47 fuel tank inerting

Airbus A319/A320 Training Manual

1 47-00-00 REV. MAR 2013

ATA 47 FUEL TANK INERTING

SYSTEM


2 47-00-00 REV. MAR 2013

GENERAL

The Fuel Tank Inerting System (FTIS) reduces the amount of oxygen in the air within the center tank. The FTIS is divided into:

the Inert Gas Generation System (IGGS),

the Conditioned Service Air System (CSAS),

the maintenance/test facilities. The FTIS interfaces with the following systems:

Fuel System,

Bleed air supply system,

Environmental Control Systems,

Centralized Fault Display System (CFDS) / ECAM.


3 47-00-00 REV. MAR 2013

GENERAL


4 47-00-00 REV. MAR 2013

FUEL TANK INERTING SYSTEM FUNCTIONS

Fuel tank flammability is possible only if the three elements get together: fuel vapor, ignition source and oxygen. To reduce the fuel tank flammability, the fuel tank inerting system reduces the concentration of oxygen in the center tank only.


5 47-00-00 REV. MAR 2013

FUEL TANK INERTING SYSTEM FUNCTIONS


6 47-00-00 REV. MAR 2013

FUEL TANK INERTING SYSTEM GENERAL VIEW

The Fuel Tank Inerting System (FTIS) is composed of two sub-systems:

The Conditioned Service Air System (CSAS),

The Inert Gas Generation System (IGGS). The CSAS takes hot air from the bleed air system and cools down the air to a level compatible with the IGGS sub-system. The CSAS is composed of:

The Conditioned service air system Controller Unit (CCU), which performs the system control and health monitoring BITE and interfaces with the FWS and CFDS.

A CSAS isolation valve, which protects the system in case of low pressure, over pressure or over temperature,

A heat exchanger to cool down the air. The IGGS uses an Air Separation Module (ASM) to filter the conditioned air stream, creating Nitrogen Enriched Air (NEA) and Oxygen Enriched Air (OEA). The OEA is sent overboard. The Dual Flow Shut Off Valve (DFSOV) controls the NEA flow to the center tank and enables the system to switch between (low/middle/high NEA flows) and isolates the IGGS from the fuel tank. The IGGS controller provides system control and health monitoring/BITE. The IGGS isolation valve is a solenoid valve. It is spring-loaded closed. During operation the IGGS Controller Unit (ICU) controls the valve to open, to let conditioned air from CSAS to the IGGS. It closes in case of too low pressure and/or overtemperature air, coming from the heat exchanger.


7 47-00-00 REV. MAR 2013

FUEL TANK INERTING SYSTEM GENERAL VIEW


8 47-00-00 REV. MAR 2013

INERT GAS GENERATION SYSTEM

The Fuel Tank Inerting System (FTIS) includes two sub-systems:

The Conditioned Service Air System (CSAS),

The Inert Gas Generation System (IGGS). The IGGS uses an Air Separation Module (ASM) to divide the conditioned air stream into Nitrogen Enriched Air (NEA) and Oxygen Enriched Air (OEA). The OEA is sent overboard. The Dual Flow Shut Off Valve (DFSOV) controls the NEA flow to the center tank, lets the system change between low/middle/high NEA flow and isolates the IGGS from the fuel tank. The IGGS controller supplies system control and health monitoring/BITE. The IGGS isolation valve is a solenoid valve. It is spring-loaded closed. During operation, the IGGS Controller Unit (ICU) controls the valve to open, to let conditioned air from CSAS to the IGGS. It closes if conditioned air pressure is too low and/or excessively hot from the heat exchanger.


9 47-00-00 REV. MAR 2013

IGGS - GENERAL


10 47-00-00 REV. MAR 2013

SYSTEM DESCRIPTION

To inert the fuel center tank and to control and monitor the IGGS, the IGGS includes:

one IGGS Isolation Gate Valve

one D-ULPA (Double ultra low particle) filter,

one temperature sensor,

two pressure transmitters (inlet and outlet of the ASM)

one oxygen sensor at the outlet of the ASM,

one Air Separation Module (ASM),

one Dual Flow Shut Off Valve (DFSOV),

one dual flapper check valve,

one IGGS Controller Unit (ICU).

