A330-200/300 Fuel Inerting Training Manual PDF
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Uploaded by EminentAspen
UAntwerp
2019
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Summary
This document is a training manual for fuel inerting systems. It details the differences between A330-200/300 and other aircraft models, including the CFM56/V2500 engine. The manual emphasizes that it is for training purposes only.
Full Transcript
A330-200/300 DIFFERENCES FROM A318/A319/A320/A321 (CFM56/V2500) TRAINING MANUAL FUEL INERTING 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 FUEL INERTING THIS MANUAL IS FOR TRAINING PURPOSES ONLY AND SHOULD NOT BE USED FOR ANY OTHER PURPOSE THESE NOTES ARE NOT UPDATED B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FUEL INERTING Fuel Tank Inerting System D/O (3)........................... 2 Conditioned Service Air System D/O (3)...................... 12 Inert Gas Generation System D/O (3)........................ 28 FTIS Indicating (2)....................................... 64 GCL13151 - GEHT0M0 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) TABLE OF CONTENTS Apr 18, 2013 47 - FUEL INERTING Page 1 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 1 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FUEL TANK INERTING SYSTEM D/O (3) GENERAL The Fuel Tank Inerting System (FTIS) has two primary systems, located on the left hand side of the belly fairing underfloor between frames (FR) 40 and FR44. The weight of all the system is 100 kg (220.5 lbs) for A330, A340-200 and A340-300, and 120 kg (264.6 lbs) for A340-500/600. On the left hand side of the air conditioning Pack 1, there is the Inert Gas Generating System (IGGS) pallet. The IGGS contains Air Separation Modules (ASMs), different valves and sensors for the temperature, pressure, and oxygen concentration. The primary function of the IGGS pallet is to separate the oxygen and the nitrogen. On the right hand side, there is the Cooled Service Air System (CSAS). The system uses the ram air which is first used for the air conditioning system. The system has a small heat exchanger installed upstream of the classical heat exchanger, a bypass shut-off valve, pressure and temperature sensors. The two systems are part of different ATA chapters: - IGGS is ATA 47 and is supplied by PARKER, - CSAS is ATA 21-58 and is supplied by LIEBHERR. GCL13151 - GEHT0M0 - FM47D1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 2 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 2 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D1000000001 GENERAL MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 3 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 3 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FUEL TANK INERTING SYSTEM D/O (3) SAFETY PRECAUTION The FTIS supplies Nitrogen Enriched Air (NEA), which is a gas with low oxygen content. The NEA can cause an asphyxiation risk to personnel if the gas is contained in confined spaces. GCL13151 - GEHT0M0 - FM47D1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 4 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 4 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D1000000001 SAFETY PRECAUTION MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 5 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 5 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FUEL TANK INERTING SYSTEM D/O (3) The air then goes into the ASMs, which separate the oxygen and the SYSTEM ARCHITECTURE nitrogen from the air. The Oxygen Enriched Air (OEA) is released overboard while a single The FTIS is made of 2 primary systems: device measures the air pressure (P3) and the oxygen concentration (O1) - The CSAS, and sends these signals to the ICU. - And the IGGS. The NEA is sent to the tank through a Double Flow and Shut-Off Valve The hot air comes from the engines to the CSAS Isolation Valve (CIV), (DFSOV). also called V1. The DFSOV is electrically controlled by the ICU and pneumatically The CIV is controlled by the CSAS Control Unit (CCU) which will get operated to adjust the air flow which goes into the tank. the position signal as feedback. The valve only opens if it is energized and if pressure is available. In The valve only opens if it is energized and if pressure is available. In other conditions, it is closed (fail safe closed). other conditions, it is closed (fail safe closed). A drain plug is installed after the DFSOV and is used for maintenance An ozone converter is installed in the line. tests. Then this air is cooled by the heat exchanger which uses the cooling air The air goes through a Dual Flapper Check Valve (DFCV) installed on flow of the air conditioning system. the skin of the upper part of the center tank, before it goes into the tank. If necessary, the temperature can be also increased by the air Bypass Valve (BPV), also called V2. The BPV has a stepper motor which is controlled by the CCU. Downstream of the BPV, a temperature sensor (T1) and a pressure sensor (P1) are installed and send signals to the two CCU channels. The CCU is the master controller used for system interrogation through the Multipurpose Control and Display Unit (MCDU). The air from the CSAS goes into the pallet through the Isolation Gate GCL13151 - GEHT0M0 - FM47D1000000001 Valve (IGV), also called V3. The IGV is electrically controlled by the IGGS Control Unit (ICU) and pneumatically operated. The valve only opens if it is energized and if pressure is available. In other conditions, it is closed (fail safe closed). Then the air goes through a Double Ultra Low Particulate Air Filter (D-ULPA). The filter has a drain port which drains directly