Airbus 30 A300 A310 Ice and Rain

MTT M540000 / R3.3 01AUG01MTT M540000 / R3.3 01AUG01For Training Purposes OnlyFor Training Purposes Only ATA 30ATA 30

A300/A310A300/A31030-30-11

ATA 30ATA 30Ice and Rain Ice and Rain

ProtectionProtection


A300/A310A300/A31030-30-22

Ice and Rain Protection System - General

The Ice and Rain Protection System permits aircraft operation withoutrestriction caused by icing or heavy rain conditions.

Aircraft Ice Protection is provided by heating of critical areas using HotAir or Electrical Power sources.

Hot Air Heated Area(s):

- Outboard half of Slat 2 (Center Slat) and entire length of Slat 3(Outer Slats) of each wing

- Engine Air Intakes (Nose Lip area of each Nacelle Nose Cowling,commonly called the D-Duct Air Inlet Lip area

Electrically Heated Area(s):

- Fresh Water (Potable Water) and Lavatory “A” Service Panels- Front Windshields (Captain and First Officer) for ice protection, Two

Side Windows (Left and Right Sliding and Fixed Windows) fordefogging conditions

- External Probes, Pitot Tubes and Static Ports- Lavatory “A” Waste Water Forward Drain Mast

For Hot Air Heating, the Engine(s) 1 and 2 supply bleed air. APU BleedAir may be used as an alternate source for Wing Anti-Ice. For ElectricalHeating, the electrical power is supplied by AC BUS 1, AC NORM BUSand DC ESS BUS.

The Rain Removal System removes rain from the LH and RH FrontWindshields that is achieved by windshield wipers. SYSTEMDEACTIVATED at the present time (Heavy rain only, by the RainRepellent Fluid System.)


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Ice and Rain Protection - General Arrangement

A300 SHOWN


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A300/A310 Wing Anti-Ice SystemDESCRIPTION

Ice Protection System for the wings is ensured by heating the leadingedge of the Center Slats (Slat Number 2)(Outboard Half) and the leadingedge of the Outer Slats (Slat Number 3)(Full Length). Hot Bleed air,supplied by the Engines (Engines 1 and 2) or the APU (Up to 15,000feet), is ducted in each wing from the fixed leading edge supply duct intothe outer slat through a telescopic tube.

The Hot Bleed Air is then distributed along this slat by a piccolo tube andalso into the Center Slat piccolo tube by a flexible connection across theslats gap. Finally the Hot Bleed Air, after heating the concerned slats,exhausts overboard through vent holes distributed along the slat rearskin.

Each wing is equipped with two Anti-Ice Shutoff Valves (SolenoidControlled and Pneumatically Operated) (NORMAL and ALTERNATE)are arranged in parallel position.

• With Engine Bleed Air Supply, only one valve is active, as selected• With APU Bleed Air Supply, both valves are active regardless of

mode selection

A Flow Limiting Restrictor is fitted down stream of each valve.

When WING ANTI ICE SUPPLY is switched ON, a signal is passed tothe Pneumatic System which increases the hot air temperature at thePrecooler outlet 227 Degrees Celsius (441°F) instead of 177 DegreesCelsius (351°F), and if operating on APU. Bleed Air, the APU Bleed Airflow will be increased.

If, during operation, an Anti-Ice Valve fails to OPEN the other valve canbe selected for operation. Without Electrical or Pneumatic Supply thevalves are springloaded to the CLOSED position.

The Wing Anti-Ice Valves will CLOSE automatically if:• Either Engine FIRE Handle is pulled while the AIR BLEED X-FEED

valve is CLOSED• The Main Landing Gear Shock Absorbers (Struts) are compressed

(Weight on Wheels)

On the ground, by the Landing Gear Shock Absorber Torque Links(Weight on Wheels), if the Wing Anti-Ice System is selected ON,overheating of the Slat Number 2 and 3 structure is prevented by meansof a Time Delay Relay which limits the Anti-Ice Valve opening time to 10seconds during the Test Operation of the system..


