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AA787 > 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.
- EEC
- CDU
- TCP
- PMG

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…
- direct and alternate.
- controlling and bypass.
- normal and alternate.
- primary and secondary.

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…
- 115 Vac with 28 Vdc as backup.
- 235 Vac with 28 Vdc as backup.
- aircraft supplied DC power with standby power as backup.
- 235 Vac with 115 Vac as backup.

A

aircraft supplied DC 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 the start 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.
- hydraulically
- bleed air
- electrically
- fuel

A

hydraulically

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11
Q

The Electronic Engine Control (EEC) has two control modes…
- normal and alternate
- primary and secondary
- normal and secondary
- primary and reversion

A

normal and alternate

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12
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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13
Q

How is low engine oil quantity displayed on the secondary engine display?
- Black number on white background
- LO displayed in amber, quantity shown inside amber box
- OIL LO displayed in amber
- Oil quantity displayed same as normal quantity is displayed

A

Black number on white background

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14
Q

When the fuel control switch is in the RUN position and the engine is at or above idle, the green RUNNING indication is shown. It blanks on the secondary engine display after…
- 10 seconds.
- 15 seconds.
- 20 seconds.
- 30 seconds.

A

30 seconds.

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15
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?
- Fuel pressure from the right fuel manifold
- APU inlet door position
- The availability of the CCS applications
- Battery voltage of the main battery

A

The availability of the CCS applications

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16
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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17
Q

The APU operates in either attended or unattended modes. When does the APU operate in attended mode?
- Any time the APU is in operation
- When either engine is starting or running, or when the airplane is in flight
- When aft external power is connected
- 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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18
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 engine thrust ramping from occuring
- Prevents idle thrust asymmetry
- Produces maximum thrust for anti-ice air demand

A

Decreases acceleration time for go-around

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19
Q

When does load shed occur during engine start?
- Only during simultaneous engine start
- Always
- Depends on electrical load before start is initiated
- Only when using external power

A

Always

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20
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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21
Q

How many attempts will the AUTOSTART system make for an in-flight start?
- Until the engine starts.
- Until FUEL CONTROL switch is moved to CUTOFF.
- Both 1 and 2.
- The AUTOSTART system limits the number of start attempts to three both on the ground and in flight.

A

Both 1 and 2.

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22
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.
- 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.

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23
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.

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24
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

25
Q

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

26
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.

27
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

28
Q

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

A

False

29
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.
- icy runways and taxiways
- low temperatures.

A

crosswinds and low groundspeeds.

30
Q

Thrust Asymmetry Protection (TAP) is an automatic feature that…
- provides protection against asymmetric thrust during takeoff or go-around by limiting thrust on the higher thrust engine.
- increases thrust for high gross weight takeoffs and go-arounds.
- automatically engages all three autopilots when an engine failure is sensed.
- increases thrust above V2 after engine failure on takeoff.

A

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

31
Q

Thrust Asymmetry Protection (TAP) is only available when…
- the flight controls are operating in Direct mode.
- the flight controls are operating in Normal mode.
- the flight controls are operating in Normal or Secondary modes.
- the autopilot is engaged.

A

the flight controls are operating in Normal mode.

32
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

33
Q

The EEC selects approach idle in flight when the landing gear is selected down or…
- flaps are commanded out of up.
- engine anti-ice is ON.
- flaps are commanded to 20.
- flaps are commanded 25 or greater.

A

flaps are commanded 25 or greater.

34
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.

35
Q

For which malfunction will the AUTOSTART abort an engine start?
- Hot start
- Loss of one starter
- No oil pressure rise
- No EGT

A

No oil pressure rise

36
Q

The limit for the number of AUTOSTART attempts on the ground is…
- 3.
- 2.
- 1.
- 4.

A

3

37
Q

The limit for the number of AUTOSTART attempts in the air is…
- 3.
- 5.
- 1.
- unlimited.

A

unlimited.

38
Q

Each engine has two ignitors. The ignitor that is used for successive engine starts is automatically selected by the…
- EEC for engine ground starts.
- EEC for both engine ground and in-flight starts.
- CCR.
- START selector.

A

EEC for engine ground starts.

