Eclipse 500 System Manual page 237

Section 10. Electrical
10. Electrical
10.1 General
The Eclipse 500 electrical power distribution system is a split bus, DC system,
powered by two 200 amp, 30 VDC regulated starter/generators driven by the
engine's accessory gearbox.
Circuit protection is provided by 127 Electronic Circuit Breakers (ECBs) in
conjunction with two mechanical circuit breakers on the left switch panel. Critical
electric functions are powered through redundant circuit breakers connected to
different power buses. This permits continued operation of all critical avionics
components even if a bus fault occurs or a circuit breaker fails. The reduction in
mechanical circuit breakers significantly reduces cockpit switch panel clutter. In
addition, the use of the more reliable, ACS controlled ECBs reduces pilot workload.
There are also two 22 amp hour, 24 VDC sealed, maintenance-free lead acid
batteries located in the nose compartment of the aircraft. A start battery and systems
battery provide aircraft power when generators are not running and float on electrical
buses when engines are running to reduce voltage transients when electrical
equipment is switched on or off. A 28 volt DC external power receptacle is located on
the lower right aft fuselage. The pilot can monitor and configure the electric system
using the electrical synoptic page on the MFD.
Entry, overhead, and baggage compartment lights are powered directly from the Hot
Battery Bus allowing them to be turned on without powering the avionics. These
lights are on a timer to avoid depleting the batteries.
Version 2.0 April 2007
Copyright © — Eclipse Aviation Corporation
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