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B756 SV (Systems Validation) > Engine, APU > Flashcards

Engine, APU Flashcards

1
Q

1) 757/763: There are two engine idle speeds: minimum and approach idle. One way
approach idle is activated automatically is when:
a) Trailing edge flaps are extended beyond position 20
b) Glideslope capture
c) Continuous ignition is selected to ON
d) Both throttles at idle and speed brakes are deployed

A

a) Trailing edge flaps are extended beyond position 20

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2
Q

2) 757/763: Approach idle provides better engine acceleration for go-around or reverse
thrust. After a ___ second delay following touchdown, the engines decelerate to
minimum idle to minimize landing distance.
a) 3
b) 8
c) 5
d) 10

A

c) 5

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3
Q

3) 763: When the engine is operating, the engine electronic engine control (EEC) is
powered by:
a) Standby AC and DC busses
b) A dedicated permanent magnet alternator (PMA)
c) Left main AC bus
d) Hot battery bus

A

b) A dedicated permanent magnet alternator (PMA)

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4
Q

4) 757: Each engine electronic engine control (EEC) is powered by:
a) Dual dedicated generators (DDG)
b) Standby AC and DC busses
c) Left main AC bus
d) Hot battery bus

A

a) Dual dedicated generators (DDG)

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5
Q 
5) 764: Anytime the engine is running, the engine electronic engine control (EEC) is
powered by:
a) Permanent magnet generator (PMG)
b) Standby AC and DC busses
c) Left main AC bus
d) Hot battery bus
A

a) Permanent magnet generator (PMG)

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6
Q

6) 763: If both channels in an electronic engine control (EEC) fail, the associated engine
will:
a) Revert to its backup system, hydro-mechanical operation
b) Maintain above idle speed
c) Decelerate to and remain at minimum fuel flow
d) Maintain its current speed until the associated EEC switch is placed in the OFF
position

A

c) Decelerate to and remain at minimum fuel flow

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7
Q

7) 757/763: How can continuous ignition and approach idle be selected without using the
engine anti-ice switches?
a) By placing the wing anti-ice switch to ON
b) By selecting flap position 1, 5 or 15
c) By performing a normal approach
d) Both cannot be selected unless the engine anti-ice switches are selected on

A

c) By performing a normal approach

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8
Q

8) 757: The thrust system consists of a hydromechanical engine fuel control with an
electronic engine control (EEC) unit. Is any overspeed protection provided for the N2
rotor?
a) The N2 rotor has protection but only during reversing operations
b) There is no N2 overspeed protection
c) There is protection for the N2 rotor provided the EEC is operating normally
d) There is always N2 overspeed protection during all phases of engine operation

A

b) There is no N2 overspeed protection

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9
Q

9) 764: If both channels in an electronic engine control (EEC) fail, the associated engine:
a) Reverts to hydro-mechanical operation
b) Reverts to the N2 control mode
c) Decelerates to and remains at minimum fuel flow
d) Performs an automatically controlled engine shutdown.

A

d) Performs an automatically controlled engine shutdown.

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10
Q

10) 767: According to the graphic, the left electronic engine control alternate mode (ALTN)
switch light has illuminated. This indicates:
a) Automatic reversion or manual selection to the alternate mode
b) Reverse thrust has no overspeed protection
c) Maximum thrust red-line protection is no longer available
d) The EEC can no longer control engine speed and decelerates to and remains at
minimum fuel flow

A

a) Automatic reversion or manual selection to the alternate mode

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11
Q

11) 757/763: What does the amber REV light displayed above each EPR indication indicate?
a) The reverser is fully retracted
b) The reverser is fully deployed
c) The reverser is in transit
d) A fault is detected in the reverser

A

c) The reverser is in transit

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12
Q 
12) 757: The thrust control system includes an electronic limiter control (ELC) unit. What is
its primary purpose?
a) N2 overspeed protection
b) N3 overspeed protection
c) N1 overspeed protection
d) EPR overboost protection
A

c) N1 overspeed protection

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13
Q

13) 757: The thrust system consists of a hydromechanical engine fuel control with an
electronic engine control (EEC) unit. The EEC sets thrust by controlling:
a) N1 based on thrust lever position
b) N2 based on thrust lever position
c) EPR based on thrust lever position
d) N3 based on thrust lever position

