AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND
RNAV/RNP NAVIGATION ELIGIBILITY
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 instru-
ment panel. Flaps act in continuous mode; the indicator displays three markings
relat-ed 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, locat-
ed between the two front seats that acts directly on the control cables, and an electri-
cal actuator controlled by a switch located on the control wheel; stabilator trim posi-
tion is displayed on a dedicated analogue indicator located on the LH area of the in-
strument 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
con-nected to a potentiometer linked to a rudder trim indicator included in the Gar-
min G1000 EIS (Engine Indication System).
To Next Page
Loading...