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A310 Wing Anti-Ice System - Component Location


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A300/A310 Wing Anti-Ice System

DESCRIPTION

Ice Protection System for the wings is ensured by heating the leadingedge of the Center Slats (Slat Number 2)(Outboard Half) and the leadingedge of the Outer Slats (Slat Number 3)(Full Length). Hot Bleed air,supplied by the Engines (Engines 1 and 2) or the APU (Up to 15,000feet), is ducted in each wing from the fixed leading edge supply duct intothe outer slat through a telescopic tube.

The Hot Bleed Air is then distributed along this slat by a piccolo tube andalso into the Center Slat piccolo tube by a flexible connection across theslats gap. Finally the Hot Bleed Air, after heating the concerned slats,exhausts overboard through vent holes distributed along the slat rearskin.Each wing is equipped with two Anti-Ice Shutoff Valves (SolenoidControlled and Pneumatically Operated) (NORMAL and ALTERNATE)are arranged in parallel position.

• With Engine Bleed Air Supply, only one valve is active, as selected• With APU Bleed Air Supply, both valves are active regardless of

mode selection

A Flow Limiting Restrictor is fitted down stream of each valve.

When WING ANTI ICE SUPPLY is switched ON, a signal is passed tothe Pneumatic System which increases the hot air temperature at thePrecooler outlet 227 Degrees Celsius (441°F) instead of 177 DegreesCelsius (351°F), and if operating on APU. Bleed Air, the APU Bleed Airflow will be increased.If, during operation, an Anti-Ice Valve fails to OPEN the other valve canbe selected for operation. Without Electrical or Pneumatic Supply thevalves are springloaded to the CLOSED position.

The Wing Anti-Ice Valves will CLOSE automatically if:• Either Engine FIRE Handle is pulled while the AIR BLEED X-FEED

valve is CLOSED• The Main Landing Gear Shock Absorbers (Struts) are compressed

(Weight on Wheels)

On the ground, by the Landing Gear Relay on the Shock AbsorberTorque Links (Weight on Wheels), if the Wing Anti-Ice System isselected ON, overheating of the Slat Number 2 and 3 structure isprevented by means of a Time Delay Relay which limits the Anti-IceValve opening time to 10 seconds during the Test Operation of thesystem..


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A300 Wing Anti Ice System - Component Location


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Wing Anti-Ice System - RH ECAM Display

GENERAL DESCRIPTION

The Blue Color Anti-Ice indication is illuminated only when the Wing Anti-Ice is selected ON.

NOTE: The RH ECAM Air Bleed Page, which is associated with the Anti-Ice System, will only be called up during low bleed air pressureconditions.


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Wing Anti-Ice System - Schematic


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Wing Anti-Ice System - Wing Bleed Air Supply

1. WING/SUPPLY PUSHBUTTON SWITCH

The PushButton Switch has a control function. The lower partincorporates a Blue ON legend.

If ON legend is illuminated to ON:• In flight, the Wing Anti-Ice System is selected ON for the wings.• On the ground, control is inhibited by the Landing Gear Relays

(Weight on Wheels).

If ON legend is extinguished to OFF:• Valves are held in the CLOSED position

2. WING/MODE SEL PUSHBUTTON SWITCH

The pushbutton switch provides two functions:• Selection• Monitoring

ALTN: The selection function is associated with the White ALTNlegend incorporated in the lower part of the Wing/Mode SelectionPushButton Switch. The ALTN legend illuminates when thepushbutton switch is released (out)

ALTN-Legend ON: The Alternate Valves are selectedALTN-Legend OFF: The Normal Valves are selected

This function is. inhibited with APU Bleed Air Supply selected inflight. In this case the four valves are selected.• FAULT: The monitoring function is associated with the Amber

Fault legend incorporated in the upper part of the Wing/ModeSelection pushbutton switch.

