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The lock disengages when the external lever is
rotated to point aft (streamlined). The lock can
also be disengaged from the cockpit by pulling
the control yoke aft from the neutral position.
NOTE
With the rudder lock engaged, the
nosewheel system allows up to 55°
of free castering when the pilot steers
with differential power and/or differential
braking. However, taxiing or
steering with rudder lock engaged
is not recommended. To release the
rudder lock from the cockpit, pull aft
on the control yoke.
Disengage the rudder lock before
towing. The rudder lock can be released
and re-engaged externally.
SECONDARY FLIGHT
CONTROLS
The secondary flight controls consist of the trim
systems for the primary flight controls, and the
lift and drag controls (flaps and speedbrakes).
TRIM SYSTEMS
Trim is provided by a tab on the inboard trailing
edge of most primary flight controls (both
elevators, the left aileron, and the rudder).
Trim systems are electrical on all three axes,
with additional mechanical trim also available
for pitch. Rudder and aileron trim are
electrically actuated by trim switches on the
lower pedestal. The elevator is operated by a
manual trim wheel on the left side of the
pedestal next to throttles. In addition, the electric
trim switches on either pilot control wheel
can control the elevator trim.
Aileron (Roll) Trim
The single aileron trim tab is on the trailing
edge of the left aileron only. The AILERON
TRIM control knob (Figure 15-5) controls the
CAUTION
15-6 510OM-00
CITATION MUSTANG OPERATING MANUAL
LEGEND
ELECTRICAL
CONTROL
AFT END OF
PEDESTAL VERTICAL
Figure 15-5. Aileron and Rudder Trim
510OM-00 15-7
CITATION MUSTANG OPERATING MANUAL
aileron trim tab through an electrical trim actuator
in the leading edge of the aileron. The
electric actuator uses two independent control
rods to move the aileron trim tab.
The aileron trim control knob is on the aft face
of the center pedestal. To operate the knob, depress
it before rotating it. Rotating the trim
knob left (counterclockwise) causes the aircraft
to roll left and trims the left wing down.
Near the bottom of the engine indication and
crew alerting system (EICAS) display, a white
horizontal analog scale and cyan pointer indicate
position of aileron trim (Figure 15-6).
If cockpit displays are set to reversionary
mode, the trim display does not appear.
The aileron trim circuit breaker is on the left CB
panel in the FLIGHT CONTROLS grouping.
Rudder (Yaw) Trim
The cockpit rudder trim tab is on the center of
the trailing edge of the rudder. It is driven by
an electrical trim actuator in the leading edge
of the rudder, controlled by the RUDDER
TRIM switch. The RUDDER TRIM switches
(centering dual sliding rocker switches) are on
the lower pedestal (see Figure 15-5).
Pushing the RUDDER TRIM switches to the
left, toward the NOSE–L position, causes the
aircraft to yaw toward the left. Pushing it right,
toward NOSE–R, causes opposite movement.
Near the bottom of the EICAS display, a white
horizontal analog scale and cyan pointer indicate
position of rudder trim (Figure 15-6).
If displays are set to reversionary mode, the
trim display does not appear.
The yaw trim circuit breaker is on the left CB
panel in the FLIGHT CONTROLS grouping.
Elevator (Pitch) Trim
The elevator trim tabs are at the trailing edges
of both elevator surfaces. Both tabs travel synchronously.
Each trim tab is connected to a mechanical
actuator by two control rods. The trim
tabs are controlled mechanically through cables
by a mechanical trim control wheel on the left
side of the pedestal beside the throttle controls
(Figure 15-7), or electrically by split switches
on the outboard grip of the control yokes.
The mechanical elevator trim system is a single
cable loop system that routes from the
command wheel in the cockpit to the tail cone,
then through the vertical tail to mechanical actuators
in each of the horizontal tail. The mechanical
actuators move linkages, which move
the trim tabs.
Additional cables connect the autopilot elevator
trim servo to the system. When the control
yoke switches are used or the autopilot is
active, the autopilot servo electrically commands
the entire mechanical system through
its cable linkage.
The elevator pitch trim servo is powered from
the left avionics bus through the AFCS circuit
breaker on the FLIGHT CONTROL pilot CB
　
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