30-ICE & RAIN

A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

30 ICE & RAIN PROTECTION

This document must be used for training purpose only

Under no circumstances should this document be used as a reference.

It will not be updated.

All rights reserved.No 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 Industrie.

GENERALSystem Presentation (1) 1..........................

WING ICE PROTECTIONSystem Presentation (1) 5..........................ECAM Page Presentation (1) 9.......................System Warnings (3) 11..............................** System Interfaces (3) 13........................System Components (2) 17............................System Components (3) 27............................

ENGINE AIR INTAKE ICE PROTECTION** System Presentation (1) 31......................System Warnings (3) 35..............................** System Interfaces (3) 37........................** System Components (2) 41........................

PROBES ICE PROTECTION** System Presentation (1) 45......................** System Description/Operation (3) 49............System Warnings (3) 53..............................System Components (3) 55............................

WINDOWS ANTI-ICING AND DEFOGGINGSystem Presentation (1) 59.........................** System Description/Operation (3) 63............System Warnings (3) 67..............................System Components (3) 69............................

WINDSHIELD RAIN PROTECTIONWiper System Presentation (1) 73...................** Wiper System Components (2) 77..................** Wiper System Components (3) 81..................** Rain Repellent System Presentation (1) 85......** Rain Repellent System D/O (3) 89................** Rain Repellent System Components (2) 93........** Rain Repellent System Components (3) 97........

DRAIN MAST ICE PROTECTIONSystem Presentation (1) 103........................** CIDS/PTP Utilization (3) 107....................System Components (3) 111..........................

POTABLE/WASTE WATER LINES ANTI-ICESystem Presentation (1) 115........................System Components (3) 119..........................

POTABLE WATER SERVICE PANEL ANTI-ICE** System Description/Operation (3) 127...........

ICE INDICATOR ILLUMINATION** System Presentation (3) 131.....................

DUAL ADVISORY ICE DETECTIONSystem Presentation (1) 135........................System Warnings (3) 139.............................System Interfaces (3) 141..........................System Components (3) 145..........................

_A319/A320/A321 TECHNICAL TRAINING MANUAL30 ICE & RAIN PROTECTIONMECHANICS / ELECTRICS & AVIONICS COURSE

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30 - ICE AND RAIN PROTECTION

30-00-00 GENERAL SYSTEM PRESENTATION

CONTENTS:GeneralSlats and EnginesWindows, Probes, Ports, Water Lines and Drain MastsIce DetectionRain Removal

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GENERAL SYSTEM PRESENTATION

GENERAL

The ICE AND RAIN PROTECTION system permits unrestrictedoperation in icing conditions and heavy rain. Criticalareas of the aircraft are protected by hot air orelectrical heating.

SLATS AND ENGINES

The three outboard leading edge slats of each wing andthe engine air intakes are supplied with hot air.

WINDOWS, PROBES, PORTS, WATER LINES AND DRAIN MASTS

The cockpit windows, the probes, ports, water linesand waste water drain masts are electrically heated.Note that other critical areas of the aircraft likewater service panels, water valves can also be iceprotected (optional systems).

ICE DETECTION

An optional dual advisory ice detection system informsthe crew in case of icing conditions.A visual lighted ice indicator is located in thecentral retainer of the windshield.Icing conditions may be expected when Outside AirTemperature (OAT) or Total Air Temperature (TAT) isbelow 8°C (46.4°F) and there is visible moisture inthe air.

RAIN REMOVAL

Rain is removed from the front windshield panels bywipers and, in heavy rain only, by a rain repellentfluid system.Note that the rain repellent system can be optionallydeactivated.

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GENERAL SYSTEM PRESENTATION



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30-11-00 WING ICE PROTECTION SYSTEMPRESENTATION

CONTENTS:SourcesValvesControlsDuctsUsers

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WING ICE PROTECTION SYSTEM PRESENTATION

SOURCES

Air for wing anti-icing is supplied by the pneumaticsystem.

VALVES

Hot air from the pneumatic system is supplied to eachwing via a pressure control shut-off valve. This valveis electrically controlled to open and pneumaticallyoperated.In case of electrical failure or lack of pressure, thevalve closes.

CONTROLS

The valves are controlled from the cockpit by a WINGANTI ICE pushbutton.On ground and only for test purposes, the WING ANTIICE pushbutton electrically opens the valves for 30seconds.

DUCTS

Air reaches slat 3 through a telescopic duct. It isdistributed to the outboard slats by picollo ducts,interconnected by flexible connections.A restrictor located downstream of the control valveadjusts the airflow. It also limits the flow in caseof a rupture of a distribution duct.

USERS

Only the three outboard slats are protected by the hotanti-icing air.Due to the aerodynamic caracteristics of the wing,slats 1 and 2 do not need to be protected.

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WING ICE PROTECTION SYSTEM PRESENTATIONTMUICE201-P01 LEVEL 1



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30-11-00 WING ICE PROTECTION ECAM PAGEPRESENTATION

CONTENTS:ECAM MEMO DisplayBLEED Page

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WING ICE PROTECTION ECAM PAGE PRESENTATION



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30-11-00 WING ICE PROTECTION SYSTEMWARNINGS

CONTENTS:Wing Anti-Ice Open on GroundLeft or Right Valve OpenWing Anti-Ice System FaultLeft or Right High Pressure

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WING ICE PROTECTION SYSTEM WARNINGS



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30-11-00 WING ICE PROTECTION SYSTEMINTERFACES

CONTENTS:Pushbutton SwitchEngine Interface Unit (EIU)Landing Gear Control and Interface Unit (LGCIU)System Data Acquisition Concentrator (SDAC)Zone Controller

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WING ICE PROTECTION SYSTEM INTERFACES

PUSHBUTTON SWITCH

The wing anti-ice pusbutton switch allows the winganti-ice system to be activated either during flightoperation or during ground test operation for a limitedtime.It also sends the pushbutton switch configuration tothe System Data Acquisition Concentrators and to theEngine Interface Units (EIUs).The wing anti-ice pusbutton switch acquires a discretesignal from the fault relay for the illumination ofthe "FAULT" light, during either valves transit or incase of disagreement between valves position and systemselection or in case of a low pressure detection.

