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EFFECTIVITY 01-00-00 Page 6
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
EFFECTIVITY Page 12
ALL
01 - GENERAL
01-00-00 AIRCRAFT DIMENSIONS
CONTENTS:
Lateral View
Top View
Front View
Door Heights
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EFFECTIVITY 01-00-00 Page 1
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
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TMUGENA02-P01 LEVEL 1
AIRCRAFT DIMENSIONS (LATERAL VIEW)
EFFECTIVITY 01-00-00 Page 2
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
EFFECTIVITY Page 14
ALL
AIRCRAFT DIMENSIONS (TOP VIEW)
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EFFECTIVITY 01-00-00 Page 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
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EFFECTIVITY Page 15
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TMUGENA02-P03 LEVEL 1
AIRCRAFT DIMENSIONS (FRONT VIEW)
EFFECTIVITY 01-00-00 Page 4
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
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AIRCRAFT DIMENSIONS (DOOR HEIGHTS)
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EFFECTIVITY 01-00-00 Page 5
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UF94200
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UF94200
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51 - STRUCTURE
51-00-00 - A320 STRUCTURE GENERAL
CONTENTS:
Metallic Materials
Composite Materials
Aircraft Drainage
Surface Pretreatment
Paint System
No Step Areas
Jacking Points
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
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EFFECTIVITY Page 19
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A320 STRUCTURE GENERAL
METALLIC MATERIALS
The basic aircraft structure is made of aluminium
alloys with stainless steel and titanium alloys in
specific areas.
COMPOSITE MATERIALS
Composite materials are used for primary and secondary
structure.
Composite materials represents about 15% of the
aircraft structural weight. CFRP is mainly used for
primary structures, whilst AFRP and GFRP are only used
for secondary structures.
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MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
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A320 STRUCTURE GENERAL
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EFFECTIVITY 51-00-00 Page 3
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MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
EFFECTIVITY Page 21
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A320 STRUCTURE GENERAL
AIRCRAFT DRAINAGE
Wings and fuselage are equipped with different types
of drains.
Holes and gaps are provided to ensure natural drainage
of the fluid collection points. Drain holes are drilled
before application of pretreatments. Remote drains are
used when natural drainage is not possible.
SURFACE PRETREATMENT
The protection of the structure against corrosion is
achieved by means of appropriate surface pretreatment
of the metallic parts.
Aluminium Alloys :
The primary protection is generally a pure aluminium
cladding. The main pretreatment used is the unsealed
chromic acid anodizing (CAA).
Titanium Alloys :
Surface interfaying with aluminium alloy parts are
zinc sprayed. The other titanium alloy surfaces are
left bare.
Titanium fasteners are either sulphuric acid anodized
or aluminium coated.
Composite materials are left bare.
TMUST0101-T02 LEVEL 1
EFFECTIVITY 51-00-00 Page 4
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
EFFECTIVITY Page 22
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A320 STRUCTURE GENERAL
TMUST0101-P02 LEVEL 1
EFFECTIVITY 51-00-00 Page 5
Dec 31/95
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
UF94200
EFFECTIVITY Page 23
　
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