A330_28_l3

A330/A340

Fuel

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING Lufthansa Technical Training

FUEL SYSTEM

A330/340−200/300 28

ATA 28

FUEL

Page 1

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A 28−00

28-00

FUEL SYSTEM

GENERAL LAYOUT General The fuel system stores fuel in five tanks. It supplies fuel to the engines and APU, and controls the center of gravity position. Fuel is stored in the main fuel tanks and in the trim tank. Most of the functions are controlled by the Fuel Control and Monitoring System ( FCMS ). Feed Concept The inner tanks are the main supply tanks. They receive fuel from the other tanks by transfers carried out and controlled by the FCMS. Management The FCMS manages the fuel system with 2 identical Fuel Control and Monitoring Computers FCMC 1 and FCMC 2. The different functions of the system are : S fuel level and temperature sensing S fuel gauging S center of gravity calculation S fuel management S indication and fault reporting S system monitoring and test

Page 2 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A 28−00

SURGE VENT TANK

SURGE VENT TANK

OPTIONAL REFUEL/DEFUEL

SURGE VENT TANK

Page 3

REFUEL/DEFUEL

Figure 1 Fuel Tanks and Feed Concept FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A340−200/300 28−00

28−00

FUEL SYSTEM

GENERAL LAYOUT General The fuel system stores fuel in five tanks. It supplies fuel to the engines and APU, and controls the center of gravity position. Fuel is stored in the main fuel tanks and in the trim tank. Most of the functions are controlled by the Fuel Control and Monitoring System (FCMS). FEED CONCEPT The inner tanks are the main supply tanks. They receive fuel from the other tanks by transfers carried out and controlled by the FCMS. MANAGEMENT The FCMS manages the fuel system with 2 identical Fuel Control and Monitoring Computers FCMC 1 and FCMC 2. The different functions of the system are : S Fuel level and temperature sensing S Fuel gauging S Center of gravity calculation S Fuel management S Indication and fault reporting S System monitoring and test

Page 4 FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A340−200/300 28−00

SURGE VENT TANK

SURGE VENT TANK

REFUEL/DEFUEL SURGE VENT TANK

REFUEL/DEFUEL

Page 5 Figure 2 Fuel Tanks and Fuel Management Concept FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00

TANK DESCRIPTION General Each tank is part of the structure. The fuel is stored in the wings and in the Trimmable Horizontal Stabilizer. Total Useable Fuel: 25670 US Gallons 97170 Liters 76.3 Tonnes The unusable fuel in the tanks and the system is less than 0.23% of the tank capacity. Inner Tanks The main tanks, the inners, are divided into 2 parts, the forward inner and the aft inner tanks. Each inner tank contains one collector cell. The collector cell is maintained full of fuel by means of jet pumps for the booster pump operation. Inner Tank Volume: 11070 US Gallons 41904 Liters 32895 kg Each collector cell quantity is 1140 kg. Outer Tanks The outer tanks maintains fuel outboard to provide bending relief. This fuel is transfered to the inner tank when a predetermined level is reached in this tank.

Trim Tank Volume 1615 US Gallons 6114 Liters 4800 kg Center Tank (A330−200 Only) The Center tank is located in the wing center section. Its fuel is normally transferred to the Inner tanks. Center Tank Volume: 10 955 US Gallons 41 468 Liters 32 550 Kg Surge Tanks The surge vent tanks vent the fuel tanks to atmosphere and collects fuel spilled from the tanks. There is a surge vent tank outboard of the outer tank on each wing, and on theright side of the trim tank. They are used for venting. Trim Surge Tank Volume 115 Liters Surge Tank Volume 900 Liters

Outer Tank Volume: 957 US Gallons 3624 Liters 2845 kg Trim Tank The trim tank provides additional fuel capacity. Fuel trim transfers enable the aircraft center of gravity to reach the optimum position so that drag is reduced and fuel economy is improved.

Page 6 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 7 Figure 3 Fuel Tanks FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

DISTRIBUTION DESCRIPTION The fuel distribution consists of : S Engine and APU Feed System S Refuel / Defuel System S Main Transfer System S Trim Transfer System

Page 8 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 9 Figure 4 Fuel System Basic Schematic A330−300 FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00

A330−200 DISTRIBUTION SCHEMATIC

Page 10 FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 11 Figure 5 Fuel System Basic Schematic A330−200 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

CONTROLS A330−300 Crossfeed Valve Pushbutton The pushbutton for the crossfeed valve is normally released out with no light on and the valve is closed. The valve opens when pushed in to connect the two wing sides together. The white ON light comes on and the green OPEN light indicates that the valve is open. Main / Standby Pumps Pushbutton There are 6 wing booster pump pushbuttons: S 4 main pumps S 2 standby pumps With all pushbuttons pressed in and no lights on, the main pumps run. A stand-by pump starts if a related pump is in low press condition. When the pressure drops, the amber FAULT light comes on. With the pump pushbutton selected OFF, the warning is inhibited. Fwd Manual Transfer Pushbutton The trim tank mode pushbutton allows a manual forward transfer to be initiated if a faiulre occurs in the auto center gravity control. If the FAULT light comes on, due to an excess AFT center of gravity or an inop auto transfer, the pushbutton must be pressed in. The FWD light comes on. If there is a trim transfer pump installed (A/C EFF.), the pump starts to run (if not already on).

Outer Tank Transfer Pushbutton The FAULT light comes on in the outer tank transfer bushbutton, in case of malfunction in the computed fuel transfers from the outer tanks to the inner tanks. In case of failure in the AUTO transfer the S OUTR TK XFR p/b must be pressed S MAN light comes on transfer is initiated overriding the auto mode. Emergency Isolation Valve The two inner tank SPLIT pushbuttons allow each section of the inner tank to be isolated. Each white ON light comes on when corresponding pushbutton is pressed, the green SHUT light comes on when the valve is closed. Reset Switches A reset switch is provided for each FCMC to reset the related computer.

Trim Tank Selector The 3 position selector is guarded in auto normal position and thus the transfer line is maintained full when the trim tank is empty. S ISOL : the transfer line is isolated by closing all the required valves S OPEN : the valves used for forward transfer are maintained open, even if low level is detected, to allow the pipe to drain.

Page 12 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 13 Figure 6 Cockpit Fuel Panel A330−300 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

A330−200 Center Tank Pumps Pushbutton The Center Tank Transfer Pumps are operated ON or OFF by a left and right pushbutton. They are normally pressed IN, with no light. Center pump operation is enabled by the pushbutton but is controlled by the Computer. The FAULT light comes on amber when the pump pressure drops. It is inhibited when OFF is selected. Center Tank Transfer Pushbutton The Center Tank Transfer pushbutton overrides automatic transfer from Center Tank to Inner Tank. When a failure occurs the FAULT light comes on amber. When the pushbutton is pressed IN, MAN comes on, transfer starts. Note that the Center Tank Transfer Pumps have to be stopped manually. Optional Jettison System On the A330−200 the Jettison System is optional Equipment.

Page 14 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 15 Figure 7 Cockpit Fuel Panel A330−200 FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00

ECAM FUEL PAGE INDICATION A330−300 General The following grafics show all fuel system information which are presented on the ECAM fuel page.

Page 16 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

FUEL USED

ENGINE FUEL USED

ENGINE LP SHUTOFF VALVE

MAIN FUEL PUMPS CROSSFEED VALVE STBY FUEL PUMP

OUTER TANK QUANTITY

COLLECTOR CELL QUANTITY INNER TANK QUANTITY

INNER TANK TEMPERATURE

OUTER TANK TEMPERATURE

TRIM TANK ISOLATION VALVE

TRIM TANK TEMPERATURE

APU PUMP

A/C GROSS WEIGHT

A/C CENTER OF GRAVITY

FUEL ON BORD

TRIM TANK QUANTITY

Page 17 Figure 8 ECAM Fuel Page FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

LOWER ECAM DISPLAY

INDICATION

No1 LP VALVE

INDICATION

CROSSFEED VALVE

COLOR

COLOR

GREEN

VALVE OPEN

AMBER

VALVE CLOSED

No2 LP VALVE

VALVE OPERATION AMBER

XX

VALVE OPERATION

GREEN

VALVE CLOSED

GREEN

VALVE OPEN

AMBER

VALVE IN OPERATION

AMBER

VALVE CLOSED BUT SHOULD BE OPEN

AMBER

VALVE OPEN BUT SHOULD BE CLOSED

AMBER

DATA NOT AVAILABLE

AMBER

XX

AMBER

VALVE OPEN BUT SHOULD BE CLOSED

VALVE CLOSED BUT SHOULD BE OPEN

DATA NOT AVAILABLE

Page 18 Figure 9 ECAM LP Fuel VLV and Crossfeed VLV FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00

MAIN−PUMP

FUEL

KG F.USED 2950

1

1490

1140

2840 5

o

c

INDICATION

2 1460

1140

32000

32000

2840 5 oc

5

STANDBY−PUMP

INDICATION

FOB: 74480KG 4800 5 c o

INDICATION

COLOR

FUEL−PUMP INDICATION

GREEN

FUEL−PUMP IN STANDBY−MODE

GREEN

IN OPERATION

FUEL−PUMP

FUEL−PUMP AMBER

SET TO ON − BUT NOT IN OPERATION

LO

AMBER

FUEL−PUMP LOW PRESSURE

XX

AMBER

DATA AVAILABLE

NO FUEL−PUMP

Page 19 Figure 10 ECAM Pumps and Quantity FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM GENERAL

A330 28−00

FUEL

KG F.USED 2950

1

1490

1140

2840 INTERTANK TRANSFER VALVE

5

FUEL

2 1460

1140

32000

1

1460

2840

32000

5 c

c5

TRANSFER TO

INTERTANK

1140

2840

LH INNER TANK

TRANSFER VALVE

5

KG F.USED 2950

2 1460

1140

32000

32000

2840

5 c

c 5

TRANSFER TO

TRANSFER TO

TRIM TANK

TRIM TANK

FOB: 74480KG 4800 −5 c

FROM

FROM

MAN XFR

TRANSFER TO

RH INNER TANK

LH INNER TANK MANUAL TRANSFER

FOB: 74480KG

RH INNER TANK

4800 −5 c

MAN XFR MANUAL TRANSFER

TRIM TANK ISOLATION INDICATION

COLOR

VALVE OPERATION

VALVE

INDICATION COLOR NIL

NIL

GREEN

VALVE OPEN− AUTOMATIC OPERATION

GREEN

VALVE OPEN− MANUAL TRANSFER

AMBER

VALVE OPEN−BUT SHOULD BE CLOSED

AMBER

INDICATION COLOR

VALVE OPERATION

VALVE CLOSED

XX XX

TRIM TANK ISOLATION VALVE

NIL

VALVE CLOSED

VALVE CLOSED

GREEN

VALVE OPEN− AUTOMATIC OPERATION

AMBER

VALVE CAUGHT OPEN

GREEN

VALVE OPEN− MANUAL TRANSFER

AMBER

VALVE CAUGHT CLOSED

AMBER

VALVE OPEN−BUT SHOULD BE CLOSED

GREEN

VALVE OPEN

GREEN

AMBER

DATA NOT AVAILABLE

NO VALVE

NIL

XX

AMBER

NO VALVE

POSITION DATA

POSITION DATA NOTE: FOR INFORMATION PURPOSES ALL THE (AUTOMATIC) TRIM TRANSFER SYSTEM

SYMBOLS ARE SHOWN ON THE DISPLAY. IT IS NOT POSSIBLE FOR CERTAIN SYMBOLS TO SHOW TOGETHER.

Page 20 Figure 11 ECAM Transfers FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 21 Figure 12 ECAM TT and APU Indication FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 22 Figure 13 ECAM Quantity and Temperatures FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM GENERAL

A330 28−00

Page 23 Figure 14 ECAM CG and Gross Weight FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

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FUEL SYSTEM FCMC

A330/A340−200/300 28−51

28−51

FCMC

SYSTEM DESCRIPTION All functions are controlled by the Fuel Control and Monitoring System (FCMS). Management The Fuel Control and Monitoring System (FCMS) manages the fuel system with 2 identical Fuel Control and Monitoring Computers : S FCMC 1 and FCMC 2. The different functions of the system are : S Fuel quantity measurement, S Main transfers, S Trim transfers and Center of Gravity positioning, S Fuel recirculation and temperature data, S Refuel/Defuel control, S Jettison, S Indication and Warning.

Page 24 FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM FCMC

A330/A340−200/300 28−51

A340 only

Page 25 Figure 15 FCMC FRA US/T-2 SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM FCMC

A330/A340-200/300 28−51

SYSTEM OPERATION General The Fuel Control and Monitoring System (FCMS) controls most of the automatic functions of the fuel system. The primary components of the FCMS are the two Fuel Control and Monitoring Computers, FCMC1 and FCMC2. Only one FCMC controls the fuel system at one time. It is usually FCMC1 unless conditions occur to cause FCMC2 to control the system. The FCMCs suppty the interface etectronics for and receive input data from these fuet system components: S fuel quantity probes S fuel temperature sensors S fuel densitometers S fuel level sensors. When the FCMCs receive this input data they continuously and independently calculate how the fuel is divided in the aircraft. The appropriate decisions about the necessary movement of the fuel can then be made. Each FCMC also receives and transmits ARINC 429 data but only one FCMC (the FCMC that is in control of the system) sends discrete (command) signals to the applicable fuel system components. The FCMCs have internal monitors which continuously give each computer its serviceability condition. The data from these monitors is continuously compared and lets the FCMCs make a decision about which computer has the best condition. That FCMC then controls the system. Each FCMC has hardware and software that give the FCMC Built−In Test Equipment (BITE). The BITE continuously monitors the FCMC and fuel sy stem components for failures and operates a BITE (self) test.

Function FCMC FUNCTIONS The FCMS can: S calculate the fuel quantity S calculate the fuel temperature S calculate the centre of gravity (CG) of the aircraft (together with the Flight Management, Guidance and Envelope Computers (FMGECs) S control the aircraft CG through the trim−transfer system S control the main transfer system S control an automatic refuel operation S stop a manual refuel or defuel operation if the fuel configuration is not safe S receive fult level signals from the fuel levet sensors and make the necessary decisions S give the fuel system data to other aircraft systems S monitor the fuel system and report the fuel system failures to the Central Maintenance Computers S control the Water Scavenge System

Page 26 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM FCMC

A330/A340-200/300 28−51

DISCRETE LEVEL SENSING

28VDC RIGHT OUTER

FUEL SYSTEM

RELAYS

TANK RIGHT INNER TANK

A340 ONLY

CMC−2

28VDC

COLLECTOR CELLS

3 AND 4

FCMC−2

CMC−1/2 FCDC−2 ADIRU−2 FMGEC−2

TRIM TANK RIGHT

FMGEC−1 FMGEC−2 FWC−1 FWC−2 DMC−1 DMC−2 DMC−3

ACT 1 DISCRETES L/GEAR SLATS

PUMPS

VALVES SOLENOIDS

CENTER

OVERHEAD

PANEL

REFUEL PANEL

ECAM

TANK

DMU

TRIM TANK CENTRE

TRIM TANK LEFT

CMC−1/2 FCDC−1 ADIRU−1 FMGEC−1

COLLECTOR CELLS

FCMC−1

28VDC CMC−1

1 AND 2

LEFT INNER TANK 28VDC

DISCRETE LEVEL SENSING

FUEL SYSTEM

RELAYS

LEFT OUTER

Page 27

TANK

Figure 16 FCMS Schematic FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM FCMC

A330/A340-200/300 28−51

Description Only one FCMC controls the system at a time. If the FCMC that is in control (usually No 1) is found to be in an unserviceable condition (or gives unsatisfactory data), the other FCMC gets control. This is a changeover procedure. System Functions Fuel Quantity and FuelTemperature Measurement Each FCMC sends condition signals and gives the interface electronics for: S approximately half of the fuel quantity probes S approximately half of the fuel temperature probes S one densitometer. The data from the quantity and temperature probes is put through signal conditioning circuits to cause an ARINC output. This output is sent to the command and monitor CPUs of each FCMC. Thus, there is no deterioration of fuel quantity data if a CPU failure occurs because each FCMC receives all of the probe data. The output from each densitometer gives accurate fuel density data to the CPU through its conditioning circuit. One densitometer supplies data to one FCMC. There is no direct connection from one densitometer to the opposite FCMC. The fuel probe data, the densitometer data and the fuel tank geometry figures (which are kept in the computer software) are used to calculate the fuel quantity and give: S the fuel quantity in each tank S the total fuel quantity in the aircraft. Each temperature probe has two sensors. Although the two outputs (one from each sensor) are connected to one FCMC, the internal configuration of the FCMC makes sure that each sensor output connects to separate signal conditioners. Thus the FCMCs each receive data from every probe. The fuel temperature data is used to give fuel temperature warnings and cautions.

Changeover Logic The FCMCs have connections between them to send serviceability data to each other. This is done through eight discrete lines and the ARINC Bus D. This function helps the FCMCs to make a decision as to which FCMC has control of the fuel system. The discrete lines give data on: S the fuel quantity measurement function S the fuel transfer (or management) function. Internal monitors continuously look at the function conditions and decide if they are healthy, failed or a condition between healthy and failed. These conditions are put to the eight changeover discrete lines in a logic series of 0 to 7 which gives a status message. Each FCMC also sends and receives condition data through the ARINC Bus D. This data uses a truth−table to make a decision as to which FCMC is the master and which FCMC is the slave (the computer status). A changeover occurs if a change in status is necessary. This will cause the discrete outputs of the previous master to be set to off and (if it is corrupted) the ARINC outputs to be flagged to off (to the receiver).

