A330-200/300 Training Manual (CFM56/V2500) PDF
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Uploaded by EminentAspen
2019
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Summary
This document is a training manual for the A330-200/300 aircraft, focusing on pneumatic systems. The manual details differences from the A318/A319/A320/A321 models and the CFM56/V2500 engine. It is for training purposes only and should not be used for other purposes.
Full Transcript
A330-200/300 DIFFERENCES FROM A318/A319/A320/A321 (CFM56/V2500) TRAINING MANUAL PNEUMATIC THIS MANUAL IS FOR TRAINING PURPOSES ONLY AND SHOULD NOT BE USED FOR ANY OTHER PURPOSE...
A330-200/300 DIFFERENCES FROM A318/A319/A320/A321 (CFM56/V2500) TRAINING MANUAL PNEUMATIC THIS MANUAL IS FOR TRAINING PURPOSES ONLY AND SHOULD NOT BE USED FOR ANY OTHER PURPOSE THESE NOTES ARE NOT UPDATED B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL PNEUMATIC Bleed Air Distribution & Supply D/O (RR700) (3)............... 2 Engine Bleed Air Managmnt SYS Gen. D/O (RR) (3)........... 10 Engine Bleed Air Transfer System D/O (3).................... 14 Engine Bleed Air Press. Reg. SYS D/O (PW&RR) (3)........... 24 Leak Detection System D/O (3)............................. 28 G7508471 - G7UT0TU CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) TABLE OF CONTENTS Nov 21, 2008 36 - PNEUMATIC Page 1 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 1 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (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. 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). The engine bleed air systems are connected to the corresponding pneumatic manifold. G7508471 - G7UT0TU - FM36D1000000003 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 2 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 2 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D1000000003 GENERAL CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 3 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 3 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (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. Each connector contains a non-return valve and a built-in nipple. A short duct connects the HP ground connectors to the crossbleed manifold, to the left of the crossbleed valve. Once connected and switched ON, ground cart delivered pressure can be checked on the ECAM BLEED page. This pressure indication is given through the engine bleed system. CAUTION: all A/C bleed systems must be switched off before the crossbleed manifold is pressurized by the ground cart. G7508471 - G7UT0TU - FM36D1000000003 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 4 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 4 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D1000000003 HP AIR GROUND SUPPLY CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 5 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 5 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) crossbleed valve automatically opens when the APU supplies bleed APU BLEED AIR SUPPLY 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 main components of the APU bleed system are the APU bleed valve the engine bleed system). and the APU check valve. APU BLEED AND CHECK VALVES The APU bleed valve is an ON/OFF butterfly valve, spring loaded closed, with a visual position indicator installed. It is electrically controlled by a solenoid and pneumatically operated. Its muscle pressure is tapped upstream of the valve. A Fully Closed (FC)/NOT FC micro switch is installed on the valve for indicating and monitoring purposes. The check valve protects the APU from reverse flow when another source supplies bleed air at a higher pressure. APU BLEED VALVE CONTROL Once the APU BLEED P/B is set to ON, a ground signal is sent to both Bleed Monitoring Computers (BMCs). Then, the BMCs send an opening command to the Electronic Control Box (ECB) if the following conditions are met: - the APU master switch is ON, - the APU BLEED P/B is ON, - no leak is detected on the APU bleed duct, - and no leak is detected on the LH pneumatic manifold. G7508471 - G7UT0TU - FM36D1000000003 Note that these two leak conditions are not active during Main Engine Start (MES). Once the ECB receives the opening command, it energizes the bleed valve solenoid only if: - the APU runs at more than 95% of speed, - no APU shutdown is carried out, - and the altitude is lower than 23000 feet (7010 meters)during climb or 21000 feet (6400meters) during descent. As a consequence, the APU bleed valve opens, the Pressure Regulating Valves (PRVs) of the two engines automatically close and the CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 6 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 6 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D1000000003 APU BLEED AIR SUPPLY - APU BLEED AND CHECK VALVES & APU BLEED VALVE CONTROL CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 7 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 7 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) As