Eclipse 500 System Manual page 238

Section 10. Electrical
10.2 Aircraft Computer System (ACS) Interfaces
The electrical system is automatically controlled by the Aircraft Computer System
(ACS) during normal operation. The two aircraft batteries (Start and Systems) have
no direct interface with the ACS and are directly controlled by the pilot through two
switches on the left switch panel.
Based on pilot commands (engine start, stop), or generator status (both operational,
one inoperative, both inoperative), the ACS automatically configures the electrical
system, as well as activating and deactivating Electronic Circuit Breakers for various
systems components. While the ACS has can command ECBs, the current
protection feature of each ECB is independent of the ACS.
In return the ACS monitors the status of electrical system components including:
contactor position, bus voltages, generator output, battery state and rate of charge or
discharge, as well as ECB status.
The ACS provides control commands and receives status information for the
following electrical system components:
1. Battery Bus Contactor
2. Start Battery Contactor/ Lighting Controller
3. Start Battery Heater
4. Systems Battery Heater
5. External Power Contactor
6. Electronic Circuit Breaker Unit #1
7. Electronic Circuit Breaker Unit #2
8. Left Generator Control Unit and Contactor
9. Right Generator Control Unit and Contactor
10. Forward Power Distribution Center
a. Electronic Circuit Breaker Unit #3
b. Left Battery Bus Contactor
c. Right Battery Bus Contactor
d. Battery Bus
e. Left Forward Bus
f. Right Forward Bus
11. Aft Power Distribution Center
a. Electronic Circuit Breaker Unit #4
b. Electronic Circuit Breaker Unit #5
c. Bus Tie Contactor (BTC)
d. Left Forward Circuit Breaker/Contactor
e. Right Forward Circuit Breaker/Contactor
f. Left Aft Bus
g. Right Aft Bus
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Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
Version 2.0 April 2007