a320 Training 28 Fuel System

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A320

TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

28 FUEL SYSTEM

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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.

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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 PRACTICES SPECIFIC PAGES ** CFDS Specific Page Presentation (3)...293

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A320 TECHNICAL TRAINING MANUAL

28 FUEL SYSTEM MECHANICS / ELECTRICS & AVIONICS COURSE

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28 FUEL SYSTEM

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28 - FUEL SYSTEM

28-00-00 SYSTEM DESIGN PHILOSOPHY

CONTENTS: General Feed Concept Management Self Examination TM UF UE 00 1 LE VE L 1

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The fuel system stores fuel in 5 tanks. It supplies fuel to the engines and APU and recirculates fuel to cool 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 the center tank pumps.

When the center tank fuel has been used, engines are supplied by the wing tank pumps, first with the inner cell fuel and then with the outer cell fuel which flows to the inner cell.

MANAGEMENT

The different functions of the system are:

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Fuel level and temperature sensing, fuel transfers, fuel recirculation, refuel/defuel control and monitoring, indications, warnings and test.

The fuel quantity indicating system comprises:

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1 Fuel Quantity Indicating Computer (FQIC).

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2 Fuel Level Sensor Control Units (FLSCUs).

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SYSTEM DESIGN PHILOSOPHY

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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.

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28 - FUEL SYSTEM

28-11-00 TANK USABLE CAPACITIES

CONTENTS: Wing Tanks Center Tank Vent Surge Tanks Self Examination TM UF UE 20 1 LE VE L 1

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

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TANK USABLE CAPACITIES - WING TANKS

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VENT SURGE TANKS

A vent surge tank is positioned in the outer section of each wing.

Each fuel tank, when normally full, has two percent additional space for expansion without spillage into the vent surge tank.

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TANK USABLE CAPACITIES

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A - 41291 LBS (18729 KG) B - 45920 LBS (20866 KG) C - 52174 LBS (23707 KG) TM UF UE 20 1 LE VE L 1

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28 - FUEL SYSTEM

28-20-00 ENGINE AND APU FUEL FEED

PRESENTATION

CONTENTS: Pumps Sequence Valves Crossfeed Valve LP Valves Pressure Switches APU Pump Transfer Valves Air Release Valve Self Examination TM UF UE 10 1 LE VE L 1

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Each main tank has 2 centrifugal booster pumps capable of supplying the engines with fuel at the required pressure and flow rate.

There are 2 pumps per tank.

The wing tank pumps run continuously during normal operation.

SEQUENCE VALVES

Pressure relief sequence valves on the wing tank pumps give priority to center tank pump supply.

The sequence valves give priority by limiting wing tank pumps output pressure.

CROSSFEED VALVE

A CROSSFEED VALVE permits connection of the left and right engine supply lines.

The crossfeed valve is normally closed. LP VALVES

The Low Pressure valves isolate the engines or APU from the fuel supply.

The LP valve is open when the related engine or APU is running; it closes when engine or APU is shut down or when FIRE pushbutton is released out.

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

APU PUMP

A specific fuel pump supplies the APU if the tank pumps are not operating. This pump takes fuel from the left supply line.

The APU fuel pump is supplied by the AC ESS SHED bus or the batteries via the static inverter.

TRANSFER VALVES

Transfer valves allow fuel to be transferred from Outer to Inner cells.

They open when the fuel level reaches low level sensors in Inner cell.

Two level sensors are installed in each inner cell. Each sensor controls two transfer valves, one in each wing, which will open when the first inner cell low level sensor becomes dry, irrespective of which side. Once open, the transfer valves close automatically at the next refuelling.

AIR RELEASE VALVE

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

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ENGINE AND APU FUEL FEED PRESENTATION

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supplying?

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. TM UF UE 10 1 LE VE L 1

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28 - FUEL SYSTEM

28-20-00 SYSTEM CONTROLS

CONTENTS: Tank Pumps Mode Selector Center Tank Pumps Crossfeed TM UF UE 30 1 LE VE L 1

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

MODE SELECTOR

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

CENTER TANK PUMPS

With the CTR TK PUMP pushbuttons pressed in, the pump will be controlled automatically if Auto mode is selected.

