a320 Training 28 Fuel System

A320TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

28 FUEL SYSTEM

This document must be used for training purpose 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 Industrie.

FUEL GENERAL** System Design Philosophy (1) 1..................** Tank Usable Capacities (1) 5....................** ENG and APU Fuel Feed Presentation (1) 11......** System Controls (1) 15..........................** Fuel ECAM Page Presentation (1) 19.............** System Normal Operation (1) 35..................** Fuel System Warnings (3) 61.....................

STORAGE, VENTING AND RECIRCULATION** Venting System Description/Operation (3) 75....** Fuel IDG Cooling System Presentation (3) 79....** Water Drain Valve Operation (2) 85.............** Tank & Venting System Components (3) 89........

FUEL DISTRIBUTION** Engine Feed SYS Description/Operation (3) 115..** APU Feed System Description/Operation (3) 121..** Main Fuel Pump System Components (3) 127.......** Engine and APU Components (3) 151...............

REFUEL/DEFUEL** Refuel/Defuel System Presentation (1) 175......** Refuel/Defuel Control Panel (1) 179............** Cockpit Preselector Presentation (1) 185.......** Refuel/Defuel System D/O (3) 189................** Automatic Refuel Operation (2) 195.............** Manual Refuel Operation (2) 201.................** Defuel Operation (3) 205........................** Fuel Transfer Operation (3) 211.................** Refuel/Defuel System Components (3) 219........

FUEL INDICATING** Quantity Indicating (3) 241.....................** Level Sensing (3) 247............................** Manual Measurement (2) 251......................

** QTY Indicating SYS Components (3) 261..........** Fuel Level Sensing Components (3) 279..........

MAINTENANCE PRACTICESSPECIFIC PAGES** CFDS Specific Page Presentation (3) 293......

_A320 TECHNICAL TRAINING MANUAL28 FUEL SYSTEMMECHANICS / ELECTRICS & AVIONICS COURSE

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EFFECTIVITYALL

28 FUEL SYSTEM

UET4200 TABLE OF CONTENTS Page

28 CONTENTSPage i

Nov 30/00


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EFFECTIVITYALL

28 FUEL SYSTEM

UET4200 TABLE OF CONTENTS Page

28 CONTENTSPage ii

Nov 30/00

THIS PAGE INTENTIONALLY LEFT BLANK

28 - FUEL SYSTEM

28-00-00 SYSTEM DESIGN PHILOSOPHY

CONTENTS:GeneralFeed ConceptManagementSelf Examination

TMUFUE001 LEVEL 1

EFFECTIVITY 28-00-00 Page 1Aug 31/98


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Page 1EFFECTIVITYALL

SYSTEM DESIGN PHILOSOPHY

GENERAL

The fuel system stores fuel in 5 tanks. It suppliesfuel to the engines and APU and recirculates fuel tocool the oil of the IDGs (Integrated Drive Generators).A vent surge tank is fitted in each wing.

FEED CONCEPT

Engines are supplied by the center tank fuel via thecenter tank pumps.When the center tank fuel has been used, engines aresupplied by the wing tank pumps, first with the innercell fuel and then with the outer cell fuel which flowsto the inner cell.

MANAGEMENT

The different functions of the system are:- Fuel level and temperature sensing, fueltransfers, fuel recirculation, refuel/defuelcontrol and monitoring, indications, warningsand test.

The fuel quantity indicating system comprises:- 1 Fuel Quantity Indicating Computer (FQIC).- 2 Fuel Level Sensor Control Units (FLSCUs).

TMUFUE001-T01 LEVEL 1



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SYSTEM DESIGN PHILOSOPHYTMUFUE001-P01 LEVEL 1



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SELF EXAMINATION

Which tanks are the main supply tanks? A - Center tank and inner cells.B - Center Tank.C - Outer Cells.

The Fuel Quantity Indicating System comprises...A - Two FQICs and two FLSCUs.B - One FQIC and two FLSCUs.C - One FQIC and one FLSCU.

TMUFUE001 LEVEL 1



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28 - FUEL SYSTEM

28-11-00 TANK USABLE CAPACITIES

CONTENTS:Wing TanksCenter TankVent Surge TanksSelf Examination

TMUFUE201 LEVEL 1

EFFECTIVITY 28-11-00 Page 1JUL 31/99


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TANK USABLE CAPACITIES

WING TANKS

Fuel is carried in three tanks: the left hand wingtank, the right hand wing tank and the center tank.Each wing tank is divided into two cells, the outercell and the inner cell.




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TMUFUE201-P01 LEVEL 1

TANK USABLE CAPACITIES - WING TANKS



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TANK USABLE CAPACITIES

CENTER TANK

VENT SURGE TANKS

A vent surge tank is positioned in the outer sectionof each wing.Each fuel tank, when normally full, has two percentadditional space for expansion without spillage intothe vent surge tank.




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TANK USABLE CAPACITIESTMUFUE201-P02 LEVEL 1



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SELF EXAMINATION

What is the maximum total fuel capacity?A - 41291 LBS (18729 KG)B - 45920 LBS (20866 KG)C - 52174 LBS (23707 KG)

TMUFUE201 LEVEL 1



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28 - FUEL SYSTEM

28-20-00 ENGINE AND APU FUEL FEEDPRESENTATION

CONTENTS:PumpsSequence ValvesCrossfeed ValveLP ValvesPressure SwitchesAPU PumpTransfer ValvesAir Release ValveSelf Examination

TMUFUE101 LEVEL 1

EFFECTIVITY 28-20-00 Page 1Jul 31/98


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ENGINE AND APU FUEL FEED PRESENTATION

PUMPS

Each main tank has 2 centrifugal booster pumps capableof supplying the engines with fuel at the requiredpressure and flow rate.There are 2 pumps per tank.The wing tank pumps run continuously during normaloperation.

SEQUENCE VALVES

Pressure relief sequence valves on the wing tank pumpsgive priority to center tank pump supply.The sequence valves give priority by limiting wingtank pumps output pressure.

CROSSFEED VALVE

A CROSSFEED VALVE permits connection of the left andright engine supply lines.The crossfeed valve is normally closed.

LP VALVES

The Low Pressure valves isolate the engines or APUfrom the fuel supply.The LP valve is open when the related engine or APUis running; it closes when engine or APU is shut downor when FIRE pushbutton is released out.

PRESSURE SWITCHES

A pressure switch for each pump monitors the pumppressure for the low pressure warning.

APU PUMP

A specific fuel pump supplies the APU if the tank pumpsare not operating. This pump takes fuel from the leftsupply line.The APU fuel pump is supplied by the AC ESS SHED busor the batteries via the static inverter.

TRANSFER VALVES

Transfer valves allow fuel to be transferred from Outerto Inner cells.They open when the fuel level reaches low level sensorsin Inner cell.Two level sensors are installed in each inner cell.Each sensor controls two transfer valves, one in eachwing, which will open when the first inner cell lowlevel sensor becomes dry, irrespective of which side.Once open, the transfer valves close automatically atthe next refuelling.

