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BATT charger and the avionics BATT charger are powered by AC bus 2 and 3
respectively.
For Training Purposes Only
Sept 04
6-3
P I LOT T R A I N I N G GU I D E
ELECTRICAL
EPGDS COMPONENTS
GX_06_001
TRUs
Avionics
Battery
APU Battery
and Battery
Charger
APU
Generator
APU Start
Contactor
Assembly
DC Power
Receptacle
DC Power
Center
AC Power
Center
AC Power
Receptacle
Cockpit Circuit
Breaker Panel
Secondary
Power Distribution
Assemblies
Generator
Control
Units
Control
Display
Units
LH Engine
VF Generators
RH Engine
VF Generators
Ram Air
Turbine
Control
Panel External
Service
Battery Panel
Charger
6-4 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
EPGDS ARCHITECTURE
TRU 1 ESS
TRU 1
ESS
TRU 2
TRU 2
APU
START
MOTOR
DC EXT
POWER
AC EXT
POWER
AC POWER CENTER
DC POWER CENTER
ELECTRICAL
CONTROL
PANEL
LH Engine RH Engine
GEN
1
GEN
2
GEN
4
GCU GCU GCU GCU GEN GCU RAT GEN GCU
115/200 V, 3 PHASE, 324-596 Hz
28 V, DC
CONTROL, PROTECTION, COMMUNICATIONS
APU
GX_06_002
EXT PWR
CONTROL
PANEL
SPDA 1 SPDA 2 SPDA 3 SPDA 4
AVIONICS
BATTERY
AVIONICS
BATTERY
CHARGER
APU
BATTERY
CHARGER
GEN
3
COCKPIT CIRCUIT BREAKER PANEL
APU
BATTERY
APU
START CONTROL
ASSEMBLY (ASCA)
EMS
CDU 1
EMS
CDU 2
For Training Purposes Only
Sept 04
6-5
P I LOT T R A I N I N G GU I D E
ELECTRICAL
AC SYSTEM
AC power is normally supplied by four variable frequency generators (VFG), two on
each engine, rated at 115 volt, 40 kVA, 3-phase, 324-596 Hz output.
The generators are brushless, oil cooled and are a three stage machine type generator.
The first machine is a permanent magnet generator (PMG), generator excitation
function, which provides output power. The second machine, is the main exciter which
receives its field excitation through the generator control unit (GCU).The GCU will
remove the generator from its bus and de-energize the generator, in the event of
malfunction. The third machine, is the main alternator, which incorporates current
transformers that are used for feeder fault and overcurrent protection.
All VFG output is routed through the AC power center (ACPC), which protects,
controls and distributes primary AC power to the main airplane buses. VFG output is
then routed through the CCBP to bus feeders 1A, 2A and 3A and the AC ESS BUS for
power distribution to the 4 transformer rectifier units (TRU). Each generator normally
powers its own bus, through a generator line contactor (GLC). In the event of a
generator malfunction, the generator transfer contactors (GTC), will automatically
switch to an alternate generator, to supply the affected bus. AC bus 2 and 3 are
automatically shed during single generator operations and AC bus 1 and 4 are priority.
AC power can also be supplied by the auxiliary power unit (APU) generator. The APU
constant frequency generator, rated at 115 volt, 40 kVA, 3-phase, 400 Hz output.
External AC power, 115 volt, 3-phase, can also be used to supply power to the AC
system.
BATTERY
MASTER
GROUND
SERVICE
EXT AC EXT DC
BATT
ON
ON
AVAIL
IN USE
AVAIL
IN USE
MIC HDPH
LAMP
TEST
APU
SHUT-OFF
GX_06_003
External AC/DC Power Status
Indicators
Displays status of external AC or
DC power.
Ground Service Mode Switch
Enables maintenance personnel to power selected AC
loads in the cabin, when AC external power is available.
Battery Master Status Indicator
Displays status of the battery master
switch (EMS or ON position).
External AC Power
Receptacle
6-6 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
EMERGENCY AC POWER
Emergency AC power is supplied by the ram air turbine (RAT) in flight, rated at
115 volts, 9 kVA, 3-phase. With engines running, the RAT will deploy with a 14-
second time delay following the loss of all AC power, if the slat/flap handle is at the
in/zero position. It will deploy automatically if the slat/flap handle is not at the in/zero
position. With a dual-engine failure, the RAT will deploy automatically, regardless of
　
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