In MAN mode, the CTR TK pumps are manually switched on or off by the related pump pushbuttons.

CROSSFEED

The XFEED pushbutton controls the crossfeed valve. The XFEED pushbutton is normally released out, the Crossfeed valve is closed.

If the pushbutton is pressed in, the valve opens and the ON white light comes on.

The green OPEN light comes on when the valve is fully open. TM UF UE 30 1-T0 1 LE VE L 1

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SYSTEM CONTROLS

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28 - FUEL SYSTEM

28-00-00 FUEL ECAM PAGE PRESENTATION

CONTENTS: Fuel On Board Fuel Used Engine LP Valves Tank Pumps Transfer Valves Crossfeed Valve APU LP Valve Fuel Quantities Fuel Temperatures TM UF UE 50 1 LE VE L 1

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FUEL ECAM PAGE PRESENTATION

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28 - FUEL SYSTEM

28-20-00 SYSTEM OPERATION

CONTENTS: Auto Mode Manual Mode Self Examination TM UF UE 90 1 LE VE L 1

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We are on the ground, slats extended and in AUTO MODE. All tank pump pushbuttons are pressed in: wing tank pumps run all the time and center tank pumps are not running because the slats are extended.

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SYSTEM OPERATION - AUTO MODE

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

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SYSTEM OPERATION - AUTO MODE (CONT’D)

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When the center tank fuel has been used, the related pumps stop automatically 5 mn after the center tank fuel low level has been reached.

The engines are supplied by the wing tank pumps.

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SYSTEM OPERATION - AUTO MODE (CONT’D)

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When the inner cell quantity decreases to a given value, the transfer valves open automatically and are latched until the next refuelling. The outer cell fuel flows to inner cell.

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SYSTEM OPERATION - AUTO MODE (CONT’D)

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LANDING ...

When the engines are stopped, the engine identification numbers become amber.

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SYSTEM OPERATION - AUTO MODE (CONT’D)

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We are in cruise ...

The center tank pumps stop with fuel remaining in the center tank.

The FAULT light comes on, on the MODE SEL pushbutton. The LO amber symbols come on as the supply pressure drops. The fuel auto feed fault message appears on the engine warning display.

FUEL: AUTO FEED FAULT

The FAULT is indicated if L or R wing tank quantity becomes less than 5000 KG and the center tank quantity is above 250 KG. TM UF UE 90 1-T0 9 LE VE L 1

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SYSTEM OPERATION - MANUAL MODE

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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 AUTO MODE with fuel in the center tank, and one minute after 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, center tank pumps:

A - Must be manually switched OFF.

B - Stop automatically and wing tank pumps start running. C - Stop automatically. TM UF UE 90 1 LE VE L 1

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28 - FUEL SYSTEM

28-00-00 SYSTEM WARNINGS

CONTENTS:

Left Tank Pump 1 Lo Press Center Tank Pump 2 Lo Press Right Tank Pump 1 + 2 Lo Press Center Tank Pumps Lo Press Xfeed Valve Fault

Engine 1 LP Valve Open Left Wing Tank Lo Level Right Transfer Valve Closed Left Outer Tank Hi Temp Right Inner Tank Lo Temp Auto Feed Fault

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SYSTEM WARNINGS - APU LP VALVE FAULT

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28 - FUEL SYSTEM

28-12-00 VENTING SYSTEM

DESCRIPTION/OPERATION

CONTENTS: General

Vent Surge Tank

Wing Tank Venting System Center Tank Venting System Overpressure Protection Vent Float Valves

Self Examination TM UF UE G0 1 LE VE L 3

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The fuel tank venting system prevents overstressing of tanks.

VENT SURGE TANK

Each vent surge tank vents to the atmosphere through a NACA type intake connected with a vent duct.

Inside the vent duct there is a vent protector (flame arrestor) which reduces the risk of a ground fire igniting the fuel tanks.

Fuel spilled through the vent pipes into the surge tank is induced back into the outer cell by a scavenge jet pump using motive power from the wing fuel pumps. WING TANK VENTING SYSTEM

Each wing tank inner and outer cells vent to the related vent surge tank. The vent lines are fitted with a vent float valve.

