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Feb 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 216
ALL
FUEL TRANSFER OPERATION
TMUFUES01-P03 LEVEL 3
EFFECTIVITY 28-25-00 Page 7
Feb 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 217
ALL
THIS PAGE INTENTIONALLY LEFT BLANK
TMUFUES01 LEVEL 3
EFFECTIVITY 28-25-00 Page 8
Feb 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 218
ALL
28 - FUEL SYSTEM
28-25-00 REFUEL AND DEFUEL SYSTEM
COMPONENTS
CONTENTS:
Coupling
Diffuser
Fuel Drain Valve
Center Tank Pressure Relief Valve
Spill Pipe Check Valve
Refuel Valve
Refuel Valve Canister
Defuel/Transfer Valve
Defuel/Transfer Valve Actuator
Air Inlet Valve
TMUFUEM01 LEVEL 3
EFFECTIVITY 28-25-00 Page 1
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 219
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS
WARNING: BEFORE YOU REFUEL OR DEFUEL THE AIRCRAFT YOU
MUST MAKE THE AREA AROUND IT SAFE.
IN THE SAFETY AREA DO NOT:
- SMOKE
- MAKE SPARKS OR FIRE
- USE EQUIPMENT WHICH IS NOT APPROVED FOR
REFUEL/DEFUEL PROCEDURES.
AIRCRAFT FUEL IS FLAMMABLE.
COUPLING
IDENTIFICATION
FIN: 40QM (100QM), 41QM (101QM)
LOCATION:
ZONE: 620 (520)
COMPONENT DESCRIPTION
The standard 2.5 inch single pressure refuel coupling
is positioned beneath the RH wing leading edge. When
not in use the coupling is fitted with a pressure
blanking cap (41QM). * A refuel coupling is also fitted
(optional) on the LH wing leading edge.
TMUFUEM01-T01 LEVEL 3
EFFECTIVITY 28-25-00 Page 2
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 220
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS - COUPLING
TMUFUEM01-P01 LEVEL 3
EFFECTIVITY 28-25-00 Page 3
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 221
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS
DIFFUSER
IDENTIFICATION
FIN: None
LOCATION:
ZONE: 540, 640, 142
COMPONENT DESCRIPTION
Fuel from the branch line ejects from the trough and
is deflected by the baffle across the floor of the
tank, with a minimum of turbulence and electrostatic
build up.
TMUFUEM01-T02 LEVEL 3
EFFECTIVITY 28-25-00 Page 4
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 222
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS - DIFFUSER
TMUFUEM01-P02 LEVEL 3
EFFECTIVITY 28-25-00 Page 5
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 223
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS
FUEL DRAIN VALVE
IDENTIFICATION
FIN: 31QM, 32QM
LOCATION:
ZONE: 540, 640
COMPONENT DESCRIPTION
The fuel drain valve allows fuel to drain from the
refuel line into each wing tank except under
refuel/defuel pressure.
TMUFUEM01-T03 LEVEL 3
EFFECTIVITY 28-25-00 Page 6
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 224
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS - FUEL DRAIN VALVE
TMUFUEM01-P03 LEVEL 3
EFFECTIVITY 28-25-00 Page 7
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 225
ALL
REFUEL AND DEFUEL SYSTEM COMPONENTS
CTR TK PRESSURE RELIEF VALVE
IDENTIFICATION
FIN: 97QM
LOCATION:
ZONE: 142
COMPONENT DESCRIPTION
Removal/Installation:
- empty Center and RH wing tanks,
- open manhole covers 148AZ and 640AB.
The pressure relief valve relieves fuel into the RH
wing tank in the event of a center tank refuelling
overflow.
TMUFUEM01-T04 LEVEL 3
EFFECTIVITY 28-25-00 Page 8
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
　
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