A380
TECHNICAL TRAINING MANUAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent
900)
LEVEL I - ATA 28 Fuel
This document must be used for training purposes only
Under no circumstances should this document be used as a reference
It will not be updated.
All rights reserved
No part of this manual may be reproduced in any form,
by photostat, microfilm, retrieval system, or any other means,
without the prior written permission of AIRBUS S.A.S.
AIRBUS Environmental Recommendation
Please consider your environmental responsability before printing this document.
A380 TECHNICAL TRAINING MANUAL
LEVEL I - ATA 28 FUEL
LAY08521 - L1AT4T0
Fuel System Introduction (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
Fuel Storage Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
Engine Feed Presentation (Me) (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
Engine Feed Presentation (US) (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
APU Fuel System Presentation (Me) (1) . . . . . . . . . . . . . . . . . . . . . . 30
APU Fuel System Presentation (US) (1) . . . . . . . . . . . . . . . . . . . . . . 34
Fuel Transfers Presentation (Me) (1) . . . . . . . . . . . . . . . . . . . . . . . . . 38
Fuel Transfers Presentation (US) (1) . . . . . . . . . . . . . . . . . . . . . . . . . 42
Refuel Defuel System Presentation (Me) (1) . . . . . . . . . . . . . . . . . . . 46
Refuel Defuel System Presentation (US) (1) . . . . . . . . . . . . . . . . . . . 52
Jettison System Presentation (Me) (1) . . . . . . . . . . . . . . . . . . . . . . . . 58
Jettison System Presentation (US) (1) . . . . . . . . . . . . . . . . . . . . . . . . 62
Fuel Quantity Management System Presentation (Me) (1) . . . . . . . . 66
Fuel Quantity Management System Presentation (US) (1) . . . . . . . . 70
Fuel System Maintenance (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
Fuel Tank Safety Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
TABLE OF CONTENTS
Jan 13, 2009
Page 1
A380 TECHNICAL TRAINING MANUAL
FUEL SYSTEM INTRODUCTION (1)
General
LAY08521 - L1AT4T0 - LM28Z1000000001
The fuel system comprises different sub-systems, which are:
- storage,
- engine feed,
- APU fuel,
- fuel transfers,
- refuel/defuel,
- jettison,
- and fuel quantity management.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL SYSTEM INTRODUCTION (1)
Jan 13, 2009
Page 2
LAY08521 - L1AT4T0 - LM28Z1000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL SYSTEM INTRODUCTION (1)
Jan 13, 2009
Page 3
A380 TECHNICAL TRAINING MANUAL
FUEL STORAGE PRESENTATION (1)
General
LAY08521 - L1AT4T0 - LM28P1000000001
The main function of the storage system is to safely store the fuel, which
supplies the engines and APU.
The storage system contains fuel in tanks and safely lets the fuel thermally
expand.
It regulates tank air pressure.
It also gives protection against fire and means to collect condensed water
from the fuel tanks.
On the aircraft, fuel is stored in eleven fuel tanks.
In the wings there are:
- the feed tanks 1 and 2 (LH) and 3 and 4 (RH),
- the LH and RH inner tanks,
- the LH and RH mid tanks,
- the LH and RH outer tanks.
In the Trimmable Horizontal Stabilizer (THS) is the trim tank.
In each wing there is a surge tank and a vent tank. These tanks are used
for temporary storage of any fuel that overflows from the wing tanks and
for wing tank air venting.
On the right hand side of the THS there is a vent/surge tank. This tank
is used for temporary storage of the fuel that overflows from the trim
tank and for trim tank air venting.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 4
LAY08521 - L1AT4T0 - LM28P1000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 5
A380 TECHNICAL TRAINING MANUAL
FUEL STORAGE PRESENTATION (1)
Fuel Tanks
LAY08521 - L1AT4T0 - LM28P1000000001
The feed tanks are used to supply fuel to the engines. They have one
closed area called the collector cell, which is a reservoir for the engine
fuel feed pumps. A dedicated jet pump is used to keep the collector cell
full. All other fuel tanks are storage and transfer tanks.
Access to the tanks is gained through manhole panels. Each tank has one
or more water drain valves.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 6
LAY08521 - L1AT4T0 - LM28P1000000001
A380 TECHNICAL TRAINING MANUAL
FUEL TANKS
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 7
A380 TECHNICAL TRAINING MANUAL
FUEL STORAGE PRESENTATION (1)
LAY08521 - L1AT4T0 - LM28P1000000001
Venting System
The tank venting system keeps the air pressure in the fuel tanks near to
the external air pressure.
The tank venting system prevents abnormal differential pressure, which
could damage the fuel tank/aircraft structure.
This function is especially necessary during the refuel or defuel operations
and when the aircraft climbs or descends.
This system also gives all means to safely discharge from the aircraft,
any fuel overflowing from the fuel tanks.
The tank venting system is a fully automatic mechanical system. There
are no manual controls and no electrical components.
WING TANKS
Each wing fuel tank is individually connected to the surge tank by internal
vent pipes. The surge tank is connected to a vent tank, which is connected
to the atmosphere through a NACA intake and flame arrestor.
The collector cells in the engine feed tanks are vented into the feed tanks
through holes located at the top of the cells.
TRIM TANK
The trim tank is connected to a vent/surge tank by internal vent pipes.
The vent/surge tank is connected to the atmosphere through a NACA
intake and flame arrestor.
