A330-200/300 TECHNICAL TRAINING MANUAL DIFFERENCE COURSE - A330 PW/RR to A330 GE CF6 T1/T1+T2 PNEUMATIC This document must be used for training purposes only Under no circumstances should this document be used as a reference It will not be updated. All rights 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 S.A.S. AIRBUS Environmental Recommendation Please consider your environmental responsability before printing this document. . 20 Bleed Air Distribution & Supply D/O (GECF6) (3) .T1/T1+T2 36 . . 48 Engine Bleed Air Transfer System D/O (GECF6) (3) . . . . . . . . . . . . . .A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC 36 Pneumatic System Presentation (GECF6) (1) . . . . . . . . SYS D/O (GECF6) (3) . . . . . . 52 Engine Bleed Air Press. D/O (GE) (3) . . . . . . . 54 G7108471 . . .A330 PW/RR to A330 GE CF6 . . . . . . .PNEUMATIC TABLE OF CONTENTS Nov 21. . . . 2 Pneumatic Line Maintenance Briefing (GECF6) (2) . 40 Engine Bleed Air Managmnt SYS Gen. . . . . . Reg. . . . .G84T0TG DIFFERENCE COURSE . . . . . . 2008 Page 1 . . . . . . . . . . . . . . . . the system sources and users.PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. .A330 PW/RR to A330 GE CF6 .FM36P5000000004 DIFFERENCE COURSE . .G84T0TG .the leak detection system.the maintenance and test facilities. G7108471 . When you work on A/C. This module describes: . .the control and indicating. APU and HP Ground Unit bleed air management system.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) GENERAL The pneumatic system is used to supply air to various A/C systems.T1/T1+T2 36 . 2008 Page 2 . .the engine. you must obey all the safety procedures listed in the AMM. PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. 2008 Page 3 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .A330 PW/RR to A330 GE CF6 .FM36P5000000004 GENERAL DIFFERENCE COURSE .G84T0TG .T1/T1+T2 36 . The pneumatic system operates pneumatically and is monitored by two Bleed Monitoring Computers (BMCs) one. The HP bleed is only used when the engines are at low power.the packs bay ventilation system. There is one BMC for each engine bleed system.the thrust reverser system. However.engines. blows across the precooler to maintain the temperature within limits. . the High Pressure Valve (HPV) closes. . The right side may be supplied by opening the crossbleed valve. The APU can also be used for bleed air supply.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) SOURCES AND USERS The pneumatic system may be supplied with High Pressure (HP) bleed air from 3 types of sources: . an overpressure valve (OPV) is installed downstream from the bleed valve to protect the system in case of overpressure. APU BLEED/HP GROUND UNIT BLEED A crossbleed duct connects the left and right bleed systems. ENGINE BLEED The engine bleed air is pressure and temperature regulated prior to supplying the pneumatic system.ground cart.A330 PW/RR to A330 GE CF6 .the water system pressurization. All the engine bleed air is supplied to the pneumatic system through the main engine BLEED valve (or Pressure Regulating Valve (PRV)). Once the IP bleed is sufficient. a HP ground power unit can be connected to the left side pneumatic system. depending on altitude. This is usually done on the ground for air conditioning and for engine start. . The temperature of the engine bleed air is regulated to a maximum value.the wing anti-icing system.FM36P5000000004 bleed in case of excessive pressure. If one BMC fails. The APU bleed supply is connected to the left side of the crossbleed duct. These users are: . Air is bled from two engine High Pressure Compressor (HPC) stages. APU BLEED air could also be used in flight.PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.T1/T1+T2 36 .APU. G7108471 . 2008 Page 4 . . .the air conditioning packs. In addition. Each BMC monitors system pressure and will shut down the engine DIFFERENCE COURSE . two. A crossbleed valve enables their interconnection or isolation. Fan discharge air modulated by the Fan Air Valve (FAV).the engines starting systems. The hot bleed air goes through an air-to-air heat exchanger called the precooler. On the ground. .the hydraulic reservoir pressurization. Both BMCs exchange data.G84T0TG . the other BMC takes over most of its monitoring functions. . The bleed air is distributed to the different users via a distribution and supply ducting network. the Intermediate Pressure (IP) stage and the HP stage. . which acts as a shut off and overall system pressure regulating valve. ENGINE BLEED & APU BLEED/HP GROUND UNIT BLEED DIFFERENCE COURSE .T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . 2008 Page 5 .G84T0TG .FM36P5000000004 SOURCES AND USERS .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. 2008 Page 6 . a single detection loop ensures the leak detection. the mid fuselage above the air conditioning packs area and on the APU bleed duct.PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. which automatically isolates the affected area. The loops are made of multiple sensing elements connected in series. In each engine pylon.