ENGINE INTERFACE UNIT (EIU)

The Engine Interface Units acquire system selectionfor engine power increase according to the bleeddemand.

LANDING GEAR CONTROL AND INTERFACE UNIT (LGCIU)

The Landing Gear Control and Interface Units (LGCIUs)send a shock absorber extended signal to the controlrelay to enable the system control when the aircraftis in flight configuration.

SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)

The System Data Acquisition Concentrators (SDACs)acquire discrete inputs to display system status onECAM warning page, ECAM MEMO page and ECAM BLEED page.

ZONE CONTROLLER

The Zone Controller acquires discrete inputs to monitorthe system and manage the bleed air.It stores failure data of the wing anti-ice system.

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WING ICE PROTECTION SYSTEM INTERFACESTMUIC4001-P01 LEVEL 3



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30-11-00 WING ICE PROTECTION SYSTEMCOMPONENTS

CONTENTS:Wing Anti-Ice Control Valve (HYMATIC)Wing Anti-Ice Control Valve (GRIMES)

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WING ICE PROTECTION SYSTEM COMPONENTS

WING ANTI-ICE CONTROL VALVE (HYMATIC)

This valve is basically installed on A319 and A320.It can be optionally installed on A321.

IDENTIFICATIONFIN : (LH) 9DL, (RH) 10DL

LOCATIONZONE : (LH) 522, (RH) 622

COMPONENT DESCRIPTIONThe wing anti-ice control valve is anelectrically-controlled, pneumatically-operatedvalve.The valve has these primary components :

- an actuator body assembly,- a controller/damper housing assembly,- a valve body/shaft assembly,- a solenoid valve assembly,- a position indicator,- two pressure switches,- two ground test points,- a filter.

The valve controls its outlet pressure at 22.5 psi(1,55 bar).If the pressure increases to 32 psi or decreases to13 psi the related switch gives a "high pressure" or"low pressure" signal.

NOTE: If a failure of the electrical or air supplyoccurs, the butterfly disc always closes.

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WING ICE PROTECTION SYSTEM COMPONENTS - WING ANTI-ICE CONTROL VALVE



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WING ANTI-ICE CONTROL VALVE (HYMATIC)

CUT VIEW (VALVE CLOSED)When the valve is de-energized, thus venting theactuator assembly air supply, the actuator spring movesthe piston to the end of its travel, and the pistonand link assembly rotates the shaft and butterfly discto the closed position. Two microswitches signal thatthe butterfly disc is in the closed position.

CUT VIEW (VALVE OPEN)When the valve is energized, the air pressure isapplied to the controller housing and actuator bodyassemblies. The action on the actuator causes thepiston and link assembly to rotate the shaft andbutterfly disc to an open position. The sensordiaphragm, in the controller housing assembly, opensthe sensor valve against the sensor spring and upstreampressure and allows upstream pressure to vent.Stability of the sensor valve is maintained by anorificed damper diaphragm in the damper housingassembly. The resulting pressure changes the positionof the piston and thereby the shaft and butterfly discto maintain the specified airflow and pressure.

MANUAL LOCKING LEVERIn the event of an anti-ice valve failure, each valvecan be locked in the closed or the open position bymeans of its mechanical locking/indicator lever.




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WING ICE PROTECTION SYSTEM COMPONENTSWING ANTI-ICE CONTROL VALVE - CUT VIEW/MANUAL LOCKING LEVER




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WING ANTI-ICE CONTROL VALVE (OPTIONAL)

This valve is basically installed on A321. It can beoptionally installed on A319 and A320.

IDENTIFICATIONFIN: (LH) 9DL, (RH) 10DL

LOCATIONZONE: (LH) 522, (RH) 622

COMPONENT DESCRIPTIONThe wing anti-ice control valve is anelectrically-controlled, pneumatically-operatedvalve.The valve has these primary components :

- an actuator assembly,- a butterfly control,- a pilot-valve assembly,- a solenoid valve- a valve position microswitch,- two pressure switches,- two ground test connections,- a 40 micron filter.

The valve controls its outlet pressure at 22.5 psi(1,55 bar).If the pressure increases to 30 psi or decreases to14 psi the related pressure switch gives a "highpressure" or "low pressure" signal.

NOTE: If a failure of the electrical or air supplyoccurs, the butterfly valve always closes.




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WING ICE PROTECTION SYSTEM COMPONENTS - WING ANTI-ICE CONTROL VALVE (OPTIONAL)TMUIC1EZZ-P03 LEVEL 2



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WING ANTI-ICE CONTROL VALVE (GRIMES)

CUT VIEWWhen the solenoid valve is energized, the poppet movesand connects the top chamber of the actuator to theatmosphere.In the middle chamber, bleed air pressure from theupstream side of the butterfly causes the actuator rodto move up and open the butterfly valve.When downstream pressure becomes higher than the forceof the main spring of the pilot valve, the needle valvemoves, thus middle and top chamber are interconnected,closing the valve.

MANUAL LOCKING LEVERTwo manual devices can lock the valve in the open orclosed position.One device has a locking screw and a lever.The other device is a plate with a slot.Each device has an indicator to show that the valveis in the open or closed position.




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WING ICE PROTECTION SYSTEM COMPONENTSWING ANTI-ICE CONTROL VALVE (OPTIONAL) - CUT VIEW - MANUAL LOCKING LEVER




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30-11-00 WING ICE PROTECTION SYSTEMCOMPONENTS

CONTENTS:Telescopic Duct

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TELESCOPIC DUCT


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WING ICE PROTECTION SYSTEM COMPONENTS - TELESCOPIC DUCTTMUIC2E01-P01 LEVEL 3



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30-21-00 ENGINE AIR INTAKE ICE PROTECTIONSYSTEM PRESENTATION

CONTENTS:SourceValveControlsUsersECAM PageSelf Examination

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ENGINE AIR INTAKE ICE PROTECTION SYSTEM PRESENTATION

SOURCE

Air is bled from a high pressure compressor stage ofeach engine.