Vent protectors (flame arrestors) prevent the ignition of the fuel vapor
in the wing vent tanks and in the trim vent/surge tank in case of external
fire. If abnormal condition occurs in the fuel system, which causes large
quantities of fuel to enter the vent tank or the vent/surge tank, then the
vent protectors let the fuel flow freely overboard.
Overpressure protectors located in the vent tanks or the vent/surge tank,
makes sure that the pressure in the vent tanks, or the vent/surge tank, and
thus the fuel tanks, does not exceed the design limits.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 8
LAY08521 - L1AT4T0 - LM28P1000000001
A380 TECHNICAL TRAINING MANUAL
VENTING SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL STORAGE PRESENTATION (1)
Jan 13, 2009
Page 9
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P2000000001
The engine feed system makes sure that the fuel is supplied to all the
engines during all flight conditions and can be isolated from one or more
engines, when necessary.
The engine feed fuel pump system comprises four independent parts, one
per engine. Under normal operation, each part supplies the fuel from its
related feed tank to the associated engine.
The crossfeed system can interconnect each part of the engine feed pump
system.
The engine Low-Pressure (LP) shut-off system lets each engine be isolated
or shut-off from the engine feed system.
These operations are controlled from the cockpit integrated control panels
and the related information is shown on the ECAM FUEL page of the
System Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 10
LAY08521 - L1AT4T0 - LM28P2000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 11
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (ME) (1)
Engine Feed Fuel Pump
LAY08521 - L1AT4T0 - LM28P2000000001
For each part of the engine fuel feed system, there are two fuel pumps
installed in each feed tank collector cell, one main pump and one standby
pump. Each pump has a pressure switch to monitor the output fuel
pressure.
Each fuel pump system is usually manually controlled from the P/BSWs
on the overhead-integrated control panel 1235 VM. When the main pump
is in low-pressure condition, the related standby pump automatically
starts.
Engine feed information is shown on the ECAM FUEL page of the SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 12
LAY08521 - L1AT4T0 - LM28P2000000001
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED FUEL PUMP
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 13
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (ME) (1)
Crossfeed System
LAY08521 - L1AT4T0 - LM28P2000000001
The crossfeed system enables any engine to be fed from any engine feed
tank. It can be also used to correct fuel imbalance between tanks, in case
of emergency condition or for maintenance purpose.
The crossfeed system has four crossfeed valves, which are normally
closed. When a crossfeed valve is open, the related fuel feed is available
in a common fuel gallery between all the four valves. If a second crossfeed
valve is opened, the two fuel feed systems are connected together.
The crossfeed valves can be manually controlled by the four P/BSWs
identified on the overhead-integrated control panel 1235VM as
CROSSFEED 1 to CROSSFEED 4.
Alternatively, the aircraft wiring automatically controls the crossfeed
valves:
- in the event of an electrical emergency condition,
- by the Fuel Quantity Management System (FQMS) for an automatic
ground transfer.
The crossfeed valve position is shown on the ECAM FUEL page of the
SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 14
LAY08521 - L1AT4T0 - LM28P2000000001
A380 TECHNICAL TRAINING MANUAL
CROSSFEED SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 15
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (ME) (1)
Low-Pressure Shut-Off System
LAY08521 - L1AT4T0 - LM28P2000000001
The engine Low-Pressure shut-off system has one LP valve per engine.
Each valve can be opened or closed using the related ENG MASTER
switch (1125 VU) on the cockpit pedestal.
In case of engine fire, the operation of the engine FIRE P/BSW on the
overhead-integrated control panel 1245 VM, will close the related LP
valve and stop the fuel supply to the engine.
The LP valve position data is shown on the ECAM FUEL page of the
SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 16
LAY08521 - L1AT4T0 - LM28P2000000001
A380 TECHNICAL TRAINING MANUAL
LOW-PRESSURE SHUT-OFF SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 17
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (ME) (1)
Heat Exchanger Fuel System
LAY08521 - L1AT4T0 - LM28P2000000001
The A380 has a pair of Hydraulic Heat Exchangers (HHX), in order to
cool down the high-pressure hydraulic fluid. This system acts as a back-up
only in the event of a failure of the primary air/hydraulic heat exchanger.
A bypass line on the engine fuel feed pipes of the engine 1 and the engine
4, diverts some fuel through the fuel/hydraulic heat exchangers via an
isolation valve and then returns the heated fuel to the related engine feed
tank.
Control of the isolation valve, and thus feed fuel recirculation, is fully
automatic from the FQMS. Recirculation is inhibited when the related
feed tank contains insufficient fuel.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 18
LAY08521 - L1AT4T0 - LM28P2000000001
A380 TECHNICAL TRAINING MANUAL
HEAT EXCHANGER FUEL SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (ME) (1)
Jan 13, 2009
Page 19
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P2000000002
The engine feed system makes sure that the fuel is supplied to all the
engines during all flight conditions and can be isolated from one or more
engines, when necessary.
The engine feed fuel pump system comprises four independent parts, one
per engine. Under normal operation, each part supplies the fuel from its
related feed tank to the associated engine.
The crossfeed system can interconnect each part of the engine feed pump
system.
The engine Low-Pressure (LP) shut-off system lets each engine be isolated
or shut-off from the engine feed system.
These operations are controlled from the cockpit integrated control panels
and the related information is shown on the ECAM FUEL page of the
System Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 20
LAY08521 - L1AT4T0 - LM28P2000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 21
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (US) (1)
Engine Feed Fuel Pump
LAY08521 - L1AT4T0 - LM28P2000000002
For each part of the engine fuel feed system, there are two fuel pumps
installed in each feed tank collector cell, one main pump and one standby
pump. Each pump has a pressure switch to monitor the output fuel
pressure.
