Electrical System:

Question 1

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

Answer 1

300 amps. AFM Pg. 1-13

Question 2

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

Answer 2

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

Question 3

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

Answer 3

Alternator. PTM Pg. 2-27

Question 4

The voltage readings on the EICAS are taken from the:

Answer 4

Left Essential bus, Right Essential bus and

the Emergency Battery bus. PTM Pg. 2-12

Question 5

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

Answer 5

24 volts. PTM Pg. 2-12

Question 6

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

Answer 6

28 volts. PTM Pg. 2-12

Question 7

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

Answer 7

300 amps. AFM Pg. 1-13

Question 8

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

Answer 8

5 second ground fault check.

PTM Pg. 2-34

Question 9

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

Answer 9

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

PTM Pg. 2-34

Question 10

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

Answer 10

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

Question 11

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

Answer 11

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

Question 12

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

Answer 12

Bus. PTM Pg. 2-36

Question 13

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

Answer 13

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

Question 14

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.

Answer 14

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

Question 15

When connecting a GPU, the bus tie should .

Answer 15

Close. PTM Pg. 2-10

Question 16

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

Answer 16

APU generator. PTM Pg. 2-9

Question 17

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

Answer 17

Bus tie. PTM Pg. 2-30

Question 18

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

Answer 18

Reset. QRH Pg. iv

Question 19

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

Answer 19

Emergency Battery bus.

PTM Pg. 2-22

Question 20

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

Answer 20

Left and Right. PTM Pg. 2-30

Question 21

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.

Answer 21

Engine start. PTM Pg. 2-30

Question 22

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

Answer 22

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

Question 23

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.

Answer 23

ON. AFM Pg. 3-13

Question 24

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

Answer 24

Main. AFM Pg. 2-9

Question 25

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

Answer 25

1,500. PTM Pg. 2-7

Question 26

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

Answer 26

GPU. PTM Pg. 2-8

Question 27

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

Answer 27

APU generator. PTM Pg. 2-8

Question 28

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

Answer 28

APU generator. PTM Pg. 2-23

Question 29

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

Answer 29

0º degrees C. AFM Pg. 2-52

Question 30

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

Answer 30

-23º degrees C. AFM Pg. 2-52

Question 31

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.

Answer 31

Split-bus system. PTM Pg. 2-31

Question 32

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.

Answer 32

Normal operations. PTM Pg. 2-31

Question 33

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.

Answer 33

Right Essential. PTM Pg. 2-31

Question 34

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.

Answer 34

Right Generator. PTM Pg. 2-31

Question 35

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

Answer 35

Green AVAIL. PTM Pg. 2-7

Question 36

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

Answer 36

14 volts minimum. PTM Pg. 2-3

Question 37

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

Answer 37

Radio. AFM Pg. 3-12

Question 38

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

Answer 38

Instrument approach. AFM Pg. 3-12

Question 39

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

Answer 39

30/50 Minutes. AFM Pg. 3-13

Question 40

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

Answer 40

60 Minutes. AFM Pg. 3-13