Level III - Ata 35 Oxygen

A380 TECHNICAL TRAINING MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

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A380 TECHNICAL TRAINING MANUAL

LEVEL III - ATA 35 OXYGEN Theory System Flight Crew Oxy gen System Description (3) . . . . . . . . . . . . . . . . . . . . 2 Passenger Oxygen System Description (3) . . . . . . . . . . . . . . . . . . . . 10 Oxygen System Maintenan ce (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 Oxygen System Operation, Control & IND (3) . . . . . . . . . . . . . . . . . 22 Oxygen System Component Location (3) . . . . . . . . . . . . . . . . . . . . . 52

MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

TABLEOFCONTENTS

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FLIGHT CREW OXYGEN SYSTEM DESCRIPTION (3) Crew Oxygen Storage The cylinder head has: - A manual, slow-opening ON/OFF valve. The valve is used during the replacement of the cylinder and to isolate the cylinder if there is a leak in the oxygen system - A direct-reading pressure gage that gives an indication of the cylinder high-pressure when the manual valve is open or closed - A switch that senses the position of the manual valve (fully open/not fully open) for the OSCU (Oxygen System Control Unit) monitoring - An overpressure port with a frangible disc to release unwanted HP through the overboard discharge line and indicator. The disc will rupture at a pressure from 177 to 213 bars (2560 to 3085 psig). The pressure reducer/transmitter, which is directly installed on the cylinder, lets: - Decrease the high pressure from the cylinder to the operating pressure, compatible with the distribution circuit - Send an electrical signal in relation to the cylinder pressure - Make the pressure of the LP oxygen safe - Help the replenishment of the cylinder without removal. It has an HP stage and an LP stage. The HP stage includes: - A pressure transducer that sends an electrical signal to the OSCU to give a cylinder pressure indication. - A filling port with a non-return valve that is connected to a thermal compensator and then to a filling line. The pressure transducer signal lets the OSCU operate a continuous

The IOMs are a back up. The OSCU sends discrete signals to the IOMs to maintain essential data shown on the ECAM. The LP stage includes: - A downstream pressure regulator that supplies a pressure of 4.4 bars (63.8166 psi) to 5.5 bars (79.7707 psi) relative to the distribution circuit - A port with a pressure relief valve that limits the LP oxygen to a maximum of 8.6 bars(124.7324 psi) relative. Unwanted pressure flows into the overboard discharge line. The filling line includes - A thermal compensator installed on th e pressure reducer/transmitter. It is a tube with a goo d thermal conductivity. The tube contains an internal component with a large surface area and high thermal inertia. This will prevent dangerous high temperature during the replenishment of the cylinder. The temperature transducer that is installed near the oxygen cylinder, measures the ambient temperature in the area and generates an electrical signal to the OSCU for computation of the temperature compensated pressure in the cylinder. A pressure fill indicator indicates the pressure inside the oxygen cylinder during filling. The pressure fill indicator has a scale with graduation: 0 to 5.9 bars (0 to 85 psig) is orange, 5,9 to 152 bars (85 to 2200 psig) is green. The pressure value displayed on the filling indicator is given by the OSCU and this value is a temperature compensated pressure. The filling indicator is mounted on the Fill panel near to the cargo door.

calculation of the cylinder internal pressure and send data to the CDS for indication on the DOOR/OXYGEN page of the ECAM (Electronic Centralized Aircraft Monitoring) system, to the FWS (Flight Warning System) and the OMS (Onboard Maintenance System), through AFDX (Avionics Full Duplex Switched Ethernet) and ADCN Avionics Communication Network). MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

FLIGHT CREW OXYGEN SYSTEM DESCRIPTION (3)

