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Lear 45 > Electrical System > Flashcards

Electrical System Flashcards

1
Q

Max continuous amperage of the engine driven generators

A

300 amps. AFM 1-13

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2
Q

The 2 main batteries and emergency batteries can be charged by

A

One or both engine driven generators, APU generator, or GPU. PTM 2-4

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3
Q

Each engine has a(n) ( ) which provides AC power to the same side windshield.

A

Alternator. PTM 2-27

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4
Q

The voltage readings on the EICAS are taken from the (3)

A

Left Essential bus, Right Essential bus, and Emergency Battery bus.

“E3”

PTM 2-12

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5
Q

When the main and emergency batteries are powering their respective buses, the EICAS voltage will read

A

Approximately 24 volts. PTM 2-12

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6
Q

When the aircraft generators, APU generator, or GPU are powering the aircraft, the EICAS voltage should read

A

Approximately 28 volts. PTM 2-12

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7
Q

The amperage readout for the APU or starter/generator will exceed 300 amps during

A

Engine start. AFM 1-13

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8
Q

In the event of a single generator failure, the bus tie should close after

A

A 5 second ground fault check. PTM 2-34

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9
Q

Following a single generator failure, the ( ) and ( ) are auto shed.

A

Left and Right Non-Essential buses. PTM 2-34

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10
Q

Which buses are auto shed following a dual generator failure? (6)

A

Left and Right Main buses
Left and Right Avionics buses
Left and Right Non Essential buses

“MAN!”

PTM 2-36

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11
Q

True or false

The exterior lights are auto shed following a dual generator failure?

A

True

PTM 2-36 and 3-12

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12
Q

Following a dual generator failure, the bus tie ( )

A

Remains open. PTM 2-36

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13
Q

Following a dual generator failure, which anti icing equipment is auto shed?

A

Wing/Stab heat, L & R main probes, and P2T2 probes. PTM 2-36, 10-4, & 10-9

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14
Q

Following a dual generator failure, the Left and Right amber NAC CAS msgs will illuminate. Why?

A

Because the NAC SOV’s fail open but the P2T2 probes are auto shed. PTM 2-36 and 10-4.

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15
Q

Name all the items auto shed after a dual generator failure.

A
  1. Left and Right Main buses
  2. Left and Right Avionics buses
  3. Left and Right Non-Essential buses
  4. Exterior lights
  5. Wing/Stab heat
  6. P2T2 probes
  7. L & R main probes

“OH MAN” Outside lights, Heat, Main buses, Avionics buses, Non-essential buses

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16
Q

After connecting a GPU, the bus tie should

A

Close. PTM 2-10

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17
Q

When the APU is connected, the bus tie should

A

Close. PTM 2-9

18
Q

During engine start, the bus tie should

A

Close. PTM 2-30

19
Q

If circuit breakers pop, they can be ( ).

A

Reset once. QRH Page iv

20
Q

The red rings on circuit breakers indicate

A

That item is on the Emergency Battery bus. PTM 2-22

21
Q

During engine start, the ( ) and ( ) open to prevent voltage spikes from damaging the avionics.

A

Left and Right Essential contactors PTM 2-30

22
Q

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

A

Emergency Battery. PTM 2-30

23
Q

The voltage reading on the EICAS should be ( ) across all busses during engine start showing the output of the emergency battery.

A

24 volts. PTM 2-12 and 2-30

24
Q

The first step following the loss of both generators and both batteries is

A

Select batteries ON one at a time. AFM 3-13

25
Q

During normal initial power up, both main batteries should be selected on ( ).

A

Simultaneously. AFM 2-9

26
Q

Max amperage output of the GPU

A

1500 amps. PTM 2-7

27
Q

True or False

When the GPU is providing power to the aircraft, left generator, right generator, and APU can come online.

A

False. PTM 2-8

28
Q

When the APU is powering the aircraft, the engine driven generators will come online automatically once ( ).

A

The engines are running. PTM 2-8

29
Q

The APU will share the amperage load with (. ).

A

The right generator. PTM 2-23

30
Q

A GPU or APU should be used for engine start below ( ).

A

0 Celsius. AFM 2-52

31
Q

The APU has been demonstrated to start at ( ).

A

-23 Celsius. AFM 2-52

32
Q

The Lear 40/45 electrical system is a ( ) with the left generator powering the left side and the right generator powering the right side and the ( ).

A

Split-bus system

Emergency battery bus

PTM 2-31

33
Q

During normal operations with both engines running, the voltage readout on the EICAS for the generators is read from the ( ).

A

Respective Essential bus. PTM 2-31

34
Q

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

A

Right generator. PTM 2-31

35
Q

A green AVAIL light on the EXT PWR switch indicator, indicates that the GPU ( ).

A

Is connected and providing good voltage and polarity. PTM 2-7

36
Q

The aircraft batteries require ( ) in order to close the contactors on the ground.

A

14 volts minimum. PTM 2-3

37
Q

Will you have any radio communication capabilities following a dual generator failure and loss of both main batteries?

A

No. AFM 3-12

38
Q

Will you be able to fly an instrument approach after a dual generator failure and loss of both main batteries?

A

No. AFM 3-12

39
Q

After a dual generator failure, how long will the main batteries last?

A 
30 minutes (28 amp hour batteries)
50 minutes (38 amp hour batteries) this is what we have

AFM 3-13

40
Q

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

A

1 hour. AFM 3-13

41
Q

What indications will you have if the emergency battery is discharging?

A
  1. Emer battery S/I will say EMER

2. White message on CWP (only white one)

Lear 45 (30 decks)

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