VALVE

For each engine, hot bleed air is ducted via an ON/OFFvalve. In the absence of air pressure, the valve isspring loaded to the closed position.Upon energization of the solenoid, the valve closes.In case of loss of electrical power supply, the valveis fully open provided engine bleed air pressure ishigh enough.

CONTROLS

For each engine, the ON/OFF valve is controlled by apushbutton.When both engine anti-ice valves are open, the CabinZone Controller determines the bleed in demand for theFull Authority Digital Engine Control (FADEC) system.This decreases the EPR limit.

USERS

The engine air intake is protected by its related bleedair, which heats the inlet lip in icing conditions.The hot air is discharged overboard.

ECAM PAGE

If at least one of the engine air intake anti-icesystems is selected ON, a message appears in green onthe ECAM MEMO display.




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ENGINE AIR INTAKE ICE PROTECTION SYSTEM PRESENTATION



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SELF EXAMINATION

What happens in case of loss of electrical powersupply to the engine anti-ice valve ?

A - The valve opens when the engine isstopped.

B - The valve opens when the engine isrunning.

C - The valve closes when the engine isrunning.

What happens in case of insufficient air pressureto the engine anti-ice valve ?

A - The valve closes as it is spring loadedclosed.

B - The valve opens as it is spring loadedopen.

C - Stays as it is.

With both engine anti-ice pushbuttons set to ON,does the EPR limit change ?

A - Yes.B - No.

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30-21-00 ENGINE AIR INTAKE ICE PROTECTIONSYSTEM WARNINGS

CONTENTS:Engine 1 or Engine 2 Valve OpenEngine 1 or Engine 2 Valve Closed

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ENGINE AIR INTAKE ICE PROTECTION SYSTEM WARNINGS



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30-21-00 ENGINE AIR INTAKE ICE PROTECTIONSYSTEM INTERFACES

CONTENTS:Pushbutton SwitchSystem Data Acquisition ConcentratorZone Controller

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ENGINE AIR INTAKE ICE PROTECTION SYSTEM INTERFACES

PUSHBUTTON SWITCH

The pusbutton switch sends a discrete signal to thesolenoid to open or close the valve, this informationis also sent to the System Data AcquisitionConcentrators (SDACs).The "FAULT" light comes on either during valve transitor in case of disagreement between valve position andsystem selection.

SYSTEM DATA ACQUISITION CONCENTRATOR

The SDACs acquire the pusbutton switch configurationand the "FAULT" condition information to display systemstatus on ECAM warning page and ECAM MEMO page.

ZONE CONTROLLER

The Zone Controller acquires the "valve not closed"position information from the valve position switchfor bleed air management.




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30-21-00 ENGINE AIR INTAKE ICE PROTECTIONSYSTEM COMPONENTS

CONTENTS:Engine Anti-Ice Valve

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ENGINE AIR INTAKE ICE PROTECTION SYSTEM COMPONENTS

ENGINE ANTI-ICE VALVE

IDENTIFICATIONFIN : 4000DN


DESCRIPTIONThe engine anti-ice valve is a butterfly shut offvalve of the on/off type.The valve is spring loaded to the closed positionin case of no air pressure.A solenoid allows the valve to :

- close, if energized,- open, if deenergized and upstream motive airpressure is high enough.

CUT VIEWTwo microswitches monitor the OPEN and CLOSE position.

MANUAL LOCKING NUTThe valve can be manually operated from an externalnut connected to the butterfly shaft.In addition, the butterfly can be locked in closed oropen position by means of a pip pin. Visual valveposition is also provided.




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30-31-00 PROBES ICE PROTECTION SYSTEMPRESENTATION

CONTENTS:FunctionControlProbe Heat ComputerCautionSelf Examination

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PROBES ICE PROTECTION SYSTEM PRESENTATION

FUNCTION

The static ports, Angle Of Attack (AOA), pitot andTotal Air Temperature (TAT) probes are electricallyheated to prevent ice formation.The captain, first officer and standby systems areindependent.Each one consists of a Probe Heat Computer (PHC) whichcontrols probe and static port heating.As there are only 2 TAT (CAPT and F/O) probes, PHC 3is not linked to a TAT probe.

CONTROL

Probes and static ports heating comes on automaticallywhen at least one engine is running.It can also be activated by the "PROBE/WINDOW HEAT"pushbutton.On ground, pitot heating is reduced and TAT heatingis cut off.LGCIU (Landing Gear Control and Interface Unit).

PROBE HEAT COMPUTER

Heating monitoring and fault indication areprovided by the related Probe Heat Computer.A probe or a sensor heating failure is sent to theECAM via Air Data Inertial Reference Unit (ADIRU)and Flight Warning Computers (FWCs).The PHC also transmits fault messages to theCentralized Fault Display Interface Unit (CFDIU).

CAUTION

Pulling the Probe Heat Computer (PHC) or EngineInterface Unit (EIU) power supply circuit breakerscauses unwanted heating of the probes and static ports.




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SELF EXAMINATION

When is the TAT probe heated ?A - In flight, not on ground.B - On ground, not in flight.C - In icing conditions only.

When is the pitot probe heated ?A - In flight, not on ground.B - In icing conditions only.C - Normal heating in flight, low heating on

ground.

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30-31-00 PROBES ICE PROTECTION SYSTEMDESCRIPTION AND OPERATION

CONTENTS:GeneralControlLanding Gear Control and Interface Unit (LGCIU)Engine RelaysPower SupplyAir Data Inertial Reference Unit (ADIRU)Centralized Fault Display Interface Unit (CFDIU)

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PROBES ICE PROTECTION SYSTEM DESCRIPTION AND OPERATION

GENERAL

Typical probe heat schematic (see following page) isshown : aircraft on ground and electrically suppliedand system "off".Remind that standby probe heat system has no TATheating.

