Eclipse 500 System Manual page 37

Section 2. Avio Avionics Suite
2.2 Aircraft Computer Systems
The Aircraft Computer System (ACS) consists of two identical ACS computers. Each
ACS unit is co-located with one of the aircrafts two Full Authority Digital Engine
Controller (FADEC) units in a Line Replaceable Unit known as an Avio Processing
Center (APC). The left Avio Processing Center is located along the left aft fuselage
wall, while the right Avio Processing Center is located underneath the baggage
compartment floor.
While these units are physically the same, each individual (left or right) ACS will
perform slightly different operations. The ACS has three primary functions
Command and Control of Systems- activation, deactivation, load shedding
Performs Pilot Commands
Monitors and Reports- Fault Sensing
2.2.1 Command and Control of systems
The command and control of systems capability of the ACS allows the pilot the
primary means of systems control on the Eclipse 500. Unlike aircraft cockpits of the
past, the Eclipse 500 is devoid of many of the various switches, levers and other
manual controls for aircraft systems. In its place, the pilot's interface takes place
primarily through the use of line select key controls on various aircraft systems
synoptic pages normally located on the MFD.
There are two types of automation that the Eclipse 500 utilizes. One type of
automation involves decisions that require speed that is faster than a pilot can make.
This type of automation is exemplified by the engine control system (FADEC- Fully
Automated Digital Engine Control). The engine demands that fuel control decision to
the engine must be made many times per second, each time taking into account a
range of aircraft parameters such as outside air temperature, air speed, and altitude.
In cases like this, the pilot is informed of overall performance (Indicated Turbine
Temperature (ITT), N1 and N2 turbine speeds and oil pressure) to verify that the
engine is performing within its design limits
The other kind of automation is aimed at reducing pilot workload. In many cases
functions that are routine or unnecessarily burdensome have been automated. An
example of this is the command of the electric fuel pumps. For most normal
operations, the electric fuel pumps are in the automatic (AUTO) mode of operation.
This means the ACS automatically activate for start, fuel crossfeed, and low fuel
pressure. Notification of the pilot that this is occurring takes place through a STATUS
level CAS message; this assures that the pilot is always kept aware of the current
state of systems components.
Automatic electrical load shedding is also provided by the ACS. When the ACS
detects a loss of electrical power, i.e. the loss of a single or the loss of both
generators; it has the capability of automatically load shedding the necessary
electrical equipment to maintain sufficient power and systems functionality for the
pilot to safely manage the aircraft.
2.2.2 Performs Pilot Commands
While several systems have automatic controls, the pilot has the capability to
override or manually control systems components from the synoptic pages.
Commands from these synoptic pages are sent to the ACS upon which the individual
components are activated.
Examples of control and command of systems include:
Version 2.0 April 2007
Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
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