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UAL 787 SKV > Electrical > Flashcards

Electrical Flashcards

1
Q

The Bus Power Control Units (BPCU) provide dynamic electrical load management when the airplane is operating on any available electrical power source. [8.60.10]

True or False?

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: [8.60.10]

A

Airplane’s 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. [8.60.10]

True or False?

A

False.

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4
Q

The ground handling mode is powered __ if no other power source is available. [8.60.10]

A

Automatically when either FWD external power is connected (AVAIL)

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5
Q

The generator drive may disconnect automatically: [8.60.10]

A

Depending on the fault condition detected.

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6
Q

Circuit breaker status is always available: [8.60.10]

A

On the CBIC (circuit breaker indication and control).

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7
Q

The permanent magnet generators (PMGs): [8.60.10]

A

Power the flight control electronics.

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8
Q

The main battery provides power to the following: [8.60.10]

A

A. Electric braking (as backup source).
B. Captain’s flight instrument bus until RAT deployment
C. L VHF communications.
D. All of the above.

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9
Q

When the FWD or AFT external power switches are illuminated “AVAIL”, they indicate: [8.60.20]

A

External power is plugged in and power quality is acceptable.

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10
Q

Thermal circuit breakers may be reset via CBIC as long as the pilots accomplish the Unannunciated Circuit Breaker supplementary procedure? [8.60.20]

True or False?

A

False.

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11
Q

The RAT will deploy automatically in flight if: [8.60.10]

A

All electrical power to the Captain and F/O’s flight instruments is lost.

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12
Q

When on the ground prior to engine start and the Hydraulic Electric Demand pumps are selected to AUTO, the pumps do not operate. This function is called: [8.60.10]

A

Load Inhibit.

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13
Q

If a total electrical failure occurs in flight, the PMGs provide Standby Power until RAT deployment. [8.60.10]

True or False?

A

False.

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14
Q

During automatic load shedding, which of the following indications may display?
[8.60.10]

A
  • LOAD SHED is displayed next the affected equipment symbol on the appropriate system synoptic.
  • A list of affected airplane systems displays on the electrical synoptic.
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15
Q

If both FWD external power are powering the main AC buses, when the APU starter/generators become available: [8.60.20]

A

The APU generators automatically replace all external power sources.

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16
Q

If a generator drive disconnect is initiated, either automatically or by selecting the respective Drive Disconnect Switch, with engines operating: [8.60.10]

A
  • The “ELEC GEN DRIVE” EICAS message displays.
  • The starter/generator is disengaged from the engine.
17
Q

When the APU starter/generators are powering the main AC buses, and both FWD external power connectors are plugged in: [8.60.10]

A

External power must be manually selected ON.

18
Q

The electrical system can be powered by the APU and FWD external at the same time. [8.60.10]

True or False?

A

True.

19
Q

The 787 provides a “no break” power transfer when changing power sources. [8.60.10]

True or False?

A

True.

20
Q

The Towing Power switch when ON, provides power for the Captain’s ACP, Captain’s Flight Interphone, Nav lights, and brakes. [8.60.10]

True or False?

A

True.

21
Q

With the loss of a single engine generator, how is power provided to the associated main bus for that generator? [8.60.10]

A

The lost main AC bus is now powered by another main AC bus.

22
Q

The Large Motor Power Distribution System (LMPS) powers: [8.60.10]

A

A. CACs and Ram fans.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.

23
Q

The PECS system provides: [8.60.10]

A

Heat dissipation for the LMPS.

24
Q

The Starter/Generators (SGs): [8.60.10]

A

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

25
Q

The RAT: [8.60.10, 8.130.10]

A
  • Provides backup hydraulic pressure to the Center system PRIMARY flight controls.
  • Provides standby electrical power.
26
Q

The standby electrical system consists of: [8.60.10]

A

The Main battery and the RAT generator.

27
Q

Electrical power for the brake system is provided by: [8.60.10]

A

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

28
Q

The APU generator OFF lights illuminate: [8.60.20]

A

The APU generator control breaker is open.

29
Q

When using external power for engine start, use of the Aft External connection reduces the amount of load shedding that takes place. [8.60.10]

True or False?

A

True.

30
Q

The aft external power receptacle is located: [8.60.10]

A

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

UAL 787 SKV (15 decks)

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