Each fuel pump system is usually manually controlled from the P/BSWs
on the overhead-integrated control panel 1235 VM. When the main pump
is in low-pressure condition, the related standby pump automatically
starts.
Engine feed information is shown on the ECAM FUEL page of the SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 22
LAY08521 - L1AT4T0 - LM28P2000000002
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED FUEL PUMP
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 23
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (US) (1)
Crossfeed System
LAY08521 - L1AT4T0 - LM28P2000000002
The crossfeed system enables any engine to be fed from any engine feed
tank. It can be also used to correct fuel imbalance between tanks, in case
of emergency condition or for maintenance purpose.
The crossfeed system has four crossfeed valves, which are normally
closed. When a crossfeed valve is open, the related fuel feed is available
in a common fuel gallery between all the four valves. If a second crossfeed
valve is opened, the two fuel feed systems are connected together.
The crossfeed valves can be manually controlled by the four P/BSWs
identified on the overhead-integrated control panel 1235VM as
CROSSFEED 1 to CROSSFEED 4.
Alternatively, the aircraft wiring automatically controls the crossfeed
valves:
- in the event of an electrical emergency condition,
- by the Fuel Quantity Management System (FQMS) for an automatic
ground transfer.
The crossfeed valve position is shown on the ECAM FUEL page of the
SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 24
LAY08521 - L1AT4T0 - LM28P2000000002
A380 TECHNICAL TRAINING MANUAL
CROSSFEED SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 25
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (US) (1)
Low-Pressure Shut-Off System
LAY08521 - L1AT4T0 - LM28P2000000002
The engine Low-Pressure shut-off system has one LP valve per engine.
Each valve can be opened or closed using the related ENG MASTER
switch (1125 VU) on the cockpit pedestal.
In case of engine fire, the operation of the engine FIRE P/BSW on the
overhead-integrated control panel 1245 VM, will close the related LP
valve and stop the fuel supply to the engine.
The LP valve position data is shown on the ECAM FUEL page of the
SD.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 26
LAY08521 - L1AT4T0 - LM28P2000000002
A380 TECHNICAL TRAINING MANUAL
LOW-PRESSURE SHUT-OFF SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 27
A380 TECHNICAL TRAINING MANUAL
ENGINE FEED PRESENTATION (US) (1)
Heat Exchanger Fuel System
LAY08521 - L1AT4T0 - LM28P2000000002
The A380 has a pair of Hydraulic Heat Exchangers (HHX), in order to
cool down the high-pressure hydraulic fluid. This system acts as a back-up
only in the event of a failure of the primary air/hydraulic heat exchanger.
A bypass line on the engine fuel feed pipes of the engine 1 and the engine
4, diverts some fuel through the fuel/hydraulic heat exchangers via an
isolation valve and then returns the heated fuel to the related engine feed
tank.
Control of the isolation valve, and thus feed fuel recirculation, is fully
automatic from the FQMS. Recirculation is inhibited when the related
feed tank contains insufficient fuel.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 28
LAY08521 - L1AT4T0 - LM28P2000000002
A380 TECHNICAL TRAINING MANUAL
HEAT EXCHANGER FUEL SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
ENGINE FEED PRESENTATION (US) (1)
Jan 13, 2009
Page 29
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P3000000001
The APU fuel system supplies fuel to the Auxiliary Power Unit (APU).
The system comprises a dedicated fuel line connected to the engine 4
fuel feed system of the right wing, two valves and an APU fuel pump.
The APU MASTER SWitch controls the APU fuel supply.
The APU FIRE P/BSW can stop the APU fuel supply.
The APU fuel system status is shown on the ECAM FUEL page of the
System Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 30
LAY08521 - L1AT4T0 - LM28P3000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 31
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM PRESENTATION (ME) (1)
APU Fuel system
LAY08521 - L1AT4T0 - LM28P3000000001
Selection of the APU MASTER SWitch on the overhead panel controls
the fuel demand of the APU.
The APU is supplied with fuel from the number 4 engine feed manifold.
If the main or standby engine 4 feed pump is operating, the pressure is
normally sufficient to operate the APU.
However, if the pressure in the fuel line is not sufficient, the APU fuel
pump will start automatically and will supply fuel to the APU.
The APU fuel system has two valves that control the fuel supply to the
APU, the APU pipe isolation valve and the APU Low Pressure (LP)
valve. The APU pipe isolation valve prevents the APU fuel line from
being pressurized when the APU is not in use. The APU LP valve located
at the rear end of the APU fuel feed line isolates the APU from the fuel
supply.
If an emergency situation occurs (APU fire or emergency shut down) or
if the Fuel Quantity Management System (FQMS) detects an APU feed
line damage, the APU fuel pump stops, the APU pipe isolation valve and
the APU LP valve are automatically controlled to the close position.
The ECAM FUEL page of the SD indicates the status of the APU fuel
system.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 32
LAY08521 - L1AT4T0 - LM28P3000000001
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 33
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P3000000002
The APU fuel system supplies fuel to the Auxiliary Power Unit (APU).
The system comprises a dedicated fuel line connected to the engine 4
fuel feed system of the right wing, two valves and an APU fuel pump.
The APU MASTER SWitch controls the APU fuel supply.
The APU FIRE P/BSW can stop the APU fuel supply.
The APU fuel system status is shown on the ECAM FUEL page of the
System Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 34
LAY08521 - L1AT4T0 - LM28P3000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 35
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM PRESENTATION (US) (1)
APU Fuel system
LAY08521 - L1AT4T0 - LM28P3000000002
Selection of the APU MASTER SWitch on the overhead panel controls
the fuel demand of the APU.