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CREW OXYGEN STORAGE MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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FLIGHT CREW OXYGEN SYSTEM DESCRIPTION (3) Crew Oxygen Distribution The Low Pressure oxygen-distribution circuit includes: - An electrical LP supply solenoid-valve with a position switch - A mechanical distribution manifold with a test port and a low-LP oxygen switch - An LP supply distribution-line with stainless-steel rigid pipes and flexible hoses - Four full-face quick-donning masks and their stowage boxes (5 optional). The Low Pressure supply valve is installed between the pressure reducer/transmitter and the distribution manifold. A 28VDC signal opens/closes the valve. The valve is opened or closed by a 28VDC electrical signal pulse from th e ESS BUS 417PP. This signal is controlled from the overhead panel, by the OXYGENB/CREW SUPPLY pushbutton switch located on the ICP panel 1211VM. The valve has an integrated electronic circuit that changes the permanent control voltage into a pulse that operates the valve. When there is no pulse, the valve coil is not energized. The valve position agrees with the last control signal, whatever the time between two opposite control signals. A switch sends the valve position to the Oxygen System Control Unit (OSCU) for monitoring and display, through the AFDX and ADCN (IOMs as back up). The function of the LP distribution manifold is to decrease the risk of leaks. It is made to optimize the reliability of the system by decreasing the number of couplings in the LP circuit. The LP distribution-manifold assembly includes:

electrical signal to the OSCU (and through IOM as back up) for the monitoring (REGUL LO PR warning message). Each of the stowage boxes includes an electrical switch, which sends a signal (door closed/ door open). The door closed-signal is sent to the OSCU for monitoring (stowage box status). The door open-signal (mask in use) is sent to the Aircraft Management Unit (AMU) to control the operation of the mask microphone getting the radio communication function.

- A test port that helps the maintenance for the pressure and leak test on the ground. The maximum pressure that can be used at the test port is 10bars (145psig) - A low-pressure switch which senses a too low pressure in the LP distribution circuit (below 3.3 bars (47.8624 psi)). This switch sends an MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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CREW OXYGEN DISTRIBUTION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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FLIGHT CREW OXYGEN SYSTEM DESCRIPTION (3) An oxygen flow indicator is an integral part of the supply valve. When there is an oxygen flow, the indicator blinks.

Crew Oxygen Dispensing Stowage boxes Each of the stowage boxes includes: - A connector for the LP oxygen supply - An electrical plug for the radio connection - A two-flap door which keeps the mask in its housing - A PRESS TO TEST AND RESET button on the left flap of the door - A pneumatic supply valve that operates when the door is open or when the PRESS TO TEST AND RESET button is pushed - A blinker flow meter that flashes when the LP oxygen flows - A pneumatic switch which lets the mask microphone operate and sends an electrical signal (box door closed and system reset) to the OSCU for the system monitoring - An OXY ON flag that makes it possible to see that the mask is supplied. A flexible hose is used to connect the box oxygen valve to the mask. One end includes a quick disconnect connection with a self-sealing coupling avoiding oxygen leakage in case of mask removal. A microphone lead including a quick disconnect device is connected to the relevant mask microphone cables. The two doors on the stowage box will keep the mask in the box. When the left-hand door is opened with the removal of the mask, the oxygen supply valve in the storage box will open. This lets oxygen flow to the mask. Once the left-hand door has been opened and the oxygen flows, a flag OXY ON will appear. This flag will not go out of sight until the supply valve has been closed and reset. The left-hand door of the stowage box has a reset/test control slide. The slide is pressed in the direction of the arrow to reset the oxygen supply valve in the closed position, when the left-hand doo r is closed. It is also pressed in the direction of the arrow to do a test of the oxygen supply without removing the mask from the storage box. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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CREW OXYGEN DISPENSING - STOWAGE BOXES MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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FLIGHT CREW OXYGEN SYSTEM DESCRIPTION (3) Crew Oxygen Dispensing (continued) Crew Oxygen Mask The full-face quick-donning mask is an emergency breathing equipment that gives protection to the flight crew from cockpit depressurization or presence of toxic fumes. The mask gives respiratory and eyes protection. It is donned and operates in less than 5 seconds with its self-inflated harness. The mask includes: - A mask and goggles assembly The mask face piece is full face and gives protection to the eyes, nose and mouth. The mask has a plasti c window with a film which protects the window when the mask is removed from its housing. The film also prevents ice formation on the window during the depressurization. - An inflatable harness The harness keeps the mask and googles assembly on the user head. The harness is made of some elastomere tubes that expand with oxygen action. The mask is stored in its stowage box with the harness deflated. When the mask is removed, the harness inflation control-plate is manually depressed. Then, the pneumatic harness inflates with oxygen pressure. When the harness is inflated, it gets the diameter and rigidity that let it be donned. When the user releases the harness control plate, the harness is depressurized and it keeps the mask tightly against the user face. - A microphone In the distribution valve of the stowage box, a pressure swi tch lets the

