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completion of auto--deploy
system test.
LAMP/UNIT Switch
Used to test auto--deploy system.
Test can only be accomplished with
two generators selected ON and
both main AC busses powered.
ADG Manual Deploy Handle
Used to manually deploy the ADG.
PWR TXFR OVERRIDE
Used to transfer AC
essential bus power source
from the ADG bus back to
the main AC bus.
REV 56, Jan 31/03
Vol. 1 07--20--14
ELECTRICAL
AC Electrical System
Flight Crew Operating Manual MASTER
CSP A--013
F. System Circuit Breakers
SYSTEM SUB--SYST
EM
CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Generators
IDG 1 DISC P9
IDG 2 DISC
DC BATTERY
P10
G t
GCU 1 BUS
1 Q10
Generator
Control
GCU 2
Q11
GCU 3 Q12
AC
ADG AUTO APU BATTERY
5
B10
Electrical
ADG MAN
DIRECT BUS B11
Power
ADG
D l
ADG DEPLOY
AUTO DC BATTERY
2 N6
Deploy ADG DEPLOY
MAN
BUS
2 N7
ADG DEPLOY
SENS AC BUS 1 1 C10
STBY PWR
CONT
MAIN BATTERY
DIRECT BUS 5 A7
AC ESS FEED ADG BUS 3 A8
AC
AC ESS FEED AC BUS 1 1 C2
Essential
ESS PWR CONT APU BATTERY
DIRECT BUS 5 B13
Bus
ESS AC XFR
CONT
DC BATTERY
BUS Q9
AC Utilit
AC UTLY BUS
FEED AC UTILITY 1 1
E2
AC
Utility
Bus 1
PWR SENS
E7
Distribution
AC UTLY BUS
CONT DC BUS 2 J4
AC UTLY BUS
FEED E2
AC Utility
Bus 2
AC UTLY BUS
SENS AC UTILITY 2
2
E7
AC UTLY BUS
CONT DC BUS 1
J4
AC Service
Bus
AC SERV BUS
FEED AC SERV R2
Vol. 1 07--30--1
REV 56, Jan 31/03
ELECTRICAL
DC Electrical System
Flight Crew Operating Manual
CSP A--013
MASTER
1. DC ELECTRICAL SYSTEM
Five transformer rectifier units (TRU’s) and two batteries (Main and APU) provide the aircraft
with DC electrical power. DC power is also available through an external DC receptacle on
the right aft fuselage.
A. Transformer Rectifier Units (TRU)
There are five TRU’s located in the nose avionics compartment. Each TRU converts
115 VAC input power to 28 VDC output power for powering the aircraft DC buses. The
TRU’s are rated at 100 amps. Normal distribution of the TRU outputs is shown in the
following table:
INPUT BUS TRU OUTPUT BUS
AC Bus 1 TRU 1 DC Bus 1 and
DC Utility Bus 1
AC B 2
TRU 2 DC Bus 2 and
DC Utility Bus 2
us Essential TRU 2 DC Essential Bus and
Battery Bus
AC Service Bus Service TRU DC Service Bus
AC Essential Bus Essential TRU 1 DC Essential Bus and
Battery Bus
B. Batteries
The main and APU nickel-cadmium batteries and their battery chargers are located in
the aft equipment compartment. The batteries provide DC power to their respective DC
battery direct buses.
The 17 AMP./HR, 24, volt main battery provides backup power to the attitude heading
reference system (AHRS), proximity sensing electronic unit (PSEU), data concentrator
units (DCU’s), aircraft clocks, and the APU electronic control unit (ECU). The main
battery also provides power to the flight compartment lighting system.
The 17 AMP./HR, 24 volt, main battery provides backup power to the inertial reference
system (IRS), proximity sensing electronic unit (PSEU), data concentrator units
(DCU’s), aircraft clocks, and the APU electronic control unit (ECU). The main battery
also provides power to the flight compartment lighting system. <0025>
The 43 AMP./HR, 24 volt, APU battery provides the cranking power for starting the
APU.
REV 56, Jan 31/03
Vol. 1 07--30--2
ELECTRICAL
DC Electrical System
Flight Crew Operating Manual MASTER
CSP A--013
Battery chargers maintain the batteries at full charge. The main battery charger is
powered from AC Utility bus 1 and the APU battery charger is powered from the AC
Utility bus 2. Battery charging is controlled automatically. Each charger monitors the
battery voltage and temperature to control the battery charge rate. If a battery reaches
the overtemperature set point (as sensed by the charger), the charging will stop to
prevent overheating (thermal runaway).
Effectivity:
S Airplanes 7001 to 7220
NOTE
In flight, both chargers will be shed during single
generator operations. On the ground, both chargers are
shed if external AC power is connected and the flaps are
out of the 0 detent, and the passenger door is closed.
　
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