The Amber FAULT legend illuminates to indicate:

• One of the valves does not CLOSE in the followingconfigurations:

• ON legend illuminated OFF• ON legend illuminated ON, on ground, test not selected• ON legend illuminated ON in flight, when the valve is not

selected ,

• One of the valves does not OPEN in the followingconfigurations:

• ON legend illuminated ON in flight, when the valve isselected

• ON legend illuminated ON, on the ground, with test selected,during the first 10 seconds, with APU Bleed Air Supply

• When the FAULT legend illuminates ON, the central warningsare activated. The FAULT legend illuminates ON briefly whenthe valves are selected OPEN, thus indicating that monitoring isperformed through a Five (5)-Second Time Delay, withoutactivating the central warnings.

• When the FAULT legend illuminates ON with Engine Bleed AirSupply, the Alternate Valves are selected. If the legend remainsON, the system is cut off.

• When the FAULT legend illuminates ON with APU Bleed AirSupply and Engine Bleed Air Supply, the Alternate Valves areaselected. If the legend remains ON, the system is cut off.

• When the FAULT legend illuminates ON with APU Bleed AirSupply, Engine Bleed Air Supply can be selected. If this is notpossible, the system must be cut off.


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A300/A310 Wing Anti-Ice Controls - Overhead Panel

Overhead Panel

21


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Wing Anti-Ice System - Left and Right Wing Valves MFA

1. LEFT AND RIGHT WING/VALVE FAULT MEMORIZED FAULTANNUNCIATOR (MFA) IS ASSOCIATED WITH ONE VALVE

When a valve is not in the selected position, the White VALVE FAULTMFA illuminates and remains illuminated to memorize the failure.

2. WING VALVES TEST PUSHBUTTON SWITCH

The PushButton Switch serves to test the using Wing Anti-IceSystem on the ground. The test is performed as follows:a. Start up APU and select APU Bleed Air Supplyb. Select Wing Anti-Ice (ON legend ON)c. Press Wing Valves Test PushButton Switch

The effective valve control on the ground is inhibited during the first 10seconds.

If the FAULT legend on the Wing/Mode Selection PushButton Switchilluminates ON and remains ON during the first 10 seconds afterpressing the Wing Valves Test PushButton Switch, one of the four valves(NORMAL or ALTERNATE) is stuck in the CLOSED or INTERMEDIATEposition.

If the FAULT legend illuminates ON after the 10 second test period, onevalve (NORMAL or ALTERNATE) is stuck in the OPEN orINTERMEDIATE position.

The VALVE FAULT MFA associated to the faulty valve illuminates to theON indication.


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Wing Anti-Ice System - Anti Ice Test Panel - BITE Controls

Maintenance Panel

21

1


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Wing Anti-Ice System - Valve Component

DESCRIPTION

The Wing Anti-Ice Valve is a shut off type valve. The valve is normallyCLOSED. In the absence of electrical signals, the valve closes throughthe action of a spring and pressure in Chamber "A". The valve can belocked in the CLOSED position. The valve position (OPEN or CLOSED)is indicated by position indicator switches used for system monitoring.

OPERATION

When the solenoid is energized, Chamber “A” is vented to ambientpressure at the valve inlet is applied to face “B” of the piston and thus

opposes the spring load. The valve OPENS if the Lock Assembly is notactuated. When the solenoid is not energized,, inlet pressure entersChamber “A”. Pressure in Chamber “A” is applied to face “A” of thepiston in addition to the spring load which CLOSES the valve.

PNEUMATIC CHARACTERISTICS

The valve OPENS at a Minimum Pressure of 10 PSIG. The opening timevaries between 0.5 and 5 Seconds, depending on the pressure applied.


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Wing Anti-Ice System - Valve Schematic


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A300/A310 Wing Anti-Ice System - Warning Logic

Below is depicted the various warnings displayed in the Flight Compartment in the event the shown faultoccurs within the Wing Anti-Ice System. Also shown graphically are the various Flight Phases at which thewarnings will or will not be displayed.