Page 28 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM FCMC

A330/A340-200/300 28−51

CHANGE OVER

CHANGE

OVER

ARINC

ARINC

D

D

TRANS− MITTER

TRANS− MITTER

CPU COM

CPU COM

CHANGE OVER

CHANGE OVER

MONITOR

MONITOR

CPU

MONITOR

INHIBIT

INHIBIT

TO

TO

MONITOR GATES

MONITOR GATES

CPU MON

Page 29

5QM1 FCMC−1

Figure 17 Changeover FCMC1 - 2 FRA US/T-2 SHM 13.12.2007

CPU

MONITOR

CPU MON 5QM2 FCMC−2

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

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FUEL SYSTEM TANKS

A330/A340−200/300 28−11

28−11

TANKS

TANK DESCRIPTION Wing Tank The wing fuel tanks and the surge tanks are located between the front and rear spars of the wing box and the wing top and bottom skin. Ribs 1 to 39 divide the wing into many compartments. The wing box is divided into different tanks by sealed ribs 1, 23, 33 and 39. Inner Tank The inner tank is located between rib 1 and 23. It is divided into two sections. The center spar between ribs 3 and 9 is sealed. Rib 9 is sealed between the front spar and the center spar, but vent holes are left at the top. Rib 3 is sealed between the center spar and the rear spar.

Trim Tank The trim tank is located in the THS main box structure between ribs 19 left hand and 18 right hand. The surge vent tank is located on the right side between ribs 18 and 20. The 4 clack valves on both ribs 3 keep the fuel in thecenter box structure. Access to the trim tank is gained through bolted panels in the front spar and small access panels in the bottom skin.

Clack Valves Three clack valves are positioned near the bottom of the center spar between ribs 2 and 3 to let the fuel flow into the collector cell. Three other clack valves are fitted at the bottom of rib 4, to direct the fuel towards the standby pump. Outer / Surge The outer tank is located between rib 23 and 33. The surge vent tank is located between rib 33 and 39. Access Access to the wing tanks is gained through many bolted man hole panels in the wing bottom skin. Inboard of rib 11 some compartments are accessible through the adjacent manhole. Emergency Isolation Valve The forward and aft sections of the inner tankl are connected together by a pipe and normally open isolation valve.

Page 30 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340−200/300 28−11

Page 31 Figure 18 Tank Structure FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11

TANK VENTING LAYOUT General The Tank Venting System is divided into two systems. The two systems are : S the Wing Tanks Venting system (which includes the Center Tank Venting from the left Wing Tank System). S the Trim Tank Venting system Wings Ventilation The Center Tank pipe and the Inner Tank pipes are the biggest vent pipes. The Outer Tank Vent pipe connects the open end fitting, inboard of rib 33, to the Inner pipe between the weir duct and rib 22. The weir duct is installed in the Inner Tank Vent pipe between rib 22 and 23 and serves for anti−syphon purposes. The Surge Vent Tank has the smallest drain pipe section. Breather Assembly Several Breather Assemblies are installed on the bottom of the vent pipes. They serve as drain valves, and let ingoeing fuel drain back to the inner tank. Vent Float Valves There are two Vent Float Valves for the Inner Tank and one for the Outer Tank.

Overpressure Protectors These are burst discs installed in the Center Tank and the Vent Surge Tanks. They prevent too high differential pressure. If they break, the Center one causes fuel to flow into the right Inner Tank, the Vent one causes fuel to flow overboard. Flame Arrestor The stack pipe connected to the NACA duct is equipped with a Flame Arrestor. If a ground fire occurs, it prevents the ignition of the fuel vapour in the Surge Tank (and thus the Tank Venting system). It also lets air flow freely through it in two directions. The NACA shape prevents ice formation. If a failure occurs in the fuel system (which causes larger quantities of fuel to enter the Surge Tank) then the Flame Arrestor lets the fuel flow freely overboard. Wing Fence If fuel comes out of the NACA Intake (or the Overpressure Protector), it could go inboard along the lower surface of the wing. A Wing Fence makes sure that such fuel falls off the wing.

Operation During flight, fuel from Inner Tank can collect in the Surge Vent Tank before flowing overboard. If there is fuel in the Surge Tank, gravity or pressurization from the NACA air intake causes fuel to move through its drain pipe to the Inner Vent pipes. From there it flows through the Breather Assemblies into the Inner Tank.

Page 32 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11

Page 33 Figure 19 Tank Venting FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11

VENTILATION FUNCTION Overpressure Protector The primary components of the overpressure protector are: S a body S a carbon disk (burst disk) S a collecting grid with a retaining ring If a difference between ambient and internal pressure occurs the burst disk breaks. The collecting grid does not let the pieces go into the surge tank. The burst disk has a white cross painted on it to check if it is correct and not damaged.

Page 34 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11

OVERPRESSURE PROTECTOR

GRID

INNER TANK VENT PIPE SURGE TANK DRAIN PIPE CENTER TANK VENT PIPE

BODY

CARBON DISC

OVERPRESSURE PROTECTOR

NACA VENT/ FLAME ARRESTOR

PAINTED CROSS ON DISC

Page 35 Figure 20 Surge Tank Components FRA US/T-2 SHM 13.12.2007

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A330/A340-200/300 28−11

Flame Arrestor The flame arrestor in the left and right wing are the same. The flame arrestor in the trim tank is almost the same, but it is smaller. The vent protector has a body with a number of cartridges and spacers installed in it. The body is a cylinder with a clip for attachement to the NACA vent at one end. At the other end is a end fitting. The spacers hold the cartridges apart from one another and keep the assy rigid. The vent protector lets air or fuel freely flow through it. Fuel Vent Valve The fuel vent valve has S a body S a float assembly S an external poppet valve The float assembly usually hangs down which keeps the poppet valve open. When the fuel level increases to a certain level it lifts the float assembly and thus closes the valve. Breather Assembly Several Breather Assemblies are installed on the bottom of the vent pipes. They serve as drain valves, and let ingoeing fuel drain back to the inner tank. NOTE:

The components used in the Trim Surge Tank are nearly the same than those installed in the Wing Surge Tanks.

Page 36 FRA US/T-2 SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11 FLAME ARRESTOR BREATHER ASSEMBLY ICE PROTECTOR

FLAME ARRESTOR

VENT VALVES

WEIR DUCT

RUBBER NOZZLE

CARTRIDGES

SPACERS WING TANK INNER TANK VENT VALVE CARTRIDGES

OUTER TANK VENT VALVE SPACERS TRIM TANK

Page 37 Figure 21 Wing/Trim Tank Ventilation Components FRA US/T-2 SHM 13.12.2007

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A330/A340-200/300 28−11

Center Tank (A340 And A330−200 Only) There are two standpipes which are above and connected to the center tank. The standpipes let the center tank be filled to its maximum capacity. Above the center tank are the two standpipes. These are located between: S the frame 40.3 and frame 47 S each side of the aircraft centerline and the first stringer S the center wing top skin and the cabin floor (but below the pressure hull) Center Tank Overpressure Protector (A340 and A330−200 Only) The center tank overpressure protectors are installed on the LH (RH) pipe in the center tank. The pipes are attached to the inner face of the LH (RH) STA0/RIB1. The overpressure protector makes sure that the pressure in the center tank is not more than the design limits. If the pressure in the center tank increases to a specified value the overpressure protector breaks open to release the pressure (into the LH (RH) inner tanks).

Center Tank Expansion Tanks (A340 and A330−200 Only) There are two expansion tanks which are above and connected to the center tank. The expansion tanks let the center tank be filled to its maximum capacity. Above the center tank are the two expansion tanks. These are located between: S the frame 40.3 and frame 47 S each side of the aircraft centerline and the first stringer S the center wing top skin and the cabin floor (but below the pressure hull) NOTE:

On earlier generation A340 aircraft there are no expansion tanks installed!

Center Tank Overpressure Protector (A340 and A330−200 only) The center tank overpressure protectors are installed on the LH (RH) pipe in the center tank. The pipes are attached to the inner face of the LH (RH) STA0/RIB1. The overpressure protector makes sure that the pressure in the center tank is not more than the design limits. If the pressure in the center tank increases to a specified value the overpressure protector breaks open to release the pressure (into the LH (RH) inner tanks) NOTE:

On earlier generation A340 aircraft there is only one overpressure protector installed which drains fuel to the right inner tank!

Page 38 FRA US/T-2 SHM 13.12.2007

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A330/A340-200/300 28−11

FUEL INLET TO EXPANSION TANK FR 40

ÍÍÍÍÍÍÍÍÍÍÍÍ ÍÍÍÍÍÍÍÍÍÍÍÍ ÍÍÍÍÍÍÍÍÍÍÍÍ ÍÍÍÍÍÍÍÍÍÍÍÍ ÍÍÍÍÍÍÍÍÍÍÍÍ ÍÍÍÍÍÍÍÍÍÍÍÍ EXPANSION

DOUBLE SKIN

TANK

VALVE

CENTER TANK AND EXPANSION

FUEL INLET TO EXPANSION TANK

TANKS VENT AIRCRAFT CENTERLINE

FR 47

TO WING VENT TO WING VENT

DRAIN

CENTER

EXPANSION

TO DRAIN

TANKS

MAST

TANK CENTER TANK

INNER TANK

FUSE COLLECTING FUEL FLOW

ASSEMBLY

GRID

TO INNER TANKS CARBON DISK

BODY

Page 39 Figure 22 Center Tank Vent Components FRA US/T-2 SHM 13.12.2007

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A330−300 28−11

CENTER TANK BOX VENTING/DRAINING A330−300 General The center box venting and drainage system prevents the collection of fuel vapour in the center box area if minor fuel leaks occur. The system consists of: S an air supply pipe S a check valve S a vent duct S a drain line with drain mast S a leak monitor Ventilation System The aire supply pipe is installed on the center box front spar. It supplies pressurized air from the air conditioning system to the center box. The check valve installed in the air supply pipe does not let fuel vapour go into the air conditioning system. The vent duct is installed in the center of the center box. The bottom of the duct is connected to a flexible hose. This hose connects the vent duct to an air vent below the belly. The vent duct causes a continuous ventilation through the center box. Draining System Two drains at the rear of the center box connect the center box to the drain line and the drain mast. The drains also causes a continuous flow of air through the center box. If a fuel leak occurs into the center box fuel will go through the drain line and the drain mast to atmosphere. The drain line has a leak monitor. The monitor keeps a small quantity of fuel for leak analysis. Maintenance personell use the leak monitor to do a check for unwanted fuel insude the center box. NOTE: The leak monitor is of the same type as the water drain valves on the wing tanks.

Page 40 FRA US/T-2 SHM 13.12.2007

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A330−300 28−11

LEAK MONITOR

BOTTOM SKIN R/H INNER TANK DRAINMAST CENTER BOX

DRAIN LINE

DRAIN

VENT DUCT LEAK MONITOR DRAIN TOOL CHECK VALVE

L/H INNER TANK

AIR SUPPLY PIPE DRAIN

Page 41 Figure 23 Center Box Venting and Draining (A330−300) FRA US/T-2 SHM 13.12.2007

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WING TANK WATER DRAIN DESCRIPTION General Each tank has one or more water drain valves. They are used to: S drain the water which could possibly come out of the fuel in the tanks S drain all the remaining fuel out of the tank (for maintenance)

Page 42 FRA US/T-2 SHM 13.12.2007

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A330/A340-200/300 28−11

REMOTE INLET INNER TANK WATER DRAINS

WING TANK WATER DRAIN

INNER CHECK VALVE

OUTER VALVE

EMERGENCY ISOLATION VALVE

OUTER TANK WATER DRAIN

ACCESS PANEL WATER DRAIN WITH REMOTE INLET

O-RING

SURGE TANK WATER DRAIN

OUTER VALVE

Page 43 Figure 24 Wing Tank Water Drain FRA US/T-2 SHM 13.12.2007

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TRIM TANK WATER DRAIN DESCRIPTION General The trim tank is equipped with 3 water drain valves S one indirect drain valve S two direct drain valves The direct drain valve has holes to drain fuel from the area of the tank adjacent to the valve. The indirect water drain body has an inlet connection in the side. This connects to a pipe that drains fuel from the area of the tank which is a short distance from the drain valve.

Page 44 FRA US/T-2 SHM 13.12.2007

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A330/A340-200/300 28−11

DRAIN VALVE SURGE TANK

DRAIN VALVE R/H SIDE FLAP TYPE CHECK VALVES

INDIRECT DRAIN

DRAIN VALVE L/H SIDE

DIRECT DRAIN

Page 45 Figure 25 Trim Tank Water Drain FRA US/T-2 SHM 13.12.2007

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TRIM PIPE SHROUD DRAIN DESCRIPTION General The trim fuel pipe has an outer shroud. If the trim transfer pipe shows fuel leackage the shroud contains the fuel amount. The shroud has a fluid drain at its lowest point. This drain is a small diameter pipe which connects the shroud to a drain mast.

Page 46 FRA US/T SHM 13.12.2007

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FUEL SYSTEM TANKS

A330/A340-200/300 28−11

DRAIN MAST

DRAINMAST

TRIM PIPE DRAIN PIPE

TRIM PIPE DRAIN

FR 53

FR 47

Page 47 Figure 26 Trim Pipe Shroud Drain FRA US/T SHM 13.12.2007

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Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

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FUEL SYSTEM APU FEED SYSTEM

A330 28−22

28−22

APU FEED SYSTEM

SYSTEM DESCRIPTION General The APU fuel pump system supplies the necessary fuel to operate the APU in all operation conditions. The system has two fuel feed pumps: S one pump is installed in the wing center section. It supplies the trim tank fuel transfer line and the APU line with fuel when the transfer system does not operate. S a second pump is installed in the tail cone section. It supplies fuel from the trim tank transfer line to the APU fuel system when the trim transfer system operates. The pump control is automatic and depends on the operating conditions. The trim tank transfer line and the APU fuel lines transfer the fuel from the left hand inner wing tank to the APU fuel system. If a fire and overheat detection occurs in the APU compartment the aft fuel feed pump is de-energized. Description When given conditions occur the forward fuel feed pump supplies the necessary fuel from the L/H inner tank to the APU fuel system through: S the forward APU fuel line S the trim tank transfer line S the fuel / air seperator S the aft APU fuel line In some conditiones the aft fuel feed pump supplies the fuel from the trim tank fuel transfer line to the APU fuel system through the fuel / air seperator and the aft fuel line installed in the stabilizer compartment.

Page 48 FRA US/T SHM 13.12.2007

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FUEL SYSTEM APU FEED SYSTEM

A330 28−22

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

L STBY

R STBY

LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 49 Figure 27 APU Fuel Feed Schematic A330−200 FRA US/T SHM 13.12.2007

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FUEL SYSTEM APU FEED SYSTEM

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APU FUEL FEED COMPONENT LOCATION FWD Apu Pump The FWD fuel feed−pump is a centrifugal pump with a single−phase 115VAC motor which moves the pump impeller. The pump can supply 360 l per hour at a pressure rise of 17 PSI. The maximum anbient operation temperatures of the pump are between − 55° C and +70° C.

FWD Apu Pump Inoperative If the FWD pump delivery pressure is insufficient the transfer line pressure switch sends a signal to the FCMCs to control the AFT pump to operate. The failure is memorized in the FCMCs.

The pump has thermo fuses installed which prevent an overtemperature. When the temperature reaches 175° C the fuses stop the powersupply to the pump. The pump supplies also fuel to the crossfeed line when all main fuel pumps are lost in flight. AFT Apu Pump The AFT fuel feed−pump is a vane type pump with a single−phase 115VAC motor which moves the pump vanes. The pump is self priming with sufficient capacity to cope with released air. The maximum ambient operation temperatures of the pump are between −55° C and +70° C Fuel Transfer Line Pressure Switch The fuel pressure switch is installed behind the fuel air separator. The switch closes when the pressure drops below 22 PSI and transmitt a signal to the FCMC to close a relay which energizes then the aft APU pump. Fuel Air Seperator The fuel air separator is installed in the stabilizer compartment inbetween the transfer line. It keeps enough fuel for APU operation if air appears in the fuel transfer line. Seperator Drain Valve The drain valve is installed at the fuel air separator behind the access door 311AL on the outer fuselage. The valve is used by the maintenance to drain off the water inside of the container.