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) LEAK DETECTION Leak detection loops are installed along the hot air supply ducts of the pneumatic system.FM36P5000000004 DIFFERENCE COURSE . or two. triggers a warning signal to the ECAM system through the System Data Acquisition Concentrator (SDAC) and sends a fault message to the Central Maintenance Computer (CMC).A330 PW/RR to A330 GE CF6 . Two loops A and B are routed in parallel along the air ducts. The leak detection loops are connected to the BMCs. An "AND" logic ensures the interconnection of the loops in the BMCs to prevent spurious warnings.G84T0TG .T1/T1+T2 36 . G7108471 . a signal is sent to the BMC one. A dual loop detection system is installed in the wings. If a leak is detected. G84T0TG .FM36P5000000004 LEAK DETECTION DIFFERENCE COURSE .A330 PW/RR to A330 GE CF6 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 . 2008 Page 7 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. CONTROL PANEL Controls for the pneumatic system are part of the AIR COND panel.FM36P5000000004 DIFFERENCE COURSE . 2008 Page 8 . located on the overhead panel.A330 PW/RR to A330 GE CF6 .G84T0TG .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) CONTROL AND INDICATING This section highlights the control panels and indications for the pneumatic system.T1/T1+T2 36 . G7108471 . 2008 Page 9 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.G84T0TG .T1/T1+T2 36 .FM36P5000000004 CONTROL AND INDICATING .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .A330 PW/RR to A330 GE CF6 .CONTROL PANEL DIFFERENCE COURSE . A330 PW/RR to A330 GE CF6 . 2008 Page 10 . G7108471 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) CONTROL AND INDICATING (continued) ECAM INDICATION The pneumatic system indications are displayed on the lower part of the ECAM BLEED page.T1/T1+T2 36 .G84T0TG .FM36P5000000004 DIFFERENCE COURSE . T1/T1+T2 36 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.G84T0TG . 2008 Page 11 .A330 PW/RR to A330 GE CF6 .ECAM INDICATION DIFFERENCE COURSE .FM36P5000000004 CONTROL AND INDICATING .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . the PRV.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) COMPONENT LOCATION The main components of the pneumatic system are located on the engines and in the pylons. 2008 Page 12 . G7108471 . The OPV and the precooler are located in the pylon.G84T0TG . the High Pressure Valve (HPV). ENGINE BLEED COMPONENTS The IPC.T1/T1+T2 36 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. the FAV are located on the engine.A330 PW/RR to A330 GE CF6 .FM36P5000000004 DIFFERENCE COURSE . 2008 Page 13 .FM36P5000000004 COMPONENT LOCATION .T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 .ENGINE BLEED COMPONENTS DIFFERENCE COURSE .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.G84T0TG . PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) COMPONENT LOCATION (continued) APU AND X BLEED COMPONENTS The crossbleed valve is located in the forward section of the lower fuselage belly fairing area. 2008 Page 14 .T1/T1+T2 36 . Get access to the HP ground connector through a small access door located on the lower fuselage belly fairing. G7108471 .A330 PW/RR to A330 GE CF6 .G84T0TG .FM36P5000000004 DIFFERENCE COURSE . The APU bleed valve is located on the APU. G84T0TG .T1/T1+T2 36 . 2008 Page 15 .APU AND X BLEED COMPONENTS DIFFERENCE COURSE .A330 PW/RR to A330 GE CF6 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .FM36P5000000004 COMPONENT LOCATION . 2008 Page 16 .A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) MAINTENANCE/TEST FACILITIES The CMCs let the maintenance crew read the failure data in the BMCs BITE via the MCDUs.A330 PW/RR to A330 GE CF6 .FM36P5000000004 DIFFERENCE COURSE . G7108471 .T1/T1+T2 36 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20.G84T0TG . G84T0TG .T1/T1+T2 36 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .A330 PW/RR to A330 GE CF6 .PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20. 2008 Page 17 .FM36P5000000004 MAINTENANCE/TEST FACILITIES DIFFERENCE COURSE . A330-200/300 TECHNICAL TRAINING MANUAL 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) SAFETY PRECAUTIONS When you work on A/C, make sure that you obey all the AMM safety procedures. This will prevent injury to persons and/or damage to the A/C. Here is an overview of the main safety precautions relative to the pneumatic system. Make sure that the pneumatic system is depressurized before starting the work as pressurized air can cause unwanted pressurization of the A/C, and injury to personnel. Parts can be hot for 1 hour after engine shutdown. Do not touch them until they are sufficiently cool. G7108471 - G84T0TG - FM36P5000000004 DIFFERENCE COURSE - A330 PW/RR to A330 GE CF6 - T1/T1+T2 36 - PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20, 2008 Page 18 A330-200/300 TECHNICAL TRAINING MANUAL G7108471 - G84T0TG - FM36P5000000004 SAFETY PRECAUTIONS DIFFERENCE COURSE - A330 PW/RR to A330 GE CF6 - T1/T1+T2 36 - PNEUMATIC 36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1) Nov 20, 2008 Page 19 A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) SYSTEM OVERVIEW The pneumatic system is used to supply air to various A/C systems. This module will review: - the system sources and users, - the engine APU and High Pressure (HP) ground unit bleed air management system, - the leak detection system, - and the control and indicating. This module will also introduce some typical line maintenance activities. G7108471 - G84T0TG - FM36B1000000004 DIFFERENCE COURSE - A330 PW/RR to A330 GE CF6 - T1/T1+T2 36 - PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20, 2008 Page 20 G84T0TG .A330 PW/RR to A330 GE CF6 . 