The APU is supplied with fuel from the number 4 engine feed manifold.
If the main or standby engine 4 feed pump is operating, the pressure is
normally sufficient to operate the APU.
However, if the pressure in the fuel line is not sufficient, the APU fuel
pump will start automatically and will supply fuel to the APU.
The APU fuel system has two valves that control the fuel supply to the
APU, the APU pipe isolation valve and the APU Low Pressure (LP)
valve. The APU pipe isolation valve prevents the APU fuel line from
being pressurized when the APU is not in use. The APU LP valve located
at the rear end of the APU fuel feed line isolates the APU from the fuel
supply.
If an emergency situation occurs (APU fire or emergency shut down) or
if the Fuel Quantity Management System (FQMS) detects an APU feed
line damage, the APU fuel pump stops, the APU pipe isolation valve and
the APU LP valve are automatically controlled to the close position.
The ECAM FUEL page of the SD indicates the status of the APU fuel
system.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 36
LAY08521 - L1AT4T0 - LM28P3000000002
A380 TECHNICAL TRAINING MANUAL
APU FUEL SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
APU FUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 37
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFERS PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P4000000001
The wing transfer system controls the movement of fuel between wing
fuel tanks.
The trim transfer system controls the longitudinal Center of Gravity (CG)
of the aircraft.
For this function the system moves fuel from the wing tanks to the trim
tank (aft transfer) or from the trim tank to the wing tanks (forward
transfer). Aft transfers are only possible when the aircraft is on the ground.
There are 3 types of transfers:
- main transfers: to supply fuel to the feed tanks,
- load alleviation transfers: to alleviate structural loads in flight or on
ground,
- Center of Gravity (CG) transfers: to control CG and to fulfill longitudinal
aircraft balance.
They are automatically controlled by the Fuel Quantity Management
System (FQMS) but can be manually overridden.
Transfer data is displayed on the ECAM FUEL page of the System
Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (ME) (1)
Jan 13, 2009
Page 38
LAY08521 - L1AT4T0 - LM28P4000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (ME) (1)
Jan 13, 2009
Page 39
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFERS PRESENTATION (ME) (1)
Fuel Transfer Routes
LAY08521 - L1AT4T0 - LM28P4000000001
Wing transfers are done by using the forward gallery (or the aft gallery
in case of failure) transfer pumps, transfer valves and inlet valves.
Trim transfers use the trim pipe and valves to connect to the aft gallery
(or the forward gallery in case of failure).
All transfers are controlled by the FQMS, provided that all transfer pumps
are selected ON, using their related P/BSWs on the overhead-integrated
control panel 1235 VM. Manual override is possible from the FUEL
panel.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (ME) (1)
Jan 13, 2009
Page 40
LAY08521 - L1AT4T0 - LM28P4000000001
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFER ROUTES
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (ME) (1)
Jan 13, 2009
Page 41
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFERS PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P4000000002
The wing transfer system controls the movement of fuel between wing
fuel tanks.
The trim transfer system controls the longitudinal Center of Gravity (CG)
of the aircraft.
For this function the system moves fuel from the wing tanks to the trim
tank (aft transfer) or from the trim tank to the wing tanks (forward
transfer). Aft transfers are only possible when the aircraft is on the ground.
There are 3 types of transfers:
- main transfers: to supply fuel to the feed tanks,
- load alleviation transfers: to alleviate structural loads in flight or on
ground,
- Center of Gravity (CG) transfers: to control CG and to fulfill longitudinal
aircraft balance.
They are automatically controlled by the Fuel Quantity Management
System (FQMS) but can be manually overridden.
Transfer data is displayed on the ECAM FUEL page of the System
Display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (US) (1)
Jan 13, 2009
Page 42
LAY08521 - L1AT4T0 - LM28P4000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (US) (1)
Jan 13, 2009
Page 43
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFERS PRESENTATION (US) (1)
Fuel Transfer Routes
LAY08521 - L1AT4T0 - LM28P4000000002
Wing transfers are done by using the forward gallery (or the aft gallery
in case of failure) transfer pumps, transfer valves and inlet valves.
Trim transfers use the trim pipe and valves to connect to the aft gallery
(or the forward gallery in case of failure).
All transfers are controlled by the FQMS, provided that all transfer pumps
are selected ON, using their related P/BSWs on the overhead-integrated
control panel 1235 VM. Manual override is possible from the FUEL
panel.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (US) (1)
Jan 13, 2009
Page 44
LAY08521 - L1AT4T0 - LM28P4000000002
A380 TECHNICAL TRAINING MANUAL
FUEL TRANSFER ROUTES
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TRANSFERS PRESENTATION (US) (1)
Jan 13, 2009
Page 45
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P5000000001
The refuel/defuel system controls the flow of fuel into or out of the
aircraft.
Two refuel/defuel couplings are installed in the leading edge of each
wing providing an interface between the refuel/defuel system and the
external fuel source.
The refuel/defuel procedures can be initiated and controlled from the
overhead panel in the cockpit or from the Integrated Refuel Panel (IRP)
in the RH lower belly fairing.
The different refuel/defuel system operations are:
- automatic refuel from the cockpit,
- automatic refuel from the IRP,
- manual refuel,
- manual pressure defuel,
- manual suction defuel,
- automatic ground transfer (Center of Gravity control),
- manual ground transfer.