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Wing and Engine Anti-Ice System - Warning Logic


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Engine Air Intake Anti-Ice - Panel 426VU Controls

1. ENG 1 OR ENG 2 P/B SWITCH

Controls Engine Anti-Ice System for the related Engine 1 or 2.

• ON (P/B Switch pressed in): ON light illuminates Blue. Anti-IceValves OPEN. The indication ENG ANTI-ICE is indicated andshown on the LH ECAM MEMO Page.

• OFF (P/B Switch released out): ON light extinguishes. Bothvalves close.

• FAULT: The light illuminates Amber Color if a valve positiondoes not agree with the PB Switch selection. FAULT lightilluminates momentarily during valve transit. If FAULT Lightremains illuminated for more than 3 seconds, the ECAM Systemis activated.


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A300/A310 Engine Anti-Ice Controls - Overhead Panel 426VU

1


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A300/A310 Engine Anti-Ice System - Hot Bleed Air SourcesDESCRIPTION

Engine Ice Protection System is .provided by heating of Nose CowlLeading Edge (Air Inlet Lip Area) utilizing hot bleed air from the EngineHigh Pressure (HP) Compressor. Each engine has its own protectionsystem, independent from the Aircraft Pneumatic System. Through anelectrically controlled valve for each respective circuit, the Nose Cowl issupplied with hot bleed air from the following:

- A300-600/GE CF6-80C2A5F (FADEC)/11TH Stage HP Compressor

- A310-200 / GE CF6-80A3 / 10TH Stage HP Compressor

- A31-200/PW JT9D-7R4/15TH Stage HP Compressor (PS4 Air)

Air from the Nose Cowl Leading Edge is exhausted overboard of the AirIntake through a single port at the bottom of the Nose Cowl Assembly.

When an Nose Cowl Anti-Ice Valve is OPEN, a signal is passed to theThrust Control Computer, which decreases the thrust limit relative toambient conditions, engine operating conditions and anti-ice bleed load.

If, while the engine is operating, the electrical power supply, fails, theNacelle Nose Cowl Anti-Ice Valve OPENS.

Each valve is monitored by a Disagree Position Switch.


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Engine Air Intake Anti-Ice - Schematic


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Nacelle Nose Cowl Air Intake - CF6 Engine Anti-Ice Valve

This is a normally-open valve with solenoid controlled shutoff. Valve inletair pressure is routed through a filter to the reference pressure regulator,passes around the metering valve of the regulator and is sensed on theunderside of the regulator diaphragm.

When this sensed pressure reaches the desired level, the spring force isovercome and the metering valve moves toward the seat to maintain thereference regulator output pressure at a constant level.

Manual override is provided by applying torque to the hexagon shaft androtating in the desired direction to open or close. When the desiredposition has been reached, the spring-loaded detent automatically locksthe shaft.

Visual position indication is provided as well as electrical positionindication at the valve open and close positions.


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Nacelle Nose Cowl Air Intake - GE CF 6 Engine Anti-Ice Valve Component


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Probe Heat System - Ice Protection Components

To prevent the formation of ice on the Air Data System Probes, electricalProbe Heating System is provided for:

• Pitot tubes• Static Ports• Alpha (angle of attack) Probes• TAT (Total Air Temperature) Probes

The system is arranged in three independent channels (CAPT, F/O,STBY). Pitot Tubes have two heating levels. Change over occursautomatically from LOW Heating level on the Ground to HIGH heatinglevel In Flight.


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Probe Heating System - Component Location


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Probe Heating System - Ice Protection Components - Continued

Two parts of the alpha probes (angle of attack) are heated (case andvane).

Only failure of vane heating will be indicated to crew.

To avoid erroneous indications, the TAT probes are not heated on theground.

The TAT probe light will not illuminate on the ground even with thesystem ON.

If probe heat is not selected ON, or if any failure or discrepancy of probeheating occurs, the respective PROBE HEAT lights on the overheadpanel will illuminate.


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Probe Heating System Ice Protection - Monitoring Logic


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Probe Heating System - Warning Logic

Below is depicted the various warnings displayed in the Flight Compartment in the event the shown faultoccurs within the Probe Heating System. Also shown graphically are the various Flight Phases at which thewarnings will or will not be displayed.