A

c) EPR based on thrust lever position

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14
Q

14) 757/763: The thrust management computer (TMC) calculates a reference _____ based
on existing pressure altitudes and ambient temperature data from the air data system.
a) N3
b) N2
c) N1
d) EPR

A

d) EPR

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15
Q

15) 757: The FUEL CONTROL switches have three positions: RUN, RICH, and CUTOFF.
When should the RICH position be used during engine start?
a) EGT 0°
b) EGT > 0°
c) After an aborted engine start
d) EGT < 0°

A

a) EGT 0°

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16
Q

16) 757/767 When does the ENG START selector automatically move from the GND
position to the AUTO position during engine start?
a) At approximately 51%
b) At approximately 50%
c) At approximately 46%
d) At approximately 45%

A

b) At approximately 50%

17
Q

17) 757/767: Minimum idle is a lower thrust than approach idle and is selected:
a) When continuous ignition is selected ON
b) When the leading edge slats are extended
c) During ground operation and all phases of flight except approach and landing
d) When the engine anti-ice switches are positioned to OFF

A

c) During ground operation and all phases of flight except approach and landing

18
Q

18) 757/763: When the standby engine indicator (SEI) selector is _________ and both CRTs
fail, engine indications will be displayed automatically.
a) Positioned to OFF
b) Positioned to AUTO or OFF
c) Positioned to AUTO
d) In any position as long as AC power is still available

A

c) Positioned to AUTO

19
Q

19) 757/767: With the FUEL CONTROL switch out of CUTOFF, rotating the ENGINE START
selector to the FLT position:
a) Causes selected ignition system for the associated engine to operate
continuously
b) Causes an auto relight to be initiated automatically
c) Bypasses the ignition selector and causes both ignition systems to operate
continuously
d) Bypasses the ignition selector and causes both ignition systems to operate
continuously for 120 seconds

A

c) Bypasses the ignition selector and causes both ignition systems to operate
continuously

20
Q

20) 757/767: During APU shutdown, the APU control system incorporates a time-delay
feature. The time delay is variable from 0 to 120 seconds. Why is this feature
incorporated?
a) To prevent AC electrical surges
b) To prevent rapid bleed air depressurization
c) To protect the unit from thermal shock
d) To allow time for the APU to position the variable guide vanes

A

c) To protect the unit from thermal shock

21
Q

21) 757/767: According to the graphic, the APU FAULT light is illuminated. The light
illuminates whenever a fault is sensed. In this situation, the APU will:
a) Automatically shut down
b) Shut down only after placing the selector to OFF and the time-delay feature is
satisfied
c) Continue to run if the fault was sensed while airborne
d) Continue to run if the fault was detected on the ground

A

a) Automatically shut down

22
Q

22) 757/767: During APU start and shutdown, the FAULT light illuminates momentarily. What
causes its illumination?
a) The APU fuel valve is not in the commanded position
b) The APU DC fuel pump has failed
c) The APU battery voltage has dropped below a preset value
d) The APU control circuitry is starting up or shutting down

A

a) The APU fuel valve is not in the commanded position

23
Q

23) 757/767: During normal operations, APU shutdown incorporates a time-delay feature
permitting APU cooling. When is the APU shut down automatically and the cool-down
delay bypassed?
a) When AC power is unavailable, and the APU DC fuel pump fails
b) When the left forward fuel pump is selected off
c) For a fault or a fire
d) When one or both of the APU fire loops fail

A

c) For a fault or a fire

24
Q

24) 757/767: Although the primary purpose of the APU is to supply electrical power and
bleed air on the ground before engine start, the APU can also be started inflight, and
provide electrical power:
a) Throughout the aircraft operating envelope
b) Up to 17,000 feet
c) Up to 35,000 feet
d) Up to 41,000 feet

