a320 Training 28 Fuel System

A320 TECHNICAL 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.

A320 TECHNICAL TRAINING MANUAL _ MECHANICS / ELECTRICS & AVIONICS COURSE

28 FUEL SYSTEM

28 FUEL SYSTEM UET4200

TABLE OF CONTENTS

Page

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

** QTY Indicating SYS Components (3) .......... 261 ** Fuel Level Sensing Components (3) .......... 279 MAINTENANCE PRACTICES SPECIFIC PAGES ** CFDS Specific Page Presentation (3) ...... 293

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

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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

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28 FUEL SYSTEM

28 FUEL SYSTEM UET4200

TABLE OF CONTENTS

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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-00-00 SYSTEM DESIGN PHILOSOPHY

TMUFUE001 LEVEL 1

UET4200

CONTENTS: General Feed Concept Management Self Examination

EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM DESIGN PHILOSOPHY GENERAL 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

TMUFUE001-T01 LEVEL 1

UET4200

The different functions of the system are: - Fuel level and temperature sensing, fuel transfers, fuel recirculation, refuel/defuel control and monitoring, indications, warnings and test. The fuel quantity indicating system comprises: - 1 Fuel Quantity Indicating Computer (FQIC). - 2 Fuel Level Sensor Control Units (FLSCUs).


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A320 TECHNICAL TRAINING MANUAL _

TMUFUE001-P01 LEVEL 1

UET4200

MECHANICS / ELECTRICS & AVIONICS COURSE

28 FUEL SYSTEM

SYSTEM DESIGN PHILOSOPHY EFFECTIVITY EFFECTIVITY ALL

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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.

TMUFUE001 LEVEL 1

UET4200

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 - FUEL SYSTEM 28-11-00 TANK USABLE CAPACITIES

TMUFUE201 LEVEL 1

UET4200

CONTENTS: Wing Tanks Center Tank Vent Surge Tanks Self Examination


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28 FUEL SYSTEM

TANK USABLE CAPACITIES WING TANKS


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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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28 FUEL SYSTEM

TANK USABLE CAPACITIES - WING TANKS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK USABLE CAPACITIES CENTER TANK VENT SURGE TANKS


UET4200

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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28 FUEL SYSTEM

TANK USABLE CAPACITIES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SELF EXAMINATION the maximum - 41291 LBS - 45920 LBS - 52174 LBS

total fuel capacity? (18729 KG) (20866 KG) (23707 KG)

TMUFUE201 LEVEL 1

UET4200

What is A B C


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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-20-00 ENGINE AND APU FUEL FEED PRESENTATION

TMUFUE101 LEVEL 1

UET4200

CONTENTS: Pumps Sequence Valves Crossfeed Valve LP Valves Pressure Switches APU Pump Transfer Valves Air Release Valve Self Examination


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28 FUEL SYSTEM

ENGINE AND APU FUEL FEED PRESENTATION PUMPS

PRESSURE SWITCHES

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.

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

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.


UET4200

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.


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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28 FUEL SYSTEM

ENGINE AND APU FUEL FEED PRESENTATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SELF EXAMINATION Are wing tank pumps running while center tank is 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.

TMUFUE101 LEVEL 1

UET4200

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.


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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-20-00 SYSTEM CONTROLS

TMUFUE301 LEVEL 1

UET4200

CONTENTS: Tank Pumps Mode Selector Center Tank Pumps Crossfeed


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28 FUEL SYSTEM

SYSTEM CONTROLS TANK PUMPS 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.


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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.


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28 FUEL SYSTEM

SYSTEM CONTROLS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TMUFUE301 LEVEL 1

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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-00-00 FUEL ECAM PAGE PRESENTATION

TMUFUE501 LEVEL 1

UET4200

CONTENTS: Fuel On Board Fuel Used Engine LP Valves Tank Pumps Transfer Valves Crossfeed Valve APU LP Valve Fuel Quantities Fuel Temperatures


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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM


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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - ENGINE LP VALVES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - ENGINE LP VALVES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - TANK PUMPS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - TANK PUMPS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - TRANSFER VALVES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - TRANSFER VALVES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - CROSSFEED VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - CROSSFEED VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - APU LP VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL ECAM PAGE PRESENTATION - APU LP VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM


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28 FUEL SYSTEM


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TMUFUE501 LEVEL 1

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28 - FUEL SYSTEM 28-20-00 SYSTEM OPERATION

TMUFUE901 LEVEL 1

UET4200

CONTENTS: Auto Mode Manual Mode Self Examination


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SYSTEM OPERATION AUTO MODE


UET4200

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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28 FUEL SYSTEM

SYSTEM OPERATION - AUTO MODE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM OPERATION AUTO MODE (CONT’D)


UET4200

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


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28 FUEL SYSTEM

SYSTEM OPERATION - AUTO MODE (CONT’D) EFFECTIVITY EFFECTIVITY ALL

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UET4200

After engine start, and regardless of the slat position, the center tank pumps run for 2 minutes. When running, center tank pumps have priority over wing tank pumps. After this delay, center tank pumps stop because slats are still extended.


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28 FUEL SYSTEM


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UET4200

That’s take-off configuration.


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28 FUEL SYSTEM


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28 FUEL SYSTEM



UET4200

With the slats retracted, the center tank pumps start again.


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28 FUEL SYSTEM


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UET4200

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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28 FUEL SYSTEM


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UET4200

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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28 FUEL SYSTEM


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UET4200

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


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28 FUEL SYSTEM


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28 FUEL SYSTEM

SYSTEM OPERATION MANUAL MODE


UET4200

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.


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28 FUEL SYSTEM

SYSTEM OPERATION - MANUAL MODE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM OPERATION MANUAL MODE (CONT’D)


UET4200

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


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28 FUEL SYSTEM

SYSTEM OPERATION - MANUAL MODE (CONT’D) EFFECTIVITY EFFECTIVITY ALL

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UET4200

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


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28 FUEL SYSTEM


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UET4200

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


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28 FUEL SYSTEM


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28 FUEL SYSTEM

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 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 A B C -

the MODE SEL pushbutton control? Center and wing tank pumps. Center tank pumps only. Wing tank pumps only.

TMUFUE901 LEVEL 1

UET4200

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.


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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-00-00 SYSTEM WARNINGS

TMUFUE401 LEVEL 3

UET4200

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 APU LP Valve Fault


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28 FUEL SYSTEM

SYSTEM WARNINGS - LEFT TANK PUMP 1 LO PRESS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - CENTER TANK PUMP 2 LO PRESS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - RIGHT TANK PUMP 1 + 2 LO PRESS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - CENTER TANK PUMPS LO PRESS EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - XFEED VALVE FAULT EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - ENGINE 1 LP VALVE OPEN EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - LEFT WING TANK LO LEVEL EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - RIGHT TRANSFER VALVE CLOSED EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - LEFT OUTER TANK HI TEMP EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - RIGHT INNER TANK LO TEMP EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - AUTO FEED FAULT EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SYSTEM WARNINGS - APU LP VALVE FAULT EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TMUFUE401 LEVEL 3

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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-12-00 VENTING SYSTEM DESCRIPTION/OPERATION

TMUFUEG01 LEVEL 3

UET4200

CONTENTS: General Vent Surge Tank Wing Tank Venting System Center Tank Venting System Overpressure Protection Vent Float Valves Self Examination


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28 FUEL SYSTEM

VENTING SYSTEM DESCRIPTION/OPERATION GENERAL

CENTER TANK VENTING SYSTEM

The fuel tank venting system prevents overstressing of tanks.

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.

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.

TMUFUEG01-T01 LEVEL 3

UET4200

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.


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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TMUFUEG01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

VENTING SYSTEM DESCRIPTION/OPERATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SELF EXAMINATION An excess pressure in the inner cell is relieved via an overpressure protector: A - Into the Outer cell. B - Into the Center tank. C - Overboard.

TMUFUEG01 LEVEL 3

UET4200

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 - FUEL SYSTEM 28-16-00 FUEL IDG COOLING SYSTEM PRESENTATION

TMUFUEH01 LEVEL 3

UET4200

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


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28 FUEL SYSTEM

FUEL IDG COOLING SYSTEM PRESENTATION PRINCIPLE

PUMP LOGIC

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.

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.

TMUFUEH01-T01 LEVEL 3

UET4200

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.


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.

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TMUFUEH01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL IDG COOLING SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL

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FUEL IDG COOLING SYSTEM PRESENTATION FRV CLOSURE : INNER CELL HIGH TEMPERATURE

FRV CLOSURE : PUMP PRESSURE LOSS

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.

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 : OUTER CELL HIGH TEMPERATURE

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.

TMUFUEH01-T02 LEVEL 3

UET4200

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.


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TMUFUEH01-P02 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL IDG COOLING SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL

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FUEL IDG COOLING SYSTEM PRESENTATION SELF EXAMINATION To which tank does the recirculated fuel return ? A - Wing tank outer cell, B - Center tank, C - Wing tank inner cell.

