Engines and APU

Question 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.

Answer 1

D. A and B are correct.

Question 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.

Answer 2

D. A and C are correct.

Question 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.

Answer 3

D. A and B are correct.

Question 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.

Answer 4

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

Question 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.

Answer 5

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

Question 6

The APU is operating in the attended mode when:

A. Either engine is starting or running.
B. One or more of the flight deck seats are occupied.
C. The airplane is in flight.
D. A and C are correct.

Answer 6

D. A and C are correct.

Question 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.

Answer 7

B. False

Question 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

Answer 8

A. EEC

Question 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.

Answer 9

C. Loss of both starter/generators.

Question 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.

Answer 10

C. Manual starts are not available.

Question 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.

Answer 11

C. N1 as the controlling parameter.

Question 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.

Answer 12

D. All the above.

Question 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.

Answer 13

A. Is automatically unlocked.

Question 14

The GEnX 1B76 engines on the 787-9 are rated at:

A. 69,800 pounds T/O thrust.
B. 84,300 pounds T/O thrust.
C. 76,100 pounds T/O thrust.
D. 90,000 pounds T/O thrust

Answer 14

C. 76,100 pounds T/O thrust.

Question 15

If an engine indication reaches a redline value, the indicator digital readout, pointer, dial change 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.

Answer 15

B. Pushing the Cancel / Recall switch.

Question 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.

Answer 16

D. Both B and C.

Question 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 65 KIAS.

Answer 17

D. Maximum T/O thrust may not be reached until 65 KIAS.

Question 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 bleed air when operated at or near maximum altitude.
D. None of the above.

Answer 18

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

Question 19

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

A. True.
B. False.

Answer 19

A. True

Question 20

Regarding the Engine Oil System:

A. There is no minimum oil quantity limit for operating the engine in flight.
B. Oil is pressurized by an engine-driven oil pump.
C. Minimum oil quantity prior to start is 18 quarts.
D. All the above.

Answer 20

D. All the above.

Question 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.

Answer 21

C. An APU limit has been exceeded.

Question 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.

Answer 22

B. Manually positioning the thrust levers to the full forward position.

Question 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.

Answer 23

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

Question 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.

Answer 24

A. True

Question 25

In the attended mode, which of the following APU faults allow the APU to continue to operate?

A. High EGT.
B. High Oil Temperature.
C. Low Oil Pressure.
D. All of the above.

Answer 25

D. All of the above.,

Question 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.

Answer 26

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

Question 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.

Answer 27

B. False

Question 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.

Answer 28

B. False

Question 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.

Answer 29

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

Question 30

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

A. Normal.
B. Secondary.
C. Direct.
D. Both A and B

Answer 30

A. Normal

Question 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.

Answer 31

C. Using both APU generators as the power source.

Question 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.

Answer 32

B. False

Question 33

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 (TAP).
C. Auto Thrust Management (ATM).
D. Minimum Speed Correction.

Answer 33

B. Thrust Asymmetry Protection (TAP).

Question 34

The APU battery is designed to support _______ consecutive start attempts.

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

Answer 34

A. 2

Question 35

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

Answer 35

A. 43,100

Question 36

Starting both engines simultaneously may be accomplished with only one APU starter/generator.

A. True.
B. False.

Answer 36

B. False

Question 37

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 airplane is below 18,000 feet.
D. Continuous restarts until the engine is started or the fuel control switch is selected to CUTOFF.

Answer 37

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

Question 38

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.

Answer 38

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

Question 39

Which of the following is true with regard to loss of three starter generators (SGs) in flight?

A. The APU autostarts.
B. RAT will deploy.
C. Only the First Officer’s Navigation Display will be unpowered.
D. A and B are correct.

Answer 39

A. The APU autostarts.