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SR20 Airplane Description
AIRSPEED
INDICATOR
PRIMARY
FLIGHT DISPLAY
Serials 1005 thru 1336 ,1337
thru 1422 w/o PFD.
Serials 1337 & subs w/ PFD.
SR20_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
March 2010
7-86 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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 1706 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. Use small suction cup and apply suction. A sound from the
warning horn will confirm that the system is operative.
March 2010
Information Manual 7-87
Cirrus Design Section 7
SR20 Airplane Description
Standard Avionics
The following paragraphs and equipment descriptions describe all
standard avionic installations offered for the SR20. The avionics
navigation and communication equipment are mounted in he center
console and are easily accessible from either pilot seat.
For detailed descriptions of specific avionic equipment, operating
procedures, or data for optional avionic equipment, refer to the
equipment manufacturer's pilot's guide and the FAA Approved
Airplane Flight Manual Supplement in Section 9 for specific
information regarding the SR20 installation.
Standard avionics suites are available in the following configurations:
Avionics Configuration 2.0 - Serials 1268 through 1336:
• Single-Axis Autopilot (S-Tec System 20)
• Integrated Audio System with Intercom (Garmin GMA 340)
• Marker Beacon Receiver (Garmin GMA 340)
• One IFR Approach-Certified GPS (Garmin GNS 430) and One
VFR GPS (Garmin GNC 250XL)
• Two VHF Communications (Garmin GNS 430 and Garmin GNC
250XL)
• Single Navigation (VOR/LOC/GS) Receiver (GNS 430)
• Mode C Transponder with Altitude Encoder (Garmin GTX 327)
• Directional Gyro
• Course Deviation Indicator
Avionics Configuration 2.1 - Serials 1268 through 1336:
• Moving Map Display (Avidyne MFD)
• Two-Axis Autopilot (S-Tec System 30)
• Integrated Audio System with Intercom (Garmin GMA 340)
• Marker Beacon Receiver (Garmin GMA 340)
• Two IFR Approach-Certified GPS (Garmin GNS 430 and
Garmin GNS 420)
• Two VHF Communications Transceivers (Garmin GNS 430 and
Garmin GNS 420)
March 2010
7-88 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
• Single Navigation (VOR/LOC/GS) Receiver (GNS 430)
　
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