FLIGHT CONTROLS
Description
Aircraft Operations Manual
8.1
PAGE
2
2.
MAIN COMPONENTS AND SUBSYSTEMS
2.1
Ailerons
Each aileron is hinged to the wing trailing edge at
two points.
The left and right aileron control channels are me-
chanically interconnected.
However, should one of the control channels be-
come jammed, the other channel can be controlled
by applying excessive force to the control wheel or
disconnected by pulling the roll disconnect handle in
the cockpit which separates the two channels from
each other. If the handle is not pulled the discon-
nect function is automatically reset when the exces-
sive control force no longer is applied.
After the handle has been pulled, disconnection is
permanent and the system can only be reset on the
ground by use of the reset switch adjacent to the
disconnect unit.
When the control channels are disconnected the left
pilot has control of the left aileron while right pilot
retains control of the right aileron, and the pilot
whose aileron channel is free, maintains sufficient
control of the aircraft with his wheel.
A centering spring unit is installed in each control
system to improve the lateral stability at extreme
sideslip angles. The spring unit also compensates
the aerodynamic upfloat in case of a disconnection
during flight.
A sensor supplies aileron position information to the
flight recorder.
The autopilot aileron servo drive is mechanically
linked to the right aileron channel.
2.2
Elevators
The elevators are hinged to the horizontal stabilizer
at three points.
The left and right elevator control channels are me-
chanically interconnected.
However, should one of the control channels be-
come jammed, the other channel can be controlled
by applying excessive force to the control column or
disconnected by pulling the pitch disconnect handle
in the cockpit which separates the two channels
from each other. If the handle is not pulled the dis-
connect function is automatically reset when the
excessive control force no longer is applied.
After the handle has been pulled, disconnection is
permanent and the system can only be reset on the
ground.
When the control channels are disconnected the left
pilot has control of the left elevator while the right
pilot retains control of the right elevator, and the
pilot whose elevator channel is free, maintains suffi-
cient control of the aircraft with his column.
In normal configuration, or if the control channels
are disconnected and no elevator is jammed, only
one pilot shall control the aircraft with his column.
If left channel is jammed, no stick pusher move-
ment is available, see AOM 19/4.1.
An elevator downspring is installed in each control
system in order to improve the stick
−
force variation
with speed at low speed. The spring acts with a
constant force over the whole elevator range of
travel. Additionally, an elevator upspring is installed
in each control system as a complement to the
downspring. The upspring only acts at elevator
angles of 6
down or more. The spring
−
force in-
creases with increased down deflection. The spring
improves the pushover characteristics of the aircraft
but has no function at manoeuvres encountered
during normal operation.
Two sensors supply elevator position information to
the flight recorder.
The autopilot elevator servo drive is mechanically
linked to the left elevator channel.
2.3
Rudder
The rudder is hinged to the fin at two points and is
operated with assistance of a spring tab. An aero-
dynamic balance horn is located at the top of the
rudder.
Each pair of rudder pedals is mechanically intercon-
nected. The pedal positions can be individually ad-
justed with a lever mounted in the center of each
pair of pedals.
A sensor supplies rudder position information to the
flight recorder.
Dec 01/20