Airbus 30 A300 A310 Ice and Rain

ATA 30 Ice and Rain Protection

MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 30 A300/A310

Ice and Rain Protection System - General The Ice and Rain Protection System permits aircraft operation without restriction caused by icing or heavy rain conditions.

Electrically Heated Area(s): -

Aircraft Ice Pro tection is provided by heating of critical areas using Hot Air or Electrical Power so urces.

-

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

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) for defogging 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 Bleed Air may be used as an alternate source for Wing Anti-Ice. For Electrical Heating, the electrical power is supplied by AC BUS 1, AC NORM BUS and DC ESS BUS. The Rain Removal System removes rain from the LH and RH Front Windshields that is achieved by windshield wipers. SYSTEM DEACTIVATED at the present time (Heavy rain only, by the Rain Repellent Fluid System.)


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Ice and Rain Protection - General Arrangement

A300 SHOWN


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A300/A310 A300/A31 0 Wing Anti-Ice System DESCRIPTION

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

Ice Protection System for the wings is ensured by heating the leading edge of the Center Slats (Slat Number 2)(Outboard Half) and the leading edge 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 15,000 feet), is ducted in each wing from the fixed leading edge supply duct into the outer slat through a telescopic tube.

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

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

The Wing Anti-Ice Valves will CLOSE automatically if: Either Engine FIRE Handle is pulled while the AIR BLEED X-FEED X-FEED valve is CLOSED The Main Landing Gear Shock Absorbers (Struts) are compressed (Weight on Wheels)

•

•

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


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

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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 means of a Time Delay Relay which limits the Anti-Ice Valve opening time to 10 seconds during the Test Operation of the system..

ATA 30 A300/A310

A310 Wing Anti-Ice System - Component Location


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A300/A310 A300/A31 0 Wing Anti-Ice System DESCRIPTION Ice Protection System for the wings is ensured by heating the leading edge of the Center Slats (Slat Number 2)(Outboard Half) and the leading edge 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 15,000 feet), is ducted in each wing from the fixed leading edge supply duct into the outer slat through a telescopic tube. The Hot Bleed Air is then distributed along this slat by a piccolo tube and also into the Center Slat piccolo tube by a flexible connection across the slats gap. Finally the Hot Bleed Air, after heating the concerned slats, exhausts overboard through vent holes distributed along the slat rear skin. Each wing is equipped with two Anti-Ice Shutoff Valves (Solenoid Controlled and Pneumatically Operated) (NORMAL (NORMAL and and ALTERNATE) ALTERNATE) are arranged in parallel position. • •

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


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A Flow Flow Limiting Limiting Restr Restricto ictorr is fitted fitted down down strea stream m of each each valve. valve. When WING ANTI ICE SUPPLY is switched ON, a signal is passed to the Pneumatic System which increases the hot air temperature at the Precooler outlet 227 Degrees Celsius (441°F) instead of 177 Degrees Celsius (351°F), and if operating on APU. Bleed Air, the APU Bleed Air flow will be increased. If, during operation, an Anti-Ice Valve fails to OPEN the other valve can be selected for operation. Without Electrical or Pneumatic Supply the valves are springloaded to the CLOSED position. The Wing Anti-Ice Valves will CLOSE automatically automatically if: Either Engine FIRE Handle is pulled while the AIR BLEED X-FEED 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 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 means of a Time Delay Relay which limits the Anti-Ice Valve opening time to 10 seconds during the Test Operation of the system..

ATA 30 A300/A310

A300 Wing Anti Ice System - Component Location Location


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Wing Anti-Ice System - RH ECAM Display GENERAL DESCRIPTION NOTE: The RH ECAM Air Bleed Page, which is associated with the AntiIce System, will only be called up during low bleed air pressure conditions.

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


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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. incorporates a Blue ON legend.