- Overpressure manual control. When the N/100% rocker switch is in the N position, the user breathes a mixture of air and oxygen. The position of the air/oxygen mixing aneroid-capsule controls the quantity of external air. This capsule gets the fully closed position at a cabin altitude of 35000 ft (10667.80 m). When the N/100% rocker switch is in the 100% position, the user breathes pure oxygen at all altitudes. Automatic overpressure: From a cabin altitude of 30000 ft. (9143.83 m), the regulator gives oxygen under positive pressure with an overpressure aneroid capsule. This overpressure supplies the minimum necessary oxygen partial pressure if a loss of pressurization occurs during the flight. Emergency function: The overpressure is necessary for the breathing if there is smoke or noxious gas in the cockpit. The user turns the PRESS TO TEST/EMERGENCY knob to get a continuous oxygen overpressure flow. A 100% oxygen selection is necessary to operate this overpressure function (rocker switch in 100% position). In the emergency conditions (smoke or noxious gas in the cockpit), a venting valve lets a small quantity of oxygen go from the mask cavity into the goggle cavity. This increases the pressure into the mask and thus, smoke or fumes cannot go into the mask. The venting system only operates when the overpressure of the regulator operates manually or automatically (cabin altitude above 30000 ft. (9143.83 m)).

microphone operate when the LP oxygen flows in the mask. - A regulator The mask regulator controls the distribution of the oxygen in the mask: - Air/oxygen dilution with altimetric automatic control - 100% pure oxygen - 100% pure oxygen with overpressure MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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CREW OXYGEN DISPENSING - CREW OXYGEN MASK MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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PASSENGER OXYGEN SYSTEM DESCRIPTION (3) Passenger Oxygen Storage The storage circuit includes: - Oxygen cylinders - Reducer/transmitters - Thermal compensators - A temperature transducer - A filling line - An overboard discharge line The cylinder head has: - A manual, slow-opening ON/OFF valve. The valve is used during the replacement of the cylinder and to isolate the cylinder if there is a leak in the oxygen system - A direct-reading pressure gage that gives an indication of the cylinder high-pressure when the manual valve is open or closed - A switch that senses the position of the manual valve (fully open/not fully open) for the OSCU (Oxygen System Control Unit) monitoring. If the cylinder is fully open the according valid pressure value is taken into account for calculating the average pressure displayed on the ECAM. - An overpressure port with a frangible disc to release unwanted high pressure through the overboard discharge line. The disc will rupture at a pressure from 177 to 213 bars (2560 to 3085 psig). A pressure reducer/transmitter is installed on each oxygen cylinder. It has: - A high-pressure inlet port from the cylinder - A high-pressure fill inlet with a non-return valve - A low-pressure outlet with a non-return valve

A pressure relief valve is installed between the intermediate pressure lin e and the overboard discharge line. If the pressure goes above 11.7 bars (169.69 PSI) the valve will open and release the pressure through the discharge line. - A thermal compensator prevents dangerous increase of the temperature when the cylinders are filling. It is installed in the fill lines immediately in front of the pressure reducer. It has a tube with an internal part with a large surface area and a high thermal inertia with high thermal coupling tube. A fill port has a flow restrictor to make sure that the pressure increases safety, and a filter to prevent contamination. An external cap has a safety chain A temperature transducer is installed adjacent to the oxygen cylinder assemblies. It received its power from the OSCU and sends a temperature signal. It has an operation range of -15 deg. C (5 deg. F) to 70 deg C (158 deg. F). The OSCU (Oxygen System Control Unit) receives signals from the temperature transducer and from the pressure reducer/transmitters. The OSCU sends a signal of the arithmetic mean pressure- temperature adjusted to the fill panel indicator and to the passenger oxygen display on the ECAM (Electronic Centralized Aircraft Monitoring) System Display (SD). It also sends a signal to the OMS (Onboard Maintenance System) and ECAM display in case of failure or malfunction, via AFDX (Avionics Full Duplex Switched Ethernet) links to the ADCN (Avionics Data Communication Network).

