曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
2.0 0.30 20.0 2.96
3.0 0.44 21.0 3.11
4.0 0.59 22.0 3.26
5.0 0.74 23.0 3.40
6.0 0.89 24.0 3.55
7.0 1.04 25.0 3.70
8.0 1.18 26.0 3.85
9.0 1.33 27.0 4.00
10.0 1.48 28.0 4.14
11.0 1.63 29.0 4.29
12.0 1.78 30.0 4.44
13.0 1.92 31.0 4.59
14.0 2.07 32.0a
a.3.5 gallon (13.2 L) Capacity
4.74
15.0 2.22
16.0 2.37
17.0 2.52
Revision 07: 05-13-08
P/N 13772-115 9 of 16
Cirrus Design Section 9
SR22 Supplements
Section 7 - System Description
• Caution •
Prolonged operation of the system in clear air, at very high
altitudes, and very cold temperatures can result in “flash”
evaporation of water and alcohol from the de-icing fluid. This
evaporation results in a glycol rich fluid that could become
“gel” like on the wing surface until the aircraft enters cloud or
descends to warmer temperatures.
The Ice Protection System can prevent, and in certain conditions,
remove ice accumulation on the flight surfaces by distributing a thin
film of glycol-based fluid on the wing, horizontal stabilizer, and
propeller. The presence of this fluid lowers the freezing temperature
on the flight surface below that of the ambient precipitation preventing
the formation and adhesion of ice. The system consists of wing and
horizontal stabilizer porous panels, propeller slinger ring, proportioning
units, metering pump, filter, strainer, fluid tank, activation switch, filler
cap, system plumbing, and attaching hardware. The system operates
on 28 VDC supplied through the 5-amp ICE PROTECTION circuit
breaker on Main Bus 1.
De-icing Fluid Tank
Serials before G3 Wing; The de-icing fluid tank is serviced through a
filler located on the LH side of the fuselage, just forward of the
baggage door. The fluid tank, located behind the rear cabin trim panel,
has a total capacity of 2.9 gallon (11.0 L).
Serials with G3 Wing; The de-icing fluid tank is serviced through a filler
located on the upper LH wing. The fluid tank, integral to the LH wing,
has a total capacity of 3.5 gallon (13.2 L). A float type quantity sensor
installed in the de-icing fluid tank supplies quantity level information to
the Engine Airframe Unit.
Switching
Serials 0334 thru 0434; A three-position switch mounted on the center
console panel controls system operation.
Serials 0435 thru 2333, 2335 thru 2419, and 2421 thru 2437; Two
switches are mounted on the bolster panel. The first switch controls
Revision 07: 05-13-08
10 of 16 P/N 13772-115
Section 9 Cirrus Design
Supplements SR22
system operation through ON and OFF positions, the second switch
controls system flow rate through MAXIMUM and NORMAL positions.
Serials with G3 Wing; Two switches are mounted on the bolster panel.
The ON/OFF switch energizes both the priming pump and the
metering pump simultaneously, the second switch controls system
flow rate through MAXIMUM and NORMAL positions.
System Indicating and Annunciation
De-icing fluid quantity indication and CAS System is available only on
Serial Numbers 2979 and subsequent with Cirrus Perspective
Integrated Avionics System installed.
De-icing Fluid Quantity Indicator
De-icing fluid quantity is shown in the lower left corner of the MFD
ENGINE page as both a simulated pressure gage and as a digital
value. The gage pointer sweeps a scale range from 0 to 4 gallon. The
fluid quantity value is displayed in white numerals below the gage.
When the ENGINE page is not active or in the case of an electronic
display failure (backup mode), fluid quantity is displayed along the LH
edge of the PFD.
Fluid quantity is measured by a float type quantity sensor installed in
the de-icing fluid tank. The fuel flow signal is sent to the Engine
Airframe Unit, processed, and transmitted to the Engine Indicating
System for display.
Crew Alerting System (CAS)
De-icing fluid quantity annunciations are displayed in the Crew Alerting
System window located to the right of the altimeter and VSI. The color
of the message text is based on its urgency and required action:
Warning (red) – Immediate crew awareness and action required.
Caution (yellow) – Immediate crew awareness and future corrective
action required.
Advisory (white) – Crew awareness required and subsequent action
may be required.
In combination with the CAS Window, the system issues an audio alert
and an expanded description of the condition is displayed in the Alerts
Window located in the lower RH corner of the PFD.
Revision 07: 05-13-08
P/N 13772-115 11 of 16
Cirrus Design Section 9
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CIRRUS DESIGN SR22西锐22飞行员操作手册和飞机飞行手册(122)