Page 50 FRA US/T SHM 13.12.2007

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CENTER BOX REAR SPAR CENTER WING BOX STABILIZER COMPARTMENT TRANSFER LINE PRESS SWITCH

TO TRIM TANK

APU ISOLATION VALVE

FUEL/AIR SEPERATOR

APU FEED LINE ( SHROUDED )

FWD PUMP CANISTER

CENTER BOX FWD APU

REAR SPAR

PUMP

FUEL TRANSFER LINE ( SHROUDED )

FROM CENTER WING BOX

SEPERATOR LP FUEL SHUTOFF VALVE

AFT APU

DRAIN VALVE

PUMP

Page 51 Figure 28 APU Fuel Feed Components FRA US/T SHM 13.12.2007

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APU FUEL PURGING FUNCTION APU Fuel Line Vent Pushbutton The switch is installed in the APU compartment at the front firewall. It is used for maintenance to prime the APU fuel supply line. Vent And Drain Valve The drain valve is installed in the APU compartment on the APU fuel supply line next to the APU Fuel Control Unit. The valve is used to drain the APU fuel supply line before entering the APU Fuel Control Unit. Priming Of The Apu System When the APU FUEL LINE VENT is pressed it energizes the control relay. The relay: S opens the LP fuel shutoff valve S opens the fuel isolation valve S the 120 sec time delay avoids to energize the forward fuel feed pump S the fuel pressure switch detects low pressure and starts the aft APU pump S after 120 sec the relay closes and energizes the forward APU feed pump S the fuel pressure switch does not detect a low pressure anymore and stops the aft fuel feed pump

Page 52 FRA US/T SHM 13.12.2007

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FUEL SYSTEM APU FEED SYSTEM

A330/A340-200/300 28−22

LEFT INNER

X-FEED LINE

CENTER SECTION

TRIM PIPE ISOLATION VALVE FWD APU PUMP

APU ISOLATION VALVE

AUXILIARY FORWARD TRANSFER VALVE

APU L/P SHUTOFFVALVE

APU DRAIN VALVE

FUEL AIR SEPARATOR

FUEL SUPPLY LINE PRESSURE SWITCH AFT FUEL PUMP

FUEL VENT PUSHBUTTON ISOLATION VALVE TRIM TANK INLET VALVE

SHROUD VENT

Page 53 Figure 29 APU Purging Components FRA US/T SHM 13.12.2007

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TRIM TRANSFER LINE DAMAGE OPERATION General The Trim Tank Transfer Pipe is shrouded and also equipped with a Transfer Pipe Break Detector. The break detector is routed inside of the transfer line shroud between FR47 and FR53.5. The wiring is monitored by both FCMC‘s. If the FCMC detects a damage in the transfer line and the APU is in use it closes the : S Fuel isolation valve S LP fuel shutoff valve S Trim pipe isolation valve S Auxiliary forward transfer valve S TT inlet valve S TT isolation valve S APU pumps are OFF

Page 54 FRA US/T SHM 13.12.2007

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FUEL SYSTEM APU FEED SYSTEM

A330/A340-200/300 28−22

FR 47

FR 53.5

TRANSFER PIPE

WIRING IS POSITIONED CLOSE TO THE PIPE

Page 55 Figure 30 Schematic Trim Tank Transfer Line FRA US/T SHM 13.12.2007

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APU FUEL FEED OPERATION General The following table shows all operating modes used for the APU feed. There is some extra modes when the forward APU pump is used: S main engine start with the forward APU pump: if the electrical power is lost to all the main pumps (Engines flameout) the fuel can be supplied by the forward APU pump. S emergency electrical configuration: when on the emergency elec panel the LAND RECOVERY pushbutton is pressed a deenergized relay stops the aft APU pump. S operation with failure: if the forward fuel feed pump is inoperative the pressure switch in the trim tank transfer line detects less than 22 PSI. The aft APU fuel feed pump supplies now fuel to the APU from the trim transfer line.

Page 56 FRA US/T SHM 13.12.2007

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FUEL SYSTEM APU FEED SYSTEM

A330/A340-200/300 28−22

OPERATING CONDITIONS

PUMP STATUS

VALVE STATUS K L

FWD

AFT

J

GROUND OPERATION FIRST 120 SEC

OFF

ON

OPEN

OPEN

SHUT

SHUT

GROUND OPERATION AFTER 120 SEC

ON

OFF

OPEN

OPEN

SHUT

SHUT

REFUEL OF TRIM TANK

OFF

ON

OPEN

SHUT

OPEN

SHUT

CLIMB TO FL 255

ON

OFF

OPEN

OPEN

SHUT

SHUT

ABOVE FL 255 ( NO TRANSFER )

OFF

ON

OPEN

SHUT

SHUT

OPEN

ABOVE FL 255 ( AFT TRANSFER )

OFF

ON

OPEN

SHUT

OPEN

SHUT

FORWARD TRANSFER

OFF

ON

OPEN

SHUT

SHUT

OPEN

DESCENT / LAND ( TRIM TANK EMPTY)

ON

OFF

OPEN

OPEN

SHUT

SHUT

APU OFF

OFF

OFF

SHUT

SHUT

SHUT

SHUT

Valve Valve Valve Valve

J K L T

T

APU LP SOV APU FUEL ISOL VLV TT INL VLV TT ISOL VLV

Page 57 FRA US/T SHM 13.12.2007

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Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

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A330 28−21

28−21

ENGINE FEED SYSTEM

SYSTEM DESCRIPTION General The engines are supplied with fuel from the inner tanks. The low pressure valves isolate the engines from the fuel supply. They are normally operated by the engine master switch, or by the FIRE p/b switch. The normally closed wing crossfeed valve divides the two engine feed systems. Each engine is supplied by two main booster pumps, installed in the collector boxes. Another standby pump is installed outside of the collector box. A pressure switch monitors the output pressure of each fuel pump. When the crossfeed valve is open, it is possible for the pumps of one inner tank to supply fuel to the 2 engines. If one main pump is failed (or is OFF) the related standby pump automatically starts. This is done by the main pump pressure switch when the pressure is less than 6 PSI. The two main pumps are connected to a jet pump in the collector cell. The jet pump keeps the collector cell full of fuel and slightly pressurized. The system has: S AIR RELEASE VALVE bleed the air from the engine feed−pipes during fuel pump operation S THERMAL RELIEF VALVE protect the engine feed−pipes against too much pressure. The Engine and Warning Diplay (EWD) and the System Display (SD) which together make the ECAM give system data to the crew. If specified failures occur: S a warning is given on the EWD S the FUEL page shows on the SD

Canister Check Valves The canister has two outlets. The upper outlet is connected to the engine feed line and contains an internal flap-type check valve. A spring loaded poppet type check valve is attached to the lower outlet which supplies pressurized fuel to the jet pump. When a fuel pump is not in operation, the two check valves prevent any reverse flow of fuel through this pump. Jet Pump The jet pumps are operated by main pump outlet pressure and that created sucton draws the fuel from the related inner tank in the collector cell. The rate of flow makes sure that the collector cell is kept full of slightly pressurized fuel so that the pumps have a positive fuel supply in the event of a negative G load. Pressure Switch The pump pressure switch monitors the output pressure of the related pump. They are installed at the rear spar. The LO PRESS threshold is 6 PSI. Electrical Emergency Configuration The Emergency Generator is powered by RAT. S Only the normal LEFT PUMP 2 is powered. If the normal LEFT PUMP 2 fails or is selected OFF, the RIGHT PUMP 2 replaces it automatically. S The crossfeed Valve opens automatically. S When Speed decreases <260kts or If Land Recovery is selected ON, all Main and STBY Pumps are lost. The FWD APU pump starts automatically irrespective of the APU master switch position.

Fuel Pump The fuel pump element is installed in a canister attached to the wing bottom skin. They are fully interchangeable and operated by a 3 phase 115V motor. The delivery pressure is 20 PSI with a nominal flow of 13638 liters per hour. The no flow pressure is 35 PSI.

Page 58 FRA US/T SHM 13.12.2007

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A330 28−21

ENGINE 1

Page 59 Figure 31 Engine Feed System Schematic FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21

ENGINE FEEDING COMPONENT LOCATION Fuel Pump Pressure Switch The pressure switch monitors the output pressure of the fuel pump. It is installed on the rear face of the wing rear spar. A banjo−connection and pressure pipe connects the pressure switch to the fuel pump. If the pressure from a main pump decreases to less than 6 psi its pressure switch: S gives a ground to connect the electrical supply to the standby pump S puts on the amber FAULT light in the main pump P/BSW S sends a signal to the Fuel Control and Monitoring System (FCMS) S sends a signal to the ECAM system Main Fuel Pump The main fuel pump system has four main pumps and two standby pumps. Two main pumps and its related standby pump makes a sub−system. Each sub−system supplies fuel to its related engine. The circuit for each sub−system contains (and connects to) the same type of equipment. As the other sub−systems are almost the same, only the operation of the No. 1 sub−system/circuit is given here. Main and standby pumps are equipped with thermal switches. If the pump element temperature increases above 192° C three thermal switches operate. The pump stops and must be replaced. For removal the pump has to pulled to a stop where the canister is closed, and then the cavity can be drained by removing the drain plug. To remove the pump completely it has to be turned 30° counterclockwise guided by a groove.

Page 60 FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21

CHECK VALVE

TO ENGINE

MAIN FUEL PUMP

FWD INNER

LP VALVE

TO ENGINE

CANISTER CHECK VALVE

MAIN FUEL PUMP AFT INNER

CANISTER

O-RING

TO JET PUMP

O-RING

PRESSURE SWITCH

ELECTRICAL REAR

Page 61

CONNECTOR

SPAR

Figure 32 Main Fuel Pump/Pressure Switch FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21

Thermal Relief Valve The valve body contains a ball and a spring. The spring holds the ball against a valve seat. When the fuel pressure increases to more than 40 psi the ball lifts (against the pressure of the spring) to release the fuel through the outlet holes. Air Release Valve The body of the valve has a mounting flange at the bottom and the rubber check valve at the top. Internally the valve has three chambers, which are: S a vent chamber S a diaphragm chamber S a float chamber The float chamber contains an annular float. Openings in the bottom of the chamber let in the fuel and air. A small opening at the top of the float chamber connects to the diaphragm−chamber. The vent valve (attached to the center of the diaphragm) closes the vent port between the float chamber and the vent chamber. Jet Pump The jet pump makes sure that its collector cell is kept full of fuel. The fuel supply flows through the nozzle and causes a suction. This suction causes fuel in the inner tanks to move through the jet pump into the collector cell. The rate of flow makes sure that the collector cell is kept full of lightly pressurized fuel (and that the fuel pumps have a fuel supply during negative ’G’ conditions).

Page 62 FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21

JET PUMP

DIFFUSER LP VALVE

INNER

INNER

MIXING

MOTIVE FLOW

TUBE

NOZZLE

SUCTION

FUEL PUMP

FLOW

PRESSURE

INLET

INLET

AIR RELEASE VALVE

ENGINE FEED THERMAL RELIEF VALVE

RUBBER CHECK VALVE

DIAPHRAGM CHAMBER DIAPHRAGM

VENT CHAMBER FLOAT CHAMBER ANNULAR FLOAT STEM ASSY

Page 63 Figure 33 Jet Pump, Air Release Valve, Thermal Relief Valve FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21

ENG LP FUEL SHUTTOFF VALVE DESCRIPTION General The engine LP fuel shutoff valve isolates its corresponding engine. The related engine master switch controls the operation of the LP valve. If the engine Fire pushbutton switch is operated the LP valve closes despite the position of the engine master switch. Description and Operation The LP fuel shutoff valve has two independent electrical control circuits. They connect through a control relay to these related switches S the ENGINE MASTER SWITCH S the FIRE PUSHBUTTON SWITCH The LP valve isolates its related engine from the engine fuel feed line. The LP valve is in the fuel feed line to the engine. The interface between the valve and the actuator is made by a spindle that goes through the front spar of the wing. A V−band clamp connects the actuator to the LP valve drive assembly on the front spar. A heat resistant box contains the actuator and the drive assembly. Thus you don’t have to go in the fuel tank to replace the actuator. Each actuator has two motors, which get their power supply from different sources: S the 28VDC HOT BUS 1 supplies the motor 1 S the 28VDC BUS 2 supplies the motor 2 Indication The actuator send position information to the SDAC and the FCMCs for valve monitoring by travel limit switches inside the actuators. The valve position can be seen on the ECAM fuel page. NOTE: In order to perform a engine motoring test it is required to have positive fuel pressure in the Fuel Metering Unit. This is achieved by opening the Circuit Breaker 1KC1. Now the deenergized Master Switch Slave Relay closes the contact to the open position and the actuator opens the LP VALVE.

Page 64 FRA US/T SHM 13.12.2007

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FUEL SYSTEM FEEDING SYSTEM

A330 28−21 LP VALVE FIRE PUSHBUTTON

ENGINE MASTER PANEL

1

2

WING FRONT SPAR

HEAT RESISTANT BOX ACTUATOR

AIR RELEASE VALVE

Page 65 Figure 34 LP Valve Schematic FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

Lufthansa Technical Training

FUEL SYSTEM CROSSFEED SYSTEM

A330 28−23

28−23

CROSSFEED SYSTEM

SYSTEM DESCRIPTION General The crossfeed system has a crossfeed valve which is normally closed. In this configuration it divides the engine fuel feed system in the left hand and the right hand system. Thus when selected open by the crew the engine feed line is opened to supply both engines by one tank only. Description The crossfeed valve is installed to the rear wall of the center wing box. The actuator is attached by a V−clamp to the crossfeed valve drive assembly. The interface is made by a spindle which coonects the valve to the actuator. A visual indicator on the casing of the actuator gives position information. Indication Crossfeed valve position information is send by travel limit switches inside of the actuator to SDAC and to the FCMCs. The valve position can be seen on the ECAM fuel page. Automatic operation The cross feed valve opens automatically in electrical emergency configuration.

Page 66 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CROSSFEED SYSTEM

A330 28−23

APU FUEL FEED CHECK VALVE

CROSSFEED VALVE REAR SPAR

V-BAND CLAMP

ACTUATOR

SEE / FEEL INDICATOR

Page 67 Figure 35 Crossfeed System Schematic FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CROSSFEED SYSTEM

A330/A340-200/300 28−23

COMPONENT DESCRIPTION Crossfeed Actuator The actuator has two electrical motors which turn the ball valve through 90° . Limit switches in the actuator control this 90° movement and set the electrical circuit for the next operation. One of the two motors can open or close the valve if the other motor does not operate. A V−Band clamp attaches the actuator to the flange of the drive assembly. A location peg makes sure the actuator engages correctly. Apu Check Valve (optional) A check valve is installed on the APU fuel feed line which connects to the engine feed line. It lets the FWD APU pump supply the engine feed line but prevents supply of fuel from the engine feed system to the APU feed line. When the fuel pressure comes from the outlet direction, the valve−plate closes and prevents fuel flow back through the valve. An O−ring prevents a fuel leakage from the valve.

Page 68 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CROSSFEED SYSTEM

A330/A340-200/300 28−23

APU CHECK VALVE

ELECTRICAL O-RING

ACTUATOR

V-CLAMP

DRIVE ASSEMBLY

ROLL PIN FLAPPER CHECK VALVE SLOT

SEE/FEEL INDICATOR

INLET

OUTLET

Page 69 Figure 36 APUCheck Valve, Crossfeed Actuator FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

28−26

MAIN TRANSFER SYSTEM

GENERAL The main transfer system controls the flow of fuel from the center and the outer tanks to the two inner tanks. The system uses fuel pumps to move the fuel from the center tank to the inner tanks. It uses gravity to move the fuel from the outer tanks to the inner tanks. The Fuel Control and Monitoring System (FCMS) automatically controls the system, but the crew can manually control it from the cockpit if necessary. The Engine/Warning Display EWD and the System Display SD (which together make the ECAM) give main transfer system information to the crew. If specified failures occur: S the FUEL page shows on the SD. The main transfer system has these components: S the five P/B switches L CTR, R CTR, CTR TANK XFR, OUTER TK XFR and T TANK MODE on the cockpit fuel panel 245VU S the Center Fuel Transfer Pump element and its related canister (which together make a transfer pump) S the Pressure Switch S the Inner Tank Inlet Valve and its related electrical actuator S the Intertank Transfer Valve and its related electrical actuator The FCMS has automatic control of the outer to inner tank fuel transfer all of the time. When you make an on selection on the L CTR or R CTR P/BSW the FCMS has control of all the main transfer system. If there is fuel in the center tank, a fuel transfer occurs in two steps: Step 1 Center Tank to Inner Tank (A330−200 only) During the first step, the two transfer pumps supply fuel pressure to the refuel gallery. Thus the pumps move fuel from the center tank to the inner tanks (or to the outer tanks if specified failure conditions occur). The pumps are attached to the bottom of the center tank as follows: S the LH transfer pump between STA3461/FR45 and STA3514/FR46 (LH side) S the RH transfer pump between STA3461/FR45 and STA3514/FR46 (RH side).

Page 70 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 71 Figure 37 Center to Inner Transfer (Auto Mode) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

Step 2 Outer Tank to Inner Tank The second step of the fuel transfer starts when the fuel in the outer tanks is moved to the inner tanks. The intertank transfer valve controls this fuel flow. It is installed, in the inner tank, on the bottom half of STA1530/RIB23 between stringer 11 and 12. The two valves open together, and gravity causes a fuel flow from the outer to the inner tanks. The actuator operates the intertank transfer valve through a driveshaft. The actuator is installed on the forward face of the front spar. When energized, it moves the intertank transfer valve to the open or closed position.

Page 72 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 73 Figure 38 Outer to Inner (Auto Mode) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

MAIN TRANSFER DESCRIPTION A330−200 CENTER TO INNER TRANSFER When the L CTR (or R CTR) P/BSW is set to on, the related transfer pump operates. The selection of one of the two switches also gives the FCMS control of the center to inner fuel transfer. It is usual for the two P/BSWs to be set to ON at the same time. The two transfer pumps then operate continuously until the center tank is empty. When the fuel contents of an inner tank decreases to UNDERFULL LEVEL (underfull is set at approximately 2500 l below the hi−level), the Fuel Quantity value is sent to the FCMS. The FCMS connects a 28VDC supply to energize the INNER TANK INLET VALVE open. The fuel in the center tank starts to flow to the inner tank. The fuel transfer continues until the fuel Hi−Level Sensor in the inner tank becomes wet. When this occurs the FCMS connects a 28VDC supply to energize the inner−tank inlet valve closed. When the fuel contents in the inner tank decreases to underfull the inlet valve is opened again. This open and close cycle continues until the center tank is empty. When the center tank LO LEVEL SENSOR is dry and the pumps are at low pressure, the FCMS: S de−energizes the two transfer pumps S closes the two inner−tank inlet valves

MANUAL OPERATION Three P/BSWs on the cockpit fuel panel 245VU give manual control of three different areas of the main transfer system. They are: S the CTR TANK XFR P/BSW S the OUTER TK XFR P/BSW S the T TANK MODE P/BSW CTR TANK XFR SWITCH When you set the CTR TANK XFR P/BSW to MAN, the fuel moves from the center tank to the inner tanks (and stops an aft fuel transfer). NOTE: When the CTR TANK XFR P/BSW is set to MAN, it is necessary for the transfer system to be carefully monitored to make sure, the inner or outer tanks are not filled to more than the necessary level and the transfer pumps do not operate for an extended time in a dry tank.

