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787 > electrical > Flashcards

electrical Flashcards

1
Q

The Bus Power Control Units (BPCU) provide dynamic electrical load management when the aircraft is operating on any available electrical power source.
A. True.
B. False.

A

A. True.

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2
Q 
If the permanent magnet alternator for the left engine EEC is not available, the EEC
receives power from the:
A. F/O's flight instrument bus.
B. 28v DC system and main battery. 
C. Captains flight instrument bus.
D. Aircrafts 115V ac system.
A

D. Aircrafts 115V ac system.

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3
Q

When starting an engine using external power to energize the starters, a minimum of
two electrical sources are required. One of these MUST be AFT external power.
A. True.
B. False.

A

B. False.

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4
Q

The ground handling mode is powered if no other power source is available.
A. Automatically when both forward external power sources are in use (ON)
B. Automatically when either FWD external power is connected (AVAIL)
C. Only if the AFT external power is connected (AVAIL)
D. The battery switch is ON

A

B. Automatically when either FWD external power is connected (AVAIL)

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5
Q

The generator drive may disconnect automatically:
A. Only on the ground.
B. Anytime an engine is shut down in flight.
C. Only when due to bearing failure.
D. Depending on the fault condition detected.

A

D. Depending on the fault condition detected.

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6
Q 
Circuit breaker status is always available .
A. On EICAS.
B. On the Status page display.
C. On the respective system synoptic.
D. On the SYS pages CB display.
A

D. On the SYS pages CB display.

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7
Q

The permanent magnet generators (PMGs)__________
A. Always power the Captains standby electrical system.
B. Provide a backup source for the hot battery buss and main battery charger.
C. Power the flight control electronics.
D. All the above.

A

C. Power the flight control electronics.

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8
Q

The main battery provides power to the following:
A. Electric braking (as backup source).
B. Captain’s flight instrument bus until RAT deployment
C. L VHF communications.
D. All of the above.

A

D. All of the above.

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9
Q

When the FWD or AFT external power switches are illuminated “AVAIL” they indicate:
A. An unpowered external power plug has been plugged in.
B. External power is plugged in and power quality is within limits.
C. DC bus synchronization has failed and external power is required.
D. The system is available for external power to be plugged in.

A

B. External power is plugged in and power quality is within limits.

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10
Q

Which of the following is true with regard to loss of three Starter Generators (SG’s)
in flight?
A. The APU autostarts.
B. RAT will deploy.
C. Only the First Officers Navigation Display will be unpowered.
D. A and B are correct.

A

A. The APU autostarts.

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11
Q

Thermal circuit breakers may be reset via CBIC as long as the crew accomplishes the Unannunciated Circuit Breaker supplementary procedure?
A. True.
B. False

A

B. False.

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12
Q

The RAT will deploy automatically in flight if:
A. Three starter generators are lost simultaneously.
B. The L2 bus is lost in conjunction with BAT LOW EICAS message.
C. Any two starter/generators fail.
D. All electrical power to the Captain and FO’s flight instruments is lost

A

D. All electrical power to the Captain and FO’s flight instruments is lost.

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13
Q

When on the ground prior to engine start and the Hydraulic Electric Demand pumps
ON, the pumps do not operate. This function is called:
A. Load Shedding.
B. Non-essential circuit breakers will open as needed.
C. APU autostart.
D. Load Inhibit.

A

D. Load Inhibit.

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14
Q

If a total electrical failure occurs in flight, the PMGs provide Standby Power until
RAT deployment.
A. True.
B. False

A

B. False.

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15
Q

During automatic load shedding which of the following indications may display?
A. LOAD SHED is displayed next the affected equipment symbol on the appropriate system synoptic.
B. A list of affected aircraft systems displays on the electrical synoptic.
C. “LOAD SHED” EICAS message displays.
D. Both A and B are correct.

A

D. Both A and B are correct.

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16
Q

Inflight, with only one starter generator available:
A. All CACs shut down.
B. The standby inverter is powered.
C. Power remains available to critical and essential equipment.
D. A and C are correct.

A

C. Power remains available to critical and essential equipment

17
Q

With the aircraft unpowered on the ground, to begin the CCR start-up process:
A. Pushing the BATTERY switch to ON will begin the left and right CCR start-up.
B. First start the APU as both CCR’s require normal AC power.
C. Turn both IRS selectors to ON.
D. Select the BATTERY switch ON.