- A pressure transducer that sends a signal to the OSCU The pressure reducer/transmitter is connected to: - An overpressure outlet. The pressure reducer has an outlet pressure of ab out 9 bars (130.53 PSI). If the outlet pressure increases to above 11.7 bars (169.69 PSI), the safety outlet releases the oxygen through the overboard discharge indicator. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

PASSENGER OXYGEN SYSTEM DESCRIPTION (3)

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PASSENGER OXYGEN STORAGE MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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PASSENGER OXYGEN SYSTEM DESCRIPTION (3) Passenger Oxygen Distribution The distribution circuit includes: - Two oxygen regulators - A low-pressure switch - Two oxygen test ports - 2 main distribution lines - A b leed/vent Valve The oxygen regulators are electrically operated. They convert intermediate pressure to low pressure to use in the distribution system. They provide variable regulation depending on cabin altitude, from 5 PSI at 10000 ft to 65 PSI at 40000 ft. They have two electrical inputs, one to open the valve and one to close it. Each oxygen regulator also has two internal switches: "Valve fully open" position, which operates the SYS ON light "Valve not fully open" or "valve fully closed" position, which send a signal via the OSCU to the OMS A low-pressure switch is installed in the intermediate pressure line between the pressure reducer/transducers and the oxygen regulators. If the pressure in the intermediate pressure line drops below 6.73 bars (98.05 PSI), the switch generates a signal to the ECAM SD and to the OMS, via the OSCU or the IOMs. There are two identical test ports. One is installed in the intermediate pressure system before the oxygen regulators, and one is installed on the low-pressure distribution, to make system tests and leak checks of the distribution system. There is one Main Distribution Line (MDL) on each passenger deck. Riser lines are connected to the main distribution lines to supply oxygen to the lateral and centre hatrack lines, on which the oxygen containers are connected. The forward and aft interconnection lines connect the two main distribution lines to each other. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

The regulators supply the forward interconnection line through a feed line. The bleed vent valves are installed in the pressurized area of the cabin at the end of the main distribution lines. They vent the lines in case of actuation of the system and prevent any container door from opening in case of small leakage of the Oxygen Regulator shut-off valves. After purging the main distribution lines, the bleed valves close pneumatically and allow a pressure built up for release of the oxygen masks.

Engine Burst Area Distribution The engine burst protection is composed of: - Two check valves - Two electrical shutoff valves - Riser line shutoff/check valves - Hatrack shutoff valves - A differential pressure switch The check valves are installed on the supply line behind the Engine Burst Area (EBA). They open when the oxygen sy stem is pressurized and the oxygen flows in the normal direction (front to rear). They will close if the oxygen flows in the opposite direction. This will occur if the applicable supply line to the check valve is damaged. The check valves together with the shutoff /check valves, and the differential pressure switch, prevent the oxygen supply to a damaged supply line. One electrical shutoff valve is installed on each MDL upstream of the engine burst area. One check valve is installed on each MDL downstream of the engine burst area. When one MDL is damaged, a differential pressure switch will detect a press ure difference and close the electrical shutoff valve of the damaged line. The electrical shutoff valves are electrically operated. They have two electrical inputs from the OSCU, one to open the valve and one to close it. Two internal switches send a position signal to the ECAM/Warning display ("CABIN OXY SHUTOFF VALVE CLOSED" for pre-flight check only) and to the OMS:


