INDICATOR - VISUAL, ICING 30-81-21
INSPECTION/CHECK 601 ALL
Inspection/Check of the Lighted 601 ALL
Icing Indicator (16DD)
DETECTOR - ICE 30-81-31
REMOVAL/INSTALLATION 401 401-499,
Removal of the Ice Detector (2DD1, 401 401-499,
2DD2)
Installation of the Ice Detector 404 401-499,
(2DD1, 2DD2)
30-CONTENTS Page 18 Aug 01/05
CES ICE AND RAIN PROTECTION - GENERAL - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
_______
The ice and rain protection system lets the aircraft operate normally in ice
conditions or heavy rain.
Ice protection is given by the use of hot air, or electrical power, to make
the necessary areas of the aircraft hot.
The areas that hot air supplies are:
-
the leading edge of the slats 3, 4 and 5 on each wing
-
the engine air intakes.
The engine bleed air system (Ref. 36-11-00) supplies the hot air to the
anti-ice system.
The items with electrical heaters are:
-
the cockpit windshield and side windows
-
the Total Air Temperature (TAT) probes
-
the Angle of Attack (alpha) probes
-
the Pitot and Static probes of the Air Data System (ADS)
-
the waste-water drain-masts.
Rain is removed from the windshield with windshield wipers.
2. Component Location
__________________
**ON A/C 001-049, 052-099, 101-149, 151-199, 201-299, 301-399,
(Ref. Fig. 001)
**ON A/C 051-051,
(Ref. Fig. 001A)
R **ON A/C 401-499,
R (Ref. Fig. 001B)
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3. System Description__________________
A. Airfoil (Ref. 30-10-00)
The airfoil anti-ice system uses hot air bled from the engine (Ref. 36-11-00) to prevent ice on the slats 3, 4 and 5 leading edge.
(1) Wing Anti-ice (Ref 30-11-00)
(Ref. Fig. 002, 003)
The ice-protection system of the wing leading-edge slats 3, 4, and 5 uses hot air from the engine bleed air system (Ref. 36-11-00). The hot air causes the slats leading edge to become warm which prevents ice. Each engine supplies its related wing.
The anti-ice valve 9DL(10DL) isolates its related wing anti-ice system from the engine bleed air system. The anti-ice valves are electro-pneumatically operated, and, for safety, spring-loaded to the closed position. It is possible to supply the two wings from only one engine bleed-air system. To do this, the crossbleed valve (Ref. 36-12-00) opens to connect the two pneumatic systems.
Lagged ducts connect the anti-ice valve to a telescopic duct at the slat 3. Each of the slats 3, 4 and 5 have a piccolo duct that supplies the hot air (bled from the engine) to the related slat leading edge. The slat 3 piccolo duct is connected to the telescopic duct. The slat 3, 4 and 5 piccolo ducts are connected together by flexible ducts. The bleed air in the slats is then released overboard through the holes in the bottom surface of the slat.
The operation of the anti-ice valve is controlled by the WING pushbutton switch (P/BSW) on the overhead panel 25VU.
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Ice and Rain Protection - Component Location
Figure 001
R 1EFF : 001-049, 052-099, 101-149, 151-199, 1 30-00-00Page 3 1201-299, 301-399, 1Aug 01/05 1 1 1CES 1
Ice and Rain Protection
Figure 001A
R 1EFF : 051-051, 1 30-00-00 Page 4
1 1 Aug 01/05
1 1
1CES 1
R Ice and Rain Protection
R Figure 001B
R 1EFF : 401-499, 1 30-00-00 Page 5
1 1 Aug 01/05
1 1
1CES 1
Wing Ice Protection Figure 002
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Wing Ice Protection - Controls and Indication Figure 003
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B. Air Intakes (Ref. 30-20-00)
The air intakes anti-ice system uses hot air (from the engine HP
compressor) to prevent ice on the engine air intakes.
(1) Engine Air Intake Ice Protection (Ref. 30-21-00)
(Ref. Fig. 004, 005)
The engine air-intake ice protection system uses hot air from the engine HP compressor intermediate stage. The hot air goes through a solenoid operated, butterfly, anti-ice valve, to make the engine intake-lip hot. Each engine has its own protection system and operates independently from the aircraft pneumatic system. If, with the engines running, there is an electrical power failure, the anti-ice valve will automatically open. If there is an anti-ice valve failure (with the aircraft on the ground) it can be manually locked in the open or the closed position.
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