In all modes of operation overbalance and overflow protection is done
by the Fuel Quantity Management System (FQMS).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 46
LAY08521 - L1AT4T0 - LM28P5000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 47
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
LAY08521 - L1AT4T0 - LM28P5000000001
CG Targeting
To do an automatic refuel, the FQMS uses two different control methods:
- CG targeting method, where the FQMS controls fuel loading and
distribution to achieve a specific target aircraft Centre of Gravity (CG),
- single vector method, where the FQMS controls fuel loading and
distribution in accordance with a fixed/predefined sequence.
To refuel to a specific CG target, the actual Zero Fuel Weight (ZFW)
and the Zero Fuel Center of Gravity (ZFCG) values must be entered into
the fuel management function through any of these means by:
- manual entry onboard the aircraft using the Multi-Function Display
(MFD) and Flight Management System (FMS),
- manual entry on board the aircraft using the Onboard Maintenance
Terminal (OMT) or the Onboard Information Terminal (OIT),
- automatic uplink of data from an airline ground terminal using the
Aircraft Communication Addressing and Reporting System (ACARS).
If specific ZFW and ZFCG values are not given, then the aircraft will be
refueled to default values using the single vector method.
During an automatic refuel, the FQMS controls, which tanks receive fuel,
when they receive fuel and the quantity of fuel they receive.
The fuel management function calculates the fuel mass necessary in each
tank to reach the ground CG target.
During a manual refuel, the operator controls the fuel loading and
distribution within the safety limits set by the FQMS.
After refueling, if new or updated ZFW and ZFCG values are entered,
an automatic ground transfer can be done from the cockpit with the AUTO
GND XFR P/BSW.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 48
LAY08521 - L1AT4T0 - LM28P5000000001
A380 TECHNICAL TRAINING MANUAL
CG TARGETING
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 49
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Fuel Routes
LAY08521 - L1AT4T0 - LM28P5000000001
To fill the tanks, the refuel/defuel coupling is connected, via auxiliary
refuel valves to 2 galleries of interconnected pipe-work, the forward
gallery and the aft gallery. The layout of the pipe-work gives two separate
routes into each wing fuel tank.
In each tank, individual branch pipes end by an inlet valve.
The fuel feed system is connected to forward gallery via a transfer/defuel
valve.
The trim pipe is connected to each aft and forward gallery, via a trim
pipe isolation valve. The trim line ends with 2 trim tank inlet valves which
give the only refuel route to the trim tank.
Downstream of each tank inlet valve, the tank piping is connected to a
single or group of refuel diffusers.
All valves are controlled by the FQMS.
To fill the fuel tanks to their maximum capacity, the aircraft must be at
the usual ground attitude datum of level +/- 2 degrees. With four fuel
hoses connected (to the refuel/defuel couplings), the minimum time to
refuel the aircraft (from the tanks empty to the maximum capacity) at a
refuel supply pressure of 2.75 bar (40 psi) is approximately 60 minutes.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 50
LAY08521 - L1AT4T0 - LM28P5000000001
A380 TECHNICAL TRAINING MANUAL
FUEL ROUTES
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 51
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P5000000002
The refuel/defuel system controls the flow of fuel into or out of the
aircraft.
Two refuel/defuel couplings are installed in the leading edge of each
wing providing an interface between the refuel/defuel system and the
external fuel source.
The refuel/defuel procedures can be initiated and controlled from the
overhead panel in the cockpit or from the Integrated Refuel Panel (IRP)
in the RH lower belly fairing.
The different refuel/defuel system operations are:
- automatic refuel from the cockpit,
- automatic refuel from the IRP,
- manual refuel,
- manual pressure defuel,
- manual suction defuel,
- automatic ground transfer (Center of Gravity control),
- manual ground transfer.
In all modes of operation overbalance and overflow protection is done
by the Fuel Quantity Management System (FQMS).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 52
LAY08521 - L1AT4T0 - LM28P5000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 53
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
LAY08521 - L1AT4T0 - LM28P5000000002
CG Targeting
To do an automatic refuel, the FQMS uses two different control methods:
- CG targeting method, where the FQMS controls fuel loading and
distribution to achieve a specific target aircraft Centre of Gravity (CG),
- single vector method, where the FQMS controls fuel loading and
distribution in accordance with a fixed/predefined sequence.
To refuel to a specific CG target, the actual Zero Fuel Weight (ZFW)
and the Zero Fuel Center of Gravity (ZFCG) values must be entered into
the fuel management function through any of these means by:
- manual entry onboard the aircraft using the Multi-Function Display
(MFD) and Flight Management System (FMS),
- manual entry on board the aircraft using the Onboard Maintenance
Terminal (OMT) or the Onboard Information Terminal (OIT),
- automatic uplink of data from an airline ground terminal using the
Aircraft Communication Addressing and Reporting System (ACARS).
If specific ZFW and ZFCG values are not given, then the aircraft will be
refueled to default values using the single vector method.
During an automatic refuel, the FQMS controls, which tanks receive fuel,
when they receive fuel and the quantity of fuel they receive.
The fuel management function calculates the fuel mass necessary in each
tank to reach the ground CG target.
During a manual refuel, the operator controls the fuel loading and
distribution within the safety limits set by the FQMS.