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A380 TECHNICAL TRAINING MANUAL - Valve fully closed - Valve not fully open. The riserline shutoff /check Valve is a differential pressure closing component to stop the flow in the defined direction, that will be positioned in each of the riser lines in the engine burst area for damage limitation in case of engine burst. The valve closes if a rupture of a riser line anywhere downstream of the valve occurs. Once closed , the valve remains closed until the pressure in the line has returned to ground ambient conditions. If a main distribution line is damaged the check valve function included in the shutoff /check valve closes as a protection against

An additional automatic activation is provided from the altitude switch, which activates directly the oxygen regulators when it detects a cabin altitude exceeding 14 000ft. For manual activation, the crew can activate the oxygen regulators via the "MAN ON" pushbutton switch on the cockpit panel 1211VM if the altitude pressure switch does not operate. When the system is activated, the shutoff valve of each regulator opens and oxygen flows into the distribution network. The distribution system is purged through two bleed vent valves, installed at the rear end of the distribution system. After purging the low-pressure part, the bleed valves close.

oxygen loss.shutoff valves are installed in the co nnection between the The hatrack closed circular riser line inside of engine burst area and the hatrack line. They are pneumatically controlled so that the oxygen is not supplied to a damaged hatrack line. In normal operation, they are open. They close if a rupture of a hatrack line occurs anywhere downstream of the valve. The differential pressure switch compares the pressure in the two main distribution lines in the engine burst area. If there is a pressure difference between the lines, the switch energizes the applicable electrical shutoff valve, which closes. In this case the oxygen will be supplied by the non-damaged MDL.

The low-pressure part isand then pressurized and which the oxygen containers will open pneumatically release the masks, fall down. When pulling the mask to their face, the passengers will open the shutoff valve of the mask and the oxygen will flow. The pressure regulators are regulating the pressure part to the required pressure depending on the flight level. When the RESET pushbutton switch is pushed and released: - The OSCU energizes the oxygen regulators that close - After 1 second, the OSCU energizes the electrical shutoff valves that open (if they are closed) - The OSCU stops the operation after 3 seconds and the ON light on the RESET P/BSW goes off The OSCU monitors the position of all relays. If one or more of the Passenger Oxygen System Activation/Regulation/Dispensing relays do not return to the pre-operation position, the ON legend on There are three possibilities to activate the system: the RESET P/BSW does not go off. - Automatically via the cabin pressure signal from the Cabin Pressure The FAULT indication of the RESET pushbutton switch appears if Control System (CPCS) the controlled positions of the valves are not reached. - Automatically via the altitude pressure switch - Manually by the crew. The OSCU receives cabin altitude information from the CPCS via AFDX Bus. The passenger oxygen system is activated automatically by the OSCU if the cabin altitude exceeds 14 000 ft. In this case, the OSCU activates the oxygen regulators. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen

OSCU Interface With Other Aircraft Systems

The OSCU has AFDX interfaces to communicate thro ugh the ADCN with other systems, as follows: - Information to the CDS, the OMS and the ACMS for maintenance data and system display on the ECAM DOOR/OXY page - Flight phase information from the FWS PASSENGER OXYGEN SYSTEM DESCRIPTION (3)

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A380 TECHNICAL TRAINING MANUAL - Cockpit warnings display through the FWS - Cabin pressure signal from the CPCS to activate the system - Passenger number information from the FMCs - Ground/Flight status from the LGERS - Cabin prerecorded announcement through the CIDS Directors. The IOMs (Input/Output Modules) are a back up for flight warning message and indications on CDS.



