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CAE Q 2 > Electrics > Flashcards

Electrics Flashcards

1
Q

Which statement about illumination of the GRD POWER AVAILABLE light is
correct?
a) Ground Power has been plugged in and automatically powers both ground services
busses.
b) Ground Power has been plugged in and meets airplane power quality standards.
c) Ground Power has been plugged in, however airplane power quality is not measured.
d) None of the above.

A

b) Ground Power has been plugged in and meets airplane power quality standards.

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2
Q

Illumination of the SOURCE OFF light indicates:
a) The source manually selected to power the Transfer Bus has failed, and the
automatic bus transfer function has closed the BTB’s to power the Transfer Bus from
another source.
b) The source manually selected to power the Generator Bus has failed, and the
automatic bus transfer function has closed the BTB’s to power the Generator Bus
from another source.
c) The associated transfer bus is no longer powered.
d) The associated generator bus is no longer powered.

A

The source manually selected to power the Transfer Bus has failed, and the
automatic bus transfer function has closed the BTB’s to power the Transfer Bus from
another source.

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3
Q

When during cruise, one engine driven generator fails:
a) Only the associated GEN OFF BUS light and SOURCE OFF light illuminate.
b) Only the associated GEN OFF BUS light, SOURCE OFF light and TRANSFER BUS
OFF light illuminate.
c) The GEN OFF BUS light, SOURCE OFF light, and TRANSFER BUS OFF light
illuminate. Also various other lights associated with systems, which were powered by
the transfer bus illuminate.
d) Due to redundancy, there will be no lights illuminating unless an annunciator panel is
pushed (recall).

A

a) Only the associated GEN OFF BUS light and SOURCE OFF light illuminate.

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4
Q

After the loss of all generators the fully charged main battery and auxiliary battery
(dual battery) provide standby power for a minimum of:
a) 30 minutes.
b) 60 minutes.
c) 90 minutes.
d) 120 minutes.

A

b) 60 minutes.

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5
Q

With the STANDBY POWER switch in the AUTO position, the loss of all engine or
APU electrical power results in automatic switching from the normal power source
to the alternate power source for standby power:
a) In flight only.
b) On the ground only.
c) Both in flight and on the ground.
d) On the ground only when the APU is running, in flight always.

A

c) Both in flight and on the ground.

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6
Q

Illumination of the STANDBY PWR OFF light indicates:

a) The AC standby bus is unpowered.
b) The DC standby bus is unpowered.
c) The battery bus is unpowered.
d) All of the above can be true.

A

d) All of the above can be true.

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7
Q

When the IDG experiences a high oil temperature:
a) The IDG automatically disconnects and its DRIVE light illuminates.
b) The IDG will keep working, unless it is disconnected automatically due to low oil
pressure.
c) The IDG automatically disconnects and the associated DRIVE light, SOURCE OFF
light and GEN OFF BUS light illuminate.
d) The IDG HIGH OIL TEMPERATURE light illuminates. The IDG has to be
disconnected manually via Generator Drive Disconnect Switch.

A

The IDG automatically disconnects and the associated DRIVE light, SOURCE OFF
light and GEN OFF BUS light illuminate.

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8
Q

. Illumination of the BAT DISCHARGE light indicates:

a) The battery charger is inoperative.
b) Excessive battery discharge is detected with the battery switch in the ON position.
c) The battery bus is not powered.
d) For maintenance purposes only, to test the capacity of the battery.

A

b) Excessive battery discharge is detected with the battery switch in the ON position.

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9
Q

The TR UNIT light will illuminate in flight:

a) When TR-1 has failed.
b) When TR-2 has failed.
c) When TR-3 has failed
d) When any TR has failed.

A

a) When TR-1 has failed.

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10
Q

Which statement about the ELEC light is correct?

a) Illumination of the ELEC light indicates a fault exists in the AC power system.
b) The ELEC light can illuminate both in flight and on the ground.
c) The ELEC light can illuminate on the ground only.
d) The ELEC light can illuminate in flight only.

A

c) The ELEC light can illuminate on the ground only.

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11
Q

The cross bus tie relay automatically opens at glide slope capture to…
a) Prevent a single bus failure from affecting both navigation receivers and Flight
Control Computers (FCC’s)
b) Provide more power to the AC STANDBY Bus
c) Ensure that the STANDBY DC is powered.
d) Make sure that the captain’s side navigation receiver and FCC is the only one
connected to the battery. This to ensure guidance in case of a total generator failure.

A 
Prevent a single bus failure from affecting both navigation receivers and Flight
Control Computers (FCC’s)
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12
Q

One basic principle of operation for the B737 electrical system is…
a) All generator bus sources can be automatically connected by the Standby Power
System
b) There is no paralleling of the AC power sources
c) There is no paralleling of any power source
d) An AC power source may be used in parallel with a DC power source.

A

b) There is no paralleling of the AC power sources

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13
Q

DC busses powered from the battery following a loss of both generators are :
a) Battery bus, DC Standby bus, Hot battery bus
b) DC standby Bus, Hot Battery Bus & Switched hot battery bus
c) Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus (even
when the battery switch is OFF)
d) Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus.

