Electrical Flashcards
(30 cards)
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. True.
A. True.
If the permanent magnet alternator for the left engine EEC is not available, the EEC receives power from the: [8.60.10]
.
D. Airplane’s115V ac system.
D. Airplane’s115V ac system
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]
B. False.
B. False
The ground handling mode is powered __ if no other power source is available. [8.60.10]
B. Automatically when either FWD external power is connected (AVAIL)
B. Automatically when either FWD external power is connected (AVAIL)
The generator drive may disconnect automatically: [8.60.10]
D. Depending on the fault condition detected.
D. Depending on the fault condition detected
Circuit breaker status is always available: [8.60.10]
D. On the CBIC (circuit breaker indication and control).
D. On the CBIC (circuit breaker indication and control).
The permanent magnet generators (PMGs): [8.60.10]
C. Power the flight control electronics.
C. Power the flight control electronics.
The main battery provides power to the following: [8.60.10]
A. Electric Braking
B. Captain’s flt inst bus until RAT deployment
C. L VHF Communications
D. All of the above.
A. Electric Braking
B. Captain’s flt inst bus until RAT deployment
C. L VHF Communications
D. All of the above.
When the FWD or AFT external power switches are illuminated “AVAIL”,
they indicate: [8.60.20]
B. External power is plugged in and power quality is acceptable.
B. External power is plugged in and power quality is acceptable
Thermal circuit breakers may be reset via CBIC as long as the pilots accomplish the Unannunciated Circuit Breaker supplementary procedure? [8.60.20]
B. False.
B. False.
The RAT will deploy automatically in flight if: [8.60.10]
D. All electrical power to the Captain and F/O’s flight instruments is lost.
D. All electrical power to the Captain and F/O’s flight instruments is lost.
If a generator drive disconnect is initiated, either automatically or by selecting the respective Drive Disconnect Switch, with engines operating: [8.60.10]
B. The “ELEC GEN DRIVE” EICAS message displays.
C. The starter/generator is disengaged from the engine.
D. B and C are correct.
B. The “ELEC GEN DRIVE” EICAS message displays.
C. The starter/generator is disengaged from the engine.
D. B and C are correct.
When the APU starter/generators are powering the main AC buses, and both FWD external power connectors are plugged in: [8.60.10]
D. External power must be manually selected ON.
D. External power must be manually selected ON
The electrical system can be powered by the APU and FWD external at the same time. [8.60.10]
A. True.
A. True.
The 787 provides a “no break” power transfer when changing power sources. [8.60.10]
A. True.
A. True.
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. True.
A. True
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.
A. The lost main AC bus is now powered by another main AC bus.
The Large Motor Power Distribution System (LMPS) powers: [8.60.10]
A. CACs and Ram fans.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.
A. CACs and Ram fans.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.
The PECS system provides: [8.60.10]
A. Heat dissipation for the LMPS.
A. Heat dissipation for the LMPS
The Starter/Generators (SGs): [8.60.10]
B. Are variable frequency and are directly connected to the engine gearbox.
B. Are variable frequency and are directly connected to the engine gearbox.
The RAT: [8.60.10, 8.130.10]
B. Provides backup hydraulic pressure to the Center system PRIMARY flight
controls.
C. Provides standby electrical power.
D. B and C are correct.
B. Provides backup hydraulic pressure to the Center system PRIMARY flight
controls.
C. Provides standby electrical power.
D. B and C are correct.
The standby electrical system consists of: [8.60.10]
C. The Main battery and the RAT generator.
C. The Main battery and the RAT generator.
Electrical power for the brake system is provided by: [8.60.10]
A. The 28vdc power system. The main battery is the backup source.
A. The 28vdc power system. The main battery is the backup source
The APU generator OFF lights illuminate: [8.60.20]
C. The APU generator control breaker is open.
C. The APU generator control breaker is open.
