A319/A320/A321 TECHNICAL TRAINING MANUAL MECHANICS / ELECTRICS & AVIONICS COURSE 01 GENERAL
This document must be used for training purpose only
Under no circumstances should this document be used as a reference.
It will not be updated.
All rights reserved. No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of Airbus Industrie.
A319/A320/A321 TECHNICAL TRAINING MANUAL _ MECHANICS / ELECTRICS & AVIONICS COURSE
01 GENERAL
01 GENERAL UFD4200
TABLE OF CONTENTS
Page
UFD4200
GENERAL ** Aircraft Dimensions (1) (A320) ................ 1 ** Aircraft Dimensions (1) (A319) ................ 7 ** Aircraft Dimensions (1) (A321)............... 13 ** Structure General (1) ........................ 19 ** Structural Breakdown and Zoning (3) ......... 29 ** Ground Handling (1) .......................... 51 ** Cockpit Presentation (1) ..................... 57 ** Avionics Compartment (1) ..................... 63 ** Cockpit Philosophy (1) ....................... 67 Electrostatic Discharge (3) ..................... 77 Computer R/I (3) ................................. 89 ** Maintenance External Visit (3)............... 91
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01 GENERAL
01 - GENERAL 01-00-00 AIRCRAFT GENERAL
TMUGENA01 LEVEL 3
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CONTENTS : Lateral View Top View Front View Door Heights
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AIRCRAFT GENERAL - LATERAL VIEW EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT GENERAL - TOP VIEW EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
AIRCRAFT GENERAL - FRONT VIEW EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT GENERAL - DOOR HEIGHTS EFFECTIVITY EFFECTIVITY ALL
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01 - GENERAL 01-00-00 AIRCRAFT DIMENSIONS
TMUGENA03 LEVEL 3
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CONTENTS : Lateral View Top View Front View Door Heights
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AIRCRAFT DIMENSIONS - TOP VIEW EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT DIMENSIONS - FRONT VIEW EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT DIMENSIONS - DOOR HEIGHTS EFFECTIVITY EFFECTIVITY ALL
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01 - GENERAL
01-00-00 AIRCRAFT DIMENSIONS
TMUGENA02 LEVEL 1
UFD4200
CONTENTS: Lateral View Top View Front View Door Heights
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AIRCRAFT DIMENSIONS (LATERAL VIEW) EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT DIMENSIONS (TOP VIEW) EFFECTIVITY EFFECTIVITY ALL
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AIRCRAFT DIMENSIONS (DOOR HEIGHTS) EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
51 - STRUCTURE 51-00-00 - A320 STRUCTURE GENERAL
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CONTENTS: Metallic Materials Composite Materials Aircraft Drainage Surface Pretreatment Paint System No Step Areas Jacking Points
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01 GENERAL
METALLIC MATERIALS
COMPOSITE MATERIALS
The basic aircraft structure is made of aluminium alloys with stainless steel and titanium alloys in specific areas.
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.
TMUST0101-T01 LEVEL 1
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A320 STRUCTURE GENERAL
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01 GENERAL
A320 STRUCTURE GENERAL AIRCRAFT DRAINAGE
SURFACE PRETREATMENT
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.
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).
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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.
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01 GENERAL
A320 STRUCTURE GENERAL PAINT SYSTEM
TMUST0101-T03 LEVEL 1
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Before the final paint system, all aluminium parts are primed. The paint system used includes polyurethane primers and paint on the external surfaces, and epoxy primers and polyurethane paint on the internal surfaces. Anti-slip paint is the overwing escape zones.
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01 GENERAL
NO STEP AREAS
JACKING POINTS
Wing and tailplane no step areas. Protective mats are required on the horizontal stabilizer as it is a carbon fiber structure.
There are three jacking points provided. Three jacking points are provided, one below each wing outboard of the pylon and one in front of the nose landing gear bay.
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A320 STRUCTURE GENERAL
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A320 STRUCTURE GENERAL EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
51 - STRUCTURE 51-00-00 A320 STRUCTURAL BREAKDOWN AND ZONING
TMUST0201 LEVEL 1
UFD4200
CONTENTS: Reference Axes ATA Chapters Section Numbers Station Numbers Zone Numbers
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A320 STRUCTURAL BREAKDOWN AND ZONING REFERENCE AXES The structure elements are localized according to the following reference axis.
TMUST0201-T01 LEVEL 1
UFD4200
Note : The reference (station 0) for all structural measurements in the X axis is located 100 in. (254 cm) forward of the aircraft nose. Here is a typical fuselage contour in the Y and Z planes. Section A-A at frame 55. These are the major aircraft reference axis.
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01 GENERAL
ATA CHAPTERS
SECTION NUMBERS
The aircraft structure is divided according to the ATA 100 specifications.
Each major part of the aircraft, corresponding to production receives a section number. The fuselage section base number is 10. The fuselage is divided into various sections for manufacturing reasons.
TMUST0201-T02 LEVEL 1
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A320 STRUCTURAL BREAKDOWN AND ZONING
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A320 STRUCTURAL BREAKDOWN AND ZONING EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING SECTION NUMBERS
TMUST0201-T03 LEVEL 1
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The general wing section base number is 20. The general tail plane section base number is 30.