2008 Page 21 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 .FM36B1000000004 SYSTEM OVERVIEW DIFFERENCE COURSE .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. Each BMC monitors system temperature and will shut down the engine bleed in case of excessive temperature. On the ground. The bleed air is distributed to different users via a distribution and supply ducting network. . If one adjacent BMC fails. A crossbleed duct connects the left and right bleed systems. The hot bleed air goes through an air-to-air heat exchanger called the precooler. The pneumatic system may be supplied with HP bleed air from 3 types of sources: . an OverPressure Valve (OPV) is installed downstream from the bleed valve to protect the system in case of overpressure. The temperature of the engine bleed air is regulated to a maximum value. .FM36B1000000004 ENGINE BLEED The engine bleed air is pressure and temperature regulated prior to supplying the pneumatic system.A330 PW/RR to A330 GE CF6 . APU bleed air may also be used in flight.the air conditioning packs.the air conditioning compartment ventilation system. .the hydraulic reservoir pressurization. an HP ground power unit can be connected to the left hand side pneumatic system. The crossbleed valve opens automatically to supply the right hand side when the APU bleed is supplying the system. In addition.APU. The APU bleed supply is connected to the left side of the crossbleed duct. . These users are: . blows across the precooler to maintain the temperature within limits.the engines starting systems. Each BMC monitors system pressure and will shut down the engine bleed in case of excessive pressure.PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. G7108471 . Air is bled from two engine High Pressure Compressor (HPC) stages. The Intermediate Pressure Check Valve (IPC) and High Pressure Valve (HPV) control the bleed air supply. APU BLEED/EXTERNAL AIR SUPPLY The APU can also be used for bleed air supply. Fan discharge air modulated by the Fan Air Valve (FAV). . . There is one BMC for each engine bleed system. Both adjacent BMCs exchange data.engines. Once the IP bleed is sufficient. The pneumatic system operates pneumatically and is monitored by two Bleed Monitoring Computers (BMCs) 1 and 2. the HPV closes and the IPC opens. A crossbleed valve enables their interconnection or isolation.the water system pressurization.T1/T1+T2 36 . 2008 Page 22 . This is usually done on the ground for air conditioning and for engine start. depending on altitude.ground cart.G84T0TG . The HP bleed is only used when the engines are at low power. which acts as a shut off and overall system pressure regulating valve. the Intermediate Pressure (IP) stage and the HP stage.the wing anti-icing system. The right hand side may be supplied by opening the crossbleed valve. the other BMC takes over most of its monitoring functions.A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) SYSTEM OVERVIEW (continued) SOURCES AND USERS The pneumatic system is used to supply temperature and pressure regulated air to various A/C systems. DIFFERENCE COURSE . However. . All the engine bleed air is supplied to the pneumatic system through the main engine bleed valve (or Pressure Regulating Valve (PRV)). SOURCES AND USERS .T1/T1+T2 36 . APU BLEED/EXTERNAL AIR SUPPLY DIFFERENCE COURSE .G84T0TG . 2008 Page 23 .FM36B1000000004 SYSTEM OVERVIEW ..A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20..A330 PW/RR to A330 GE CF6 . Two loops (A and B) are routed in parallel along the air ducts. G7108471 . 2008 Page 24 .T1/T1+T2 36 . The BMC uses "AND" logic to generate a leak warning and to prevent spurious warnings. The loops are made of multiple sensing elements connected in series. a single detection loop is monitored for leaks by the respective BMC. the mid fuselage and in the air conditioning compartment to monitor the packs and bleed ducts. A dual loop detection system is installed in the wings.G84T0TG . are installed along the hot air supply ducts of the pneumatic system and are monitored by the BMCs. The APU supply duct is also monitored by a dual-loop system.PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) SYSTEM OVERVIEW (continued) LEAK DETECTION Leak detection elements.FM36B1000000004 DIFFERENCE COURSE .A330 PW/RR to A330 GE CF6 . connected in series. In each engine pylon. T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . 2008 Page 25 .LEAK DETECTION DIFFERENCE COURSE .G84T0TG .FM36B1000000004 SYSTEM OVERVIEW . make the thrust reverser unserviceable and open the LH thrust reverser cowl door. the related engine bleed system should not be used at low power setting. remove the locking pin from its stowage. referring to the MEL. The conditions for dispatch require the valve to be locked in the closed position and the related engine bleed system is inoperative.on the manual override.on the PRV. .FM36B1000000004 DIFFERENCE COURSE .G84T0TG .High Pressure Valve) deactivated. The aircraft may also be dispatched with one of the engine HP valves (HPV . referring to the MEL.T1/T1+T2 36 . .open the RH fan cowl. . . make sure that the valve is in the CLOSED position and install the locking pin to secure the valve closed. .A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) MEL/DEACTIVATION The aircraft may be dispatched with one of the engine bleed valves PRV deactivated.on the manual override. 2008 Page 26 . remove the locking pin from its stowage. .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.make the thrust reverser unserviceable and open the RH thrust reverser cowl door.open the LH fan cowl.on the HPV. The conditions for dispatch require the valve to be locked in the closed position. G7108471 .A330 PW/RR to A330 GE CF6 . Procedure to lock the valve closed: . make sure that the valve is in the CLOSED position and install the locking pin to secure the valve closed. Procedure to lock the valve closed: . In addition. T1/T1+T2 36 .FM36B1000000004 MEL/DEACTIVATION DIFFERENCE COURSE .G84T0TG . 2008 Page 27 .A330 PW/RR to A330 GE CF6 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. A330 PW/RR to A330 GE CF6 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.FM36B1000000004 MEL/DEACTIVATION DIFFERENCE COURSE .G84T0TG . 2008 Page 28 .T1/T1+T2 36 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . A330-200/300 TECHNICAL TRAINING MANUAL This Page Intentionally Left Blank G7108471 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.FM36B1000000004 DIFFERENCE COURSE .G84T0TG .T1/T1+T2 36 . 2008 Page 29 .A330 PW/RR to A330 GE CF6 . For the wings and APU loops. FAV.For engines pylon loops. During a ground air start. First the installation of the filler ring inside the bleed duct groove and then the installation of the seal with its green face visible from outside. The only indication that external ground air is supplied is indication of system pressure on the left hand side. The access door is on the belly fairing. It is used to do an on-wing operational test of the HPV. Then disconnect the ground air supply and make a crossbleed start for subsequent starts. it is recommended to use the ground air supply to start the first engine.A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) MAINTENANCE TIPS Troubleshooting Note: The condition of an overheat detection loop is checked by measurement of its Insulation Resistance (I/R). .twist the seam of the foil wrap tight. .FM36B1000000004 . 2008 Page 30 when the aircraft is on the ground to indicate that the external pneumatic supply will be connected directly to the left hand side of the system. The leak may be found by using the (aluminum) foil-wrapping procedure to locate the source. the I/R must be above 6 K .wrap the foil around the joint one time. the I/R must be above 25 K NOTE: I/R measurement must be done using an Alternate Current (AC) loop controller (Example: 9240SI). It does not indicate that external pneumatic supply is connected or even that the access door is open. the crossbleed valve must be manually operated. Procedure: . NOTE: The leak may also be found by using the alternative procedure with the use of the dry developer. the connection is located on the lower fuselage. This procedure is also used to check for leaks after installation of a bleed valve or a duct. The GND indication on the ECAM BLEED page sometimes causes confusion.A330 PW/RR to A330 GE CF6 . A test set is available to help in troubleshooting of the pneumatic system. OPV and pressure transducers. GND appears on the BLEED page DIFFERENCE COURSE . . G7108471 . For safety.G84T0TG . PRV.run the engine. NOTE: No lubricant has to be applied prior and/or during installation of PTFE seal.T1/T1+T2 36 . The installation of PTFE (Teflon) seals on the bleed air duct is done in two steps. there is the possibility of a high-pressure air leak on the engine pneumatic ducts.after shutdown.secure the foil wrap on either side of the joint with lockwire.PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. To make an engine start with ground air. If the ENG BLEED LEAK warning is displayed on the ECAM. The use of Direct Current (DC) loop controller will impact the electrical characteristics of the sensing element. . as detailed in the related TSM task 36-22-00-810-xxx): . check for any evidence of leaks. FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE .A330 PW/RR to A330 GE CF6 .G84T0TG .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 . 2008 Page 31 . A330 PW/RR to A330 GE CF6 . 2008 Page 32 .T1/T1+T2 36 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG . A330 PW/RR to A330 GE CF6 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE . 2008 Page 33 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.G84T0TG . G84T0TG .T1/T1+T2 36 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. 2008 Page 34 .A330 PW/RR to A330 GE CF6 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE . PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20. 2008 Page 35 .A330 PW/RR to A330 GE CF6 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE .T1/T1+T2 36 .G84T0TG . T1/T1+T2 36 . 2008 Page 36 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG .A330 PW/RR to A330 GE CF6 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE . FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.T1/T1+T2 36 .G84T0TG .A330 PW/RR to A330 GE CF6 . 2008 Page 37 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . T1/T1+T2 36 .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.G84T0TG .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . 2008 Page 38 .A330 PW/RR to A330 GE CF6 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE . A330 PW/RR to A330 GE CF6 . 2008 Page 39 .G84T0TG .T1/T1+T2 36 .FM36B1000000004 MAINTENANCE TIPS DIFFERENCE COURSE .PNEUMATIC PNEUMATIC LINE MAINTENANCE BRIEFING (GECF6) (2) Nov 20.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 . 2008 Page 40 .A330 PW/RR to A330 GE CF6 .FM36D1000000005 DIFFERENCE COURSE . The engine bleed air systems are connected to the corresponding pneumatic manifold. G7108471 . The APU can supply air to the LH and RH pneumatic manifolds on ground and during climb up to 23000 feet (7010 meters) and during the descent from 21000 feet (6400 meters).A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) GENERAL The crossbleed valve connects or disconnects the LH and the RH pneumatic manifolds. High Pressure (HP) ground connectors can supply air to the LH pneumatic manifold and through the crossbleed valve to the RH pneumatic manifold when connected to a ground cart.T1/T1+T2 36 .G84T0TG .PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20. A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .FM36D1000000005 GENERAL DIFFERENCE COURSE .G84T0TG .A330 PW/RR to A330 GE CF6 .T1/T1+T2 36 . 2008 Page 41 .PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20. Each connector contains a non-return valve and a built-in nipple. to the left of the crossbleed valve.T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 . 2008 Page 42 . G7108471 . Once connected and switched ON.G84T0TG .A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) HP AIR GROUND SUPPLY The ground air source supplies air through the two HP ground connectors installed at the bottom left of the belly fairing. ground cart delivered pressure can be checked on the ECAM BLEED page. A short duct connects the HP ground connectors to the crossbleed manifold.PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20. This pressure indication is given through the engine bleed system.FM36D1000000005 DIFFERENCE COURSE . CAUTION: all A/C bleed systems must be switched off before the crossbleed manifold is pressurized by the ground cart. 2008 Page 43 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG .FM36D1000000005 HP AIR GROUND SUPPLY DIFFERENCE COURSE .A330 PW/RR to A330 GE CF6 .T1/T1+T2 36 .PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20. . the BMCs send an opening command to the Electronic Control Box (ECB) if the following conditions are met: . the APU bleed valve opens. .no APU shutdown is carried out.FM36D1000000005 . As a consequence.no leak is detected on the APU bleed duct. It is electrically controlled by a solenoid and pneumatically operated. it energizes the bleed valve solenoid only if: . . a ground signal is sent to both Bleed Monitoring Computers (BMCs). .the APU BLEED P/B is ON. APU BLEED VALVE CONTROL Once the APU BLEED P/B is set to ON. 2008 Page 44 G7108471 . Then.the APU runs at more than 95% of speed.and no leak is detected on the LH pneumatic manifold. with a visual position indicator installed.A330 PW/RR to A330 GE CF6 .G84T0TG .T1/T1+T2 36 . . Its muscle pressure is tapped upstream of the valve. APU BLEED AND CHECK VALVES The APU bleed valve is an ON/OFF butterfly valve.A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) APU BLEED AIR SUPPLY The main components of the APU bleed system are the APU bleed valve and the APU check valve. Note that these two leak conditions are not active during Main Engine Start (MES). The check valve protects the APU from reverse flow when another source supplies bleed air at a higher pressure. A Fully Closed (FC)/NOT FC micro switch is installed on the valve for indicating and monitoring purposes.the APU master switch is ON. the Pressure Regulating Valves (PRVs) of the two engines automatically close and the DIFFERENCE COURSE . spring loaded closed. crossbleed valve automatically opens when the APU supplies bleed air to the users. APU bleed valve position and bleed pressure are indicated on the ECAM BLEED page (the pressure value is given by the engine bleed system). Once the ECB receives the opening command.PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20.and the altitude is lower than 23000 feet (7010 meters)during climb or 21000 feet (6400meters) during descent. PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20.G84T0TG .FM36D1000000005 APU BLEED AIR SUPPLY .APU BLEED AND CHECK VALVES & APU BLEED VALVE CONTROL DIFFERENCE COURSE . 