ELECTRICAL
Sep 13/2004
Flight Crew Operating Manual
Volume 2
REV 1
CSP 100-6
07-01-01
REV 1
INTRODUCTION
Primary DC electrical power is provided by two engine-driven generators and one APU-driven generator supplying 28 volt
power to a split bus electrical system. An automatic electrical load-shedding system prevents generator overload and
prolongs battery duration during a single or dual generator failure. Two main batteries power essential avionics,
communication, and instrumentation. A separate battery powers the independent standby instrument system. An optional
hydraulically driven electrical generator is available to provide electrical power generation in the event all engine and APU
generator power is lost.
A ground power unit can be connected to the aircraft to provide electrical power if desired.
The only AC electrical power requirements are for passenger convenience. This power is provided by inverters located in
the aft accessory compartment.
The electrical system incorporates a split, multiple bus system for power distribution interconnected by contactors, fuses,
and circuit breakers. These react automatically to isolate a malfunctioning circuit.
Summary of Contents for Challenger 300
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