AIRCRAFT ICE PROTECTION SYSTEM
DESCRIPTION AND OPERATION OF FOUR AIRCRAFT ICE PROTECTION SYSTEM
(With reference to A330 Aircraft as shown above)
1. WING ANTI-ICING – using hot air bleed from pneumatic systems (red color)
2. ENGINE ANTI-ICING – using hot air bleed from engine HP compressor (red color)
3. PROBE HEATING – electrically controlled heating applied to Pitot, Static and TAT probes
4. WINDOW HEATING – electrically controlled heating on cockpit windows
WING ANTI-ICE PROTECTION
The Wing Anti-ice protection system is designed normally for flight operation only, and during icing condition when needed hot air is supplied by the pneumatic system to the four outboard slats to raise the temperature. Bleed air is supplied to each wing through two Wing Anti Ice (WAI) valves on each wing side left and right.
The hot air is sprayed thru piccolo tubes on the leading edges and exhausted overboard.
This Wing anti-icing is controlled by the crew using a push-button selector in the cockpit control panel turning ON or OFF position. Cockpit indications will be available to the crew when it is available and also when it is faulty.
WING ANTI-ICE OPERATION
ENGINE ANTI-ICE PROTECTION
The engine anti-icing is not ON all the time on ground or inflight conditions. Engine air intake ice protection protects the engine during operation in ambient icing or snowy conditions. Hot air bled from high pressure compressor example from third stage is used to heat the air intake lip. Hot air is supplied through an engine air intake anti-ice valve.
The system is turn ON when needed using the individual engine push-button switch for engine anti-ice control ON or OFF position. Indications will be available to the cr...
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... boost the air pressure by compression and high pressure air goes through the Secondary heat exchanger for further cooling using ram air.
The air coming from the Secondary heat exchanger now expands through the ACM Turbine side which brings the temperature down between 2 to 10 degree Centigrade after expansion at Turbine exit.
Moisture or water collected is separated thru Water Separator before it is delivered into the cabin air conditioned manifold.
Temperature control valve is used to set the temperature at the Turbine outlet by allowing hot air bleed to mix with too much cold temperature for further regulation of the ACM outlet temperature.
This cold air from air plenum is distributed into the cabin ducts with further trimming or hot air mixing to set a comfortable temperature for passenger inside the cabin.
Works Cited
Airbus Training Manual
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