TMUFUEH01 LEVEL 3

UET4200

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

TMUFUEU01 LEVEL 2

UET4200

CONTENTS: General Job Set Up Drain Procedure Close Up


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28 FUEL SYSTEM

WATER DRAIN VALVE OPERATION GENERAL

JOB SET UP

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:

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.

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.

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.

TMUFUEU01-T01 LEVEL 2

UET4200

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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TMUFUEU01-P01 LEVEL 2

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28 FUEL SYSTEM

WATER DRAIN VALVE OPERATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TMUFUEU01 LEVEL 2

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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-12-00 TANK AND VENTING SYSTEM COMPONENTS

TMUFUEJ01 LEVEL 3

UET4200

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


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28 FUEL SYSTEM

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

WARNING: Obey the fuel safety procedures.

WATER DRAIN VALVE

WARNING: Do not get your clothes soaked with fuel. Use approved protective clothing when you go in a fuel tank.

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

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.

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.

TMUFUEJ01-T01 LEVEL 3

UET4200

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).


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TMUFUEJ01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - WATER DRAIN VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS CLACK VALVE IDENTIFICATION FIN: None LOCATION ZONE: 540, 640


UET4200

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.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - CLACK VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS CAP/ADAPTER GRAVITY FILL IDENTIFICATION FIN: 42QM, 43QM, 44QM, 45QM LOCATION ZONE: 540, 640 COMPONENT DESCRIPTION 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. make

sure

that


UET4200

NOTE: Before gravity refuelling transfer valves are open.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - CAP/ADAPTER GRAVITY FILL EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS OVERPRESSURE PROTECTOR IDENTIFICATION FIN: 46QM, 47QM, 102QM, 103QM, (96QM)


UET4200

LOCATION ZONE: 540, 640, (147)


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - OVERPRESSURE PROTECTOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS FUEL VENT PROTECTOR IDENTIFICATION FIN: 48QM, 49QM LOCATION ZONE: 550, 650


UET4200

COMPONENT DESCRIPTION Vent protector consists of: - ice protector - 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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Page Page 98 10 Apr 30/96



UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - FUEL VENT PROTECTOR EFFECTIVITY EFFECTIVITY ALL

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Page Page 99 11 Apr 30/96


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS FLOAT VENT VALVE IDENTIFICATION FIN: 15QM, 16QM, 17QM, 18QM LOCATION ZONE: 540, 640


UET4200

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


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - FLOAT VENT VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS CHECK VALVE IDENTIFICATION FIN: 50QM, 51QM, 52QM, 53QM, 120QM, 121QM, 93QM LOCATION ZONE: 540, 640, 141


UET4200

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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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - CHECK VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS PRESSURE RELIEF VALVE IDENTIFICATION FIN: 97QM LOCATION ZONE: 142


UET4200

COMPONENT DESCRIPTION The pressure relief valve relieves fuel into the RH wing tank in the event of a center tank refuelling overflow. Removal/Installation: - empty Center and RH wing tanks - open manhole covers 148AZ and 640AB.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - PRESSURE RELIEF VALVE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS NACA VENT INTAKE IDENTIFICATION FIN: None LOCATION ZONE: 550, 650


UET4200

COMPONENT DESCRIPTION The flush mounted NACA vent intake provides connection of the vent system to the atmosphere and maintains a slight positive pressure in the fuel tanks during forward flight. The VENT SURGE TANK will hold 50 US gallons before overflowing into the upturned NACA INTAKE duct.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - NACA VENT INTAKE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS VAPOR SEAL IDENTIFICATION FIN: None LOCATION ZONE: 140


UET4200

COMPONENT DESCRIPTION The vapor seal is a fabric membrane that isolates the Center tank from the air conditioning compartment below. Pressurized air from the air conditioning system flows through the space between the vapor seal and the tank bottom to ventilate it.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - VAPOR SEAL EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS DRAIN MAST IDENTIFICATION FIN: None LOCATION ZONE: 140


UET4200

COMPONENT DESCRIPTION A system of drains at the rear of the vapor seal conveys drainage and ventilating (exhaust) air through a drain mast to atmosphere. The drain mast is an aluminium fairing bolted to the underside of the fuselage.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - DRAIN MAST EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS LEAK MONITOR IDENTIFICATION FIN: None LOCATION ZONE: 140


UET4200

COMPONENT DESCRIPTION In the event of fuel flowing from the drain mast, check the leak monitor to determine the area of leakage center tank or APU fuel supply line.


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UET4200


28 FUEL SYSTEM

TANK AND VENTING SYSTEM COMPONENTS - LEAK MONITOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TMUFUEJ01 LEVEL 3

UET4200



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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-21-00 ENGINE FEED SYSTEM DESCRIPTION AND OPERATION

TMUFUKA01 LEVEL 3

UET4200

CONTENTS: General Main Pumps 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


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Page 115 Page 1 Oct 31/96


28 FUEL SYSTEM

ENGINE FEED SYSTEM DESCRIPTION AND OPERATION GENERAL 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.

TMUFUKA01-T01 LEVEL 3

UET4200

MAIN PUMPS The main pumps, driven by a 3 phase 115/200 volt AC motor, have different power supplies. When it is in operation, 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 related canisters, - two fuel strainers, - a suction valve, - two check valves. CANISTER CHECK VALVES The canister allows replacement of the fuel pump without draining fuel.


The wing fuel pump element is located in a canister attached to the wing bottom skin, with an inlet connected to a fuel strainer. The canister has three outlets: - one upper outlet is connected to the engine feed line and contains an internal flap-type check valve. - the other upper outlet is connected to a sequence valve. - a smaller outlet is connected to the scavenge jet pumps and the fuel pump pressure switch. When a fuel pump is not in operation, the two check valves prevent any reverse flow of fuel through the pump. The center fuel pump element is located in a canister attached to the center tank bottom skin, with a lower inlet connected to a fuel strainer. The canister has two outlets: - an upper outlet is connected to the engine feed line and contains an internal flap-type check valve. - 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.

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TMUFUKA01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

ENGINE FEED SYSTEM DESCRIPTION AND OPERATION EFFECTIVITY EFFECTIVITY ALL

28-21-00



28 FUEL SYSTEM

BY PASS SUCTION VALVE

CROSSFEED VALVE

A by pass suction valve is installed on the engine 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".

The crossfeed valve in the center (transfer) tank is 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.

AIR RELEASE VALVE SEQUENCE 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.

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

TMUFUKA01-T02 LEVEL 3

UET4200

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.


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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TMUFUKA01-P02 LEVEL 3

UET4200


28 FUEL SYSTEM

ENGINE FEED SYSTEM DESCRIPTION AND OPERATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SELF EXAMINATION In normal first? A B C -

operation, which tank will be emptied The inner cell. The center tank. 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.

TMUFUKA01 LEVEL 3

UET4200

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 - FUEL SYSTEM 28-22-00 APU FEED SYSTEM DESCRIPTION AND OPERATION

TMUFUKE01 LEVEL 3

UET4200

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


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Page 121 Page 1 Jul 31/98


28 FUEL SYSTEM

APU FEED SYSTEM DESCRIPTION AND OPERATION GENERAL

PRESSURE SWITCH

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.

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).

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.

TMUFUKE01-T01 LEVEL 3

UET4200

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.


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 FUEL VENT pushbutton is used to purge the system during 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 overhead panel is pressed. - The APU FIRE SHUT-OFF switch on the panel forward of the nose landing gear bay is operated. - The fire detection system operates on the ground.

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TMUFUKE01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

APU FEED SYSTEM DESCRIPTION AND OPERATION EFFECTIVITY EFFECTIVITY ALL

28-22-00



28 FUEL SYSTEM

CROSSFEED OPERATION When the crossfeed valve is open, the right-hand engine 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

TMUFUKE01-T01 LEVEL 3

UET4200

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.


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28 FUEL SYSTEM

SELF EXAMINATION The function is: A - To B - To C - To

of the APU fuel pump pressure switch signal any pressure to the ECAM. control the pump operation. shut the APU LP valve in case of fire.

TMUFUKE01 LEVEL 3

UET4200

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.


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28 FUEL SYSTEM

TMUFUKE01 LEVEL 3

UET4200



28-22-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-20-00 MAIN FUEL PUMP SYSTEM COMPONENTS

TMUFUEK01 LEVEL 3

UET4200

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


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28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS PRESSURE SWITCH IDENTIFICATION FIN: 23QA, 27/24QA, 28QA (39QA, 40QA) LOCATION ZONE: 570, 571, 670, 671 (140)

TMUFUEK01-T01 LEVEL 3

UET4200

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


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TMUFUEK01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - PRESSURE SWITCH EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS AIR RELEASE VALVE IDENTIFICATION FIN: 86QM, 87QM LOCATION ZONE: 540, 640


UET4200

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


28-20-00




UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - AIR RELEASE VALVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS SEQUENCE VALVES IDENTIFICATION FIN: None LOCATION ZONE: 540, 640


UET4200

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


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UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - SEQUENCE VALVES EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS CENTER TANK FUEL PUMP IDENTIFICATION FIN: 37QA, 38QA LOCATION ZONE: 140


UET4200

COMPONENT DESCRIPTION The pump delivers fuel at 11000 lb/hr (4989kg/hr) at 30 psi (2.08 bar). Thermal fuse: 200 degrees C. The pump is installed in a canister containing a slide valve so that the pump can be removed without having to drain the tank.