AIR RELEASE VALVE

Each engine supply line has an Air Release valve atits highest point to enable the line to be bled.




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ENGINE AND APU FUEL FEED PRESENTATION



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SELF EXAMINATION

Are wing tank pumps running while center tank issupplying?

A - Yes, wing tank pumps are always running.B - No, only when center tank is empty.C - No, because of center tank pump priority.

The engine LP valve closes when:A - the fuel booster pumps pressure

decreases.B - the engine is shut down or the ENG FIRE

pushbutton is released out.C - the engine fire detection system senses

an engine fire.

When there is a low level in one inner cell:A - one intercell transfer valve opens.B - two transfer valves in one wing, open.C - two transfer valves, one in each wing,

open.

TMUFUE101 LEVEL 1



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28 - FUEL SYSTEM

28-20-00 SYSTEM CONTROLS

CONTENTS:Tank PumpsMode SelectorCenter Tank PumpsCrossfeed

TMUFUE301 LEVEL 1

EFFECTIVITY 28-20-00 Page 1Nov 30/95


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SYSTEM CONTROLS

TANK PUMPS

When a wing tank pump pushbutton is pressed in, therelated pump runs.

MODE SELECTOR

The MODE SEL pushbutton selects the center tank pumpsto automatic or manual mode.

CENTER TANK PUMPS

With the CTR TK PUMP pushbuttons pressed in, the pumpwill be controlled automatically if Auto mode isselected.In MAN mode, the CTR TK pumps are manually switchedon or off by the related pump pushbuttons.

CROSSFEED

The XFEED pushbutton controls the crossfeed valve.The XFEED pushbutton is normally released out, theCrossfeed valve is closed.If the pushbutton is pressed in, the valve opens andthe ON white light comes on.The green OPEN light comes on when the valve is fullyopen.




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SYSTEM CONTROLS



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TMUFUE301 LEVEL 1



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28 - FUEL SYSTEM

28-00-00 FUEL ECAM PAGE PRESENTATION

CONTENTS:Fuel On BoardFuel UsedEngine LP ValvesTank PumpsTransfer ValvesCrossfeed ValveAPU LP ValveFuel QuantitiesFuel Temperatures

TMUFUE501 LEVEL 1

EFFECTIVITY 28-00-00 Page 1Jun 30/98


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FUEL ECAM PAGE PRESENTATION



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FUEL ECAM PAGE PRESENTATIONTMUFUE501-P02 LEVEL 1



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FUEL ECAM PAGE PRESENTATION - ENGINE LP VALVES



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FUEL ECAM PAGE PRESENTATION - ENGINE LP VALVESTMUFUE501-P04 LEVEL 1



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FUEL ECAM PAGE PRESENTATION - TANK PUMPS



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FUEL ECAM PAGE PRESENTATION - TANK PUMPSTMUFUE501-P06 LEVEL 1



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FUEL ECAM PAGE PRESENTATION - TRANSFER VALVES



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FUEL ECAM PAGE PRESENTATION - TRANSFER VALVESTMUFUE501-P08 LEVEL 1



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FUEL ECAM PAGE PRESENTATION - CROSSFEED VALVE



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FUEL ECAM PAGE PRESENTATION - CROSSFEED VALVETMUFUE501-P10 LEVEL 1



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FUEL ECAM PAGE PRESENTATION - APU LP VALVE



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FUEL ECAM PAGE PRESENTATION - APU LP VALVETMUFUE501-P12 LEVEL 1



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FUEL ECAM PAGE PRESENTATION



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FUEL ECAM PAGE PRESENTATIONTMUFUE501-P14 LEVEL 1



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TMUFUE501 LEVEL 1



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28 - FUEL SYSTEM

28-20-00 SYSTEM OPERATION

CONTENTS:Auto ModeManual ModeSelf Examination

TMUFUE901 LEVEL 1

EFFECTIVITY 28-20-00 Page 1May 31/00


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SYSTEM OPERATION

AUTO MODE

We are on the ground, slats extended and in AUTO MODE.All tank pump pushbuttons are pressed in: wing tankpumps run all the time and center tank pumps are notrunning because the slats are extended.




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SYSTEM OPERATION - AUTO MODE



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SYSTEM OPERATION

AUTO MODE (CONTD)

At engine start, the fuel used indication is reset.The engine identification number becomes white.




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SYSTEM OPERATION - AUTO MODE (CONTD)



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SYSTEM OPERATION

AUTO MODE (CONTD)

After engine start, and regardless of the slatposition, the center tank pumps run for 2 minutes.When running, center tank pumps have priority overwing tank pumps.After this delay, center tank pumps stop because slatsare still extended.




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SYSTEM OPERATION

AUTO MODE (CONTD)

Thats take-off configuration.




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SYSTEM OPERATION

AUTO MODE (CONTD)

With the slats retracted, the center tank pumps startagain.




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SYSTEM OPERATION - AUTO MODE (CONTD)TMUFUE901-P05 LEVEL 1



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SYSTEM OPERATION

AUTO MODE (CONTD)

When the center tank fuel has been used, the relatedpumps stop automatically 5 mn after the center tankfuel low level has been reached.The engines are supplied by the wing tank pumps.




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SYSTEM OPERATION

AUTO MODE (CONTD)

When the inner cell quantity decreases to a givenvalue, the transfer valves open automatically and arelatched until the next refuelling. The outer cell fuelflows to inner cell.




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SYSTEM OPERATION

AUTO MODE (CONTD)

LANDING ...When the engines are stopped, the engine identificationnumbers become amber.




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SYSTEM OPERATION

MANUAL MODE

We are in cruise ...The center tank pumps stop with fuel remaining in thecenter tank.The FAULT light comes on, on the MODE SEL pushbutton.The LO amber symbols come on as the supply pressuredrops. The fuel auto feed fault message appears on theengine warning display.FUEL: AUTO FEED FAULTThe FAULT is indicated if L or R wing tank quantitybecomes less than 5000 KG and the center tank quantityis above 250 KG.




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SYSTEM OPERATION - MANUAL MODETMUFUE901-P09 LEVEL 1



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SYSTEM OPERATION

MANUAL MODE (CONTD)

Manual mode engaged.MAN comes on white. The center tank pumps run again.




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SYSTEM OPERATION - MANUAL MODE (CONTD)TMUFUE901-P10 LEVEL 1



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SYSTEM OPERATION

MANUAL MODE (CONTD)

When the center tank is empty, the pump low pressurewarnings come on as the pumps continue to run.




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SYSTEM OPERATION

MANUAL MODE (CONTD)

The center tank pump symbols are amber because thepumps have been manually selected OFF.




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SELF EXAMINATION

What happens if you extend the slats in flight,with fuel in the center tank, AUTO mode selected?

A - Center tank pumps start.B - Center tank pumps stop.C - Center tank pumps stay as they are.

What happens on ground, slats extended, in AUTOMODE with fuel in the center tank, and one minuteafter engines start?

A - Center tank pumps are running.B - Center tank pumps are stopped.C - The wing tank pumps are stopped.