The ducts are large enough to ensure that if the pressure refuelling shut-off failed, excess fuel can be discharged overboard through the NACA intake. A rubber check valve installed in the vent line allows any fuel that finds its way into the vent lines to drain back into the tank.

The center tank vents into the left hand vent surge tank.

The center tank vent line is a conventional open line, large enough for airflow, which is provided with a check valve.

OVERPRESSURE PROTECTION

Overpressure protectors are installed in the system to relieve pressure in the tanks that might occur through vent blockage or a pressure refuelling gallery failure.

An excess pressure in the outer cell relieves fuel into the inner cell via an overpressure protector mounted on rib 15.

An excess pressure in the inner cell or in the Vent surge tank relieves fuel overboard via an overpressure protector installed on a tank access panel.

The center tank overpressure protector relieves fuel into the left inner cell.

VENT FLOAT VALVES

Two vent float valves prevent fuel from passing in the vent lines during aircraft bank manoeuvres.

The open ends of the ducts and the vent float valves which permit air to vent but not fuel, are positioned at the optimum levels for refueling and normal ground/flight manoeuvers.

A vent float valve fitted to the outer side of sealed rib 15 permits air to be vented from the outer cell to the inner cell during flight manoeuvers.

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VENTING SYSTEM DESCRIPTION/OPERATION

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via 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.

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28 - FUEL SYSTEM

28-16-00 FUEL IDG COOLING SYSTEM

PRESENTATION

CONTENTS: Principle Fuel Return Pump Logic

Fuel Return Valve Closure : Low Level

Fuel Return Valve Closure : Inner Cell High Temperature Fuel Return Valve Closure : Outer Cell High Temperature Fuel Return Valve Closure : Pump Pressure Loss

Fuel Return Valve Closure : Overflow Self Examination TM UF UE H0 1 LE VE L 3

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The Integrated Drive Generator oil is cooled by fuel; a recirculation system is installed.

Some fuel supplying the engines is used to cool the IDG oil. A return valve allows the hot fuel to be returned to the Outer cell.

The Return valve opens at low engine fuel flow if the engine oil temperature is above 93 degrees C.

The return valve mixes the hot fuel with cold fuel from the LP pump to maintain the temperature of the returned fuel below 100 degrees C.

FLSCU1 and ECU1 control the recirculation system in the left wing.

FLSCU2 and ECU2 control the right wing system. FUEL RETURN

The recirculated fuel is sent to the outer cell through a check valve and a pressure holding valve in order to prevent the fuel from boiling.

The pressure holding valve maintains a pressure of 18 psi 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 tank to the engine when the recirculation system is not in operation.

Note: When the Outer cell is full, the fuel overflows into the Inner cell through a spill pipe.

As long as fuel is being delivered from the center tank, the wing tanks are still full and will tend to overfill, as the returned fuel is delivered to the wings tanks. In this case the center tank pump stops when the inner cell reaches the FULL level.

The wing tank pumps will operate until approximately 1100 lbs (500 kg) of fuel have been used i.e.: underfull sensors reached. The logic circuit then restarts the Center tank pump.

FRV CLOSURE : LOW LEVEL

The fuel return valve closes when the fuel level in the 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 620 lbs (280 kg).

Note : Closing the return valve will reduce the amount of unuseable fuel. TM UF UE H0 1-T0 1 LE VE L 3

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FUEL IDG COOLING SYSTEM PRESENTATION

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The fuel return valve closes if the fuel temperature is too high in the inner cell (52.5 degrees C). As the returned fuel is hot, the FLSCU prevents temperature limitation exceedance.

In this case, the FLSCU sends an inhibition signal to the FADEC for FRV closure.

FRV CLOSURE : OUTER CELL HIGH TEMPERATURE

The fuel return valve closes if the fuel temperature is too high in the outer cell (55 degrees C).

This prevents a large volume of high temperature fuel from entering the inner cell, in the event of intercell valve opening.

This also keeps the fuel temperature at an acceptable level should a tank rupture occur.

The fuel return valve closes if a low pressure is signalled by all pumps of one wing supplying the related engine and crossfeed valve closed, or if a low pressure is signalled by all pumps of both wings with crossfeed valve opened.