2008 Page 45 .A330 PW/RR to A330 GE CF6 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 . the APU bleed valve is not FC. . . 2008 Page 46 .crossbleed engine start.T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 . the crossbleed valve auto-control relay supplies electrical power to the crossbleed valve primary motor and the crossbleed valve opens. Either automatic or manual control can be selected using the crossbleed valve selector of the AIR panel. G7108471 . . When the crossbleed valve selector switch is set to CLOSE.or when an engine bleed system fails.and there is no leak detected.G84T0TG . the secondary motor closes the crossbleed valve.PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20. . As soon as: . which opens the valve. the APU bleed valve closes and. A Fully Open (FO) or Fully Close (FC) position of the valve is sent to the two BMCs by 2 micro switches. the valve position is given by the 2 microswitches and shown on the ECAM BLEED page.the APU BLEED P/B is ON. AUTOMATIC CONTROL When the crossbleed valve selector is in the AUTO position.FM36D1000000005 MANUAL CONTROL The manual opening control can be used in the subsequent cases: . the crossbleed valve primary motor power supply is cut out. When the APU BLEED is deselected. As in the automatic mode. the BMCs send a ground signal to the crossbleed valve auto-control relay. Two electrical motors. through the primary valve motor. it directly supplies the secondary crossbleed valve motor. The FO position feedback from the microswitch is indicated on the ECAM BLEED page through the BMCs.A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) CROSSBLEED SYSTEM The crossbleed valve is an electrically controlled butterfly shut-off valve. As a consequence. the crossbleed valve closes. are used for manual or automatic operation. which work independently. INCORRECT OPERATION If a disagreement between the valve position and command occurs.cross supply by a ground cart. in turn. DIFFERENCE COURSE . The FC feedback from the second microswitch is displayed on the BLEED page. When the crossbleed valve selector switch is set to OPEN. As soon as a manual control is selected. the crossbleed valve control is carried out by the BMCs. the BMCs trigger an ECAM message and the BLEED page comes up automatically. .PNEUMATIC BLEED AIR DISTRIBUTION & SUPPLY D/O (GECF6) (3) Nov 20.AUTOMATIC CONTROL .T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 . INCORRECT OPERATION DIFFERENCE COURSE .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG . 2008 Page 47 .FM36D1000000005 CROSSBLEED SYSTEM .. pressure limitation system to regulate the bleed air pressure in order to prevent overpressure.pneumatic transfer system. It selects one of the two compressor stages of the engine HP compressor in agreement with the supplied pressure. It is generally bled from an Intermediate Pressure (IP) stage of the engine compressor (stage 8) to minimize fuel penalty. D/O (GE) (3) GENERAL The main air bleed sources are the engines.FM36D6000000004 DIFFERENCE COURSE .PNEUMATIC ENGINE BLEED AIR MANAGMNT SYS GEN.T1/T1+T2 36 . Air can be bled from two different stages.temperature limitation system to regulate the bleed air temperature in order to prevent over temperature. air is automatically bled from the High Pressure (HP) stage of the compressor (stage 14). .G84T0TG . . Each engine bleed air system includes the following sub-system: . G7108471 . When pressure from the IP bleed port is insufficient to supply the network. D/O (GE) (3) Nov 20.A330 PW/RR to A330 GE CF6 . 2008 Page 48 .A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR MANAGMNT SYS GEN. G84T0TG .A330 PW/RR to A330 GE CF6 .PNEUMATIC ENGINE BLEED AIR MANAGMNT SYS GEN.A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .T1/T1+T2 36 .FM36D6000000004 GENERAL DIFFERENCE COURSE . D/O (GE) (3) Nov 20. 2008 Page 49 . D/O (GE) (3) Nov 20. At low engine speed. which modulates fan airflow through an air-to-air heat exchanger. The FAV is controlled by the BMC through the Control Thermostat (ThC). especially during A/C descent with engines at idle. The shut-off function of the PRV through the thermostat solenoid is controlled by the corresponding BMC or by using the ENG BLEED P/Bs located on the AIR panel or the engine FIRE P/B. bleed air is ducted to the bleed air distribution and supply network. The HPV can also be closed by action on the engine BLEED P/Bs A check valve located on the IP bleed port avoids reverse flow when air is bled from the HP stage. 