CITATION MUSTANG OPERATING MANUAL
INTRODUCTION
This chapter describes the flight controls of the Cessna Model 510 Citation Mustang.
The aircraft has fixed and moveable surfaces that provide stability and control during
flight. The primary flight controls are ailerons, rudder, and elevators. Secondary flight
controls include trim devices, flaps, and speedbrakes. Control locks are also described.
GENERAL
The flight control systems consist of the control
surfaces, trim control surfaces, trim indicating
systems, and the related mechanical
and electrical systems that control the airplane
during flight.
The primary flight controls (elevators,
ailerons, and rudder) directly control aircraft
movement around the three axes of flight
(pitch, roll, and yaw). They are manually actuated
through cables by dual conventional
control yokes and dual sets of rudder pedals
in the cockpit. They can be immobilized by
control locks when on the ground to prevent
damage to the control surfaces and systems
from wind gusts striking the aircraft.
The secondary flight controls include trim,
flaps, and speedbrakes. Trim tabs, electrically
or mechanically adjusted through controls on the
cockpit pedestal or control yoke, assist flight
control on all three axes. Mechanical elevator
trim, adjusted through a cockpit pedestal wheel,
is also provided.
CHAPTER 15
FLIGHT CONTROLS
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Flaps and speedbrakes directly adjust airplane
lift and drag. Both controls are electrically actuated.
Flaps are operated by a handle on the
cockpit pedestal. Speedbrakes are operated by
a switch on the throttle.
All flight control surfaces are shown in
Figure 15-1.
PRIMARY FLIGHT
CONTROLS
DESCRIPTION
The primary flight controls (ailerons, rudder,
and elevators) are manually operated by either
the pilot or the copilot through a conventional
control yoke and rudder pedal arrangement.
Control inputs are transmitted to the control
surfaces through cables, bellcranks, and
pushrods. The rudder pedals also operate the
nosewheel steering and wheel brakes (see
Chapter 14—“Landing Gear and Brakes”). A
flexible mechanical interconnect between the
rudder and ailerons provides improved lateral
stability.
The primary flight controls can also be controlled
by the autopilot and yaw damper (see
Chapter 16—“Avionics”).
The rudder, both elevators, and the left aileron
are each equipped with a trim tab that is electrically
actuated from the cockpit. The elevator
tabs can also be mechanically positioned
by the pitch trim wheel on the control pedestal.
AILERON SYSTEM
Two ailerons (one on the outboard trailing
edge of each wing) provide roll control.
Neutral aileron position is 2° up. The ailerons
are controlled through cables connected to
the cockpit control yokes and the autopilot
aileron electric servo. The control yoke rotates
70° in each direction to provide maximum
aileron deflection.
15-2 510OM-00
CITATION MUSTANG OPERATING MANUAL
FLAP
ELEVATOR
TRIM TAB
TRIM TAB
TRIM TAB
RUDDER
SPEEDBRAKE
AILERON
STRAKE
Figure 15-1. Flight Control Surfaces
510OM-00 15-3
CITATION MUSTANG OPERATING MANUAL
Operation
When the pilot rotates the control yokes counterclockwise,
the right aileron rotates down and
the left aileron rotates up, causing the aircraft
to roll left. By turning the control yokes clockwise,
the opposite is true.
When the autopilot is operating, the autopilot
roll servo provides inputs to the aileron control
system. A single autopilot roll servo is mechanically
connected to the aileron cable
system. When the autopilot is engaged, the
autopilot servo provides autopilot input to the
aileron system in response to the automatic
flight control system (AFCS) commands.
Disengaging the autopilot can be accomplished
by three normal means:
• The AP or YD button on the AFCS controller
• The AP TRIM DISC switch on either
control yoke
• By commanding pitch trim
Either pilot can manually override the servo
motor by applying force to the control yoke.
For information on the AFCS (including autopilot),
refer to Chapter 16—“Avionics.”
Aileron-Rudder Interconnect
A flexible mechanical interconnect between
rudder and ailerons provides improved lateral
stability. Movement of the ailerons results in
　
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