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Electrical Control Panel..............................................................................................07-01-16
Electrical Synoptic Page............................................................................................07-01-17
EICAS Messages.......................................................................................................07-01-18
May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6
07-00-01
ELECTRICAL
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.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
07-01-01
ELECTRICAL
INTRODUCTION (Cont)
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
07-01-02
ELECTRICAL
ELECTRICAL SYSTEM
DESCRIPTION
The Challenger 300 electrical system is a 28 vdc system and divided into two main functions:
-Power generation system
-Power distribution system
The electrical power generation system consists of the following power sources:
-Two main generators provide electrical energy to feed the loads under normal operation in flight and ground operations. Either one of the engines provides sufficient generator power for normal operations -One APU generator can share electrical loads with the engine generators at medium and low altitudes or provide enough electrical generation capability to replace one or both engine generators during failure conditions -Two onboard batteries that feed the essential loads under emergency conditions when the generators are inoperative, and on the ground for feeding all loads -One standby instrument battery located in the nose landing gear bay area. It provides power to the standby instrument system for approximately 5 hours when fully charged -One optional hydraulic motor driven generator with a non-time limited source of electrical power in the event total generated power is lost -Additonally, an external DC power source for ground operation
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