28-20-00




UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - CENTER TANK FUEL PUMP EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS CENTER TANK FUEL PUMP REMOVAL INFORMATION IDENTIFICATION FIN: 37QA, 38QA LOCATION ZONE: 140


UET4200

COMPONENT DESCRIPTION PUMP 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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UET4200


28 FUEL SYSTEM

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

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS WING TANK FUEL PUMP IDENTIFICATION FIN: 21QA, 25QA, 22QA, 26QA LOCATION ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION Sequence valve reduces pump outlet pressure to 25 psi. The pump is installed in a canister containing a slide valve so that the pump can be removed without having to drain the tank.


28-20-00




UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - WING TANK FUEL PUMP EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS WING TANK FUEL PUMP REMOVAL INFORMATION IDENTIFICATION FIN: 21QA, 25QA, 22QA, 26QA LOCATION ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION PUMP REMOVAL: - disconnect electricalconnector - remove attachment bolts - use extractor screws in removal holes - drain it - turn the pump - pull it out


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UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - WING TANK FUEL PUMP REMOVAL INFORMATION EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS SCAVENGE JET PUMP IDENTIFICATION FIN: 66QM to 69QM, 89QM, 90QM LOCATION ZONE: 540, 640, 141, 142


UET4200

COMPONENT DESCRIPTION The Jet pump has: - a venturi type passage - a non-return valve - ports for pipe connection - an attachment plate with studs


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UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - SCAVENGE JET PUMP EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS TRANSFER VALVE IDENTIFICATION FIN: 27QM, 28QM, 29QM, 30QM LOCATION ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION Each valve consists of a cast light alloy body housing a spherical plug.


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UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS TRANSFER VALVE DRIVE IDENTIFICATION FIN: 70QM, 71QM, 72QM, 73QM LOCATION ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION The drive shaft has 2 universal joints. It is keyed at one end for engagement with the actuator and splined at the other end for engagement with the valves.


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UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVE DRIVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS TRANSFER VALVE ACTUATOR IDENTIFICATION FIN: 9QP, 10QP, 11QP, 12QP LOCATION ZONE: 520, 620, 570, 670


UET4200

COMPONENT DESCRIPTION MECHANICAL INDICATOR: shows valve open or closed.


28-20-00




UET4200


28 FUEL SYSTEM

MAIN FUEL PUMP SYSTEM COMPONENTS - TRANSFER VALVE ACTUATOR EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

TMUFUEK01 LEVEL 3

UET4200



28-20-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-20-00 ENGINE AND APU COMPONENTS

TMUFUEL01 LEVEL 3

UET4200

CONTENTS: Pressure Holding Valve (recirculation) Check Valve (recirculation) Crossfeed Valve Crossfeed Valve Actuator Engine LP Fuel Valve Engine LP Fuel Valve Actuator APU Fuel Pressure Switch APU Fuel Pump APU Fuel Pump Canister APU Fuel LP Valve APU Fuel LP Valve Actuator


28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS PRESSURE HOLDING VALVE (recirculation/cooling) IDENTIFICATION FIN: 124QM, 125QM LOCATION ZONE: 540, 640

TMUFUEL01-T01 LEVEL 3

UET4200

COMPONENT DESCRIPTION Valve maintains line pressure of 18 psi; if pressure increases, fuel bleeds into outer cell.


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TMUFUEL01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

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

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS CHECK VALVE (recirculation/cooling) IDENTIFICATION FIN: 122QM, 123QM LOCATION ZONE: 471, 481


UET4200

COMPONENT DESCRIPTION One fuel recirculation check valve is mounted on the lower side of the bottom skin between ribs 7 and 8 and prevents reverse flow from the tank to the engine in the event of a fuel pipe failure.


28-20-00




UET4200


28 FUEL SYSTEM

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

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS CROSSFEED VALVE IDENTIFICATION FIN: 10QM LOCATION ZONE: 142


UET4200

COMPONENT DESCRIPTION Access to Crossfeed valve: - defuel Center tank - open main door of RH main gear - remove manhole cover 148AZ.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - CROSSFEED VALVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS CROSSFEED VALVE ACTUATOR IDENTIFICATION FIN: 5QE LOCATION ZONE: 148


UET4200

COMPONENT DESCRIPTION The Crossfeed valve actuator has twin electric motors which drive a common differential gear to turn the spherical plug through 90 degrees. This gear allows either motor to drive the valve if the other motor is inoperative.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - CROSSFEED VALVE ACTUATOR EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS ENGINE LP FUEL VALVE IDENTIFICATION FIN: 12QM, 13QM LOCATION ZONE: 520, 620


UET4200

COMPONENT DESCRIPTION Each Engine LP valve is bolted to a mounting on the wing front spar.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - ENGINE LP FUEL VALVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS ENGINE LP FUEL VALVE ACTUATOR IDENTIFICATION FIN: 9QG, 10QG LOCATION ZONE: 520, 620


UET4200

COMPONENT DESCRIPTION The epicyclic gear allows one of the 2 motors to turn the spherical plug if the other motor is inoperative.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - ENGINE LP FUEL VALVE ACTUATOR EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS APU FUEL PRESSURE SWITCH IDENTIFICATION FIN: 7QC LOCATION ZONE: 141


UET4200

COMPONENT DESCRIPTION Pressure switch monitors APU pump inlet pressure: 21.7 psi: switch closure to start the pump 23.3 psi: switch opening to stop the pump.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - APU FUEL PRESSURE SWITCH EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS APU FUEL PUMP IDENTIFICATION FIN: 4QC LOCATION ZONE: 141


UET4200

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


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - APU FUEL PUMP EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS APU FUEL PUMP CANISTER IDENTIFICATION FIN: 9QM LOCATION ZONE: 141


UET4200

COMPONENT DESCRIPTION The CANISTER is attached to the inside of the wing box rear spar with 5 bolts. Three of these bolts are used to secure a drain gutter to the outside of the rear spar to collect any fuel leakage and divert it away from the installation area.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - APU FUEL PUMP CANISTER EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS APU FUEL LP VALVE IDENTIFICATION FIN: 14QM


UET4200

LOCATION ZONE: 147


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - APU FUEL LP VALVE EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

ENGINE AND APU COMPONENTS APU FUEL LP VALVE ACTUATOR IDENTIFICATION FIN: 3QF LOCATION ZONE: 147


UET4200

COMPONENT DESCRIPTION The actuator can be removed from the valve in-situ without having to drain the system.


28-20-00




UET4200


28 FUEL SYSTEM

ENGINE AND APU COMPONENTS - APU FUEL LP VALVE ACTUATOR EFFECTIVITY EFFECTIVITY ALL

28-20-00



28 FUEL SYSTEM

TMUFUEL01 LEVEL 3

UET4200



28-20-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 REFUEL/DEFUEL SYSTEM PRESENTATION

TMUFUEF01 LEVEL 1

UET4200

CONTENTS: R/D Coupling Refuel Valves Diffusers Air Inlet and Drain Valves Defuel/Transfer Valve Pressure Relief Valve High Level Sensor Self Examination


28-25-00

Page 175 Page 1 Nov 30/95


28 FUEL SYSTEM

REFUEL/DEFUEL SYSTEM PRESENTATION R/D COUPLING

AIR INLET AND DRAIN VALVES

A single pressure refuelling coupling is positioned under the right hand wing leading edge. The Refuel/Defuel coupling supplies the center tank and Outer cells. When the Outer cells are full, fuel overflows into the Inner cells via a spill pipe. The RH coupling is standard while the LH coupling shown is optional. When not in use, the coupling is fitted with a pressure blanking cap.

The Air Inlet valve installed on the refuel line, admits air into the refuel line so that the line may drain. A drain valve drains fuel from the refuel line into the inner cell. The Air Inlet Valve is near the inner cell Refuel Valve. The fuel is free to flow through the drain valve except under refuel line pressure. DEFUEL/TRANSFER VALVE

REFUEL VALVE The fuel flow into each tank is controlled by a solenoid operated Refuel valve. All Refuel valves are identical and interchangeable. They may be manually operated, by pushing a plunger on the valve itself. DIFFUSERS

PRESSURE RELIEF VALVE The pressure relief valve will relieve fuel into the Right hand wing tank in the event of a center tank refuelling overflow. HIGH LEVEL SENSOR One high level sensor is installed in the center tank and in each Inner cell. When immersed in fuel, the related Refuel valve closes.

