AIRCRAFT ICE CUBES PROTECTION SYSTEM
DESCRIPTION AND OPERATION OF 4 AIRCRAFT ICE PROTECTION PROGRAM
(With reference to A330 Airplane as proven above)
1 ) WING ANTI-ICING employing hot air bleed from pneumatic systems (red color)
2 . ENGINE ANTI-ICING using hot air hemorrhage from engine HP compressor (red color)
3. PROBE HEATING electrically controlled heating put on Pitot, Static and TAT probes
some. WINDOW HEATING SYSTEM electrically controlled heating on habitacle windows
WING ANTI-ICE SAFEGUARD
The Wing Anti-ice safety system is designed normally to get flight procedure only, and during icing state when needed heat is supplied by pneumatic program to the 4 outboard slats to raise the temperature. Hemorrhage air comes to each wing through two Wing Anti Ice (WAI) valves on each wing part left and right.
The air can be sprayed thru piccolo pipes on the leading edges and exhausted overboard.
This Side anti-icing is usually controlled by the team using a push-button selector in the cockpit the control panel turning IN or OFF position. Habitacle indications as well available to the staff when it is obtainable and also launched faulty.
WING ANTI-ICE OPERATION
ENGINE ANTI-ICE PROTECTION
The engine anti-icing is not ON all the time on earth or inflight conditions. Engine air intake ice safeguard protects the engine during operation in ambient topping or arctic conditions. Heat bled via high pressure converter example by third level is used to heat the air intake lip. Hot air comes through an engine air absorption anti-ice device.
The system can be turn ON when needed using the individual engine push-button switch pertaining to engine anti-ice control ON or AWAY position. Signals will be available for the cr...
... boost the surroundings pressure simply by compression and high pressure atmosphere goes through the Secondary warmth exchanger for further cooling applying ram air flow.
The air from the Secondary high temperature exchanger now expands throughout the ACM Generator side which usually brings the temperature straight down between a couple of to 10 degree Centigrade after development at Turbine exit.
Water or water collected can be separated through Water Separator before it truly is delivered in the cabin surroundings conditioned manifold.
Temperature control valve is utilized to set the temperature on the Turbine wall plug by allowing for hot air hemorrhage to mix with too much cold temperature for further dangerous the ACM outlet heat.
This cool air by air plenum is allocated into the cottage ducts with further cutting off or heat mixing setting a comfortable temperatures for traveling inside the vacation cabin.
Airbus Training Manual