NORMAL OPERATION

The bleed air comes from the CSAS and it is filtered by the D-ULPA filter to keep the ASM inlet clean, without hydrocarbons and dust. Downstream of the D-ULPA filter, one temperature sensor and one pressure sensor send air parameters to the ICU. The ASM, which is the core of the IGGS, removes oxygen and sends NEA to the fuel center tank. The OEA is sent overboard through an outlet on the HPGC door. Downstream of the ASM, an oxygen sensor measures the oxygen rate to prevent a high oxygen concentration in the center tank. The oxygen sensor has a pressure sensing capability when it is energized and thus it prevents over-pressure in the center tank. The DFSOV controls the NEA flow to the fuel tank and lets the system change between low/mid/high NEA flow in relation to the flight phases. The DFSOV also isolates the IGGS from the fuel tank if an abnormal operation occurs. A Dual Flapper Check Valve makes a double barrier to the possible back-flow of fuel.


11 47-00-00 REV. MAR 2013

SYSTEM DESCRIPTION AND OPERATION


12 47-00-00 REV. MAR 2013

ABNORMAL OPERATION

If there is overpressure or overtemperature, the ICU de-energizes the IGGS Isolation Gate Valve solenoid to close the IGGS Isolation Gate Valve. If the oxygen sensor senses an oxygen concentration higher than 12%, the ICU de-energizes the IGGS Isolation Gate Valve solenoid and the DFSOV solenoid to close the IGGS Isolation Gate Valve and the DFSOV.


13 47-00-00 REV. MAR 2013

ABNORMAL OPERTION


14 47-00-00 REV. MAR 2013

COMPONENT DESCRIPTION

AIR SEPERATION MODULE (ASM)

The ASM is the core of the Inert Gas Generation System. It removes oxygen from the compressed air stream. It makes Nitrogen Enriched Air (NEA) and Oxygen Enriched Air (OEA). The NEA is sent to the fuel tank and the OEA is sent overboard. An ASM is a semi-permeable hollow-fiber membrane bundle contained in a pressure containment canister.


15 47-00-00 REV. MAR 2013

AIR SEPARATION MODULE


16 47-00-00 REV. MAR 2013

DUAL FLAPPER CHECK VALVE

NEA is supplied from the IGGS to the Fuel tank by the distribution pipe and nozzle. A twin check valve system prevents fuel ingress from the fuel tank back to the IGGS. The system is contained in one housing that includes two in-line flapper type check valves (Dual flapper check valve). These valves are on the outer side of the fuel tank.


17 47-00-00 REV. MAR 2013

DUAL FLAPPER CHECK VALVE


18 47-00-00 REV. MAR 2013

ICU INTERFACES

The ADIRU 1 supplies Standard Altitude, True Airspeed, Total Air Temperature and Altitude Rate signals to the ICU. The CCU makes the communication possible between the IGGS controller, the CFDIU and the FWS. The communication between the two controllers is also used to give the condition of each system. For example, if the CSAS stops because of an overtemperature scenario, the CCU will tell the ICU that the system is closed and they will compare the readings of the sensors that come from the two systems.


19 47-00-00 REV. MAR 2013

ICU INTERFACES


20 47-00-00 REV. MAR 2013

OPERATION/CONTROL AND INDICATING

The flight crew has no operational interaction with the system. When the aircraft is on ground the FTIS does not operate, unless it is necessary for maintenance operations. During maintenance operations, there are two interactive BITE modes:

Interactive BITE without bleed air, and

Interactive BITE with bleed air from Auxiliary Power Unit (APU) or ground supply, air-conditioning Pack1 ON and Pack2 OFF.

During aircraft flight, the FTIS operates automatically when the ICU receives a GO signal from the CSAS. This occurs only with the subsequent conditions:

Bleed air available through Engine 1 Pressure Regulating Valve (PRV) open, or Engine 2 PRV open and Cross Feed Valve open;

Weight On Wheels (WOW) is FALSE: ESS LH L/G COMPRESSED & NORM LH L/G COMPRESSED;

Environmental Control System (ECS): Pack 1 in operation Flow Control Valve (FCV) is not Fully Closed, or Pack 2 in operation FCV is not Fully Closed and Pack 1 Push Button (P/B) is OFF and Cross Bleed Valve is open,

IGGS Latch status: not latched;

IGGS Total Average Air Temperature is lower than 47 deg. C (116.60 deg. F);

Transit to idle is true;

ENG 1 FIRE = 'no fire'. The FTIS has three NEA flow modes:

Low, during climb and cruise phases;

Mid, during approach phase;

High, during usual descent phase. The ICU interfaces with the CCU, and the two monitor environmental conditions independently from each other. If one of the two finds an incorrect condition, they will stop safely. The ICU has digital and analog lanes: Digital, that controls the system and stop functions.

