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B737-700 NG Systems > Electrical > Flashcards

Electrical Flashcards

1
Q

What are the three main divisions of the electrical system?

A

AC Power, DC Power, Standby Power

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2
Q

The aircraft battery supplies _____ power

A

DC

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3
Q

What sources supply AC power to the aircraft?

A

Engine generators, APU generator, & External Power all produce AC power

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4
Q

T/F: There is no paralleling of AC sources of power

A

True

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5
Q

T/F: The source of power being connected to a transfer bus automatically disconnects an existing AC source

A

True

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6
Q

External ground power provides __________ to both AC Transfer Busses.

A

115 volt AC electrical power

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7
Q

The blue APU GEN OFF BUS light on the Forward Overhead Panel indicates what?

A

The APU is running but the APU generator is not powering a bus.

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8
Q

T/F: The APU provides complete aircraft power by powering both AC Transfer Busses simultaneously.

A

True

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9
Q

What is the IDG?

A

Integrated Drive Generator. This is the engine-driven generator that provides electrical power (AC)

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10
Q

T/F: Reactivation of an IDG may be accomplished in flight.

A

False. This can only be done on the ground my maintenance personnel

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11
Q

The DRIVE light on the overhead panel illuminates for what conditions?

A

IDG Failure, Engine Shutdown, IDG automatic disconnect (usually if oil temp exceeds limits), IDG disconnected via the disconnect switch

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12
Q

Each engine-driven generator produces the required _____ volt and _____ hertz power required by the aircraft

A

115 volt; 400 hertz

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13
Q

When does the blue GEN BUS OFF light illuminate?

A

Anytime respective IDG is not providing power to the related transfer bus

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14
Q

T/F: The Bus Tie Breakers (BTBs) are controlled by the BUS TRANS switch located on the overhead panel

A

True. When this switch is in AUTO and the source powering the Transfer Bus is disconnected or fails, the source powering the opposite Transfer Bus automatically picks up the unpowered bus.

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15
Q

The Ground Service Buses provide power to what?

A

Aircraft cabin and to the battery charger

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16
Q

The Galley Power Switch supplies electrical power to ______ and the ________ when AC transfer busses are powered.

A

galleys; broadband satellite system

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17
Q

Which buses are typically shed if an electrical overload occurs?

A

Galley Bus(s) and the Main Bus(s) (same side first, then opposite side if required)

18
Q

What do the Transformer Rectifiers do?

A

Convert AC power to DC power

19
Q

Transformer Rectifier #3 (TR 3) can be powered from what sources?

A

AC Transfer Bus 2 (normal) & AC Transfer Bus 1 (during a power loss)

20
Q

TR 3 primarily supplies DC power to what ?

A

Battery Bus. It also serves as a backup power source to TR 1 & 2

21
Q

The TR UNIT light on the forward overhead panel indicates what

A

In Flight: TR1 has failed, or TR2 & TR3 have failed (at the same time)
On Ground: Any TR fault has occurred

22
Q

The Cross Bus Tie Relay connects what?

A

DC Bus 1, DC Bus 2, and DC Standby Bus (In flight, this relay is normally closed and the buses are connected)

23
Q

What is the AC Standby Bus’s normal source of electrical power?

A

AC Transfer Bus 1 (The bus can also be powered by the main battery via through the static inverter)

24
Q

During normal operations, the DC Standby Bus receives power from what sources?

A

TR1, TR2, and TR3. (The bus can also be powered directly by the battery)

25
Q

T/F: The auxiliary battery operates in parallel with the main battery at all times?

A

False. It only operates in parallel during use of standby power. It is normally isolated from the electrical system.

26
Q

What kind of battery does the aircraft have ?

A

A 24 volt DC nickel-cadmium battery

27
Q

The normal battery voltage range is ?

A

22 - 30 volts

28
Q

What three battery buses are connected to the battery?

A

1.Battery Bus (powered when BAT switch is selected ON)
2.Hot Battery Bus (always connected)
3. Switched Hot Battery Bus (powered when BAT switch is selected ON)

29
Q

What provides power for the Main Battery Charger?

A

AC Ground Service Bus 2

30
Q

T/F: A fully charged battery has sufficient capacity to provide standby power for a minimum of 30 minutes.

A

True

31
Q

What Buses comprise the standby power system?

A

AC Standby Bus, DC Standby Bus, Hot Battery Bus, Switched Hot Battery Bus, and Battery Bus

32
Q

T/F: The DRIVE light will illuminate when IDG oil pressure is low or an under frequency condition exists?

A

True

33
Q

When will the DC cross bus tie relay open automatically?

A

Glide slope capture during a Flight Director or Autopilot approach, or when the BUS TRANS switch is switched to OFF

34
Q

The AC Standby Bus is powered by ________________

A

AC Transfer Bus 1

35
Q

T/F: If the aircraft takes off with the APU providing power to the AC Transfer Busses and the APU fails or is shutdown, the BTB’s automatically transfer the electrical load to the engine generators.

A

True (only on initial takeoff)

36
Q

If there is a failure of AC Transfer Bus 1 or the source of power to DC Bus 1, both the AC and DC Standby Busses are powered by _____________________

A

the battery charger

37
Q

The ELEC light illuminates on the __________ and indicates a fault in the ____________ or the standby power system.

A

ground only; DC power system

38
Q

What is the purpose of selecting the BUS TRANSFER switch OFF?

A
  1. To open the cross bus tie relay (DC system)
  2. To inhibit the bus tie breaker auto switching (AC system)
39
Q

If the guarded BUS TRANS switch is switched to OFF, what will happen?

A

Bus Tie Breaker (BTB) automatic switching is now inhibited

40
Q

An illuminated STANDBY PWR OFF light indicates a power loss to which bus?

A

One or more of the following: AC standby bus, DC standby bus, or the Battery Bus

41
Q

T/F: The BAT position of the STANDBY POWER switch
overrides the automatic switching of the standby power and manually places the AC Standby Bus, DC Standby Bus, and Battery Bus on battery power.

A

True

B737-700 NG Systems (23 decks)

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