TMUFUEF01-T01 LEVEL 1

UET4200

Diffusers, installed on the Refuel lines, diffuse fuel into the tanks with minimum turbulence and electrostatic build up.

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


28-25-00



TMUFUEF01-P01 LEVEL 1

UET4200


28 FUEL SYSTEM

REFUEL/DEFUEL SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

SELF EXAMINATION The Inner A B C -

cell is refuelled only when: Center tank is full. Outer cell is full. Outer cell is empty.

TMUFUEF01 LEVEL 1

UET4200

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


28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 REFUEL/DEFUEL CONTROL PANEL

TMUFUEP01 LEVEL 1

UET4200

CONTENTS: Multi-Tank Indicator High Level Lights Refuel Valve Selectors Mode Selector Open Light Test Switch Preselected Actual Rocker Switch End Light


28-25-00

Page 179 Page 1 Feb 30/96


28 FUEL SYSTEM

REFUEL/DEFUEL CONTROL PANEL MULTI-TANK INDICATOR

OPEN LIGHT

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

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

HIGH LEVEL LIGHTS TEST SWITCH A blue HI LVL light for each tank comes on when the associated high level sensor is covered. The corresponding refuel valve will close. REFUEL VALVE SELECTOR There is one Refuel Valve selector per tank. For an automatic refueling, these Refuel Valves selectors remain in the NORM position. For defuelling the valves will not open. Selector set to open : the Refuel valve operation depends on the MODE SELECTOR position. With the Mode Selector in the Refuel position, each Refuel valve closes when the associated high level is reached.When the REFUEL VALVE selector is set to the SHUT position, the Refuel valve is closed. This is independent of the MODE SELECTOR position.

When the TEST switch is set to the HI LVL position, the HI LVL lights come on if the high level sensors and their circuits are serviceable.A filament test is performed when the TEST switch is set to LTS. All the panel lights come on and all quantity indications show 8s.

TMUFUEP01-T01 LEVEL 1

UET4200

MODE SELECTOR With the MODE SELECTOR at OFF, the Refuel Valves are closed. When the MODE SELECTOR is set to REFUEL, the Refuel Valves operate automatically or manually depending on the position of the Refuel Valve selectors.For Defueling or Transfer of fuel the MODE SELECTOR is set to DEFUEL/TRANSFER. It opens the Defuel/Transfer Valve.


28-25-00



TMUFUEP01-P01 LEVEL 1

UET4200


28 FUEL SYSTEM

REFUEL/DEFUEL CONTROL PANEL EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL/DEFUEL CONTROL PANEL PRESELECTED When automatic refueling, the fuel quantity taken aboard is governed by the setting on the PRESELECTED display. ACTUAL The ACTUAL Total quantity indication displays the amount of fuel on board. ROCKER SWITCH The desired fuel figure of the Preselector is obtained by tripping the rocker switch to decrease or increase. END LIGHT

TMUFUEP01-T02 LEVEL 1

UET4200

The green END light comes on when automatic refuelling is complete. It flashes in case of incorrect fuel preselection or when automatic refuel operation has stopped for any reason other than completion of normal operation.


28-25-00



TMUFUEP01-P02 LEVEL 1

UET4200


28 FUEL SYSTEM

REFUEL/DEFUEL CONTROL PANEL EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

TMUFUEP01 LEVEL 1

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-00-00 COCKPIT PRESELECTOR PRESENTATION

Quantity

Preselector

In

Flight

TMUFUZB01 LEVEL 3

UET4200

CONTENTS: General Optional Fuel Compartment


28-00-00



28 FUEL SYSTEM

COCKPIT PRESELECTOR PRESENTATION GENERAL The basic refuel/defuel system of the A/C is controlled from the belly fairing refuel/defuel panel. OPTIONAL FUEL COMPARTMENT

QUANTITY

PRESELECTOR

IN

FLIGHT

Optionally, the refuelling operation can also be controlled from the cockpit via the cockpit refuel panel. From this preselector, the aircrew can set the required quantity of fuel during an automatic refuelling operation. This cancels any fuel quantity set on the belly fairing refuel/defuel panel.

TMUFUZB01-T01 LEVEL 3

UET4200

When the required fuel quantity is set on the cockpit preselector, the ready for refuelling light comes on. Located in the right hand wing, adjacent to the refuel coupling, it can operate in parallel with an optional ready for refuelling light installed adjacent to the L/H refuel coupling.


28-00-00



TMUFUZB01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

COCKPIT PRESELECTOR PRESENTATION EFFECTIVITY EFFECTIVITY ALL

28-00-00



28 FUEL SYSTEM

TMUFUZB01 LEVEL 3

UET4200



28-00-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 REFUEL/DEFUEL SYSTEM DESCRIPTION AND OPERATION

TMUFUKH01 LEVEL 3

UET4200

CONTENTS: General Refuel/Defuel Control Panel Refuel/Defuel Coupling Refuel Valves and Refuel Gallery Spill Pipes Diffusers Air Inlet and Drain Valves Defuel/Transfer Valve Pressure Relief Valves High Level Sensors Overwing Refueling Points Self Examination


28-25-00



28 FUEL SYSTEM

REFUEL/DEFUEL SYSTEM DESCRIPTION AND OPERATION GENERAL

REFUEL/DEFUEL COUPLING

The Refuel/Defuel system controls the fuel flow into or out of the aircraft. Automatic Refueling, manual refuel, defuel or ground transfer are controlled from the Refuel/Defuel control panel, installed on the belly fairing.A Refuel/Defuel coupling, also installed in the leading edge of the wing, is the interface between the Refuel/Defuel system and the external fuel source. Wing tank gravity refueling is possible.To fill the fuel tanks to their maximum capacity, the aircraft must be level.During an automatic refueling, the refueling of each fuel tank is controlled by the Fuel Quantity Indicating Computer (FQIC).The main fuel pumps are used to defuel the aircraft. The defuel/transfer valve and the crossfeed valve must be open.

The Refuel/Defuel coupling supplies the wing tanks and the center tank. When not in use, the coupling is fitted with a pressure blanking cap.The Refuel/Defuel coupling has a standard 2.5 inch adaptor flange.The coupling ring has a break-away groove around its circumference. This prevents damage to the aircraft structure if a sideways force is applied. REFUEL VALVE AND REFUEL GALLERY Each refuel valve, one per tank, is the interface between the refuel gallery and the related fuel tank.The valve is controlled by a solenoid which, when energized and a refuel pressure is supplied,opens the valve.The refuel gallery is a fuel line that connects all the refuel valves together.

REFUEL/DEFUEL CONTROL PANEL

TMUFUKH01-T01 LEVEL 3

UET4200

SPILL PIPES The primary components on the refuel/defuel control panel are: - the control panel - the fuel quantity preselector - the fuel quantity indicator. When the quick-release door of the Refuel/Defuel control panel is opened, it operates a microswitch which sends a signal to the FQIC and connects the 28VDC supply to the Refuel/Defuel electrical circuits.


During a refuel operation, the outer cell is filled first. When it is full, fuel flows into the inner cell through the spill pipe which connects the two cells together. DIFFUSERS The diffusers, installed on refuel lines, diffuse fuel into the tanks with minimum turbulence and electrostatic build up.

28-25-00



TMUFUKH01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

REFUEL/DEFUEL SYSTEM DESCRIPTION AND OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

AIR INLET AND DRAIN VALVES

OVERWING REFUELING POINTS

The air inlet valve lets air into the refuel gallery after refueling. Thus fuel can drain from the refuel gallery through the fuel drain valve.A pipe extends from the air inlet valve to the outboard side of RIB 21. This pipe makes sure that the air inlet remains above the fuel level at all times.This stops the movement of fuel from one wing tank to another by gravity. The fuel drain valves are closed by fuel pressure in the refuel gallery. When the pressure source is removed, the valve opens to allow fuel to drain from the refuel gallery into the wing tank.

Each wing tank has an overwing refuel point installed in the upper wing surface, to refuel the aircraft when a pressure refuel source is not available.During an overwing refuel, the fuel only goes into the wing tank. It is then necessary to do a fuel transfer to get the fuel into the correct fuel-load configuration.

DEFUEL/TRANSFER VALVE The defuel/transfer valve connects the main fuel pump system to the refuel gallery. When open, the valve permits the fuel in the main fuel pump system to be moved into the refuel gallery.The valve is controlled by the MODE SELECT switch on the Refuel/Defuel control panel. PRESSURE RELIEF VALVE

TMUFUKH01-T01 LEVEL 3

UET4200

The pressure relief valve releases fuel into the right hand wing tank if a center tank overflow occurs. HIGH LEVEL SENSOR One high level sensor is installed in each tank.When the high level sensor is immersed in fuel, the Fuel Level Sensor Control Unit (FLSCU) receives this state, amplifies this signal to control the refuel valve to close.


