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00
V
KVA
AC BUS 2
V
KVA
GEN
2
GEN
1
AC ESS BUS
AC BUS 4
AC BUS 3
V
KVA
V
KVA
GEN
3
GEN
4
0 0 0
0 0 0
115
400
V
HZ
RAT GEN
RAT GEN GEN 4
GEN 1 GEN 2
APU
GEN
GEN 3
AC ESS BUS
GX_06_020
APU
GEN
GEN
RAT
GEN
4
GEN
1
GEN
3
GEN
2
NOTE: The RAT GEN has priority, only if it has been deployed and RAT GEN ON
-Normally powered by GEN 4, alternately powered by the following, in descending priority:
AC BUS 3 AC BUS 2 AC BUS 3
P
R
I
O
R
I
T
Y
ON
OFF
RAT GEN
For Training Purposes Only
Sept 04
6-21
P I LOT T R A I N I N G GU I D E
ELECTRICAL
EXT AC POWER
AC ELECTRICAL
EXT
AC
115
0
400
V
KVA
HZ
AC ELECTRICAL
GEN
APU
00
V
KVA
00
V
KVA
GEN
2
GEN
1
00
V
KVA
00
V
KVA
GEN
3
GEN
4
EXT
AC
115
23
400
V
KVA
HZ
EXT
AC
115
0
400
V
KVA
HZ
EXT
AC
115
0
400
V
KVA
HZ
• - Comes on to indicate that
external AC power is connected and is the
correct phase, voltage and frequency.
• - Indicates that external power
is being used or can be used by the
airplane power distribution system to
maintain power to the AC buses.
AVAIL Light
ON LIGHT
NOTE:
The ON light will remain illuminated, even
when another source(s) is powering AC
buses, to indicate that the priority system
can call upon EXT AC if needed.
GX_06_021
EXT
AC
115
28
400
V
KVA
HZ
00
V
KVA
00
V
KVA
GEN
2
GEN
1
GEN
APU
00
V
KVA
00
V
KVA
GEN
3
GEN
4
AC BUS 1
AC BUS 2
AC ESS BUS
AC BUS 4
AC BUS 3
AC ESS BUS
AC BUS 4
AC BUS 3
AC BUS 1
AC BUS 2
115
23
400
V
KVA
HZ
00
0
V
KVA
HZ
AVAIL
ON
EXT AC
AVAIL
ON
EXT AC
AVAIL
ON
EXT AC
6-22 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
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 buses 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 bus 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 and annunciate, when it senses a battery fault or charger
fault.
External DC power is supplied to the airplane via 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 buses.
GX_06_022
External DC Power
Receptacle
For Training Purposes Only
Sept 04
6-23
P I LOT T R A I N I N G GU I D E
ELECTRICAL
DC SYSTEM DISTRIBUTION
GX_06_023
AC
BUS
2A
AC
BUS
1A
AC
ESS
BUS
DC BUS 1 DC BUS 2
　
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