CONTROL

Probes and static ports heating comes on automaticallywhen at least one engine is running.It can also be activated by the "PROBE/WINDOW HEAT"pushbutton.On ground, pitot heating is reduced and TAT heatingis cut off.


When one of the three control conditions is met, theflight condition enables heating of the TAT sensor andfull wave heating of the pitot probe.

ENGINE RELAYS

OIL LOW PRESSURE AND GROUND relays are energized bythe Engine Interface Unit (EIU) when the related engineis not running.If you have to pull the EIU power supply circuitbreaker, the related ENGINE OIL LOW PRESS AND GROUNDrelays are deenergized, this will cause related probesand static ports to be heated.

POWER SUPPLY

The PHC is supplied with 28 Volts DC.The static ports are supplied with 28 Volts DC ; theAOA sensor, TAT sensor and pitot probe are suppliedwith 115 Volts AC.If you pull the PHC power supplied circuit breaker,the related probes and static ports will be fullyheated.

AIR DATA/INERTIAL REFERENCE UNIT (ADIRU)

In case of a probe heating fault the PHC sends adiscrete output to its respective ADIRU which in turntransmits the failure to the Flight Warning Computers(FWCs).

CENTRALIZED FAULT DISPLAY INTERFACE UNIT (CFDIU)

The CFDIU is connected to the PHC for fault systemtransmission.The PHC is a type 2 system (ARINC 429 output,maintenance test discrete input).

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PROBES ICE PROTECTION SYSTEM DESCRIPTION AND OPERATIONTMUICEY01-P01 LEVEL 3



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30-31-00 PROBES ICE PROTECTION SYSTEMWARNINGS

CONTENTS:Single Probe FailureProbe Heat Computer Failure

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PROBES ICE PROTECTION SYSTEM WARNINGS



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30-31-00 PROBES ICE PROTECTION SYSTEMCOMPONENTS

CONTENTS:Probe Heat Computer

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PROBES ICE PROTECTION SYSTEM COMPONENTS

PROBE HEAT COMPUTER

IDENTIFICATIONFIN : (PHC1) 6DA1, (PHC2) 6DA2, (PHC3) 6DA3

LOCATIONZONE : (PHC1 and PHC3) 121, (PHC2) 122

DESCRIPTIONPHC is a type 2 computer.




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30-42-00 WINDOWS ANTI-ICING AND DEFOGGINGSYSTEM PRESENTATION

CONTENTS:FunctionControlWindow Heat Computer (WHC)CautionSelf Examination

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WINDOWS ANTI-ICING AND DEFOGGING SYSTEMPRESENTATION

FUNCTION

Windshields and side windows are electricallyheated to maintain clear visibility in icing ormisting conditions.The system is made up of two independent systems.Each one includes one Window Heat Computer (WHC),one windshield and two windows (one fixed and onesliding).

CONTROL

Windshield and windows heating comes on automaticallywhen at least one engine is running.It can also be manually activated by the "PROBE/WINDOWHEAT" pushbutton.The windshield heating operates at low power on theground and high power in flight.

WINDOW HEAT COMPUTER (WHC)

Temperature regulation, overheat protection andfault indication are provided by each Window HeatComputer (WHC).In case of a windshield or a window heating fault,the Window Heat Computer (WHC) sends an output toECAM via the System Data Acquisition Concentrator(SDAC).The WHCs also transmit fault messages to theCentralized Fault Display Interface Unit (CFDIU).

CAUTION

Pulling the Engine Interface Unit (EIU) power supplycircuit breakers causes the unwanted heating of thewindshield and the side windows.




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WINDOWS ANTI-ICING AND DEFOGGING SYSTEM PRESENTATIONTMUICE401-P01 LEVEL 1



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SELF EXAMINATION

What happens in case of a WHC failure ?A - The failed WHC connects to the other.B - Both systems are lost.C - The heating of the related side is lost.

What happens when the EIU power supply circuitbreakers are pulled ?

A - Nothing happens.B - The windshield heating is cut off.C - The windshield and windows are heated.

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30-42-00 WINDOWS ANTI-ICING AND DEFOGGINGSYSTEM DESCRIPTION AND OPERATION

CONTENTS:GeneralPower SupplyControlComputerUsersEngine RelaysLanding Gear Control and Interface Unit (LGCIU)System Data Acquisition Concentrator (SDAC)Centralized Fault Display Interface Unit (CFDIU)

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WINDOWS ANTI-ICING AND DEFOGGING SYSTEM DESCRIPTION AND OPERATION

GENERAL

The window and windshield anti-icing and demistingsystem is designed to maintain clear visibility throughthe cockpit front and side windows in icing or mistingconditions.Windshields are de-iced, sliding and fixed windows aredimisted.

POWER SUPPLY

Each WHC, windshield and one side windows have theirown power supply.The WHC is supplied with 28 Volts DC. The windows aresupplied with 115 Volts AC. The windshield is suppliedwith a dual phase of 115 Volts AC.

CONTROL

The heating is cut off when the three ground signalsare sent to the AND logic.The windshield and windows are heated either when oneengine is running or when the PROBE/WINDOW HEATpushbutton is set to "ON".

COMPUTER

Each WHC ensures the monitoring of its system. Itidentifies and memorizes the faulty component.It also incorporates protection against overvoltagedue to lightning strike and to static electricity onthe windows. The WHC provides independent temperatureregulation between 35 and 42°C (95 and 107.6°F).Safety : Heating is cut off if temperature reaches +60or -60°C (140 or -76°F).

USERS

Each window and each windshield comprises a heatingelement and two single loop sensors. One of the twosensors is a spare.