soon as a manual control is selected, the crossbleed valve primary CROSSBLEED SYSTEM motor power supply is cut out. When the crossbleed valve selector switch is set to OPEN, it directly supplies the secondary crossbleed The crossbleed valve is an electrically controlled butterfly shut-off valve. valve motor, which opens the valve. When the crossbleed valve Two electrical motors, which work independently, are used for manual selector switch is set to CLOSE, the secondary motor closes the or automatic operation. A Fully Open (FO) or Fully Close (FC) position crossbleed valve. As in the automatic mode, the valve position is given of the valve is sent to the two BMCs by 2 micro switches. Either automatic by the 2 microswitches and shown on the ECAM BLEED page. or manual control can be selected using the crossbleed valve selector of the AIR panel. INCORRECT OPERATION AUTOMATIC CONTROL If a disagreement between the valve position and command occurs, the BMCs trigger an ECAM message and the BLEED page comes up When the crossbleed valve selector is in the AUTO position, the automatically. crossbleed valve control is carried out by the BMCs, through the primary valve motor. As soon as: - the APU BLEED P/B is ON, - the APU bleed valve is not FC, - and there is no leak detected, the BMCs send a ground signal to the crossbleed valve auto-control relay. As a consequence, the crossbleed valve auto-control relay supplies electrical power to the crossbleed valve primary motor and the crossbleed valve opens. The FO position feedback from the microswitch is indicated on the ECAM BLEED page through the BMCs. When the APU BLEED is deselected, the APU bleed valve G7508471 - G7UT0TU - FM36D1000000003 closes and, in turn, the crossbleed valve closes. The FC feedback from the second microswitch is displayed on the BLEED page. MANUAL CONTROL The manual opening control can be used in the subsequent cases: - cross supply by a ground cart, - crossbleed engine start, - or when an engine bleed system fails. CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 8 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 8 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D1000000003 CROSSBLEED SYSTEM - AUTOMATIC CONTROL... INCORRECT OPERATION CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) BLEED AIR DISTRIBUTION & SUPPLY D/O (RR700) (3) Nov 20, 2008 36 - PNEUMATIC Page 9 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 9 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) GENERAL The main air bleed sources are the engines. Air can be bled from two different stages. It is generally bled from an Intermediate Pressure (IP) stage of the IP compressor stage 8 to minimize fuel penalty. When pressure from the IP bleed port is insufficient to supply the network, air is automatically bled from the High Pressure (HP) compressor stage 6. Each engine bleed air system includes the following sub-system: - pneumatic transfer system. It selects one of the two compressor of the engine IP or HP compressor in agreement with the supplied pressure, - pressure limitation system to regulate the bleed air pressure in order to prevent overpressure, - temperature limitation system to regulate the bleed air temperature in order to prevent over temperature. G7508471 - G7UT0TU - FM36D6000000003 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 10 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 10 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D6000000003 GENERAL CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 11 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 11 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) 150°C on demand from the air conditioning system if the wing anti-ice BLEED AIR TRANSFER system is not operative (solenoid energized). Finally, bleed air is ducted to the bleed air distribution and supply The transfer from one bleed port to another is carried out using a HP network. bleed Valve (HPV) at the HP stage. The transfer depends on the available pressure and engine speeds. In the normal engine bleed air configuration, MONITORING the air is bled from the IP port at high engine speed. At low engine speed, especially during A/C descent with engines at idle, the IP port pressure The position of the valves, bleed air temperature and pressure are indicated is insufficient and the air is automatically bled from the HP port. on the ECAM bleed page. Transfer to the IP stage can be forced by closing the HPV via a solenoid incorporated in the HPV. This transfer is commanded by the Electronic Engine Controller (EEC) of the related engine. 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. 