曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

aluminum. The rudder is attached to the aft vertical stabilizer shear
web at three hinge points and to the fuselage tailcone at the rudder
control bell crank.
Rudder motion is transferred from the rudder pedals to the rudder by a
single cable system under the cabin floor to a sector next to the
elevator sector pulley in the aft fuselage. A push-pull tube from the
sector to the rudder bell crank translates cable motion to the rudder.
Springs and a ground adjustable spring cartridge connected to the
rudder pedal assembly tension the cables and provide centering force.
A rudder-aileron interconnect is installed to provide a maximum of 5°
down aileron with full rudder deflection. Right rudder input will cause
right roll input and left rudder input will cause left roll input. With
neutral aileron trim, aileron inputs will not cause rudder deflection.
On some airplanes, an electrically operated trim tab on the trailing
edge of the rudder allows pilot-operated rudder trim. Airplanes without
electric rudder trim have a ground adjustable trim tab installed.
Control Locks
The Cirrus SR22 control system is not equipped with gust locks. The
trim spring cartridges have sufficient power to act as a gust damper
without rigidly locking the position.
Revision A5
P/N 13772-001 7-13
Cirrus Design Section 7
SR22 Airplane Description
SR22_FM07_1463
Figure 7-3
Rudder Control System
Revision A5
7-14 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Trim Systems
Roll and pitch trim are provided by adjusting the neutral position of a
compression spring cartridge in each control system by means of an
electric motor. The electric roll trim is also used by the autopilot to
position the ailerons. An electrically actuated trim tab on the rudder, if
installed, provides rudder trim. It is possible to easily override full trim
or autopilot inputs by using normal control inputs.
Ground adjustable trim tabs are installed on the elevator and right
aileron to provide small adjustments in neutral trim. On airplanes
without electric rudder trim, a ground adjustable trim tab is installed on
the rudder. These tabs are factory set and do not normally require
adjustment.
Pitch Trim Control System
An electric motor changes the neutral position of the spring cartridge
attached to the elevator control horn. A conical trim button located on
top of each control yoke controls the motor. Moving the switch forward
will initiate nose-down trim and moving the switch aft will initiate noseup
trim. Neutral (takeoff) trim is indicated by the alignment of a
reference mark on the yoke tube with a tab attached to the instrument
panel bolster. The elevator trim also provides a secondary means of
aircraft pitch control in the event of a failure in the primary pitch control
system not involving a jammed elevator. Elevator (pitch) trim operates
on 28 VDC supplied through the 2-amp PITCH / YAW TRIM circuit
breaker on Main Bus 1.
Roll Trim Control System
An electric motor changes the neutral position of a spring cartridge
attached to the left actuation pulley in the wing. A conical trim button
located on top of each control yoke controls the motor. Moving the
switch left will initiate left-wing-down trim and moving the switch right
will initiate right-wing-down trim. Neutral trim is indicated by the
alignment of the line etched on the control yoke with the centering
indication marked on the instrument panel. The aileron trim also
provides a secondary means of aircraft roll control in the event of a
failure in the primary roll control system not involving jammed ailerons.
Aileron trim operates on 28 VDC supplied through the 2-amp ROLL
TRIM circuit breaker on Main Bus 1.
Revision A7
P/N 13772-001 7-15
Cirrus Design Section 7
SR22 Airplane Description
Yaw Trim System
Yaw trim is provided by spring cartridge attached to the rudder pedal
torque tube and console structure. The spring cartridge provides a
centering force regardless of the direction of rudder deflection. The
yaw trim is ground adjustable only.
On airplanes with electric rudder (yaw) trim, trim changes are pilot
controlled through a linear actuator connected to a hinged trim tab on
the rudder trailing edge. The actuator is installed in the rudder. A
RUDDER TRIM indicator with integral rocker switch is mounted in the
console immediately adjacent to the FLAP control switch. Pressing the
left half of the switch initiates Nose L trim and pressing the right half
initiates Nose R trim. A needle sweeps the trim indicator scale to
indicate trim position. The full Nose Right trim tic is labeled TAKEOFF.
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：CIRRUS DESIGN SR22西銳22飛行員操作手冊(cè)和飛機(jī)飛行手冊(cè)(59)