OUTER TO INNER TRANSFER As the fuel is burned, the fuel contents of one of the two inner tanks decreases to LO LEVEL (3500 kg) on the FQI indication. When this occurs, the FCMS connects a 28VDC supply to the two INTERTANK TRANSFER VALVES. The valves open and gravity causes the fuel to flow from the outer to the inner tanks. The fuel transfer continues until the fuel contents, of the inner tank that caused the fuel transfer, increases to 4000 kg. When this occurs the FCMS closes the Intertank Transfer Valves. They open together again when the fuel level in one of the two inner tanks again decreases to 3500kg. This open and close cycle continues until the two outer tanks are empty. When an outer tank FQI signal is below 10 kg for 5 minutes the related intertank transfer valve is energized closed.

Page 74 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 75 Figure 39 Center to Inner Transfer (Manual Mode) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

OUTER TK XFR SWITCH When you set the OUTER TK XFR P/BSW to ON, the fuel moves from the center and outer tanks to the inner tanks (and stops an aft fuel transfer). Following valves are hardwired controlled: S left and right Intertank Transfer Valves OPEN S left and right Inner Tank Inlet Valves OPEN S left and right Outer Tank Inlet Valves OPEN S Aft Transfer Valves SHUT S Trim Pipe Isoaltion Valve SHUT S Center Tank Inlet Valve SHUT

Page 76 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 77 Figure 40 Outer to Inner (Manual Mode) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

MAIN TRANSFER DESCRIPTION A330−300 OUTER TO INNER AUTOTRANSFER As the fuel is burned, the fuel contents of one of the two inner tanks decreases to LO LEVEL (3500 kg) on the FQI indication. When this occurs, the FCMS connects a 28VDC supply to the two INTERTANK TRANSFER VALVES. The valves open and gravity causes the fuel to flow from the outer to the inner tanks. The fuel transfer continues until the fuel contents, of the inner tank that caused the fuel transfer, increases to 4000 kg. When this occurs the FCMS closes the Intertank Transfer Valves. They open together again when the fuel level in one of the two inner tanks again decreases to 3500kg. This open and close cycle continues until the two outer tanks are empty. When an outer tank FQI signal is below 10 kg for 5 minutes the related intertank transfer valve is energized closed.

Page 78 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 79 Figure 41 Outer to Inner Autotransfer A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26

OUTER TO INNER MANUALTRANSFER When you set the OUTER TK XFR P/BSW to ON, the fuel moves from the outer tanks to the inner tanks (and stops an aft fuel transfer). Following valves are hardwired controlled: S left and right Intertank Transfer Valves OPEN S left and right Inner Tank Inlet Valves OPEN S left and right Outer Tank Inlet Valves OPEN S Aft Transfer Valves SHUT S Trim Pipe Isoaltion Valve SHUT

Page 80 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330 28−26 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 81 Figure 42 Outer to Inner Manual Transfer A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330/A340-200/300 28−26

MAIN TRANSFER COMPONENTS Fuel Pump Element The fuel pump element is the same type as those in the main fuel pump system. For its description refer to the main fuel pump system. Fuel Pump Canister The canisters make it possible to replace the fuel element when there is fuel in the center tank. The outlet pipe from each canister contains a check valve. This check valve prevents an opposite fuel flow through the pump when it is not in operation. The check valve and a slide−valve seal the canister when you replace the fuel pump element. Transfer Fuel Pump Pressure Switch The pressure switch monitors the output pressure of the transfer pump. If the pressure decreases to less than 6 PSI the pressure switch: S puts on the amber FAULT light of the related L CTR or R CTR P/BSW S sends a signal to the ECAM. Inner Tank Inlet Valve The inlet valve is installed in the fuel supply line to each inner tank. There it independently controls the flow of fuel from the refuel gallery to the inner tank. The valve is installed in the center tank and attaches to the forward face of the rear spar. The valve has a spindle which goes through the rear spar to engage with the actuator. This actuator attaches to the rear face of the rear spar. When energized it moves the inlet valve to the open or closed position.

Page 82 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330/A340-200/300 28−26

CENTER TANK REAR SPAR

O-RING

CENTER TANK

O-RING INNER TANK PRESSURE

INLET VALVE

SWITCH PUMP CANISTER

ELECTRICAL ACTUATOR ELECTRICAL REAR

CONNECTOR

TRANSFER

SPAR

PUMP

C

C O

O

OPEN POSITION

CLOSED POSITION

ELECTRICAL CONNECTOR

COVER

Page 83 Figure 43 Inner Tank Inlet Valve, Pressure Switch, Transfer Pump FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330/A340-200/300 28−26

Intertank Transfer Valve The valve has a body attached to a mounting flange and a driveshaft. The valve body holds a ball valve. The ball valve has a rectangular location slot into which the driveshaft engages. Four bolts connect the mounting flange to the aircraft structure. The driveshaft connects the actuator to the intertank transfer valve. The driveshaft has: S a universal joint and a length adjuster S a rectangular drive (which engages in the location slot in the ball valve) at the other end. The actuator has a body with a mounting flange. The body contains one 28VDC electrical motor. This motor drives a gear which turns the transfer−valve driveshaft and the ball valve through 90°. There is a mechanical indicator on the body which shows the position of the valve (open or closed).

Page 84 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM MAIN TRANSFER SYSTEM

A330/A340-200/300 28−26

FRONT SPAR

ELECTRICAL ACTUATOR RIB 23

C DRIVE

O

C O

SHAFT

ELECTRICAL OPEN POSITION

CLOSED POSITION

CONNECTOR

Page 85 Figure 44 Intertank Transfer Valve FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28-00 FUEL SYSTEM 28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON...

Lufthansa Technical Training

FUEL SYSTEM EMERGENCY ISOLATION

A330/A340-200/300 28−11

28−11

FUEL ISOLATION

SYSTEM DESCRIPTION General The emergency isolation valve is used to separate the FWD inner to the AFT inner tank. This is done by selecting the INNER TANK SPLIT pushbutton on the overhead panel. The crew selects the normally open valve to shut in case of structural damage after an engine burst. Description OFF: The emergency isolation valve (inner tank division) is open. ON: The valve closes and the inner tank is split in two parts. In case of tank damage the fuel from either inner tank division may be used. The ON light comes on amber. SHUT: Comes on blue when the valve is shut. During refueling, whenever the first inner tank high level sensor becomes wet, the valve closes. At the end of refueling, the valve opens again An electrical actuator operates the emergency isolation valve. The actuator is installed on the aft face of the rear spar. The interface between the actuator and the valve is a driveshaft that goes through the rear spar. Operation An electrical actuator operates the emergency isolation valve through a driveshaft. The actuator is installed on the rear spar. Thus you do not have to go into the fuel tank to replace the actuator. The actuator has two motors, which get their power supply from different sources: S motor 2 the 28VDC BUS 2 S motor 1 the 28VDC ESS BUS/SHED The INNER TANK SPLIT pushbutton on the fuel control panel 211VU (which is part of the cockpit overhead panel) controls the operation of the emergency isolation valves.

Page 86 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM EMERGENCY ISOLATION

A330/A340-200/300 28−11

V-BAND CLAMP FUEL TRANSFER PIPE

ISOLATION VALVE

VISUAL

ON SHUT

INDICATOR DUAL ACTUATOR

AMBER INDICATION BLUE INDICATION

WING REAR SPAR

SEE-FEEL INDICATOR

CLOSED POSITION

OPEN POSITION

Page 87 Figure 45 Emergency Isolation Valve FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

28−27

TRIM TANK TRANSFER

SYSTEM DESCRIPTION General The trim transfer system controls the Center of Gravity (CG) of the aircraft. For this function the system moves fuel from the wings to the trim tank (Aft transfer) or from the trim tank to the wings (Forward Transfer). This movement of fuel changes the CG of the aircraft. The system operates automatically but the crew can manually set a forward transfer. The Fuel Control and Monitoring System calculates the CG of the aircraft and compares the result to a target−value. If necessary, the FCMS then makes a decision to move fuel aft or forward to control the CG. Aft Transfer Usually only one aft transfer is made during each flight. But (as the fuel burns) many small forward−transfers are made to control the CG. It is only possible for the FCMS to send an aft transfer signal. Forward Transfer A forward transfer is carried out several times during flight depending on the situation.

Description A three−position switch (ISOL/AUTO/OPEN) on the cockpit fuel panel 245VU: S ISOL isolates the trim tank S AUTO lets the system operate automatically S OPEN drains the trim pipe The trim transfer system has six fuel valves (with their related electrical actuators), an air release valve, three check valves and a fuel pump with a pressure switch. They are identified as: S the left and right Aft Transfer Valves S the Auxiliary Forward Transfer Valve S the Trim Pipe Isolation Valve S the TrimTank Isolation Valve S the Trim Tank Inlet Valve S the Air Release Valve S the Trim Transfer Pump and its pressure switch

Page 88 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 89 Figure 46 Trim Transfer Overview A330−200 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

THIS PAGE INTENTIONALLY LEFT BLANK

Page 90 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 91 Figure 47 Trim Transfer Overview A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER SYSTEM

A330/A340−200/300 28−27

SYSTEM FUNCTION General Before each flight the crew input the aircraft Zero Fuel Center of Gravity (ZFCG) and Zero Fuel Weight (ZFW) data into the FMS. The two FMS computers independently transmit this data to the FCMS. The FCMS compares the two sets of data and (if they agree) uses it to set the datum for the CG calculation. The FCMS accepts the data from one FMS computer if the other is unserviceable. The FCMS then uses the calculated CG datum, the computed aircraft fuel−contents data and the known tank moment−arms to calculate the aircraft CG The Flight Management, Guidance and Envelope Computer (FMGEC) independently monitors the CG of the aircraft. If it detects that the aircraft’s CG is too far aft, it moves the target CG forward. If it detects the problem a second time, it sends a signal to the FWC. The FWC stops the CG control and shows a warning to the crew. The crew then manually set a forward transfer. The automatic operation of the system is divided into two parts: S the AFT TRANSFER S the FORWARD TRANSFER

Aft Transfer Usually only one aft transfer is made during each flight. But (as the fuel burns) many small forward−transfers are made to control the CG. It is only possible for the FCMS to send an aft transfer signal, when all the conditions that follow occur: S the calculated CG is less than the target CG minus 0.5% Mean Aerodynamic Chord (MAC) S the landing gear and slats are fully retracted S the inner tank fuel contents are more than 6250 kg each. S the trim tank is not full S the aircraft is above 25500 ft Forward Transfer S A forward transfer is carried out if one of these conditions occurs: S the calculated CG is greater than the target CG S the fuel contents of one of the two inner tanks decreases to 6250 kg S the FCMS receives 35 minutes−to−destination data from the Flight Management System (FMS) S the jettison system is set to ON S the aircraft descends below 24500 ft

Page 92 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER SYSTEM

A330/A340−200/300 28−27

Page 93 Figure 48 Trim Transfer Logic FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

TRIM TANK TRANSFER OPERATION General Before each flight the crew input the aircraft Zero Fuel Center of Gravity (ZFCG) and Zero Fuel Weight (ZFW) data into the FMS. The two FMS computers independently transmit this data to the FCMS. The FCMS compares the two sets of data and (if they agree) uses it to set the datum for the CG calculation. The FCMS accepts the data from one FMS computer if the other is unserviceable. The FCMS then uses the calculated CG datum, the computed aircraft fuel contents data and the known tank moment arms to calculate the aircraft CG. The Flight Management, Guidance and Envelope Computer (FMGEC) independently monitors the CG of the aircraft. If it detects that the aircraft’s CG is too far aft, it moves the target CG forward. If it detects the problem a second time, it sends a signal to the FWC. The FWC stops the CG control and shows a warning to the crew. The crew then manually set a forward transfer. The automatic operation of the system is divided into two parts: S the AFT TRANSFER S the FORWARD TRANSFER

Page 94

S the CTR TANK XFR P/BSW is set to MAN S the OUTER TK XFR P/BSW is set to MAN NOTE: Usually only one aft transfer is made during each flight. This transfer stops when the aft CG target is reached or the trim tank is full. A second aft transfer can only start, if the CG is 2% forward of the target and the trim tank fuel level is less than 3000 kg. Center tank contains fuel During an aft transfer the Transfer Pumps move the fuel from the center tank to the trim tank. The FCMS opens the: S Trim Pipe Isolation Valve S Trim Tank Inlet Valve

Aft Transfer The FCMS has full control of the aircraft CG when the aircraft is above 25500 ft, until the aircraft descends below 24500 ft. An aft transfer can only start when all of these conditions occur at the same time: S the calculated CG is less than the target CG minus a constant moment S the landing gear is retracted S the slats are retracted S the trim tank is not full S the inner tank fuel contents are more than 6250 kg each. The aft transfer stops if one of these conditions occur: S the trim tank becomes full S the calculated CG is greater than the target CG S the fuel quantity in an inner tank decreases to less than 6250 kg S the crew set the T TANK MODE P/BSW to FWD S the jettison system is set to ON FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 95 Figure 49 Aft Transfer from Centertank A330−200 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

Center tank empty The main pumps move fuel from the inner tanks to the trim tank. The FCMC opens: S the Trim Tank Inlet Valve S the Trim Pipe Isolation Valve S the LH and RH Aft Transfer Valves If the inner tanks are more than 500 kg out of balance, then the aft transfer is from the heavier side.

Page 96 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 97 Figure 50 Aft Transfer from Inner A330−200 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

Aft Transfer A330−300 The main pumps move fuel from the inner tanks to the trim tank. The FCMC opens: S the Trim Tank Inlet Valve S the Trim Pipe Isolation Valve S the LH and RH Aft Transfer Valves If the inner tanks are more than 500 kg out of balance, then the aft transfer is from the heavier side.

Page 98 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 99 Figure 51 Aft Transfer A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

FORWARD TRANSFER OPERATION A330−200 AUTO OPERATION The FCMS sends a forward transfer signal if one of these conditions occurs: S the calculated CG is greater than the target CG S the fuel contents of one of the two inner tanks decreases to 4000 kg (the forward transfer continues until the fuel quantity is greater than 4100 kg) S the FCMS receives a 35 minutes to destination signal S the jettison system is set to ON S the aircraft descends below 24500 ft Center tank contains fuel A forward transfer is not usually necessary when there is fuel in the center tank. If fuel is in the center tank, the forward transfer is into the center tank. The FCMS opens: S the Auxiliary Foward Transfer Valve S the Trim Tank Isolation Valve NOTE: If the center tank becomes full during a forward transfer, the auxiliary forward transfer valve is closed. It does not open again until the fuel quantity in the tank has decreased 2500 liters below hi−level.

Page 100 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 101 Figure 52 Fwd Transfer (Center Tank) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

Center tank empty The fuel goes from the trim tank to the inner tanks through the inner tank inlet valves. The FCMS opens: S the Trim Pipe Isolation Valve S the Trim Tank Isolation Valve S the Inner Tank Inlet Valves During this fuel−transfer the fuel tank supplied can become full. If this occurs the FCMS closes the inner tank inlet valve. The fuel−transfer stops until the fuel quantity in the inner tank decreases to hi−level minus 2000 kg. During this fuel−transfer the inner tanks may become more than 500 kg out of balance. If this occurs, the inner tank inlet valve of the heavier tank will close and forward transfer to the heavier tank will stop.

Page 102 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 103 Figure 53 Fwd Transfer (Inner Tanks) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

MANUAL OPERATION When the T TANK MODE P/BSW is set to FWD, the CG control stops and a forward transfer (into the center tank) starts. The Trim Transfer pump starts to run (if installes and if not already on). The forward transfer has to be monitored to make sure that the center tank is not filled to more than the necessary level. These valves move to the position shown: S the Trim Tank Isolation Valve OPEN S the Auxiliary Forward Transfer Valve OPEN S the Trim Pipe Isolation Valve CLOSED S the Aft Transfer Valves CLOSED When the T TANK MODE P/BSW is released it gives the FCMS CG control again. If necessary the aft transfer starts again.

Page 104 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 105 Figure 54 Fwd Transfer (FWD P/B Pushed) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

ISOLATION CONTROL The T TANK FEED switch has three positions (AUTO, ISOL and OPEN). S AUTO position This is the usual position of the switch which gives the FCMS full control of the trim transfer system. S ISOL position When the switch is set to ISOL the FCMS closes the: − Trim Tank Isolation Valve − Trim Tank Inlet Valve − Auxiliary Forward Transfer Valve − Trim Pipe Isolation Valve S OPEN position When the switch is set to open, this valves are controlled to open: − Trim Tank Isolation Valve − Trim Tank Inlet Valve − Auxiliary Forward Transfer Valve The fuel in the trim tank and trim pipe then drains into the center tank. During flight the trim transfer pipe is automatically isolated when the landing gear control lever is set to DOWN. The FCMS closes the: S Trim Pipe Isolation Valve S Trim Tank Isolation Valve

Page 106 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 107 Figure 55 Fwd Transfer (Feeding Switch to open) FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

FORWARD TRANSFER OPERATION A330−300 AUTOMATIC OPERATION The fuel goes from the trim tank to the inner tanks through the inner tank inlet valves. The FCMS opens: S the Trim Tank Isolation Valve S the Aux Fwd. Transfer Valve S the Trim Pipe Isolation Valve S the Inner Tank Inlet Valves During this fuel−transfer the fuel tank supplied can become full. If this occurs the FCMS closes the inner tank inlet valve. The fuel−transfer stops until the fuel quantity in the inner tank decreases to hi−level minus 2000 kg. During this fuel−transfer the inner tanks may become more than 500 kg out of balance. If this occurs, the inner tank inlet valve of the heavier tank will close and forward transfer to the heavier tank will stop. MANUAL OPERATION When the T TANK MODE P/BSW is set to FWD, the CG control stops and a forward transfer (into the center tank) starts. The Trim Transfer pump starts to run (if installes and if not already on). The forward transfer has to be monitored to make sure that the inner tanks are not filled to more than the necessary level. When the T TANK MODE P/BSW is released it gives the FCMS CG control again. If necessary the aft transfer starts again.

