曝光台 注意防骗
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any air between the main metering pumps and the fluid reservoir.
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38 of 44 P/N 13772-134
Section 9 Cirrus Design
Supplements SR22
Figure - 2
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25
LEGEND
1. LH Outbd Panel
2. LH Vent
3. LH Inbd Panel
4. LH Filler Cap
5. LH Level Sender
6. LH Level Switch
7. Windshield Nozzles
8. Slinger Ring
9. 3-Way Valve
10. RH Level Switch
11. RH Inbd Panel
12. RH Level Sender
13. RH Filler Cap
SR22_FM09_2965
14. Stall Transducer
15. RH Vent
16. RH Outbd Panel
17. RH Drain Valve
18. RH Tank Strainer
19. In-Line Strainer
20. Flow Transducer
21. Pump Control Unit
22. Metering Pump 1
23. Metering Pump 2
24. High Pressure Switch
25. Low Pressure Switches
26. RH H Stab Panel
27. RH Elevator Tip Panel
28. V Stab Panel
29. LH Elevator Tip Panel
30. LH H Stab Panel
31. Tail Proportioning Unit
32. Filter Assembly
33. Windshield Pump
34. Solenoid Valve
35. Main Proportioning Unit
36. LH Tank Strainer
37. LH Drain Valve
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System Schematic
Revision 02: 11-17-09
P/N 13772-134 39 of 44
Cirrus Design Section 9
SR22 Supplements
Heated Stall Warning Transducer
The system incorporates a heated stall transducer which provides
dynamic stall speed indications to the pilot in addition to triggering stall
warning. The front plate and vane of the transducer are heated to
prevent ice accumulation from interfering with its operation. The
transducer is mounted on the right wing, on the inboard end of the
outboard porous panel. Stall vane heat is provided when the PITOT
HEAT Switch on the bolster switch panel is switched ON.
The heated stall transducer operates on 28 VDC supplied though the
10-amp STALL VANE HEAT circuit breaker on the NON ESS BUS.
The stall warning computer operates on 28 VDC supplied though the
5-amp STALL WARNING circuit breaker on the ESS BUS 2.
Ice-Inspection Lights
To provide visual verification of icing conditions and confirmation of
fluid flow, ice inspection lights are flush mounted to the RH and LH
fuselage skin just aft of the engine cowling. The bi-directional
inspection lights illuminate the leading edge of the wing and horizontal
stabilizer. Components of the system include the LED light assemblies
and a two-position toggle switch labeled ICE on the Exterior Lights
section of the bolster switch panel.
The ice-inspection lights operates on 28 VDC supplied through the 5-
amp ICE PROTECT A circuit breaker on MAIN BUS 1.
Storage and Distribution
Anti-Ice fluid is stored in two 4.25 gallon (16.1L) sealed wet bays in
each wing formed by two ribs, the main spar, and the forward lateral
main landing gear rib. Approximately 0.50 (1.9L) gallon is unusable.
The total usable fluid capacity is 8.0 gallons (30.2L). The anti-ice fluid
is supplied to the leading edge porous panels and propeller slinger
ring by two positive displacement metering pumps, or in the case of a
metering pump failure, an on-demand backup pump. A separate ondemand
gear pump controls the flow to the windshield spray nozzles.
Revision 02: 11-17-09
40 of 44 P/N 13772-134
Section 9 Cirrus Design
Supplements SR22
System Indicating and Control
Anti-Ice fluid information is displayed as bar graphs and text in the
lower left corner of the MFD ENGINE page. The left (L) bar graph,
marked from 0 to 4 U.S. gallons in 1-gallon increments, indicates left
tank fluid quantity. Fluid quantity is also displayed below the bar graph
in 0.1-gallon increments. The right (R) graph uses an identical scale
for the right tank. Fluid endurance and range predictions computed by
the avionics system and based on the expected nominal flow rate for
the selected mode are also displayed.
Fluid quantity is measured by a float type quantity sensor installed in
the anti-ice fluid tank. The fluid quantity and flow information is sent to
the Engine Airframe Unit, processed, and transmitted to the Engine
Indicating System for display.
When the system is operating in the default, automatic tank selection
mode (AUTO), a white box is centered around the “L” and “R” located
above each bar graph and a light blue box is displayed around the
selected Anti-Ice System mode. During normal operation, the white
box will switch between the left and right tank as the fluid level
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(111)
