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When the Panel selector button is pushed, both butterfly valves are
closed providing maximum airflow to the instrument panel and armrest
eyeball outlets. Pressing the Panel-Foot selector button opens the
cabin floor butterfly valve allowing airflow to the rear seat foot warmer
diffusers and the front seat outlets mounted to the underside of each
kickplate. Selecting Panel-Foot-Windshield button opens the
windshield diffuser butterfly valve which permits shared airflow to the
defrosting mechanism and cabin floor outlets. When the Windshield
selector button is pushed the cabin floor butterfly valve is closed
providing maximum airflow to the windshield diffuser.
Temperature Selection
The temperature selector is electrically linked to the hot and cold air
valves. Rotating the selector simultaneously opens and closes the two
valves, permitting hot and cold air to mix and enter the distribution
system. Rotating the selector clockwise, permits warmer air to enter
the system - counterclockwise, cooler air.
On aircraft with the optional Air Conditioning System installed, when
the air conditioning button (snowflake) is pushed, the valve on the
firewall completely closes and the air-conditioner is activated. When
recirculation button is pushed, the fresh air valve completely closes
and cabin air is recirculated to provide for maximum air conditioning
operation. When the air conditioning system is on and the temperature
selector is rotated to the full cool position, recirculating mode can be
activated to provide maximum cabin cooling. Air conditioning or
recirculating mode is not available when the airflow fan selector is in
the “0” position. Recirculating mode is not available unless the air
conditioning system is operating.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-63
Stall Warning System
The airplane is equipped with an electro-pneumatic stall warning
system to provide audible warning of an approach to aerodynamic
stall. The system consists of an inlet in the leading edge of the right
wing, a pressure switch and associated plumbing, and Serials 3026
thru 3409, a piezo-ceramic horn behind the instrument panel or,
Serials 3410 & subs, the avionics system aural warning system.
As the airplane approaches a stall, the low pressure on the upper
surface of the wings moves forward around the leading edge of the
wings. As the low pressure area passes over the stall warning inlet, a
slight negative pressure is sensed by the pressure switch. The
pressure switch then provides a signal to cause the warning horn to
sound, the red STALL warning CAS annuncation to illuminate, and, if
engaged, the autopilot system to disconnect.
The warning sounds at approximately 5 knots above stall with full flaps
and power off in wings level flight and at slightly greater margins in
turning and accelerated flight.
The system operates on 28 VDC supplied though the 2-amp STALL
WARNING circuit breaker on the ESS BUS 2.
Preflight Check
With battery power on, the stall warning system preflight check is
accomplished as follows:
Stall warning system preflight check:
1. Use small suction cup and apply suction. A sound from the
warning horn will confirm that the system is operative.
March 2010
7-64 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Pitot-Static System
The Pitot-Static system consists of a single heated Pitot tube mounted
on the left wing and dual static ports mounted in the fuselage. The
Pitot heat is pilot controlled through a panel-mounted switch. An
internally mounted alternate static pressure source provides backup
static pressure should that the primary static source becomes blocked.
Water traps with drains, under the floor in the cabin, are installed at
each Pitot and static line low point to collect any moisture that enters
the system. The traps should be drained at the annual inspection and
when water in the system is known or suspected.
Pitot Heat Switch
The heated Pitot system consists of a heating element in the Pitot
tube, a rocker switch labeled PITOT HEAT, and associated wiring. The
switch and circuit breaker are located on the left side of the switch and
control panel. When the Pitot heat switch is turned on, the element in
the Pitot tube is heated electrically to maintain proper operation in
possible icing conditions. The Pitot heat system operates on 28 VDC
supplied through the 7.5-amp PITOT HEAT circuit breaker on the
NON-ESSENTIAL BUS.
Pitot Heat Annunciation
Illumination of the PITOT HEAT Caution indicates that the Pitot Heat
　
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本文鏈接地址：西銳20飛機信息手冊 SR22 AIRPLANE INFORMATION MANUAL 2979(73)