in the belly fairing. Downstream of the filter, a temperature sensor (T2) and a pressure sensor (P2) are installed and send signals to the two ICU channels. MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 6 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 6 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D1000000001 SYSTEM ARCHITECTURE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 7 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 7 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FUEL TANK INERTING SYSTEM D/O (3) FTIS OPERATIVE CONDITIONS Different conditions are necessary for the operation of the system. The primary condition is that the aircraft must be in flight. The Fuel Tank Inerting System (FTIS) does not operate on the ground. GCL13151 - GEHT0M0 - FM47D1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 8 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 8 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D1000000001 FTIS OPERATIVE CONDITIONS MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 9 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 9 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D1000000001 FTIS OPERATIVE CONDITIONS MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FUEL TANK INERTING SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 10 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 10 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) GENERAL VIEW The primary component of the Conditioned Service Air System (CSAS) is the Temperature Control Module (TCM). The TCM includes a heat exchanger and a Bypass Valve (BPV). GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 12 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 11 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 GENERAL VIEW MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 13 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 12 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) CSAS ISOLATION VALVE (V1) The CSAS Isolation Valve (CIV) is a butterfly valve that is controlled by a solenoid, and pneumatically operated. The CIV lets the hot bleed air flow to the TCM. Without bleed air pressure or without electrical power, the valve closes automatically and stops the operation of the system. The isolation valve is operated by the CSAS Control Unit (CCU). The CIV has a locking mechanism (manual override) used to lock the valve during the tests, to make sure that it stays closed and isolates possible leaks. It is not necessary to close the CIV for aircraft dispatch under Master Equipment List (MEL). GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 14 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 13 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 CSAS ISOLATION VALVE (V1) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 15 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 14 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 CSAS ISOLATION VALVE (V1) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 16 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 15 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) OZONE CONVERTER The ozone converter is installed between the CIV and the Heat Exchanger. The ozone converter uses a catalytic process to decrease the ozone concentration in the air supplied to the TCM. This gives protection to the Air Separation Modules (ASMs) fibers. GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 18 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 16 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 OZONE CONVERTER MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 19 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 17 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) TEMPERATURE CONTROL MODULE The TCM includes: - A CSAS heat exchanger which decreases the temperature of the hot bleed air from the pneumatic system, - A bypass valve, which adds hot bleed air to the cold air from the heat exchanger to increase the temperature if necessary, - A temperature sensor (T1) which monitors the temperature of the conditioned air that flows to the Inert Gas Generating System (IGGS), - A pressure sensor (P1) which monitors the pressure of the conditioned air that flows to the IGGS. GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 20 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 18 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 TEMPERATURE CONTROL MODULE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 21 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 19 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) TEMPERATURE SENSOR (T1) The temperature sensor (T1) is installed in the bleed air duct. It is a dual sensor which has analog and digital probes. It monitors the conditioned air and transmits the signals to the CCU. The CCU will close all the valves when the temperature becomes too high. GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 22 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 20 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 TEMPERATURE SENSOR (T1) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 23 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 21 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) PRESSURE SENSOR (P1) The pressure sensor (P1) is installed in the bleed air duct. It is a single sensor which monitors the conditioned air and transmits the signals to the two CCU channels. GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 24 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 22 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 