Eclipse 500 System Manual page 114

Section 6. Ice Protection
6.2 Aircraft Computer System (ACS) Interfaces
The ACS has control and monitoring functionality over both the Anti-ice and Deice
components of the ice protection system.
The deice system includes a bleed air deice manifold that is responsible for routing
engine bleed air through various valves and pressure switches to the wing and
horizontal stabilizer boots.
The anti-ice system consists of automatically heated air data probes (discussed in
the Air Data Chapter) and heated engine inlets.
Air is routed to both deice manifold and the engine inlets by a pressure regulating
shut-off valve on each engine.
The pilot selections using the ENG/WING switch on the center switch panel are sent
through the PFD to the ACS, which in turn controls inflation and deflation of the
boots and routing of air to the engine inlets by turning on and off applicable Electronic
Circuit Breakers (ECBs). The ECBs for the ice protection system are located within
the Aft Power Distribution Center in Electronic Circuit Breaker Units (ECBUs) four
and five.
Six sensors allow the ACS to monitor the ice protection system components for low
bleed air pressure from the engine or low pressure within the deice boots. The
pressures switches also provide feedback to the ACS for failure monitoring.
ICE PROTECTION SYSTEM SENSORS
1. Left Engine
a. Inlet Temperature
b. Regulated Pressure Switch
2. Right Engine
a. Inlet Temperature
b. Regulated Pressure Switch
3. Deice Boots
a. Outer Wing Boot Pressure Switch
b. Inner Wing/Stabilizer Boot Pressure Switch
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Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
Version 2.0 April 2007