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Flight Safety Lear 45/40 Required Knowledge Areas > Electrical System: > Flashcards

Electrical System: Flashcards

1
Q

The maximum continuous amperage of the engine driven generators is: amps.

A

300 amps. AFM Pg. 1-13

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2
Q

The Lear 45 has two main aircraft batteries and an emergency battery:

A

Which are charged when a GPU is connected, APU generator is on line, or one or both engine driven generators are online.
PTM Pg. 2-4

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3
Q

Each engine has an ( ) which provides AC power to heat the same side windshield.

A

Alternator. PTM Pg. 2-27

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4
Q

The voltage readings on the EICAS are taken from the:

A

Left Essential bus, Right Essential bus and

the Emergency Battery bus. PTM Pg. 2-12

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5
Q

When the main aircraft and emergency batteries are providing power to their respective busses, the EICAS voltages will read approximately: ( ) Volts.

A

24 volts. PTM Pg. 2-12

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6
Q

When the Aircraft Generators, APU generator or a GPU is powering the aircraft, the voltage readings on the EICAS will read approximately: ( ) Volts.

A

28 volts. PTM Pg. 2-12

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7
Q

During engine start, the amperage readout for the APU or the starter/generator driving the starter will
exceed: ( ) amps.

A

300 amps. AFM Pg. 1-13

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8
Q

In the event of a single generator failure, the bus tie should close after a: ( ) second ground fault check.

A

5 second ground fault check.

PTM Pg. 2-34

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9
Q

In the event of a single generator failure, the: ( ) & ( ) Non-Essential busses are auto shed.

A

The Left and Right Non-Essential busses are auto shed.

PTM Pg. 2-34

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10
Q

In the event of a dual generator failure: the ( ) & ( ) Main, ( ) & ( ) Main Avionics, and ( ) & ( ) Non-Essential busses are auto shed.

A

Left & Right Main, & Left & Right Main Avionics, & Left & Right Non- Essential Busses are auto shed. PTM Pg. 2-36

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11
Q

In the event of a dual generator failure, the ( ) lights are auto shed.

A

Exterior. PTM Pg. 2-36 and 3-12

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12
Q

During a dual generator failure the ( ) tie remains open.

A

Bus. PTM Pg. 2-36

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13
Q

In the event of a dual generator failure, the ( / ) Heat is auto shed.

A

Wing/Stab. PTM Pg. 2-36 and 10-9

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14
Q

In the event of a dual generator failure, the SOV’s open, but the ( ) probes are auto shed resulting in left and right amber NAC on the EICAS.

A

NAC/P2T2 probes. PTM Pg. 2-36 and 10-4

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15
Q

When connecting a GPU, the bus tie should .

A

Close. PTM Pg. 2-10

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16
Q

When connecting the ( ) generator before the left generator comes on line, the bus tie should
close.

A

APU generator. PTM Pg. 2-9

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17
Q

During an engine start, the ( ) tie should close if not already closed.

A

Bus tie. PTM Pg. 2-30

18
Q

Circuit Breakers, if popped, can be ( ) one time.

A

Reset. QRH Pg. iv

19
Q

Circuit Breakers with a red rings denote equipment powered by the:

A

Emergency Battery bus.

PTM Pg. 2-22

20
Q

During engine start, the ( ) & ( ) essential contactors open to prevent voltage spikes from damaging sensitive avionic components. PTM Pg. 2-30

A

Left and Right. PTM Pg. 2-30

21
Q

During ( ) start, the Left and Right Essential contactors open resulting in the Emergency Battery powering the Left and Right Essential, Left and Right Essential Avionics and Emergency Battery busses.

A

Engine start. PTM Pg. 2-30

22
Q

The voltage reading on the EICAS should read ( ) volts across all busses during engine start show-ing the voltage output of only the emergency battery. PTM Pgs. 2-12 and 2-30

A

24 Volts. PTM Pgs. 2-12 and 2-30

23
Q

In the event of a loss of both generators and both main batteries, the first step is to select each bat-
tery “ ”, one at a time.

A

ON. AFM Pg. 3-13

24
Q

During initial power up, the ( ) aircraft batteries should be selected on simultaneously.

A

Main. AFM Pg. 2-9

25
Q

A GPU used on a Lear 40/45 is limited to amps.

A

1,500. PTM Pg. 2-7

26
Q

When the ( ) is providing power to the aircraft, the left generator, right generator and APU generator cannot come on line.

A

GPU. PTM Pg. 2-8

27
Q

When the ( ) generator is powering the aircraft, the engine driven generators will come on line automatically once the engines are running.

A

APU generator. PTM Pg. 2-8

28
Q

The ( ) generator will share the amperage load with the right generator.

A

APU generator. PTM Pg. 2-23

29
Q

Below º degrees C, a GPU or APU should be used for engine start.

A

0º degrees C. AFM Pg. 2-52

30
Q

The APU has been demonstrated to start at - º degrees C.

A

-23º degrees C. AFM Pg. 2-52

31
Q

The Lear 40/45 electrical system is a ( ) -bus system, with the left generator powering the left side of the aircraft and the right generator powering the right side of the aircraft and the emergency battery bus.

A

Split-bus system. PTM Pg. 2-31

32
Q

During ( ) operations with both engines running, the voltage readout on the EICAS for the Left Essential bus reflects the voltage output of the left generator.

A

Normal operations. PTM Pg. 2-31

33
Q

During normal operations with both engines running, the voltage readout on the EICAS for the ( ) Essential bus reflects the voltage output of the right generator.

A

Right Essential. PTM Pg. 2-31

34
Q

During normal operation with both engines running, the voltage readout on the EICAS for the Emergency Battery Bus reflects the voltage output of the ( ) generator.

A

Right Generator. PTM Pg. 2-31

35
Q

A ( ) AVAIL light on the EXT PWR switch indicator, indicates the GPU is providing good voltage and polarity.

A

Green AVAIL. PTM Pg. 2-7

36
Q

The aircraft batteries require ( ) volts minimum in order for the battery contactors to close on the ground.

A

14 volts minimum. PTM Pg. 2-3

37
Q

Following a dual generator failure with a subsequent loss of both main aircraft batteries, all ( ) communications will be lost.

A

Radio. AFM Pg. 3-12

38
Q

Following a dual generator failure with a subsequent loss of both main aircraft batteries, the aircraft will be unable to fly an ( ) approach.

A

Instrument approach. AFM Pg. 3-12

39
Q

The main aircraft batteries should last ( ) minutes (28 amp hour batteries) or ( ) minutes (38 amphour batteries) after loss of both generators and completion of the appropriate checklist.
AFM Pg. 3-13

A

30/50 Minutes. AFM Pg. 3-13

40
Q

The emergency battery should last ( ) minutes after the loss of both generators and completion of the appropriate checklist.

A

60 Minutes. AFM Pg. 3-13

Flight Safety Lear 45/40 Required Knowledge Areas (22 decks)

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