A380-LEVEL I - ATA 30 Ice _ Rain Protection

A380 TECHNICAL TRAINING MANUAL MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL I - ATA 30 Ice & Rain Protection

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A380 TECHNICAL TRAINING MANUAL

LEVEL I - AT ATA 30 ICE & RAIN PROTECTION P ROTECTION Ice and Rain Protection Protection System Introduction Introduction . . . . . . . . . . . . . . . . . . . 2 Wing Ice Protection Protection System System Presentation Presentation . . . . . . . . . . . . . . . . . . . . . 14 Engine Air Intake Ice Ice Protection Protection Presentation Presentation . . . . . . . . . . . . . . . . . . 18 Windshield Windshield Anti-Icin Anti-Icing g / Defogging & Rain Prot Presentation Presentation . . . . . 24 Potable & Waste Water Water Ice Protection Presentation . . . . . . . . . . . . . 32 Ice Detection System Presentation Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . 36

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MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL I - ATA ATA 30 Ice & Rain Protection

TABLE OF CONTENTS

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION General The aircraft can be operated without restriction in icing conditions or heavy rain thanks to the Ice and Rain Protection system. Hot air or electrical heating protect critical areas of the aircraft. The different sub systems of the Ice and Rain Protection system are: - the wing ice protection, - the engine air intake ice protection, - the windshield anti-icing, defogging and rain protection, - the potable and waste water ice protection, - the ice detection.

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ICE IC E AN AND D RAI RAIN N PR PROTE TECT CTIO ION N SYS SYSTE TEM M INT INTR ROD ODUC UCTI TION ON

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Wing Ice Protection During icing conditions the slat Nº4 of each wing is heated with hot air from the pneumatic system through two Wing Anti-Ice Valves Valves (WAIVs). Only one valve is activated when the system is in operation. (for each flight the valve activated changes to avoid hidden failure cases). Two Anti-Ice Control Units (AICUs) control the WAIVs.

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Engine Air Intake Ice Protection Engine air intake ice protection protects the engine during operation in ambient icing conditions. Hot air bled from each engine compressor is used to heat the air intake lip via an engine Anti-Ice Valve. This maintains the inlet duct of the engine free of harmful accumulation of ice. The four valves are controlled by two AICUs.

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Windshield Anti-Icing Anti-Icing - Defogging and Rain Protection Ice protection for windshield and demisting for windows is electrically achieved. Window heat is automatically initiated at first engine start-up. In case of severe icing conditions on ground, automatic operation can be overridden by means of the PROBE/WINDOW HEAT pushbutton switch. The two AICUs, one for each side, monitor and control the heaters, and include an overheat protection. Rain removal from the windshield is done by two independent wipers and in heavy rain, by a rain repellent system. The systems are controlled from the overhead panel. The rain repellent is inhibited on the ground when the engines are stopped.

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Potable and Waste Water Ice Protection An automatic ice protection of the water lines is installed to prevent ice formation. The system is an anti-ice system, but not a de-icing system. The system has 3 subsystems: the waste water ice protection, the water servicing panels heating and the potable water ice protection. Two Ice Protection Control Units (IPCUs) control the electrical heating elements in the related area.

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Ice Detection The purpose of the ice detection system is to give the crew an indication of the icing conditions. In addition the ice detection system automatically controls the Wing Anti Ice and Nacelle Anti Ice systems. The system is composed of two separate ice detectors installed symmetrically on the upper part of the nose part of the fuselage below the rear fixed windows. Two Two external visual ice indicators installed bet ween the two windshields tell the crew that icing conditions are encountered, by formation of ice on lighted visual indicators.

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WING ICE IC E PROTECTION SYSTEM PRESENTA PRESENTATION TION General During icing conditions the slat Nº4 of each wing is heated with hot air from the pneumatic syst em through two redun dant Wing Anti-Ice Valves Valves (WAIVs). (WAIVs). Each valve operates alternatively with a flight cycle. Two Anti-Ice Control Units (AICUs) control the WAIVs.

