Rudder System - Cirrus SR22 Pilot Operating Handbook

Section 7 Cirrus Design
Airplane Description SR22

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.
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.
7-12 P/N 13772-001
Revision A5