What does the MODE SEL pushbutton control?A - Center and wing tank pumps.B - Center tank pumps only.C - Wing tank pumps only.

When the center tank is empty, in AUTO MODE, centertank pumps:

A - Must be manually switched OFF.B - Stop automatically and wing tank pumps

start running.C - Stop automatically.

TMUFUE901 LEVEL 1



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28 - FUEL SYSTEM

28-00-00 SYSTEM WARNINGS

CONTENTS:Left Tank Pump 1 Lo PressCenter Tank Pump 2 Lo PressRight Tank Pump 1 + 2 Lo PressCenter Tank Pumps Lo PressXfeed Valve FaultEngine 1 LP Valve OpenLeft Wing Tank Lo LevelRight Transfer Valve ClosedLeft Outer Tank Hi TempRight Inner Tank Lo TempAuto Feed FaultAPU LP Valve Fault

TMUFUE401 LEVEL 3



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SYSTEM WARNINGS - LEFT TANK PUMP 1 LO PRESS



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SYSTEM WARNINGS - CENTER TANK PUMP 2 LO PRESS



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SYSTEM WARNINGS - RIGHT TANK PUMP 1 + 2 LO PRESS



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SYSTEM WARNINGS - CENTER TANK PUMPS LO PRESSTMUFUE401-P04 LEVEL 3



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SYSTEM WARNINGS - XFEED VALVE FAULTTMUFUE401-P05 LEVEL 3



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SYSTEM WARNINGS - ENGINE 1 LP VALVE OPENTMUFUE401-P06 LEVEL 3



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SYSTEM WARNINGS - LEFT WING TANK LO LEVELTMUFUE401-P07 LEVEL 3



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SYSTEM WARNINGS - RIGHT TRANSFER VALVE CLOSEDTMUFUE401-P08 LEVEL 3



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SYSTEM WARNINGS - LEFT OUTER TANK HI TEMPTMUFUE401-P09 LEVEL 3



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SYSTEM WARNINGS - RIGHT INNER TANK LO TEMPTMUFUE401-P10 LEVEL 3



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SYSTEM WARNINGS - AUTO FEED FAULTTMUFUE401-P11 LEVEL 3



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SYSTEM WARNINGS - APU LP VALVE FAULTTMUFUE401-P12 LEVEL 3



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TMUFUE401 LEVEL 3



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28 - FUEL SYSTEM

28-12-00 VENTING SYSTEMDESCRIPTION/OPERATION

CONTENTS:GeneralVent Surge TankWing Tank Venting SystemCenter Tank Venting SystemOverpressure ProtectionVent Float ValvesSelf Examination

TMUFUEG01 LEVEL 3



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VENTING SYSTEM DESCRIPTION/OPERATION

GENERAL

The fuel tank venting system prevents overstressingof tanks.

VENT SURGE TANK

Each vent surge tank vents to the atmosphere througha NACA type intake connected with a vent duct.Inside the vent duct there is a vent protector (flamearrestor) which reduces the risk of a ground fireigniting the fuel tanks.Fuel spilled through the vent pipes into the surgetank is induced back into the outer cell by a scavengejet pump using motive power from the wing fuel pumps.

WING TANK VENTING SYSTEM

Each wing tank inner and outer cells vent to the relatedvent surge tank. The vent lines are fitted with a ventfloat valve.The ducts are large enough to ensure that if thepressure refuelling shut-off failed, excess fuel canbe discharged overboard through the NACA intake.A rubber check valve installed in the vent line allowsany fuel that finds its way into the vent lines todrain back into the tank.

CENTER TANK VENTING SYSTEM

The center tank vents into the left hand vent surgetank.The center tank vent line is a conventional open line,large enough for airflow, which is provided with acheck valve.

OVERPRESSURE PROTECTION

Overpressure protectors are installed in the systemto relieve pressure in the tanks that might occurthrough vent blockage or a pressure refuelling galleryfailure.An excess pressure in the outer cell relieves fuelinto the inner cell via an overpressure protectormounted on rib 15.An excess pressure in the inner cell or in the Ventsurge tank relieves fuel overboard via an overpressureprotector installed on a tank access panel.The center tank overpressure protector relieves fuelinto the left inner cell.

VENT FLOAT VALVES

Two vent float valves prevent fuel from passing in thevent lines during aircraft bank manoeuvres.The open ends of the ducts and the vent float valveswhich permit air to vent but not fuel, are positionedat the optimum levels for refueling and normalground/flight manoeuvers.A vent float valve fitted to the outer side of sealedrib 15 permits air to be vented from the outer cellto the inner cell during flight manoeuvers.TM

UFUEG01-T01 LEVEL 3



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VENTING SYSTEM DESCRIPTION/OPERATIONTMUFUEG01-P01 LEVEL 3



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SELF EXAMINATION

An excess pressure in the inner cell is relievedvia an overpressure protector:

A - Into the Outer cell.B - Into the Center tank.C - Overboard.

The Vent Float Valves:A - Prevent fuel from entering the vent

lines.B - Allow fuel to drain from the vent lines.C - Maintain the fuel tanks pressurized.

TMUFUEG01 LEVEL 3



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28 - FUEL SYSTEM

28-16-00 FUEL IDG COOLING SYSTEMPRESENTATION

CONTENTS:PrincipleFuel ReturnPump LogicFuel Return Valve Closure : Low LevelFuel Return Valve Closure : Inner Cell High TemperatureFuel Return Valve Closure : Outer Cell High TemperatureFuel Return Valve Closure : Pump Pressure LossFuel Return Valve Closure : OverflowSelf Examination

TMUFUEH01 LEVEL 3

EFFECTIVITY 28-16-00 Page 1Sep 30/98


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FUEL IDG COOLING SYSTEM PRESENTATION

PRINCIPLE

The Integrated Drive Generator oil is cooled by fuel;a recirculation system is installed.Some fuel supplying the engines is used to cool theIDG oil. A return valve allows the hot fuel to bereturned to the Outer cell.The Return valve opens at low engine fuel flow if theengine oil temperature is above 93 degrees C.The return valve mixes the hot fuel with cold fuelfrom the LP pump to maintain the temperature of thereturned fuel below 100 degrees C.FLSCU1 and ECU1 control the recirculation system inthe left wing.FLSCU2 and ECU2 control the right wing system.

FUEL RETURN

The recirculated fuel is sent to the outer cell througha check valve and a pressure holding valve in orderto prevent the fuel from boiling.The pressure holding valve maintains a pressure of 18psi in the return line; if the pressure increases,fuel bleeds through the valve into the Outer cell.The check valve prevents fuel flow from the wing tankto the engine when the recirculation system is not inoperation.Note: When the Outer cell is full, the fuel overflows

into the Inner cell through a spill pipe.

PUMP LOGIC

As long as fuel is being delivered from the centertank, the wing tanks are still full and will tend tooverfill, as the returned fuel is delivered to thewings tanks. In this case the center tank pump stopswhen the inner cell reaches the FULL level.The wing tank pumps will operate until approximately1100 lbs (500 kg) of fuel have been used i.e.: underfullsensors reached. The logic circuit then restarts theCenter tank pump.