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. The valve acts as a shut-off and PRV. The PRV is fully and pneumatically operated and controlled by the thermostat solenoid. The shut-off function of the PRV through the thermostat solenoid is controlled by the corresponding BMC or by using the ENG G7508471 - G7UT0TU - FM36D6000000003 BLEED P/Bs located on the AIR panel or the engine FIRE P/B. A fully pneumatic Overpressure Valve (OPV) protects the system against overpressure. TEMPERATURE LIMITATION The temperature regulation of the bleed air system is carried out by a Fan Air Valve (FAV), which modulates fan airflow through an air-to-air heat exchanger. The FAV is controlled by the BMC through the Control Thermostat (ThC). The temperature regulation gives two temperature settings: 200°C for nominal conditions (solenoid not energized) and CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 12 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 12 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D6000000003 BLEED AIR TRANSFER... MONITORING CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR MANAGMNT SYS GEN. D/O (RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 13 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 13 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (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. HIGH PRESSURE BLEED VALVE The HPV is pneumatically operated for pressure limitation and safety. It is a spring-loaded closed shut-off valve. The HPV is electrically controlled to close by a double coil solenoid. The minimum operating pressure of the valve is 12 psi and it pneumatically regulates the pressure around 40 psi. It has a Fully Closed (FC)/NOT FC microswitch for monitoring and indicating. For maintenance purposes, the HPV has a ground test port, a mechanical position indicator and a threaded hole which lets the butterfly locked in the closed position. IP CHECK VALVE The IP check valve is a non-return valve which closes automatically to prevent HP air from re-circulating toward the IP stage when the HPV is open. G7508471 - G7UT0TU - FM36D2000000005 BLEED TRANSFERRED PRESSURE TRANSDUCER The bleed transferred pressure transducer is installed on a bracket in the engine pylon. Its pressure sense line tapping is taken downstream of the HPV. CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 14 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 14 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D2000000005 DESCRIPTION - HIGH PRESSURE BLEED VALVE... BLEED TRANSFERRED PRESSURE TRANSDUCER CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 15 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 15 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) DESCRIPTION (continued) PRESSURE TRANSFER SYSTEM It enables selection of HP compressor stage air is bled from. It includes two mains components: HP valve and IPC valves. Air is bled by the IPC or HPV depending on the available pressure and engine speeds as follows: - Normal configuration, at high engine speed air is bled from the IP 8th stage through the IPC valves. - When engines at idle or during descent, at low engine speed, the IP pressure is insufficient. Air is automatically bled from the HP 15th stage through the HP valve. The downstream pressure causes the IPC valves to close. Closing signal from: - EEC (engine parameters) - BMC (bleed systems data) through relay - ENG BLEED P/B through relay G7508471 - G7UT0TU - FM36D2000000005 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 16 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 16 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D2000000005 DESCRIPTION - PRESSURE TRANSFER SYSTEM CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 17 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 17 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) NORMAL OPERATION The IP/HP bleed transfer control is pneumatically achieved. When the IP stage pressure exceeds the HPV target value of an average of 40 psi, the HPV closes and air bleed is supplied by the IP stage. The HPV is electrically controlled close by solenoid energization by the Engine Electronic Controller (EEC) following: - an internal logic, - a Bleed Monitoring Computer (BMC) demand via a relay, - by action on the ENG BLEED P/B via a relay. The HPV position is shown on the SD BLEED page. G7508471 - G7UT0TU - FM36D2000000005 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 18 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 18 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D2000000005 NORMAL OPERATION CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 19 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 19 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) ABNORMAL HIGH PRESSURE BLEED VALVE CLOSURE An abnormal BMC closure function is used for system protection purposes or during specific operations. The BMC sends a HPV closing command to the EEC via a relay. This HPV closing command is sent any time the Pressure Regulating Valve (PRV) is commanded closed. The HPV also closes when the HP pressure is higher than 85 psi, the Wing Anti Ice (WAI) is not selected and the altitude is higher than 26000 feet (7925 meters), or when the compressor exit temperature is higher than 430 degrees Celsius and the HP pressure higher than 75 psi. If the IP/HP transfer fails, the HPV pneumatically closes when the upstream pressure is higher than 185 