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For other load devices requiring DC power, 115–volt AC power is converted to 28–volt DC power by
four 150 Amp transformerrectifier
units (TRU). 28–volt DC power is distributed through the DC
power center (DCPC) and the secondary power distribution assemblies (SPDA) on the following
busses:
· DC bus 1 and 2
· DC essential bus
· Battery bus
· DC Emergency bus
The 25–ampere hour, 24–volt DC avionics battery provides power to the following:
· Stored energy to selected electronic equipment during normal ground operations.
· During flight in an emergency (loss of all generators) to the flight essential DC loads.
The 42 ampere hour, 25.2 volt DC APU battery provides power to the following:
· Stored energy for starting the APU during both ground and flight operations.
· During flight in an emergency (loss of all generators) to the flight essential DC loads.
The following busses are connected directly to the battery terminals:
· Avionics battery direct bus
· APU battery direct bus
Battery chargers and battery heaters, powered by the main AC buses, maintain the main and APU
batteries in a charged and warm condition.
An Electrical Control Panel, located in the cockpit, provides control of all generators, external AC and
DC power and battery master.
An Electrical Management System (EMS), located in the cockpit, controls and displays the status of
circuit breaker, on the two control display units (CDU).
External AC power, supplied through the AC receptacle, situated at the aft left side of the airplane
(on the fairing at the root of the wing trailing edge) provides power to:
· AC bus 1, 2, 3 and 4
· AC essential bus
External DC power, supplied through the DC receptacle, situated at the aft of the airplane (adjacent
the aft service panel), provides power to the APU battery direct bus.
The APU can be started using external DC power.
The airplane batteries cannot be charged through external DC power.
ELECTRICAL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
07−10−1
EPGDS COMPONENTS
3
TRU
AVIONICS BATTERY
AND BATTERY CHARGER
RAT
DCPC
CCBP
ACPC
VFG
APU BATTERY
AND BATTERY CHARGER
APU START
CONTACTOR
ASSEMBLY(ASCA)
SPDA
GCU
1
2
4
EXT AC PANEL
EXT DC PANEL
GF0710_001
APU GENERATOR
ELECTRICAL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
07−10−2
EPGDS ARCHITECTURE
GEN
4
GEN
3
GEN
2
GEN
1
LH Engine
RH Engine
APU
GEN
GCU
GCU
GCU GCU
COCKPIT CIRCUIT BREAKER PANEL (CCBP)
AC POWER CENTER (ACPC)
RAT GEN GCU
ELECTRICAL
CONTROL
PANEL
AC EXT
POWER
EXT PWR
CONTROL
PANEL
TRU 1 TRU 2
ESS
TRU 1
ESS
TRU 2
APU
BATTERY
DC EXT
POWER
APU
START CONTROL
ASSEMBLY(ASCA)
DC POWER CENTER (DCPC)
SPDA 1 SPDA 2 SPDA 3 SPDA 4
EMS
CDU 1
EMS
CDU 2
APU
BATTERY
CHARGER
115/200 V, 3 PHASE, 324−596 Hz
28 V, DC
CONTROL, PROTECTION, COMMUNICATIONS
APU
START
MOTOR
GCU
AVIONICS
BATTERY
AVIONICS
BATTERY
CHARGER
GF0710_002
ELECTRICAL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
07−10−3
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
stage is a permanent magnet generator (PMG), generator excitation function, which provides output
power. The second stage 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 deenergize
the generator, in
the event of malfunction. The third stage, 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 busses. VFG output is then routed through the
CCBP to bus feeders 1, 2 and 3 and the AC ESS BUS for power distribution to the 4 transformer
　
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