PRESSURE SENSOR (P1) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 25 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 23 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL CONDITIONED SERVICE AIR SYSTEM D/O (3) CSAS CONTROL UNIT The CCU is installed in the avionics bay. The CCU communicates with the IGGS Control Unit (ICU) and monitors the CSAS parameters such as the Fuel Tank Inerting System (FTIS) inlet temperature and pressure. The CCU can stop the system if necessary. NOTE: The CCU stops when the internal temperature becomes too high. The CCU sends the faults in flight to the Centralized Maintenance Computer (CMC). The faults on ground are also sent to the CMC in flight if the fault is not corrected. GCL13151 - GEHT0M0 - FM47DNCSAS00001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 26 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 24 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47DNCSAS00001 CSAS CONTROL UNIT MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) CONDITIONED SERVICE AIR SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 27 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 25 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) GENERAL VIEW The Inert Gas Generating System (IGGS) is contained in an IGGS pallet assembly. The primary components of the IGGS are the Air Separation Modules (ASMs). The IGGS also has valves, temperature and pressure sensors, a filter, and an oxygen concentration sensor. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 28 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 26 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 GENERAL VIEW MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 29 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 27 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 GENERAL VIEW MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 30 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 28 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) ISOLATION GATE VALVE The Isolation Gate Valve (IGV) is a pneumatic gate valve installed downstream of the IGGS pallet inlet and upstream of the filter. This valve is used to isolate the IGGS from the Conditioned Service Air System (CSAS). During a CSAS over-temperature, the IGV does not let hot air (more than 85°C (185°F)) go into the ASM and be in contact with fuel or fuel vapors. The valve includes: - A solenoid, - A pressure relief valve, - A position switch, - An actuation pressure stem, - A visual indication stem. The valve is controlled to close when there is: - Over-temperature (Temp > 85°C) detected by temperature sensor T2, - Over-pressure (pressure > 60 psig) detected by pressure sensor P2, - Under-pressure (pressure < 15 psig) detected by pressure sensor P2, - A CSAS Control Unit (CCU) signal that stops the FTIS. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 32 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 29 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 ISOLATION GATE VALVE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 33 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 30 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 ISOLATION GATE VALVE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 34 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 31 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) D-ULPA FILTER The Double Ultra Low Particle Air (D-ULPA) Filter is installed immediately downstream of the IGV. Its function is to remove all pollutions, debris or droplets which can be mixed with the air that comes from the CSAS and which can cause damage to the ASMs fibers. The D-ULPA filter assembly includes a manifold, a bowl, and a disposable filter cartridge. The manifold is attached to the pallet and has an inlet port and an outlet port. The bowl has a drain port. The unit housing design does not have a service life limit. The replacement interval of the filter cartridge is 7,000 Flight Hours (FHs). During maintenance, it is only necessary to replace the internal filter element. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 36 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 32 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 D-ULPA FILTER MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 37 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 33 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 D-ULPA FILTER MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 38 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 34 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) TEMPERATURE SENSOR (T2) The primary function of the IGGS temperature sensor (T2) is to prevent the injection of hot gases from the CSAS into the fuel tank. It prevents damage caused to the ASMs by an over-temperature condition. If the temperature is higher than the pre-determined detection threshold, the IGGS Control Unit (ICU) isolates the system. T2 also supplies a temperature reading in support of the system health monitoring. To do this, it uses a sampling from the oxygen sensor. T2 has two probes to measure the temperature of the airflow that comes from the CSAS. Temperature measurements from one probe are monitored by the analog controller part and measurements from the second probe are managed in the digital controller part. These two probes can control the system to close if an over-temperature is detected. PRESSURE SENSOR (P2) The IGGS pressure sensor (P2) is installed between T2 and the ASMs inlet. This sensor monitors the IGGS and detects over-pressure and under-pressure conditions. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 40 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 35 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 TEMPERATURE SENSOR (T2) & PRESSURE SENSOR (P2) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 41 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 36 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) AIR SEPARATION MODULE The ASMs are the primary components of the IGGS. The ASM is a semi-permeable hollow-fiber membrane bundle contained in a pressure containment canister. This canister is a cylinder with 3 ports. The fibers are parallel to the axis of the cylinder, and connect the air inlet with the Nitrogen Enriched Air (NEA) outlet. The outer side of the fiber communicates with the Oxygen Enriched Air (OEA) outlet. Thus, the gases go through the fiber bundle and then go out of the canister through the OEA outlet. Most of these gases are oxygen, carbon dioxide and vapors of water. Nitrogen molecules will flow directly from the air inlet to the NEA outlet because they are bigger than the permeable fiber walls. NOTE: There are 2 ASMs on the A330 and A340-200/300, and 3 on the A340-500/600. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 42 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 37 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 AIR SEPARATION MODULE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 43 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 38 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) OXYGEN AND PRESSURE SENSORS (O1 AND P3) The oxygen sensor (O1) is installed immediately downstream of the ASMs. The sensor has an oxygen-sensitive capsule to measure the oxygen concentration in the NEA flow for system monitoring. The oxygen sensor also measures the NEA pressure. The sensor sends the signals to the ICU, which then sends fault data to the Centralized Maintenance System (CMS). The oxygen sensor is started one time in each flight during the cruise flight phase. During the warm-up period, the unit does an automatic Power-up Built-In Test Equipment (P-BITE) test. Fault indications are inhibited before the end of the warm-up period. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 44 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 39 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 OXYGEN AND PRESSURE SENSORS (O1 AND P3) MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 45 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 40 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) DUAL FLOW SHUT-OFF VALVE The Dual Flow Shut-Off Valve (DFSOV) is used to isolate the IGGS from the center fuel tank when necessary. The DFSOV is closed when the FTIS is not in operation. In operation, the DFSOV closes if: - The NEA flow pressure becomes less than 15 psi (1.0342 bar), - The NEA flow pressure becomes more than 60 psi (4.1369 bar), - And/or the NEA flow temperature becomes more than 85°C (185.00°F). The ICU supplies 28V DC power to the two DFSOV solenoids. Each solenoid operates a DFSOV poppet which causes the ICU to open the DFSOV and to adjust the NEA flow to the fuel tank. The valve includes position indication switches (one for each poppet). The switches are used by the ICU to supply DFSOV status information for system monitoring and fault detection. The valve also has a mechanical visual position indicator on each poppet to help line maintenance during the troubleshooting of system anomalies when the valve is installed on the aircraft. The valve is failsafe in the closed position. In normal operation, it closes when there is low upstream pressure or a defective solenoid. When closed, the valve prevents all upstream fuel leakage with a maximum of 20 psig back-pressure. GCL13151 - GEHT0M0 - FM47D2000000001 There are four operational modes: - Closed position => A/C on ground, - Low-flow position => During climb and cruise, - Mid-flow position => During approach, - And high-flow position => During descent. MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 46 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 41 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 DUAL FLOW SHUT-OFF VALVE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 47 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 42 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 DUAL FLOW SHUT-OFF VALVE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 48 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 43 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) FTIS PIPE ROUTING The NEA pipe starts from the IGGS pallet and then goes behind the mixer unit in the rear part of the forward cargo compartment. In this area, the pipe is made of four aluminum pipe segments. The pipe goes on top of the center tank and then to the inlet of the tank. This entrance is below the cabin floor. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 50 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 44 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 FTIS PIPE ROUTING MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 51 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 45 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) DUAL FLAPPER CHECK VALVE The Dual Flapper Check Valve (DFCV) is installed downstream of the pallet, on top of the center tank. This valve stops reverse flow if necessary (from the NEA outlet to the ASMs) and prevents a fuel leak out of the tank or upstream into the IGGS. The valve has a test port which can be used when there are leaks or during the test. When the DFCV is installed, a pressure test must be done (See MPD 470000-05-1 at 12,000 FHs). IN-TANK HOUSING The In-Tank Housing (ITH) is installed in the center tank, immediately below the DFCV. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 52 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 46 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 DUAL FLAPPER CHECK VALVE & IN-TANK HOUSING MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 53 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 47 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) - Total Air Temperature (TAT), IGGS CONTROL UNIT - Corrected Average Static Pressure, - Altitude Rate, The ICU is installed in the avionics compartment, between FR11 and - And Computed Airspeed signals. FR12, on the top of the Nose Landing Gear (NLG) bay. There is no The FCMCs send data to the ICU about fuel density, center tank fuel airflow around the ICU. The ICU has a protection which causes it to stop quantity, and FCMC labels. when there is an internal over-temperature. These signals are used to know the volume of fuel in the center tank. The ICU and CCU automatically control the FTIS without pilot action. The IGGS stops (valves controlled to the closed position) when the The ICU has 2 channels and communicates with different computers: volume of fuel in the center tank is 95% of the maximum fuel level, which - The CCU, which is the master, causes all valves to close. The system starts again when the fuel quantity - The Air Data/Inertial Reference Unit 1 (ADIRU1) and ADIRU 3 for becomes less than 90% of the maximum fuel level. redundancy, If the communication stops between the ICU and the FCMCs, the valves - The Fuel Control and Monitoring Computers (FCMCs), close for safety reasons. If there are no communications from the FCMCs - The Flight Data Interface Management Unit (FDIMU). for more than 120 seconds, the ICU sends a fault report. The ICU stops The IGGS operation is fully automatic and controlled by the ICU. the recording of the fault when FCMC communication starts again. The ICU receives all signals from the valves and sensors, and does the The FTIS must meet very strict safety requirements. necessary computations to monitor and control the IGGS and for IGGS The system has different safety functions, with all necessary redundancies. health monitoring. These functions are: The primary functions of the ICU are: - To make sure that air at temperatures higher than 85°C (185°F) does - To monitor the health of the IGGS equipment (but not the DFCV), not get in contact with fuel or fuel vapors, - To control the NEA flow mode (low, high or mid), - To make sure that no fuel goes into the ASMs or farther upstream. - To give over-temperature protection (if there is a failure of the CSAS), The ICU and CCU have digital and analog sections with which the FTIS - To give IGGS over-pressure protection (this is not a fuel tank GCL13151 - GEHT0M0 - FM47D2000000001 can be stopped when a critical fault is detected. overpressure protection). For each unit, a critical fault detected by one of the sections causes a fault - To report the IGGS state to the CCU. to be logged to the other section. The CCU is used for communication between the ICU, the Centralized The digital latched fault can be erased by a satisfactory maintenance Maintenance System (CMS), the Flight Warning System (FWS) and the procedure done through the CMS. FDIMU. The communication between the two units also gives the state The ICU analog latch is reset only by a power cycle. of each system (e.g. if the CSAS stops because of an over-temperature condition, the CCU will tell the ICU that the system is stopped) and is FUEL BACKFLOW PROTECTION used to compare the sensor readings that come from the two systems. The FDIMU records communication between the CCU and the ICU to There are three different protections in the FTIS to prevent fuel/fuel vapor monitor the FTIS performance. ingestion from the fuel tanks: The ADIRU1 (and ADIRU3 for redundancy) send these data to the ICU: MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 54 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 48 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL - The valves that will close when 'Low pressure' is detected by the ICU through the pressure sensor, - The DFCV, - The IGV and the DFSOV, which are pneumatic valves. If the pressure in the IGGS is not sufficient, these valves close even if they continue to receive an 'ON' command. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 55 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 49 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 IGGS CONTROL UNIT & FUEL BACKFLOW PROTECTION MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 56 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 50 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 IGGS CONTROL UNIT & FUEL BACKFLOW PROTECTION MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 57 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 51 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) The ICU will latch this fault that will be erased by a power cycle followed OVER-TEMPERATURE PROTECTION by a satisfactory MCDU BITE test. The air over-temperature is prevented by the ICU, the temperature sensors (T1 and T2), the IGV and the DFSOV. The ICU has digital and analog sections. If a failure occurs in the digital section, the analog part is used as a back-up protection. The ICU digital section controls the valves to close when T1 detects an air temperature equal to or higher than 120°C. The ICU will latch this fault that will be erased by a satisfactory BITE test. The analog section also controls the valves to close when T1 detects an air temperature