psi. VALVE POSITION DISAGREEMENT When the HPV is controlled open and is detected in the closed position, the BMC triggers an ECAM message and the BLEED page comes up automatically. G7508471 - G7UT0TU - FM36D2000000005 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 20 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 20 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D2000000005 ABNORMAL HIGH PRESSURE BLEED VALVE CLOSURE & VALVE POSITION DISAGREEMENT CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 21 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 21 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) MONITORING The bleed transferred pressure transducer is used for system monitoring and fault isolation regarding the PRV and HPV. An associated fault message is sent to the Central Maintenance System (CMS) for maintenance purposes. G7508471 - G7UT0TU - FM36D2000000005 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 22 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 22 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D2000000005 MONITORING CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR TRANSFER SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 23 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 23 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) the PRV. The transducer is connected to both Bleed Monitoring SYSTEM DESCRIPTION Computers (BMCs). The pressure regulating system is composed of several components: - the Pressure Regulating Valve (PRV) associated to a Thermostat control Solenoid (ThS), - the Over Pressure Valve (OPV), - the bleed regulated pressure transducer. PRESSURE REGULATING VALVE The function of the PRV is to regulate the engine bleed pressure but it does not ensure pneumatic reverse flow protection. The reverse flow protection is done by the High Pressure bleed Valve (HPV). The PRV is a butterfly type valve, pneumatically operated and electrically controlled by the ThS. The PRV operates pneumatically in relation with the associated ThS. The Ths is connected to the PRV by a pneumatic sense line and is installed in the duct downstream of the precooler exchanger. The "Fully Closed (FC)/NOT FC" position is sensed by a microswitch used for monitoring and indicating. The valve has a ground test port and a mechanical position indicator that has a threaded hole. This threaded hole lets the butterfly be locked in the closed position. G7508471 - G7UT0TU - FM36D3000000005 OVERPRESSURE VALVE The OPV protects the downstream pneumatic system if the PRV does not operate correctly (overpressure). The OPV is a pneumatically actuated valve and is normally open. Muscle pressure for valve actuation is tapped from an integral pressure port located upstream of the valve. BLEED REGULATED PRESSURE TRANSDUCER The bleed regulated pressure transducer is a silicon type transducer, linked by a pressure sense line to a pressure tapping downstream of CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 24 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 24 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D3000000005 SYSTEM DESCRIPTION - PRESSURE REGULATING VALVE... BLEED REGULATED PRESSURE TRANSDUCER CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 25 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 25 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) - if an overpressure occurs, PRESSURE REGULATION - if an over temperature occurs, - during engine start, The PRV is normally spring-loaded closed in the absence of upstream - during APU bleed supply. pressure. A minimum upstream pressure of 8 psi is necessary to open the valve. OVERPRESSURE PROTECTION The PRV regulates pneumatically the downstream static pressure to: - 52 psi maximum, If the bleed regulated pressure rises above 60 psi, the BMC detects an - 44 psi minimum. overpressure condition and closes the PRV. A warning message is The PRV will reduce the downstream static pressure by the ThS when displayed on the EWD and the BLEED page comes up automatically on the temperature downstream of the precooler exchanger is higher than the SD showing the HPV and the PRV closed in amber. 235 degrees Celsius. In addition to the overpressure electrical monitoring done by the BMC, the OPV gives a fully pneumatic back up protection in case of failure. BLEED SYSTEM ISOLATION FUNCTION The OPV is designed to start to close automatically when the upstream pressure increases above 75 psi and is fully closed at 85 psi. The valve Each engine bleed system can be isolated from the pneumatic manifold remains closed as long as the upstream pressure is higher than 52 psi (±3 in abnormal or specific conditions by closing the PRV. psi). MANUAL ISOLATION MONITORING The engine bleed system can be isolated manually from the pneumatic manifold by releasing the corresponding BLEED P/B on the AIR The bleed regulated pressure transducer is used for system monitoring panel, and therefore energizing the ThS, resulting in the PRV closure. and fault isolation regarding the PRV and OPV. An