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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. Pitot heat should be used only when
required. The Pitot heat system operates on 28 VDC supplied through
the 7.5-amp PITOT HEAT/COOLING FAN circuit breaker on the Non-
Essential Bus.
Pitot Heat Light
Illumination of the amber PITOT HEAT caution light indicates that the
Pitot Heat switch is in the 'on' position and the Pitot heater is not
receiving electrical current. A current sensor on the Pitot heater power
supply wire provides current sensing. The PITOT HEAT warning light
operates on 28 VDC supplied through the 2-amp ANNUN / ENGINE
INST circuit breaker on the Essential Bus.
June 2007
Information Manual 7-83
Cirrus Design Section 7
SR22 Airplane Description
AIRSPEED
INDICATOR
Serials 0002 thru 0434 ,0435
thru 0820 w/o PFD.
Serials 0435 & subs w/ PFD.
PRIMARY
FLIGHT DISPLAY
SR22_FM07_1013D
PITOT MAST
STATIC
BUTTONS
PITOT-STATIC
WATER TRAPS
ALTERNATE
STATIC
AIR SOURCE
VERTICAL SPEED
INDICATOR ALTIMETER
ALTITUDE
TRANSDUCER
(OPTIONAL)
ALTITUDE
ENCODER
ANNUNCIATOR
PITOT
HEAT
LOGIC
CURRENT
SENSOR
HEATER
7.5A
PITOT
HEAT
CB PITOT HEAT SW
Figure 7-16
Pitot-Static System Schematic
June 2007
7-84 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
Alternate Static Source
An alternate static pressure source valve is installed on the switch and
control panel to the right of the pilot's leg. This valve supplies static
pressure from inside the cabin instead of the external static port. If
erroneous instrument readings are suspected due to water or ice in
the pressure line going to the standard external static pressure source,
the alternate static source valve should be turned on. Pressures within
the cabin will vary with open heater/vents. Whenever the alternate
static pressure source is selected, refer to Section 5 airspeed
calibration and altitude for corrections to be applied.
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 a piezoceramic
horn behind the instrument panel. 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 sense inlet, a slight negative
pressure is sensed by the pressure switch. The pressure switch
completes a ground circuit causing the warning horn to sound, and
Serials 2044 and subsequent; the autopilot system to disconnect. The
warning horn provides a 94dB continuous 2800 Hz tone. 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 Essential Bus.
With battery power on, the stall warning system preflight check is
accomplished as follows:
Stall warning system preflight check:
1. Place a clean handkerchief over the vent opening.
2. Use mouth or small suction cup and apply suction. A sound from
the warning horn will confirm that the system is operative.
June 2007
Information Manual 7-85
Cirrus Design Section 7
SR22 Airplane Description
Standard Avionics
The following paragraphs and equipment descriptions describe all
standard avionic installations offered for the SR22. The avionics
navigation and communication equipment are mounted in the center
console and are easily accessible from either pilot seat.
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(79)
