A
A
I
I
R
R
P
P
L
L
A
A
N
N
E
E
T
T
E
E
C
C
H
H
N
N
I
I
C
C
A
A
L
L
D
D
E
E
S
S
C
C
R
R
I
I
P
P
T
T
I
I
O
O
N
N
,
,
O
O
P
P
E
E
R
R
A
A
T
T
I
I
N
N
G
G
,
,
M
M
A
A
I
I
N
N
T
T
E
E
N
N
A
A
N
N
C
C
E
E
A
A
N
N
D
D
R
R
E
E
P
P
A
A
I
I
R
R
M
M
A
A
N
N
U
U
A
A
L
L
2-25
Document No.:
EV97SLNOEN
Date of Issue:
02/2008
Revision:
-
2.3.11 Control system
2.3.11.1 Longitudinal control system description
The airplane is equipped with a classic dual control system. The elevator is controlled by a control
stick, with connecting rods and arms. A control stick push/pull movement is transmitted, by a rod
inside the quadrant between the seats to the elevator through a two-armed lever located
underneath the baggage compartment floor cover. The angular displacement of the two-armed
lever is transferred by a longitudinal motion of two rods, connected with a single arm lever, inside
the middle rear part of the fuselage. The rear rod is connected to the elevator single-arm lever.
A control stick motion is limited by two stops. Both control sticks have a common "push-down" stop
on the center-section and each control stick has a "pull-up" stop formed with a reinforcement
riveted on the front edge of each seat. The rods have adjustable ends and swivel bearings to
adjust the elevator deflections.
2.3.11.2 Lateral control system description
The ailerons are controlled by control sticks, connecting rods and arms. A control stick lateral
motion is transferred by a short rod in the cockpit to a longitudinal movement of a longer rod in the
wing. This in turn transferrs to the angular displacement of a two-armed lever attached to the wing
main spar. The two-armed lever angular movement is transferred to the ailerons by short rods.
The rods have adjustable ends to adjust the aileron deflections. The control stick has a termination
stop.
Electric aileron trim tab control can be installed optionally. Control switches are located on the
control stick, trim tab position indicator is located on the instrument panel.
CAUTION
To adjust an aileron deflection, never use the adjustable end of the short rod which is accessible
when wing fillet (covering the space between the wing and fuselage) is removed. See Figure in
2.3.11.7.1.
2.3.11.3 Directional control system description
The rudder control system is dual. The rudder is controlled by cables attached at the rudder pedals
and guided alongside the fuselage sides to the rudder. The rudder control cable is equipped with
adjusting stops located in the cockpit (see figure on page 2-29). The rudder pedals are attached to
the cockpit floor. There are toe brake pedals on the pilot's rudder pedals to operate the main wheel
brakes (co-pilot toe brake pedals optional). The cables are connected to the hinges in the lower
part of the rudder leading edge. The cables are prestressed by means of nose wheel control rods.
The rudder control is connected to the nosewheel landing gear to control the nosewheel by the
adjustable rods.