28-25-00



28 FUEL SYSTEM

SELF EXAMINATION How is the Refuel valve normally opened ? A - By energization of a solenoid and application of fuel pressure. B - Only by pressing-in the manual command button. C - Only by opening the panel door and application of pressure or suction. When performing a Refuel, Defuel or ground transfer, the R/D electrical circuits are enabled by ? A - Power from the aircraft electrical network only. B - Carrying out the high level test. C - Contact of the panel door position relay.

TMUFUKH01 LEVEL 3

UET4200

What is the purpose of the fuel drain valve ? A - To decrease the fuel flow in the R/D gallery. B - To avoid a reverse flow to the R/D gallery. C - To drain remaining fuel from the R/D gallery.


28-25-00



28 FUEL SYSTEM

TMUFUKH01 LEVEL 3

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 AUTOMATIC REFUEL OPERATION

TMUFUET01 LEVEL 2

UET4200

CONTENTS: Preparation On Panel 800 VU Automatic Refueling Close-up


28-25-00

Page 195 Page 1 Jan 31/96


28 FUEL SYSTEM

AUTOMATIC REFUEL OPERATION PREPARATION

ON PANEL 800 VU

You must stop the fuel tanker 200 ft. (60 m) from the aircraft nose. If there is a test on the weather radar, do not refuel the aircraft until the test is completed. Before you refuel the aircraft you must make the area around the aircraft safe. Aircraft fuel is flammable. Persons in the safety area must not: - Smoke. - Make sparks of fire. - Use any equipment which is not approved for the refuel procedure. Obey the safety precautions for the refuel procedure. Make sure that the fuel tanker driver has drained the water from the fuel tanker.

Set and hold the TEST switch in the LTS position. - all the panel lights come on. - the FUEL QTY and REFUEL displays show eights. Release the TEST switch. - all the panel lights go off. - The FUEL QTY and REFUEL displays show the tank quantities. Set and hold the TEST switch to the HI LVL position. - the HI LVL lights change condition; if they were on, they will go off and vice versa. Release the TEST switch. - the HI LVL lights go back to their initial condition.

TMUFUET01-T01 LEVEL 2

UET4200

CAUTION: DO NOT USE THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME TO REFUEL THE AIRCRAFT. USE ONLY ONE SIDE. WARNING: YOU MUST MAKE SURE THAT YOU HAVE GROUNDED THE FUEL TANKER AND THE AIRCRAFT CORRECTLY. Put the access platform in place. Make sure that the hose coupling is clean, then connect it to the aircraft. Energize the aircraft electrical network. Open access door 192 MB. Make sure that the panel floodlight comes on. Refuel pressure at the couplings is maximum 50 psi (3.45 bar).


28-25-00



TMUFUET01-P01 LEVEL 2

UET4200


28 FUEL SYSTEM

AUTOMATIC REFUEL OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

AUTOMATIC REFUELING

CLOSE-UP

The required total quantity of fuel is preselected by using the rocker switch to decrease or increase the figure until the required total quantity is shown on the preselector indicator. The total contents actually in the tanks is shown in the ACTUAL display. - REFUEL VALVES switches remain at NORM and guarded. - Lift the guard then set the MODE SELECT switch to REFUEL. - Start the pumps on the fuel tanker. All the REFUEL VALVES open, the tanks fill simultaneously but in the wing tanks the outer cells will fill before the inner cells start filling to ensure the VMO requirements are met. If less than a full load is being taken on, the distribution is in the following order: outer cells, inner cells, center tank, depending on the fuel load required. On the REFUEL panel, the END light comes on when refueling is completed and the final quantity on board will be as PRESELECTED with 100 Kg tolerance. - Set the MODE SELECT switch to OFF and guard it.

Close access door 192 MB. De-energize the aircraft electrical network. Disconnet the hose-coupling of the fuel tanker from the aircraft. Install the cap of refuel coupling. Disconnect the fuel tanker to aircraft ground cable. Remove the access platform.

TMUFUET01-T02 LEVEL 2

UET4200

AUTOMATIC REFUEL OPERATION


28-25-00



TMUFUET01-P02 LEVEL 2

UET4200


28 FUEL SYSTEM

AUTOMATIC REFUEL OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

TMUFUET01 LEVEL 2

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 MANUAL REFUEL OPERATION

TMUFUEQ01 LEVEL 2

UET4200

CONTENTS: Preparation On Panel 800 VU


28-25-00



28 FUEL SYSTEM

MANUAL REFUEL OPERATION PREPARATION

ON PANEL 800 VU

You must stop the fuel tanker 200 ft. (60 m) from the aircraft nose, if there is a test on the weather radar. Do not refuel the aircraft until the test is completed. Before you refuel the aircraft you must make the area around the aircraft safe. Aircraft fuel is flammable. Persons in the safety area must not: - Smoke. - Make sparks or a fire. - Use any equipment which is not approved for the refuel procedure. Obey the safety precautions for the refuel procedure. Make sure that the fuel tanker driver has drained the water from the fuel tanker.

The High Level and Filament tests must be performed. - Put the REFUEL VALVES switch(es) of the tank(s) to be refuelled to the OPEN position. - Put the MODE SELECT switch to the REFUEL position. - Make sure that the ACTUAL display increases. - Monitor the tank quantity display on the MTI. - When each tank has the correct fuel content or the HIGH LEVEL is reached (in this case, the REFUEL VALVE closes automatically), put its REFUEL VALVE switch to the SHUT position. - Stop the pump on the fuel tanker. - SET MODE SELECT switch to the OFF position. - Make sure that all switches are in their NORM and guarded position.

TMUFUEQ01-T01 LEVEL 2

UET4200

CAUTION: DO NOT USE THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME TO REFUEL THE AIRCRAFT. USE ONLY ONE SIDE. WARNING: YOU MUST MAKE SURE THAT YOU HAVE GROUNDED THE FUEL TANKER AND THE AIRCRAFT CORRECTLY. Make sure that the hose coupling is clean, then connect it to the aircraft. Energize the aircraft electrical network. Open the access door 192 MB. Make sure that the panel floodlight comes on. Refuel pressure at the couplings is 50 psi (3.45 bar).


28-25-00



TMUFUEQ01-P01 LEVEL 2

UET4200


28 FUEL SYSTEM

MANUAL REFUEL OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

TMUFUEQ01 LEVEL 2

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 DEFUEL OPERATION

TMUFUER01 LEVEL 3

UET4200

CONTENTS: Defuel Operation


28-25-00



28 FUEL SYSTEM

DEFUEL OPERATION

TMUFUER01-T01 LEVEL 3

UET4200

For a defuelling, operate the REFUEL / DEFUEL panel on panel 800VU and the FUEL panel in the cockpit while watching the FUEL page on the lower ECAM display unit. When defuelling, the engine feed pumps are used to push the fuel through the engine feed pipeline and then by transfer through the refuel lines to discharge at the refuel coupling. - Set the MODE SELECT switch to DEFUEL XFR position and check that OPEN light comes on. - Put XFEED pushbutton ON and check that the valve OPEN light comes on (overhead panel on flight deck). - Refuel valves are closed. - On FUEL overhead panel, set pumps ON. The outer cells are defuelled when the inner cells have been emptied.When the fuel level in the inner cell drops to the low level sensors, the sensors signal the intercell transfer valves to open to permit the fuel in the outer cell to drain into the inner cell. It is then discharged by the inner cell pumps.


28-25-00



TMUFUER01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

DEFUEL OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

DEFUEL OPERATION When required tank quantity is defuelled, reset the system as follows: - On the FUEL panel, set XFEED pushbutton to OFF and the MODE SEL pushbutton to AUTO. - On the REFUEL/DEFUEL panel set MODE SELECT to OFF and check that OPEN light goes off.

TMUFUER01-T02 LEVEL 3

UET4200

NOTE: The flight unbalance limitation is 2000 KG.


28-25-00



TMUFUER01-P02 LEVEL 3

UET4200


28 FUEL SYSTEM

DEFUEL OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

TMUFUER01 LEVEL 3

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 FUEL TRANSFER OPERATION

TMUFUES01 LEVEL 3

UET4200

CONTENTS: Fuel Transfer Operation


28-25-00



28 FUEL SYSTEM

FUEL TRANSFER OPERATION

TMUFUES01-T01 LEVEL 3

UET4200

Transfer of fuel from the left wing into the right wing until the two wing tank contents are equal.


28-25-00



TMUFUES01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL TRANSFER OPERATION EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

FUEL TRANSFER OPERATION Open the DEFUEL/TRANSFER valve. Open the right tank REFUEL valve. Open the CROSSFEED valve. Start the left tank pumps.


UET4200

-


28-25-00




UET4200


28 FUEL SYSTEM


28-25-00



28 FUEL SYSTEM

FUEL TRANSFER OPERATION


UET4200

Stop the fuel transfer when the quantity of the two wing tanks is balanced. Reset all the switches.


