I A P 2 0 2 3 . 0 0 1 - A F M / I R I S T E X A N I I P A G E | 58
FOR SIMULATION USE ONLY – NOT A TRAINING AID
is limited to 18° trailing edge up and 16° trailing edge down deflection. The elevator
is mass balanced with weights located in the elevator horns. Two down springs
fitted to the elevator bell crank provide a balanced control feel.
A bob weight is installed on the front control stick which increases stick forces as
G-load on the aircraft increases, to improve control feel and help prevent
overstressing the airframe.
Elevator Trim
Elevator (pitch) trim is provided by an electromechanical actuator which drives a
tab surface installed on the right side of the elevator.
The actuator is controlled by a combined roll/pitch trim switch located on the
control stick grip in each cockpit. Elevator tab travel is limited to 5.5° trailing edge
up and 22° trailing edge down.
Trim position is indicated on the triple-trim indicator on the trim control panel.
Power is provided through a circuit breaker, placarded AIL/EL TRIM, located on the
battery bus circuit breaker panel in the front cockpit.
RUDDER
The rudder system includes the rudder, rudder pedals, cables, pulleys, and a bell
crank, with one push-pull rod and two rudder centering springs. The front and rear
cockpit rudder pedals are interconnected by tie rods.
Rudder pedal position adjustment is accomplished with a hand crank located on the
centre console of each cockpit. The crank is connected to a jackscrew on the
pedals. Pedal position can be adjusted a total of 7 inches from forward to aft.
The rudder is deflected by movement of the rudder pedals in either cockpit. Rudder
travel is limited to 24° left and 24° right deflection. The rudder surface is statically
mass balanced with a balance weight installed in the rudder horn.
Rudder Trim
Rudder (yaw) trim is provided by an electromechanical actuator located in the
vertical stabilizer, which drives an anti-servo tab surface on the trailing edge of the
rudder. The actuator is controlled by a switch installed on the PCL in each cockpit.
Tab deflection with the rudder at neutral is limited to 9° trailing edge right and 9°
trailing edge left.
Trim position is indicated on the trim control panel. Power is provided through a
circuit breaker, placarded RUD TRIM, located on the battery bus circuit breaker
panel in the front cockpit.
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