Electrical System: Flashcards
The maximum continuous amperage of the engine driven generators is: amps.
300 amps. AFM Pg. 1-13
The Lear 45 has two main aircraft batteries and an emergency battery:
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
Each engine has an ( ) which provides AC power to heat the same side windshield.
Alternator. PTM Pg. 2-27
The voltage readings on the EICAS are taken from the:
Left Essential bus, Right Essential bus and
the Emergency Battery bus. PTM Pg. 2-12
When the main aircraft and emergency batteries are providing power to their respective busses, the EICAS voltages will read approximately: ( ) Volts.
24 volts. PTM Pg. 2-12
When the Aircraft Generators, APU generator or a GPU is powering the aircraft, the voltage readings on the EICAS will read approximately: ( ) Volts.
28 volts. PTM Pg. 2-12
During engine start, the amperage readout for the APU or the starter/generator driving the starter will
exceed: ( ) amps.
300 amps. AFM Pg. 1-13
In the event of a single generator failure, the bus tie should close after a: ( ) second ground fault check.
5 second ground fault check.
PTM Pg. 2-34
In the event of a single generator failure, the: ( ) & ( ) Non-Essential busses are auto shed.
The Left and Right Non-Essential busses are auto shed.
PTM Pg. 2-34
In the event of a dual generator failure: the ( ) & ( ) Main, ( ) & ( ) Main Avionics, and ( ) & ( ) Non-Essential busses are auto shed.
Left & Right Main, & Left & Right Main Avionics, & Left & Right Non- Essential Busses are auto shed. PTM Pg. 2-36
In the event of a dual generator failure, the ( ) lights are auto shed.
Exterior. PTM Pg. 2-36 and 3-12
During a dual generator failure the ( ) tie remains open.
Bus. PTM Pg. 2-36
In the event of a dual generator failure, the ( / ) Heat is auto shed.
Wing/Stab. PTM Pg. 2-36 and 10-9
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.
NAC/P2T2 probes. PTM Pg. 2-36 and 10-4
When connecting a GPU, the bus tie should .
Close. PTM Pg. 2-10
When connecting the ( ) generator before the left generator comes on line, the bus tie should
close.
APU generator. PTM Pg. 2-9
During an engine start, the ( ) tie should close if not already closed.
Bus tie. PTM Pg. 2-30
Circuit Breakers, if popped, can be ( ) one time.
Reset. QRH Pg. iv
Circuit Breakers with a red rings denote equipment powered by the:
Emergency Battery bus.
PTM Pg. 2-22
During engine start, the ( ) & ( ) essential contactors open to prevent voltage spikes from damaging sensitive avionic components. PTM Pg. 2-30
Left and Right. PTM Pg. 2-30
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.
Engine start. PTM Pg. 2-30
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
24 Volts. PTM Pgs. 2-12 and 2-30
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.
ON. AFM Pg. 3-13
During initial power up, the ( ) aircraft batteries should be selected on simultaneously.
Main. AFM Pg. 2-9
A GPU used on a Lear 40/45 is limited to amps.
1,500. PTM Pg. 2-7
When the ( ) is providing power to the aircraft, the left generator, right generator and APU generator cannot come on line.
GPU. PTM Pg. 2-8
When the ( ) generator is powering the aircraft, the engine driven generators will come on line automatically once the engines are running.
APU generator. PTM Pg. 2-8
The ( ) generator will share the amperage load with the right generator.
APU generator. PTM Pg. 2-23
Below º degrees C, a GPU or APU should be used for engine start.
0º degrees C. AFM Pg. 2-52
The APU has been demonstrated to start at - º degrees C.
-23º degrees C. AFM Pg. 2-52
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.
Split-bus system. PTM Pg. 2-31
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.
Normal operations. PTM Pg. 2-31
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.
Right Essential. PTM Pg. 2-31
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.
Right Generator. PTM Pg. 2-31
A ( ) AVAIL light on the EXT PWR switch indicator, indicates the GPU is providing good voltage and polarity.
Green AVAIL. PTM Pg. 2-7
The aircraft batteries require ( ) volts minimum in order for the battery contactors to close on the ground.
14 volts minimum. PTM Pg. 2-3
Following a dual generator failure with a subsequent loss of both main aircraft batteries, all ( ) communications will be lost.
Radio. AFM Pg. 3-12
Following a dual generator failure with a subsequent loss of both main aircraft batteries, the aircraft will be unable to fly an ( ) approach.
Instrument approach. AFM Pg. 3-12
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
30/50 Minutes. AFM Pg. 3-13
The emergency battery should last ( ) minutes after the loss of both generators and completion of the appropriate checklist.
60 Minutes. AFM Pg. 3-13
