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The six primary sources are monitored, switched, distributed and controlled by the DCPC. The DCPC
reconfigures the busses automatically in the event of a TRU failure.
Four main DC buses provide DC power to the secondary airplane loads. Each TRU normally powers
a bus, through a TRU line contactor (TLC). In the event of a TRU malfunction, the TRU transfer
contactors (TTC), will automatically switch to an alternate TRU, to supply the affected bus. DC
busses 1 and 2 are automatically shed during single TRU operations.
The avionics battery direct bus and DC emergency bus power is distributed to their secondary loads
through circuit breakers.
Two nickel cadmium batteries are installed in the airplane. Both batteries are used together in an
emergency to provide DC power for a minimum of 15 minutes.
Each battery has a separate dedicated battery charger, to maintain that battery in a fully charged
condition. The battery charger provides protection against battery overtemperature, defective or
unbalanced cell, open/short battery temperature sense thermistor, open/short battery voltage sense
lines and charger overtemperature. The charger will shut itself off, if required and annunciate when it
senses a battery fault or charger fault.
External DC power is supplied to the airplane via the DC external power receptacle. The APU start
contactor assembly (ASCA) checks the power being delivered from the power unit before connecting
it to the airplane busses.
EXTERNAL DC POWER
RECEPTACLE
GF0710_032
ELECTRICAL
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
07−10−23
DC SYSTEM DISTRIBUTION
EXT
DC
AC BUS 2A AC BUS 1A AC ESS BUS AC BUS 3A
CCBP
CCBP
A2
CCBP
G6
CCBP
E11
CCBP
E8
CCBP
C2
ESS
TRU 2
ESS
TRU 1 TRU 1 TRU 2
DC BUS 1 DC ESS BUS BATT BUS DC BUS 2
TLC 1 TTC 1 TTC 2 TLC 2
ETC
DCPC
TLC 3 TTC 3 TTC 4 TLC 4
AVIONICS BATT
DIRECT BUS
START
APU BATT
DIRECT BUS
CCBP
C4
CCBP
C6
ASCA
EPC
APUSC
BATTERY APU
AVIONICS
BATTERY
APU
EBBC
ETTC
SSPC 1 SSPC 2 SSPC 3
SSPC 4
SSPC 5
DC EMERGENCY
BUS
GF0710_033
ELECTRICAL
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
07−10−24
ELECTRICAL PANEL
External DC power is controlled manually. Battery master must be selected ON for all phases of
flight.
External DC Switch
Displays status of DC external power:
AVAIL Light − Comes on to indicate
that external DC power is connected
and is operating within limits.
ON Light − Indicates external DC
power is powering the APU battery
direct bus.
BATT MASTER Switch
Used to control battery power.
OFF − Isolates the battery
bus from the batteries.
EMS − Electrical Management
System is in maintenance
mode.
ON − Battery bus is powered
by battery (only if no AC power
on the airplane).
GF0710_034a
ELECTRICAL
ON
BATT MASTER
OFF
EMS
ON ON
AVAIL AVAIL
EXT AC EXT DC
PUSH OFF/RESET
OFF OFF
FAIL FAIL
GEN 3 GEN 4
OFF
FAIL
GEN 2
OFF
FAIL
GEN 1
OFF
FAIL
APU GEN
PUSH
OFF/RESET
OFF
ON
RAT GEN
ELECTRICAL
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
07−10−25
DC SYSTEM EICAS MESSAGES
BATT BUS FAIL
Indicates that battery
bus is not powered
due to a fault.
BATT MASTER OFF
Indicates that the battery
switch is not on.
DC EMER BUS FAIL
Indicates that DC
EMER BUS is not
powered due to a fault.
APU (AV) BATT FAIL
Indicates that APU (AV)
battery has failed, voltage or
temperature is out of range.
DC BUS 1 (2) FAIL
Indicates that
affected DC bus is not
powered due to a fault
or is shed.
DC ESS BUS FAIL
Indicates that
DC ESS BUS is not
powered due to a fault.
ELEC SYS FAIL
(on ground only)
Indicates that a major
fault has been detected
in the electrical system.
GF0710_035a
APU BATT FAIL
AV BATT FAIL
BATT MASTER OFF
BATT BUS FAIL
DC BUS 1 FAIL
DC BUS 2 FAIL
DC ESS BUS FAIL
DC EMER BUS FAIL
ELEC SYS FAIL
CAIMS LEVEL A fault.
Prevents aircraft dispatch
　
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