FRV CLOSURE : LOW LEVEL

The fuel return valve closes when the fuel level inthe inner cell drops to the low level sensors.Note: The low level sensor i.e. IDG shut-off sensor

(38QJ) signals the return valve to close at 620lbs (280 kg).

Note : Closing the return valve will reduce the amountof unuseable fuel.

TMUFUEH01-T01 LEVEL 3



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TMUFUEH01-P01 LEVEL 3




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FRV CLOSURE : INNER CELL HIGH TEMPERATURE

The fuel return valve closes if the fuel temperatureis too high in the inner cell (52.5 degrees C).As the returned fuel is hot, the FLSCU preventstemperature limitation exceedance.In this case, the FLSCU sends an inhibition signal tothe FADEC for FRV closure.

FRV CLOSURE : OUTER CELL HIGH TEMPERATURE

The fuel return valve closes if the fuel temperatureis too high in the outer cell (55 degrees C).This prevents a large volume of high temperature fuelfrom entering the inner cell, in the event of intercellvalve opening.This also keeps the fuel temperature at an acceptablelevel should a tank rupture occur.

FRV CLOSURE : PUMP PRESSURE LOSS

The fuel return valve closes if a low pressure issignalled by all pumps of one wing supplying therelated engine and crossfeed valve closed, or if a lowpressure is signalled by all pumps of both wings withcrossfeed valve opened.This is to reduce fuel flow and allow maximum availablepressure for fuel burn during gravity feeding.Low pressure is sensed by the pump low pressure switchand signalled to the fuel level sensing control units(FLSCUs).

FRV CLOSURE : OVERFLOW

The fuel return valve closes if the center tank pumpfails to respond to the logic signals of the fullsensors, causing the wing tank to overflow into thevent surge tank.

TMUFUEH01-T02 LEVEL 3



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FUEL IDG COOLING SYSTEM PRESENTATIONTMUFUEH01-P02 LEVEL 3



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SELF EXAMINATION

To which tank does the recirculated fuel return ?A - Wing tank outer cell,B - Center tank,C - Wing tank inner cell.

What happens if the fuel level in the inner celldrops to the low level sensor ?

A - The Fuel Return Valve closes,B - The Fuel Return Valve opens,C - The center tank pumps start.

TMUFUEH01 LEVEL 3



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28 - FUEL SYSTEM

28-11-00 WATER DRAIN VALVE OPERATION

CONTENTS:GeneralJob Set UpDrain ProcedureClose Up

TMUFUEU01 LEVEL 2



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WATER DRAIN VALVE OPERATION

GENERAL

Water which collects beneath the fuel in the lowestparts of the wing tanks is drained away through smallbore pipes connected to manuallyoperated water drain valves.To drain remaining fuel and water:

WARNING: DO NOT GET AIRCRAFT FUEL:- IN YOUR MOUTH,- IN YOUR EYES,- ON YOUR SKIN FOR A LONG TIME,AIRCRAFT FUEL IS POISONOUS.

WARNING: DO NOT GET YOUR CLOTHES SOAKED WITH FUEL.

WARNING: BEFORE YOU REFUEL OR DEFUEL THE AIRCRAFT YOUMUST MAKE THE AREA AROUND IT SAFE.IN THE SAFETY AREA DO NOT:- SMOKE,- MAKE SPARKS OR FIRE,- USE ANY EQUIPMENT WHICH IS NOT APPROVED FORREFUEL/DEFUEL PROCEDURES,AIRCRAFT FUEL IS FLAMMABLE.

JOB SET UP

A - Follow the safety precautionsB - Put the access platform below the applicable water

drain valve.C - Put the container below the applicable water drain

valve.D - Put "NO SMOKING" warning notices at the limit of

the safety area.E - On the TEST EQUIPMENT JET PUMP fully retract the

nut (4), the screw (3) and the plunger (1) assembly.F - Install the TEST EQUIPMENT JET PUMP:

(1) Put the hexagonal end of the bush (2) into thebase plate of the drain valve.(2) Turn the bush (2) through 30 deg.(3) Turn the nut (4) until it touches and sealsagainst the bottom skin.(4) Put the end of the hose into the container.

DRAIN PROCEDURE

A - Hold the bush (2) and turn the screw (3) to theend of its travel. This causes the plunger (1) toopen the drain valve and the fuel to flow.

CLOSE UP

A - When the fuel flow stops, remove the TEST EQUIPMENTJET PUMP.

B - Remove all the ground support equipment, themaintenance equipment, the standard and specialtools and all other items.

C - Make sure that the work area is clean and clearof tools and other items.TM

UFUEU01-T01 LEVEL 2



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WATER DRAIN VALVE OPERATIONTMUFUEU01-P01 LEVEL 2



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TMUFUEU01 LEVEL 2



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28 - FUEL SYSTEM

28-12-00 TANK AND VENTING SYSTEMCOMPONENTS

CONTENTS:Water Drain ValveClack ValveCap/Adapter Gravity FillOverpressure ProtectorFuel Vent ProtectorFloat vent valveCheck valvePressure Relief ValveNACA Vent IntakeVapor SealDrain Mast Leak Monitor

TMUFUEJ01 LEVEL 3

EFFECTIVITY 28-12-00 Page 1Apr 30/96


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TANK AND VENTING SYSTEM COMPONENTS

WARNING: Do not get aircraft fuel:- in your mouth- in your eyes (aircraft fuel is poisonous)- on your skin for a long time.

WARNING: Obey the fuel safety procedures.

WARNING: Do not get your clothes soaked with fuel. Useapproved protective clothing when you go ina fuel tank.

WARNING: Make sure that the Landing gear safety-locksand the wheel chocks are in position.

WARNING: Make sure you put a warning notice in thecockpit to advise not to operate the flightcontrols because:- persons are near the flight control surfaces- equipment is near flight control surfaces.

WARNING: Make sure that you have correct fire fightingequipment available before you start any taskon fuel system.

WARNING: Make sure that all the circuits in maintenanceare isolated before you supply electricalpower to the aircraft.

WARNING: Do not go into a fuel tank until the fuel-gasconcentration is less than 25 % of LowerExplosive Limit (LEL).

WARNING: Do not remove your respirator while you arein a fuel tank (unless the fuel-gasconcentration is less than 5 % of LEL).A high concentration is unhealthy and toxic.

WATER DRAIN VALVE

IDENTIFICATIONFIN: 21QM, 22QM, 23QM, 24QM, 25QM, 26QM, (94QM, 95QM)

LOCATIONZONE: 540, 550, 640, 650, (141, 142)

COMPONENT DESCRIPTIONPeriodic operation of the valves ensures that waterdoes not collect in quantities sufficient to causemalfunction of the engines.