ENGINE RELAYS

OIL LOW PRESSURE AND GROUND relays are energized bythe Engine Interface Unit (EIU) when the related engineis not running.If you have to pull the EIU circuit breakers, therelated ENGINE OIL LOW PRESS AND GROUND relays aredeenergized, this will cause windshield and windowsto be heated.


LGCIUs inputs are used for the two heating levels ofthe windshield.When flight configuration is detected, the windshieldis fully heated by the dual phase.

SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)

SDACs receive two discrete inputs from each WHC, onefor the windshield and one for both windows to informthe crew of a heating fault.

CENTRALIZED FAULT DISPLAY INTERFACE UNIT (CFDIU)

The CFDIU is connected to the WHC for fault systemtransmission.The WHC is a type 2 system (ARINC 429 output,maintenance test discrete input).

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30-42-00 WINDOWS ANTI-ICING AND DEFOGGINGSYSTEM WARNINGS

CONTENTS:Left or Right Windshield FaultLeft or Right Window FaultLeft and Right Windshield Fault

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WINDOWS ANTI-ICING AND DEFOGGING SYSTEM WARNINGS



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30-42-00 WINDOWS ANTI-ICING AND DEFOGGINGSYSTEM COMPONENTS

CONTENTS:Window Heat Computer

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WINDOWS ANTI-ICING AND DEFOGGING SYSTEM COMPONENTS

WINDOW HEAT COMPUTER

IDENTIFICATIONFIN : (WHC1) 2DG1, (WHC2) 2DG2

LOCATIONZONE : (WHC1) 121, (WHC2) 122

DESCRIPTIONWHC is a type 2 computer.




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30-45-00 WINDSHIELD RAIN PROTECTION-WIPERSYSTEM PRESENTATION

CONTENTS:FunctionControlCautionSelf Examination

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WINDSHIELD RAIN PROTECTION-WIPER SYSTEM PRESENTATION

FUNCTION

Rain removal from the windshield is ensured by twoindependent wipers powered by DC motors.The wiper system is designed to work efficiently upto 200 knots.

CONTROL

Each wiper is controlled by a rotary selector locatedon the overhead panel."SLOW" or "FAST" speed can be selected.The selector switch can be optionally equipped withand "INTerMiTtent" position. During intermittentoperation, the DC motor is assisted by a timer.When the selector is set to "OFF", the wiper stops inthe parking position and is lifted off the aircraftstructure, at the bottom part of the windshield.

CAUTION

Do not operate the wipers on a dry windshield.

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WINDSHIELD RAIN PROTECTION-WIPER SYSTEM PRESENTATIONTMUIC21ZZ-P01 LEVEL 1



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SELF EXAMINATION

How is each wiper controlled ?A - By a three or four position rotary

selector.B - By a pushbutton.C - Automatically, depending on the weather

conditions.

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30-45-00 WINDSHIELD RAIN PROTECTION-WIPERSYSTEM COMPONENTS

CONTENTS:Wiper ArmWiper Blade

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WINDSHIELD RAIN PROTECTION-WIPER SYSTEM COMPONENTS

WIPER ARM

IDENTIFICATIONFIN: (LH) 306DM, (RH) 307DM

LOCATIONZONE: 211, 212

SWEEPING PRESSUREThe pressure of the wiper is adjustable thanks to anadjustment bolt.The equivalent force necessary to lift the wiper fromthe windshield surface must be 4.5 daN (10.12 lbf),standard value read on a spring scale.

WIPER BLADE

IDENTIFICATIONFIN: (LH) 304DM, (RH) 305DM


REMOVAL/INSTALLATIONIt is possible to replace the blade without removingthe arm.




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WIPER SYSTEM COMPONENTS - WIPER ARM/BLADE ASSEMBLYTMUIC6E01-P01 LEVEL 2



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TMUIC6E01 LEVEL 2



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30-45-00 WINDSHIELD RAIN PROTECTION-WIPERSYSTEM COMPONENTS

CONTENTS:Motor ConverterWiper Timer (optional)

TMUIC7EZZ LEVEL 3



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WINDSHIELD RAIN PROTECTION-WIPER SYSTEM COMPONENTS

MOTOR CONVERTER

IDENTIFICATIONFIN: (LH) 6DB1, (RH) 6DB2


COMPONENT DESCRIPTIONThe motor/converter assembly provides the sweepingangle via the arm/blade assembly. It is also used tostow the wiper arm when the system is switched off.The motor can be replaced without dismantling thecomplete assembly.

WIPER TIMER (OPTIONAL)

Wiper timers are installed to operate the optionalINTerMiTtent function of the wipers.

IDENTIFICATIONFIN: (LH) 7DB1, (RH) 7DB2





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WIPER SYSTEM COMPONENTS - MOTOR CONVERTER ASSEMBLY - WIPER TIMER (OPTIONAL)TMUIC7EZZ-P01 LEVEL 3



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TMUIC7EZZ LEVEL 3



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30-45-00 WINDSHIELD RAIN PROTECTION-RAINREPELLENT SYSTEM PRESENTATION

CONTENTS:FunctionControlCautionSelf Examination

TMUIC2205 LEVEL 1



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WINDSHIELD RAIN PROTECTION-RAIN REPELLENT SYSTEM PRESENTATION

FUNCTION

In heavy rain conditions, a rain repellent liquid,stored in a pressurized bottle, may be sprayed on thewindshield to improve visibility.The spray nozzles are permanently purged by air fromcabin hot air supply.

CONTROL

When the rain repellent pushbutton is pressed in, thesolenoid valve opens for a short time.This causes a measured quantity of rain repellentliquid to be sprayed onto the related windshield.To repeat the cycle, the pushbutton must be pressedagain.On ground, the rain repellent system is inhibited whenboth engines are shut down.

CAUTION

The rain repellent liquid is very corrosive.So do not use rain repellent liquid on a dry windshield.In event of inadvertent application, wash at theearliest opportunity.




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WINDSHIELD RAIN PROTECTION-RAIN REPELLENT SYSTEM PRESENTATIONTMUIC2205-P01 LEVEL 1



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SELF EXAMINATION

When is the rain repellent system inhibited ?A - In flight.B - On ground.C - On ground when the engines are shut down.