After refueling, if new or updated ZFW and ZFCG values are entered,
an automatic ground transfer can be done from the cockpit with the AUTO
GND XFR P/BSW.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 54
LAY08521 - L1AT4T0 - LM28P5000000002
A380 TECHNICAL TRAINING MANUAL
CG TARGETING
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 55
A380 TECHNICAL TRAINING MANUAL
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Fuel Routes
LAY08521 - L1AT4T0 - LM28P5000000002
To fill the tanks, the refuel/defuel coupling is connected, via auxiliary
refuel valves to 2 galleries of interconnected pipe-work, the forward
gallery and the aft gallery. The layout of the pipe-work gives two separate
routes into each wing fuel tank.
In each tank, individual branch pipes end by an inlet valve.
The fuel feed system is connected to forward gallery via a transfer/defuel
valve.
The trim pipe is connected to each aft and forward gallery, via a trim
pipe isolation valve. The trim line ends with 2 trim tank inlet valves which
give the only refuel route to the trim tank.
Downstream of each tank inlet valve, the tank piping is connected to a
single or group of refuel diffusers.
All valves are controlled by the FQMS.
To fill the fuel tanks to their maximum capacity, the aircraft must be at
the usual ground attitude datum of level +/- 2 degrees. With four fuel
hoses connected (to the refuel/defuel couplings), the minimum time to
refuel the aircraft (from the tanks empty to the maximum capacity) at a
refuel supply pressure of 2.75 bar (40 psi) is approximately 60 minutes.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 56
LAY08521 - L1AT4T0 - LM28P5000000002
A380 TECHNICAL TRAINING MANUAL
FUEL ROUTES
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
REFUEL DEFUEL SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 57
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P6000000001
In case of an emergency situation, the jettison system is used to dump
fuel overboard to decrease the aircraft gross weight before landing. The
jettison system operation can only be initiated manually, but it can be
stopped manually or automatically. It is always under the control of the
Fuel Quantity Management System (FQMS).
Only the fuel in the transfer tanks is jettisoned. There is no fuel jettison
from the feed tanks.
The jettison system data is displayed on the ECAM FUEL page of the
system display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 58
LAY08521 - L1AT4T0 - LM28P6000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 59
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM PRESENTATION (ME) (1)
Jettison System
LAY08521 - L1AT4T0 - LM28P6000000001
Once fuel jettison has been manually initiated by means of two guarded
P/BSWs, ARM and ACTIVE, located on the cockpit overhead panel
1211 VM, operation of the jettison system is automatic. The jettison
valves are controlled by the FQMS via the aircraft wiring. The jettison-rate
is approximately 3300 kg (7275 lb) per minute.
Fuel is simultaneously jettisoned from the outer, mid and inner tanks of
each wing. If there is fuel in the trim tank, a forward fuel transfer occurs.
Up to twelve transfer pumps can be automatically started to supply the
fuel flow from the fuel tanks to the forward and aft galleries. The fuel
flows through the galleries, the left and right jettison valves, the jettison
pipes and overboard of each wing.
The system can be manually stopped by the crew through the guarded
P/BSWs, ARM and ACTIVE, or automatically if the FQMS stops the
operation at a pre-set jettison final gross weight.
The jettison system data is displayed on the ECAM FUEL page of the
(SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 60
LAY08521 - L1AT4T0 - LM28P6000000001
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (ME) (1)
Jan 13, 2009
Page 61
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P6000000002
In case of an emergency situation, the jettison system is used to dump
fuel overboard to decrease the aircraft gross weight before landing. The
jettison system operation can only be initiated manually, but it can be
stopped manually or automatically. It is always under the control of the
Fuel Quantity Management System (FQMS).
Only the fuel in the transfer tanks is jettisoned. There is no fuel jettison
from the feed tanks.
The jettison system data is displayed on the ECAM FUEL page of the
system display (SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 62
LAY08521 - L1AT4T0 - LM28P6000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 63
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM PRESENTATION (US) (1)
Jettison System
LAY08521 - L1AT4T0 - LM28P6000000002
Once fuel jettison has been manually initiated by means of two guarded
P/BSWs, ARM and ACTIVE, located on the cockpit overhead panel
1211 VM, operation of the jettison system is automatic. The jettison
valves are controlled by the FQMS via the aircraft wiring. The jettison-rate
is approximately 3300 kg (7275 lbs) per minute.
Fuel is simultaneously jettisoned from the outer, mid and inner tanks of
each wing. If there is fuel in the trim tank, a forward fuel transfer occurs.
Up to twelve transfer pumps can be automatically started to supply the
fuel flow from the fuel tanks to the forward and aft galleries. The fuel
flows through the galleries, the left and right jettison valves, the jettison
pipes and overboard of each wing.
The system can be manually stopped by the crew through the guarded
P/BSWs, ARM and ACTIVE, or automatically if the FQMS stops the
operation at a pre-set jettison final gross weight.
The jettison system data is displayed on the ECAM FUEL page of the
(SD).
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 64
LAY08521 - L1AT4T0 - LM28P6000000002
A380 TECHNICAL TRAINING MANUAL
JETTISON SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
JETTISON SYSTEM PRESENTATION (US) (1)
Jan 13, 2009
Page 65
A380 TECHNICAL TRAINING MANUAL
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME) (1)
General
LAY08521 - L1AT4T0 - LM28P7000000001
The Fuel Quantity Management System (FQMS) automatically controls
and monitors most of the sub-systems of the fuel system. This is achieved
using avionics computing units to acquire system data, do various
computations and generate control and indication signals/data.
The main functions are:
- fuel quantity measurement,
- fuel temperature measurement,
- Centre of Gravity calculation,
- fuel transfer control/management,
- system indications,
- system monitoring and test,
- fault reporting.