Temperature stop limits are as follows:

IGGS temperature more than 66 deg. C (150.80 deg. F) and less than 75 deg. C (167.00 deg. F). In these conditions, if the IGGS operates with a high flow, it changes to mid flow after one minute; if the IGGS operates with a mid flow, it changes to low flow after one minute; if the IGGS operates with a low flow, it stops after three minutes.

IGGS temperature more than 75 deg. C (167.00 deg. F) and less than 85 deg. C (185.00 deg. F), it stops after two minutes.

IGGS temperature of 85 deg. C (185.00 deg. F) and pressure threshold is 60 psi (4.1369 bar). Analog, that gives an independent over-temperature stop. Temperature stop limit is 90 deg. C (194.00 deg. F) instantaneous.

To do the digital and analog latch reset, the aircraft must be on ground. The digital latch reset occurs after a successful interactive BITE, and the analog latch reset after power cycle. The ICU controls and monitors the IGGS, and does BITE functions that monitors the system health. During the cruise flight phase, the ICU monitors one time the IGGS health. The Gross-Failure Detection Lookup-Tables compares its data with these inputs, to find if the ASM operates correctly. If the ASM does not operate correctly again and again three times, the ICU sends a failure message to the CCU, and the CCU gives an Electronic Centralized Aircraft Monitoring (ECAM) Status Message.. to the Centralized Fault Display Interface Unit (CFDIU), at the end of the flight, for maintenance functions.


21 47-00-00 REV. MAR 2013

FTIS FAILURE INDICATION ON STATUS PAGE


22 47-00-00 REV. MAR 2013

MAINTENANCE/TEST FACILITIES

The CCU interfaces with the ICU. Both controllers monitor the operational conditions independently. The CSAS receives temperature information from the ICU and, if necessary, adjust the Temperature. The Centralized Fault Display Interface Unit (CFDIU) gives test functions of the CCU, available through the MCDU in the cockpit. The CCU also has BITE functions of the ICU.

POWER UP TEST

When the FTIS energizes the IGGS system, the ICU does the subsequent tests:

ICU internal BITE,

ARINC communication,

isolation valve status,

DFSOV status,

temperature sensor status,

pressure sensor status.


23 47-00-00 REV. MAR 2013

MAINTENANCE/TEST FACILITIES


24 47-00-00 REV. MAR 2013

ACCESS FTIS SYSTEM BITE

When the aircraft is on ground the FTIS does not operate, unless it is necessary for maintenance operations. During maintenance operations, there are two interactive BITE modes:

Interactive BITE without bleed air. And

Interactive BITE with bleed air from Auxiliary Power Unit (APU) or ground supply, air-conditioning Pack1 ON and Pack2 OFF.


25 47-00-00 REV. MAR 2013

ACCESS FUEL TANK INERTING SYSTEM BITE


26 47-00-00 REV. MAR 2013

SYSTEM DATA

Press Line Select Key 6R to display CSAS/IGGS Specific Data, (System Data)


27 47-00-00 REV. MAR 2013

DISPLAY SYSTEM DATA


28 47-00-00 REV. MAR 2013

LRU IDENTIFICATION

Press Line Select Key 3L to display part numbers and serial numbers for the CSAS Controller and the IGGS Controller.


29 47-00-00 REV. MAR 2013

LRU IDENTIFICATION


30 47-00-00 REV. MAR 2013

LAST LEG REPORT

Press Line Select Key 1L on the CSAS/IGGS menu to display the Last Leg Report.


31 47-00-00 REV. MAR 2013

LAST LEG REPORT


32 47-00-00 REV. MAR 2013

PREVIOUS LEGS

Press Line Select Key 2L on the CSAS/IGGS menu to display the Previous Legs Report.


33 47-00-00 REV. MAR 2013

PREVIOUS LEGS REPORT


34 47-00-00 REV. MAR 2013

GROUND REPORT

Press Line Select Key 4L on the CSAS/IGGS menu to display the Ground Report.


35 47-00-00 REV. MAR 2013

GROUND REPORT


36 47-00-00 REV. MAR 2013

TROUBLESHOOTING DATA

Press Line Select Key 5L on the CSAS/IGGS menu to display the Troubleshooting Data.