What should be done in case of inadvertentapplication ?

A - Wash at the earliest opportunity.B - Wash at the next overhaul.C - No action is necessary.

TMUIC2205 LEVEL 1



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30-45-00 WINDSHIELD RAIN PROTECTION-RAINREPELLENT SYSTEM DESCRIPTION ANDOPERATION

CONTENTS:GeneralRain Repellent CircuitPurge CircuitOperationSelf Examination

TMUICE605 LEVEL 3



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WINDSHIELD RAIN PROTECTION-RAIN REPELLENT SYSTEM DESCRIPTION AND OPERATION

GENERAL

The system is designed to improve visibility throughthe windshield in heavy rain, particulary when thewipers are not sufficient.The system operates independently on the captain sideand on the first officer side.

RAIN REPELLENT CIRCUIT

The rain repellent fluid used is of type 3 and ispackage in a nitrogen pressurized can.The can is directly fitted to the rain repellent fluidgage. A purge pushbutton is used when the can isreplaced.A nozzle sprays the rain repellent fluid onto therelated windshield through four orifices.

PURGE CIRCUIT

The spray nozzle lines are permanently purged by airfrom cabin hot air supply.The blow out reservoir works as a pressure accumulator,a decanting reservoir and has a test connection.

OPERATION

Upon actuation of the pushbutton switch, the timecontrolled solenoid valve of the associated sideenables fluid release to the spray nozzle for a presetperiod of timeThe solenoid valve is preset for a period of 0.4 second.To initiate a new cycle, it is necessary to release,then to press the pusbutton switch again. Between eachcycle, the lines are automatically and permanentlypurged by hot air.The pressure indication shows the nitrogen pressurein the bottle. When the needle is in the yellow range,or the can is completly empty, the bottle should bereplaced.




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WINDSHIELD RAIN PROTECTION-RAIN REPELLENT SYSTEM DESCRIPTION AND OPERATIONTMUICE605-P01 LEVEL 3



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SELF EXAMINATION

How long is the spray sequence ?A - 0.4 second.B - 1 second.C - 4 seconds.

Does each side of the system operate independently ?A - Yes.B - No.C - One side can be connected to the other.

TMUICE605 LEVEL 3



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30-45-00 WINDSHIELD RAIN PROTECTION-RAINREPELLENT SYSTEM COMPONENTS

CONTENTS:Fluid CanGauge Assy

TMUIC8E03 LEVEL 2



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WINDSHIELD RAIN PROTECTION-RAIN REPELLENT SYSTEM COMPONENTS

FLUID CAN

IDENTIFICATIONFIN : 1DM

LOCATIONZONE : 211

GROUND CHECKSCheck reading on the pressure gauge, if the pointerappears in the yellow sector, approximately tenapplications of fluid are left in the can.when replacing the can purge the system using the purgepushbutton.

GAUGE ASSY

IDENTIFICATIONFIN : 2DM

LOCATIONZONE : 211




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RAIN REPELLENT SYSTEM COMPONENTS - FLUID CAN - GAUGE ASSYTMUIC8E03-P01 LEVEL 2



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TMUIC8E03 LEVEL 2



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30-45-00 WINDSHIELD RAIN PROTECTION-RAINREPELLENT SYSTEM COMPONENTS

CONTENTS:Blow Out ReservoirSolenoid ValvesCheck ValvesSpray Nozzles

TMUIC9E01 LEVEL 3



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BLOW OUT RESERVOIR

LOCATIONZONE : 121

DESCRIPTIONThe blow out reservoir is connected to the airconditioning system in order to purge the spray nozzlelines after each application of the rain repellentfluid.It constitutes a decantation reservoir in case of fluidor water leakages through the valves.It can also serve as a test connector to check forabsence of clogging of the nozzles, using anappropriate pressurization tool.




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RAIN REPELLENT SYSTEM COMPONENTS - BLOW OUT RESERVOIRTMUIC9E01-P01 LEVEL 3



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SOLENOID VALVES

IDENTIFICATIONFIN : (LH) 3DB1, (RH) 3DB2

LOCATIONZONE : 211, 212

DESCRIPTIONThe solenoid valve is normally closed.Upon energization, the valve controls the quantity ofrain repellent fluid released to the nozzles by meansof an incorporated electronic timing device.

CHECK VALVES

IDENTIFICATIONFIN : (LH) 3DM, (RH) 4DM


DESCRIPTIONEach purge check valve is designed to prevent fluidto flow to the rain repellent blow out reservoir.

SPRAY NOZZLES





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RAIN REPELLENT SYSTEM COMPONENTS - SOLENOID VALVES - CHECK VALVES - SPRAY NOZZLESTMUIC9E01-P02 LEVEL 3



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TMUIC9E01 LEVEL 3



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30-71-00 DRAIN MAST ICE PROTECTION SYSTEMPRESENTATION

GeneralControl SupplyUsersControl UnitMonitoringTestSelf Examination

TMUICEJ02 LEVEL 1



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DRAIN MAST ICE PROTECTION SYSTEMPRESENTATION

GENERAL

The waste water from the galley and lavatorycompartment wash basins is dumped overboard throughdrain masts.

CONTROL SUPPLY

To protect drain masts against ice formation,electrical heating, through an automaticallycontrolled system, is provided when the aircraft iselectrically supplied.

USERS

The flexible heater foil, bonded on the drain masttube, is temperature regulated via a sensor and poweredby the drain mast heating Control Unit.The AC POWER supply line, within the drain mast, isprovided with a thermal switch opening at 57°C (135°F).It will regulate the temperature in case of normaltemperature control failure.

CONTROL UNIT

The Control Unit regulates the temperature of the drainmast tube. The correct operation of the system ismonitored by the BITE function of the Control Unit.Each Control Unit regulates the heating temperatureof the associated drain mast tube between 5°C (40°F)and 15°C (59°F).

