Electrical

Question 1

1) The Bus Power Control Units (BPCU) provide dynamic electrical load management when the aircraft is operating on any available electrical power source.
A. True.
B. False

Answer 1

1) The Bus Power Control Units (BPCU) provide dynamic electrical load management when the aircraft is operating on any available electrical power source.
A. True.

Question 2

2) If the permanent magnet alternator for the left engine EEC is not available, the EEC receives power from the:
A. F/O's flight instrument bus.
B. 28v DC system and main battery.
C. Captains flight instrument bus.
D. Aircrafts 115V ac system.

Answer 2

2) If the permanent magnet alternator for the left engine EEC is not available, the EEC receives power from the:

D. Aircrafts 115V ac system.

Question 3

3) 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.
A. True.
B. False.

Answer 3

3) 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.

B. False.

Question 4

4) The ground handling mode is powered if no other power source is available.
A. Automatically when both forward external power sources are in use (ON)
B. Automatically when either FWD external power is connected (AVAIL)
C. Only if the AFT external power is connected (AVAIL)
D. The battery switch is ON

Answer 4

4) The ground handling mode is powered if no other power source is available.

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

Question 5

5) The generator drive may disconnect automatically:
A. Only on the ground.
B. Anytime an engine is shut down in flight.
C. Only when due to bearing failure.
D. Depending on the fault condition detected.

Answer 5

5) The generator drive may disconnect automatically:

D. Depending on the fault condition detected.

Question 6

6) Circuit breaker status is always available .
A. On EICAS.
B. On the Status page display.
C. On the respective system synoptic.
D. On the SYS pages CB display.

Answer 6

6) Circuit breaker status is always available .

D. On the SYS pages CB display.

Question 7

7) The permanent magnet generators (PMGs)__________
A. Always power the Captains standby electrical system.
B. Provide a backup source for the hot battery buss and main battery charger.
C. Power the flight control electronics.
D. All the above.

Answer 7

7) The permanent magnet generators (PMGs)__________

C. Power the flight control electronics.

Question 8

8) The main battery provides power to the following:
A. Electric braking (as backup source).
B. Captain’s flight instrument bus until RAT deployment
C. L VHF communications.
D. All of the above.

Answer 8

8) The main battery provides power to the following:
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

9) When the FWD or AFT external power switches are illuminated “AVAIL” they indicate:
A. An unpowered external power plug has been plugged in.
B. External power is plugged in and power quality is within limits.
C. DC bus synchronization has failed and external power is required.
D. The system is available for external power to be plugged in.

Answer 9

9) When the FWD or AFT external power switches are illuminated “AVAIL” they indicate:

B. External power is plugged in and power quality is within limits.

Question 10

10) Which of the following is true with regard to loss of three Starter Generators (SG’s) in flight?
A. The APU autostarts.
B. RAT will deploy.
C. Only the First Officers Navigation Display will be unpowered.
D. A and B are correct.

Answer 10

10) Which of the following is true with regard to loss of three Starter Generators (SG’s) in flight?
A. The APU autostarts.

Question 11

11) Thermal circuit breakers may be reset via CBIC as long as the crew accomplishes the Unannunciated Circuit Breaker supplementary procedure?
A. True.
B. False.

Answer 11

11) Thermal circuit breakers may be reset via CBIC as long as the crew accomplishes the Unannunciated Circuit Breaker supplementary procedure?

B. False.

Question 12

12) The RAT will deploy automatically in flight if:
A. Three starter generators are lost simultaneously.
B. The L2 bus is lost in conjunction with BAT LOW EICAS message.
C. Any two starter/generators fail.
D. All electrical power to the Captain and FO’s flight instruments is lost.

Answer 12

12) The RAT will deploy automatically in flight if:

D. All electrical power to the Captain and FO’s flight instruments is lost.

Question 13

13) When on the ground prior to engine start and the Hydraulic Electric Demand pumps ON, the pumps do not operate. This function is called:
A. Load Shedding.
B. Non-essential circuit breakers will open as needed.
C. APU autostart.
D. Load Inhibit.

Answer 13

13) When on the ground prior to engine start and the Hydraulic Electric Demand pumps ON, the pumps do not operate. This function is called:

D. Load Inhibit.

Question 14

14) If a total electrical failure occurs in flight, the PMGs provide Standby Power until RAT deployment.
A. True.
B. False.

Answer 14

14) If a total electrical failure occurs in flight, the PMGs provide Standby Power until RAT deployment.

B. False.

Question 15

15) During automatic load shedding which of the following indications may display?
A. LOAD SHED is displayed next the affected equipment symbol on the
appropriate system synoptic.
B. A list of affected aircraft systems displays on the electrical synoptic.
C. “LOAD SHED” EICAS message displays.
D. Both A and B are correct.

Answer 15

15) During automatic load shedding which of the following indications may display?
A. LOAD SHED is displayed next the affected equipment symbol on the
appropriate system synoptic.
B. A list of affected aircraft systems displays on the electrical synoptic.

D. Both A and B are correct.

Question 16

16) Inflight, with only one starter generator available:
A. All CACs shut down.
B. The standby inverter is powered.
C. Power remains available to critical and essential equipment.
D. A and C are correct.

Answer 16

16) Inflight, with only one starter generator available:

C. Power remains available to critical and essential equipment.

Question 17

17) With the aircraft unpowered on the ground, to begin the CCR start-up process:
A. Pushing the BATTERY switch to ON will begin the left and right CCR start-up.
B. First start the APU as both CCR’s require normal AC power.
C. Turn both IRS selectors to ON.
D. Select the BATTERY switch ON.

