7-12
P/N 13772-005
Section 7
Cirrus Design
Systems Description
SR22T
Rudder System
The rudder provides airplane directional (yaw) control. The rudder is of
conventional design with skin, spar and ribs manufactured of
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.
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.
A ground adjustable trim tab is installed on the rudder to provide small
adjustments in neutral trim. This tab is factory set and does not
normally require adjustment.
Control Locks
The airplane’s 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.
Original Issue
