4E-6 Developed for Training Purposes Leerjet 35/36
February 1998
CAE SimuFlite
Rudder
The rudder is mechanically positioned by cables connected
directly to a dual set of rudder pedals. Full range of motion is
30×(+2×,-1×) left and right of center. Rudder control is provided
manually by either set of interconnected rudder pedals or auto-
matic damping through the primary or secondary yaw damper
servos.
Rudder Trim
The rudder trim is accomplished by an electric motor-driven
trim tab on the rudder and controlled by the dual-segmented
trim-tab switch on the center pedestal. The switch is labeled
NOSE LEFT/ OFF/NOSE RIGHT; it consists of an upper and
lower half, and both halves must be turned simultaneously to
effect rudder trim tab movement.
The rudder trim indicator on the center pedestal shows the
position of the rudder in units of travel right or left.
Yaw Damper
The yaw damper provides automatic stabilization about the
yaw axis by controlling transient yaw motion with rudder move-
ment. A dual (primary and secondary) yaw damper system is
installed on the Learjet 35/36. Both must be operational and
one must be engaged for flight.
The yaw damper is engaged by depressing the PRI or SEC
engage (ENG) button and can be disengaged by depressing
the control wheel master switch, depressing the associated
OFF switch, or engaging the opposite yaw damper. Disengag-
ing the autopilot with the wheel master also disengages the
yaw damper. The yaw damper should be disengaged while
using rudder trim. Be sure to re-engage yaw damper after trim
is established.
On aircraft with FC-200, the yaw damper must be disengaged
for landing during the landing flare. On aircraft with FC-530,
the yaw damper disengages at touchdown through the squat
switch relay box during full flap landings.
To Next Page
Loading...