TMUFUEJ01-T01 LEVEL 3



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TMUFUEJ01-P01 LEVEL 3

TANK AND VENTING SYSTEM COMPONENTS - WATER DRAIN VALVE



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CLACK VALVE

IDENTIFICATIONFIN: None

LOCATIONZONE: 540, 640

COMPONENT DESCRIPTIONRibs 1 and 2 form a Collector Box around the wing tankfuel pumps.Clack valves at the bottom of rib 2 permit fuel toenter the box but prevent it draining out again.This ensures a fuel supply at the pumps during wingdown manoeuvres.




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TANK AND VENTING SYSTEM COMPONENTS - CLACK VALVE



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CAP/ADAPTER GRAVITY FILL

IDENTIFICATIONFIN: 42QM, 43QM, 44QM, 45QM


COMPONENT DESCRIPTIONAn overwing gravity fill cap/adapter is installed inthe top surface of each wing tank, giving direct accessto the outer cell.The cap is removed by lifting the hinged handle, setflush in the top of the cap, and turning to unlock.

NOTE: Before gravity refuelling make sure thattransfer valves are open.




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TANK AND VENTING SYSTEM COMPONENTS - CAP/ADAPTER GRAVITY FILL



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OVERPRESSURE PROTECTOR

IDENTIFICATIONFIN: 46QM, 47QM, 102QM, 103QM, (96QM)

LOCATIONZONE: 540, 640, (147)




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TANK AND VENTING SYSTEM COMPONENTS - OVERPRESSURE PROTECTOR



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FUEL VENT PROTECTOR

IDENTIFICATIONFIN: 48QM, 49QM


COMPONENT DESCRIPTIONVent protector consists of:

- ice protector- flame arrestor

Ice protector prevents freezing of the flame arrestorduring descent. Flame arrestor reduces the risk ofground fire igniting the fuel tank.




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TANK AND VENTING SYSTEM COMPONENTS - FUEL VENT PROTECTOR



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FLOAT VENT VALVE



COMPONENT DESCRIPTIONA float operated arm opens or closes this valvedepending upon the fuel level, to permit air to bevented.Valve also opens when:

- inward pressure differential is 0.5 psig(0.0345 bar) with a full tank.

- outward pressure differential is 1 psig(0.69 bar) with fuel level below float.




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TANK AND VENTING SYSTEM COMPONENTS - FLOAT VENT VALVETMUFUEJ01-P06 LEVEL 3



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CHECK VALVE

IDENTIFICATIONFIN: 50QM, 51QM, 52QM, 53QM, 120QM, 121QM, 93QM

LOCATIONZONE: 540, 640, 141

COMPONENT DESCRIPTIONRubber check valves are installed in the vent linesto allow any fuel that finds its way into the ventlines to drain back into the tank.




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TANK AND VENTING SYSTEM COMPONENTS - CHECK VALVETMUFUEJ01-P07 LEVEL 3



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PRESSURE RELIEF VALVE

IDENTIFICATIONFIN: 97QM

LOCATIONZONE: 142

COMPONENT DESCRIPTIONThe pressure relief valve relieves fuel into the RHwing tank in the event of a center tank refuellingoverflow.Removal/Installation:

- empty Center and RH wing tanks- open manhole covers 148AZ and 640AB.




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TANK AND VENTING SYSTEM COMPONENTS - PRESSURE RELIEF VALVETMUFUEJ01-P08 LEVEL 3



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NACA VENT INTAKE



COMPONENT DESCRIPTIONThe flush mounted NACA vent intake provides connectionof the vent system to the atmosphere and maintains aslight positive pressure in the fuel tanks duringforward flight.The VENT SURGE TANK will hold 50 US gallons beforeoverflowing into the upturned NACA INTAKE duct.




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TANK AND VENTING SYSTEM COMPONENTS - NACA VENT INTAKETMUFUEJ01-P09 LEVEL 3



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VAPOR SEAL


LOCATIONZONE: 140

COMPONENT DESCRIPTIONThe vapor seal is a fabric membrane that isolates theCenter tank from the air conditioning compartmentbelow.Pressurized air from the air conditioning system flowsthrough the space between the vapor seal and the tankbottom to ventilate it.




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TANK AND VENTING SYSTEM COMPONENTS - VAPOR SEALTMUFUEJ01-P10 LEVEL 3



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DRAIN MAST


LOCATIONZONE: 140

COMPONENT DESCRIPTIONA system of drains at the rear of the vapor seal conveysdrainage and ventilating (exhaust) air through a drainmast to atmosphere.The drain mast is an aluminium fairing bolted to theunderside of the fuselage.




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TANK AND VENTING SYSTEM COMPONENTS - DRAIN MASTTMUFUEJ01-P11 LEVEL 3



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LEAK MONITOR


LOCATIONZONE: 140

COMPONENT DESCRIPTIONIn the event of fuel flowing from the drain mast, checkthe leak monitor to determine the area of leakagecenter tank or APU fuel supply line.




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TANK AND VENTING SYSTEM COMPONENTS - LEAK MONITORTMUFUEJ01-P12 LEVEL 3



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TMUFUEJ01 LEVEL 3



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28 - FUEL SYSTEM

28-21-00 ENGINE FEED SYSTEM DESCRIPTIONAND OPERATION

CONTENTS:GeneralMain PumpsCanister Check ValvesPressure SwitchesBy pass suction ValveAir Release ValveLP ValvesJet PumpsCrossfeed ValveSequence ValveIntercell Transfer ValveFuel Supply LogicSelf Examination

TMUFUKA01 LEVEL 3

EFFECTIVITY 28-21-00 Page 1Oct 31/96


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ENGINE FEED SYSTEM DESCRIPTION AND OPERATION

GENERAL

The main fuel pump system supplies fuel from the fueltanks to the engines. Each tank has two centrifugalbooster pumps.Fuel is first provided by the center tank pumps andthen by the wing tank pumps when the center tank isempty.The crossfeed system divides the engine fuel feedsystem into two independent feed systems.

MAIN PUMPS

The main pumps, driven by a 3 phase 115/200 volt ACmotor, have different power supplies. When it is inoperation, each main pump supplies the fuel to:

- its related engine,- the fuel recirculation cooling system,- the crossfeed system,- the refuel/defuel system.

Each wing tank collector comprises:- two fuel pumps contained in their relatedcanisters,

- two fuel strainers,- a suction valve,- two check valves.

CANISTER CHECK VALVES

The canister allows replacement of the fuel pumpwithout draining fuel.

The wing fuel pump element is located in a canisterattached to the wing bottom skin, with an inletconnected to a fuel strainer.The canister has three outlets:

- one upper outlet is connected to the enginefeed line and contains an internal flap-typecheck valve.

- the other upper outlet is connected to asequence valve.

- a smaller outlet is connected to the scavengejet pumps and the fuel pump pressure switch.

When a fuel pump is not in operation, the two checkvalves prevent any reverse flow of fuel through thepump.The center fuel pump element is located in a canisterattached to the center tank bottom skin, with a lowerinlet connected to a fuel strainer.The canister has two outlets:

- an upper outlet is connected to the engine feedline and contains an internal flap-type checkvalve.

