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B787 Study > ENGINE AND APU > Flashcards

ENGINE AND APU Flashcards

1
Q

1) The EEC when operating in the Alternate mode:

A. Provides no Thrust Limit (overboost) protection.

B. Provides N1 and N2 overspeed protection.
C. Does not allow autothrottle operation.

D. A and B are correct.

A

A and B are correct.

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2
Q

2) In flight, the EEC selects approach idle if:

A. Flaps are 25 or greater.
B. RA is below 2500 feet and decreasing.

C. Landing gear is selected down.
D. A and C are correct

A

A and C are correct

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3
Q

3) The Autostart system monitors _____ during a ground start.

A. Oil pressure
B. Hot or hung starts

C. Oil quantity
D. A and B are correct.

A

A and B are correct.

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4
Q

4) A low oil quantity condition will be annunciated on EICAS by:

A. Reverse highlighting (black numbers on a white background) the oil quantity display.
B. An amber OIL QTY (L or R) caution message and associated beeper when
2.0 gallons remain.
C. Oil quantity indicator will change to red and flash.

D. Oil quantity is never monitored.

A

Reverse highlighting (black numbers on a white background) the oil quantity display.

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5
Q

5) The reverse thrust levers can be raised only when:

A. The autothrottles are disengaged.
B. Below 100 knots.
C. On the ground with the forward thrust levers in the idle position.
D. None of the above.

A

On the ground with the forward thrust levers in the idle position.

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6
Q

6) The APU is operating in the attended mode when:

A. Either engine is running or being started.
B. One or more of the flight deck seats are occupied.

C. The aircraft is in flight.
D. A and C are correct.

A

A and C are correct.

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7
Q

7) The engine autostart system will make a maximum of three start attempts before aborting the engine start sequence when in flight.

A. True.
B. False.

A

FALSE

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8
Q

8) When the thrust levers are positioned to the full forward position, the ____ provides N1 and N2 overspeed protection.

A. EEC
B. CDU
C. Auto Thrust Limiter System (ATLS)

D. Mechanical Limiters

A

EEC

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9
Q

9) On the ground, the engine autostart system will not attempt a second start after which of the following malfunctions?

A. No N2 rotation.
B. No oil temperature rise.
C. Loss of both starter/generators.
D. All the above.

A

Loss of both starter/generators.

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10
Q

10) Manual engine starts are accomplished:

A. Using the Manual Start supplementary procedure.
B. By turning OFF the AUTO START switch and manually selecting the Start and Fuel Cutoff valves.
C. Manual Starts are not available.
D. By coordinating with maintenance via the Flight Interphone.

A

Manual Starts are not available.

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11
Q

11) Regardless of the EEC switch position, thrust is set using:

A. N2 as the controlling parameter.
B. Fuel Flow as the controlling parameter.
C. N1 as the controlling parameter.
D. The charted EGT limit.

A

N1 as the controlling parameter.

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12
Q

12) While operating in the UNATTENDED mode, the APU will shut down for:

A. An overspeed.
B. High EGT.
C. Speed droop.

D. All the above.

A

All the above.

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13
Q

13) With the FUEL CONTROL switch in the CUTOFF position, the associated fire switch:

A. Is automatically unlocked.
B. Requires an active fire signal to unlock.
C. Automatically discharges the first fire bottle when a fire is detected.

D. Resets locked STATUS messages.

A

Is automatically unlocked.

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14
Q

14) The GEnX 1B74/75 engines on the 787-9 are rated at:

A. 69,800 pounds T/O thrust.
B. 84,300 pounds T/O thrust.

C. 74,100 pounds T/O thrust.

D. 90,000 pounds T/O thrust

A

74,100 pounds T/O thrust.

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15
Q

15) If an engine indication reaches a redline value the indicator digital readout, pointer, dial changes to a red color. The indicator color change can be reset to white (if the exceeded parameter has returned to normal) by:

A. Pushing TO/GA.

B. Pushing the Cancel / Recall switch.

C. Selecting the respective Autothrottle disconnect switch OFF then ON.

D. Pushing RESET.

A

Pushing the Cancel / Recall switch.

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16
Q

16) If AUTORELIGHT is displayed above N2:

A. Select continuous on the Ignition Select Switch.
B. Both igniters are running in the continuous condition.
C. The fuel control switch is in run and engine speed has decayed to below idle.

D. Both B and C.

A

Both B and C.

17
Q

17) The thrust ramping feature compensates for high stress loads due to crosswinds or low groundspeeds.What effect does this have on engine operation?

A. Commanded T/O thrust will be reached within 5 seconds of selecting TOGA.

B. Delayed high speed engine response.
C. May cause noticeable autothrottle stagger.
D. Maximum T/O thrust may not be reached until 65kts IAS.

A

Maximum T/O thrust may not be reached until 65kts IAS.

18
Q

18) Which statement is correct regarding APU operation?

A. The APU supplies electrical power and bleed air on the ground and only electrical power in flight.
B. Electrical power is available when at or below 43,100 ft.
C. There is no loss of electrical capacity when operated at or near maximum altitude.
D. None of the above.

A

Electrical power is available when at or below 43,100 ft.

19
Q

19) When the reverse thrust levers are moved aft to the interlock position, the autothrottles disengage and the auto speedbrakes, if not armed, deploy.