A

D. Select the BATTERY switch ON.

18
Q

If a generator drive disconnect is initiated, either automatically or by selecting the respective Drive Disconnect Switch, with engines operating:
A. Select the RESET option in the electrical synoptic to reconnect the starter/generator.
B. The “ELEC GEN DRIVE” EICAS message displays.
C. The starter/generator is disengaged from the engine.
D. B and C are correct.

A

D. B and C are correct.

19
Q

When the APU starter/generators are powering the main AC busses, and both FWD
external power connectors are plugged in:
A. External power is automatically applied.
B. External power only becomes available after APU shutdown.
C. The APU generator powers the R1 and R2 AC busses & FWD external powers the L1 and L2 busses.
D. External power must be manually selected ON.

A

D. External power must be manually selected ON

20
Q

The electrical system can be powered by the APU and FWD external at the same time.
A. True.
B. False.

A

A. True.

21
Q

The 787 provides a “no break” power transfer when changing power sources.
A. True.
B. False.

A

B. False.

22
Q

The Towing Power switch when ON, provides power for the Captains ACP, Captains Flight Interphone, Nav lights, and Brakes.
A. True.
B. False.

A

A. True.

23
Q

With the loss of a single engine generator, how is power provided to the associated main bus for that generator?
A. The lost main AC bus is now powered by the other main AC busses.
B. All 3 powered AC busses share the load equally.
C. AC Standby Inverter powers the bus.
D. The PMG’s will provide backup power to the associated bus.

A

A. The lost main AC bus is now powered by the other main AC busses.

24
Q 
The Large Motor Power Distribution System (LMPS) powers:
A. CACs.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.
A

D. All the above.

25
Q

The PECS system provides:
A. Heat dissipation for the LMPS.
B. Cooling for the FD displays and indicators.
C. Cooling for the left and right CCR’s.
D. Heat dissipation for the LMPS anytime the battery switch is on.

A

A. Heat dissipation for the LMPS.

26
Q

After landing, PECS cooldown begins when both packs AND the hydraulic EMP’s are shutdown. Minimum time required prior to removing electrical power is:
A. 22 minutes when using only one external power source.
B. There is no minimum when the OAT if 15°C or below.
C. 10 minutes when using APU power or both forward external power sources.
D. A and C are correct.

A

D. A and C are correct.

27
Q

The Starter/Generators (SGs):
A. Are variable frequency and utilize a CSD to provide stable output.
B. Are variable frequency and are directly connected to the engine gearbox.
C. Operate in pairs through a motor drive regulator.
D. Are variable frequency, and provide one primary and one backup output to each L and R main bus.

A

B. Are variable frequency and are directly connected to the engine gearbox.

28
Q

The RAT:
A. May only be deployed below 310kts/.85 Mach.
B. Provides backup hydraulic pressure to the Center system PRIMARY flight controls.
C. Provides standby electrical power.
D. B and C are correct.

A

D. B and C are correct.

29
Q

The standby electrical system consists of:
A. The Standby Inverter, the Main Battery, APU Battery, and the PMG’s.
B. The flight control electronics system.
C. The Main battery and the RAT generator.
D. All the above.

A

C. The Main battery and the RAT generator.

30
Q

Electrical power for the brake system is provided by:
A. The 28vdc power system. The main battery is the backup source.
B, The main battery for the primary source. The 28 vdc system is the backup.
C. The left PMGs as the primary source. The Captain’s Flight Instrument bus for backup.
D. Main battery for the primary system and 20 minute rechargeable batteries for the backup.

A

A. The 28vdc power system. The main battery is the backup source.

31
Q

The APU generator OFF lights illuminate:
A. When the APU generator is in standby mode.
B. Anytime the APU generator has been manually replaced by external power.
C. The APU generator control breaker is open.
D. The APU generator CSD has been failed.

A

C. The APU generator control breaker is open.

32
Q

When using external power for engine start, use of the Aft External connection improves the start time and reduces the amount of load shedding that takes place.
A. True.
B. False.

A

A. True.

33
Q

The aft external power receptacle is located:
A. On the left side of the fuselage immediately below the positive pressure relief valve.
B. On the fuselage, between the main gear doors.
C. On the left side of the fuselage aft of the wing.
D. In a locked compartment in the wing/body fairing on the left side of the fuselage, aft of the wing.

A

C. On the left side of the fuselage aft of the wing.

787 (16 decks)

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