SV Electrical Flashcards

1
Q

T or F
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]

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: [8.60.10]

A

D. Airplane’s115V ac system.

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3
Q

T or F
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]

A

B. False.

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4
Q

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

A

B. 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

D. Depending on the fault condition detected.

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6
Q

Circuit breaker status is always available: [8.60.10]

A

D. On the CBIC (circuit breaker indication and control).

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7
Q

The permanent magnet generators (PMGs): [8.60.10]

A

C. 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

B. External power is plugged in and power quality is acceptable.

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10
Q

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

A

B. False

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11
Q

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

A

D. 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

D. Load Inhibit.

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13
Q

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

A

B. False.

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14
Q

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

A

A. LOAD SHED is displayed next the affected equipment symbol on the
appropriate system synoptic.
B. A list of affected airplane systems displays on the electrical synoptic.
D. Both A and B are correct.

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15
Q

In flight, with only one starter generator available: [8.20.20]

A

A. All CACs shut down.
C. Power remains available to critical and essential equipment.
D. A and C are correct.

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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

B. The “ELEC GEN DRIVE” EICAS message displays.
C. The starter/generator is disengaged from the engine.
D. B and C are correct.

17
Q

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

A

D. External power must be manually selected ON.

18
Q

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

A

A. True.

19
Q

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

A

A. True.

20
Q

T or F
The Towing Power switch when ON, provides power for the Captain’s ACP,
Captain’s Flight Interphone, Nav lights, and brakes. [8.60.10]

A

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

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

A. Heat dissipation for the LMPS.

24
Q

The Starter/Generators (SGs): [8.60.10]

A

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

25
Q

The RAT: [8.60.10, 8.130.10]

A

B. Provides backup hydraulic pressure to the Center system PRIMARY flight
controls.
C. Provides standby electrical power.
D. B and C are correct.

26
Q

The standby electrical system consists of: [8.60.10]

A

C. The Main battery and the RAT generator

27
Q

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

A

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

28
Q

The APU generator OFF lights illuminate: [8.60.20]

A

C. The APU generator control breaker is open.

29
Q

T or F
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.
[8.60.10]

A

A. True

30
Q

The aft external power receptacle is located: [8.60.10]

A

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