equal to or higher than 125°C. The ICU will latch this fault that will be erased by a power cycle followed by a satisfactory MCDU BITE test. The ICU digital section controls the valves to close in these conditions: - When T2 detects an air temperature equal to or higher than 85°C, the IGGS stops immediately. The ICU will latch this fault that will be erased by a satisfactory BITE test. - When T2 detects an air temperature between 75°C and 85°C for 2 minutes, the IGGS stops and the fault will be latched. - When T2 detects an air temperature between 66°C and 75°C for 1 minute, the IGGS will change to mid-flow mode if it was in high-flow. GCL13151 - GEHT0M0 - FM47D2000000001 If the condition continues for 1 minute more, the IGGS changes to low-flow mode. If the condition continues again for 3 minutes, the IGGS stops and the fault will be latched. NOTE: This sequence is the longest possible shutdown-time for ASM supply temperatures between 66°C and 75°C. If the IGGS is already in MID or LOW flow when the incorrect temperature is detected, a shorter sequence will be applied as applicable. - When T2 detects an air temperature equal to or higher than 90°C, the IGGS stops immediately. MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 58 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 52 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 OVER-TEMPERATURE PROTECTION MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 59 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 53 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) TESTS For FTIS maintenance, there are 6 tests to do. Refer to the AMM tasks for applicable instructions and values. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 60 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 54 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 TESTS MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 61 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 55 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL INERT GAS GENERATION SYSTEM D/O (3) MAINTENANCE TIPS - Put leakage detection fluid on all connections that can have a leak. - Use a manometer to pressurize to 4.1 bar (58.6 psi). - Make sure that there are no signs of leakage other than the permitted leaks. NOTE: - Permitted leaks: The leakage is permitted if the bubbles in the solutions that you applied before on the connections stay permanently. It is also permitted if bubbles break after a time. - Not permitted leaks: The leakage is not permitted if the bubbles do not stay around the coupling, because the leak blows the solution away from the coupling. GCL13151 - GEHT0M0 - FM47D2000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 62 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 56 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47D2000000001 MAINTENANCE TIPS MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) INERT GAS GENERATION SYSTEM D/O (3) Apr 16, 2013 47 - FUEL INERTING Page 63 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 57 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FTIS INDICATING (2) OPERATIONAL IMPACT The FTIS failure messages are only shown in flight phases 1 and 10. The Fuel Tank Inerting System (FTIS) can stay inoperative during 10 days renewable one time by the European Aviation Safety Agency (EASA). No actions from the pilots are necessary during flight and there are no maintenance actions related to the Minimum Equipment List (MEL) (no valves to close or plugs to remove). The system can be reset with the Multipurpose Control and Display Unit (MCDU) or with the Circuit Breakers (C/Bs) (C/Bs pulled). GCL13151 - GEHT0M0 - FM47I1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 64 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 58 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47I1000000001 OPERATIONAL IMPACT MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 65 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 59 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FTIS INDICATING (2) STATUS MAINTENANCE PAGE Most components or system failures detected by the Inert Gas Generation System (IGGS) Control Unit (ICU) or the Conditioned Service air System (CSAS) Control Unit (CCU) immediately cause a latching of the system. When a failure occurs, the CSAS Isolation Valve (CIV), the Dual Flow Shut-Off Valve (DFSOV) and the Isolation Gate Valve (IGV) close automatically. GCL13151 - GEHT0M0 - FM47I1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 66 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 60 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47I1000000001 STATUS MAINTENANCE PAGE MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 67 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 61 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FTIS INDICATING (2) INERTING MENU IN THE MCDU To get access to the INERTING menu (ATA 47) in the MCDU, select the CMS page. Select SYSTEM REPORT/TEST. Then select NEXT PAGE to go to the fifth page, and select INERTING. GCL13151 - GEHT0M0 - FM47I1000000001 MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 68 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 62 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL GCL13151 - GEHT0M0 - FM47I1000000001 INERTING MENU IN THE MCDU MECHANICAL & AVIONICS COURSE - T1+T2 (LVL 2&3) FTIS INDICATING (2) Apr 16, 2013 47 - FUEL INERTING Page 69 B1/B2_A320_DIFF_FR_A320 DVIATION TRAINING SERVICES 63 REV. 1 FOR TRAINING PURPOSES ONLY DATE: 01.06.2019 A330 RR Trent 700 TECHNICAL TRAINING MANUAL FTIS INDICATING (2) INERTING MENU IN THE MCDU (continued) SPECIFIC DATA T