The Amber FAULT legend FAULT legend illuminates to indicate: The lower part

•

One of the valves does not CLOSE in the following configurations: 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 ,

•

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

•

•

•

•

•

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

•

2. WING/MODE SEL PUSHBUTTON SWITCH

•

The pushbutton switch provides two functions: Selection Monitoring

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• •

ALTN: ALTN: The selection function is associated associated with the the White White ALTN legend incorporated in the lower part of the Wing/Mode Selection PushButton Switch. The ALTN legend illuminates when the pushbutton switch is released (out) ALTN-Legend ALTN-Legend ON: ON: The Alter Alterna nate te Valve Valves s are are select selected ed ALTN-Legend OFF: The Normal Normal Valves Valves are are sele selecte cted d

•

This function is. inhibited with APU Bleed Air Supply selected in flight. In this case the four valves are selected. FAULT: FAULT: The monitoring function is associated with the Amber Fault legend incorporated in the upper part of the Wing/Mode Selection pushbutton switch. •


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•

One of the valves does not OPEN in the following configurations: ON legend illuminated ON in flight, when the valve is selected 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 warnings are activated. The FAULT legend illuminates ON briefly when the valves are selected OPEN, thus indicating that monitoring is performed through a Five (5)-Second Time Delay, without activating the central warnings. When the FAULT legend illuminates ON with Engine Bleed Air Supply, the Alternate Valves are selected. If the legend remains ON, the system is cut off. When the FAULT legend illuminates ON with APU Bleed Air Supply and Engine Bleed Air Supply, the Alternate Valves area selected. If the legend remains ON, the system is cut off. When the FAULT legend illuminates ON with APU Bleed Air Supply, Engine Bleed Air Supply can be selected. If this is not possible, the system must be cut off.

ATA 30 A300/A310

A300/A310 Wing Anti-Ice Controls - Overhead Panel

Overhead Panel

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Wing Anti-Ice System - Left and Right Wing Valves MFA 1.

LEFT AND RIGHT WING/VALVE FAULT MEMORIZED MEMORIZED FAULT ANNUNCIATOR (MFA) IS ASSOCIATED WITH ONE VALVE

When a valve is not in the selected position, the White VALVE FAULT MFA illuminates and remains illuminated to memorize the failure. 2.

WING VALVES TEST PUSHBUTTON SWITCH The PushButton Switch serves to test the using Wing Anti-Ice System on the ground. The test is performed as follows: a. Start up APU and select APU Bleed Air Supply b. 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 10 seconds. If the FAULT legend on the Wing/Mode Selection PushButton Switc h illuminates ON and remains ON during the first 10 seconds after pressing the Wing Valves Test PushButton Switch, one of the four valves (NORMAL or ALTERNATE) is stuck in the CLOSED or INTERMEDIATE position. If the FAULT legend illuminates ON after the 10 second test period, one valve (NORMAL or ALTERNATE) is stuck in the OPEN or INTERMEDIATE position. The VALVE FAULT MFA associated to the faulty valve illuminates to the ON indication.


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

1

Maintenance Panel

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

opposes the spring load. The valve OPENS if the Lock Assembly is not actuated. When the solenoid is not energized,, inlet pressure enters Chamber “A”. Pressure in Chamber “A” is applied to face “A” of the piston in addition to the spring load which CLOSES the valve. PNEUMATIC CHARACTERISTICS The valve OPENS at a Minimum Pressure of 10 PSIG. The opening time varies between 0.5 and 5 Seconds, depending on the pressure applied.

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


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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 fault occurs within the Wing Anti-Ice Anti-Ice System. Also shown graphically are the various Flight Flight Phases at which the warnings 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.

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•

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

•

OFF (P/B Switch released out): ON light extinguishes. Both valves close.


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FAULT: The light illuminates Amber Color if a valve position does not agree with the PB Switch selection. FAULT light illuminates momentarily during valve transit. If FAULT Light remains illuminated for more than 3 seconds, the ECAM System is activated.

ATA 30 A300/A310

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

1


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A300/A310 Engine Anti-Ice System - Hot Bleed Air Sources DESCRIPTION Engine Ice Protection System is .provided by heating of Nose Cowl Leading Edge (Air Inlet Lip Area) utilizing hot bleed air from the Engine High Pressure (HP) Compressor. Each engine has its own protection system, independent from the Aircraft Pneumatic System. Through an electrically controlled valve for each respective circuit, the Nose Cowl is supplied with hot bleed air from the following:

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

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A310-200 / GE CF6-80A3 / 10

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A31-200/PW JT9D-7R4/15

TH

TH

Stage HP Compressor

Air from the Nos e Cowl Leading Edge is exhausted overboard of the Air Intake 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 the Thrust Control Computer, which decreases the thrust limit relative to ambient conditions, engine operating conditions and anti-ice bleed load. If, while the engine is operating, the electrical power supply, fails, the Nacelle Nose Cowl Anti-Ice Valve OPENS.