These functions are hosted in the system's avionics resources.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME)
(1)
Jan 13, 2009
Page 66
LAY08521 - L1AT4T0 - LM28P7000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME)
(1)
Jan 13, 2009
Page 67
A380 TECHNICAL TRAINING MANUAL
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME) (1)
LAY08521 - L1AT4T0 - LM28P7000000001
FQMS Architecture
The FQMS comprises a number of electronic LRUs/LRMs, fuel system
application software and sensors.
Part of the FQMS application software is installed on two Fuel Quantity
Data Concentrators (FQDCs), the primary part of the software is installed
on four CPIOMs-F.
The FQDCs interface between the system's in-tank sensors and probes,
pumps and valves, and the CPIOMs-F. The following sensors and probes
in the system are:
- capacitance probes, for fuel level measurement,
- Probe Compensators Temperature Units (PCTUs), for fuel permittivity
measurement,
- dual element temperature sensors, for fuel temperature measurement,
- arrangement of a compensator (with single integral temperature sensor)
and a densitometer (with single integral temperature sensor) on a common
back plate named Fuel Properties Measurement Units (FPMUs), for
determination of the characteristics of an uplifted fuel.
The FQMS also includes an Integrated Refuel Panel (IRP), which is used
to control and observe ground operations such as refuel, defuel and ground
transfers.
The FQMS Application Software in the CPIOMs-F is divided into seven
partitions. Each partition is responsible for the realization of certain
FQMS functions. The partitions are split in MONitor and COMmand
partitions.
The COM partitions and their corresponding functions are:
- Measurement: fuel quantity determination, fuel temperature
determination, overflow condition determination and fault
monitoring/reporting,
- Management: management of fuel uplift, fuel transfer between aircraft
tanks, defuel or jettison, generation of pump/valve control stimuli and
fault monitoring/reporting,
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
- CG Measurement: computation of aircraft gross weight, aircraft
longitudinal center of gravity and aft center of gravity target and fault
monitoring/reporting.
The MON partitions and their corresponding functions are:
- Integrity: checking of system computations to ensure safety and high
integrity,
- Monitor: checking of system conditions to detect erroneous
computations,
- CG Measurement: second computation of aircraft gross weight, aircraft
longitudinal center of gravity and aft center of gravity target,
- System BITE: system health determination, side changeover control,
collection of system fault reports, fault isolation and reporting and
management of interactive dialogue with CMS.
The four CPIOMs-F are grouped into pairs to form two computing lanes
or sides. Through the two FQDCs, each side receives, via ARINC 429
communication buses, data from probes and sensors as well as feedback
data from the fuel system's active pumps and valves.
They also receive data from the Integrated Refuel Panel.
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME)
(1)
Jan 13, 2009
Page 68
LAY08521 - L1AT4T0 - LM28P7000000001
A380 TECHNICAL TRAINING MANUAL
FQMS ARCHITECTURE
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (ME)
(1)
Jan 13, 2009
Page 69
A380 TECHNICAL TRAINING MANUAL
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US) (1)
General
LAY08521 - L1AT4T0 - LM28P7000000002
The Fuel Quantity Management System (FQMS) automatically controls
and monitors most of the sub-systems of the fuel system. This is achieved
using avionics computing units to acquire system data, do various
computations and generate control and indication signals/data.
The main functions are:
- fuel quantity measurement
- fuel temperature measurement
- Centre of Gravity calculation
- fuel transfer control/management
- system indications
- system monitoring and test
- fault reporting
These functions are hosted in the system's avionics resources.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US)
(1)
Jan 13, 2009
Page 70
LAY08521 - L1AT4T0 - LM28P7000000002
A380 TECHNICAL TRAINING MANUAL
GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US)
(1)
Jan 13, 2009
Page 71
A380 TECHNICAL TRAINING MANUAL
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US) (1)
LAY08521 - L1AT4T0 - LM28P7000000002
FQMS Architecture
The FQMS comprises a number of electronic LRUs/LRMs, fuel system
application software and sensors.
Part of the FQMS application software is installed on two Fuel Quantity
Data Concentrators (FQDCs), the primary part of the software is installed
on four CPIOMs-F.
The FQDCs interface between the system's in-tank sensors and probes,
pumps and valves, and the CPIOMs-F. The following sensors and probes
in the system are:
- capacitance probes, for fuel level measurement,
- Probe Compensators Temperature Units (PCTUs), for fuel permittivity
measurement,
- dual element temperature sensors, for fuel temperature measurement,
- arrangement of a compensator (with single integral temperature sensor)
and a densitometer (with single integral temperature sensor) on a common
back plate named Fuel Properties Measurement Units (FPMUs), for
determination of the characteristics of an uplifted fuel.
The FQMS also includes an Integrated Refuel Panel (IRP), which is used
to control and observe ground operations such as refuel, defuel and ground
transfers.
The FQMS Application Software in the CPIOMs-F is divided into seven
partitions. Each partition is responsible for the realization of certain
FQMS functions. The partitions are split in MONitor and COMmand
partitions.
The COM partitions and their corresponding functions are:
- Measurement: fuel quantity determination, fuel temperature
determination, overflow condition determination and fault
monitoring/reporting,
- Management: management of fuel uplift, fuel transfer between aircraft
tanks, defuel or jettison, generation of pump/valve control stimuli and
fault monitoring/reporting,
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
- CG Measurement: computation of aircraft gross weight, aircraft
longitudinal center of gravity and aft center of gravity target and fault
monitoring/reporting.
