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In the event of a complete AC power failure in flight, the ADG will automatically deploy
and supply emergency AC power to the ADG bus and to the AC essential bus. If the
automatic deploy function fails, the ADG can be deployed manually by pulling the ADG
manual release handle on the ADG CONTROL control panel at the rear of the center
console.
Vol. 1 07--20--11
ELECTRICAL
AC Electrical System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
The ADG is heated in flight by an internal heater. The heater protects against frost or
ice formation which could prevent the ADG from deploying in an emergency. The
heater is continuously powered in flight from AC Bus 1 when the nose gear is up and
locked. On landing, when the nose gear is extended, power is removed from the
heater.
The ADG bus will supply power to the 3B hydraulic pump, flaps and slats and pitch trim
channel 2. If either main generator is restored, the crew can override the ADG by
pressing the PWR TXFR OVERRIDE button on the ADG control panel. This will
reconnect the restored IDG to power AC bus 1 and 2. The ADG will continue to power
the critical flight controls and the ADG bus. The flaps and slats will move at half speed
when powered from the ADG bus.
The ADG generator, voltage, frequency and ADG bus indications on the EICAS, AC
ELECTRICAL synoptic page are only displayed when the ADG bus is powered.
The ADG will continue to operate and supply power to the ADG bus until the airspeed
decreases below 135 kts. At that point, if the APU generator or IDG has not been
restore, the only power available will be from the batteries.
The ADG cannot be restowed in flight. It is restowed manually, on the ground, by
maintenance personnel.
Air Driven Generator (ADG)
Figure 07---20---6
ADG Manual Deploy Handle
and Auto--Deploy Panel
Center Pedestal
TEST Light (green)
Comes on after successful
completion of auto--deploy
system test.
UNIT
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.
UNIT
TEST
PWR TXFR
OVERRIDE
ADG
CONTROL
ADG
Vol. 1 07--20--12
ELECTRICAL
AC Electrical System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
F. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Generators
IDG 1 DISC P10
IDG 2 DISC P11
G t
GCU 1 BATTERY BUS Q9
Generator
Control
GCU 2 1 Q10
GCU 3 Q11
AC Bus 1 PWR SENS
AC BUS 1
C14
ADG ADG HEATER
C13
AC Bus 2 PWR SENS AC BUS 2 2 C14
AC Essential AC ESS FEED AC
1
S2
Bus PWR SENS
ESSENTIAL S11
AC El t i l AC Service
PWR SENS D10
Electrical
Power
Bus AC SERVICE
FEED
AC SERVICE 2
E2
AC P
ACPC CONT 1 DC BUS 1 1 D13
Power
Center
ACPC CONT 2 DC BUS 2 L9
ACPC CONT 3 N1
ADG Deploy
ADG DEPLOY
AUTO BATTERY BUS
2 N6
ADG DEPLOY
MAN N7
External AC
EXT AC PWR APU BATT
DIRECT BUS 5 A8
Power EXT AC PWR
1
MAIN
BATTERY
DIRECT BUS
6 A8
Vol. 1 07--30--1
ELECTRICAL
DC Electrical System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. DC ELECTRICAL SYSTEM
Four transformer rectifier units (TRU) and two batteries (Main and APU) provide the aircraft
with DC electrical power.
A. Transformer Rectifier Units (TRU)
AC power from AC bus 1, AC bus 2 and from the AC essential bus is converted by four
transformer rectifier units to 28VDC and supplied to DC bus 1, DC bus 2, DC essential
bus, battery bus, DC service bus and the DC utility bus. 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
AC Bus 2
TRU 2 DC Bus 2 / DC Utility Bus
Essential TRU 2 DC Battery Bus
AC Essential Bus Essential TRU 1 DC Essential Bus
ESS TRU 2 is normally supplied AC power from AC BUS 2. If AC BUS 2 is not
available, ESS TRU 2 will be automatically supplied from the AC ESS BUS, via the ESS
TRU 2 XFR switch.
B. Batteries
There are two nickel--cadmium batteries installed in the aircraft, an APU battery and a
main battery. The APU battery is located in the aft equipment compartment and
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