Page 108 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 109 Figure 56 FWD Trim Transfer A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27

Trim Tank Isolation The T TANK FEED switch 13QN has three positions (AUTO, ISOL and OPEN). S AUTO position AUTO is the usual position of the switch which gives the FCMS full control of the trim transfer system. S ISOL position When the switch is set to ISOL it connects a 28VDC supply to close the trim−tank isolation valve. It also connects a ground to the relay 18QN (trim tank fuel−isolation slave). This relay connects a 28VDC supply to close: − the trim−tank inlet valve − the auxiliary forward−transfer valve − the trim−pipe isolation valve. S OPEN position In this position, these valves stay open. − the trim-tank inlet valve − the trim tank isolation valve − the aux fwd. transfer valve − the trim pipe isolation valve − the inner tank inlet valves. The fuel in the trim tank and trim pipe then drains into the two inner tanks.

Page 110 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330 28−27 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 R PUMP 2

APU FWD PUMP

R STBY

L STBY RH INNER TK INLET VLV

LH INNER TK INLET VLV

LH EMER ISOL VLV

TRIM PIPE ISOL VLV

REFUEL ISOL VLV LH LH OUTER TK INLET VLV

RH EMER ISOL VLV

REFUEL ISOL VLV RH RH OUTER TK INLET VLV

AUX FWD X-FER VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

LH OUTER TANK

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 111 Figure 57 FWD Trim Transfer Override A330−300 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330/A340-200/300 28−27

TRIM TANK TRANSFER COMPONENTS General

Trim Tank Transfer Pump ( AC MSN 101 and on )

The trim tank is installed in the THS and moves when the THS moves. A flex hose connects the trim pipe to the trim tank. The flex hose keeps the trim pipe connected to the trim tank during movements of the THS.

The Trim Transfer Pump is installed in a canister (mounting plate) in the forward face of the trim tank. There it supplies the fuel pressure for the forward transfers. The mounting plate has three check valves fitted. When the pump is removed from the mounting plate, the three check valves close. Thus the pump can be replaced when there is fuel in the trim tank.

Trim Tank Isolation Valve The Trim Tank Isolation Valve is installed in the fuel line from the trim tank to the trim pipe. It controls the forward transfer of fuel from the trim tank to the trim pipe. The valve is installed below the trim tank. It has a valve spindle which comes out of the valve to engage with an actuator. The actuator is attached to the valve. When energized it moves the valve to the open or closed position. The supply from the trim tank to the isolation valve is normally from the trim transfer pump. If the trim transfer pump is not in operation, then the supply is through an outlet in the bottom of the tank. The outlet has a coarse mesh strainer. Trim Tank Inlet Valve The Trim Tank Inlet Valve is installed in the fuel supply pipe to the trim tank. It controls the flow of fuel into the trim tank. The valve is installed in the trim tank and is attached to the bottom skin. It has a valve spindle which goes through the bottom of the trim tank to engage with an actuator. The actuator is attached to (and below) the bottom skin of the trim tank. When energized it moves the valve to the open or closed position. Air Release Valve The Air Release Valve is installed on the trim pipe in the trim tank. The air release valve automatically bleeds the air from the trim pipe into the trim tank. This function prevents a build−up of air in the trim pipe, which could pass to the APU.

The trim transfer pump also gives the fuel supply to the water scavenge system. The forward fuel transfer check valve is installed in the transfer fuel pipe outlet in the trim tank. When the trim transfer pump is in operation, the check valve prevents the flow of fuel from the trim pump back into the trim tank. When the pump is not in operation, it lets the fuel gravity feed into the trim pipe. Transfer Pump Operation ( AC MSN 101 and on ) The FCMS controls the operation of the trim transfer pump. There are no indications in the cockpit that the pump is in operation. The pump operates when all of these conditions occur at the same time: S the aircraft is in flight and the landing gear and slats are retracted S there is more than 200 kg of fuel in trim tank or the trim tank lo−level sensor is wet The pump then operates all of the time. When the trim−tank isolation valve opens, the pump supplies fuel pressure for the forward transfer. The trim transfer pump stops when one of these conditions occur: S the aircraft is in flight and the landing gear is extended S there is less than 200 kg of fuel in trim tank and the trim tank lo−level sensor is dry The trim transfer pump pressure−switch has low pressure for more than 10 minutes. The trim transfer pump does not operate when the aircraft is on the ground (except if the FWD Transfer P/B is set to on - this overrides the automatic control of the pump).

Page 112 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM TRIM TANK TRANSFER

A330/A340-200/300 28−27

TRIM TANK OUTLET CHECK TRIM TANK

VALVE

INLET VALVE AIR RLEASE VALVE

FRONT

TRIM TANK

SPAR

ISOLATION VALVE

TRIM TANK TRANSFER PUMP FUEL OUTLET VAPOUR DISCHARGE

FUEL INLET

FIXED ELECTRICAL CONNECTOR

DRAIN PLUG

Page 113 Figure 58 Trim Tank Components FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM WATER SCAVENGE SYSTEM

A330/A340-200/300 28−17

28−17

WATER SCAVENGE

SYSTEM DESCRIPTION Old Installation (AC SN 051-099) If water gets into the fuel in the trim tank, the water scavenge system keeps that water in suspension. The system has an electrical fuel pump, together with two jet pumps, which operate when these two conditions occur: S the trim tank has more than 1000 kg (2200 lb) of fuel S a main fuel pump is in operation. New installation (AC SN 101-199) The trim tank transfer pump is a booster pump 115 V 3 phase operated. The pump operates two jet pumps inside of the trim tank for recirculation purposes, and is also used for forward transfers. The FCMS controls the operation of the trim transfer pump. There is no indication in the cockpit that the pump is in operation. The pump operates under following conditions: S the aircraft is in flight and the landing gear and slats are retracted S there is more than 200 kg of fuel in the trim tank or the trim tank lo-level sensor is wet. The pump then operates all the time. When the trim tank isolation valve opens, the pump supplies fuel to carry out the forward transfer. The trim tank transfer pump stops when one of these conditions occur: S aircraft in flight and landing gear extended S there is less than 200 kg of fuel in the trim tank and the trim tank lo-level sensor is dry S the trim tank transfer pressure switch has low pressure for more than 10 minutes The trim tank transfer pump does not operate on ground (as long as the FWD Transfer P/B is not set to on).

Page 114 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM WATER SCAVENGE SYSTEM

A330/A340-200/300 28−17 TRIM TANK TRANSFER PUMP

TRIM TANK

TRIM TANK TRANSFER PUMP

OUTLET SIDE FIXED ELECTRICAL CONNECTOR

TRIM TANK JET PUMPS

JET PUMP OPERATION PRESSURE SUCTION SIDE

Page 115 Figure 59 Water Scavenge Components FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

28−25

REFUEL/DEFUEL SYSTEM

REFUEL/DEFUEL PANEL CONTROLS Fuel Quantity Indicator The Fuel Quantity Indicator (FQI) displays the quantity of fuel in each tank, the actual total fuel in the aircraft, and the preselected fuel. Here, the quantities are displayed in 1000 kg units. HIGH LEVEL Lights The High Level lights (Blue) come on, when the related fuel tank high level sensors are wet. Each light has a filament press-to-test facility. Refuel LOAD (INCrease/DECrease) Switch This switch selects the refuel load for automatic refueling. This is displayed in the PRESELECTED window of the Fuel Quantity Indicator. The preselected load can be increased or decreased using the switch. OVERFLOW Lights An Overflow light (Amber) comes on if the associated Surge Vent Tank sensor is covered by fuel. Each light has a filament press-to-test facility.

MODE SELECTOR The Mode Selector is guarded in the OFF position. When set to REFUEL or DEFUEL it energizes the Refuel Isolation Valve. With the selector in the REFUEL position, the Inlet Valves operate automatically or manually, depending on their Refuel/Defuel Valve switch position. When the Mode Selector is in the DEFUEL position, the Refuel/Defuel Valves switches can be opened and closed as necessary. REFUEL/DEFUEL VALVES Switches There is one Refuel/Defuel Valve Switch per Tank. Guarded in the NORM position, it automatically controls its Inlet Valve depending on the Mode Selector position. With the Refuel/Defuel Valve Switch in the SHUT position, the Inlet Valve is always closed. When a Refuel/Defuel Valve Switch is set to OPEN, the Inlet Valve opens if the Mode Selector is also set to REFUEL or DEFUEL. In refuel mode, the valve closes if high level is detected in its fuel tank Note that to refuel the Trim Tank, the Center Tank Valve must also be set to OPEN. On the A330−200 the Center Tank cannot be defueled unless the Trim Tank is also set to Defuel. (CG position interlock)

Page 116

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

OPTIONAL REFUEL PUSHBUTTON SW.

285VU

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

REFUEL OFF DEFUEL

L INR TK

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

990VU

Page 117 Figure 60

Refuel/Defuel Panel

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

COCKPIT Light The CKPT Light (Green) comes on, when cockpit refueling is selected. Then the Load Select Switch is disabled since Cockpit Refueling has priority. END Light S The END Light (Green) comes on steady, when the refueling is completed and selected fuel quantity equals actual fuel quantity ± 100 kg. S The END Light (Green) comes on flashing, − if there is a system failure causing the Refuel/Defuel Isolation Valve to shut or the tank inlet valves to shut (tank specific). − one of the Tank Switches is not in NORM position during refueling. − if there is an unbalance between the wings by > 3000 kg or there is a difference between Actual and Preselected Quantity >100 kg.

APU EMERGENCY SHUT DOWN Switch When the APU Emergency Shut Down PB Sw. is pressed, the APU shuts down immediately. It is used if a fuel spillage or overflow occurs or in any other emergency condition. TRANSFER VALVE Switch To transfer fuel on ground, the TRANSF. VALVE Switch can be used. Transfer is possible from the Inner or Center tanks to any tank except the Trim Tank. The switch is normally guarded in the CLOSED position and the Aft Transfer Valves are closed. When the TRANSF. VALVE Switch is set to OPEN, the Aft Transfer Valves open, if at least one main pump is selected ON. The fuel feed line is then connected to the refuel gallery.

HIGH LEVEL TEST Pushbutton Switch When the High Level Test PB Sw is pressed, all HIGH LEVEL and OVERFLOW lights indicate the opposite of the current condition, if their circuits and sensors are serviceable. Also, the FQI indicator shows 8s, CKPT and END lights come on. NOTE:

This test has to be performed before any refuel or defuel operation.

Optional REFUEL Pusbutton Switch An optional REFUEL PB Sw. can be installed in the cockpit on the overhead panel. However various options exist for additional control panels. The FCMC is able to handle up to 3 Refuel panels per aircraft.

POWER SUPPLY Switch The Power Supply Switch is normally guarded in the NORM position. In this position, refueling and defueling operations are powered by external power connected or APU generator on line. If the Power Supply Switch is in the BAT position, the refueling and defueling operations are powered by batteries 1 and 2.

Page 118

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

OPTIONAL REFUEL PUSHBUTTON SW.

285VU

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

REFUEL OFF DEFUEL

L INR TK

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

990VU

Page 119 Figure 61

Refuel/Defuel Panel

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340−200/300 28−25

SYSTEM DESCRIPTION Refuel The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel or defuel is controlled from a refuel control panel in the RH lower belly fairing. There is a refuel/defuel coupling (installed in the leading edge of the LH and RH wing) that is the interface between the refuel/defuel system and the external fuel source. Each refuel/defuel couplingcan have two refuel/defuel hoses connected to it. There are two different procedures to refuel the aircraft. These are: S the Pressure Refuel (Automatic or Manual) S the Overwing Refuel To fill the fuel tanks to their maximum capacity, the aircraft must be at the usual ground attitude datum. With a refuel supply pressure at 50 PSI from four fuel hoses, the minimum time to pressure refuel the aircraft (from the usual reserves to maximum capacity) is approximately 33 minutes Defuel There are two procedures to defuel the aircraft. These are: S the Pressure Defuel (the aircraft fuel−pumps supply the fuel pressure for the defuel) S the Suction Defuel (the external defuel source supplies the suction to remove the fuel). Refuel Gallery The refueling gallery consists of the distribution manifold with a fuel inlet valve for each of the tanks. The interface between the refueler and the refueling gallery are the Refuel/Defuel Isolation Valves in the L/H and the R/H wing. These valves are controlled to open through the FCMC if there is no refueling shut down signal during refueling. A Manual Override Button allows the valve to open, if the computer signal is not present. Fuel pressure actuates the valves to the open position.

Page 120 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340−200/300 28−25

REFUEL GALLERY

CENTER TANK

PRESS SWITCH

TRANSFER PUMP

TRIM TANKRESTRICTOR

REFUEL GALLERY REFUEL ISOLATION VALVE M REFUEL / DEFUEL

S M

COUPLING

M

M

OVERWING

EMERGENCY

REFUEL CAP

TRIM PIPE

ISOLATION

ISOL VALVE

M

M

CENTER

INNER TANK

TANK INLET

INLET VALVE

VALVE DEPRESSURIZING

M

VALVE INNER TANK

AUX FWD

CENTER TANK

INLET VALVE

TRANSFER

RESTRICTOR

VALVE

VALVE

VALVE

M SURGE PRESSURE RELIEF VALVE

TRIM TANK ISOL VALVE

OUTER TANK INLET VALVE DIFFUSERS

TRIM TANK INLET VALVE

M M

Page 121 Figure 62 Refuel System Schematic FRA US-T SHM 13.12.2007

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

SYSTEM LOCATION Overwing Refueling Each inner tank has an overwing refuel adaptor. This can be used to refuel the aircraft when a pressure refuel source is not available. The fuel only goes into the inner tank. Then it is necessary to do a ground fuel transfer to get the fuel into the correct fuel−load configuration. The adaptor has an overwing refuel cap which gives access to and seals the adaptor. The refuel adaptor and cap is installed in the upper wing surface with an electrical ground point adjacent to it. Refuel Adapter The refuel/defuel coupling is the interface between the aircraft refuel/defuel system and the external fuel supply. It is attached to the forward face of the wing front spar. Access to the refuel/defuel coupling is through a hinged door in the bottom of the leading edge. Each refuel/defuel coupling has two valve heads. Thus as many as four hoses can be connected to the aircraft at the same time. Each refuel adaptor has a refuel coupling cap. The refuel isolation valve controls the fuel supply from the refuel source to the refuel gallery. The valve is electrically controlled, but hydraulically operated. Thus when the valve is energized and a refuel pressure is supplied the isolation valve opens. The isolation valve has a manual override−button. If the valve does not open electrically, the manual override−button can be used to open the valve. The valve is installed in the center of each refuel/defuel coupling.

Isolation Valve The isolation valve assembly is installed in the center of the refuel/defuel coupling. The (de−energized) solenoid valve uses fuel (which is behind the piston) to make a hydraulic−lock. This hydraulic−lock and the compression springs hold the piston in the closed position. When the solenoid valve energizes, the hydraulic−lock is released. The fuel pressure then pushes the piston (against the spring pressure) to the open position. The fuel that made the hydraulic−lock is pushed through the discharge valve and into the refuel gallery. The manual command button (on the front of the valve body) connects directly to the manual command valve. If the solenoid valve does not operate, the manual command button can be pushed in (and held) to release the hydraulic−lock. The isolation valve then operates as usual. During a suction defuel the suction pressure opens the drain valve. This lets fuel drain from the second chamber and the piston chamber. The suction then opens the valve against the spring pressure. Only one of the two adaptors gives the suction pressure for the drain valve. Thus, if only one adaptor is used for a suction defuel, it must be the one marked USE THIS ADAPTOR TO DEFUEL.

Page 122 FRA US/T SHM 13.12.2007

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

NOTE: ON SOME AIRPLANE REFUELING STATION ONLY ON ONE SIDE

MANUAL OVERRIDE BUTTON

HINGED ACCESS PANEL

OVERWING REFUEL CAP ISOLATION SOLENOID

O-RING SEAL

COUPLING CAP

REFUEL ADAPTER

ADAPTER NUT

Page 123 Figure 63 Refuel/Overwing Adapter FRA US/T SHM 13.12.2007

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

COMPONENT DESCRIPTION Refuel Gallery Pressure Switch During a refuel, the refuel−gallery low−pressure switch (53QU) monitors the fuel pressure in the refuel gallery. If the pressure in the refuel gallery decreases to below a specified limit, the pressure switch will operate. This causes the trim tank isolation function to operate and isolates the trim pipe. The APU forward fuel pump then supplies the APU with fuel from the left inner tank through the APU isolation valve. The pressure switch is attached to the rear face of the rear spar. Tank Inlet Valve The tank inlet valves are the interface between the refuel gallery and the tank. Its primary function is to control the flow of fuel from the refuel gallery into any fuel tank. But during a suction defuel it also controls the fuel flow out of the tanks. The valves are installed: S on the wing front spar S on the wing rear spar S on the center box rear spar. The valve has a valve spindle which goes through the front or rear spar to engage with the electrical actuator. The actuator attaches to the rear face of the rear spar. When energized it moves the inlet valve to the open or the closed position. Center Tank Restrictor Valve (A340/A330−200 only) The center−tank refuel restrictor valve is located immediately downstream of the center−tank inlet valve. Its function is to prevent an overpressure of the center tank structure during a refuel. The valve is installed in the center tank and attaches to the forward face of the rear spar.

