Elec

Question 1

The bus power control units provide electrical load management when the aircraft is operating on:

Answer 1

any available electrical power source.

Question 2

If the permanent magnet generators are not available, the flight control electronics receive power from the:

Answer 2

28v DC system and main battery.

Question 3

What is the minimum number of external power sources required for an external power ONLY engine start?

Answer 3

Two (L&R Fwd)

Question 4

The ground handling mode is powered when _____ if no other power source is available.

Answer 4

either FWD external power is connected (AVAIL)

Question 5

The generator drive may disconnect automatically _____.

Answer 5

depending on the fault condition detected

Question 6

How can the flight crew determine circuit breaker status?

Answer 6

Check the CBIC display.

Question 7

What is the purpose of the permanent magnet generators (PMGs)?

Answer 7

C. Powers the flight control electronics.

Question 8

The main battery power to the following:

Answer 8

A. electric breaking (as backup source).
B. The Captains Flight instrument bus until RAT deployment
C. Towing and refueling operations

Question 9

The illuminated “AVAIL” light on the FWD of AFT external power switches indicate:

Answer 9

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

Question 10

Which of the following is true with regard to loss of two Starter Generators (SG’s) in flight?

Answer 10

D. Some load shedding will occur.

Question 11

Electronic Circuit Breakers can be operned or closed using CBIC on the ground or in flight.

Answer 11

A. True

Question 12

Which circuit breaker types may be reset via CBIC?

Answer 12

B. Electronic

Question 13

Which of the following conditions will cause the RAT to deploy automatically in flight?

Answer 13

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

Question 14

To remain within the capacity of the available power sources, ____ will occur.

Answer 14

( Mark it was not highlited so here are all the possible answers)
Load Inhibit
Non-essential circuit breakers will open as needed
APU autostart
Load Shedding

Question 15

If a loss of all electrical power to Capt’s and FO’s flight instrument occurs in flight, the _____ provides Stanby Power until RAT deployment.

Answer 15

Main battery

Question 16

Which of the following indications will display during automatic load shedding?

Answer 16

A. LOAD SHED is displayed next the affected equipment symbol on the appropriate system synoptic.
C. a list of affected aircraft systems on the electrical synoptic.

Question 17

Inflight, with only one starter generator available _____?

Answer 17

power remains available to critical and essential equipment.

Question 18

With the airplane unpowered on the ground, pushing the battery switch to ON:

Answer 18

begins the left CCR start-up process

Question 19

If a drive disconnect switch is pushed, with engines operating:

Answer 19

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.

Question 20

If both FWD external power are powering the main AC busses, when the APU starter/generators become available:

Answer 20

APU generator power replaces FWD external power

Question 21

The APU and FWD external can power the aircraft at the same time:

Answer 21

A. True

Question 22

Power source transfers are made without interruption when the aircraft is on the ground:

Answer 22

B. False

Question 23

The Towing Power panel provides power for ___.

Answer 23

A. Capt’s audio control panel, Capt’s flight interphone.

B. Brakes, Navigation lights

Question 24

How can crew members differentiate between an open Electronic circuit breaker (ECB) and an open Thermal circuit breaker (TCB)?

Answer 24

Open TCB’s are shown using a crosshatched diplay while ECB’s are solid white.

Question 25

Inflight, when will the APU auto start?

Answer 25

With a loss of three or more starter/generators.

Question 26

If any engine generator fails, how is power provided to it’s associated main AC bus?

Answer 26

The lost main AC bus is now powered be another main AC bus.

Question 27

The Large Motor Power Distribution System (LMPS) powers _____.

Answer 27

A. CAC’s
B. Hydraulic pumps
C. power for APU and Engine starting

Question 28

During an autoland approach with LAND 3 annunciated below 200ft, the R1 starter/generator fails. Which of the following occurs:

Answer 28

The ASA continues to display LAND 3.

Question 29

The PECS system provides ____.

Answer 29

heat dissipation for the LMPS

Question 30

After landing, PECS cooldown begind when ____?

Answer 30

packs AND hydraulic EMPS’s are shutdown

Question 31

The Starter/Generators (SG’s) ____.

Answer 31

are variable frequency and are directly connected to the engine gearbox

Question 32

The RAT provides:

Answer 32

A. stanby electrical power

B. backup hydraulic pressure

Question 33

The standby electrical system consists of:

Answer 33

C. The Main battery and the RAT generator.

Question 34

Primary and backup power for the brake system is provided by:

Answer 34

28vdc power for the primary system and the main battery for the backup source.

Question 35

The main battery can supply DC power for:

Answer 35

A. engine and APU fire detection
B. the Left CCR.
C. Capt’s inboard and lower DU.

Question 36

The APU generator OFF lights illuminate when:

Answer 36

The APU generator control breaker is open.

Question 37

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.

Answer 37

A. True

Question 38

The aft external power receptable is located:

Answer 38

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