or unattended modes that are utilized to determine what faults will cause the APU to shut down immediately. When does the APU operate in attended mode?

When either engine is starting or running, or when the airplane is in flight

When aft external power is connected

Any time the APU is in operation

When the flight deck door is closed and locked

A

When either engine is starting or running, or when the airplane is in flight

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17
Q

The EEC automatically selects minimum idle, approach idle, or icing idle as appropriate for phase of flight. Approach idle is selected when flaps are commanded to 25 or greater, or the landing gear is selected DOWN. What is the purpose of approach idle?

Decreases acceleration time for go-around

Prevents idle thrust asymmetry

Produces maximum thrust for anti-ice and rain protection air demands

Prevents engine thrust ramping

A

Decreases acceleration time for go-around

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18
Q

When does load shed occur during engine start?

Only during simultaneous engine start

Depends on electrical load before start is initiated

Only when using external power and then only for the first engine start

Always

A

Always

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19
Q

During ground starts, the AUTOSTART system monitors engine parameters and aborts the start without motoring and without making another start attempt for…

Loss of both starters

No N1 rotation

No oil pressure rise

All of the above.

A

All of the above

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20
Q

How many attempts will the AUTOSTART system make for an in-flight start?

One

Two full start cycles

The AUTOSTART system limits the number of start attempts to three both on the ground and in flight.

The EEC does not limit the start attempts in the air.

A

The EEC does not limit the start attempts in the air.

21
Q

The engine auto-relight function is activated on the ground and in-flight whenever…

an engine is at or below idle with flaps out of the UP detent and the FUEL CONTROL switch in RUN.

an engine is at or below idle with the FUEL CONTROL switch in RUN.

continuous ignition is selected.

the engines are running. Continuous ignition is automatic.

A

an engine is at or below idle with the FUEL CONTROL switch in RUN

22
Q

A red ENG FAIL is displayed on both PFDs and ENG FAIL on both HUDs is displayed when…

actual thrust is less than commanded thrust during takeoff with airspeed between 65 knots and 6 knots prior to V1.

engine performance is more than commanded engine performance any time in flight.

actual thrust is less than commanded thrust during takeoff at any airspeed.

actual thrust exceeds commanded thrust on approach below 100 feet AGL.

A

actual thrust is less than commanded thrust during takeoff with airspeed between 65 knots and 6 knots prior to V1.

23
Q

Thrust Control Malfunction Accommodation is an EEC function that provides thrust asymmetry protection under what circumstances?

On the ground to protect against idle thrust asymmetry

In the event of an engine failure on takeoff below 1000ft AGL

During a go-around at light weights and aft CG

At any time a thrust asymmetry is detected by the EEC

A

On the ground to protect against idle thrust asymmetry

24
Q

APU fuel is supplied from the left fuel manifold by any operating AC fuel pump or by the DC fuel pump in the left main tank. Even with no fuel pumps operating, the APU is designed to be started on the ground or in flight up to 14,000 feet.

True

False

A

True

25
Q

The EEC alternate mode provides two levels of controls. They are referred to as…

soft and hard.

reversion and manual.

asymmetric and symmetric.

scheduled and regulated.

A

soft and hard

26
Q

When operating in EEC alternate mode, maximum rated thrust is reached at a thrust lever position less than full forward. As a result, thrust overboost can occur at full forward thrust lever position.

True

False

A

True

27
Q

Autothrottles will disconnect whenever the EEC automatically switches to the alternate mode.

True

False

A

False

28
Q

Thrust ramping is an EEC normal mode function that slowly increases thrust until takeoff thrust is achieved to compensate for high stress loads on engine fan blades due to…

crosswinds and low groundspeeds.

tailwinds and high groundspeeds.

low temperatures.

icy runways and taxiways

A

crosswinds and low groundspeeds

29
Q

Thrust Asymmetry Protection (TAP) is an automatic feature that…

automatically engages all three autopilots when an engine failure is sensed.

increases thrust for high gross weight takeoffs and go-arounds.

increases thrust above V2 after engine failure on takeoff.

provides protection against asymmetric thrust during takeoff or go-around by limiting thrust on the higher thrust engine.

A

provides protection against asymmetric thrust during takeoff or go-around by limiting thrust on the higher thrust engine.

30
Q

Thrust Asymmetry Protection (TAP) is only available when…

the flight controls are operating in Normal mode.

the flight controls are operating in Direct mode.

the autopilot is engaged.

the flight controls are operating in Normal, Secondary or Direct mode. The flight control mode has no effect on TAP.