Page 124 FRA US/T SHM 13.12.2007

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FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

ELECTRICAL CONNECTOR POSITION INDICATOR SPLINED SHAFT

WING SPAR

REFUEL GALLERY PRESS SWITCH

C

C DUMMY O

O CENTER BOX

OPEN POSITION

CONNECTOR

CLOSED POSITION

REAR SPAR

INLET VALVE DEACTIVATION TOOL

Page 125 Figure 64 Inlet Valve, Deactivation Tool, Gallery Pressure Switch FRA US/T SHM 13.12.2007

Lufthansa Technical Training

SERVICING REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

REFUELING FUNCTION WARNING: S S S

S

OBEY THE FUEL SAFETY PROCEDURES. THIS CAN PREVENT INJURY AND DAMAGE. Make sure that the ACCU PRESS on the triple indicator has sufficiant pressure. If necessary, pressurize the Blue hydraulic system. Make sure that the PARK BRAKE is ON. Make sure that the chocks are in position as follows: − Move the aft NLG chocks away from the tires. During the refuel the NLG tires roll aft as the MLG shock absorber compresses. − Make sure that the chocks do not touch the MLG tires. The weight of the fuel can lower the aircraft and cause the tires to catch the chocks. − Do not put chocks at the CLG tires. Make sure that a fuel sampling for water contamination check is done to the fuel in the fuel tanker/pump unit.

Aircraft Maintenance Configuration

WARNING:

MAKE SURE THAT YOU GROUND THE FUEL TANKER AND THE AIRCRAFT CORRECTLY. IF YOU DO NOT A DANGEROUS ELECTRICAL DISCHARGE CAN OCCUR. S Ground the aircraft and the fuel tanker/pump unit. Then bond them together electrically.

NOTE: Bonding is essential, grounding is recommended. S Energize the aircraft electrical circuits S Do the ADIRS start procedure NOTE: S S S S

You can use 1, 2, 3 or 4 refuel hoses to do an automatic pressure refuel. This procedure uses the four refuel hoses. Put 2 access platforms in position, below the access panels. Open the access panels. Remove the refuel/defuel coupling caps. Make sure that the couplings of the fuel supply hoses are clean. Connect the four hoses to the aircraft refuel/defuel couplings.

Page 126 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

SERVICING REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

B B B

A

A

EXTERNAL POWER RECEPTACLE A EXTERNAL POWER RECEPTACLE B

EXT PWR AVAIL light (amber) illuminates, when Ground Power is connected and available

C C

NOSE LANDING GEAR

MAIN LANDING GEAR

C

EXT PWR NOT IN USE light (white) illuminates, when Ground Power is connected but not used

LANDING GEAR

GROUND CABLE

Page 127 Figure 65 External Power Panel; Grounding Points FRA US-T SHM 13.12.2007

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SERVICING REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

PRESSURE REFUEL WITH AUTOMATIC CONTROL FROM THE REFUEL/DEFUEL PANEL 990VU Job Set Up S Open the access panel. S On the REFUEL/DEFUEL CONTROL PANEL do this test: 1. If only the battery power is available, put the PWR SUPPLY switch to BAT.

2. Start the pump on the fuel tanker/pump unit. 3. At the refuel/defuel control panel : A. Put the MODE SELECT switch to the REFUEL position.

NOTE:

NOTE:

During the first 30 seconds after power−up, the indications at the fuel panel must be ignored. 2. Lift the guard, then push in and hold the HI LEVEL TEST switch : − the CKPT and END lights come on. − the fuel quantity, PRESELECTED and ACTUAL displays show all 8. − the HI−LEVEL lights and the OVERFLOW lights go to the opposite condition. 3. Release (out) the HI−LEVEL TEST switch. Wait for 10 seconds: − the lights go back to their initial condition − the fuel quantity, PRESELECTED and ACTUAL displays go back to their initial condition. Procedure CAUTION:

DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 3.4 BAR (50 PSI). THIS WILL PREVENT DAMAGE TO THE AIRCRAFT FUEL SYSTEM. 1. On the refuel/defuel control panel : A. Put the LOAD switch to the INC position and hold it there. B. Make sure that the numbers on the PRESELECTED display increase. C. When the PRESELECTED display shows the necessary fuel load, release the LOAD switch. D. Make sure that the REFUEL VALVES switches are in the NORM position and guarded. NOTE:

If the following switches ar not in the correct configuration, the END light will flash: S At least on INLET VALVE switches is in OPEN or SHUT position S On the FUEL panel, the CTR TANK XFR PB Sw set to MAN S On the FUEL panel, the T TANK MODE PB Sw set to FWD S On the FUEL panel, the OUTER TK XFR PB Sw set to MAN B. Make sure that the numbers on the fuel quantity and the ACTUAL displays increase.

NOTE:

The refuel times (shown in the illustration) give the estimated time taken (in minutes) to refuel the aircraft from the initial (init) fuel quantity to the preselected fuel quantity. Each refuel-time range given makes an allowance for the densities from 0.76 kg/l to 0.82 kg/l, with a fuel pressure of 3.45 bar (50 psi) at the refuel coupling. C. When the refuel stops, make sure that: S the END light comes on and does not flash S the numbers on the ACTUAL and the PRESELECTED displays are stable and are the same ± 200 kg (± 440.9244 lb). D. Set the MODE SELECT switch to OFF. E. If the power supply is from the battery, put the PWR SUPPLY switch to NORM. 4. Stop the pump on the fuel tanker/pump unit.

If a switch is moved to SHUT during the automatic refuel, the applicable valve closes. if a switch is moved to OPEN during the automatic refuel, the FCMS ignores the command until the automatic refuel is complete. then, after approximately 15 seconds, the refuel will continue (in manual mode) into the applicable tank.

Page 128 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

SERVICING REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

REFUEL OFF DEFUEL

L INR TK

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

990VU

Page 129 Figure 66 Refuel/Defuel Panel FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340−200/300 28−25

Cockpit Refuel Control (optional) An automatic pressure refuel can also be controlled from the cockpit. The MCDU (Ref. 22−82−00) is used to: S set the preselected fuel quantity S do a test of the fuel hi−level sensors. When the cockpit refuel P/BSW 37QU is pushed (in): S the ON light comes on S the ready−to−refuel lights 36QU1(36QU2) at the LH(RH) refuel/defuel coupling come on S the CKPT light on the refuel/defuel panel 990VU comes on. When fuel pressure is available at the refuel/defuel couplings, the automatic pressure refuel starts. The refuel procedure is then as shown for the refuel/defuel panel 990VU. When the refuel is complete, the END light comes on and the ready−to−refuel lights 36QU1(36QU2) at the LH(RH) refuel/defuel coupling go off. The REFUEL P/BSW is then released (out) and: S the ON light goes off S the CKPT light on the refuel/defuel panel 990VU goes off.

Page 130 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340−200/300 28−25

READY TO REFUEL LIGHT ( GREEN )

285VU COCKPIT REFUEL SWITCH ACCESS PANEL

Page 131 Figure 67 Cockpit Refueling FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

PRESSURE REFUEL WITH MANUAL CONTROL FROM THE REFUEL/DEFUEL PANEL 990VU Job Set Up S Refer to Procedure AUTOMATIC CONTROL Procedure CAUTION:

DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 3.4 BAR (50 PSI). THIS WILL PREVENT DAMAGE TO THE AIRCRAFT FUEL SYSTEM. 1. On the refuel/defuel control panel 990VU: A. Put the REFUEL/DEFUEL VALVE switches for the fuel tanks you want to refuel to the OPEN position.

7. Set the MODE SELECT switch to OFF. 8. Put the applicable REFUEL VALVE switches to the NORM position 9. If the power supply is from the battery, put the PWR SUPPLY switch to NORM. 10.Stop the pump on the fuel tanker/pump unit.

NOTE:

To refuel the trim tank, you must have one of these conditions: the two innner tank inlet valves are open the center tank inlet valve is open the two inner tank fuel quantities are above 14000kg one inner tank quantity is above 14000kg and the other inner tank inlet valve is open B. Put the REFUEL/DEFUEL VALVE switches for the tanks you do not want to refuel to the SHUT position. 2. Start the pump on the fuel tanker/pump unit. 3. Put the MODE SELECT switch 3QU to the REFUEL position. 4. Monitor the fuel quantity displays. S S S S

NOTE:

If necessary use the applicable manual refuel distribution graph to make sure that the fuel distribution is correct for flight. 5. If the trim tank is to be refueled, it must be done in two steps: A. When the trim tank fuel quantity reaches 1000kg below that shown on the applicable graph, shut the trim tank inlet valve. B. When the two inner tanks are at the target value open the trim tank inlet valve. 6. When each tank has the correct fuel quantity, put its REFUEL/DEFUEL VALVE switch to the SHUT position NOTE:

Page 132

Each tank quantity can increase 100kg to 200kg after the REFUEL/DEFUEL VALVE switch is set to SHUT position

FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340-200/300 28−25

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

REFUEL OFF DEFUEL

L INR TK

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

990VU

Page 133 Figure 68 Refuel/Defuel Panel FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330 28−25

PRESSURE DEFUEL DESCRIPTION General The defuel system uses the same fuel valves and fuel lines as the refuel system. The aircraft can be defuelled through one or more of the refuel hose adaptors. But when only one adaptor on a refuel/defuel coupling is used, it must be the one identified USE THIS ADAPTOR TO DEFUEL. In this description, the defuel is through the four adaptors. There are two procedures to defuel the aircraft which are: S the Pressure Defuel S the Suction Defuel The pressure defuel cannot start unless all the wing inlet valves are closed. This prevents the possibility of a tank overflow, because the inner tanks have no fuel hi−level sensor protection during a defuel. It is only possible to pressure defuel the inner and center fuel tanks. To defuel the other fuel tanks, their fuel must first be moved to the center or inner tanks.

Page 134

Wing Tank Pressure Defueling The MODE SELECT switch has to be set to DEFUEL The TRANSF VALVE switch is set to OPEN (which sends a signal to the FCMS) When the main fuel pumps or the stby fuel pumps are set to on, the FCMS opens the aft transfer valves. The FCMS also energizes the refuel isolation valve. The fuel pumps (with the related crossfeed valves open) then push the fuel through the aft transfer valves into the refuel / defuel gallery. From there it goes out of the aircraft to the defueller. The aft transfer valve cannot open unless all these conditions occur: S one or more of the LH (RH) main or standby fuel pumps are in operation S the trim tank is empty S the surge tank fuel−sensors are not wet S the outer−tank inlet valves are closed S the center−tank inlet valve is closed S the inner−tank inlet valves are closed FRA US/T SHM 13.12.2007

When the fuel quantity in an inner tank decreases to 3500 kg the intertank transfer valves automatically open. The fuel in the outer tanks moves to the inner tanks which are subsequently defuelled. To defuel the trim tank during a pressure defuel, it is necessary to set a forward fuel transfer. Thus the fuel from the trim tank goes into the center tank as the fuel in center tank is removed from the aircraft. NOTE:

If a surge tank fuel−sensor becomes wet during the defuel the LH and RH aft transfer valves close.

NOTE:

If the Refuel / Defuel ISOL VALVE is not opened it can be overridden by pressing the MANUAL OVERRIDE BUTTON during defueling!

Center Tank Pressure Defueling (A330−200 Only) The MODE SELECT switch has to be set to DEFUEL The Center Tank transfer pump(s) are set to ON The transfer pumps push the fuel out of the aircraft to the defueller. To defuel the trim tank during a pressure defuel, it is necessary to set a forward fuel transfer. Thus the fuel from the trim tank goes into the center tank as the fuel in center tank is removed from the aircraft.

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330 28−25 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 135 Figure 69 Pressure Defueling A330−200 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330 28−25

SUCTION DEFUEL DESCRIPTION General It is possible to suction defuel all of the fuel tanks. To do this: S the MODE SELECT switch is set to DEFUEL S the necessary fuel−tank inlet valves are set to OPEN The FCMS energizes the refuel isolation solenoid and (when the defueller supplies the suction) the valve opens. The fuel is then removed from the selected fuel tanks (through the refuel diffusers and the open inlet valves). To do a suction defuel it is necessary for the level sense function of the FCMS to be in operation. If the full FCMS is energized it moves the fuel valves to the position shown on the refue / defuel panel (the NORM position closes the valve). NOTE:

If the trim tank contains fuel, then fuel−system interlocks prevent a suction defuel of the inner tanks

Page 136 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330 28−25 LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 137 Figure 70 Suction Defueling A330−200 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

FUEL GROUND TRANSFER DESCRIPTION General It is possible to do a ground transfer from the center or inner tanks to all the tanks (but not usually to the trim tank). The FCMS must be energized. Inner Tank Ground Transfer To do a ground fuel−transfer from the inner tank: S the MODE SELECT switch is set to REFUEL S the TRANSF VALVE switch is set to OPEN S the necessary REFUEL/DEFUEL−VALVES switches are set to OPEN S the MAIN or STBY fuel pumps are set to ON NOTE:

The TRANSF VALVE switch opens the LH aft transfer valve (only if a related stby or main pump is on), and opens the RH transfer valve (only if a related stby or main pump is on). This function prevents a loss of fuel pressure to the APU when it is supplied through the forward APU fuel pump.

Page 138 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL DEFUEL SYSTEM

A330/A340-200/300 28−25

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

L INR TK

REFUEL OFF DEFUEL

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

Page 139 Figure 71 Inner Tank Ground Transfer FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

CENTER TANK GROUND TRANSFER DESCRIPTION To do a ground fuel transfer from the center tank: S the MODE SELECT switch is set to REFUEL S the necessary REFUEL/DEFUEL VALVES switches are set to OPEN S the TRANSF VALVE switch is set to OPEN (the transfer valves do not open, but the inlet valves go into the refuel mode) S the MAIN fuel pumps are set to OFF S the TRANSFER pump(s) are set to ON NOTE:

If fuel remains in the center tank after a maintenance operation, it is recommended that it is transferred to the inner tanks. This will make sure that the fuel is in the correct configuration for an automatic pressure refuel.

Page 140 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM REFUEL/DEFUEL

A330/A340−200/300 28−25

990VU

HIGH LEVEL L OUTR TK

L INR TK

CTR TK

TRIM TK

R INR TK

OVER FLOW R OUTR TK

L

INC

kg

TT

HI LVL TEST

R

TRANSF. VALVE OPEN

X 1000 L INR

CENTRE

R INR

PRESELECTED

LOAD

CKPT END L OUTER

TRIM

R OUTER

ACTUAL

REFUEL-DEFUEL-VALVES MODE SELECTOR

L OUTR TK

L INR TK

REFUEL OFF DEFUEL

CTR TK

R INR TK R OUTR TK

TRIM TK OPEN

DEC

CLOSED

PWR SUPPLY

APU EMERGENCY

NORM

NORM

SHUT DOWN

SHUT BAT

Page 141 Figure 72 Center Tank Ground Transfer FRA US-T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340-200/300 28−40

28−40

FUEL INDICATING

SYSTEM DESCRIPTION The indicating systems are : S the Quantity Indicating System (which gives separate and total fuel quantity indications). S the Manual Magnetic Indicators (a secondary system used to estimate the fuel quantity when the aircraft is on the ground) S the Tank Level Sensing (which gives indications and warnings when the fuel is at given leveis) S the Fuel Temperature Measurement System (which gives continuous temperature indications, and warnings when the fuel temperature is at given levels) Quantity Indicating The fuel quantity indicating system (FQI) measures the total guantity of fuel in the range unusable to overflow. It gives indications for each of these fuel tank / areas : S the LH and RH outer tanks S the Center Tank S the LH and RH inner tanks S the LH and RH collector cells S the trim tank. The FQI has fuel probes with a capacitance that is in proportion to the amount of fuel that touches the probes. The Fuel Control and Monitoring System continuously measures this capacitance and: S transmits the fuel level data to the Engine/Warning Display (EWD) and the System Display (SD) S uses the fuel quantity data to control the fuel system operation The Manual Magnetic Indicators (MMI) are a secondary direct reading system used (only on the ground) to calculate the fuel guantity in the tanks. It is not necessary to have electrical power to use the indicators.

Tank Level Sensing The tank level sensing monitors the fuel level in: S the surge tanks S the outer tanks S the inner tanks S the center tank S trim tank S the trim surge tank The system has level sensors which send fuel level signals to the FCMS. The FCMS uses the fuel level data to: S control the operation of the tank inlet valves during a refuel or a fuel transfer S close the trim tank isolation valve when the trim tank is empty S send fuel level warnings to the EWD Fuel Temperature Measurement The fuel temperature measurement system monitors the temperature of the fuel in : S the LH outer tank S the LH and RH collector cells S the trim tank. The system has temperature sensors of which the electrical resistance changes in proportion to the changes in temperature. The FCMS measures this resistance and transmits the temperature data to the EWD and tbe SD.

Page 142 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340-200/300 28−40

Page 143 Figure 73 Fuel Indication Schematic FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340−200/300 28−40

MANUAL MAGNETIC INDICATORS General The Manual Magnetic Indicators (MMI) are a secondary direct reading system used to calculate the fuel quantity on ground. They are installed in: S the inner tanks S the outer tanks It is not necessary to have electrical power to use the MMIs. Each MMI has a magnetic level indicator (MLI). The MLI is a glass reinforced plastic rod which has marks to show the fuel level. A set of mathematical tables is used to make the fuel quantity calculation. These connect together: S the MLI indication S the aircraft attitude S the specific gravity of the fuel NOTE:

To calculate the quantity in the trim tank the tank must be emptied to the inners.

