a380-level i - ata 30 ice _ rain protection

A380 TECHNICAL TRAINING MANUAL

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

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reservedNo part of this manual may be reproduced in any form,

by photostat, microfilm, retrieval system, or any other means,without the prior written permission of AIRBUS S.A.S.

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


TABLE OF CONTENTS Mar 21, 2006Page 1

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ICE AND RAIN PROTECTION SYSTEM INTRODUCTION

General

The aircraft can be operated without restriction in icing conditions orheavy rain thanks to the Ice and Rain Protection system. Hot air orelectrical 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.


ICE AND RAIN PROTECTION SYSTEM INTRODUCTION Mar 15, 2006Page 2


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Wing Ice Protection

During icing conditions the slat Nº4 of each wing is heated with hot airfrom the pneumatic system through two Wing Anti-Ice Valves (WAIVs).Only one valve is activated when the system is in operation. (for eachflight the valve activated changes to avoid hidden failure cases). TwoAnti-Ice Control Units (AICUs) control the WAIVs.




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WING ICE PROTECTION




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Engine Air Intake Ice Protection

Engine air intake ice protection protects the engine during operation inambient icing conditions.Hot air bled from each engine compressor is used to heat the air intakelip via an engine Anti-Ice Valve. This maintains the inlet duct of theengine free of harmful accumulation of ice.The four valves are controlled by two AICUs.




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ENGINE AIR INTAKE ICE PROTECTION




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Windshield Anti-Icing - Defogging and Rain Protection

Ice protection for windshield and demisting for windows is electricallyachieved.Window heat is automatically initiated at first engine start-up.In case of severe icing conditions on ground, automatic operation can beoverridden by means of the PROBE/WINDOW HEAT pushbutton switch.The two AICUs, one for each side, monitor and control the heaters, andinclude an overheat protection.Rain removal from the windshield is done by two independent wipersand 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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WINDSHIELD ANTI-ICING - DEFOGGING AND RAIN PROTECTION




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Potable and Waste Water Ice Protection

An automatic ice protection of the water lines is installed to prevent iceformation. The system is an anti-ice system, but not a de-icing system.The system has 3 subsystems: the waste water ice protection, the waterservicing panels heating and the potable water ice protection.Two Ice Protection Control Units (IPCUs) control the electrical heatingelements in the related area.




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POTABLE AND WASTE WATER ICE PROTECTION




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Ice Detection

The purpose of the ice detection system is to give the crew an indicationof the icing conditions. In addition the ice detection system automaticallycontrols the Wing Anti Ice and Nacelle Anti Ice systems.The system is composed of two separate ice detectors installedsymmetrically on the upper part of the nose part of the fuselage belowthe rear fixed windows.Two external visual ice indicators installed between the two windshieldstell the crew that icing conditions are encountered, by formation of iceon lighted visual indicators.




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ICE DETECTION




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WING ICE PROTECTION SYSTEM PRESENTATION

General

During icing conditions the slat Nº4 of each wing is heated with hot airfrom the pneumatic system through two redundant Wing Anti-Ice Valves(WAIVs). Each valve operates alternatively with a flight cycle. TwoAnti-Ice Control Units (AICUs) control the WAIVs.


WING ICE PROTECTION SYSTEM PRESENTATION Mar 15, 2006Page 14


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WING ICE PROTECTION SYSTEM PRESENTATION

Operation, Control and Monitoring

Hot air is supplied to each wing via two redundant wing anti-ice valveslocated in each wing leading edge. Hot air is bled in the slat via piccolotubes. The valves are pneumatically operated and electrically controlled.In case of loss of electrical power supply or lack of pressure, the valvecloses.The valves are controlled by the AICUs and by two pushbuttons on the"ANTI-ICE" control panel, located on the overhead panel. The systemoperates automatically and in flight only. The "FAULT" light comes onin case of abnormal operation.On ground and only for test purposes, the WING pushbutton electricallyopens the valves for 30 seconds to prevent heat damage.




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OPERATION, CONTROL AND MONITORING




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ENGINE AIR INTAKE ICE PROTECTION PRESENTATION

General

The engine air intake anti-ice protection is automatically selected whenicing conditions are expected on ground or in flight.The function of the engine air intake ice protection is to supply HP3 airto heat the inlet lip during icing conditions.


ENGINE AIR INTAKE ICE PROTECTION PRESENTATION Mar 15, 2006Page 18


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Bleed Air Source

Hot air used to heat the engine air intake lip is bled from the third stageof the engine High Pressure Compressor (HP3) through an Shut-Off valve(SOV) and a pressure Regulating Anti Ice Valve (RAIV).For each engine, hot bleed air is ducted via a pressure regulating and ashut-off valve. The SOV is pneumatically operated, electrically controlledvia a solenoid and spring loaded open. Upon solenoid energization theSOV will close. When the engine is running and the solenoid isde-energized, the RAIV regulates the air pressure. In case of electricalloss the SOV will open.