MONITORING

The system status is sent to the CabinIntercommunication Data System (CIDS) for indicationon the Forward Attendant Panel (FAP) and theProgramming and Test Panel (PTP).The failure of the heater (HTR) or Control Unit (CU)is indicated on the FAP (CIDS CAUTION light), on thePTP and on the front face of the Control Unit (HTR andCU lights).The drain mast data is stored in the Centralized FaultDisplay Interface Unit (CFDIU).

TEST

To perform a complete test of the drain mast system,two tests must be carried out,one from the Programming and Test Panel (PTP), and thesecond on each Control Unit.If test is satisfactory :- on the PTP, the message "DRAIN MAST TEST OK" isdisplayed,- on the front face of the Control Unit, HTR and CUlights are on as long as the associated TEST pushbuttonis pressed in.

TMUICEJ02-T01 LEVEL 1



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DRAIN MAST ICE PROTECTION SYSTEM PRESENTATIONTMUICEJ02-P01 LEVEL 1



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SELF EXAMINATION

How do you perform a complete test of the drainmast heating system ?

A - From PTP.B - From test pushbutton of the Control Unit.C - Both.

TMUICEJ02 LEVEL 1



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30-71-00 DRAIN MAST ICEPROTECTION-CIDS-PTP UTILIZATION

CONTENTS:Drain Mast Ice Protection-PTP Utilization

TMUICEL01 LEVEL 3



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DRAIN MAST ICE PROTECTION-CIDS-PTP UTILIZATION

SYSTEM STATUS

DRAINMAST FAILIn our example, a failure has been detected on thedrain mast ice protection system.

TMUICEL01-T01 LEVEL 3



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TMUICEL01-P01 LEVEL 3

DRAIN MAST ICE PROTECTION-CIDS-PTP UTILIZATION



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DRAIN MAST ICE PROTECTION-CIDS-PTP UTILIZATIONTMUICEL01-P02 LEVEL 3



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30-71-00 DRAIN MAST ICE PROTECTION SYSTEMCOMPONENTS

CONTENTS:Drain MastControl Unit

TMUICAE02 LEVEL 3



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DRAIN MAST ICE PROTECTION SYSTEM COMPONENTS

DRAIN MAST

IDENTIFICATIONFIN : (FWD) 4DU, (AFT) 14DU


CONTROL UNIT

IDENTIFICATIONFIN : (FWD) 5DU, (AFT) 15DU


TMUICAE02-T01 LEVEL 3



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DRAIN MAST ICE PROTECTION SYSTEM COMPONENTS - DRAIN MAST - CONTROL UNITTMUICAE02-P01 LEVEL 3



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TMUICAE02 LEVEL 3



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30-70-00 POTABLE/WASTE WATER LINESANTI-ICE SYSTEM PRESENTATION

CONTENTS:GeneralControl SupplyControl UnitTest

TMUICEN01 LEVEL 1



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POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM PRESENTATION

GENERAL

The potable and waste water lines in section 13 and14 are insulated and electrically heated to preventice formation in or around the water lines.The system comprises a Control Unit and heaterassemblies associated to two sensors.

CONTROL SUPPLY

Each system operates as soon as the aircraft iselectrically supplied.

CONTROL UNIT

Each Control Unit regulates the temperature range ofeach group of heater assemblies via their respectivesensor.The heating temperature is regulated between 6oC(42.8oF) and 10oC (50oF).

TEST

A manual test of the system is available via apushbutton located on the Control Unit.On the front face of the Control Unit, two green "OK"LEDs come on if the test is satisfactory.

TMUICEN01-T01 LEVEL 1



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POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM PRESENTATIONTMUICEN01-P01 LEVEL 1



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TMUICEN01 LEVEL 1



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30-70-00 POTABLE/WASTE WATER LINESANTI-ICE SYSTEM COMPONENTS

CONTENTS:Control UnitWaste Water HeaterWaste Water SensorPotable Water HeaterPotable Water Sensor

TMUIC1N01 LEVEL 3



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POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM COMPONENTS

CONTROL UNIT

IDENTIFICATIONFIN : 3DW

LOCATIONZONE : 132

DESCRIPTIONThe mechanical pushbutton must be pressed in forremoval/installation of the Control Unit.

TMUIC1N01-T01 LEVEL 3



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TMUIC1N01-P01 LEVEL 3

POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM COMPONENTS - CONTROL UNIT



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WASTE WATER HEATER

IDENTIFICATIONFIN : 41DU, 42DU

LOCATIONZONE : 131

WASTE WATER SENSOR

IDENTIFICATIONFIN : 40DU

LOCATIONZONE : 131




UFD4200


POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM COMPONENTSWASTE WATER HEATER - WASTE WATER SENSOR




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POTABLE WATER HEATER

IDENTIFICATIONFIN : 4DW, 9DW, 16DW

LOCATIONZONE : 131

POTABLE WATER SENSOR

IDENTIFICATIONFIN : 10DW

LOCATIONZONE : 131




UFD4200


POTABLE/WASTE WATER LINES ANTI-ICE SYSTEM COMPONENTSPOTABLE WATER HEATER - POTABLE WATER SENSOR




UFD4200



TMUIC1N01 LEVEL 3



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30-72-00 POTABLE WATER SERVICE PANELANTI-ICE SYSTEMDESCRIPTION/OPERATION

CONTENTS:GeneralControl SupplyTemperature Regulation

TMUICEO02 LEVEL 3

EFFECTIVITY 30-72-00 Page 1Dec 31/95


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POTABLE WATER SERVICE PANEL ANTI-ICE SYSTEM DESCRIPTION/OPERATION

GENERAL

The fill/drain nipple at the potable water servicepanel is electrically heated to prevent ice formation.

CONTROL SUPPLY

The system operates as soon as the aircraft iselectrically supplied.