A. True.
B. False.

A

TRUE

20
Q

20) Regarding the Engine Oil System:

A. There is no minimum oil quantity limit for operating the engine in flight.

B. The oil pressure varies as a function of pressure altitude.
C. Minimum oil quantity prior to start is 18 quarts.

D. All the above

A

All the above

21
Q

21) When the “APU LIMIT” EICAS message is displayed:

A. The APU is limited to no more than 120 minutes of operation.

B. The APU has automatically shut down.
C. An APU limit has been exceeded.
D. The APU electrical output is load limited.

A

An APU limit has been exceeded.

22
Q

22) With the EECs operating in the normal mode, what action will provide maximum available thrust?

A. Selecting CLB/CON on the MCP.
B. Manually positioning the thrust levers to the full forward position.
C. Selecting TOGA on either thrust lever, regardless of autothrottle status.

D. Selecting T/O 1 on the Thrust Ref page.

A

Manually positioning the thrust levers to the full forward position.

23
Q

23) Which statement is TRUE concerning the hard alternate EEC mode?

A. If a fault occurs in the normal mode, control is automatically transferred to the hard alternate mode.
B. In the hard alternate mode, the EEC uses N1 as the controlling parameter.

C. Engine thrust limit protection is always provided in hard alternate modes.

D. Overspeed protection is not available in the hard alternate mode.

A

In the hard alternate mode, the EEC uses N1 as the controlling parameter.

24
Q

24) Thrust control malfunction accommodation (TCMA) can automatically shut down an engine to protect against idle thrust asymmetry conditions while on the ground.

A. True.
B. False.

A

TRUE

25
Q

25) In the attended mode, which of the following faults do NOT cause an automatic APU shutdown:

A. High EGT.
B. High Oil Temperature.

C. Low Oil Pressure.
D. All of the above.

A

All of the above.

26
Q

26) How many starter/generators are available to start the APU?

A. Two, one electric and one pneumatic. The pneumatic is preferred if available.
B. Two electric. Only the Right S/G is available for a battery start.

C. Two electric. Only the Left S/G is available for a battery start.

D. One, electric only.

A

Two electric. Only the Right S/G is available for a battery start.

27
Q

27) The momentary illumination of the APU FAULT during start is indicative of a non- normal condition and the APU should be manually shut down and investigated.

A. True.
B. False.

A

FALSE

28
Q

28) In flight or on the ground with no engines running or being started, the APU is operating in the unattended mode.

A. True. B. False.

A

FALSE

29
Q

29) The ENG display switch on either DSP, when selected:

A. Adds or removes the Secondary Engine instruments on EICAS below the
Primary instruments.
B. Places the Secondary Engine on the respective lower display unit.

C. Replaces the full EICAS messages display with a full engine display.

D. Resets any exceedances displayed on EICAS.

A

Adds or removes the Secondary Engine instruments on EICAS below the
Primary instruments.

30
Q

30) In what Flight Control mode(s) is Thrust Asymmetry Protection (TAP) available?

A. Normal.
B. Secondary.

C. Direct.
D. Both A and B

A

Normal.

31
Q

31) Simultaneous engine start requires:

A. All three external power sources available.

B. Simultaneous starts are prohibited.
C. Using both APU generators as the power source.
D. Temperature at time of start does not exceed 100° F.

A

Using both APU generators as the power source.

32
Q

32) An engine failure during takeoff prior to V1 will generate a time critical warning ENGINE FAIL, in conjunction with illumination of the Master Warning lights and a Warning Siren.

A. True.
B. False.

A

TRUE

33
Q

33) The minimum APU oil quantity for start is quarts.

A. 8

B. 10

C. 12
D. No required minimum quantity.

A

No required minimum quantity.

34
Q

34) During single engine Takeoff or Go-Around, the EEC may reduce thrust on the operating engine to maintain the required climb performance. This feature is called:

A. Auto Climb.
B. Thrust Asymmetry Protection or TAP.
C. Auto Thrust Management or ATM.

D. Minimum Speed Correction.

A

Thrust Asymmetry Protection or TAP.

35
Q

35) The APU battery is designed to support consecutive start attempts

A. 2
B. 3
C. 4
D. 5

A

2

36
Q

36) The APU is designed to be started and operating in flight at altitudes up to feet.

A. 43,100

B. 14,000

C. 10,000

D. 22,000

A

43,100

37
Q

37) Starting both engines simultaneously increases the a/c pack (CAC) restart time.

A. True. B. False.

A

FALSE

38
Q

38) If an engine fails while in flight, the autostart system will attempt:

A. To automatically engage the associated S/G in the start configuration.
B. 2 restarts, then a 20 minute cool down.
C. Continuous restarts only if the aircraft is below 18,000 feet.
D. Continuous restarts until the engine is started or the fuel control switch is selected to CUTOFF.

A

Continuous restarts until the engine is started or the fuel control switch is selected to CUTOFF.

39
Q

39) Thrust Asymmetry Protection (TAP) is automatic and can be verified by:

A. A “TAP” message on EICAS.
B. Observing a thrust reduction on the N1 indicator of the operating engine.
C. An indication of CON above the N1 indicator.
D. Movement of the thrust lever on the operating engine.

A

Observing a thrust reduction on the N1 indicator of the operating engine.

B787 Study (16 decks)

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