28-25-00




UET4200


28 FUEL SYSTEM


28-25-00



28 FUEL SYSTEM

TMUFUES01 LEVEL 3

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-25-00 REFUEL AND DEFUEL SYSTEM COMPONENTS

TMUFUEM01 LEVEL 3

UET4200

CONTENTS: Coupling Diffuser Fuel Drain Valve Center Tank Pressure Relief Valve Spill Pipe Check Valve Refuel Valve Refuel Valve Canister Defuel/Transfer Valve Defuel/Transfer Valve Actuator Air Inlet Valve


28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS 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 EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES. AIRCRAFT FUEL IS FLAMMABLE.

COUPLING IDENTIFICATION FIN: 40QM (100QM), 41QM (101QM) LOCATION: ZONE: 620 (520)

TMUFUEM01-T01 LEVEL 3

UET4200

COMPONENT DESCRIPTION The standard 2.5 inch single pressure refuel coupling is positioned beneath the RH wing leading edge. When not in use the coupling is fitted with a pressure blanking cap (41QM). * A refuel coupling is also fitted (optional) on the LH wing leading edge.


28-25-00



TMUFUEM01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - COUPLING EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS DIFFUSER IDENTIFICATION FIN: None LOCATION: ZONE: 540, 640, 142


UET4200

COMPONENT DESCRIPTION Fuel from the branch line ejects from the trough and is deflected by the baffle across the floor of the tank, with a minimum of turbulence and electrostatic build up.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - DIFFUSER EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS FUEL DRAIN VALVE IDENTIFICATION FIN: 31QM, 32QM LOCATION: ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION The fuel drain valve allows fuel to drain from the refuel line into each wing tank except under refuel/defuel pressure.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - FUEL DRAIN VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS CTR TK PRESSURE RELIEF VALVE IDENTIFICATION FIN: 97QM LOCATION: ZONE: 142


UET4200

COMPONENT DESCRIPTION Removal/Installation: - empty Center and RH wing tanks, - open manhole covers 148AZ and 640AB. The pressure relief valve relieves fuel into the RH wing tank in the event of a center tank refuelling overflow.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - CTR TK PRESSURE RELIEF VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS SPILL PIPE CHECK VALVE IDENTIFICATION FIN: 54QM, 55QM LOCATION: ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION A check valve is installed in each spill pipe. This sphincter-type valve allows fuel in the spill pipe to drain through it into the tank but does not permit reverse flow.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - SPILL PIPE CHECK VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS REFUEL VALVE IDENTIFICATION FIN: 7QU, 10QU, 8QU


UET4200

LOCATION: ZONE: 520, 620, 148


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - REFUEL VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS REFUEL VALVE CANISTER IDENTIFICATION FIN: 19QM, 20QM, 88QM LOCATION: ZONE: 540, 640, 148


UET4200

COMPONENT DESCRIPTION The valve assembly may be removed from the canister without loss of fuel.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - REFUEL VALVE CANISTER EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS DEFUEL/TRANSFER VALVE IDENTIFICATION FIN: 11QM LOCATION: ZONE: 142


UET4200

COMPONENT DESCRIPTION When open, the defuel/transfer valve connects the refuel pipeline to the engine supply line when defuelling or transferring from tank to tank.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - DEFUEL/TRANSFER VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS DEFUEL/TRANSFER VALVE ACTUATOR IDENTIFICATION FIN: 11QU LOCATION: ZONE: 148


UET4200

COMPONENT DESCRIPTION The actuator (11GV) is secured to its mounting by a "V" band clamp.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - DEFUEL/TRANSFER VALVE ACTUATOR EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS AIR INLET VALVE IDENTIFICATION FIN: None LOCATION: ZONE: 520, 620


UET4200

COMPONENT DESCRIPTION The air inlet valve admits air into the refuel line, so that the line may drain.


28-25-00




UET4200


28 FUEL SYSTEM

REFUEL AND DEFUEL SYSTEM COMPONENTS - AIR INLET VALVE EFFECTIVITY EFFECTIVITY ALL

28-25-00



28 FUEL SYSTEM

TMUFUEM01 LEVEL 3

UET4200



28-25-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-42-00 QUANTITY INDICATING

TMUFUEB01 LEVEL 3

UET4200

CONTENTS: General FQI Computer Probes Capacitance Index Compensator (CIC) Cadensicons Fuel Level Sensing Control Units (FLSCUs) Refuel Control Panel Multi-tank Indicator (MTI) Preselector L/G Control Lever ADIRUs CFDS FMGCs ECAM Self Examination


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Page 241 Page 1 Sep 30/99


28 FUEL SYSTEM

QUANTITY INDICATING GENERAL

CAPACITANCE INDEX COMPENSATOR (CIC)

The fuel quantity indicating is a computerized capacitance type system. The system mainly provides: - fuel mass measurement and display. - fuel temperature measurement and display. - automatic control of aircraft refuelling. - system integrity monitoring using BITE. - ARINC 429 digital data for interface to other systems.

The Capacitance Index Compensator has a capacitance in proportion to the dielectric constant of the fuel. The Capacitance Index Compensator is the lower part of one of the lower probes in each wing Inner cell and center tank; and has a dual operation: measurement of the dielectric constant of the fuel when fully covered by fuel and a fuel probe when not fully covered by fuel.

FQI COMPUTER The Fuel Quantity Indicating computer performs the fuel mass calculations and controls the whole system by means of various interfaces. The Fuel Quantity Indicating (FQI) Computer has 2 identical channels for fuel mass calculation. Each channel calculates the tank quantities and monitors the other one; the most accurate being the operational one. If one channel fails the system operates normally, but CFDS report will indicate the failure.

CADENSICONS The cadensicons give a signal to the computer in proportion to the density and the dielectric constant of the fuel held in each tank. One cadensicon is installed on the floor of each tank and consists of 2 sensors; one measuring the density and the other one the dielectric constant of the fuel, both parameters being used for calculation of the fuel quantity.

TMUFUEB01-T01 LEVEL 3

UET4200

PROBES A set of capacitance probes in each tank gives a signal to the computer in proportion to the amount of probe covered by fuel. There are 5 probes in the center tank, 12 in each inner cell and 2 in each outer cell. 2 probes are located in the optional additional center tank. A single probe failure (except for probe 13 and 14) doesn’t affect the system indication.


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TMUFUEB01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

QUANTITY INDICATING EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM


UET4200

QUANTITY INDICATING FUEL LEVEL SENSING CONTROL UNITS (FLSCUs)

PRESELECTOR

This interface is mainly used: - To shut the related Refuel valve when the high level is reached in each tank - To initiate the BITE test of the high level sensors and their related circuits, by using the test switch on the refuel control panel. High level sensors in each tank, send a signal to the FQI computer, via the FLSCU. The test is initiated via the FQI computer and the FLSCU. Sensor and system status are sent from the FQI computer to the CFDS.

The preselector shows the preselected and actual total fuel quantities as monitored by the computer.

REFUEL CONTROL PANEL

ADIRUs

The Fuel Quantity Indicating computer provides automatic shut-off at a preselected refuel quantity with correct distribution of final load. When the MODE selector switch on the refuel/defuel control panel has been set to REFUEL, the FQI computer first makes sure that it is physically possible to take the preselected fuel quantity on the aircraft. Throughout the automatic refuel operation the FQI computer monitors the density of fuel in each tank and the distribution of the load.

Acceleration data is received from Air Data Inertial Reference System during flight and is used as an alternate source of attitude. The Air Data Inertial Reference Units (ADIRUs) send the acceleration/attitude informations. Normally, effects of attitude, changes in acceleration, effective pitch and roll angles are calculated from the height of fuel at each probe and the knowledge of the tank geometry stored in the computer memory.

MULTI-TANK INDICATOR (MTI)

CFDS

A multi-tank indicator displays the fuel quantity in each tank.

ARINC 429 output links transmit BITE information from the Computer to the Centralized Fault Display System. The Centralized Fault Display System (CFDS) monitors fault conditions and BITE.


L/G CONTROL LEVER The computer receives ground/flight information from the landing gear control lever. The FQI computer receives ground information from the landing gear, when selected DOWN with aircraft on jacks. This signal is used to provide electrical supply to the FQI computer in this specific configuration.

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28 FUEL SYSTEM

QUANTITY INDICATING FMGC Fuel parameters are sent to the Flight Management and Guidance Computers (FMGC) for navigation computations. ECAM


UET4200

Total and individual tank fuel mass information is sent to the ECAM display unit.


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28 FUEL SYSTEM

SELF EXAMINATION What happens if one channel of the FQIC fails? A - Half of the Quantity Indicating data is no longer available. B - FQIS operates normally, only CFDS report will indicate failure. C - Fuel warning is triggered in addition to CFDS report.

TMUFUEB01 LEVEL 3

UET4200

What happens if a quantity probe (other than 13 or 14) fails? A - Corresponding tank qty display flashes. B - Quantity indication disappears. C - Quantity indication remains the same.


