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AC Synoptic Page Color Coding - Integrated Drive Generators (2 of 2)........................... 7-30
AC Synoptic Page Color Coding - APU Generator (1 of 2)............................................... 7-31
AC Synoptic Page Color Coding - APU Generator (2 of 2)............................................... 7-32
AC Synoptic Page Color Coding - AC Electrical Power Distribution................................. 7-33
AC Synoptic Page Color Coding - External AC Electrical Power...................................... 7-34
ELECTRICAL
7-iv For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
AC Synoptic Page Color Coding - Air-Driven Generator .................................................. 7-35
DC Synoptic Page - TRU Power Distribution System (1 of 2) .......................................... 7-36
DC Synoptic Page - TRU Power Distribution System (2 of 2) .......................................... 7-37
DC Synoptic Page - Battery Power Distribution System (1 of 2) ...................................... 7-38
DC Synoptic Page - Battery Power Distribution System (2 of 2) ...................................... 7-39
DC Synoptic Page - DC Electrical Power Distribution (1 of 2) .......................................... 7-40
DC Synoptic Page - DC Electrical Power Distribution (2 of 2) .......................................... 7-41
ELECTRICAL
For Training Purposes Only
May 03
7-1
P I LOT T R A I N I N G GU I D E
CHAPTER 7: ELECTRICAL Introduction
The Challenger 604 primarily uses 115-volt AC power and also 28-volt DC electrical
power.
Engine-driven integrated drive generators (IDGs) supply the primary source of AC
electrical power. A generator mounted on the Auxiliary Power Unit (APU) provides an
alternate source of AC electrical power. In flight, if a total loss of AC power occurs,
the air-driven generator (ADG) is deployed from the right side of the forward fuselage
to provide an emergency source of AC electrical power. External AC electrical power
is supplied through an electrical power receptacle located on the right side of the
forward fuselage.
Various aircraft systems and components require DC electrical power for operation.
DC electrical power needs are primarily supplied by four Transformer Rectifier Units
(TRU) mounted in the nose compartment. Two nickel-cadmium (NiCad) batteries,
located in the aft equipment bay, store and provide a source of DC electrical power for
normal and emergency operations.
The aircraft is capable of accepting 28-volt DC external electrical power through a DC
power receptacle installed on the rear fuselage below the right engine.
Five circuit breaker panels provide power distribution. Four circuit breaker panels are
located in the flight compartment and the fifth panel is in the aft equipment bay.
Control and operation are accomplished through the ELECTRICAL POWER Panel
located on the left side of the overhead panel. AC and DC electrical system
information is provided on the EICAS.
ELECTRICAL
7-2 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
AC Electrical Power Sources
Figure 7-1
DC Electrical Power Sources
Figure 7-2
Generator 2
P604_07_001
APU
Generator
Generator 1
Air-Driven
Generator (ADG)
External
Power
Transformer
Rectifier Units
Main Battery
Charger
APU Battery
Main Battery
APU Battery
Charger
External
Power
P604_07_004
ELECTRICAL
For Training Purposes Only
May 03
7-3
P I LOT T R A I N I N G GU I D E
Alternating Current (AC) System
Description
Three AC generators provide AC power for the aircraft electrical systems. Two
engine-driven generators power all AC buses during normal operations. An APU
generator provides a source of AC electrical power when the aircraft is on the ground
with the engines off, and during flight if both engine-driven generators become
inoperative.
AC Electrical System
Figure 7-3
GEN
1
GCU
1
GLC1 GLC2
GTC1 GTC2
AC ESS BUS
TX CONTACTOR
UTILITY
BUS CONTACTOR 1
UTILITY
BUS CONTACTOR 2
ADG
GEN
ADG
GCU
ENG.
1
GEN
2
GCU
2
ENG.
2
APU
EMERG AC TX
CONTACTOR
EXT.
AC
APU
GCU
APU
GEN
EXT
PWR
MON
P604_07_002
NOTE: This schematic only displays AC power sources.
Disregard the position of the GLCs and Generator Transfer Contactors (GTCs).
AC UTILITY ADG BUS
BUS 1
AC BUS 1 AC BUS 2
AC UTILITY
　
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