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Jason Boeing 787 Dreamliner > Electrical > Flashcards

Electrical Flashcards

1
Q

If the permanent magnet generators are not available, the flight control electronics receive power from the:
• FO’s flight instrument bus.
• 28v DC system and main battery.
• Captain’s flight instrument bus.
• directly from the EEC electronics units.

A

• 28v DC system and main battery.

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2
Q

What is the minimum number of external power sources required for an external power ONLY engine start?
• Two (Either forward and the aft external)
• Three
• Engine start is not available on external power only
• Two (L&R Fwd)

A

• Two (L&R Fwd)

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3
Q

The ground handling mode is powered when ___ if no other power source is available.
• both forward external power sources are in use (ON)
• either FWD external power is connected (AVAIL)
• only AFT external power is connected (AVAIL)
• the battery switch is ON

A

• either FWD external power is connected (AVAIL)

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4
Q

The generator drive may disconnect automatically ____
• only on the ground
• due to excessive frequency variations
• due to bearing failure
• depending on the fault condition detected

A

• depending on the fault condition detected

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5
Q

How can the flight crew determine circuit breaker status?
• Check the CBIC display.
• Check the Status page display.
• Check the Electrical synoptic.
• Open CBs automatically display on EICAS.

A

• Check the CBIC display.

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6
Q

What is the purpose of the permanent magnet generators (PMGs)?
A. Powers the Captain’s standby electrical system.
B. Powers the hot battery buss and main battery charger.
C. Powers the flight control electronics.
D. All the above.

A

C. Powers the flight control electronics.

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7
Q

The main battery provides power to the following:
A. electric braking (as backup source).
B. The Captain’s Flight instrument bus until RAT deployment
C. Towing and refueling operations
D. All the above

A

D. All the above

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8
Q

The illuminated “AVAIL” light on the FWD or AFT external power switches indicate:
• External power is plugged in and voltage and frequency are within limits.
• External power is plugged in and is being used.
• AC busses have lost all power and are looking for an external power source.
• The system is available for external power to be plugged in.

A

• External power is plugged in and voltage and frequency are within limits.

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9
Q

Which of the following is true with regard to loss of two Starter Generators (SGs) in flight?
A. APU will Auto Start.
B. RAT will deploy.
C. First Officer’s flight instruments will be unpowered.
D. Some load shedding will occur.

A

D. Some load shedding will occur.

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10
Q

Electronic Circuit Breakers can be opened or closed using CBIC on the ground or in flight.
A. True
B. False

A

A. True

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11
Q

Which circuit breaker types may be reset via CBIC?

A. Thermal
B. Electronic
C. Both A and B are correct
D. Circuit breakers cannot be reset via CBIC

A

B. Electronic

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12
Q

Which of the following conditions will cause the RAT to deploy automatically in flight?
• Loss of the R 1 bus.
• Loss of the L2 bus with BAT LOW EICAS message.
• Loss of two starter generators
• Loss of all electrical power to the Capt’s and FO’s flight instruments

A

• Loss of all electrical power to the Capt’s and FO’s flight instruments

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13
Q

To remain within the capacity of the available power sources, __ will occur.
• Load Inhibit
• Non-essential circuit breakers will open as needed
• APU autostart
• Load Shedding

A

• Load Shedding

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14
Q

If a loss of all electrical power to Capt’s and FO’s flight instruments occurs in flight, the ____ provides Standby Power until RAT deployment.
• Main battery
• APU battery
• PMGs
• Dedicated standby power bus batteries

A

• Main battery

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15
Q

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

A

D. Both A and C are correct.

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16
Q

lnflight, with only one starter generator available ?
• engine anti-ice is no longer available
• power remains available to critical and essential equipment.
• the standby inverter is powered.
• all CACs go to high flow to maintain pressurization

A

• power remains available to critical and essential equipment.

17
Q

With the airplane unpowered on the ground, pushing the battery switch to ON:
• begins the left and right CCR start-up process
• Powers the left inboard and outboard displays.
• Powers the left TCP.
• begins the left CCR start-up process.

A

• begins the left CCR start-up process.

18
Q

If a drive disconnect switch is pushed, with engines operating:
A. The starter/generator is disengaged from the engine.
B. The “ELEC GEN DRIVE” EICAS message displays.
C. Maintenance action will be required to reconnect the starter/generator.
D. All of the above.

A

D. All of the above.

19
Q

If both FWD external power are powering the main AC busses, when the APU starter/generators become available:
• The APU generator power is automatically applied when all external power is removed.
• APU generator power replaces FWD external power.
• The APU generator powers the R1 and R2 AC busses & FWD external powers the L1 and L2 busses.
• APU generator power must be manually selected ON

A

• APU generator power replaces FWD external power.