This is to reduce fuel flow and allow maximum available pressure for fuel burn during gravity feeding.

Low pressure is sensed by the pump low pressure switch and signalled to the fuel level sensing control units (FLSCUs).

FRV CLOSURE : OVERFLOW

The fuel return valve closes if the center tank pump fails to respond to the logic signals of the full sensors, causing the wing tank to overflow into the vent surge tank.

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FUEL IDG COOLING SYSTEM PRESENTATION

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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 cell drops to the low level sensor ?

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

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28 - FUEL SYSTEM

28-11-00 WATER DRAIN VALVE OPERATION

CONTENTS: General Job Set Up Drain Procedure Close Up TM UF UE U0 1 LE VE L 2

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Water which collects beneath the fuel in the lowest parts of the wing tanks is drained away through small bore pipes connected to manually

operated 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 YOU

MUST MAKE THE AREA AROUND IT SAFE. IN THE SAFETY AREA DO NOT:

- SMOKE,

- MAKE SPARKS OR FIRE,

- USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES,

AIRCRAFT FUEL IS FLAMMABLE.

A - Follow the safety precautions

B - 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 the base plate of the drain valve.

(2) Turn the bush (2) through 30 deg.

(3) Turn the nut (4) until it touches and seals against 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 the end of its travel. This causes the plunger (1) to open the drain valve and the fuel to flow.

CLOSE UP

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

B - Remove all the ground support equipment, the maintenance equipment, the standard and special tools and all other items.

C - Make sure that the work area is clean and clear of tools and other items.

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WATER DRAIN VALVE OPERATION

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28 - FUEL SYSTEM

28-12-00 TANK AND VENTING SYSTEM

COMPONENTS

CONTENTS:

Water Drain Valve Clack Valve

Cap/Adapter Gravity Fill Overpressure Protector Fuel Vent Protector Float vent valve Check valve

Pressure Relief Valve NACA Vent Intake Vapor Seal Drain Mast Leak Monitor TM UF UE J0 1 LE VE L 3

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- 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. Use approved protective clothing when you go in a fuel tank.

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

WARNING: Make sure you put a warning notice in the cockpit to advise not to operate the flight controls because:

- persons are near the flight control surfaces - equipment is near flight control surfaces. WARNING: Make sure that you have correct fire fighting equipment available before you start any task on fuel system.

WARNING: Make sure that all the circuits in maintenance are isolated before you supply electrical power to the aircraft.

WARNING: Do not go into a fuel tank until the fuel-gas concentration is less than 25 % of Lower Explosive Limit (LEL).

in a fuel tank (unless the fuel-gas concentration is less than 5 % of LEL). A high concentration is unhealthy and toxic. WATER DRAIN VALVE

IDENTIFICATION

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

ZONE: 540, 550, 640, 650, (141, 142) COMPONENT DESCRIPTION

Periodic operation of the valves ensures that water does not collect in quantities sufficient to cause malfunction of the engines.

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TANK AND VENTING SYSTEM COMPONENTS - WATER DRAIN VALVE

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IDENTIFICATION FIN: None LOCATION

ZONE: 540, 640

COMPONENT DESCRIPTION

Ribs 1 and 2 form a Collector Box around the wing tank fuel pumps.

Clack valves at the bottom of rib 2 permit fuel to enter the box but prevent it draining out again. This ensures a fuel supply at the pumps during wing down manoeuvres. TM UF UE J0 1-T0 2 LE VE L 3

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TANK AND VENTING SYSTEM COMPONENTS - CLACK VALVE

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IDENTIFICATION

FIN: 42QM, 43QM, 44QM, 45QM LOCATION

ZONE: 540, 640

An overwing gravity fill cap/adapter is installed in the top surface of each wing tank, giving direct access to the outer cell.

The cap is removed by lifting the hinged handle, set flush in the top of the cap, and turning to unlock. NOTE: Before gravity refuelling make sure that

transfer valves are open.