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Probe Heat System - Warning Logic


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Probe Heating System - Flight Compartment Controls and Indications

1. TAT, ENG 1 OR. 2, L OR R STAT, PITOT, ALPHA LIGHTS

Lights illuminate Amber, if:

- Respective probe heat circuit not selected ON- Probe Heating Supply failed- Probe Heating Control failed

If a PITOT light illuminates on the Ground, in addition to the abovecauses the system may be in the high heating mode due to failure ofswitchover.

If a PITOT light illuminates In Flight, in addition to the above causesthe system may be in the LOW heating mode due to failure ofswitchover.

Illumination of a PROBE HEAT light is accompanied by ECAMActivation.

NOTE: The TAT light remains extinguished (OFF) when switched ONon the ground although the probe is not heated.

2. CAPT, F/O, STBY P/B SWITCHES

Controls the activation of Probe Heating System of their respectivecircuits.

• ON (PB Switch pressed in)

Probe heating is activated. Respective PROBE HEAT lights willextinguish.

• OFF (PB Switch released out)

OFF light illuminates White. Probe heating is deactivated.Respective PROBE HEAT lights illuminate Amber.


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PROBE HEATING SYSTEM - Overhead Panel 433VU

1

2


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Flight Compartment Window Heat System - General Description

DESCRIPTION

The Flight Compartment Windows are electrically heated; the FrontWindshields for ice protection and defogging, the Side Windows (Slidingand Fixed) for defogging only.

Two Anti-Ice Regulators (Windshield Heat Temperature Controllers)control the Front Windshield temperatures to 35°C/42°C. A TemperatureSensor in each windshield signals the actual temperature to the relatedregulator, which accordingly activates or deactivates the heating powersupply from regulator control to the heating elements of Windshield andSide Windows.

The two Side Windows heat is not temperature controlled.

A Regulator Unit failure results in illuminating the FAULT light on theWINDOW HEAT Panel 433VU.

Front Windshields are heated on two heating power levels. LOW heatingpower is used on the Ground. HIGH heating power is used In Flight.

Window Heat failure warnings are provided by two FAULT indicationsand the ECAM Activation.

On the Maintenance Panel 472VU, the WINDOW HEAT Test Panelprovides Controls and Indications for testing the Heating Power Supplyand for testing the Protection and Warning circuits are installed.


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A300/A310 Window Heat System Regulator (Temperature Controller) - Component Location


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Windshield Windows Anti-Icing and Defogging System - Component Operation

DESCRIPTION

The Flight Compartment windows are electrically heated; the windshieldpanels for ice protection and defogging, the two Side Windows (Slidingand Fixed) for defogging only.

Two window temperature controllers control the windshield temperaturesto 35°C/42°C. A temperature sensor in each windshield panel signals theactual. temperature to the related controller, which accordingly activatesor deactivates the heating power supply from the control module of thecontroller to the heating elements of the windshield and side windows.

The windshield may be heated on two heating power levels. LOWheating power is used on the ground. HIGH heating power is for In Flightuse only. It is inhibited on the Ground.

Illumination of two FAULT legends and activation of the ECAM Systemindicate Window Heat System failure.

Devices for testing the Heating Power Supply and the Protection andWarning circuits are provided on the WINDOW HEAT section of theMaintenance Panel 472VU. A Window Heat Protection Unit is installedbetween the Window Temperature Controller and the windows(Windshield Windows, Sliding and Fixed Side Window ).

Each side is provided with one Protection Unit. The unit serves to protectthe Window Heat Controller against over voltage due to lightning strikesor to the discharge of electrostatic loads accumulated on the windows tothe airframe structure. These induced over voltages pass through theSensor and/or Power Supply wires and the protection consists inreducing the over voltages on each wire.


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Window Heating System - General Schematic


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Window Heating System - Overhead Panel 433VU and Maintenance Panel 472VU Controls

1. PWR L OR it P/B SWITCH

Controls activation of Window Heat System left or right hand sides.

