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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 8°
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.
Control Locks
The Cirrus SR20 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.
March 2010
Information Manual 7-13
Cirrus Design Section 7
SR20 Airplane Description
SR20_FM07_1463
Figure 7-3
Rudder Control System
March 2010
7-14 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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. It is possible to easily override full trim or
autopilot inputs by using normal control inputs.
Ground adjustable trim tabs are installed on the rudder, elevator and
right aileron to provide small adjustments in neutral trim. 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. Pressing down on the switch will disconnect the autopilot if the
autopilot was engaged. 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
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. Pressing down on the switch will
disconnect the autopilot if the autopilot was engaged. 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.
March 2010
Information Manual 7-15
Cirrus Design Section 7
SR20 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.
March 2010
7-16 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Flight Deck Arrangement
The following paragraphs are a general description of the flight deck,
instruments, and controls. Details relating to the instruments, switches,
circuit breakers, and controls on the instrument panel, bolster, and
center console are located with the description of the affected system.
Instrument Panel
The instrument panel is designed for glare-free use in all flight
conditions. The instrument panel is arranged primarily for use by the
pilot in the left seat; however, it can be viewed from either seat. Flight
instruments and annunciators are located on the left side of the panel
and engine instruments are located on the right side of the instrument
panel. A large color multifunction display is located between the flight
instruments and the engine instruments. Temperature controls are
located on the right side below the engine instruments. The SR20
　
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