A

d) Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus.

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14
Q

DC voltage and amperage may be read on the DC voltmeter and ammeter for the
battery and each of the 3 TR’s. The Standby power and Battery bus displays only
DC voltage. Normal indication is: ______ Volts
a) 24 ± 4 V
b) 26 ± 6 V
c) 24 ± 2 V
d) 26 ± 4 V

A

26 ± 4 V

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15
Q

The engine Integrated Drive Generators (IDG’s):
a) Are three phase, 115 volt and 400-cycle direct current.
b) Adjusts varying generator speeds throughout normal range of operation.
c) Allow the generator to maintain a variable speed throughout the normal range of
operating range of the engine.
d) Have an integral electro-mechanical disconnect device that does provide complete
mechanical isolation of the IDG.

A

Have an integral electro-mechanical disconnect device that does provide complete
mechanical isolation of the IDG.

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16
Q

AC transfer busses:

a) Supply power to the 115V AC busses.
b) Cannot be powered by both external power and APU at the same time.
c) Can be paralleling sources of power.
d) Both A and B are correct.

A

d) Both A and B are correct.

17
Q

.Illumination of the amber BAT DISCHARGE light indicates:

a) The battery is being overcharged.
b) Excessive battery discharge is detected with the battery switch ON.
c) Discharging when the DC meter is in BAT position with the battery switch ON.
d) The battery bus is not powered.

A

b) Excessive battery discharge is detected with the battery switch ON.

18
Q

Illumination of the amber generator drive (DRIVE) light indicates low oil pressure
caused by which of the following?
a) IDG failure.
b) IDG disconnected through generator drive DISCONNECT switch.
c) IDG automatic disconnect due to high oil pressure.
d) Both A and B are correct.

A

d) Both A and B are correct.

19
Q

Illumination of the GEN OFF BUS light indicates:

a) The related main bus is not powered.
b) The related transfer bus is not powered. (answer also correct)
c) The IDG is not supplying power to the related transfer bus.
d) The APU is running and not powering a bus

A

c) The IDG is not supplying power to the related transfer bus.

20
Q

.In flight, if the APU generator is supplying both AC transfer busses, positioning the
BUS TRANS switch to OFF will:
a) Cause AC transfer bus 1 to lose power.
b) Cause AC transfer bus 2to lose power.
c) Cause both AC transfer busses to lose power.
d) Not cause either AC transfer bus to lose power.

A

d) Not cause either AC transfer bus to lose power.

21
Q

Both AC transfer busses can be powered simultaneously by:

a) A single IDG on the ground.
b) The APU generator while on the ground or in flight.
c) The APU and external power.
d) Both A and B are correct.

A

d) Both A and B are correct.

22
Q

If a take-off is made with the APU powering both transfer busses.
a) One transfer bus will disconnect automatically after lift off.
b) If the APU is either shut down, or fails, the engine generators are automatically
connected to their related transfer busses.
c) The generators will not automatically come on line if the APU is shut down or fails.
d) Both transfer busses will automatically disconnect after lift off.

A

If the APU is either shut down, or fails, the engine generators are automatically
connected to their related transfer busses.

23
Q 
On the ground, with the BATTERY switch OFF and the STANDBY POWER switch in
AUTO, the battery bus is:
a) Not powered.
b) Powered by TR#3.
c) Powered by the hot battery bus.
d) Powered by the battery.
A

a) Not powered.

24
Q

The ground power switch when momentarily moved to the ON position and ground
power is available:
a) Removes previously connected power from DC transfer busses.
b) Connects ground power to AC main busses if power quality is correct.
c) Disconnects ground power from AC transfer busses.
d) Connects ground power to AC transfer busses if power quality is correct.

A

d) Connects ground power to AC transfer busses if power quality is correct.

25
Q

With the BUS TRANSFER switch in AUTO, the crosstie bus relay automatically
opens under which of the following conditions?
a) At localizer capture
b) At glide slope capture during a flight director or autopilot ILS approach.
c) When TR1 and TR 2 fail.
d) When AC volts meter reaches 26 volts (+/- 4 volts)

A

b) At glide slope capture during a flight director or autopilot ILS approach.

26
Q

When the STANDBY POWER switch is OFF:

a) The STANDBY PWR OFF light will be illuminated.
b) AC standby bus, static inverter and DC standby bus are powered.
c) AC standby bus is powered by battery through static inverter.
d) The static inverter provides 28-volt DC power to transfer bus 1.

A

a) The STANDBY PWR OFF light will be illuminated.

27
Q

The 115 volt AC standby bus is powered by:
a) The 115-volt AC transfer bus 1 under normal conditions.
b) The battery bus through the static inverter under normal conditions.
c) The battery through the static inverter when both engine driven generators and the
APU fail.
d) Both A and C are correct.

A

d) Both A and C are correct.

CAE Q 2 (15 decks)

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