Trim Systems; Pitch Trim Control System; Roll Trim Control System - Cirrus SR22 Pilot Operating Handbook

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 nose-
up 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.
7-14 P/N 13772-001
Revision A7