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BLEED AIR SOURCE




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Control And Indicating

The controls and indicating are located on the overhead panel on theanti-ice. For each engine, the Anti-Ice Control Unit (AICU) controls thevalves. Automatic operation of the valves is selected by the AUTO MODEpushbutton. The system can be manually activated by means of the ANTIICE/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 isdisplayed on the Centralized Display System (CDS).




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CONTROL AND INDICATING




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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 inicing or foggy conditions. This is achieved by electrical heating of thewindshield and windows by the Anti-Ice Control Units (AICUs).Rain removal from the windshield is done by two independent wipersand a rain repellent liquid, stored in a pressurized bottle, which may besprayed onto the windshield to improve visibility.


WINDSHIELD ANTI-ICING / DEFOGGING & RAIN PROTPRESENTATION

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COCKPIT WINDOWS ANTI-ICE DEFOGGING AND RAIN PROTECTION



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Anti-Ice And Defogging Control and Monitoring

Heating is automatically initiated at first engine start-up and stops at lastengine shut down. The PROBE / WINDOW HEAT pushbutton allowsmanual selection.Monitoring and overheat protection control are achieved by two Anti-IceControl Units (AICUs), one for each side. For the windshield, there are2 heating levels, low on ground and normal in flight. For other windowsthere 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 heatingusing temperature feedback from the temperature sensors.In case of window heating fault, the AICU sends an output to theCentralized Display System (CDS).The AICUs also transmit fault messages to the Central MaintenanceSystem (CMS).



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ANTI-ICE AND DEFOGGING CONTROL AND MONITORING



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Wiper System

Each windshield has its own individually controlled wiper.A two-speed electrical motor controlled by the WIPER control selectorlocated on the overhead panel, actuates each wiper. SLOW or FASTspeed can be selected. When the selector is set to OFF, the wiper stopsin the parking position on the lower part of the windshield and is liftedoff the aircraft structure.A test of the electrical motors is triggered by the AICUs.



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WIPER SYSTEM



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Rain Repellent System

The rain repellent system is composed of a pressurized rain repellent canassembly for storage, a gage assembly for pressure indicating, timecontrolled 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 andnozzles. When the rain repellent pushbutton is pressed in, the solenoidvalve opens for a short time. This causes a measured quantity of rainrepellent liquid to be sprayed onto the related windshield on ground, therain repellent system is inhibited when engines are shut down.



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RAIN REPELLENT SYSTEM



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POTABLE & WASTE WATER ICE PROTECTION PRESENTATION

General

An automatic electrical water ice protection system is installed to preventice formation in the water pipes and drain masts in flight or on groundat freezing temperature. Two Ice Protection Control Units (IPCUs) controland monitor this system.


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POTABLE & WASTE WATER ICE PROTECTION PRESENTATION

Electrical Heating Elements - Control And Monitoring

Electrical heating elements have temperature sensors that are installedon 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 IceProtection Control Units (IPCUs). The Ice Protection Control Units turnthe electrical heating on or off depending on information from temperaturesensors. Programmable temperature thresholds are stored in the IPCUs.IPCU intercommunicates via DEU-B (Decoder/Encoder Unit) with theCIDS directors to monitor and indicate the status of the Ice ProtectionSystem.




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ELECTRICAL HEATING ELEMENTS - CONTROL AND MONITORING




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ICE DETECTION SYSTEM PRESENTATION

General

The purpose of the ice detection system is to give to the crew indicationsof icing conditions. In addition the ice detection system automaticallycontrols the Wing Anti Ice and Nacelle Anti Ice systems.The system is composed of two separate ice detectors installedsymmetrically on the upper part of the nose part of the fuselage belowthe rear fixed windows.Two external visual ice indicators installed between the two windshieldstell the crew that icing conditions are encountered, by formation of iceon visual indicators.


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ICE DETECTION SYSTEM PRESENTATION

Operation

The ice detection system is made of two ice detectors installed on theskin of the aircraft. They are connected to the Anti-Ice Control Units(AICU). In AUTO mode, the AICUs operate automatically the WAI andEngine Air Intake anti ice systems depending on ice detectors information.The ice detection system operates in flight above 1500 Ft and when theTotal Air Temperature (TAT) is below 10 degrees Celsius. The systemis inhibited on ground.

Indication and Monitoring

There are two levels of detection: ICE DETECTED related to anelementary detection and SEVERE ICE DETECTED related to 7elementary detections. In auto mode, the ICE signal activates the EngineAir Intake Ice Protection and the SEVERITY signal activates the WingAnti-Ice (WAI) through the AICU. This signal is reset (ice detectorRESET input) and its processing is inhibited as long as the WAI isactivated.These two levels are displayed on the EWD. A fault signal is displayedwhen the two ice detectors are faulty.

Visual Light Indicator

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




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OPERATION ... VISUAL LIGHT INDICATOR




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a380-level i - ata 30 ice _ rain protection

Documents

ice rain protectionice

engine antiice valve

pneumatic system

retrieval system

wing antiice valves

air intakelip

training purposes onlyunder

windshield antiicing