TEMPERATURE REGULATION

A thermostat controls the heating and the heater hasan overheat protection.Approximate heating operation is between 6°C (43°F) and13°C (55°F).Overheat Protection : 110°C (230°F).

TMUICEO02-T01 LEVEL 3



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POTABLE WATER SERVICE PANEL ANTI-ICE SYSTEM DESCRIPTION/OPERATIONTMUICEO02-P01 LEVEL 3



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TMUICEO02 LEVEL 3



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30-81-00 ICE INDICATOR ILLUMINATIONSYSTEM PRESENTATION

CONTENTS:GeneralIce IndicatorControl

TMUIC6001 LEVEL 3



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ICE INDICATOR ILLUMINATION SYSTEM PRESENTATION

GENERAL

A visual ice indicator is fitted in the centralretainer of the windshield. It can be illuminated toappreciate the icing conditions at night or indarkness.

ICE INDICATOR

The illuminated ice indicator consists of a titaniumpart with openings, a transparent cover and a LightEmitting Diode.

IDENTIFICATIONFIN: 16DD

CONTROL

The indicator illumination LED is supplied with 28VDCand controlled by the ICE IND & STBY COMPASS switch.




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ICE INDICATOR ILLUMINATION SYSTEM PRESENTATIONTMUIC6001-P01 LEVEL 3



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TMUIC6001 LEVEL 3



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30-81-00 DUAL ADVISORY ICE DETECTIONSYSTEM PRESENTATION

CONTENTS:FunctionDetectionMessagesMonitoringSelf Examination

TMUIC3001 LEVEL 1

EFFECTIVITY 30-81-00 Page 1Jun 30/94


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DUAL ADVISORY ICE DETECTION SYSTEM PRESENTATION

FUNCTION

The purpose of the dual advisory ice detection systemis to provide :

- better detection of icing conditions,- fuel saving by cutting off the hot air bleedfor the anti-ice systems when the latter areno longer necessary.

The dual advisory ice detection system is made of twoice detectors installed on the aircraft skin anddirectly connected to the Flight Warning Computer (FWC)to send warning messages to the crew on the Engine andWarning Display.

DETECTION

Two levels of detection are provided :- "ICE DETECTED" corresponding to an elementarydetection,

- "SEVERE ICE DETECTED" corresponding to 7successive elementary detections.

The ice detection system is operating at electricalpower up and sends warning messages in flight, above1500 feet and when TAT is below 8°C, even with one icedetector faulty.

MESSAGES

The ice detectors generate three different discretesignals :

- "ICE DETECTED" signal when engine air intakeanti-ice is necessary,

- "SEVERE ICE DETECTED" signal when wing anti-iceis necessary,

- FAULT signal when the two ice detectors arefaulty.

MONITORING

Each ice detector is provided with a BITE function forcontinuous monitoring.The FAULT signals are also sent to the System DataAcquisition Concentrator (SDAC) and to the CentralizedFault Display Interface Unit (CFDIU).




UFD4200



DUAL ADVISORY ICE DETECTION SYSTEM PRESENTATION



UFD4200


SELF EXAMINATION

How many levels of ice detection are provided ?A - Two.B - Three.C - Seven.

When is the ice detection system inhibited ?A - At last engine shut down.B - At electrical power off.C - On ground, below 1500 feet or TAT < 8°C.

TMUIC3001 LEVEL 1



UFD4200



30-81-00 DUAL ADVISORY ICE DETECTIONSYSTEM WARNINGS

CONTENTS:Ice DetectedSevere Ice DetectedIce Detect Fault

TMUIC3201 LEVEL 3



UFD4200



DUAL ADVISORY ICE DETECTION SYSTEM WARNINGS



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30-81-00 DUAL ADVISORY ICE DETECTIONSYSTEM INTERFACES

CONTENTS:FWCsSDACsCFDIUWing Anti-Ice Relays

TMUIC3301 LEVEL 3



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DUAL ADVISORY ICE DETECTION SYSTEM INTERFACES

FWCs

Each ice detector sends "ICE" and "SEVERITY" signalsto Flight Warning Computers 1 and 2 respectively incase of an elementary ice detection or 7 elementaryice detections.This in order to display class 1 warning messages onthe ECAM warning display. These messages can berespectively inhibited by engine or wing anti-iceselection.

SDACs

Each ice detector sends a "FAULT" signal to SystemData Acquisition Concentrators 1 and 2 in case offailure during either power up, MCDU or in operationtests.A class 1 failure message is displayed on the ECAMwarning display in case of dual ice detector failure.

CFDIU

Each ice detector sends a "FAULT" signal to theCentralized Fault Display Interface Unit in case offailure during either power up, MCDU or in operationtests.A class 2 fault message is displayed on the MCDUANTI-ICE ICE DETECTOR 1 or 2 system page in case ofice detector failure.

WING ANTI-ICE RELAYS

When wing anti-ice valves are controlled to open, twoground signals are sent to the ice detectors in orderto reset the ice detection counter and cut off the"SEVERITY" signal.




UFD4200



DUAL ADVISORY ICE DETECTION SYSTEM INTERFACES



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TMUIC3301 LEVEL 3



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30-81-31 DUAL ADVISORY ICE DETECTIONSYSTEM COMPONENTS

CONTENTS:Ice Detectors

TMUIC3401 LEVEL 3



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DUAL ADVISORY ICE DETECTION SYSTEM COMPONENTS

ICE DETECTORS

IDENTIFICATIONFIN: (LH) 2DD1, (RH) 2DD2

LOCATIONZONE: 121

DESCRIPTIONThe probe consists of a magnetostrictive nickel alloytube. In addition, the strut also contains the driveand feedback coils and probe heaters, and the probebiaising magnetic.The microcomputer section consists of a 8035microcomputer, 27C32 EPROM and an interface latch.




UFD4200



DUAL ADVISORY ICE DETECTION SYSTEM COMPONENTS - ICE DETECTORS



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TMUIC3401 LEVEL 3



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Documents

30-ICE & RAIN