Stage HP Compressor (PS4 Air) 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 inlet air pressure is routed through a filter to the reference pressure regulator, passes around the metering valve of the regulator and is sensed on the underside of the regulator diaphragm.

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

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

Visual position indication is provided as well as electrical position indication 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, electrical Probe 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 occurs automatically from LOW Heating level on the Ground to HIGH heating level 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 and vane).

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

Only failure of vane heating will be indicated to crew.

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

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


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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 fault occurs within the Probe Heating System. Also shown graphically are the various Flight Phases at which the warnings 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

2.

Lights illuminate Amber, if: -

CAPT, F/O, STBY P/B SWITCHES Controls the activation of Probe Heating System of their respective circuits.

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 above causes the system may be in the high heating mode due to failure of switchover. If a PITOT light illuminates In Flight, in addition to the above causes the system may be in the LOW heating mode due to failure of switchover.

ON (PB Switch pressed in) Probe heating is activated. Respective PROBE HEAT lights will extinguish.

•

OFF (PB Switch released out) OFF light illuminates White. Probe heating is deactivated. Respective PROBE HEAT lights illuminate Amber.

Illumination of a PROBE HEAT light is accompanied by ECAM Activation. NOTE: The TAT light remains extinguished (OFF) when switched ON on the ground although the probe is not heated.


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PROBE HEATING SYSTEM - Overhead Panel 433VU

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2


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Flight Compartment Window Heat System - General Description DESCRIPTION The Flight Compartment Windows are electrically heated; the Front Windshields for ice protection and defogging, the Side Windows (Sliding and Fixed) for defogging only.

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

Two Anti-Ice Regulators (Windshield Heat Temperature Controllers) control the Front Windshield temperatures to 35°C/42°C. A Temperature Sensor in each windshield signals the actual temperature to the related regulator, which accordingly activates or deactivates the heating power supply from regulator control to the heating elements of Windshield and Side Windows. The two Side Windows heat is not temperature controlled.

Front Windshields are heated on two heating power levels. LOW heating power is used on the Ground. HIGH heating power is used In Flight. Window Heat failure warnings are provided by two FAULT indications and the ECAM Activation. On the Maintenance Panel 472VU, the WINDOW HEAT Test Panel provides Controls and Indications for testing the Heating Power Supply and 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 windshield panels for ice protection and defogging, the two Side Windows (Sliding and Fixed) for defogging only.

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

Two window temperature controllers control the windshield temperatures to 35°C/42°C. A temperature sensor in each windshield panel signals the actual. temperature to the related controller, which accordingly activates or deactivates the heating power supply from the control module of the controller to the heating elements of the windshield and side windows. The windshield may be heated on two heating power levels. LOW heating power is used on the ground. HIGH heating power is for In Flight use only. It is inhibited on the Ground.

Devices for testing the Heating Power Supply and the Protection and Warning circuits are provided on the WINDOW HEAT section of the Maintenance Panel 472VU. A Window Heat Protection Unit is installed between 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 protect the Window Heat Controller against over voltage due to lightning strikes or to the discharge of electrostatic loads accumulated on the windows to the airframe structure. These induced over voltages pass through the Sensor and/or Power Supply wires and the protection consists in reducing 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. •

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

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

3. OK LIGHTS Lights illuminate White during PWR TEST to indicate satisfactory condition of Window Heat Power Supply.

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

4. SAFETY TEST SELECTOR

FAULT: The light illuminates Amber if the related Window Heat System has failed. Heating power is disconnected disconnected and disconnection latched in the event of: •

• •

Front Windshield temperature of less than -60°C or greater than +60°C Failure of Sensing or Regulation Circuit Loss of 28VDC Power Supply to the Regulator

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

The FAULT light will extinguish after: • • •

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

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

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Illumination of the FAULT light is accompanied by ECAM Activation.

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2. PWR TEST PUSHBUTTON •

Activate Activates s test of heating heating power supply supply to Front LH/RH LH/RH Windshie Windshields lds and Side Windows, at the same time for both sides. Before test, the PWR PB Switches on the Overhead Panel 433VU must be selected to ON.


TEMP HI: Front Windshield Windshield temperature temperature in excess of 60°C is simulated

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NEUTRAL: NEUTRAL: Test circuit is de-energized. de-energized. To cancel cancel the warnings warnings and to reset the, system, the PWR PB Switches must be, selected OFF/R (OFF/RESET) after the test. TEMP LO: Front Windshield Windshield temperature less than -60°C is simulated. Indications will will be identical identical to test in TEMP HI position.

