曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

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
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.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Cessna塞斯納公務機飛行手冊(88)