Figure 25.Flight Controls Schematic - Eclipse 500 System Manual

Section 3. Flight Controls
3. Flight Controls
3.1 General
The flight control system consists of primary flight controls (ailerons, rudder, and
elevator) and secondary flight controls (wing flaps and trim).
The primary flight controls are operated with a sidestick and rudder pedals at each
pilot station. The primary flight control system is a mechanical system which uses
bellcranks, pushrods, cables, and pulleys to actuate the control surfaces. Rudder
pedals are individually adjustable. Static wicks are attached to the elevator (two per
elevator) and wing tip tanks(one per tip tank) to discharge static electricity.
Trim for the three primary flight controls is electrically powered. Elevator and aileron
trim is controlled by a four-position switch on the top of each sidestick. Rudder trim is
controlled by a rotary switch mounted on the aft portion of the center pedestal. Trim
position for all three axes is displayed on the MFD. If a normal trim control fails, all
three trim systems can be controlled using the flight controls synoptic page on the
MFD. All trim motors can be inhibited in the event of a trim runaway.
To protect against high wind conditions, a gust lock is placed over the left sidestick to
secure the ailerons and elevator in place, while the rudder is locked by mechanical
resistance from the nose wheel steering system.
The wing flaps are electrically powered fowler flaps, controlled by a three-position
flap selector lever located on the throttle quadrant. Flap position is displayed on the
upper portion of the MFD.
Version 2.0 April 2007
Figure 25. Flight Controls Schematic
Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
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