曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

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
Revision A7
7-84 P/N 13772-001
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. Use small suction cup and apply suction. A sound from the
warning horn will confirm that the system is operative.
Revision A9
P/N 13772-001 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.
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 SR22 installation.
Standard avionics suites are available in the following configurations:
Avionics Configuration A - Serials 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD:
• 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)
• Single Navigation (VOR/LOC/GS) Receiver (GNS 430)
• Mode C Transponder with Altitude Encoder (Garmin GTX 327)
• Horizontal Situation Indicator
• Course Deviation Indicator
Avionics Configuration B - Serials 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD:
• Moving Map Display (Avidyne MFD)
• Two-Axis Autopilot (S-Tec System 55X)
• Integrated Audio System with Intercom (Garmin GMA 340)
• Marker Beacon Receiver (Garmin GMA 340)
• Two IFR Approach-Certified GPS (Garmin GNS 430)
Revision A7
7-86 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
• Two VHF Communications Transceivers (Garmin GNS 430)
• Two Navigation (VOR/LOC/GS) Receiver (GNS 430)
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：CIRRUS DESIGN SR22西銳22飛行員操作手冊(cè)和飛機(jī)飛行手冊(cè)(84)