- a smaller outlet is connected to the scavengejet pumps and the fuel pump pressure switch.

PRESSURE SWITCHES

The pressure switches monitor the output of the pumpsthrough a pressure pipe.If the pressure from the mainpump decreases to less than 6 psi (0,41 bar) thepressure switch sends a warning signal to the ECAMsystem.

TMUFUKA01-T01 LEVEL 3



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ENGINE FEED SYSTEM DESCRIPTION AND OPERATIONTMUFUKA01-P01 LEVEL 3



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BY PASS SUCTION VALVE

A by pass suction valve is installed on the enginefeed line, downstream of the main pumps. In case ofcomplete main pump failure, the by pass suction valveallows fuel to be sucked from the tank by the enginedriven pumps and thus supply the engine by "gravity".

AIR RELEASE VALVE

The air release valve releases air trapped in theengine fuel feed line.The air release valve is installed at the high pointbetween the pump and the LP valve.

LP VALVES

The LP valve is installed on the wing tank front spar,in the feed line to the engine.Each LP valve has a actuator with 2 electric motors,each of which is supplied by different 28VDC powersources.The LP valve isolates the engine fuel feed supply atshut-down (normal procedure) or in case of emergency(engine fire procedure).

JET PUMPS

Center tank scavenge jet pumps move fuel and watercaught in the tank to the related main pump inlet.Outer cell scavenge jet pumps move the surge tank fuelto the rear intercell transfer valves.Check valves, in the line between the surge tank,combined with these jet pumps make sure that fuel cannot enter the surge tank via the pump if the main pumpsare off.

CROSSFEED VALVE

The crossfeed valve in the center (transfer) tank isusually in the closed position.In this position, it divides the main fuel pump systeminto two parts (one part for each engine).When the crossfeed valve is open, either tank cansupply fuel to either engine.

SEQUENCE VALVE

The wing tank pumps are equipped with a sequence valveto make sure that the center tank is emptied first.

INTERCELL TRANSFER VALVE

The intercell transfer valves enable the outer cellfuel to flow into the inner cell when the inner celllow level sensors are dry.

FUEL SUPPLY LOGIC

When all the tanks contain fuel, the center tank willbe emptied first.Keeping a fuel mass in the wings aslong as possible reduces the bending stresses at thewing roots.When the center tank fuel has been used, engines aresupplied by the inner cells fuel. The outer cell fuelflows to the inner cell by gravity through the transfervalves which open when the inner cell fuel quantitydecreases to a given value.

TMUFUKA01-T02 LEVEL 3



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ENGINE FEED SYSTEM DESCRIPTION AND OPERATIONTMUFUKA01-P02 LEVEL 3



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SELF EXAMINATION

In normal operation, which tank will be emptiedfirst?

A - The inner cell.B - The center tank.C - The outer cell.

The by pass suction valve is in operation,therefore:

A - The two wing tank pumps are in operation.B - Only one wing tank pump supplies its

associated engine.C - Both pumps are stopped.

On ground, the engines are stopped, how do youclose the LP valve?

A - By releasing out the ENG FIRE P/B.B - By removing electrical power from A/C.C - The valve is already closed.

TMUFUKA01 LEVEL 3



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28 - FUEL SYSTEM

28-22-00 APU FEED SYSTEM DESCRIPTION ANDOPERATION

CONTENTS:GeneralAuxiliary Power Unit (APU) PumpCanistersPressure SwitchAPU Low pressure (LP) Shut-off ValveCrossfeed OperationFUEL VENT PushbuttonAPU MASTER SWITCHSelf Examination

TMUFUKE01 LEVEL 3



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APU FEED SYSTEM DESCRIPTION AND OPERATION

GENERAL

The APU fuel supply system comprises a fuel pump, anLP fuel valve and an actuator on the rear wall of thecenter tank. The fuel supply to the APU is normallyfrom the left-hand crossfeed line.The APU LP fuel shut-off system has an LP fuel valvethat controls the supply of fuel to the APU. If an APUfire occurs on ground, the APU emergency shut downsystem closes the LP fuel valve to stop the flow offuel. When the crossfeed valve is open, either enginefeed line (left or right) can supply fuel to the APU.

AUXILIARY POWER UNIT (APU) PUMP

The fuel pressure for the APU comes from either theengine fuel pumps or the APU fuel pump.For normal operation, the essential busbar 801XP (115VAC) supplies the pump motor. When the busbar is notenergized, the static inverter busbar 901XP (115V AC)supplies the pump motor.

CANISTERS

The canister permits pump replacement even with fuelin the tanks or in the APU fuel line.When a pump is removed, the fuel pressure closes thecanister inlet and outlet.

PRESSURE SWITCH

The pressure switch controls pump operation. Thepressure in the left crossfeed line goes through thecheck valve to operate a microswitch.The APU fuel pump stops if the crossfeed line pressurereaches 23.3 PSI absolute (1.6 bar) and restarts at21,7 PSIA (1.5 bar).

APU LOW PRESSURE (LP) SHUT-OFF VALVE

The APU Low Pressure fuel shut-off valve is used toisolate the APU fuel supply line from the left enginefeed line, when the APU does not operate. The two DCmotors in the actuator are supplied from different 28VDC sources.The valve opens when:

- The APU MASTER SW is set to ON, or the FUELVENT push-button switch in the APU compartmentis pressed and held.

The FUEL VENT pushbutton is used to purge the systemduring ground maintenance.

- The valve closes when:- The APU MASTER SW is set to OFF.- The FUEL VENT pushbutton is released.- The APU FIRE pushbutton switch on the overheadpanel is pressed.

- The APU FIRE SHUT-OFF switch on the panelforward of the nose landing gear bay isoperated.

- The fire detection system operates on theground.

TMUFUKE01-T01 LEVEL 3



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APU FEED SYSTEM DESCRIPTION AND OPERATIONTMUFUKE01-P01 LEVEL 3



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CROSSFEED OPERATION

When the crossfeed valve is open, the right-hand enginefeed line can also supply the APU fuel supply line.

FUEL VENT PUSHBUTTON

When the aircraft is on the ground, it is possible tooperate the pump to purge the fuel line.A pushbutton (hold) on FR 80 in the APU compartmentis used to operate the pump.

APU MASTER SWITCH

If the APU MASTER SW pushbutton is pressed to ON, theAPU pump will operate if the pump inlet pressure isbelow 1.5 bar (21.7 PSI) absolute.This is initiated automatically through the pressureswitch.

TMUFUKE01-T01 LEVEL 3



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SELF EXAMINATION

The function of the APU fuel pump pressure switchis:

A - To signal any pressure to the ECAM.B - To control the pump operation.C - To shut the APU LP valve in case of fire.

How many motors does the APU LP valve have?A - One DC motor.B - Two DC motors.C - Two motors, one DC (for a battery start)

and one AC.

