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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
to the control lock system: aileron/elevator
control lock and rudder lock.
Aileron/Elevator Control Lock
To lock the aileron and elevator control surfaces,
a removable flag-insert device fits through a
hole in both the control yoke bushing at the control
panel and the back of the pilot control yoke
(Figure 15-3). A special U-shaped lock pin
locks the yoke in a most-forward position, nose
down with the wheel at ailerons-neutral. The
U-shape of the pin ensures that no single pin
device can engage the lock. The device, installed
from the top, pins the control yoke to
the instrument panel. The flag on the pin covers
the pilot primary flight display (PFD) airspeed
tape and horizontal situational indicator
(HSI). The flag portion of the pin is keyed to
the instrument panel receptacle so the control
lock cannot be installed without obstructing
the view of the pilot.
The yoke position and the visual obstruction
from the flag provide unmistakable warning
of control lock engagement. To insert the lock:
• Rotate the yoke to the center position so
the receptacle in the bushing and the receptacle
on the control yoke are aligned.
• Move the yoke forward until both ends
of the pin can be inserted into their respective
receptacles.
• Insert the U-shaped pin of the flag device
into the receptacles.
• Check the control wheel is locked in
both pitch and roll.
When removing the lock:
• Grasp the U-shaped pin between the receptacles
(with the right hand) and remove,
raising it straight up until clear of
both receptacles.
• Stow the control lock.
• Check the control yoke is free and clear
for both roll and pitch.
Rudder Lock
The rudder control lock inserts a pin into the
aft rudder pulley, preventing movement of the
rudder. The rudder lock must be operated from
outside the aircraft (Figure 15-4).
To lock the rudder, the pilot rotates a handle
on an external lever on the left side of the tail
CITATION MUSTANG OPERATING MANUAL
Figure 15-4. Rudder Lock System (Left
Side of Tail Cone)
Figure 15-3. Aileron/Elevator Control
Lock
cone 60° counterclockwise (up), which inserts
a pin into the aft rudder pulley to lock the
rudder torque tube.
　
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