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WING IC ICE PR PROTECTION SY SYSTEM PR PRESENTATIO N

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WING ICE IC E PROTECTION SYSTEM PRESENTA PRESENTATION TION Operation, Control and Monitoring Hot air is supplied to each wing via two redundant wing anti-ice valves located in each wing leading edge. Hot air is bled in the slat via piccolo tubes. The valves are pneumatically operated and electrically contro lled. In case of loss of electrical power supply or lack of pressure, the valve closes. The valves are controlled by the AICUs and by two pushbuttons on the "ANTI-ICE" control panel, located on the overhead panel. The system operates automatically and in flight only. The "FAUL "FAULT" T" light comes on in case of abnormal operation. On ground and only for test purposes, th e WING pushbutton electrically opens the valves for 30 seconds to prevent heat damage.

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ENGINE AIR INT INTAKE AKE ICE PROTECTION PRESENT PRESEN TATION General The engine air intake anti-ice protection is automatically selected when icing conditions are expected on ground or in flight. The function of the engine air intake ice protection is to supply HP3 air to heat the inlet lip during icing conditions.

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ENGI EN GINE NE AI AIR R INT INTAK AKE E ICE ICE PRO PROTE TECT CTIO ION N PRES PRESEN ENT TATI TION ON

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ENGINE AIR INT INTAKE AKE ICE PROTECTION PRESENT PRESEN TATION Bleed Air Source Hot air used to heat the engine air intake lip is bled from the third stage of the engine High Pressure Compressor (HP3) through an Shut-Off valve (SOV) and a pressu re Regulating Anti Ice Valve Valve (RAIV). For each engine, hot bleed air is ducted via a pressure regulating and a shut-off valve. The SOV is pneumatically operated, electrically controlled via a solenoid and spring loaded open. Upon solenoid energization the SOV will close. When the engine is running and the solenoid is de-energized, the RAIV regulates the air pressure. In case of electrical loss the SOV will open.

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ENGINE AIR INT INTAKE AKE ICE PROTECTION PRESENT PRESEN TATION Control And Indicating The controls and indicating are located on the overhead panel on the anti-ice. For each engine, the Anti-Ice Control Unit (AICU) controls the valves. Automatic Automatic operation of the valves is selected by the AUTO MODE pushbutton. The system can be manually activated by means of the ANTI ICE/ENG pushbuttons (through the AICUs). In case of abnormal operation the pushbutton FAULT light comes on. If at least one of the 4 engine anti-ice systems is on, the indication is displayed on the Centralized Display System (CDS).

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WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROT PRESENTATION Cockpit Windows Anti-Ice Defogging and Rain Protection The anti-icing and defogging system keeps windshield and windows in icing or foggy conditions. This is achieved by electrical heating of the windshield and windows by the Anti-Ice Control Units (AICUs). Rain removal from the windshield is done by two independent wipers and a rain repellent liquid, stored in a pressurized bottle, which may be sprayed onto the windshield to improve visibility.

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WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROT PRESENTATION

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WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROT PRESENTATION Anti-Ice And Defogging Control and Monitoring Heating is automatically initiated at first engine start-up and stops at last engine shut d own. The PROBE / WINDOW HEAT HEAT pushbutton allows manual selection. Monitoring and overheat protection control are achieved by two Anti-Ice Control Units (AICUs), one for each side. For the windshield, there are 2 heating levels, low on ground and normal in flight. For other windows there is only one heating level. Ground/flight information is given by the status of the landing gear. The AICUs control the windshield and windows temperature heating using temperature feedback from the temperature sensors. In case of window heating fault, the AICU sends an output to the Centralized Display System (CDS). The AICUs also transmit fault messages to the Central Maintenance System (CMS).