TMUFUKE01 LEVEL 3



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TMUFUKE01 LEVEL 3



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28 - FUEL SYSTEM

28-20-00 MAIN FUEL PUMP SYSTEM COMPONENTS

CONTENTS:Pressure SwitchAir Release ValveSequence ValveCenter Tank Fuel PumpCenter Tank Fuel Pump Removal InformationWing Tank Fuel PumpWing Tank Fuel Pump Removal InformationScavenge Jet PumpTransfer ValveTransfer Valve DriveTransfer Valve Actuator

TMUFUEK01 LEVEL 3



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MAIN FUEL PUMP SYSTEM COMPONENTS

PRESSURE SWITCH

IDENTIFICATIONFIN: 23QA, 27/24QA, 28QA (39QA, 40QA)

LOCATIONZONE: 570, 571, 670, 671 (140)

COMPONENT DESCRIPTIONA pressure switch for each fuel pump is mounted on theoutside face of the rear wall of the tanks

TMUFUEK01-T01 LEVEL 3



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TMUFUEK01-P01 LEVEL 3

MAIN FUEL PUMP SYSTEM COMPONENTS - PRESSURE SWITCH



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AIR RELEASE VALVE



COMPONENT DESCRIPTIONIt allows air, but not fuel, to be expelled from thepipeline and prevents air being sucked in.




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MAIN FUEL PUMP SYSTEM COMPONENTS - AIR RELEASE VALVE



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SEQUENCE VALVES



COMPONENT DESCRIPTIONThe SEQUENCE VALVES are pressure relief valves attachedto secondary outlets on wing tank pumps only.




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MAIN FUEL PUMP SYSTEM COMPONENTS - SEQUENCE VALVES



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CENTER TANK FUEL PUMP

IDENTIFICATIONFIN: 37QA, 38QA

LOCATIONZONE: 140

COMPONENT DESCRIPTIONThe pump delivers fuel at 11000 lb/hr (4989kg/hr) at30 psi (2.08 bar). Thermal fuse: 200 degrees C.The pump is installed in a canister containing a slidevalve so that the pump can be removed without havingto drain the tank.




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MAIN FUEL PUMP SYSTEM COMPONENTS - CENTER TANK FUEL PUMP



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CENTER TANK FUEL PUMP REMOVAL INFORMATION

IDENTIFICATIONFIN: 37QA, 38QA

LOCATIONZONE: 140

COMPONENT DESCRIPTIONPUMP REMOVAL:

- disconnect electrical connector- remove attachment bolts- use extractor screws in removal holes- drain it- turn the pump- pull it out




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MAIN FUEL PUMP SYSTEM COMPONENTS - CENTER TANK FUEL PUMP REMOVAL INFORMATION



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WING TANK FUEL PUMP

IDENTIFICATIONFIN: 21QA, 25QA, 22QA, 26QA


COMPONENT DESCRIPTIONSequence valve reduces pump outlet pressure to 25 psi.The pump is installed in a canister containing a slidevalve so that the pump can be removed without havingto drain the tank.




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MAIN FUEL PUMP SYSTEM COMPONENTS - WING TANK FUEL PUMPTMUFUEK01-P06 LEVEL 3



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WING TANK FUEL PUMP REMOVAL INFORMATION

IDENTIFICATIONFIN: 21QA, 25QA, 22QA, 26QA


COMPONENT DESCRIPTIONPUMP REMOVAL:

- disconnect electricalconnector- remove attachment bolts- use extractor screws in removal holes- drain it- turn the pump- pull it out




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MAIN FUEL PUMP SYSTEM COMPONENTS - WING TANK FUEL PUMP REMOVAL INFORMATIONTMUFUEK01-P07 LEVEL 3



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SCAVENGE JET PUMP

IDENTIFICATIONFIN: 66QM to 69QM, 89QM, 90QM

LOCATIONZONE: 540, 640, 141, 142

COMPONENT DESCRIPTIONThe Jet pump has:

- a venturi type passage- a non-return valve- ports for pipe connection- an attachment plate with studs




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MAIN FUEL PUMP SYSTEM COMPONENTS - SCAVENGE JET PUMPTMUFUEK01-P08 LEVEL 3



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TRANSFER VALVE



COMPONENT DESCRIPTIONEach valve consists of a cast light alloy body housinga spherical plug.




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MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVETMUFUEK01-P09 LEVEL 3



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TRANSFER VALVE DRIVE



COMPONENT DESCRIPTIONThe drive shaft has 2 universal joints. It is keyedat one end for engagement with the actuator and splinedat the other end for engagement with the valves.




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MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVE DRIVETMUFUEK01-P10 LEVEL 3



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TRANSFER VALVE ACTUATOR

IDENTIFICATIONFIN: 9QP, 10QP, 11QP, 12QP

LOCATIONZONE: 520, 620, 570, 670

COMPONENT DESCRIPTIONMECHANICAL INDICATOR: shows valve open or closed.




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MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVE ACTUATORTMUFUEK01-P11 LEVEL 3



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TMUFUEK01 LEVEL 3



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28 - FUEL SYSTEM

28-20-00 ENGINE AND APU COMPONENTS

CONTENTS:Pressure Holding Valve (recirculation)Check Valve (recirculation)Crossfeed ValveCrossfeed Valve ActuatorEngine LP Fuel ValveEngine LP Fuel Valve ActuatorAPU Fuel Pressure SwitchAPU Fuel PumpAPU Fuel Pump CanisterAPU Fuel LP ValveAPU Fuel LP Valve Actuator

TMUFUEL01 LEVEL 3



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ENGINE AND APU COMPONENTS

PRESSURE HOLDING VALVE (recirculation/cooling)



COMPONENT DESCRIPTIONValve maintains line pressure of 18 psi; if pressureincreases, fuel bleeds into outer cell.

TMUFUEL01-T01 LEVEL 3



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TMUFUEL01-P01 LEVEL 3

ENGINE AND APU COMPONENTS - PRESSURE HOLDING VALVE (recirculation/cooling)



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CHECK VALVE (recirculation/cooling)



COMPONENT DESCRIPTIONOne fuel recirculation check valve is mounted on thelower side of the bottom skin between ribs 7 and 8 andprevents reverse flow from the tank to the engine inthe event of a fuel pipe failure.




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ENGINE AND APU COMPONENTS - CHECK VALVE (recirculation/cooling)



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CROSSFEED VALVE


LOCATIONZONE: 142

COMPONENT DESCRIPTIONAccess to Crossfeed valve:

- defuel Center tank- open main door of RH main gear- remove manhole cover 148AZ.




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ENGINE AND APU COMPONENTS - CROSSFEED VALVE



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CROSSFEED VALVE ACTUATOR

IDENTIFICATIONFIN: 5QE

LOCATIONZONE: 148

COMPONENT DESCRIPTIONThe Crossfeed valve actuator has twin electric motorswhich drive a common differential gear to turn thespherical plug through 90 degrees. This gear allowseither motor to drive the valve if the other motor isinoperative.




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ENGINE AND APU COMPONENTS - CROSSFEED VALVE ACTUATOR



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ENGINE LP FUEL VALVE



COMPONENT DESCRIPTIONEach Engine LP valve is bolted to a mounting on thewing front spar.