The MON partitions and their corresponding functions are:
- Integrity: checking of system computations to ensure safety and high
integrity,
- Monitor: checking of system conditions to detect erroneous
computations,
- CG Measurement: second computation of aircraft gross weight, aircraft
longitudinal center of gravity and aft center of gravity target,
- System BITE: system health determination, side changeover control,
collection of system fault reports, fault isolation and reporting and
management of interactive dialogue with CMS.
The four CPIOMs-F are grouped into pairs to form two computing lanes
or sides. Through the two FQDCs, each side receives, via ARINC 429
communication buses, data from the two group of probes and sensors as
well as feedback data from the fuel system's active pumps and valves.
They also receive data from the Integrated Refuel Panel.
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US)
(1)
Jan 13, 2009
Page 72
LAY08521 - L1AT4T0 - LM28P7000000002
A380 TECHNICAL TRAINING MANUAL
FQMS ARCHITECTURE
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL QUANTITY MANAGEMENT SYSTEM PRESENTATION (US)
(1)
Jan 13, 2009
Page 73
A380 TECHNICAL TRAINING MANUAL
FUEL SYSTEM MAINTENANCE (1)
LAY08521 - L1AT4T0 - LM28P8MAINT0001
Fuel Safety Items
When you work on aircraft, make sure that you obey all the AMM safety
procedures. This will prevent injury to persons and /or damage to the
aircraft. Here is an overview of main safety precautions relative to the
fuel system.
Make sure that the safety area is clear and clean. Respect the safety
precautions within the safety distances.
During a refueling, the area must be kept clear to let the tanker move
away in an emergency.
Aircraft must not be refueled less than 30 meters (100ft) from radar or
HF radio equipment under test or in operation in the aircraft or ground
installation.
Put the '' NO SMOKING '' warning notices around the work area.
Ground and bond the aircraft.
In the work area:
- do not use any material / tool which may cause sparks,
- use only necessary and approved electrical / electronic equipment,
- make sure the air flow is sufficient to work safely in tanks, otherwise
use a respirator,
- do not pull or move metal objects along the ground,
- immediately flush away or remove any fuel leakage.
Make sure that you have the proper fire fighting equipment available.
The fuel/kerosene is poisonous. Avoid any contact between fuel and your
eyes, mouth, nose, ears or your skin.
Use the approved protective clothing to prevent personal contamination
and formation of static electricity.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL SYSTEM MAINTENANCE (1)
Jan 13, 2009
Page 74
LAY08521 - L1AT4T0 - LM28P8MAINT0001
A380 TECHNICAL TRAINING MANUAL
FUEL SAFETY ITEMS
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL SYSTEM MAINTENANCE (1)
Jan 13, 2009
Page 75
A380 TECHNICAL TRAINING MANUAL
FUEL TANK SAFETY PRESENTATION (1)
General
Following three fuel tank explosions over the past 14 years which resulted
in 346 fatalities, the U.S Department of Transportation's Federal Aviation
Administration (FAA), have introduced new regulations to improve fuel
tank safety.
These regulations relate to the prevention of ignition sources within fuel
tanks of current type certificated aircraft. They require carrying out a
one-time fuel system safety and design review.
LAY08521 - L1AT4T0 - XM28P1000000001
Critical Design Configuration Control Limitations (CDCCL)
The FAA issued Special Federal Aviation Regulation (SFAR) 88
which gives a detailed description of the CDCCL concept.
The DGAC requested the SFAR 88 (TGL 47) to be added to PART
145, PART M and PART 147 to reinforce the application of these
regulations.
This includes:
- a conception part intended to aircraft design features,
- a maintenance part.
A CDCCL is a limitation requirement to preserve a critical ignition
source prevention feature of the fuel system design that is necessary
to prevent the occurrence of an unsafe condition.
The function of the CDCCL is to give instructions to retain the critical
ignition source prevention feature during configuration change that
may be caused by alterations, repairs or maintenance actions.
The aircraft manufacturers have to emit a document to their customers
giving the list of all the maintenance tasks impacted by the CDCCL.
For AIRBUS this document is called the Fuel Airworthiness
Limitations and it is added to the Airworthiness Limitation Section
part 5.
CDCCL items are listed in Airworthiness Limitations Form.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TANK SAFETY PRESENTATION (1)
Dec 20, 2007
Page 76
LAY08521 - L1AT4T0 - XM28P1000000001
A380 TECHNICAL TRAINING MANUAL
GENERAL - CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS (CDCCL)
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TANK SAFETY PRESENTATION (1)
Dec 20, 2007
Page 77
A380 TECHNICAL TRAINING MANUAL
FUEL TANK SAFETY PRESENTATION (1)
Fuel System Design Configuration
LAY08521 - L1AT4T0 - XM28P1000000001
The Airbus aircraft fuel systems have, by design, a number of features
that are intended to protect the system from inadvertent ignition.
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TANK SAFETY PRESENTATION (1)
Dec 20, 2007
Page 78
LAY08521 - L1AT4T0 - XM28P1000000001
A380 TECHNICAL TRAINING MANUAL
FUEL SYSTEM DESIGN CONFIGURATION
GENERAL FAMILIARIZATION COURSE - T4 (RR Trent 900)
LEVEL I - ATA 28 Fuel
FUEL TANK SAFETY PRESENTATION (1)
Dec 20, 2007
Page 79
AIRBUS S.A.S.
31707 BLAGNAC cedex, FRANCE
STM
REFERENCE LAY08521
JANUARY 2009
PRINTED IN FRANCE
AIRBUS S.A.S. 2009
ALL RIGHTS RESERVED
AN EADS COMPANY