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WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROT PRESENTATION Wiper System Each windshield has its own individually controlled wiper. A two-speed electrical motor controlled by the WIPER control selector located on the overhead panel, actuates each wiper. SLOW or FAST speed can be selected. When the selector is set to OFF, the wiper stops in the parking position on the lower part of the windshield and is lifted off the aircraft structure. A test of the electrical motors is triggered by the AICUs.

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WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROT PRESENTATION Rain Repellent System The rain repellent system is composed of a pressurized rain repellent can assembly for storage, a gage assembly for pressure indicating, time controlled solenoid valves, 2 spray nozzles and a blow out reservoir, which lets the spray nozzles be purged with hot air. Normally hot air from the trim air system purges the repellent lines and nozzles. When the rain repellent pushbutton is pressed in, the solenoid valve opens for a short time. This causes a measured quantity of rain repellent liquid to be sprayed onto the related windshield on ground, the rain repellent system is inhibited when engines are shut down.

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POTABLE & WASTE WATER ICE PROTECTION PRESENTATION General An automatic electrical water ice protection sys tem is installed to prevent ice formation in the water pipes and drain masts in flight or on ground at freezing temperature. Two Ice Protection Control Units (IPCUs) control and monitor this system.

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POTABLE POT ABLE & WASTE WATER ICE ICE PROTEC PROTECTION TION PRESEN PRESENT TATION

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POTABLE & WASTE WATER ICE PROTECTION PRESENTATION Electrical Heating Elements - Control And Monitoring Electrical heating elements have temperature sensors that are installed on the following components: - water lines, - drain masts, - water service panels, - potable water tank lines and valves, - waste tank drain lines and valves. Electrical heating elements are controlled and monitored by two Ice Protection Control Units (IPCUs). The Ice Protection Control Units turn the electrical heating on or off depending on information from temperature sensors. Programmable temperature thresholds are stored in the IPCUs. IPCU intercommunicates via DEU-B (Decoder/Encoder Unit) with the CIDS directors to monitor and indicate the status of the Ice Protection System.

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ICE DETECTION SYSTEM PRESENTATION General The purpose of the ice detection system is to give to the crew indications of icing conditions. In addition the ice detection system automatically controls the Wing Anti Ice and Nacelle Anti Ice systems. The system is composed of two separate ice detectors installed symmetrically on the upper part of the nose part of the fuselage below the rear fixed windows. Two Two external visual ice indicators installed bet ween the two windshields tell the crew that icing conditions are encountered, by formation of ice on visual indicators.

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ICE DETECTION SYSTEM PRESENTATION

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ICE DETECTION SYSTEM PRESENTATION Operation The ice detection system is made of two ice detectors installed on the skin of the aircraft. They are connected to the Anti-Ice Control Units (AICU). In AUTO mode, the AICUs operate aut omatically the WAI and Engine Air Intake anti ice systems depending on ice detectors information. The ice detection system operates in flight above 1500 Ft and when the Total Air Temperature Temperature (TAT) (TAT) is below 10 degrees Celsius. The system is inhibited on ground.

Indication and Monitoring There are two levels of detection: ICE DETECTED related to an elementary detection and SEVERE ICE DETECTED related to 7 elementary detections. In auto mode, the ICE s ignal activates the Engine Air Intake Ice Protection and the SEVERITY signal activates the Wing Anti-Ice (WAI) through the AICU. This signal is reset (ice detector RESET input) and its processing is inhibited as long as the WAI is activated. These two levels are displayed on the EWD. A fault signal is displayed when the two ice detectors are faulty.

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The ICE IND AND STBY COMPASS switch control the lighting of the lighted icing indicators. 7

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AIRBUS S.A.S. 31707 BLAGNAC cedex, FRANCE STM REFERENCE L0Y06082 MARCH 2006 PRINTED IN FRANCE AIRBUS S.A.S. 2006 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

A380-LEVEL I - ATA 30 Ice _ Rain Protection

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