Study Guide: Engines and APU

Question 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

Answer 1

Trailing edge flaps are extended beyond position 20

Question 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.

Answer 2

5

Question 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

Answer 3

A dedicated permanent magnet alternator (PMA)

Question 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

Answer 4

Dual dedicated generators (DDG)

Question 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

Answer 5

Permanent magnet generator (PMG)

Question 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

Answer 6

Decelerate to and remain at minimum fuel flow

Question 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

Answer 7

By performing a normal approach

Question 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?

Answer 8

There is no N2 overspeed protection

Question 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.

Answer 9

Performs an automatically controlled engine shutdown.

Question 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

Answer 10

Automatic reversion or manual selection to the alternate mode

Question 11

757/763: What does the amber REV light displayed above each EPR indication indicate?

Answer 11

The reverser is in transit

Question 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

Answer 12

N1 overspeed protection

Question 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

Answer 13

EPR based on thrust lever position

Question 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

Answer 14

EPR

Question 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°

Answer 15

EGT 0°

Question 16

757/767 When does the ENG START selector automatically move from the GND position to the AUTO position during engine start?

Answer 16

At approximately 50%

Question 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

Answer 17

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

Question 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

Answer 18

Positioned to AUTO

Question 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

Answer 19

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

Question 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

Answer 20

To protect the unit from thermal shock

Question 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

Answer 21

Automatically shut down

Question 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

Answer 22

The APU fuel valve is not in the commanded position

Question 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?

Answer 23

For a fault or a fire

Question 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

Answer 24

Throughout the aircraft operating envelope

Question 25

757/767: Fuel is normally supplied to the APU from the left main fuel tank. Should conditions require, fuel can be supplied from: ## Footnote 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

Answer 25

Any fuel tank through the crossfeed system

Question 26

757/767: While on the ground, turning the BAT switch off causes the APU to:

Answer 26

Shut down

Question 27

757/767: In flight, APU bleed air is available up to approximately:

Answer 27

17,000 feet

Question 28

757/767: The APU fuel valve fails to reach the commanded position during an APU start or shutdown, this is indicated by: ## Footnote 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

Answer 28

APU fault light and EICAS advisory APU FUEL VAL

Question 29

763: If a fault exists in the thrust reverser system, this will be indicated by: ## Footnote 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

Answer 29

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

Question 30

757: According to the graphic, the R EEC INOP light is illuminated. This indicates: ## Footnote 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

Answer 30

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

Question 31

757: According to the graphic, the L ELC INOP light is illuminated. This indicates: ## Footnote 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

Answer 31

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

Question 32

757/763: When pushed, the maximum indication reset (MAX IND RESET): ## Footnote 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

Answer 32

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

Question 33

757/767: The magenta fuel on command bug is displayed. When is this bug shown? ## Footnote 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

Answer 33

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

Question 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. ## Footnote a) CONT b) FLT c) AUTO d) OFF

Answer 34

CONT

Question 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). ## Footnote a) Idle speed b) 20% c) 10% d) 30%

Answer 35

Idle speed