• ON (PB Switch pressed in): Power is supplied to the Anti-IceRegulator. Heating elements in the window panes are supplied,Front and Side windows are heated.

• OFF (PB Switch released out): OFF/R light illuminates White.Window heat system is deactivated.

• FAULT: The light illuminates Amber if the related Window HeatSystem has failed. Heating power is disconnected anddisconnection latched in the event of:

• Front Windshield temperature of less than -60°C or greaterthan +60°C

• Failure of Sensing or Regulation Circuit• Loss of 28VDC Power Supply to the Regulator

The FAULT light will extinguish after:

• Recovery of 28VDC Power Supply to Anti-Ice Regulator• Selection of PWR PB Switch to OFF/R

Illumination of the FAULT light is accompanied by ECAM Activation.

2. PWR TEST PUSHBUTTON

Activates test of heating power supply to Front LH/RH Windshieldsand Side Windows, at the same time for both sides. Before test, thePWR PB Switches on the Overhead Panel 433VU must be selectedto ON.

When the pushbutton is pressed, the TEST OK lights will illuminate ifthe Heating Power Supply is satisfactory. The duration of test islimited by a Time Relay to 10 seconds.

3. OK LIGHTS

Lights illuminate White during PWR TEST to indicate satisfactorycondition of Window Heat Power Supply.

4. SAFETY TEST SELECTOR

Controls test of Temperature Control and Warning Circuits. Beforetest the PWR PB Switches on the Overhead Panel 433VU must beselected ON. The SAFETY TEST selector is springloaded to neutral(Center Position).

• TEMP HI: Front Windshield temperature in excess of 60°C issimulated

• Both FAULT lights illuminate on Overhead Panel 433VU• Heating Power Supply is disconnected• ECAM Activation

• NEUTRAL: Test circuit is de-energized. To cancel the warningsand to reset the, system, the PWR PB Switches must be,selected OFF/R (OFF/RESET) after the test.

• TEMP LO: Front Windshield temperature less than -60°C issimulated. Indications will be identical to test in TEMP HIposition.


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Window Heat System - Controls and Warning Logic

4 3 21


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Front Windshield Rain Protection System - Operation

DESCRIPTION

Rain Removal System for the Front Windshields is provided by twowipers. Each wiper is driven by a two-speed electric motor.

They are controlled by two WIPER Rotary Selectors Switches on theOverhead Panel 429VU; one for the Captain and one for the F/O (FirstOfficer).

The Wiper System has a parking position of the wiper blade with thescraper, just lifted from the window face, to avoid accumulation of sandand scratching of the glass.

SYSTEM DEACTIVATED: FOR INFORMATIONAL PURPOSES ONLYIN THE EVENT THE SYSTEM IS REACTIVATED AT A LATER DATE.

The Rain Repellent System is provided as an aid to improve visibilitythrough Front Windshields in heavy rain.

It includes a pressurized bottle, which supplies rain repellent fluid throughtwo time-controlled solenoid valves to the spray nozzles and twopushbuttons for operation; one for each side for the Captain and FirstOfficer (F/O).

Timing devices limit the amount of rain repellent fluid for one applicationcycle.

The system is automatically purged by hot air from the Hot Air SupplyManifold of the Air Conditioning System.

Rain Protection SystemRain Protection SystemDeactivated on All A300/A310 FedEx Fleet AircraftDeactivated on All A300/A310 FedEx Fleet Aircraft


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Windshield Wiper and Rain Repellent System - Schematic


FOR INFORMATIONAL PURPOSES ONLY


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Windshield Rain Repellent Fluid Can Replacement - General Procedure

WARNING: IF SKIN OR EYES ARE ACCIDENTALLY EXPOSED TORAIN REPELLENT FLUID, FLUSH AREA IMMEDIATELY WITHWATER.

