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points.
Aileron control motion is generated through the pilot’s control yokes by
rotating the yokes in pivoting bearing carriages. Push rods link the
pivoting carriages to a centrally located pulley sector. A single cable
system runs from the sector to beneath the cabin floor and aft of the
rear spar. From there, the cables are routed in each wing to a vertical
sector/crank arm that rotates the aileron through a right angle conical
drive arm.
March 2010
Information Manual 7-11
Cirrus Design Section 7
SR20 Airplane Description
SR20_FM07_1462
Figure 7-2
Aileron Control System
March 2010
7-12 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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 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. 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. 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
　
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