37 47-00-00 REV. MAR 2013

TROUBLESHOOTING DATA


38 47-00-00 REV. MAR 2013

DIRECT ACCESS TO TROUBLESHOOTING DATA

Press Line Select Key 2R or 4R on the CSAS/IGGS Last Leg Report menu (with faults) to display the Troubleshooting Data.


39 47-00-00 REV. MAR 2013

DIRECT ACCESS TO TROUBLESHOOTING DATA


40 47-00-00 REV. MAR 2013

CLASS 3 FAULTS

Press Line Select Key 1R on the CSAS/IGGS menu to display the Class 3 Faults.


41 47-00-00 REV. MAR 2013

CLASS 3 FAULTS


42 47-00-00 REV. MAR 2013

INTERACTIVE BITE SYSTEM TESTS

Press Line Select Key 2R on the CSAS/IGGS menu to display the CSAS/IGGS Test Menu.


43 47-00-00 REV. MAR 2013


44 47-00-00 REV. MAR 2013

BITE TEST CHOICES


45 47-00-00 REV. MAR 2013

CSAS/IGGS MAIN TEST PAGE


46 47-00-00 REV. MAR 2013

SYSTEM TEST WITHOUT BLEED PRESSURE

Tests the following components:

CSAS Controller

IGGS Controller

CSAS Isolation Valve, closed position only

Bypass Valve

Pressure Sensor, P1

Temperature Sensor, T1

Gate Valve, closed position only


Pressure Sensor, P2

Oxygen Sensor (electrical wiring only

Dual Flow Shut-Off Valve, closed position only

Does not test these components:

CSAS Isolation Valve in open position

Gate Valve in open position

Dual Flow Shut-Off Valve in open position

Ozone Converter

Heat Exchanger

Filter

ASM

Dual Flapper Check Valve


47 47-00-00 REV. MAR 2013

CSAS/IGGS BITE WITHOUT BLEED


48 47-00-00 REV. MAR 2013

SYSTEM TEST WITH BLEED PRESSURE

Tests the following components:

CSAS Controller

IGGS Controller

CSAS Isolation Valve

Bypass Valve

Pressure Sensor, P1


Gate Valve


Pressure Sensor, P2

Oxygen Sensor (electrical wiring only)

Dual Flow Shut-Off Valve

Does not test these components:

Ozone Converter

Heat Exchanger

Heat Exchanger

ASM

Dual Flapper Check Valve


49 47-00-00 REV. MAR 2013

SYSTEM TEST WITH BLEED


50 47-00-00 REV. MAR 2013

AIR SEPARATION MODULE LOCATION


51 47-00-00 REV. MAR 2013

AIR SEPARATION MODULE LOCATION


52 47-00-00 REV. MAR 2013

AIR FILTER LOCATION


53 47-00-00 REV. MAR 2013

AIR FILTER


54 47-00-00 REV. MAR 2013

IGGS BLEED AIR TEMPERATURE SENSOR LOCATION


55 47-00-00 REV. MAR 2013

IGGS BLEED AIR TEMPERATURE SENSOR


56 47-00-00 REV. MAR 2013

CSAS ISOLATION VALVE LOCATION


57 47-00-00 REV. MAR 2013

CSAS/IGGS ISOLATION VALVE


58 47-00-00 REV. MAR 2013

AIR SEPARATION MODULE PRESSURE MONITORING SENSOR LOCATION


59 47-00-00 REV. MAR 2013

AIR SEPARATION MODULE PRESSURE MONITORING SENSOR


60 47-00-00 REV. MAR 2013

IGGS OXYGEN SENSOR LOCATION


61 47-00-00 REV. MAR 2013

IGGS OXYGEN SENSOR


62 47-00-00 REV. MAR 2013

DUAL FLOW SHUTOFF VALVE LOCATION


63 47-00-00 REV. MAR 2013

DUAL FLOW SHUTOFF VALVE


64 47-00-00 REV. MAR 2013

CSAS ISOLATION VALVE


65 47-00-00 REV. MAR 2013

IGGS PALLET LOCATION


66 47-00-00 REV. MAR 2013

IGGS PALLET


67 47-00-00 REV. MAR 2013

CSAS CONTROL UNIT LOCATION


68 47-00-00 REV. MAR 2013

CSAS CONTROL UNIT


69 47-00-00 REV. MAR 2013

IGGS CONTROL UNIT LOCATION


70 47-00-00 REV. MAR 2013

IGGS CONTROL UNIT

47 fuel tank inerting

Engineering