39
Q

Each engine has a(n) _____________ actuated fan air thrust reverser.
- hydraulically
- electrically
- bleed air
- mechanically

A

hydraulically

40
Q

The EICAS advisory message _______________ is displayed on the ground to indicate a fault occurred in the thrust reverser system.
- ENG REVERSER (L or R)
- ENG REV LIMITED (L or R)
- REV (L or R)
- ENG REV AIR/GND

A

ENG REVERSER (L or R)

41
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

42
Q

The reverse thrust levers can only be raised when…
- the forward thrust levers are in the idle position.
- below 100 knots.
- the autothrottles are disengaged.
- the speedbrakes are stowed.

A

the forward thrust levers are in the idle position.

43
Q

Moving the fuel control switch to CUTOFF closes the fuel valve(s), removes ignitor power, and…
- disarms the EEC.
- resets all fuel related EICAS messages.
- unlocks the engine fire switch.
- locks the start valve closed.

A

unlocks the engine fire switch.

44
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.

45
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

46
Q

Under what conditions in flight will the APU start automatically regardless of the APU selector position?
- Three or more engine generators go offline
- Loss of all displays
- Loss of Captain’s instruments
- Loss of both packs

A

Three or more engine generators go offline

47
Q

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

A

True

48
Q

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

49
Q

The engines can only be started with the autostart system.
- True
- False

A

tRUE

50
Q

Which of the following will cause the APU to shut down immediately in unattended mode?
- High EGT.
- High oil temperature.
- Low oil pressure.
- All of the above.

A

All of the above.

51
Q

What does the highlighted red line indicate during an engine start?
- Max motoring EGT limit
- Minimum EGT for dual engine start
- EGT Start Limit
- Engine starter cutout limit

A

EGT Start Limit

52
Q

When starting both engines simultaneously on the ground, when is the AUTOSTART sequence initiated?
- When the second FUEL CONTROL switch is placed to RUN.
- When rotating the START selector to START and placing the FUEL CONTROL switch to RUN.
- When selecting Engine AUTOSTART.
- When forward external power sources are selected ON and the START selector is rotated to START.

A

When rotating the START selector to START and placing the FUEL CONTROL switch to RUN.

53
Q

What would cause the start to abort the AUTOSTART sequence on the ground, without motoring or attempting a second and even a third start attempt?
- Hung start , loss of one starter, or low oil pressure.
- Loss of both starters, no N1 rotation, or no oil pressure.
- High EGT, high oil pressure, or high oil temperature.
- Loss of one starter, no N2 rotation, or low oil pressure.

A

Loss of both starters, no N1 rotation, or no oil pressure.

54
Q

After completing the [ ] ENG AUTOSTART R checklist, you are permitted…
- one additional start attempt.
- three auto restart attempts.
- no restarts.
- two additional auto restart attempts.

A

no restarts.

55
Q

During a ground start, the autostart system monitors engine parameters and attempts to correct the start for…
- loss of both starters.
- no oil pressure rise.
- EEC failure.
- no EGT rise.

A

no EGT rise.

56
Q

While advancing engine thrust to takeoff power, the Master Caution light illuminates, the aural beeper sounds, and the engine EICAS message ENG THRUST R displays. You also notice that the right engine N1 thrust command arc is filled amber. These indications tell you…
- the right autothrottle is disconnected.
- the green reference/target N1 exceeds the amber N1 maximum limit.
- the right engine thrust is less than the commanded thrust.
- the right engine will exceed the maximum N1 limit.

A

the right engine thrust is less than the commanded thrust.

57
Q

During takeoff roll, you get the indication shown from the Engine Failure Alert System. The Engine Failure Alert System is active…
- between 65 KIAS and 6 knots prior to V1.
- between V1 and flaps up.
- prior to 65 KIAS.
- up to 400 AGL.

A

between 65 KIAS and 6 knots prior to V1.

58
Q

During takeoff roll the Engine Failure Alert System indications are…
- a red ENG FAIL on both PFDs, voice annunciation “Engine Fail”, Master WARNING lights, and the EICAS caution message ENG LIMIT EXCEED (L or R)
- a red ENG FAIL on both PFDs, voice annunciation “Engine Fail”, Master WARNING lights, and the EICAS caution message ENG FAIL (L or R)
- a red ENG FAIL on both PFDs, voice annunciation “Engine Fail”, Master WARNING lights, and the EICAS caution message ENG AUTOSTART (L or R)
- a amber ENG FAIL on both PFDs, voice annunciation “Engine Fail”, Master CAUTION lights, and the EICAS caution message ENG THRUST (L or R)

A

a red ENG FAIL on both PFDs, voice annunciation “Engine Fail”, Master WARNING lights, and the EICAS caution message ENG FAIL (L or R)

AA787 (20 decks)

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