AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION
Section 7 – Airframe and Systems description
FLIGHT CONTROLS
3. FLIGHT CONTROLS
Aircraft flight controls are operated through conventional stick and rudder pedals.
Longitudinal 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 systems positioned in each main wing which control ailerons differen-
tially. 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 in-
strument 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 a control wheel, located be-
tween the two front seats that acts directly on the control cables.
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 ac-
tuator controlled by a rocker switch located near the pitch trim wheel; the surface is
connected to a potentiometer linked to a rudder trim analogue indicator located on
the LH area of the instrument panel.
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