associated fault The "FC/NOT FC" microswitch indicates the position of the valve to message is sent to the ECAM and to the Central Maintenance System the BMC, which is displayed on the ECAM BLEED page. (CMS) for maintenance purposes. G7508471 - G7UT0TU - FM36D3000000005 FIRE ISOLATION If an engine fire occurs, the bleed system of the affected engine is isolated by releasing the corresponding FIRE P/B on the overhead panel, energizing the ThS. The ECAM BLEED page shows the position of the PRVs. AUTOMATIC ISOLATION The BMC can isolate automatically engine bleed air supply by energizing the ThS: - if a pylon or wing leak is detected, CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 26 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 26 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D3000000005 PRESSURE REGULATION... MONITORING CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) ENGINE BLEED AIR PRESS. REG. SYS D/O (PW&RR) (3) Nov 20, 2008 36 - PNEUMATIC Page 27 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 27 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL LEAK DETECTION SYSTEM D/O (3) GENERAL The leak detection system is divided into two sub-systems, left and right. The separation is made at the crossbleed valve level. The detection loops are located along the bleed air network. Each loop is composed of overheat sensing elements connected in series. Dual loop detection systems are installed in the wings, packs and crossbleed valve area and the APU bleed duct area. A single loop detection system is installed in the pylons. SENSING ELEMENTS The sensing elements have a solid center conductor set in an aluminum oxide insulator and are integrated in an outer tube connected to A/C ground. Eutectic salt fills the space between the outer tubing and the center conductor. Each sensing element is permanently subjected to the temperature of the compartment it protects. For any temperature higher than a preset value and applied to a small length of the element, the resistance of the eutectic salt rapidly decreases and continuity is established between the tube and the conductor. The center conductor is grounded. G7508471 - G7UT0TU - FM36D5000000004 CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) LEAK DETECTION SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 28 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 28 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D5000000004 GENERAL & SENSING ELEMENTS CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) LEAK DETECTION SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 29 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 29 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL LEAK DETECTION SYSTEM D/O (3) The FAULT legend of APU BLEED P/BSW comes on if a leak is detected BMC LOOP MONITORING in the APU bleed air system. The FAULT legend of the BLEED P/BSWs remains on as long as the Each Bleed Monitoring Computer (BMC) monitors four detection loops: hot air leak continues. - one in the engine pylon, - one in the LH wing and above the LH pack, - one in the RH wing and above the RH pack, - one APU loop. Both BMCs exchange loop status data via ARINC buses. BMC 1 sends an APU leak discrete signal to BMC 2. If one BMC operation is lost, the other BMC takes over for wing/pack and APU leak monitoring but the corresponding pylon leak detection is lost. LEAK DETECTION OPERATION As soon as a leak occurs, the hot air increases the temperature of the affected area detection loops and thus modifies their resistance. This resistance change is detected by the corresponding BMC which isolates the affected system by closing the relevant valves. During APU bleed operation, if a hot air leak is detected, a closure demand is sent by the BMC to the Electronic Control Box (ECB) which does the APU bleed valve closure control, except during Main Engine Start (MES) sequence. G7508471 - G7UT0TU - FM36D5000000004 If the APU bleed valve is commanded closed and the crossbleed valve selector is in the AUTO mode, the crossbleed valve closes too. As soon as a leak is detected, a warning message is displayed on the EWD. In addition, the AIR panel BLEED P/BSWs are used to indicate leaks and their FAULT legend comes on in amber. The FAULT legend of engine 1 BLEED P/BSW comes on if a leak is detected in the left pneumatic manifold. The FAULT legend of engine 2 BLEED P/BSW comes on if a leak is detected in the right pneumatic manifold. CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) LEAK DETECTION SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 30 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 30 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330-200/300 TECHNICAL TRAINING MANUAL G7508471 - G7UT0TU - FM36D5000000004 BMC LOOP MONITORING & LEAK DETECTION OPERATION CMQ - SA family to A330-200/300 - T1+T2 (Lvl 2&3) (RR Trent 700) LEAK DETECTION SYSTEM D/O (3) Nov 20, 2008 36 - PNEUMATIC Page 31 B1/B2_A330_DIFF_FR_A320 DVIATION TRAINING SERVICES 31 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019