Page 144 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340−200/300 28−40

FUEL TANK TOP SKIN

FLOAT

TUBE

TANK FUEL LEVEL INDICATION

MLI ROD

MLI ROD

HOUSING LOCKED POSITION

FUEL TANK BOTTOM SKIN

Page 145 Figure 74 Manual Magnetic Indicators FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340-200/300 28−40

SYSTEM DESCRIPTION General All the wing Manual Magnetic Indicators (MMIs) are installed in the bottom surface of the fuel tank. Access to the MLI is from below the wing. An attitude monitor is installed in the aircraft fuselage. The MMIs are installed as follows: S five in each inner tank S three in each outer tank. The assembly of each MLI housing is almost the same, but the angle of th body mounting flanges (and the length of their tubes) are different. The end cap prevents a fuel leakage when the MLI is in use or removed. The body is attached to the other end of the tube and connects the MLI-housing to the fuel tank. The float assembly (which contains a magnet) is free to move up and down the outside of the tube. The MLI-housing (which fully contains the MLI) has a bayonet−type recess into which the MLI bayonetlock engages. Attitude Monitor The attitude monitor is a circular level with graduations on the surface. Each square of the grid is equal to 0.5 ° change of attitude. The position of the bubble in relation to the grid gives the aircraft attitude. NOTE: In case of a failed Attitude Monitor the Pitch and Roll position readout can be taken from the SPECIFIC DATA pages through the MCDU from the FCMCs or with the ACMC Alpha Callup Menü. AIRCRAFT ATTITUDE CONVERSION TABLE Pitch Ref Roll minus2.5 1 minus 1.5 minus2.0 2 minus 1.0 minus1.5 3 minus 0.5 minus1.0 4 0.0 minus0.5 5 plus 0.5 0.0 6 plus 1.0

Ref A B C D E F

Page 146 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM INDICATING

A330/A340-200/300 28−40

STICK HEIGHT ATTITUDE MONITOR READING PITCH ROLL 1 A 1 B 1 C 1 1 1 1 2 2 2 2 2 2 2 3 3 3 3 3 3 3

4 4 4 4 4 4 4 5 5 5 5 5 5 5

6 6 6 6 6 6 6 7 7 7 7 7 7 7

D E F G G F E D

C B A A B C D E F G G F E D

C B A A B C

60

62

64

66

68

6010

6320

5880 5770 5660 5560 5470 5380 5280 5370 5460 5560 5670 5780

6190

6640 6500 6360 6240

6970 6820 6670 6540 6420 6300 6200

7310 7150

72

74

76

78

8020 7830 7650 7490 7340 7200 7070 6980

8380

8750 8540 8340

9130 8910

8160

8510

LITERS

5910

5820 5690 5570 5470 5370 5280

6060 5940 5840 5740 5640 5550 5640 5740 5850 5960 6090 6220 6130

6120

6020 5920 5820 5920 6030 6140

6270 6400 6550 6450 6310 6170

5280 5380 5480 5600 5720 5630

5990 5860 5750 5650 5550 5460 5370 5460 5560 5660 5780 5900 6040 5950

5510

5810

6120

5390 5290

5990 5870 5750 5650 5550 5470 5560 5670 5780 5900 6040

5190 5100 5190

C B A A B C

5310

5420 5550 5470 5340 5230

5690 5570 5470 5370 5280 5200 5290 5380 5490 5600 5730 5860 5780 5640 5520

D E F G

5120

5410

5020 4850 4940

5300

D E F G G F E D

70

5190 5100

5020 4930 5020 5110

5200

5110

5200

6050 5930 5830 5730 5640 5740 5840 5960 6080 6210

6360 6270

6180 6100

5960 5820 5700 5580 5380 5480

6100 6210

6320 6440 6580 6720 6880 6780 6630 6480 6350 6230 6110 6010

5920 6020 6130

6260 6390 6530 6690 6600 6450 6300 6170

6050 5930 5830 5740 5850 5960 6080 6210

6360 6520 6430 6280

6990 6850 6720 6600 6480 6390 6500 6620 6750 6900 7050 7220 7120

6950 6800 6660 6530

7660 7480 7320 7170

7030 6900 6770 6680 6800 6930 7070 7220 7390 7560 7470 7290 7120

6980 6840

6410

6710

6290 6200

6580 6490

6310

6610

6440 6570

6740 6880 7040 7200 7380 7290

6710

6860 7030 6940 6770 6620 6480 6350 6220 6110

6030 6140

6260 6390 6530 6690 6860 6780 6610

6130

6450

6000 5870 5660 5760

6310 6170

5940 6050

7110

6950 6790 6650 6520 6400 6320 6440 6570 6710

6860 7030 7210 7130

6950 6780 6630 6480 6230 6350

7110

7250 7400 7560 7730 7920 7830 7640 7460 7300 7150 7010

6880 6790 6920 7060 7210

7370 7550 7740 7650 7460 7280 7120

6970 6830 6700 6620 6740 6880 7030 7200 7380 7570 7490 7290 7110

6950 6800 6530 6660

8180

7990 7820 7660 7520 7380 7280 7420 7570 7730 7900 8080 8290 8190

7990 7800 7630 7470 7330 7190 7100

7230 7380 7540 7710

7900 8110

8020 7820 7630 7450 7290 7150 7010

6920 7060 7210

7370 7540 7730 7940 7860 7650 7460 7290 7120

6840 6980

7990 7840 7690 7600 7740 7900 8070 8250 8440 8660 8570 8350

8700

7920 8070 8240

7880 8070 8270 8480 8400 8180

7980 7800 7630 7470 7320 7240 7380 7540 7710

7900 8100

8140

7980 7820 7730 7890 8050 8230 8430 8640 8870 8790 8550 8340

2

1:

IRS−1

)

1:

2

1:

−0.917

0.148

L6

R2

0.181

*####

R3

L4

L5

R1

−0.950

R4

#####

#####

#####

#####

#####

#####

#####

#####


SCRATCHPAD

PRINT*

R5

R6

7960 7800 7640 7560 7710

7880 8060 8260 8470 8710

7810

8180

7630 7450

7980 7790 7470 7630

7300

*ROLL (DEGS

1:

IRS−1

)

8150

8320 8240 8020

7150

*PTCH (DEGS

L3

8320

7710

L1

9040 8950 8720 8510

7560

ALPHA SOURCE POS

L2

7970 7800 7650 7500

1/8

ALPHA CALL−UP

8410 8610 8810

8150

7410

ACMS

8330 8170 8010

8630 8390

ATTITUDE MONITOR

Page 147 Figure 75 MMI Table and Attitude Monitor FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM LEVEL SENSING

A330/A340−200/300 28−46

28−46

TANK LEVEL SENSING

DESCRIPTION The tank level sensing systern monitors the level of fuel in: S the LH (RH) Surge Tank S the LH (RH) Outer Tank S the LH (RH) Inner Tank S the Center Tank S the Trim Tank S the Trim Surge Tank. The system has level sensors which send fuel level signals to the Fuel Control and Monitoring System (FCMS). The FCMS uses the fuel level data to: S control the operation of transfer pumps when the center tank is at lo−level S stop a fuel jettison (if an inner tank lo−level sensor becomes dry) S control the operation of the refuel restrictor valve during a refuel S control the operation of the emergency isolation valves during a refuel S close the trim−tank isolation valve when the trim tank is empty S transmit fuel level warnings to the Engine/Warning Display (EWD) The tank level sensing system has sensors which are installed in the tanks as follows: Hi−Level Sensors: S two in the outer tank S two in the inner tank S two in the center tank S two in the trim tank Lo−Level Sensors: S two in the inner tank S one in the center tank S one in the trim tank Overflow Sensor: S one in the wing surge tank

Hi Level Sensing The Outer, Inner and Trim fuel tanks each have a pair of hi−level sensors which are installed at the same height in the tank. When the two hi−level sensors in a fuel tank become wet: S the FCMS closes the related tank inlet valve The Center Tank has two hi−level sensors. During a refuel, when the first hi−level sensor becomes wet: S the FCMS closes the Center Tank Restrictor Valve When the second hi−level sensor becomes wet: S the FCMS closes the Center Tank Inlet Valve Lo Level Sensing The lo−level sensor in the center tank is installed near to the lowest point in the tank. When the sensor has been dry for more than 3 minutes: S the FCMS stops the Tansfer Pumps The lo−level sensors in the inner tank are installed at a height which is approximately equal to a fuel quantity of 2700 kg in each inner tank. If the two sensors in one of the inner tanks are dry (for more than 30 seconds) S the FCMS sends a warning to the ECAM S the FCMS stops a Jettison System operation When the trim tank the lo−level sensor has been dry for 1 minute: S the FCMS sends a warning to the ECAM S the FCMS closes the Trim Tank Isolation Valve Overflow Level Sensing The overflow sensors are installed in the surge tanks near to the lowest point in the tank. If an overflow sensor becomes wet during a refuel: S the FCMS closes all the (open) Inlet Valves and the Refuel/Defuel Isolation Valves

Page 148 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM LEVEL SENSING

A330/A340−200/300 28−46

SENSOR

SENSOR

LO-LEVEL

HI-LEVEL

SENSOR HI-LEVEL LEVEL SENSOR EXAMPLE INSTALLATION

SENSOR LO-LEVEL SENSOR

SENSOR LO-LEVEL

HI-LEVEL

SENSOR

SENSOR

HI-LEVEL

HI-LEVEL

SENSOR SURGE TANK OVERFLOW

SENSOR SURGE TANK OVERFLOW

Page 149 Figure 76 Tank Level Sensing Schematic FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM LEVEL SENSING

A330/A340−200/300 28−46

Etops-Sensor (A330 only) The ETOPS warning sensors in the inner tank are installed at a height which is equal to a fuel quantity that is sufficient for 180 minutes flying. When this sensor is dry, the FCMS sends a warning to the ECAM.

Page 150 FRA US-T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM LEVEL SENSING

A330/A340−200/300 28−46 SENSOR LO−LEVEL GROUP A

SENSOR LO−LEVEL GROUP B

STA0/RIB1

64QJ 1(64QJ2) SENSOR ETOPS WARNING

SENSOR HI−LEVEL GROUP A

STA1144/RIB17

SENSOR HI−LEVEL GROUP B

SENSOR HI−LEVEL GROUP A

SENSOR HI−LEVEL GROUP B

STA2000/RIB30 STA2316/RIB35 SENSOR SURGE TANK OVERFLOW LH WING SHOWN RH WING OPPOSITE HAND

Page 151 Figure 77 Etops Sensor (A330 only) FRA US-T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM TEMPERATURE MEASUREMENT

A330/A340-200/300 28−49

28−49

TEMPERATURE MEASUREMENT

SYSTEM DESCRIPTION General The fuel-temperature measurerment system uses temperature sensors to monitor the temperature of the fuel in: S the LH outer tank S the LH and RH inner tank S the trim tank. The electrical resistance of the temperature sensors changes in proportion to the changes in temperature. The Fuel Control and Monitoring System FCMS measures this change in resistance and: S transmits the temperature data to the EWD and the SD Description The fuel temperature measurement system has these components: S the LH Outer Tank Temperature Sensor S the LH (RH) Collector Cell Temperature Sensors S the Trim Tank Temperature Sensor Each temperature sensor is installed near to the lowest part of the tank. This makes sure that the temperature sensor is kept in the fuel for most of the time.

Operation The temperature sensor unit has: S a body S two temperature sensors The FCMS monitors the temperature of the fuel continuously. If the temperature increases or decreases to a given value a warning is given in the cockpit. The warning is given at the advisory limit and is shown again at the warning limit. SENSOR

ADVISORY

WARNING

OUTER TANK

−40 _ C

−47 _ C

TRIM TANK

−40 _ C

−47 _ C

INNER TANK ENG FEED

−35 _ C

−42 _ C

INNER TANK JET A

+40 _ C

+59.5 _ C

NOTE: When the fuel quantity for the LH outer tank is below 11OO kg or the trim tank is below 1OOOkg S the related tank fuel temperature data is not shown on the SD S there are no advisory or warning messages given for those tanks.

Page 152 FRA US/T SHM 13.12.2007

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FUEL SYSTEM TEMPERATURE MEASUREMENT

A330/A340-200/300 28−49

SENSOR HIGH TEMPERATURE

SENSOR LOW TEMPERATURE INNER TANK

TRIM TANK SENSOR LOW TEMPERATURE

SENSOR INSTALLATION EXAMPLE

OUTER TANK

Page 153 Figure 78 Fuel Temperature Measurement Schematic FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

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FUEL SYSTEM JETTISON SYSTEM

A330 28−30

28−30

JETTISON SYSTEM (OPTIONAL ON A330−200)

SYSTEM DESCRIPTION The jettison system makes it possible to discard some of the aircraft fuel in flight. The crew manually start the operation of the jettison system from the cockpit. The jettison system has two jettison valves. They are identified as: S the LH Fuel Jettison Valve with its actuator S the RH Fuel Jettison Valve with its actuator The activated system continues until one of these conditions occur: S the crew stops the operation S the Fuel Control and Monitoring System stops the operation at a pre−set jettison final gross weight S the total fuel quantity in the two inner tanks is less than 10000 kg S the two lo−Level sensors in one of the inner tanks become dry Operation of the jettison system also causes a forward fuel−transfer to occur. The jettison system output−rate is approximately 1150 kg per minute. The jettison valve is installed in a fuel line from the refuel gallery. The valve controls the flow of fuel from the refuel gallery to the jettison pipe. The valve is installed in the inner tank and is attached to the bottom skin. When the valve opens, the all fuel pumps remove fuel from the Center and Inner tanks. The fuel then goes through the jettison valve, the jettison pipe and overboard.

Page 154 FRA US/T SHM 13.12.2007

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FUEL SYSTEM JETTISON SYSTEM

A330 28−30

LH INNER TANK FWD SECTION

RH INNER TANK FWD SECTION

CENTER TANK

ENGINE

ENGINE

2

1 X-FEED VLV ENG 2 FUEL LP VLV

ENG 1 FUEL LP VLV AFT X-FER VALVES APU ISOL VLV

L PUMP 2

LH

RH

L PUMP 1

R PUMP 1 APU FWD PUMP

R PUMP 2 R STBY

L STBY LH INNER TK INLET VLV

LH EMER ISOL VLV

CTR TK INLET VLV

RH INNER TK INLET VLV

RH EMER ISOL VLV

CTR TK INL RESTR. VLV REFUEL ISOL VLV LH LH OUTER TK INLET VLV

LH X-FER PUMP

JETTISON VLV LH

AUX FWD X-FER VLV

REFUEL ISOL VLV RH

RH X-FER PUMP

TRIM PIPE ISOL VLV

LH INNER TANK AFT SECTION

LH INTERTANK X-FER VLV

APU AFT PUMP

LH OUTER TANK

RH OUTER TK INLET VLV

JETTISON VLV RH

RH INNER TANK AFT SECTION TRIM TK X-FER PUMP APU LP VLV

RH INTERTANK X-FER VLV

RH OUTER TANK

TRIM TK ISOL VLV TRIM TK INLET VLV

APU

TRIM TANK

Page 155 Figure 79 Jettison System Schematic (A330−200 only) FRA US/T SHM 13.12.2007

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FUEL SYSTEM JETTISON SYSTEM

A330/A340-200/300 28−30

SYSTEM OPERATION The jettison system operation can only be started manually, but it can be stopped manually or automatically. Jettison System set to ON When the two jettison P/BSWs are set to ON: S the two Jettison Valves open S the two Transfer Pumps supply fuel from the center tank (if fuel is in the center tank) S if open, the Trim Pipe Isolation Valve and all the fuel tank Inlet Valves (but not Trim Tank Inlet) close S the two Aft Transfer Valves open S all the Crossfeed Valves open (A340 only) S all the Main and Standby Pumps supply fuel from the inner tanks S it starts a forward transfer into the center tank NOTE:

The standby pumps and the crossfeed valves stay in the jettison mode until one or the two jettison P/BSWs are released out. The fuel (from the inner and center tanks) then flows through the jettison valves, the jettison pipe in the No. 4 flaptrack fairing and overboard.

Jettison System Manually Set to Off When the JETTISON ARM P/BSW or the JETTISON ACTIVE P/BSW is set to OFF it closes: S the LH jettison valve S the RH jettison valve Fuel Quantity stops the Jettison System Operation The crew can set an jettison final gross weight (JFGW) at which the operation of the jettison system automatically stops. The crew sets the necessary gross weight on the MCDU and then sets the two JETTISON P/BSWs to ON. The jettison system will continue to discard fuel until the aircraft weight is the same as the jettison final gross weight set (or until a different jettison−stop condition occurs). Fuel Level stops the Jettison System Operation The fuel level sensing system stops a jettison operation: S if a fuel quantity is not set or S one of the two JETTISON P/BSWs is not set to off. S When one of the lo−level sensors (in the inner tank) becomes dry it closes the jettison valves. Jettison Valve Actuator Each actuator is attached to the drive assembly of the jettison valve (below the inner tank) with a V−band clamp. Thus you do not have to go into the fuel tank to replace the actuator. The interface between the actuator and its jettison valve is a valve spindle that goes through the fuel tank bottom−skin.