2008 Page 50 . Transfer to the IP stage can be forced by closing the HPV via a solenoid incorporated in the HPV. MONITORING The position of the valves. bleed air temperature and pressure are indicated on the ECAM bleed page.A330 PW/RR to A330 GE CF6 .FM36D6000000004 TEMPERATURE LIMITATION The temperature regulation of the bleed air system is carried out by a Fan Air Valve (FAV). The temperature regulation gives two temperature settings: 200°C for nominal conditions (solenoid not energized) and DIFFERENCE COURSE .G84T0TG . the IP port pressure is insufficient and the air is automatically bled from the HP port. A fully pneumatic Overpressure Valve (OPV) protects the system against overpressure. In the normal engine bleed air configuration. Finally.T1/T1+T2 36 . D/O (GE) (3) BLEED AIR TRANSFER The transfer from one bleed port to another is carried out using a HP bleed Valve (HPV) at the HP stage. 150°C on demand from the air conditioning system if the wing anti-ice system is not operative (solenoid energized). The valve acts as a shut-off and PRV. The transfer depends on the available pressure and engine speeds. the air is bled from the IP port at high engine speed. The PRV is fully and pneumatically operated and controlled by the thermostat solenoid. G7108471 .A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR MANAGMNT SYS GEN.PNEUMATIC ENGINE BLEED AIR MANAGMNT SYS GEN. This transfer is commanded by the Bleed Monitoring Computers (BMCs). PRESSURE LIMITATION Air is then sent through the engine bleed air pressure regulation system first composed of a Pressure Regulating Valve (PRV) associated to a thermostat solenoid. MONITORING DIFFERENCE COURSE .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 ..FM36D6000000004 BLEED AIR TRANSFER . D/O (GE) (3) Nov 20.PNEUMATIC ENGINE BLEED AIR MANAGMNT SYS GEN.T1/T1+T2 36 .A330 PW/RR to A330 GE CF6 ..G84T0TG . 2008 Page 51 . the HPV pneumatically closes when the upstream pressure is higher than 105 psi. G7108471 .FM36D2000000004 VALVE POSITION DISAGREEMENT When the HPV is controlled open and is detected in the closed position.G84T0TG . HP VALVE The HPV is pneumatically operated for pressure limitation and safety. The HPV bleed valve position is shown on the SD BLEED page.A330 PW/RR to A330 GE CF6 . The minimum operating pressure of the valve is 10 psi. ABNORMAL HIGH PRESSURE BLEED VALVE CLOSURE An abnormal BMC closure function is used for system protection purposes or during specific operations by solenoid energization. BLEED TRANSFERRED PRESSURE TRANSDUCER The bleed transferred pressure transducer is located in the engine pylon.A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (GECF6) (3) DESCRIPTION The selection of the High Pressure (HP) compressor stage source on each engine is carried out through a HP bleed Valve (HPV) and an Intermediate Pressure (IP) check valve. The HPV is electrically controlled close by solenoid energization either DIFFERENCE COURSE . or when the compressor discharge temperature is higher than 400 degrees Celsius and the HP14 pressure higher than 75 psi. It pneumatically regulates the pressure around 36 psi. the BMC triggers an ECAM message and the BLEED page comes up automatically. Its pressure sense line tapping is taken downstream of the HPV. 2008 Page 52 . The HP8/HP14 transfer is inhibited when the HP pressure is higher than 85 psi and the Wing Anti Ice (WAI) is not selected and the altitude is higher than 26000 feet (7925 meters). automatically by the Bleed Monitoring Computer (BMC) or by ENG BLEED "OFF" pushbutton action. When the HP8 stage pressure exceeds the HPV target value of an average of 36 psi. For maintenance purposes. The HPV is a spring-loaded closed shut-off valve. MONITORING The bleed transferred pressure transducer is used for system monitoring and fault isolation regarding the PRV and HPV. It is equipped with a solenoid for valve operation control.PNEUMATIC ENGINE BLEED AIR TRANSFER SYSTEM D/O (GECF6) (3) Nov 20. This HPV closing command is sent by the BMC any time the Pressure Regulating Valve (PRV) is commanded closed and when an untimely HP8/HP14 transfer is inhibited. If the HP8/HP14 transfer fails. It is electrically controlled to close by a solenoid. NORMAL OPERATION The HP8/HP14 bleed transfer control is pneumatically achieved. the HPV closes and air bleed is supplied by the HP8 stage. the HPV is equipped with a ground test port. IP CHECK VALVE The IP check valve is a non-return valve which closes automatically to prevent HP14 air from re-circulating toward the HP8 stage when the HPV is open. An associated fault message is sent to the Central Maintenance System (CMS) for maintenance purposes. a mechanical position indicator and a special screw with a manual override for locking in the closed position. and a Fully Closed (FC)/NOT FC microswitch for monitoring and indicating.T1/T1+T2 36 . 