A

a) Throughout the aircraft operating envelope

25
Q

25) 757/767: Fuel is normally supplied to the APU from the left main fuel tank. Should
conditions require, fuel can be supplied from:
a) The right main fuel tank only
b) Any fuel tank through the crossfeed system
c) The left main fuel tank only
d) The center fuel tank only

A

b) Any fuel tank through the crossfeed system

26
Q

26) 757/767: While on the ground, turning the BAT switch off causes the APU to:
a) Shut down
b) Continue running, but the RUN light will no longer be visible
c) Continue running, but the APU selector will become unpowered
d) Shut down if external power is selected on

A

a) Shut down

27
Q

27) 757/767: In flight, APU bleed air is available up to approximately:
a) 41,000 feet
b) 35,000 feet
c) 17,000 feet
d) 43,000 feet

A

c) 17,000 feet

28
Q

28) 757/767: The APU fuel valve fails to reach the commanded position during an APU start
or shutdown, this is indicated by:
a) EICAS advisory APU FUEL VAL
b) APU FAULT light and flashing APU RUN light
c) APU fault light and EICAS advisory APU FUEL VAL
d) The APU FAULT light

A

c) APU fault light and EICAS advisory APU FUEL VAL

29
Q

29) 763: If a fault exists in the thrust reverser system, this will be indicated by:
a) A REV ISLN light on the center control pedestal and status message
b) A REV ISLN light on the center control pedestal and an EICAS advisory message
REV ISLN VAL
c) An amber REV annunciation above each digital EPR indication
d) There are no indications shown when on the ground

A

b) A REV ISLN light on the center control pedestal and an EICAS advisory message
REV ISLN VAL

30
Q

30) 757: According to the graphic, the R EEC INOP light is illuminated. This indicates:
a) A failure is detected but the EEC will still provide overboost protection
b) A failure is detected in the system and the EEC trim motor holds the current trim
level until the unit is turned off
c) A failure is detected and overspeed protection is no longer provided
d) A failure is detected in the system and engine limit protection is not available

A

b) A failure is detected in the system and the EEC trim motor holds the current trim
level until the unit is turned off

31
Q

31) 757: According to the graphic, the L ELC INOP light is illuminated. This indicates:
a) A failure is detected in the system and engine limit protection is not available
b) A failure is detected and overboost protection is no longer provided
c) A failure is detected but the ELC will still provide N1 overspeed protection
d) A failure is detected in the system and the ELC will hold the current trim level
until the unit is turned off

A

d) A failure is detected in the system and the ELC will hold the current trim level
until the unit is turned off

32
Q

32) 757/763: When pushed, the maximum indication reset (MAX IND RESET):
a) Resets and blanks all overtemp and overspeed values stored in computer
memory
b) Resets and blanks the reduced thrust setting to the maximum thrust value
c) Resets and blanks all standby engine indicator (SEI) maximum exceedance
values
d) Resets and blanks all maximum exceedance values on EGT, N1, N2, and N3

A

d) Resets and blanks all maximum exceedance values on EGT, N1, N2, and N3

33
Q

33) 757/767: The magenta fuel on command bug is displayed. When is this bug shown?
a) Only on the ground when an engine is shutdown
b) Only inflight when the airspeed is greater than that for a windmilling start
c) Engine is shutdown on the ground, or inflight, when X-BLD is displayed
d) Only inflight when X-BLD is annunciated

A

c) Engine is shutdown on the ground, or inflight, when X-BLD is displayed

34
Q

34) 764/763(66XX): There are two engine idle speeds: minimum idle and approach idle. The
EEC selects these idle speeds automatically. Rotating the ENGINE START selectors to
_______ manually selects approach idle.
a) CONT
b) FLT
c) AUTO
d) OFF

A

a) CONT

35
Q

35) 764: The ignition system includes an automatic relight feature. It is enabled in the air or
on the ground if N2 drops below _____. If this occurs, the EEC will energize both ignition
systems for the affected engine(s).
a) Idle speed
b) 20%
c) 10%
d) 30%

A

a) Idle speed

B756 SV (Systems Validation) (17 decks)

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