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a comparable movement of the rudder (as
sensed through the rudder pedals). If the pilot
rolls the aircraft to the left, the interconnect also
causes some rudder deflection (and resultant
airplane yawing) to the left. Conversely, pressure
on the rudder pedals and movement of
the rudder results in a coordinated movement
of the ailerons and control yoke.
In flight, to intentionally slip or skid/yaw the
airplane, the pilot can override the interconnect
by applying opposite forces to the control yoke
and rudder pedals (“cross-controlling”). On
the ground, the interconnect may cause some
aileron and control yoke movement, as a coordinated
response to rudder movements caused
by the crew steering with the rudder pedals.
RUDDER SYSTEM
The rudder on the trailing edge of the vertical
stabilizer provides yaw control. It moves as
much as 35° left or right of center. It is controlled
through cables connected to the cockpit
control pedals and the autopilot yaw servo.
The rudder is moved by fore and aft movement
of the pedals.
The rudder pedals are floor-mounted and nonadjustable.
The pedals are connected to the rudder
through mechanical linkages and cables.
Two separate rudder cable loops, routed differently,
provide redundancy to protect against
an engine rotor noncontainment (Figure 15-2).
Operation
Pressing either pilot rudder pedal (left or right)
moves the rudder in that direction, which yaws
the airplane that direction. Copilot controls
work the same. Pilot and copilot pedals are mechanically
linked so the pilot applying the
greater force controls yawing, and controls
the amount of pedal movement for both pilots.
The rudder pedals also control nosewheel
steering (refer to Chapter 14—“Landing Gear
and Brakes.”).
The single autopilot yaw servo is mechanically
connected to the rudder. When the autopilot
is engaged, the yaw servo provides input to
the rudder system in response to the AFCS
commands.
The yaw damper can be disengaged by:
• Pressing the YD button on the AFCS
controller
• Pressing the AP TRIM DISC switch on
either control yoke
Additionally, pilots can manually override the
yaw servo motor by pushing the rudder pedals.
For information on the AFCS (including
autopilot), refer to Chapter 16—“Avionics.”
ELEVATOR SYSTEM
The elevators are on the trailing edge of the
horizontal stabilizer and provide longitudinal
(pitch) control of the airplane. The elevators
are mechanically controlled through
cables by either pilot moving the control yoke
fore and aft, or by the autopilot pitch servo.
The pitch system is a manual system consisting
of conventional mechanical flight control
components. A cable run from the pilot and
copilot control yokes to a common elevator
pulley provides output to the elevator surfaces.
The aft elevator pulley is attached to
each surface by a pushrod and horn. Motion
from the aft elevator pulley is transmitted to
the elevators by their respective pushrod.
In the event of engine rotor non containment,
separate elevator trim systems provide
sufficient pitch control for elevator
control redundancy.
Operation
By moving the control column aft (approximately
4 inches maximum deflection), the elevators
rotate up, causing the nose of the
aircraft to pitch up. By moving the control column
forward (approximately 3 inches maximum
deflection), the opposite motion occurs.
A single pitch servo is mechanically connected
to the elevator cables. When the autopilot is engaged,
the pitch servo provides autopilot input
to the elevator system in response to the AFCS
commands.
Normally, the autopilot can be disengaged by:
• Pressing the AP or YD button on the
AFCS controller
• Pressing the AP TRIM DISC switch on
either control yoke
• Commanding electric pitch trim
The pitch servo can also be manually overridden
by either pilot applying a force to the
15-4 510OM-00
CITATION MUSTANG OPERATING MANUAL
Figure 15-2. Rudder Control System Installation
510OM-00 15-5
control yoke. For information on the AFCS
(including autopilot), refer to Chapter 16—
“Avionics.”
CONTROL LOCK
SYSTEMS
Control locks, when engaged, restrain the primary
flight controls. The control lock system
prevents damage to the control surfaces and
systems from wind gusts striking the aircraft
while it is on the ground. There are two parts
　
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