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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-46-00 FUEL LEVEL SENSING

TMUFUEC01 LEVEL 3

UET4200

CONTENTS: General High Level Low Level Full level Underfull level Overflow Level Temperature Sensing Self Examination


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28 FUEL SYSTEM

FUEL LEVEL SENSING GENERAL The aircraft is equipped with two multi-channel Fuel Level Sensing Control Units (FLSCUs) and a third one, if the Additional Center Tank (ACT) is installed. They provide high fuel level sensing, low fuel level sensing, full fuel level sensing, underfull fuel level sensing, overflow level and temperature sensing. Fuel level and temperature sensors feed signals to the multi-channel amplifiers. The FLSCUs detect and amplify the signals and trigger switching functions in the appropriate circuits.

A separate low level sensor signals the IDG fuel return valve to close. Exposure of the optional ACT low level sensors causes the fuel forward transfer to stop. FULL LEVEL When the inner cell full level is reached, the center tank pumps are signalled to stop and the inner cell pumps then supply the engines until the fuel level reaches the underfull level. The full level sensors monitor the IDG fuel cooling recirculation.

HIGH LEVEL UNDERFULL LEVEL The high level sensors, when immersed in fuel, signal the associated tank refuel valve to shut when the MODE SELECT switch is set to REFUEL. Wet high level sensors cause the associated: - tank refuel valves to shut, - blue HI LVL lights to come on, on the refuel/defuel control panel (800 VU). Wet center tank high level sensor causes fuel transfer from optional ACT to center tank to stop.

TMUFUEC01-T01 LEVEL 3

UET4200

LOW LEVEL Exposure of the center tank low level sensors causes the center tank pumps to stop after a time delay. Exposure of the inner cell low level sensor to air results in immediate opening of the intercell transfer valves. Exposure of the inner cell low level sensor to air for 30 seconds causes LO LEVEL warning to appear on ECAM.


When fuel level in the wing tank inner cell drops to the underfull sensors, they signal the center tank pumps to restart, provided fuel is in center tank. There is approximately 1100 lbs (500 kg) difference between the full level and the underfull level. OVERFLOW LEVEL If the center tank pump fails to stop with inner cell full level reached, the fuel will overflow into the surge vent tank and the overflow sensor signals the return valve to close. TEMPERATURE SENSING To ensure that the fuel temperature at the engine inlet does not exceed the engine limits, the temperature sensors signal the closure of the return valve.

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TMUFUEC01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

SELF EXAMINATION What happens when a low level is detected in the inner cell? A - Automatically, transfer valves open to admit fuel to inner cell. B - Automatically, transfer valves close to isolate the inner cell. C - Restart of the pumps to suck fuel from the outer cell. What is A B C

the purpose of the IDG SHUT-OFF sensor? - To stop the center tank pumps. - To restart cooling fuel recirculation. - To stop the cooling fuel recirculation

In which cells are full level sensors fitted? A - Inner and outer cells. B - Inner cells only. C - Outer cells only.

TMUFUEC01 LEVEL 3

UET4200

What happens if a high level is detected? A - A warning is triggered: too much fuel. B - All the refuelling operations are stopped. C - The corresponding refuel valve closes.


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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-43-00 MANUAL MEASUREMENT

TMUFUEA01 LEVEL 1

UET4200

CONTENTS: Fuel Level Magnetic Indicator Location Fuel Level Magnetic Indicator Operation Attitude Monitor Fuel Quantity Tables


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28 FUEL SYSTEM

MANUAL MEASUREMENT FUEL LEVEL MAGNETIC INDICATOR LOCATION

TMUFUEA01-T01 LEVEL 1

UET4200

Without electrical power, the quantity indicating system is inoperative. In this case, the fuel Manual Magnetic Indicators must be used to monitor the quantity in the tanks. One Manual Magnetic Indicator (MMI) is installed in the center tank and five in each wing tank: 4 in each inner cell, 1 in each outer cell.


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TMUFUEA01-P01 LEVEL 1

UET4200


28 FUEL SYSTEM

MANUAL MEASUREMENT - FUEL LEVEL MAGNETIC INDICATOR LOCATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

MANUAL MEASUREMENT FUEL LEVEL MAGNETIC INDICATOR OPERATION


UET4200

Prior to using the Magnetic Manual Indicators, a reading is taken on the attitude monitor to determine the out-of-level attitude of the aircraft in the pitch and roll axes. To measure the FUEL QUANTITY, the magnetic level indicator has to be unlocked. To accomplish this, use a screwdriver to push the applicable MMI and turn it through 90deg. Hold and carefully lower the MMI fully. Then carefully lift the MMI until you fell the magnets. Read the units mark nearest to the bottom-skin of the wing and write down the number. Retract the MMI and use a screwdriver to turn it through 90 deg to lock it. Use the table for the applicable aircraft attitude and the applicable MMI stick number to find the volume of the fuel in each tank.


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UET4200


28 FUEL SYSTEM

MANUAL MEASUREMENT - FUEL LEVEL MAGNETIC INDICATOR OPERATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

MANUAL MEASUREMENT ATTITUDE MONITOR


UET4200

The attitude monitor is a circular level with a graduated surface. Each square of the grid is equal to 5 deg. of change of attitude. The position of the bubble in relation to the grid indicates the aircraft attitude.


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UET4200


28 FUEL SYSTEM

MANUAL MEASUREMENT - ATTITUDE MONITOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

MANUAL MEASUREMENT FUEL QUANTITY TABLES


UET4200

There is a specific table for each indicator on both wings. In this example, indicator number five on the right wing is used. The aircraft attitude, the fuel density and reading on the metering stick allow the fuel quantity in each tank to be read using the FUEL QUANTITY TABLES. Now suppose that the MMI is five, the mark is "8", if the bubble on the attitude monitor shows "4G", the result is 750 Liters.


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UET4200


28 FUEL SYSTEM

MANUAL MEASUREMENT - FUEL QUANTITY TABLES EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

TMUFUEA01 LEVEL 1

UET4200



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Page Page260 10 Jan 31/96


28 FUEL SYSTEM

28 - FUEL SYSTEM 28-42-00 FUEL QUANTITY INDICATING SYSTEM COMPONENTS

TMUFUEN01 LEVEL 3

UET4200

CONTENTS: Fuel Quantity Probe Cadensicon Sensor Fuel Quantity Preselector Multi-tank Indicator FQIC Memory Module Manual Magnetic Fuel Level Indicator Attitude Monitor


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Page 261 Page 1 May 31/96


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS FUEL QUANTITY PROBE IDENTIFICATION FIN: 21QT to 39QT LOCATION ZONE: 540, 640, 141, 142

TMUFUEN01-T01 LEVEL 3

UET4200

COMPONENT DESCRIPTION The fuel probes are installed to make sure that at least one probe is always cutting the useable fuel surface.


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TMUFUEN01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - FUEL QUANTITY PROBE EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS CADENSICON SENSOR IDENTIFICATION FIN: 19QT1, 19QT2, 20QT LOCATION ZONE: 540, 640, 141


UET4200

COMPONENT DESCRIPTION Each cadensicon houses 2 sensors covered by fuel. A fixed capacitor covered by fuel is the primary source for dielectric constant of the fuel in each tank and a densitometer float measures fuel density. Both parameters are used for calculations of the fuel quantity. As density of the fuel grade in use changes with temperature, a fuel thermistor makes an allowance for temperature variations.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - CADENSICON SENSOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS FUEL QUANTITY PRESELECTOR IDENTIFICATION FIN: 5QT LOCATION ZONE: 192


UET4200

COMPONENT DESCRIPTION Each LED display presents fuel quantity in kg x 1000. The PRESELECTOR has self contained BITE operations which are controlled by the FQI Computer, by data supplied through the Arinc 429 data bus link.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - FUEL QUANTITY PRESELECTOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS MULTI-TANK INDICATOR IDENTIFICATION FIN: 6QT LOCATION ZONE: 192


UET4200

COMPONENT DESCRIPTION Each LED display presents fuel quantity in kg x 1000. The display is justified to the right and the zero,in tens columns is never displayed. If the fuel mass is less than 1000 kg, the display will show a leading "0". If an Arinc 429 bus failure or an internal processing failure occurs, the MTI will blank all displays.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - MULTI-TANK INDICATOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS FQIC IDENTIFICATION FIN: 3QT LOCATION ZONE: 92VU


UET4200

COMPONENT DESCRIPTION The FQI computer is of the 3 MCU size and is connected to the aircraft electrical wiring through an Arinc 600 connector.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - FQIC EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS MEMORY MODULE IDENTIFICATION FIN: 7QT LOCATION ZONE: 92VU


UET4200

COMPONENT DESCRIPTION The connector plug is polarized to prevent damage caused by incorrect installation. The FQIC uses the OBRM (EPROM) to make sure that the hardware is compatible with the FQIS.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - MEMORY MODULE EFFECTIVITY EFFECTIVITY ALL

28-42-00



28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS MANUAL MAGNETIC FUEL LEVER INDICATOR IDENTIFICATION FIN: 104QM TO 113QM, 92QM LOCATION ZONE: 540, 640, 142 COMPONENT DESCRIPTION MMI OPERATION: - Press in the pushbutton and quarter turn in either direction to eject the rod. - Withdraw the rod lightly until magnetic attraction is felt. - Read fuel level on graduated rod at point coinciding with sight collar. - Using this reading, the fuel specific gravity and the a/c attitude, calculate the quantity of fuel in the tank using charts. - Replace the indicator rod by sliding it into the tube and lock by a quarter turn.


