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autopilot operations are also provided.
The SN3308 detects and warns of abnormal conditions such as
flagged navigation receivers and failed directional gyro or flux detector.
It also monitors its own internal temperature and provides warnings for
over-temperature or loss of cooling conditions.
Redundant circuits paralleled through diodes at the indicator supply
DC electrical power for gyro operation. 28 VDC for the redundant
power circuits is supplied through the 5-amp HSI 1 circuit breaker on
the Essential Bus and 5-amp HSI 2 circuit breaker on Main Bus 2.
Auto Slew automatically turns the course pointer in response to
waypoint sequencing or Direct-To navigation from the GPS receiver
eliminating manual course changes at waypoints and reducing pilot
workload.
Heading and Course Sync allows the pilot, with one button, to
automatically set the heading bug directly to his current heading, or to
set the course pointer directly to a VOR station, simultaneously
centering course deviation. Course and heading command outputs for
autopilot operations are also provided.
Magnetic Compass
A conventional, internally lighted, liquid filled, magnetic compass is
installed on the cabin headliner immediately above the windshield. A
compass correction card is installed with the compass.
Revision A5
7-32 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Wing Flaps
The electrically controlled, single-slotted flaps provide low-speed lift
enhancement. Each flap is manufactured of aluminium and connected
to the wing structure at three hinge points. Rub strips are installed on
the top leading edge of each flap to prevent contact between the flap
and wing flap cove. The flaps are selectively set to three positions: 0%,
50% (16° ) and 100% (32° ) by operating the FLAP control switch. The
FLAP control switch positions the flaps through a motorized linear
actuator mechanically connected to both flaps by a torque tube.
Proximity switches in the actuator limit flap travel to the selected
position and provide position indication. The wing flaps and control
circuits are powered by 28 VDC through the 15-amp FLAPS circuit
breaker on the Non-Essential Bus.
Flap Control Switch
An airfoil-shaped FLAPS control switch is located at the bottom of the
vertical section of the center console. The control switch is marked
and has detents at three positions: UP (0%), 50% and 100% (Down).
The appropriate VFE speed is marked at the Flap 50% and 100%
switch positions. Setting the switch to the desired position will cause
the flaps to extend or retract to the appropriate setting. An indicator
light at each control switch position illuminates when the flaps reach
the selected position. The UP (0%) light is green and the 50% and
FULL (100%) lights are yellow.
Revision A5
P/N 13772-001 7-33
Cirrus Design Section 7
SR22 Airplane Description
SR22_FM07_1460
Figure 7-7
Wing Flaps
Revision A5
7-34 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Landing Gear
Main Gear
The main landing gear are bolted to composite wing structure between
the wing spar and shear web. The landing gear struts are constructed
of composite material for fatigue resistance. The composite
construction is both rugged and maintenance free. The main wheels
and wheel pants are bolted to the struts. Each main gear wheel has a
15 x 6.00 x 6 tire with inner-tube installed. Standard wheel pants are
easily removable to provide access to tires and brakes. Access plugs
in the wheel pants can be removed to allow tire inflation and pressure
checking. Each main gear wheel is equipped with an independent,
hydraulically operated, single-disc type brake.
Nose Gear
The nose gear strut is of tubular steel construction and is attached to
the steel engine mount structure. The nosewheel is free castering and
can turn through an arc of approximately 216 degrees (108 degrees
either side of center). Steering is accomplished by differential
application of individual main gear brakes. The tube-type nosewheel
tire is 5.00 x 5.
Airplane Cabin
Cabin Doors
• Caution •
Serials 0795, 0820 and subsequent: The seat back must be in the fully
upright or the fully reclined position before closing the cabin door. Seat
backs in the forward or break-over position can cause damage to the
door handle or interior panel.
Two large forward hinged doors allow crew and passengers to enter
and exit the cabin. The door handles engage latching pins in the door
frame receptacles at the upper aft and lower aft door perimeter. Gas
　
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