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PASSENGER OXYGEN DISTRIBUTION - ENGINE BURST AREA DISTRIBUTION ... OSCU INTERFACE WITH OTHER AIRCRAFT SYSTEMS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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PASSENGER OXYGEN DISTRIBUTION - ENGINE BURST AREA DISTRIBUTION ... OSCU INTERFACE WITH OTHER AIRCRAFT SYSTEMS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM MAINTENANCE (3) Tests OMS Interactive Tests Overview The oxygen system provides the following interactive tests : - System test - Pin Programming Test These tests are launched from the OMS HMI (using the OMT, OIT or PMAT)

Passenger Distribution Test Text of step 1 of subtopic page 1


OXYGEN SYSTEM MAINTENANCE (3)

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TESTS - OMS INTERACTIVE TESTS OVERVIEW & PASSENGER DISTRIBUTION TEST MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM MAINTENANCE (3) Safety Precaution Obey these safety precautions: WARNING: KEEP ALL HYDROCARBONS (FUELS, LUBRICANTS,...ETC) AWAY FROM ALL SOURCES OF OXYGEN. OXYGEN BECOMES EXPLOSIVE WHEN IT TOUHES HYDROCARBONS. TO PREVENT CONTAMINATION OF THE OXYGEN SYSTEM, MAKE SURE THAT YOUR HANDS AND ALL THE TOLLS ARE CLEAN.

MPD Tasks



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OXYGEN SYSTEM OPERATION, CONTROL & IND (3) General


OXYGEN SYSTEM OPERATION, CONTROL & IND (3)

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GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM OPERATION, CONTROL & IND (3) Flight Crew Oxygen System There are two oxygen thresholds for the cockpit high-pressure indication (P1and P2): P1 (Dispatch pressure): Oxygen cylinder pressure to protect 4 cockpit (option: 5) occupants covering depressurization and toxic gases/smoke emissions (PIN programmed in the OSCU depending on the maximum number of cockpit occupants, the number of oxygen cylinders installed, and the intended operation of the aircraft). P2 (Cockpit Minimum Pressure): Oxygen cylinder pressure to protect 2 cockpit occupants covering depressurization and toxic gases/smoke emissions (15 minutes oxygen supply) depending on the intended operation of the aircraft. When P2P2,

- Amber when oxygen cylinder pressure P2
- Amber when P

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FLIGHT CREW OXYGEN SYSTEM MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM OPERATION, CONTROL & IND (3) Cabin Oxygen System If the OSCU detects a low pressure in the intermediate pressure system via the low pressure switch, this will trigger a failure signal. The ECAM caution OXY CABIN OXYGEN PRESS LO is displayed.

Reset Pushbutton The reset button is used to reset the electrical circuit, to reset the sh ut off valve of oxygen regulator and the electrical s hutoff valves of main distribution lines after system operation. The reset button has an indication light that lights for 3 seconds if the reset button is pushed. The oxygen containers stay open. The fault light comes on if the valves reset position is not reached.



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CABIN OXYGEN SYSTEM - RESET PUSHBUTTON MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM OPERATION, CONTROL & IND (3) Cabin Oxygen System (continued) Engine Burst Shut Off Valve Warning If the electrical shutoff valves for engine burst protection in the main distribution lines are not in the fully open position and the oxygen system is not activated, the OSCU will detect this failure by continuous BITE and trigger a failure signal. The ECAM caution OXY CABIN OXYGEN SHUT OFF VALVE CLOSED is displayed



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CABIN OXYGEN SYSTEM - ENGINE BURST SHUT OFF VALVE WARNING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM OPERATION, CONTROL & IND (3) Tests Capabilities Passenger Distribution Test By initiated Passenger Distribution Test, it shall be possible to verify the correct functioning of the electrical shutoff valves, the main distribution line check valve and the differential pressure switch. This is only possible on ground and with activation of the oxygen system.



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TESTS CAPABILITIES - PASSENGER DISTRIBUTION TEST MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 35 Oxygen


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OXYGEN SYSTEM COMPONENT LOCATION (3) Cockpit Cabin Emergency Avionics Bay LH FWD Fuselage Main Avionics Bay FWD Cargo Compartment Cabin System Flight Crew System


OXYGEN SYSTEM COMPONENT LOCATION (3)

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OXYGEN SYSTEM COMPONENT LOCATION (3)

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AIRBUS S.A.S. 31707 BLAGNAC cedex, FRANCE STM REFERENCE L1W06161 APRIL 2006 PRINTED IN FRANCE AIRBUS S.A.S. 2006 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

Level III - Ata 35 Oxygen

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