AFMS N°D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED
AEROPLANES
Section 7 – Airframe and Systems description -
FLIGHT CONTROLS
3 FLIGHT CONTROLS
Aircraft flight controls are operated through conventional stick and rudder pedals. Longi-
tudinal control acts through a system of push-rods and is equipped with a trim tab. a cable
control circuit is confined within the cabin and it is connected to a pair of push-pull rod sys-
tems positioned in each main wing which control ailerons differentially. Aileron trimming is
carried out on ground through a small tab positioned on left aileron.
Flaps are extended via an electric servo actuator controlled by a switch on the instrument
panel. Flaps act in continuous mode; the indicator displays three markings related to 0°,
takeoff (T/O) and landing (FULL) positions. A breaker positioned on the right side of the
instrument panel protects the electric circuit.
The control of the stabilator trim is operated by means of both a control wheel, located be-
tween the two front seats that acts directly on the control cables, and an electrical actuator
controlled by a switch located on the control wheel; stabilator trim position is displayed on a
dedicated analogue indicator located on the LH area of the instrument panel.
Rudder Trimming device for lateral control is provided by means of an electrical actuator
controlled by a rocker switch located near the pitch trim wheel; the surface is connected to
a potentiometer linked to a rudder trim indicator included in the Garmin G1000 EIS (Engine
Indication System).
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