Eclipse 500 System Manual page 38

Section 2. Avio Avionics Suite
Engine System Control- Ignition control Engine dry motoring
Fire Suppression
Fuel system control- electric fuel pumps, fuel crossfeed
Flight Controls- primary flap and trim control, secondary trim control
Electrical- control of electronic circuit breakers
Environmental- fan activation and speed, temperature control
Pressurization- aircraft pressurization settings
Ice Protection- anti-ice and de-ice controls
Primary landing gear control
Exterior Lighting- command of ECB's to activate and deactivate lighting
2.2.3 Systems Monitoring and reporting
The systems monitoring and reporting capability of the ACS' allow reporting of
various systems status to the pilot through the Primary and Multi-Function Displays
(PFD & MFD). Examples of system monitoring and fault sensing include:
Electrical system monitoring
Fuel System monitoring- (fuel gauging probes, fuel pumps, valves)
Secondary engine parameter monitoring- (fuel flow, oil temperature, oil pressure)
Engine fire detection
Pressurization and climate control system monitoring (temperature sensors,
valves)
Trim monitoring- (trim motor the current state and position of primary and
secondary flight controls: flaps, trims, control surfaces)
Landing gear monitoring- (gear position, actuator operation)
Ice Protection monitoring- (operation of anti-ice and deice system components)
Door indication monitoring- (state of main cabin door)
Brake system monitoring- (brake fluid level)
Oxygen system monitioring- (oxygen pressure)
Control monitoring is often attached to various Crew Alerting System Messages
(CAS), (ex. PARKING BRAKE status message indicates that the PARKING BRAKE
handle is pulled out).
As a compliment to monitoring of systems, the ACS also provides fault sensing
capability for the various systems components and their associated sensors. Failure
monitoring is provided for various systems, some examples include the failure of:
flap actuators; control valves, such as the fuel shutoff valve; sensors, such as the
climate control temperature sensors. Should a component or sensor fail a CAS
message is displayed to the pilot to indicate that a failure has occurred. Due to the
built in redundancy of aircraft systems, many of these failures do not result in a
complete loss in system functionality, but only a loss in a redundant component.
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Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
Version 2.0 April 2007