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ENGINE AND APU COMPONENTS - ENGINE LP FUEL VALVE



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ENGINE LP FUEL VALVE ACTUATOR

IDENTIFICATIONFIN: 9QG, 10QG


COMPONENT DESCRIPTIONThe epicyclic gear allows one of the 2 motors to turnthe spherical plug if the other motor is inoperative.




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ENGINE AND APU COMPONENTS - ENGINE LP FUEL VALVE ACTUATORTMUFUEL01-P06 LEVEL 3



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APU FUEL PRESSURE SWITCH

IDENTIFICATIONFIN: 7QC

LOCATIONZONE: 141

COMPONENT DESCRIPTIONPressure switch monitors APU pump inlet pressure:21.7 psi: switch closure to start the pump23.3 psi: switch opening to stop the pump.




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ENGINE AND APU COMPONENTS - APU FUEL PRESSURE SWITCHTMUFUEL01-P07 LEVEL 3



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APU FUEL PUMP

IDENTIFICATIONFIN: 4QC

LOCATIONZONE: 141

COMPONENT DESCRIPTIONFour bolts secure the Pump element to the canister,from which it can be withdrawn, leaving the canisterin-situ. A drain plug enables the pump element to bedrained before removal.A security plate, held by 2 screws, prevents the pumpelement being removed without having removed the drainplug.A thermal fuse, set at 175 C ( 347 F ), protects themotor from overheat condition.




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ENGINE AND APU COMPONENTS - APU FUEL PUMPTMUFUEL01-P08 LEVEL 3



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APU FUEL PUMP CANISTER


LOCATIONZONE: 141

COMPONENT DESCRIPTIONThe CANISTER is attached to the inside of the wing boxrear spar with 5 bolts. Three of these bolts are usedto secure a drain gutter to the outside of the rearspar to collect any fuel leakage and divert it awayfrom the installation area.




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ENGINE AND APU COMPONENTS - APU FUEL PUMP CANISTERTMUFUEL01-P09 LEVEL 3



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APU FUEL LP VALVE


LOCATIONZONE: 147




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ENGINE AND APU COMPONENTS - APU FUEL LP VALVETMUFUEL01-P10 LEVEL 3



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APU FUEL LP VALVE ACTUATOR

IDENTIFICATIONFIN: 3QF

LOCATIONZONE: 147

COMPONENT DESCRIPTIONThe actuator can be removed from the valve in-situwithout having to drain the system.




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ENGINE AND APU COMPONENTS - APU FUEL LP VALVE ACTUATORTMUFUEL01-P11 LEVEL 3



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TMUFUEL01 LEVEL 3



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28 - FUEL SYSTEM

28-25-00 REFUEL/DEFUEL SYSTEM PRESENTATION

CONTENTS:R/D CouplingRefuel ValvesDiffusersAir Inlet and Drain ValvesDefuel/Transfer ValvePressure Relief ValveHigh Level SensorSelf Examination

TMUFUEF01 LEVEL 1



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REFUEL/DEFUEL SYSTEM PRESENTATION

R/D COUPLING

A single pressure refuelling coupling is positionedunder the right hand wing leading edge. TheRefuel/Defuel coupling supplies the center tank andOuter cells. When the Outer cells are full, fueloverflows into the Inner cells via a spill pipe.The RH coupling is standard while the LH coupling shownis optional.When not in use, the coupling is fitted with a pressureblanking cap.

REFUEL VALVE

The fuel flow into each tank is controlled by a solenoidoperated Refuel valve.All Refuel valves are identical and interchangeable.They may be manually operated, by pushing a plungeron the valve itself.

DIFFUSERS

Diffusers, installed on the Refuel lines, diffuse fuelinto the tanks with minimum turbulence andelectrostatic build up.

AIR INLET AND DRAIN VALVES

The Air Inlet valve installed on the refuel line,admits air into the refuel line so that the line maydrain. A drain valve drains fuel from the refuel lineinto the inner cell.The Air Inlet Valve is near the inner cell RefuelValve.The fuel is free to flow through the drain valve exceptunder refuel line pressure.

DEFUEL/TRANSFER VALVE

The Defuel/Transfer valve is controlled from theRefuel/Defuel panel.When open, it connects the Refuel line and the Enginesupply line for defuelling.

PRESSURE RELIEF VALVE

The pressure relief valve will relieve fuel into theRight hand wing tank in the event of a center tankrefuelling overflow.

HIGH LEVEL SENSOR

One high level sensor is installed in the center tankand in each Inner cell. When immersed in fuel, therelated Refuel valve closes.

TMUFUEF01-T01 LEVEL 1



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REFUEL/DEFUEL SYSTEM PRESENTATIONTMUFUEF01-P01 LEVEL 1



UET4200


SELF EXAMINATION

The Inner cell is refuelled only when:A - Center tank is full.B - Outer cell is full.C - Outer cell is empty.

Refuel valves may be actuated:A - Electrically only.B - Manually only.C - Electrically or manually.

TMUFUEF01 LEVEL 1



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28 - FUEL SYSTEM

28-25-00 REFUEL/DEFUEL CONTROL PANEL

CONTENTS:Multi-Tank IndicatorHigh Level LightsRefuel Valve SelectorsMode SelectorOpen LightTest SwitchPreselectedActualRocker SwitchEnd Light

TMUFUEP01 LEVEL 1

EFFECTIVITY 28-25-00 Page 1Feb 30/96


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REFUEL/DEFUEL CONTROL PANEL

MULTI-TANK INDICATOR

The Multi-Tank Indicator displays the quantity of fuelin each wing and the Center Tank.

HIGH LEVEL LIGHTS

A blue HI LVL light for each tank comes on when theassociated high level sensor is covered. Thecorresponding refuel valve will close.

REFUEL VALVE SELECTOR

There is one Refuel Valve selector per tank. For anautomatic refueling, these Refuel Valves selectorsremain in the NORM position. For defuelling the valveswill not open. Selector set to open : the Refuel valveoperation depends on the MODE SELECTOR position. Withthe Mode Selector in the Refuel position, each Refuelvalve closes when the associated high level isreached.When the REFUEL VALVE selector is set to theSHUT position, the Refuel valve is closed. This isindependent of the MODE SELECTOR position.

MODE SELECTOR

With the MODE SELECTOR at OFF, the Refuel Valves areclosed. When the MODE SELECTOR is set to REFUEL, theRefuel Valves operate automatically or manuallydepending on the position of the Refuel Valveselectors.For Defueling or Transfer of fuel the MODESELECTOR is set to DEFUEL/TRANSFER. It opens theDefuel/Transfer Valve.

OPEN LIGHT

The amber OPEN light comes on when the MODE SELECTORis set to DEFUEL/XFR. It confirms the opening of theDefuel/Transfer Valve.

TEST SWITCH

When the TEST switch is set to the HI LVL position,the HI LVL lights come on if the high level sensorsan

Documents

a320 Training 28 Fuel System