Section 7 – Airframe and Systems description
AIRFRAME
2.4. FLIGHT CONTROLS
The main flight control system controls the airplane in three axes. All primary
controls (ailerons, rudder and stabilator) are manually operated by a conventional
control column and rudder pedals, pulleys, cables, bellcranks and rods.
The secondary flight controls consist of a two-axis trim system and a flaps system.
Complete dual controls are provided for pilot and co-pilot.
Longitudinal control acts through a system of push-pull rods connected to the con-
trol column and moving the stabilator whose anti-tab winglet works also as trim
tab. Autopilot pitch servo (if installed) is connected to the push-pull rods system
through driving cables.
Longitudinal trim is performed by a small tab positioned on the stabilator and
manually operated via a control wheel positioned between the two crew seats. As
optional, it is available an electrically operated longitudinal trim which it is also
controlled by the autopilot system, when installed.
Trim position is monitored by an indicator on the instrument panel. A trim dis-
connect toggle switch is provided.
Ailerons control is of mixed type with push-rods and cables; 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 differentially.
The U-shaped control wheels, hinged on the top of the control column, control the
ailerons. Control wheel motion is transferred to the ailerons through a cable loop,
up to the interconnecting rod linking the two push-pull rod systems which finally
transmit the motion to the ailerons.
When either aileron control wheel is rotated, the crossover cable rotates the other
control wheel.
The left aileron has a trim tab adjustable on ground: its deflection allows for lat-
eral trimming of the airplane.
Both flaps are extended via a single electric actuator controlled by a switch on the
instrument panel. Flaps act in continuous mode; the analogue indicator displays
three markings related to 0°, takeoff (T/O) and landing (FULL) positions.
An aural warning is generated whenever the flaps are lowered to the FULL posi-
tion and the landing gear is not down-locked.
Rudder is operated through a cable system. A rudder trim tab allows aircraft direc-
tional trimming, especially in case of OEI operation: it is electrically operated via
a switch located on the central console placed between crew seats.
Its position is monitored by an indicator on the instrument panel. A trim discon-
nect toggle switch is provided.
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