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ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/2005
07-01-04 CSP 100-6 REV 2
ELECTRICAL SYSTEM (Cont)
EXTERNAL POWER (Cont)
Neither the engine-driven nor the APU-driven generators come online with the GPU selected ON. If they are on when the
GPU is selected, they drop offline. Engine-driven generators automatically come online after engine start, but not if the
GPU is selected ON. The aircraft main batteries do not have to be on to close the GPU antiflash contactor.
GPU output voltage is indicated on the SUMMARY page and on the ELECTRICAL system synoptic display. No indication
of amps drawn from the GPU is provided.
With the external power cable connected, the following indications are annunciated on the ELECTRICAL synoptic display.
EXT PWR symbol and line are white when AVAIL, green when selected on, and removed when disconnected. These appear
whenever a GPU cable is connected to the airplane, and a voltage of greater than 5 vdc is sensed by the power monitor.
Electrical panel shown with the optional Hydraulic Motor Driven Generator (HMDG) system.
L BATT EXT PWR R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF OFF
OFF
ON
BUS TIE
L GEN APU GEN R GEN
R ESS
R MAIN R AUX
L ESS
L AUX L MAIN
STBY
INST
OFF
L BATT EXT PWR R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF OFF
OFF
ON
BUS TIE
L GEN APU GEN R GEN
R ESS
R MAIN R AUX
L ESS
L AUX L MAIN
STBY
INST
OFF
ON
HYD GEN
EV 2
ELECTRICAL
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6 07-01-05
ELECTRICAL SYSTEM (Cont)
BATTERIES
The batteries are located in the fuselage fairing aft of the left wing. During APU start, the right battery is isolated from the
rest of the aircraft and provides power to the APU starter. The bus tie closes and the left battery provides power to the rest
of the aircraft for emergency operation during total generator failure. They also provide power to the battery buses even
when the batteries are selected off.
The standard batteries are 24 volt nickel-cadmium (NICAD) rated at 44-amp hr.
Gases produced by the main batteries are vented overboard through two tubes that extend from the battery cases.
The batteries are connected to the essential buses when the contactors are closed. When a generator is online, it is connected
to the main buses and charges the battery.
When the batteries are connected on their corresponding buses in parallel with the generators, they are charged by the generators.
Individual battery voltages and temperatures can be read on the ELECTRICAL and SUMMARY synoptic displays on the
MFD.
During a total generator failure, the aircraft batteries provide power for necessary essential equipment for a
limited duration.
Standby Instrument power is supplied by a dedicated 24 vdc battery. The standby instrument is activated by a separate
STBY INST switch located on the ELECTRICAL power panel.
If the batteries are allowed to significantly discharge prior to bringing a generator on-line, the charging current may be large
enough to result in a APU GEN OVERLOAD, or L (R) GEN OVERLOAD caution CAS message for a short time as the
batteries recharge.
POWER CENTERS
The two DC power centers (left and right) provide the following functions:
- Protect the loads from abnormal electrical power quality
- Control and reconfigure the distribution system in response to manual switching or when a fault occurs. This
reconfiguration shall ensure the supply of the buses in accordance with an established priority relating to the power
sources available
- Ensure the coupling of the two channels on the ground when only batteries or external DC power are available, or
in flight when only one generator is available
- Control the automatic load shedding
- Isolate the faulted distribution buses when a short circuit occurs on a feeder or on a bus
- Distribute the electrical power to loads located in the aft of the aircraft
- Distribute the electrical power to secondary power centers located in the front fuselage of the aircraft
- Protect distribution cables from short circuit
Additionally, there is an Auxiliary Power Center for the APU Generator.
REV 2
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/2005
07-01-06 CSP 100-6 REV 2
ELECTRICAL SYSTEM (Cont)
SECONDARY POWER CENTERS
The secondary power centers are located on the equipment rack in the front fuselage of the aircraft. They are fed by the
distribution buses of the direct current power centers and distribute electrical power to the loads in the front fuselage of the
　
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