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TANK AND VENTING SYSTEM COMPONENTS - CAP/ADAPTER GRAVITY FILL

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IDENTIFICATION FIN: 46QM, 47QM, 102QM, 103QM, (96QM) LOCATION ZONE: 540, 640, (147) TM UF UE J0 1-T0 4 LE VE L 3

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TANK AND VENTING SYSTEM COMPONENTS - OVERPRESSURE PROTECTOR

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IDENTIFICATION FIN: 48QM, 49QM LOCATION

ZONE: 550, 650

Vent protector consists of:

-

ice protector

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flame arrestor

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

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TANK AND VENTING SYSTEM COMPONENTS - FUEL VENT PROTECTOR

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IDENTIFICATION

FIN: 15QM, 16QM, 17QM, 18QM LOCATION

ZONE: 540, 640

A float operated arm opens or closes this valve depending upon the fuel level, to permit air to be vented.

Valve also opens when:

-

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

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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 VALVE

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IDENTIFICATION

FIN: 50QM, 51QM, 52QM, 53QM, 120QM, 121QM, 93QM LOCATION

ZONE: 540, 640, 141 COMPONENT DESCRIPTION

Rubber check valves are installed in the vent lines to allow any fuel that finds its way into the vent lines to drain back into the tank.

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TANK AND VENTING SYSTEM COMPONENTS - CHECK VALVE

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IDENTIFICATION FIN: 97QM LOCATION ZONE: 142

The pressure relief valve relieves fuel into the RH wing tank in the event of a center tank refuelling overflow.

Removal/Installation:

-

Canister Check Valves Pressure Switches By pass suction Valve Air Release Valve LP Valves

Jet Pumps

Crossfeed Valve Sequence Valve

Intercell Transfer Valve Fuel Supply Logic

Self Examination TM UF UK A0 1 LE VE L 3

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The main fuel pump system supplies fuel from the fuel tanks to the engines. Each tank has two centrifugal booster pumps.

Fuel is first provided by the center tank pumps and then by the wing tank pumps when the center tank is empty.

The crossfeed system divides the engine fuel feed system into two independent feed systems.

MAIN PUMPS

two check valves. CANISTER CHECK VALVES

The canister allows replacement of the fuel pump without draining fuel.

attached to the wing bottom skin, with an inlet connected to a fuel strainer.

a smaller outlet is connected to the scavenge jet pumps and the fuel pump pressure switch. PRESSURE SWITCHES

The pressure switches monitor the output of the pumps through a pressure pipe.If the pressure from the main pump decreases to less than 6 psi (0,41 bar) the pressure switch sends a warning signal to the ECAM system. TM UF UK A0 1-T0 1 LE VE L 3

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ENGINE FEED SYSTEM DESCRIPTION AND OPERATION

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feed line, downstream of the main pumps. In case of complete main pump failure, the by pass suction valve allows fuel to be sucked from the tank by the engine driven pumps and thus supply the engine by "gravity". AIR RELEASE VALVE

The air release valve releases air trapped in the engine fuel feed line.

The air release valve is installed at the high point between 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 power sources.

The LP valve isolates the engine fuel feed supply at shut-down (normal procedure) or in case of emergency (engine fire procedure).

JET PUMPS

Center tank scavenge jet pumps move fuel and water caught in the tank to the related main pump inlet. Outer cell scavenge jet pumps move the surge tank fuel to the rear intercell transfer valves.

Check valves, in the line between the surge tank, combined with these jet pumps make sure that fuel can not enter the surge tank via the pump if the main pumps are off.

usually in the closed position.

In this position, it divides the main fuel pump system into two parts (one part for each engine).

When the crossfeed valve is open, either tank can supply fuel to either engine.

SEQUENCE VALVE

The wing tank pumps are equipped with a sequence valve to make sure that the center tank is emptied first. INTERCELL TRANSFER VALVE

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

FUEL SUPPLY LOGIC

When all the tanks contain fuel, the center tank will be emptied first.Keeping a fuel mass in the wings as long as possible reduces the bending stresses at the wing roots.

When the center tank fuel has been used, engines are supplied by the inner cells fuel. The outer cell fuel flows to the inner cell by gravity through the transfer valves which open when the inner cell fuel quantity decreases to a given value.

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ENGINE FEED SYSTEM DESCRIPTION AND OPERATION

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first?

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 you close 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.

