Electrical System Flashcards
Max continuous amperage of the engine driven generators
300 amps. AFM 1-13
The 2 main batteries and emergency batteries can be charged by
One or both engine driven generators, APU generator, or GPU. PTM 2-4
Each engine has a(n) ( ) which provides AC power to the same side windshield.
Alternator. PTM 2-27
The voltage readings on the EICAS are taken from the (3)
Left Essential bus, Right Essential bus, and Emergency Battery bus.
“E3”
PTM 2-12
When the main and emergency batteries are powering their respective buses, the EICAS voltage will read
Approximately 24 volts. PTM 2-12
When the aircraft generators, APU generator, or GPU are powering the aircraft, the EICAS voltage should read
Approximately 28 volts. PTM 2-12
The amperage readout for the APU or starter/generator will exceed 300 amps during
Engine start. AFM 1-13
In the event of a single generator failure, the bus tie should close after
A 5 second ground fault check. PTM 2-34
Following a single generator failure, the ( ) and ( ) are auto shed.
Left and Right Non-Essential buses. PTM 2-34
Which buses are auto shed following a dual generator failure? (6)
Left and Right Main buses
Left and Right Avionics buses
Left and Right Non Essential buses
“MAN!”
PTM 2-36
True or false
The exterior lights are auto shed following a dual generator failure?
True
PTM 2-36 and 3-12
Following a dual generator failure, the bus tie ( )
Remains open. PTM 2-36
Following a dual generator failure, which anti icing equipment is auto shed?
Wing/Stab heat, L & R main probes, and P2T2 probes. PTM 2-36, 10-4, & 10-9
Following a dual generator failure, the Left and Right amber NAC CAS msgs will illuminate. Why?
Because the NAC SOV’s fail open but the P2T2 probes are auto shed. PTM 2-36 and 10-4.
Name all the items auto shed after a dual generator failure.
- Left and Right Main buses
- Left and Right Avionics buses
- Left and Right Non-Essential buses
- Exterior lights
- Wing/Stab heat
- P2T2 probes
- L & R main probes
“OH MAN” Outside lights, Heat, Main buses, Avionics buses, Non-essential buses
After connecting a GPU, the bus tie should
Close. PTM 2-10
When the APU is connected, the bus tie should
Close. PTM 2-9
During engine start, the bus tie should
Close. PTM 2-30
If circuit breakers pop, they can be ( ).
Reset once. QRH Page iv
The red rings on circuit breakers indicate
That item is on the Emergency Battery bus. PTM 2-22
During engine start, the ( ) and ( ) open to prevent voltage spikes from damaging the avionics.
Left and Right Essential contactors PTM 2-30
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.
Emergency Battery. PTM 2-30
The voltage reading on the EICAS should be ( ) across all busses during engine start showing the output of the emergency battery.
24 volts. PTM 2-12 and 2-30
The first step following the loss of both generators and both batteries is
Select batteries ON one at a time. AFM 3-13
During normal initial power up, both main batteries should be selected on ( ).
Simultaneously. AFM 2-9
Max amperage output of the GPU
1500 amps. PTM 2-7
True or False
When the GPU is providing power to the aircraft, left generator, right generator, and APU can come online.
False. PTM 2-8
When the APU is powering the aircraft, the engine driven generators will come online automatically once ( ).
The engines are running. PTM 2-8
The APU will share the amperage load with (. ).
The right generator. PTM 2-23
A GPU or APU should be used for engine start below ( ).
0 Celsius. AFM 2-52
The APU has been demonstrated to start at ( ).
-23 Celsius. AFM 2-52
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 ( ).
Split-bus system
Emergency battery bus
PTM 2-31
During normal operations with both engines running, the voltage readout on the EICAS for the generators is read from the ( ).
Respective Essential bus. PTM 2-31
During normal operations with both engines running, the voltage readout on the EICAS for the Emergency Battery Bus reflects the voltage readout of the ( ).
Right generator. PTM 2-31
A green AVAIL light on the EXT PWR switch indicator, indicates that the GPU ( ).
Is connected and providing good voltage and polarity. PTM 2-7
The aircraft batteries require ( ) in order to close the contactors on the ground.
14 volts minimum. PTM 2-3
Will you have any radio communication capabilities following a dual generator failure and loss of both main batteries?
No. AFM 3-12
Will you be able to fly an instrument approach after a dual generator failure and loss of both main batteries?
No. AFM 3-12
After a dual generator failure, how long will the main batteries last?
30 minutes (28 amp hour batteries) 50 minutes (38 amp hour batteries) this is what we have
AFM 3-13
The emergency battery should last ( ) after the loss of both generators and following the appropriate checklist.
1 hour. AFM 3-13
What indications will you have if the emergency battery is discharging?
- Emer battery S/I will say EMER
2. White message on CWP (only white one)
Following a single generator failure, can you select the non-essential buses back on?
Yes
Following a dual generator failure, can you select any of the autoshed buses back on?
Yes, you can select the L and R main buses back on, but NOT the non-essential buses.
