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ELECTRICAL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
07−10−24
AC BUS FEED SYSTEM (CONT'D)
EXT AC Power
external AC power is available and is the
correct phase, voltage and frequency.
ON Light − Indicates that external power
is being used or can be used by the
airplane power distribution system to
maintain power to the AC busses.
NOTE
The ON light will remain illuminated, even
when other source(s) is powering AC
busses, to indicate that the priority system
can call upon EXT AC if needed.
AVAIL Light − Comes on to indicate that
GF0710_031
GEN
1
GEN
3
GEN
4
AC ELECTRICAL
V
KVA
0
0
GEN
2
GEN
V
KVA
HZ
APU
V
KVA
0
0
AC BUS 1
AC BUS 2 AC BUS 3
AC BUS 4
AC ESS BUS
V
KVA
115
400HZ
GEN
1
GEN
3
GEN
4
AC ELECTRICAL
GEN
2
AC ESS BUS
EXT
AC 28
0
0
0
V
KVA
0
0
V
KVA
0
0
EXT
AC
AC BUS 1 AC BUS 4
AC BUS 2 AC BUS 3
V
KVA
0
0
V
KVA
0
0
V
KVA
HZ
115
23
400
V
KVA
0
0
V
KVA
0
0
GEN
APU
V
KVA
115
0
400HZ
EXT
AC
V
KVA
115
0
400HZ
EXT
AC
EXT
AC
V
KVA
115
0
400HZ
V
KVA
115
400HZ
28
ON
AVAIL
EXT AC
ON
EXT AC
ON
EXT AC
ELECTRICAL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
07−10−25
DC SYSTEM
There are six primary DC power sources: four identical transformer rectifier units (TRU), an Avionics
battery and an APU battery. All sources are routed through the DC power center (DCPC).
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 busses provide DC power to the DC 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, APU 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
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
07−10−26
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
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
07−10−27
ELECTRICAL PANEL
External DC power is controlled manually. Battery master must be selected ON for all phases of
　
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