AFMS
N"D07
FOR
GARMIN
GFC700
AUTOPILOT
AND
VARIABLE
PITCH
PROPELLER
EQUIPPED
AEROPLANES
PageAPV
7-8
3
FLIGHTCONTROLS
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 aileron trailing edge.
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/0)
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 G 1000 EIS (Engine
Indication System) strip page.
Section
7 -
Airframe
and
Systems
description
FLIGHT
CONTROLS
Ed.
2,
Rev.4
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