Electrical Flashcards
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?
True.
If the permanent magnet alternator for the left engine EEC is not available, the EEC receives power from the: [8.60.10]
Airplane’s 115V 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]
True or False?
False.
The ground handling mode is powered __ if no other power source is available. [8.60.10]
Automatically when either FWD external power is connected (AVAIL)
The generator drive may disconnect automatically: [8.60.10]
Depending on the fault condition detected.
Circuit breaker status is always available: [8.60.10]
On the CBIC (circuit breaker indication and control).
The permanent magnet generators (PMGs): [8.60.10]
Power the flight control electronics.
The main battery provides power to the following: [8.60.10]
A. Electric braking (as backup source).
B. Captain’s flight instrument 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]
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]
True or False?
False.
The RAT will deploy automatically in flight if: [8.60.10]
All electrical power to the Captain and F/O’s flight instruments is lost.
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]
Load Inhibit.
If a total electrical failure occurs in flight, the PMGs provide Standby Power until RAT deployment. [8.60.10]
True or False?
False.
During automatic load shedding, which of the following indications may display?
[8.60.10]
- 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.
If both FWD external power are powering the main AC buses, when the APU starter/generators become available: [8.60.20]
The APU generators automatically replace all external power sources.
If a generator drive disconnect is initiated, either automatically or by selecting the respective Drive Disconnect Switch, with engines operating: [8.60.10]
- The “ELEC GEN DRIVE” EICAS message displays.
- The starter/generator is disengaged from the engine.
When the APU starter/generators are powering the main AC buses, and both FWD external power connectors are plugged in: [8.60.10]
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]
True or False?
True.
The 787 provides a “no break” power transfer when changing power sources. [8.60.10]
True or False?
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]
True or False?
True.
With the loss of a single engine generator, how is power provided to the associated main bus for that generator? [8.60.10]
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.
The PECS system provides: [8.60.10]
Heat dissipation for the LMPS.
The Starter/Generators (SGs): [8.60.10]
Are variable frequency and are directly connected to the engine gearbox.
The RAT: [8.60.10, 8.130.10]
- Provides backup hydraulic pressure to the Center system PRIMARY flight controls.
- Provides standby electrical power.
The standby electrical system consists of: [8.60.10]
The Main battery and the RAT generator.
Electrical power for the brake system is provided by: [8.60.10]
The 28vdc power system. The main battery is the backup source.
The APU generator OFF lights illuminate: [8.60.20]
The APU generator control breaker is open.
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?
True.
The aft external power receptacle is located: [8.60.10]
On the left side of the fuselage aft of the wing.
