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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.
GF0710_031
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
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 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.
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
ELECTRICAL
DC SYSTEM DISTRIBUTION
CCBP
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
ELECTRICAL
ELECTRICAL PANEL
External DC power is controlled manually. Battery master must be selected ON for all phases of
flight.
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).
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.
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