SV Electrical

Question 1

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]

Answer 1

A. True.

Question 2

If the permanent magnet alternator for the left engine EEC is not available, the EEC
receives power from the: [8.60.10]

Answer 2

D. Airplane’s115V ac system.

Question 3

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]

Answer 3

B. False.

Question 4

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

Answer 4

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

Question 5

The generator drive may disconnect automatically: [8.60.10]

Answer 5

D. Depending on the fault condition detected.

Question 6

Circuit breaker status is always available: [8.60.10]

Answer 6

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

Question 7

The permanent magnet generators (PMGs): [8.60.10]

Answer 7

C. Power the flight control electronics.

Question 8

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

Answer 8

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

Question 9

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

Answer 9

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

Question 10

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]

Answer 10

B. False

Question 11

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

Answer 11

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

Question 12

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]

Answer 12

D. Load Inhibit.

Question 13

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

Answer 13

B. False.

Question 14

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

Answer 14

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.

Question 15

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

Answer 15

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

Question 16

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

Answer 16

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

Question 17

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

Answer 17

D. External power must be manually selected ON.

Question 18

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

Answer 18

A. True.

Question 19

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

Answer 19

A. True.

Question 20

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]

Answer 20

A. True

Question 21

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

Answer 21

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

Question 22

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

Answer 22

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

Question 23

The PECS system provides: [8.60.10]

Answer 23

A. Heat dissipation for the LMPS.

Question 24

The Starter/Generators (SGs): [8.60.10]

Answer 24

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

Question 25

The RAT: [8.60.10, 8.130.10]

Answer 25

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

Question 26

The standby electrical system consists of: [8.60.10]

Answer 26

C. The Main battery and the RAT generator

Question 27

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

Answer 27

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

Question 28

The APU generator OFF lights illuminate: [8.60.20]

Answer 28

C. The APU generator control breaker is open.

Question 29

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]

Answer 29

A. True

Question 30

The aft external power receptacle is located: [8.60.10]

Answer 30

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