ATA 30 A300/A310

Window Heat System - Controls and Warning Logic

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Front Windshield Rain Protection System - Operation DESCRIPTION Rain Removal System System for the Front Windshields is provided by two wipers. Each wiper is driven by a two-speed two-speed electric motor. motor.

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

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

The Rain Repellent System is provided as an aid to improve visibility through Front Windshields in heavy rain. It includes a pressurized bottle, which supplies rain repellent fluid through two time-controlled solenoid valves to the spray nozzles and two pushbuttons for operation; one for each side for the Captain and First Officer (F/O).

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

Timing devices limit the amount of rain repellent fluid for one application cycle. The system is automatically purged by hot air from the Hot Air Supply Manifold of the Air Conditioning System.

Rain Protection System Deactivated on All A300/A310 FedEx Fleet Aircraft MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 30 A300/A310

Windshield Wiper and Rain Repellent System - Schematic

FOR INFORMATIONAL PURPOSES ONLY

Rain Protection System Deactivated on All A300/A310 FedEx Fleet Aircraft


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Windshield Rain Repellent Fluid Can Replacement - General Procedure WARNING: IF SKIN OR EYES ARE ACCIDENTALLY EXPOSED TO RAIN REPELLENT FLUID, FLUSH AREA IMMEDIATELY WITH WATER.

WARNING: THE RAIN REPELLENT SYSTEM MUST NOT BE LEFT WITHOUT A FLUID CAN INSTALLED UNLESS THE SYSTEM BLEED PORT IS OPENED. UNDESIRABLY HIGH PRESSURE CAN DEVELOP IN THE SYSTEM UNDER CERTAIN AMBIENT TEMPERATURE CONDITIONS.

CAUTION: DO NOT ALLOW ANY SPILLED REPELLENT FLUID TO REMAIN IN CONTACT WITH AIRCRAFT STRUCTURE. TO PREVENT CORROSION, ALL REPELLENT FLUID SHOULD BE WASHED OFF WITH SOAP AND WATER WITHIN 2 HOURS.

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

RAIN REPELLENT FLUID CAN REMOVAL

INSTALLATION

A. Connect hose to b leed valve on fluid gauge and place free end in a container.

A. Install seal, then manually screw can on to fluid gauge. B. Close and secure can retaining retaining clamp. clamp.

B. Press Press bleed button button to depressu depressurize rize the the system. system. C. Press bleed button, then check that level of fluid in gauge rises. D. Check Check syste system m for for leaks. leaks.


Rain Protection System Deactivated on All A300/A310 FedEx Fleet Aircraft MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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Windshield Rain Repellent System - Component Location


Rain Protection System Deactivated on All A300/A310 FedEx Fleet Aircraft


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Front Windshield Wiper System - Component Description DESCRIPTION Two wipers are available; one for the Left Windshield Pane (Captain) and one for the Right Windshield Pane (First Officer).

Each wiper system consists of the following components: •

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

• • • •

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


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

ATA 30 A300/A310

Front Windshield Wiper System - Component Location


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Front Windshield Wiper System - Controls and Operation Cycles

1.

CAPTAIN AND FIRST SELECTOR SWITCHES

OFFICER

(F/O)

WIPER

ROTARY SLOW: SLOW: Wipers operate at 75 Cycles/Minute.

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

OFF:

Wiper Wiper oper operat atio ion n sto stops ps in PARKING position. Wipers are out of view for the Flight Deck Crew or Maintenance Crew.

FAST: FAST: Wipers Wipers operate operate at 150 Cycles/ Cycles/Minut Minute. e.


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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 dumped overboard through the Forward Drain Mast located on the forward belly area of the fuselage. To prevent ice formation in or around the drain mast, electrical heating is provided both on the Ground and in the Air (In Flight).

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

The Drain Mast have decals located on each side of the mast to identify the mast is heated and could be HOT (Depending on the System Configuration while in the GROUND MODE) The Drain Mast Mast Circuit Breaker can be pulled to deactivate the mast heating circuit during Ground Parking and/or Maintenance Conditions. The words HOT on each side of the Drain Mast are in Red Color

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

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

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

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


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


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THIS PAGE INTENTIONALLY LEFT BLANK ATA 30 - END COURSE CODE - M540000


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Airbus 30 A300 A310 Ice and Rain

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