UET4200

CAUTION: YOU CAN EASILY CAUSE DAMAGE TO THE MAGNETIC LEVEL INDICATORS. DO NOT TOUCH OR PUSH AGAINST THEM WHEN YOU ARE IN THE FUEL TANK.


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - MANUAL MAGNETIC FUEL LEVEL INDICATOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS ATTITUDE MONITOR IDENTIFICATION FIN: 39QM LOCATION ZONE: 192

graduated to .5 deg bubble in attitude.


UET4200

COMPONENT DESCRIPTION ATTITUDE MONITOR is a circular level with surface. Each square of the grid is equal of change of attitude. The position of the relation to the grid indicates the aircraft


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UET4200


28 FUEL SYSTEM

FUEL QUANTITY INDICATING SYSTEM COMPONENTS - ATTITUDE MONITOR EFFECTIVITY EFFECTIVITY ALL

28-42-00



28 FUEL SYSTEM

TMUFUEN01 LEVEL 3

UET4200



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28 FUEL SYSTEM

28 - FUEL SYSTEM 28-46-00 FUEL LEVEL SENSING COMPONENTS

TMUFUEO01 LEVEL 3

UET4200

CONTENTS: High Level Sensor Low Level Sensor Full Level Sensor Underfull Level Sensor Overflow Sensor Wing Tank Temperature Sensor Fuel Level Sensing Control Unit IDG Shut-off Sensor


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28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS DESCRIPTION: All sensors are similar in construction. The level sensor contains a thermistor and a fast blow fuse. The temperature sensors contain a platinium wire resistor and a fast blow fuse.

TMUFUEO01-T01 LEVEL 3

UET4200

OPERATION: When the sensing thermistor is exposed to air, its temperature raises by the applied current. When it is immersed, the high thermal conductivity of the fuel in comparison with air, causes the thermistor temperature to fall.


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TMUFUEO01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS EFFECTIVITY EFFECTIVITY ALL

28-46-00



28 FUEL SYSTEM

HIGH LEVEL SENSOR

LOW LEVEL SENSOR

IDENTIFICATION FIN: 17QJ1, 17QJ2, 20QJ

IDENTIFICATION FIN: 15QJ1, 16QJ1, 15QJ2, 16QJ2, 21QJ, 22QJ

LOCATION ZONE: 540, 640, 141, 142

LOCATION ZONE: 540, 640, 141, 142

COMPONENT DESCRIPTION When immersed in fuel each High Level sensor signals its associated tank refuel valve to shut.

COMPONENT DESCRIPTION Depending on their installation the low level sensors control respectively center tank pumps or Outer cell Transfer valves operation and LO LEVEL ECAM warning.


UET4200

FUEL LEVEL SENSING COMPONENTS


28-46-00




UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS - HIGHT LEVEL SENSOR - LOW LEVEL SENSOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FULL LEVEL SENSOR

UNDERFULL LEVEL SENSOR

IDENTIFICATION FIN: 23QJ1, 23QJ2, 27QJ1, 27QJ2

IDENTIFICATION FIN: 24QJ1, 24QJ2, 25QJ1, 25QJ2, 26QJ1, 26QJ2

LOCATION ZONE: 540, 640


COMPONENT DESCRIPTION The full level sensors monitor the IDG fuel cooling operation.

COMPONENT DESCRIPTION The Underfull level sensors control Center tank pumps operation.


UET4200

FUEL LEVEL SENSING COMPONENTS


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UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS - FULL LEVEL SENSOR - UNDERFULL LEVEL SENSOR EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS OVERFLOW SENSOR

WING TK TEMPERATURE SENSOR

IDENTIFICATION FIN: 28QJ1, 28QJ2

IDENTIFICATION FIN: 29QJ1, 29QJ2, 30QJ1, 30QJ2



the

wing

tank

COMPONENT DESCRIPTION The temperature sensor is similar to the level sensor but has a platinium wire resistor in place of the thermistor. R = 1,000 ohms at 0 degree C.


UET4200

COMPONENT DESCRIPTION This sensor detects if fuel from overflows into the vent surge tank.


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UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS - OVERFLOW SENSOR - WING TK TEMPERATURE SENSOR EFFECTIVITY EFFECTIVITY ALL

28-46-00



28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS FUEL LEVEL SENSING CONTROL UNIT IDENTIFICATION FIN: 7QJ, 9QJ LOCATION ZONE: 121


UET4200

COMPONENT DESCRIPTION Each unit contains a channel for each level and temperature sensor. The BITE to check the sensor input and output circuitry is controlled and monitored by the FQIC.


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UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS - FUEL LEVEL SENSING CONTROL UNIT EFFECTIVITY EFFECTIVITY ALL

28-46-00



28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS IDG SHUT-OFF SENSOR IDENTIFICATION FIN: 38QJ1, 38QJ2 LOCATION ZONE: 540, 640


UET4200

COMPONENT DESCRIPTION At low fuel state the IDG cooling fuel recirculation is stopped when signalled by the IDG SHUT-OFF level sensor in the Inner cell, in order to avoid an increase in the amount of unusable fuel that would otherwise flow over the tank floor.


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UET4200


28 FUEL SYSTEM

FUEL LEVEL SENSING COMPONENTS - IDG SHUT-OFF SENSOR EFFECTIVITY EFFECTIVITY ALL

28-46-00



28 FUEL SYSTEM

TMUFUEO01 LEVEL 3

UET4200



28-46-00



28 FUEL SYSTEM

28 - FUEL SYSTEM 28-00-00 CFDS SPECIFIC PAGE PRESENTATION

TMUFUXM01 LEVEL 3

UET4200

CONTENTS: Fqis Status Flss Status Input Parameter Values


28-00-00



28 FUEL SYSTEM

CFDS SPECIFIC PAGE PRESENTATION The fuel system is a "type 1" system and is not available in CFDS ’backup" mode. FQIS STATUS The FQIS STATUS allows access to channel 1 (or 2) BITE memory, channel 1 has priority when both channels have the same health. A list is produced each time an FQIS LRU is detected as being currently failed or deemed failed or at the last FQI power-up test. All failure classes are reported. The operating grade for each channel is displayed and decoded as follows: - GRADE 1: normal operation, - GRADE 2: normal operation, - GRADE 3: normal operation with reduced accuracy, - GRADE 4: outside normal operation (display blanked) - GRADE 5: FQIC outputs.

- BITE

3 - Outer cell underfull sensors, remaining low level sensors, FWD intercell transfer valves, - BITE 4 - Inner cell full/underfull sensors, logic contol circuits, temperature sensors. Selection of NEXT PAGE gives the list of failed BITE 4 FLSS LRUs. EXAMPLE: BITE 4 has failed: - R underfull sensor and L wing temperature sensor have failed. NOTE: - the intercell transfer valves are reported under FQIS status. - FLSS status results are only kept on the channel that was the master at power-up.

TMUFUXM01-T01 LEVEL 3

UET4200

FLSS STATUS The FQI The and the

last FLSS power-up test result is recorded in the channel which was the master at that time. FLSS BITE is run automatically 30s after power-up consists of four separate procedures displayed on MCDU page: - BITE 1 - High level sensors, surge tank sensors, - BITE 2 - Read intercell transfer valves, some low level sensors,


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TMUFUXM01-P01 LEVEL 3

UET4200


28 FUEL SYSTEM

CFDS SPECIFIC PAGE PRESENTATION EFFECTIVITY EFFECTIVITY ALL

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28 FUEL SYSTEM

CFDS SPECIFIC PAGE PRESENTATION FQIS INPUT PARAMETER VALUES The following information is provided: - permitivity calculated from cadensicon, - density calculated from cadensicon, - permitivity calculated from CIC, - fuel temperature in Inner and outer cells, - effective pitch and roll attitudes. FQIS PROBE CAPACITANCE VALUES This page gives the values for all the capacitance devices in the tanks. FQIS DISCRETE INPUT VALUES This page gives the states for all discrete inputs to the FQIS. A "1" represents the active state.

TMUFUXM01-T02 LEVEL 3

UET4200

EXAMPLE: Bit position R3 is at "1" : means that the refuel door is open.


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UET4200


28 FUEL SYSTEM


28-00-00




UET4200


28 FUEL SYSTEM


28-00-00


a320 Training 28 Fuel System

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