Page 156 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM JETTISON SYSTEM

A330/A340-200/300 28−30

JETTISON VALVE DEACTIVATION

OUTBOARD

FUEL

FLAP

OUT JETTISON VALVE

JETTISON PIPE DUMMY PLUG FLAP TRACK 4

(WITH SHUNT) DRIVE ASSEMBLY

O-RING JETTISON VALVE FUEL TANK V- CLAMP

SKIN DOWEL

VALVE LOCKING TOOL

ELECTRICAL

LOCK-KEY

ACTUATOR

Page 157 Figure 80 Jettison Components FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330/A340

Fuel

28−00 FUEL SYSTEM 28−51 FCMC 28−11 TANKS 28−22 APU FEED SYSTEM 28−21 ENGINE FEED SYSTEM 28−23 CROSSFEED SYSTEM 28−26 MAIN TRANSFER SYSTEM 28−11 FUEL ISOLATION 28−27 TRIM TANK TRANSFER 28−17 WATER SCAVENGE 28−25 REFUEL/DEFUEL SYSTEM 28−40 FUEL INDICATING 28−46 TANK LEVEL SENSING 28−49 TEMPERATURE MEASUREMENT 28−30 JETTISON SYSTEM (OPTIONAL ON... 28−50 CONTROL AND MONITORING

Lufthansa Technical Training

FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

28−50

CONTROL AND MONITORING

FCMC EXTERNAL INTERFACES On Board Maintenance System (OMS) The On Board Maintenance System is in constant relation with all aircraft systems. Each FCMC is only connected to Central Maintenance Computer 1, although on separate ARINC 429 buses. However, if CMC 1 fails, data will be received from CMC 2 via CMC 1 and the source will be transparent to the FCMS. The ARINC inputs from the CMCs are the Universal Time Correlation, Flight Phase, Aircraft Configuration, Date and Aircraft Identification. ARINC outputs to the CMCs are LRU Identification and Maintenance Information. Flight Management Guidance And Envelope Computer (FMGEC) The Auto Flight System sends ARINC data. Each FMGEC sends a discrete input of an Aft CG Target Forward signal. The FMGEC sends Zero Fuel Weight, Aircraft Gross Weight, Aircraft Longitudinal Center of Gravity, Zero Fuel Center of Gravity, Preselected Fuel Quantity and remaining time to destination. Air Data And Inertial Reference System (ADIRS) The Air Data and Inertial Reference System transmits altitude and accelerations by ARINC busses. The Air Data and Inertial Reference System transmits the Barometric Altitude, the Longitudinal, Lateral and Normal Accelerations. Flight Control Data Concentrator (FCDC) The Flight Control Data Concentrators send the Horizontal Tailplane Angle data.

Flight Warning Computer (FWC) Fuel System warnings are sent through ARINC busses to the Flight Warning Computers. Display Management Computer (DMC) ECAM FUEL Indications are displayed through the Display Management Computers. Aircraft Condition Monitoring System (ACMS) Fuel parameters are transmitted to the Aircraft Condition Monitoring System. Slat Flap Control Computer (SFCC) Each Slat Flap Control Computer inputs two discrete signals. The two SFCC input signals are the Slat/Flap Lever Position (retracted or not) and Slats extended or not. Landing Gear Control And Interface Unit (LGCIU) The two Landing Gear Control and Interface Units transmit two discrete signals. A third discrete input comes from the Landing Gear Position Lever. The LGCIU inputs are : − LH Main Landing Gear locked down, − Nose Gear compressed. Electronic Control Box (ECB) An APU fuel command discrete signal is received from the Electronic Control Box when fuel is required. The FCMCs receive APU Pumps Low Pressure signals.

Weight And Balance System (WBS) The Weight and Balance System can input the Aircraft Gross Weight and the Aircraft Longitudinal Center of Gravity. (The Weight and Balance System is an option.)

Page 158 FRA US/T SHM 13.12.2007

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FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

Page 159 Figure 81 FCMC External Interfaces FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

FCMC BITE TEST General Each FCMC has hardware and software that together give the FCMC Built In Test Equipment BITE. The BITE has these functions: S continuously monitor the FCMC and fuel system components for failure S to do a BITE system test S to do a Valve Test S to do a Level Sense Test The FCMC supplies data to the CMCs. The CMCs are the interface between the FCMC-BITE and the MCDU. Fuel Valve Test The FUEL VALVE TEST gives the maintenance the ability to transfer fuel in all tanks. Thus carefully notice the CAUTION page to be aware of the transfer condition. In order to abort the test press RETURN, and all tested valves will go to their failsafe CLOSED position. When the Trim Tank is to be filled notice the safety graph what gives the maximum allowable Trim Tank Quantity. Each valve has two Lines on the FUEL VALVES TEST page. The second Line aligns with the function keys to give SHUT and OPEN seLections. The valve conditions can be: S OPEN S SHUT S FAIL OPEN S FAIL UNKNOWN S FAIL SHUT S ABNORMAL The valve test function is not available during an aircraft refuel operation.

FUEL IN WING TANK

FUEL LOADS WINGS TO TRIM TANK

50000kg

40000kg

30000kg

20000kg

10000kg

0

1000kg

2000kg

3000kg

4000kg

4800kg

FUEL IN TRIM TANK

Page 160 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

MAIN MENU FCMC 1

LAST LEG

FCMC 1

CLASS 3

FUEL VALVE TEST

FAULTS>


CAUTION

SYSTEM

PREVIOUS LEGS

TESTS>


FUEL VALVE


TEST>

1

OPERATION OF THESE VALVES MAY CAUSE THE AIRCRAFT TO JETTISON FUEL OR OVERBALANCE

LEVEL SENSE

TEST> TROUBLE SHOOT

CONTINUE*

2

GROUND


REPORT> INPUT



PARAMETERS>

FCMC 1

FCMC 1

1/6

FUEL VALVE TEST

1/6

FUEL VALVE TEST

*SHUT

VALVE DESCRIPTION STATE

OPEN*

*SHUT

VALVE DESCRIPTION STATE

OPEN*

*SHUT

VALVE DESCRIPTION STATE

OPEN*

*SHUT

VALVE DESCRIPTION STATE

OPEN*


PRINT*

3 TEST IN PROGRESS

PRINT*


PRINT*

Page 161 Figure 82 FCMC Fuel Valve Test FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

Input Parameters If this selection is made on the MCDU the page shows the external input values stored in the FCMC. These inputs are: S probe capacitances S fuel permittivities S fuel densities S fuel temperatures S effective surface attitude (pitch and roll provided by ADIRUs) S discrete inputs (including level sensor conditions) NOTE:

The page which is shown on the MCDU gets an automatic update every 5 sec. If a parameter is not available it is replaced with a dash (–) character.

Page 162 FRA US/T SHM 13.12.2007

Lufthansa Technical Training

FUEL SYSTEM CONTROL AND MONITORING

A330/A340-200/300 28−50

EXAMPLE PAGE 4

2 LAST LEG



FCMC 1

FCMC 1

CLASS 3

FAULTS> TANK

PITCH

L OUTR

−01.32

00.20

L INR

−01.32

00.20

COLL 1

−01.32

00.20

COLL 2

−01.32

00.20

LEVEL SENSE

COLL 3

−01.32

00.20

TEST>

COLL 4

−01.32

00.20

R INR

−01.32

00.20

R OUTR

−01.32

00.20

SYSTEM

TESTS> FUEL VALVE


TROUBLE SHOOT


4/10

INPUT PARAMETER

TEST>

GROUND

REPORT> INPUT

1

PARAMETERS>


ROLL

PRINT*

EXAMPLE PAGE 9

3 FCMC 1

9/10

INPUT PARAMETER FCMS DISCRETE INPUTS ABCDEFGHJKLMNPQRSTV 1

0 0 0 0 0 0 0

2

0 0 0 0 0 0 0 0 0 0

3

1 1 1 1 1 1 1

4

1 1 1 1 1 1 1 1 1 1 1 1

5 6

1 1 1 1 1 1 1 1 1 1 1 1 1 1 0 − 0 − 1 1

7

1 1 1 1 1

8

0 0 0 0 0 0 1 1


PRINT*

Page 163 Figure 83 FCMC Input Parameters FRA US/T SHM 13.12.2007

Lufthansa Technical Training

A330 28 L3

TABLE OF CONTENTS ATA 28 FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1

28−23

CROSSFEED SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . COMPONENT DESCRIPTION . . . . . . . . . . . . . . . . . . . . . .

66 66 68

28−26

MAIN TRANSFER SYSTEM . . . . . . . . . . . . . . . . . . . . . . . GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAIN TRANSFER DESCRIPTION A330−200 . . . . . . . . . MAIN TRANSFER DESCRIPTION A330−300 . . . . . . . . . MAIN TRANSFER COMPONENTS . . . . . . . . . . . . . . . . . .

70 70 74 78 82

28−11

FUEL ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . .

86 86

28−27

TRIM TANK TRANSFER . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIM TANK TRANSFER OPERATION . . . . . . . . . . . . . . . FORWARD TRANSFER OPERATION A330−200 . . . . . FORWARD TRANSFER OPERATION A330−300 . . . . . TRIM TANK TRANSFER COMPONENTS . . . . . . . . . . . .

88 88 92 94 100 108 112

28−17

WATER SCAVENGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . .

114 114

28−25

REFUEL/DEFUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . REFUEL/DEFUEL PANEL CONTROLS . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPONENT DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . REFUELING FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . . PRESSURE DEFUEL DESCRIPTION . . . . . . . . . . . . . . . SUCTION DEFUEL DESCRIPTION . . . . . . . . . . . . . . . . . FUEL GROUND TRANSFER DESCRIPTION . . . . . . . . . CENTER TANK GROUND TRANSFER DESCRIPTION

116 116 120 122 124 126 134 136 138 140

28−40

FUEL INDICATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . .

142 142 146

28-00

FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL LAYOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 2

28−00

FUEL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL LAYOUT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TANK DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISTRIBUTION DESCRIPTION . . . . . . . . . . . . . . . . . . . . A330−200 DISTRIBUTION SCHEMATIC . . . . . . . . . . . . . CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM FUEL PAGE INDICATION A330−300 . . . . . . . . . .

4 4 6 8 10 12 16

28−51

FCMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . .

24 24 26

28−11

TANKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TANK DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TANK VENTING LAYOUT . . . . . . . . . . . . . . . . . . . . . . . . . . VENTILATION FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . CENTER TANK BOX VENTING/DRAINING A330−300 . WING TANK WATER DRAIN DESCRIPTION . . . . . . . . . TRIM TANK WATER DRAIN DESCRIPTION . . . . . . . . . . TRIM PIPE SHROUD DRAIN DESCRIPTION . . . . . . . . .

30 30 32 34 40 42 44 46

28−22

APU FEED SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . APU FUEL FEED COMPONENT LOCATION . . . . . . . . . APU FUEL PURGING FUNCTION . . . . . . . . . . . . . . . . . . TRIM TRANSFER LINE DAMAGE OPERATION . . . . . . APU FUEL FEED OPERATION . . . . . . . . . . . . . . . . . . . . .

48 48 50 52 54 56

28−21

ENGINE FEED SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE FEEDING COMPONENT LOCATION . . . . . . . ENG LP FUEL SHUTTOFF VALVE DESCRIPTION . . . .

58 58 60 64

Page i

A330 28 L3

TABLE OF CONTENTS 28−46

TANK LEVEL SENSING . . . . . . . . . . . . . . . . . . . . . . . . . . . DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

148 148

28−49

TEMPERATURE MEASUREMENT . . . . . . . . . . . . . . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . .

152 152

28−30

JETTISON SYSTEM (OPTIONAL ON A330−200) . . . . . SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . SYSTEM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . .

154 154 156

28−50

CONTROL AND MONITORING . . . . . . . . . . . . . . . . . . . . FCMC EXTERNAL INTERFACES . . . . . . . . . . . . . . . . . . . FCMC BITE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

158 158 160

Page ii

TABLE OF FIGURES Figure 1 Figure 2 Figure 3 Figure 4 Figure 5 Figure 6 Figure 7 Figure 8 Figure 9 Figure 10 Figure 11 Figure 12 Figure 13 Figure 14 Figure 15 Figure 16 Figure 17 Figure 18 Figure 19 Figure 20 Figure 21 Figure 22 Figure 23 Figure 24 Figure 25 Figure 26 Figure 27 Figure 28 Figure 29 Figure 30 Figure 31 Figure 32 Figure 33 Figure 34 Figure 35

Fuel Tanks and Feed Concept . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Tanks and Fuel Management Concept . . . . . . . . . . . . . . . . Fuel Tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel System Basic Schematic A330−300 . . . . . . . . . . . . . . . . . . Fuel System Basic Schematic A330−200 . . . . . . . . . . . . . . . . . . Cockpit Fuel Panel A330−300 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Fuel Panel A330−200 . . . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM Fuel Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM LP Fuel VLV and Crossfeed VLV . . . . . . . . . . . . . . . . . . . ECAM Pumps and Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM Transfers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM TT and APU Indication . . . . . . . . . . . . . . . . . . . . . . . . . . ECAM Quantity and Temperatures . . . . . . . . . . . . . . . . . . . . . . ECAM CG and Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . FCMC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FCMS Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Changeover FCMC1 - 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tank Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tank Venting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Surge Tank Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wing/Trim Tank Ventilation Components . . . . . . . . . . . . . . . . . Center Tank Vent Components . . . . . . . . . . . . . . . . . . . . . . . . . . Center Box Venting and Draining (A330−300) . . . . . . . . . . . . . Wing Tank Water Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trim Tank Water Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trim Pipe Shroud Drain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APU Fuel Feed Schematic A330−200 . . . . . . . . . . . . . . . . . . . . APU Fuel Feed Components . . . . . . . . . . . . . . . . . . . . . . . . . . . APU Purging Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Schematic Trim Tank Transfer Line . . . . . . . . . . . . . . . . . . . . . . Engine Feed System Schematic . . . . . . . . . . . . . . . . . . . . . . . . Main Fuel Pump/Pressure Switch . . . . . . . . . . . . . . . . . . . . . . . Jet Pump, Air Release Valve, Thermal Relief Valve . . . . . . . . LP Valve Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Crossfeed System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . .

3 5 7 9 11 13 15 17 18 19 20 21 22 23 25 27 29 31 33 35 37 39 41 43 45 47 49 51 53 55 59 61 63 65 67

Figure 36 Figure 37 Figure 38 Figure 39 Figure 40 Figure 41 Figure 42 Figure 43 Figure 44 Figure 45 Figure 46 Figure 47 Figure 48 Figure 49 Figure 50 Figure 51 Figure 52 Figure 53 Figure 54 Figure 55 Figure 56 Figure 57 Figure 58 Figure 59 Figure 60 Figure 61 Figure 62 Figure 63 Figure 64 Figure 65 Figure 66 Figure 67 Figure 68 Figure 69 Figure 70

APUCheck Valve, Crossfeed Actuator . . . . . . . . . . . . . . . . . . . Center to Inner Transfer (Auto Mode) . . . . . . . . . . . . . . . . . . . . Outer to Inner (Auto Mode) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Center to Inner Transfer (Manual Mode) . . . . . . . . . . . . . . . . . . Outer to Inner (Manual Mode) . . . . . . . . . . . . . . . . . . . . . . . . . . . Outer to Inner Autotransfer A330−300 . . . . . . . . . . . . . . . . . . . Outer to Inner Manual Transfer A330−300 . . . . . . . . . . . . . . . . Inner Tank Inlet Valve, Pressure Switch, Transfer Pump . . . . Intertank Transfer Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Emergency Isolation Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trim Transfer Overview A330−200 . . . . . . . . . . . . . . . . . . . . . . . Trim Transfer Overview A330−300 . . . . . . . . . . . . . . . . . . . . . . . Trim Transfer Logic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aft Transfer from Centertank A330−200 . . . . . . . . . . . . . . . . . . Aft Transfer from Inner A330−200 . . . . . . . . . . . . . . . . . . . . . . . Aft Transfer A330−300 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fwd Transfer (Center Tank) . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fwd Transfer (Inner Tanks) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fwd Transfer (FWD P/B Pushed) . . . . . . . . . . . . . . . . . . . . . . . . Fwd Transfer (Feeding Switch to open) . . . . . . . . . . . . . . . . . . FWD Trim Transfer A330−300 . . . . . . . . . . . . . . . . . . . . . . . . . . FWD Trim Transfer Override A330−300 . . . . . . . . . . . . . . . . . . Trim Tank Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Water Scavenge Components . . . . . . . . . . . . . . . . . . . . . . . . . . Refuel/Defuel Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refuel/Defuel Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refuel System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refuel/Overwing Adapter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inlet Valve, Deactivation Tool, Gallery Pressure Switch . . . . . External Power Panel; Grounding Points . . . . . . . . . . . . . . . . . Refuel/Defuel Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Refueling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Refuel/Defuel Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pressure Defueling A330−200 . . . . . . . . . . . . . . . . . . . . . . . . . . Suction Defueling A330−200 . . . . . . . . . . . . . . . . . . . . . . . . . . . .

69 71 73 75 77 79 81 83 85 87 89 91 93 95 97 99 101 103 105 107 109 111 113 115 117 119 121 123 125 127 129 131 133 135 137

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TABLE OF FIGURES Figure 71 Figure 72 Figure 73 Figure 74 Figure 75 Figure 76 Figure 77 Figure 78 Figure 79 Figure 80 Figure 81 Figure 82 Figure 83

Inner Tank Ground Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . Center Tank Ground Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Indication Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual Magnetic Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . MMI Table and Attitude Monitor . . . . . . . . . . . . . . . . . . . . . . . . . Tank Level Sensing Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . Etops Sensor (A330 only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Temperature Measurement Schematic . . . . . . . . . . . . . . . Jettison System Schematic (A330−200 only) . . . . . . . . . . . . . . Jettison Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FCMC External Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FCMC Fuel Valve Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FCMC Input Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

139 141 143 145 147 149 151 153 155 157 159 161 163

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