2008 Page 53 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG .T1/T1+T2 36 .FM36D2000000004 DESCRIPTION .PNEUMATIC ENGINE BLEED AIR TRANSFER SYSTEM D/O (GECF6) (3) Nov 20.A330 PW/RR to A330 GE CF6 .. MONITORING DIFFERENCE COURSE .. REG. electrically controlled.the PRV control solenoid. . The PRV shuts upon energization of the control solenoid. The "Fully Closed (FC)/NOT FC" position is sensed by a microswitch used for monitoring and indicating.PNEUMATIC G7108471 . The PRV control solenoid pneumatically reduces the PRV regulated pressure when the temperature downstream of the precooler exchanger exceeds 235 degrees Celsius.engine P/B action (for redundancy) DIFFERENCE COURSE .FM36D3000000004 BLEED SYSTEM ISOLATION FUNCTION Each engine bleed system can be isolated from the pneumatic manifold in abnormal or specific conditions by closing the PRV.malfunction. SYS D/O (GECF6) (3) SYSTEM DESCRIPTION The pressure regulating system is composed of several components: . The valve closes depending on upstream pressure. valve open position from the microswitch and actual regulated pressure can be checked on the SD BLEED page. The PRV is pneumatically operated and electrically controlled by a PRV control solenoid. a mechanical position indicator and a de-activation maintenance device.A330 PW/RR to A330 GE CF6 . REG. The transducer is electrically connected to the BMC 1 and BMC 2. As soon as the valve regulates. The valve has a ground test port.A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR PRESS. . PRV CONTROL SOLENOID The control solenoid fulfills the control of the PRV. The solenoid is directly energized in case of: .44 psi minimum.the bleed regulated pressure transducer. . . It is also energized via the Bleed Monitoring Computer (BMC) in case of: . BLEED REGULATED PRESSURE TRANSDUCER The PRV pressure transducer is linked by a pressure sense line to a pressure tapping downstream of the PRV. The PRV control solenoid controls the PRV closure when the valve solenoid is energized by the BMC or by action on the ENG BLEED P/B or ENG FIRE P/B.ENG BLEED OFF P/B action. SYS D/O (GECF6) (3) . pneumatically operated. Muscle pressure for valve actuation is tapped from an integral pressure port located upstream of the valve.the Over Pressure Valve (OPV). . Nov 20.the Pressure Regulating Valve (PRV). . OVERPRESSURE VALVE The OPV is a pneumatically actuated valve.ENG FIRE P/B action.52 psi maximum. . PRESSURE REGULATING VALVE The PRV is a fireproof. A minimum upstream pressure of 8 psi is necessary to open the valve. spring-loaded open. pressure regulating and Shut-Off Valve (SOV).engine start. The OPV gives protection to the downstream pneumatic system if the PRV does not operate correctly. 2008 Page 54 ENGINE BLEED AIR PRESS.T1/T1+T2 36 . The control solenoid pneumatically controls the pressure regulation depending on the air temperature at the precooler outlet when the temperature is higher than 235 degrees Celsius.APU bleed supply.G84T0TG . The PRV regulates pneumatically the downstream static pressure to: . PRESSURE REGULATION The PRV is normally spring loaded closed in the absence of upstream pressure. . 2008 Page 55 .during APU bleed supply. the OPV gives a fully pneumatic back up protection in case of PRV regulation failure. The valve remains closed as long as the upstream pressure is higher than 52 psig (+3/-3 psig). REG.during engine start.if an overpressure occurs.A330-200/300 TECHNICAL TRAINING MANUAL MANUAL ISOLATION An engine bleed system can be isolated manually from the manifold by releasing the corresponding BLEED P/B on the AIR panel. The ECAM BLEED page shows the position of the PRVs. . OVERPRESSURE PROTECTION G7108471 . An associated fault message is sent to the Central Maintenance System (CMS) for maintenance purposes.if an over temperature occurs. AUTOMATIC ISOLATION The BMC can isolate automatically engine bleed air supply by energizing the PRV control solenoid: . MONITORING The bleed regulated pressure transducer is used for system monitoring and fault isolation regarding the PRV and OPV.FM36D3000000004 If the bleed regulated pressure rises above 60 psi. In addition to the overpressure electrical monitoring done by the BMC. SYS D/O (GECF6) (3) Nov 20. . The OPV is designed to start to close automatically when the upstream pressure increases above 75 psig and is fully closed at 85 psig (+0/-10 psig). and therefore energizing the PRV solenoid. .A330 PW/RR to A330 GE CF6 . DIFFERENCE COURSE .T1/T1+T2 36 . the BMC detects an overpressure condition and closes the PRV. A warning message is displayed on the EWD and the BLEED page comes up automatically on the SD showing the High Pressure Valve (HPV) and the PRV closed in amber. energizing the PRV solenoid. the bleed system of the affected engine is isolated by releasing the corresponding FIRE P/B on the overhead panel. FIRE ISOLATION If an engine fire occurs. which is displayed on the ECAM BLEED page. resulting in the PRV closure.PNEUMATIC ENGINE BLEED AIR PRESS. . The "FC/NOT FC" microswitch indicates the position of the valve to the BMC.G84T0TG .if a pylon or wing leak is detected. .. SYS D/O (GECF6) (3) Nov 20.FM36D3000000004 SYSTEM DESCRIPTION .T1/T1+T2 36 .A330-200/300 TECHNICAL TRAINING MANUAL G7108471 .G84T0TG .PNEUMATIC ENGINE BLEED AIR PRESS.A330 PW/RR to A330 GE CF6 . REG. 2008 Page 56 . MONITORING DIFFERENCE COURSE . A330-200/300 TECHNICAL TRAINING MANUAL This Page Intentionally Left Blank G7108471 . SYS D/O (GECF6) (3) Nov 20.PNEUMATIC ENGINE BLEED AIR PRESS.A330 PW/RR to A330 GE CF6 . 2008 Page 57 .FM36D3000000004 DIFFERENCE COURSE .G84T0TG . REG.T1/T1+T2 36 . 2008 ALL RIGHTS RESERVED AN EADS COMPANY .S.AIRBUS S. 31707 BLAGNAC cedex. FRANCE STM REFERENCE G7108471 NOVEMBER 2008 PRINTED IN FRANCE AIRBUS S.A.S.A.