曝光台 注意防骗
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changes.
Manual tank selection mode is selected by pressing the ANTI-ICE
softkey to access control of the LEFT and RIGHT tanks. In manual
mode, a light blue box is displayed around the selected tank, gallons
remaining, and the selected Anti-Ice System mode. Pressing AUTO
returns the system to automatic tank selection mode. In the case of an
electronic display failure (backup mode), fluid quantity is displayed
along the LH edge of the PFD.
Refer to the Perspective Integrated Avionics System Pilot’s Guide for
additional information on system annunciation and control.
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Cirrus Design Section 9
SR22 Supplements
LEGEND
1. Anti-Ice System Indication
2. Ice Inspection Lights
3. Pitot and Stall Vane Heat
4. Anti-Ice System ON / OFF Switch
0
1
2
3
4
L
Range 79 NM
R
3.8 2.6
5 7 8
1
5. NORM / HIGH Mode Switch
6. MAX Mode Push Button
7. Pump Backup Switch
8. Wind Shield Push Button
SR22_FM09_2983
Bolster Panel
2 3 4 6
ENGINE ANTI-ICE DCLTR ASSIST FUEL
Anti Ice - TKS
Time Rem (H:MM)
Max 0:31
High 1:03
Norm 2:06
Gal
NOTE
Illustration depicts system
during Auto Tank Mode with
LH and RH tanks ON while
operating in MAX mode.
Figure - 3
System Indication and Switching
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Section 9 Cirrus Design
Supplements SR22
Mode Control
Switches are mounted on the bolster switch panel:
• NORM controls both pumps to operate quarter-time
intermittently, i.e. 30 seconds on, 90 seconds off.
• HIGH controls #1 pump to operate continuously, i.e. two times
the normal flow rate.
• MAX controls both pumps to operate continuously for 2 minutes,
i.e. four times the normal flow rate. Pump setting then reverts to
the mode selected by the ICE PROTECT Mode Switch.
• WINDSHLD controls the windshield pump to operate
continuously for approximately 3 seconds.
• PUMP BKUP is used in the event of a system failure. When
pump backup mode is selected, an alternate circuit by-passes
the pump control unit and supplies power to the #2 metering
pump which in turn operates continuously.
If the system is ON and PUMP BKUP is selected, the #1
metering pump will continue to run (if not failed) and the range
and endurance will decrease, e.g. selection of NORM and
PUMP BKUP will reduce range and endurance as if MAX were
selected.
System Operation
• Caution •
Prolonged operation of the system in clear air, above 15,000
feet MSL and temperatures less than -4 F (-20 C) can result in
“flash” evaporation of water and alcohol from the anti-ice fluid.
This evaporation results in a glycol rich fluid that could
become “gel” like on the wing surface until aircraft enters
precipitation or warmer temperatures.
Upon normal system operation, the metering pumps pull anti-ice fluid
simultaneously from both wing reservoirs into a tee containing two
solenoid valves. The normally open solenoid valves provide automatic
fluid balancing by allowing the system to draw fluid from one or both
reservoirs depending on the relative quantity in each reservoir. The
solenoid will shut off a reservoir when either the float sender or low
level switch senses a low fluid level to prevent air from entering the
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Cirrus Design Section 9
SR22 Supplements
system. A pilot override is also provided to manually select a specific
reservoir via the avionics system.
Both metering pumps are controlled by the pump control unit which
controls the operation of the windshield pump and both metering
pumps when NORMAL, MAX, HIGH, and/or WINDSHLD modes are
selected by the pilot via bolster switch panel. The selected operating
mode is annunciated on the avionics system as well as an integral
LED indicator adjacent to the selected switch within the bolster switch
panel. In the event of a pump control unit failure, the pump control unit
may be by-passed by selecting the PUMP BKUP mode on the bolster
switch panel.
From the solenoids, the fluid continues through an in-line strainer and
then a flow transducer which provides fluid flow rate to the avionics
system before it reaches the pumps. At the pump outlets, the fluid
passes through a high pressure switch and then two in-line filters. The
switch location is intended to send a high pressure signal to the
annunciation system in the event of a clogged filter(s). The fluid then
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(112)