20
Q

The APU and FWD external can power the aircraft at the same time.
A True
B. False

A

A True

21
Q

The bus power control units provide electrical load management when the aircraft is operating on:
• engine starter generators only.
• aft external power only.
• fwd external power only
• any available electrical power source.

A

• any available electrical power source.

22
Q

Power source transfers are made without interruption when the aircraft is on the ground.
A True
B. False

A

B. False

23
Q

How can crew members differentiate between an open Electronic circuit breaker (ECB) and an open Thermal circuit breaker (TCB)?
• Open TCBs are shown using a crosshatched display while ECBs are solid white.
• Open TCBs are displayed in red, while ECBs are displayed in amber
• TCBs display a capitol “T” immediately to the right of the symbology.
• Open TCBs are shown using a solid white display while ECBs are crosshatched.

A

• Open TCBs are shown using a crosshatched display while ECBs are solid white.

24
Q

lnflight, when will the APU auto start?
• With an in-flight engine failure.
• With a loss of three or more starter/generators.
• Anytime the RAT is deployed.
• When power is lost to two main AC Busses.

A

• With a loss of three or more starter/generators.

25
Q

The Towing Power panel provides power for ____
A. Capt’s audio control panel, Capt’s flight interphone,
B. Brakes, Navigation lights
C. Radio communications
D. Both A and B are correct

A

D. Both A and B are correct

26
Q

If any engine generator fails, how is power provided to its associated main AC bus?
• The lost main AC bus is now powered by another main AC bus.
• The RAT deploys & powers the AC bus.
• The main battery will energize the AC inverter to power the bus.
• The PMGs will provide backup power to the associated bus.

A

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

27
Q

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

A

D. All the above

28
Q

During an autoland approach with LAND 3 annunciated below 200ft, the R1 SG fails. The following occurs:
• The ASA display changes to LAND 2.
• The ASA display changes to NO AUTOLAND.
• The ASA continues to display LAND 3.
• The ECIAS displays NO AUTOLAND.

A

• The ASA continues to display LAND 3.

29
Q

The PECS system provides __
• heat dissipation for the LMPS
• cooling for the FWD and AFT passenger entertainment systems
• cooling for the left and right CCRs.
• additional cooling to the FD crew rest area

A

• heat dissipation for the LMPS

30
Q

After landing, PECS cooldown begins when __?

• packs are shutdown
• hydraulic EMPs are shutdown
• IRSs are selected OFF
• packs AND hydraulic EMPs are shutdown

A

• packs AND hydraulic EMPs are shutdown

31
Q

The Starter/Generators (SGs) ____
• are variable frequency and utilize a CSD to provide stable output
• are variable frequency and are directly connected to the engine gearbox
• ganged in pairs through a hydro/electric motor drive
• are variable frequency, and utilize the engine variable stator vanes to control output

A

• are variable frequency and are directly connected to the engine gearbox

32
Q

The RAT provides:
A. standby electrical power
B. backup hydraulic pressure
C. Alternate pneumatic pressure
D. A and B are correct

A

D. A and B are correct

33
Q

The standby electrical system consists of:
A. The Standby Inverter.
B. The flight control electronics system.
C. The Main battery and the RAT generator.
D. All the above.

A

C. The Main battery and the RAT generator.

34
Q

Primary and backup power for the brake system is provided by:
• 28 vDC power for the primary system and the main battery for the backup source
• The R1 AC bus for the primary source and the Capt’s Flight instrument bus as the backup source
• The FO’s Flight instrument bus as the primary source and the APU battery as the backup source.
• Main battery for the primary system and 20 minute rechargeable batteries for the backup

A

• 28 vDC power for the primary system and the main battery for the backup source

35
Q

The main battery can supply DC power for:
A. engine and APU fire detection.
B. the Left CCR .
C. Capt’s inboard and lower DU.
D. All the above.

A

D. All the above.

36
Q

The APU generator OFF lights illuminate when:
• The APU generator is in standby mode.
• The APU generator power has been replaced by external power.
• The APU generator control breaker is open.
• The APU generator power has been replaced by engine starter generator power.

A

• The APU generator control breaker is open.

37
Q

The benefit of using all three external power sources for engine start, is that aft external can assist the forward external if starting the right engine first.
A. True
B. False

A

A. True

38
Q

The aft external power receptacle is located:
A. on the right side of the fuselage below the aft cargo door.
B. on the fuselage, between the main gear doors.
C. on the left side of the fuselage aft of the outflow valve.
D. on the left side of the fuselage aft of the wing.

A

D. on the left side of the fuselage aft of the wing.

Jason Boeing 787 Dreamliner (19 decks)

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