Answer 17

17) With the aircraft unpowered on the ground, to begin the CCR start-up process:

D. Select the BATTERY switch ON.

Question 18

18) If a generator drive disconnect is initiated, either automatically or by selecting the respective Drive Disconnect Switch, with engines operating:
A. Select the RESET option in the electrical synoptic to reconnect the
starter/generator.
B. The “ELEC GEN DRIVE” EICAS message displays.
C. The starter/generator is disengaged from the engine.
D. B and C are correct.

Answer 18

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

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

Question 19

19) When the APU starter/generators are powering the main AC busses, and both FWD
external power connectors are plugged in:
A. External power is automatically applied.
B. External power only becomes available after APU shutdown.
C. The APU generator powers the R1 and R2 AC busses & FWD external
powers the L1 and L2 busses.
D. External power must be manually selected ON.

Answer 19

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

D. External power must be manually selected ON.

Question 20

20) The electrical system can be powered by the APU and FWD external at the same time.
A. True.
B. False.

Answer 20

20) The electrical system can be powered by the APU and FWD external at the same time.
A. True.

Question 21

21) The 787 provides a “no break” power transfer when changing power sources.
A. True.
B. False.

Answer 21

21) The 787 provides a “no break” power transfer when changing power sources.

B. False.

Question 22

22) The Towing Power switch when ON, provides power for the Captains ACP, Captains Flight Interphone, Nav lights, and Brakes.
A. True.
B. False.

Answer 22

22) The Towing Power switch when ON, provides power for the Captains ACP, Captains Flight Interphone, Nav lights, and Brakes.
A. True.

Question 23

23) With the loss of a single engine generator, how is power provided to the associated main bus for that generator?
A. The lost main AC bus is now powered by the other main AC busses.
B. All 3 powered AC busses share the load equally.
C. AC Standby Inverter powers the bus.
D. The PMG’s will provide backup power to the associated bus.

Answer 23

23) With the loss of a single engine generator, how is power provided to the associated main bus for that generator?
A. The lost main AC bus is now powered by the other main AC busses.

Question 24

24) The Large Motor Power Distribution System (LMPS) powers:
A. CACs.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.

Answer 24

24) The Large Motor Power Distribution System (LMPS) powers:
A. CACs.
B. Hydraulic pumps.
C. Power for APU and Engine starting.
D. All the above.

Question 25

25) The PECS system provides:
A. Heat dissipation for the LMPS.
B. Cooling for the FD displays and indicators.
C. Cooling for the left and right CCR’s.
D. Heat dissipation for the LMPS anytime the battery switch is on.

Answer 25

25) The PECS system provides:

A. Heat dissipation for the LMPS.

Question 26

26) After landing, PECS cooldown begins when both packs AND the hydraulic EMP’s are shutdown. Minimum time required prior to removing electrical power is:
A. 22 minutes when using only one external power source.
B. There is no minimum when the OAT if 15°C or below.
C. 10 minutes when using APU power or both forward external power sources.
D. A and C are correct.

Answer 26

26) After landing, PECS cooldown begins when both packs AND the hydraulic EMP’s are shutdown. Minimum time required prior to removing electrical power is:
A. 22 minutes when using only one external power source.

C. 10 minutes when using APU power or both forward external power sources.
D. A and C are correct.

Question 27

27) The Starter/Generators (SGs):
A. Are variable frequency and utilize a CSD to provide stable output.
B. Are variable frequency and are directly connected to the engine gearbox.
C. Operate in pairs through a motor drive regulator.
D. Are variable frequency, and provide one primary and one backup output to each L and R main bus.

Answer 27

27) The Starter/Generators (SGs):

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

Question 28

28) The RAT:
A. May only be deployed below 310kts/.85 Mach.
B. Provides backup hydraulic pressure to the Center system PRIMARY flight
controls.
C. Provides standby electrical power.
D. B and C are correct.

Answer 28

28) The RAT:

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

Question 29

29) The standby electrical system consists of:
A. The Standby Inverter, the Main Battery, APU Battery, and the PMG’s.
B. The flight control electronics system.
C. The Main battery and the RAT generator.
D. All the above.

Answer 29

29) The standby electrical system consists of:

C. The Main battery and the RAT generator.

Question 30

30) Electrical power for the brake system is provided by:
A. The 28vdc power system. The main battery is the backup source.
B, The main battery for the primary source. The 28 vdc system is the backup.
C. The left PMGs as the primary source. The Captain’s Flight Instrument bus for
backup.
D. Main battery for the primary system and 20 minute rechargeable batteries for
the backup.

Answer 30

30) Electrical power for the brake system is provided by:

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

Question 31

31) The APU generator OFF lights illuminate:
A. When the APU generator is in standby mode.
B. Anytime the APU generator has been manually replaced by external power.
C. The APU generator control breaker is open.
D. The APU generator CSD has been failed.

Answer 31

31) The APU generator OFF lights illuminate:

C. The APU generator control breaker is open.

Question 32

32) 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.
A. True.
B. False.

Answer 32

32) 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.
A. True.

Question 33

33) The aft external power receptacle is located:
A. On the left side of the fuselage immediately below the positive pressure relief valve.
B. On the fuselage, between the main gear doors.
C. On the left side of the fuselage aft of the wing.
D. In a locked compartment in the wing/body fairing on the left side of the
fuselage, aft of the wing.

Answer 33

33) The aft external power receptacle is located:

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