A

the flight controls are operating in Normal mode

31
Q

The purpose of the Transient Bleed System (TBS) is to unload the compressor during engine acceleration for increased engine stall margin.

True

False

A

True

32
Q

The EEC selects approach idle in flight when the landing gear is selected down or…

flaps are commanded to 20.

flaps are commanded 25 or greater.

flaps are commanded out of up.

engine anti-ice is ON.

A

flaps are commanded 25 or greater

33
Q

Which of the following is false?

The autostart sequence is initiated by rotating the START selector to START and moving the FUEL CONTROL switch to RUN.

The START selector applies electrical power to the starter motors to begin dry motoring the engine(s).

Autostart allows the EEC to control fuel and ignition.

The autostart system will attempt to correct for no N1 rotation.

A

The autostart system will attempt to correct for no N1 rotation.

34
Q

For which malfunction will the AUTOSTART abort an engine start?

No oil pressure rise

Hot start

Loss of one starter

No EGT

A

No oil pressure rise

35
Q

The limit for the number of AUTOSTART attempts on the ground is…

4.

1.

2.

3.

A

3.

36
Q

The limit for the number of AUTOSTART attempts in the air is…

1.

5.

unlimited.

3.

A

unlimited

37
Q

Each engine has two ignitors. The ignitor that is used for successive engine starts is automatically selected by the…

EEC for successive engine ground starts. Dual ignitors are always used for in-flight starts.

EEC for both successive engine ground and in-flight starts.

CCR.

START selector.

A

EEC for successive engine ground starts. Dual ignitors are always used for in-flight starts

38
Q

Each engine has a(n) _____________ actuated fan air thrust reverser.

mechanically

hydraulically

electrically

bleed air

A

hydraulically

39
Q

The EICAS advisory message _______________ is displayed on the ground to indicate a fault occurred in the thrust reverser system.

ENG REVERSER (L,R)

ENG REV LIMITED (L,R)

REV (L,R)

ENG REV AIR/GND

A

ENG REVERSER (L,R)

40
Q

During APU start, if no AC power is available a DC pump in the _____ main tank will supply APU fuel.

left

center

right

aux

A

left

41
Q

The reverse thrust levers can only be raised…

on the ground when the forward thrust levers are in the idle position.

below 100 knots

the autothrottles are disengaged.

the speedbrakes are stowed

A

on the ground when the forward thrust levers are in the idle position

42
Q

Moving the fuel control switch to CUTOFF closes the fuel valve(s), removes ignitor power, and…

unlocks the engine fire switch.

locks the start valve closed.

disarms the EEC.

resets all fuel related EICAS messages.

A

unlocks the engine fire switch

43
Q

In flight with the FUEL control switch in RUN, both engine ignitors are switched on by the EEC in the respective engine when…

an engine flameout or rollback is detected.

engine anti-ice is selected ON.

the ignition switch is placed to CONTINUOUS.

flaps are selected out of up.

A

an engine flameout or rollback is detected

44
Q

Thrust Control Malfunction Accommodation is an EEC function that provides protection against idle thrust asymmetry conditions while on the ground.

True

False

A

True

45
Q

Under what conditions in flight will the APU start automatically regardless of the APU selector position?

Loss of all displays

Loss of Captain’s instruments

Three or more engine generators go offline

Loss of both packs

A

Three or more engine generators go offline

46
Q

During takeoff or go-around, TAP may limit thrust on the higher thrust engine to enhance safety.

True

False

A

True

47
Q

During an APU start, the main airplane battery powers the APU fuel shutoff valve, DC fuel pump, and fire detection systems. The APU battery powers the APU controller (APUC), air inlet door and the right starter if required. The APU battery is designed to support ____ consecutive start attempts before a ____ minute cooling period must be observed?

2, 5

2, 13

3, 22

5, 5

A

2, 5

48
Q

The engines can only be started with the autostart system.

True

False

A

True

49
Q

The APU operates in either attended or unattended modes that are utilized to determine what faults will cause the APU to shut down immediately. The attended mode operates when either engine is starting or running, or when the airplane is in flight. The unattended mode operates in all other configurations on the ground. Which of the following will not cause the APU to shut down immediately in unattended mode?

High EGT.

High oil temperature.

Low oil pressure.

All of the above will cause the APU to shutdown immediately in unattended mode.

A

All of the above will cause the APU to shutdown immediately in unattended mode.

AB's Dreamliner Study (15 decks)

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