CAUTION: DO NOT ALLOW ANY SPILLED REPELLENT FLUID TOREMAIN IN CONTACT WITH AIRCRAFT STRUCTURE. TO PREVENTCORROSION, ALL REPELLENT FLUID SHOULD BE WASHED OFFWITH SOAP AND WATER WITHIN 2 HOURS.

RAIN REPELLENT FLUID CAN REMOVAL

A. Connect hose to bleed valve on fluid gauge and place free end in acontainer.

B. Press bleed button to depressurize the system.

WARNING: THE RAIN REPELLENT SYSTEM MUST NOT BE LEFTWITHOUT A FLUID CAN INSTALLED UNLESS THE SYSTEM BLEEDPORT IS OPENED. UNDESIRABLY HIGH PRESSURE CAN DEVELOPIN THE SYSTEM UNDER CERTAIN AMBIENT TEMPERATURECONDITIONS.

C. Open clamp securing can to partition. Unscrew and remove can. Alsoremove and discard seal.

INSTALLATION

A. Install seal, then manually screw can onto fluid gauge.

B. Close and secure can retaining clamp.

C. Press bleed button, then check that level of fluid in gauge rises.

D. Check system for leaks.




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Windshield Rain Repellent System - Component Location




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Front Windshield Wiper System - Component Description

DESCRIPTION

Two wipers are available; one for the Left Windshield Pane (Captain) andone for the Right Windshield Pane (First Officer).

The two wipers are independently actuated through two-speed electricmotors controlled by the WIPER Rotary Control Switches located on theFlight Compartment Overhead Panel 429VU.

The wipers have a parking position clear of the area of visibility. Thewiper blades are slightly lifted from the windshield face to avoid sandaccumulation which could cause scratching of the windshield.

Each wiper system consists of the following components:

• Windshield Wiper Motor• Flexible Drive Shaft• Mechanical Converter Unit• Wiper Arm with Wiper Blade• Associated Flight Compartment Controls


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Front Windshield Wiper System - Component Location


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Front Windshield Wiper System - Controls and Operation Cycles

1. CAPTAIN AND FIRST OFFICER (F/O) WIPER ROTARYSELECTOR SWITCHES

The Rotary Selector Switches control the Windshield Wiper Motorson each side of the Left and Right Front Windshields.

FAST: Wipers operate at 150 Cycles/Minute.

SLOW: Wipers operate at 75 Cycles/Minute.

OFF: Wiper operation stops in PARKING position. Wipers areout of view for the Flight Deck Crew or Maintenance Crew.


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Front Windshield Wiper System - Control Panel 429VU

1


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Drain Mast Ice Protection

DESCRIPTION AND OPERATION

Waste water from the Lavatory “A” Wash Basin (Sink) is dumpedoverboard through the Forward Drain Mast located on the forward bellyarea of the fuselage. To prevent ice formation in or around the drainmast, electrical heating is provided both on the Ground and in the Air (InFlight).

The Drain Mast have decals located on each side of the mast to identifythe mast is heated and could be HOT (Depending on the SystemConfiguration while in the GROUND MODE) The Drain Mast CircuitBreaker can be pulled to deactivate the mast heating circuit duringGround Parking and/or Maintenance Conditions. The words HOT oneach side of the Drain Mast are in Red Color

The plumbing system carries waste water from Lavatory “A”Compartment Wash Basin (Sink) to Lower Forward Drain Mast locatedon 'the outer skin of the aircraft.

Lavatory “A” Drain Mast is an electrically heated tube, shrouded by anaerodynamically shaped, cast aluminum fairing.

The Heating Element is rated at 285 Watts. On the Ground it is suppliedwith 28 VAC from an Autotransformer.

In Flight 115 VAC is routed to a Rectifier which supplies the heatingelement with 100 VDC / + 3 VDC.

On the Ground the Heating Element can be operated using 115 VAC fora maximum of Five (5) minutes.


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Lavatory “A” Drain Mast Ice Protection System - Component Location


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ATA 30 - END

COURSE CODE - M540000

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Airbus 30 A300 A310 Ice and Rain

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