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28 - FUEL SYSTEM

28-22-00 APU FEED SYSTEM DESCRIPTION AND

OPERATION

CONTENTS: General

Auxiliary Power Unit (APU) Pump Canisters

Pressure Switch

APU Low pressure (LP) Shut-off Valve Crossfeed Operation

FUEL VENT Pushbutton APU MASTER SWITCH Self Examination TM UF UK E0 1 LE VE L 3

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The APU fuel supply system comprises a fuel pump, an LP fuel valve and an actuator on the rear wall of the center tank. The fuel supply to the APU is normally from the left-hand crossfeed line.

The APU LP fuel shut-off system has an LP fuel valve that controls the supply of fuel to the APU. If an APU fire occurs on ground, the APU emergency shut down system closes the LP fuel valve to stop the flow of fuel. When the crossfeed valve is open, either engine feed line (left or right) can supply fuel to the APU. AUXILIARY POWER UNIT (APU) PUMP

The fuel pressure for the APU comes from either the engine fuel pumps or the APU fuel pump.

For normal operation, the essential busbar 801XP (115V AC) supplies the pump motor. When the busbar is not energized, the static inverter busbar 901XP (115V AC) supplies the pump motor.

CANISTERS

The canister permits pump replacement even with fuel in the tanks or in the APU fuel line.

When a pump is removed, the fuel pressure closes the canister inlet and outlet.

The pressure switch controls pump operation. The pressure in the left crossfeed line goes through the check valve to operate a microswitch.

The APU fuel pump stops if the crossfeed line pressure reaches 23.3 PSI absolute (1.6 bar) and restarts at 21,7 PSIA (1.5 bar).

APU LOW PRESSURE (LP) SHUT-OFF VALVE

The APU Low Pressure fuel shut-off valve is used to isolate the APU fuel supply line from the left engine feed line, when the APU does not operate. The two DC motors in the actuator are supplied from different 28 VDC sources.

The valve opens when:

-

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

The fire detection system operates on the ground. TM UF UK E0 1-T0 1 LE VE L 3

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APU FEED SYSTEM DESCRIPTION AND OPERATION

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feed line can also supply the APU fuel supply line. FUEL VENT PUSHBUTTON

When the aircraft is on the ground, it is possible to operate the pump to purge the fuel line.

A pushbutton (hold) on FR 80 in the APU compartment is used to operate the pump.

APU MASTER SWITCH

If the APU MASTER SW pushbutton is pressed to ON, the APU pump will operate if the pump inlet pressure is below 1.5 bar (21.7 PSI) absolute.

This is initiated automatically through the pressure switch. TM UF UK E0 1-T0 1 LE VE L 3

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SELF EXAMINATION

The function of the APU fuel pump pressure switch is:

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.

TM UF UK E0 1 LE VE L 3

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THIS PAGE INTENTIONALLY LEFT BLANK TM UF UK E0 1 LE VE L 3

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28 - FUEL SYSTEM

28-20-00 MAIN FUEL PUMP SYSTEM COMPONENTS

CONTENTS:

Pressure Switch Air Release Valve Sequence Valve

Center Tank Fuel Pump

Center Tank Fuel Pump Removal Information Wing Tank Fuel Pump

Wing Tank Fuel Pump Removal Information Scavenge Jet Pump

Transfer Valve

Transfer Valve Drive Transfer Valve Actuator

TM UF UE K0 1 LE VE L 3

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IDENTIFICATION

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

ZONE: 570, 571, 670, 671 (140) COMPONENT DESCRIPTION

A pressure switch for each fuel pump is mounted on the outside face of the rear wall of the tanks

TM UF UE K0 1-T0 1 LE VE L 3

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TM UF UE K0 1-P0 1 LE VE L 3

MAIN FUEL PUMP SYSTEM COMPONENTS - PRESSURE SWITCH

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IDENTIFICATION FIN: 86QM, 87QM LOCATION

ZONE: 540, 640

It allows air, but not fuel, to be expelled from the pipeline and prevents air being sucked in.

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TM UF UE K0 1-P0 2 LE VE L 3

MAIN FUEL PUMP SYSTEM COMPONENTS - AIR RELEASE VALVE

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ZONE: 540, 640

The SEQUENCE VALVES are pressure relief valves attached to secondary outlets on wing tank pumps only.