During flights we have come to know that the APU can be shut down shortly after the engines start running, as the energy needed can then be produce by the engines. What more can you tell about the relationship between the Engine and the APU for the B777 plane? Take the test to find out!
TO 1
D-TO
TO
TO 2
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The engines will exceed the maximum rated thrust.
The engines will produce maximum climb thrust
The engines will produce maximum rated thrust.
The EEC alternate mode will automatically engage.
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The engines will exceed the maximum rated thrust.
The engines will produce maximum cruise thrust.
The EEC alternate mode will automatically engage.
The engines will produce maximum rated thrust.
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Engine oil pressure is low.
Engine oil pressure is high.
Engine oil temperature is low
Engine oil temperature is high.
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Engine oil pressure is low.
Engine oil pressure is high.
Engine oil temperature is low.
Engine oil temperature is high.
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The engine fuel valve on the left engine is closed.
The spar or engine fuel valve on the left engine has not reached its commanded position.
Both the spar and the engine fuel valves on the left engine are commanded to the same position.
The fuel/oil heat exchanger valve is not functioning.
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The engine fuel valve on the right engine is open.
Both the spar and the engine fuel valves on the right engine are commanded to the same position.
The spar or engine fuel valve on the right engine has not reached its commanded position.
The fuel filter bypass valve is not functioning.
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After START has been selected on the START/IGNITION selector
After reaching maximum motoring speed
After the engine stabilizes at idle
After 18% N2 has been reached
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Left hydraulic system
Center hydraulic system
Left engine bleed air
Right engine bleed air
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Left engine bleed air
Right engine bleed air
Center hydraulic system
Right hydraulic system
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The right engine reverser will provide maximum reverse thrust for a limited time.
The right engine reverser will not deploy or will be limited to idle on landing.
The right engine reverse thrust indication is not valid.
The right engine reverse thrust is limited to rejected takeoffs only.
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The secondary engine indications
The primary engine indications
The status display
There is no flight deck display for engine oil quantity
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Low oil pressure
High oil temperature
Broken fanblade
Hot start
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Auto-relight provides flameout protection by activating the autostart system.
Auto-relight provides flameout protection by activating both ignitors.
Auto-relight opens the start valve automatically if the engine N2 decreases.
Auto-relight provides hung start protection by deactivating the ignitor.
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The APU is out of fuel.
The APU in cooldown mode.
The APU has automatically shut down.
The APU controller has shut down the packs.
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The APU is out of fuel.
An APU limit has been exceeded.
The APU has automatically shut down.
The APU pneumatic output is limited.
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APU controller failure
High EGT
Low oil pressure
High oil temperature
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TO 1
D-TO 1
TO
D-TO
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The EEC automatically uses the alternate mode.
Full rated thrust is automatically commanded on the affected engine.
The Autothrottle disconnects.
The affected engine goes to flight idle.
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The engine operates in the soft alternate mode.
The EICAS message ENG CONTROL is displayed
Maximum and commanded N1 values are removed from the N1 indication.
Reference and target N1 are displayed on the N1 indication.
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Control for the left engine is in the alternate mode.
A fault is detected in the left engine control system.
Left engine speed is below idle.
A limit has been exceeded on the left engine.
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The right fuel control switch is in RUN at low engine RPM with the autostart switch OFF.
The right engine start valve is open when commanded close.
Autostart has failed to start the left engine.
Autostart is attempting to start the right engine, wait for further indications.
The left engine autostart switch is OFF.
Autostart has failed to start the left engine.
The left engine start/ignition selector remains in the START position or the start valve is open when commanded closed.
The left fuel control switch is in RUN at low engine RPM with the autostart switch OFF.
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The displayed line is red.
The line displays with the fuel control switch in CUTOFF
The line displays with N2 RPM below idle.
The line displays at all times on the ground.
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The engine RPM is below idle and the fuel control switch is in RUN.
The In-Flight Start Envelope display shows the airspeed range foe an in-flight start at the current flight level when the airplane is below the maximum flight level for an in-flight start.
The respective engine fire switch is in.
The In-Flight Start Envelope display is magenta.
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The engine fuel valve is armed.
The spar fuel valve is armed.
The engine ignitor(s) is/are armed.
The EEC opens the valve and turns on the ignitor(s) when required.
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A secondary engine Parameter is exceeded
The displays initially receive electrical power.
A Fuel Control switch is moved to CUTOFF on the ground.
A Fuel Control switch is moved to CUTOFF in flight.
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A manual start is possible with the Autostart system switch in the ON position.
Manual start procedures are part of the normal Engine Start procedure.
The EEC controls when fuel is first provided to the engine.
The EICAS message ENG AUTOSTART is displayed if the fuel control switch is moved to RUN before the rpm specified in the manual start procedure.
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The EEC alternates ignitors for successive starts on the ground.
Standby AC power is the normal power source.
Each engine has four ignitors.
Engine Auto-Relight requires the Autostart system to be on.
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The autopilot disengages when the reverse thrust levers are pulled back to the interlock position.
The auto speedbrakes deploy when the reverse thrust levers are pulled back to the interlock position.
The reverse thrust levers can be raised only when the forward thrust levers are in the idle position and the radio altitude is less than 10 feet.
The reverser translating sleeves move aft assisted by fan air flowing through stationary cascade guide vanes.
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The EICAS message ENG REV LIMITED is displayed if the reverser cannot deploy when commanded.
Not all conditions limiting or preventing reverse thrust can be detected before reverse thrust is selected.
The amber REV indication changes to green REV when the reverser interlock is released.
The reverse thrust levers can be limited from moving beyond the interlock position by conditions that limit or prevent reverse thrust.
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A red ENG FAIL is displayed on the PFD if actual thrust is less than commanded thrust during takeoff with airspeed between 65 knots and V1.
The EICAS message ENG FAIL (L or R) is displayed if an engine unexpectedly decelerates to less than idle speed.
The EICAS message ENG FAIL (L or R) is displayed until the engine recovers or the fuel control switch is moved to CUTOFF.
The EICAS message ENG FAIL (L or R) is displayed if actual thrust is not increasing to commanded thrust and airspeed is below V1.
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Airborne vibration indications have limiting values that must not be exceeded.
High vibration levels automatically display the secondary engine parameters.
No flight crew actions are based solely on vibration indications.
High N1 vibration indication would most likely accompanied by tactile vibration.
There is no minimum oil quantity
Low oil quantity cannot automatically display the secondary engine display.
Low oil quantity is displayed as black numbers on a white background.
There are no flight crew procedures based solely on response to low oil quantity.
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The APU can be started by an electric start motor or an air turbine starter.
The main airplane battery powers the APU fire detection system.
The APU battery powers the electric start motor, the inlet door and the fuel valve.
The air turbine starter has priority over the electric start motor.
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During APU start on the ground, starting fuel is supplied from the center tank DC fuel pump until AC power is available.
The starter engages immediately. When the air inlet door reaches full open, fuel and ignition are provided.
With the APU generator switch in the OFF position, automatic APU start in the event that both AC transfer busses lose power is inhibited
On the ground, the APU can be started with no pumps operating.
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