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A320 STRUCTURAL BREAKDOWN AND ZONING SECTION NUMBERS
TMUST0201-T04 LEVEL 1
UFD4200
The engine sectionbase number is 40. The landing gear section base number is 50. The general belly fairing section base number is 60.
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A320 STRUCTURAL BREAKDOWN AND ZONING STATION NUMBERS The station number is the distance in centimeters of a cross section from a reference point. The station/frame numbers shown correspond to the section boundaries. Here are the engine station numbers. reference
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Note : For the vertical stabilizer the station is z=0 at the VTZ axis.
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A320 STRUCTURAL BREAKDOWN AND ZONING EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING STATION NUMBERS Horizontal stabilizer station numbers. Note : For the horizontal stabilizer the reference station is y=0 at the A/C Y axis. Wings station numbers.
TMUST0201-T06 LEVEL 1
UFD4200
Note : For wings the reference station is wing reference axis (WY). WY is located at 1868 mm (73.54 in) from A/C X axis.
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A320 STRUCTURAL BREAKDOWN AND ZONING EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING ZONE NUMBERS
TMUST0201-T07 LEVEL 1
UFD4200
There are 8 major zones in the aircraft. Each major zone is identified by the first digit of a three digit number. Fuselage and vertical stabilizer zones.
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A320 STRUCTURAL BREAKDOWN AND ZONING EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING ZONE NUMBERS Belly fairing zones. Landing gear zones.
TMUST0201-T08 LEVEL 1
UFD4200
Wings and horizontal stabilizer zones.
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A320 STRUCTURAL BREAKDOWN AND ZONING EFFECTIVITY EFFECTIVITY ALL
51-00-00
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING ZONE NUMBERS Nacelles and pylon zones.
TMUST0201-T09 LEVEL 1
UFD4200
Door zones.
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01 GENERAL
A320 STRUCTURAL BREAKDOWN AND ZONING ZONE NUMBERS
TMUST0201-T10 LEVEL 1
UFD4200
Access doors and panels are identified by the number of the zone in which the panel is located followed by a two-letter suffix which locates it within the zone. Here is an example of access panel doors on the left wing lower surface.
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01 GENERAL
01 - GENERAL 01-00-00 GROUND HANDLING
TMUGENB03 LEVEL 3
UFD4200
CONTENTS : Servicing points A/C Servicing Arrangement 1 Turning Radii
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01 GENERAL
SIMULATOR COCKPIT SAFETY CHECK LIST BEFORE POWER UP
BEFORE LEAVING THE SIMULATOR
1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15.
1. 2. 3. 4. 5. 6. 7. 8.
PLACARDS............................... CHECK CIRCUIT BRAKERS ........................ CHECK BAT 1.2 ...................OFF (CHECK VOLTAGE) FIRE HANDLE (ENGINE/APU) ............ IN/LATCHED WIPERS .................................. OFF LANDING GEAR LEVER ...................... DOWN THRUST LEVERS ..............IDLE/REVERSE STOWED ENGINE MASTER LEVERS...................... OFF ENGINE START ROTARY SELECTOR ........... NORMAL SLAT/FLAPS LEVER ............... CHECK POSITION SPEED BRAKE LEVER .............. CHECK POSITION PARKING BRAKE ............................. ON WEATHER RADAR/ATC TRANSPONDER ............. OFF EXTERNAL POWER (IF AVAILABLE) .............. ON BAT 1.2 .................................. ON
ADIR’S ................................... EXTERIOR LIGHTS ........................... APU BLEED P/B ............................. APU MASTER SW ............................. EMERGENCY EXIT LIGHT....................... CRT’S (ECAM-EFIS) ......................... BAT 1.2 .................................. EXTERNAL POWER ............................
OFF OFF OFF OFF OFF OFF OFF OFF
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AFTER POWER UP 1. 2. 3. 4. 5. 6.
VENT PANEL...................CHECK NO LIGHTS ON PROBE HEAT/WINDOW HEAT.............. AS REQUIRED EXTERIOR LIGHTS .................... AS REQUIRED ANNUNCIATOR LIGHT TEST..................PERFORM FUEL PUMPS................................ OFF LANDING GEARS INDICATION ............ DOWN LOCKED
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01 GENERAL
25 - EQUIPMENT/FURNISHING 25-10-00 COCKPIT PRESENTATION
TMUESCP01 LEVEL 1
UFD4200
CONTENTS: General Overhead Panel Glareshield Main Instrument Panel Center Pedestal Side Consoles
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01 GENERAL
COCKPIT PRESENTATION GENERAL
MAIN INSTRUMENT PANEL
The cockpit is equipped with adjustable seats for two crew members, a third occupant seat and depending of configuration a folding seat for a fourth occupant. Various furnishings and equipment are fitted in the cockpit for the comfort, convenience and safety of the occupants.
Six interchangeable Cathode Ray Tubes are located on the main instrument panel. Two of them are dedicated to the ECAM. The others are two Primary Flight Displays and two Navigation Displays. Stand-by instruments and landing gear controls are also located on the main instrument panel.
OVERHEAD PANEL The controls of most aircraft systems are located on the overhead panel. The overhead panel is divided into two main sections: - a FWD section including the system panels. - an AFT section mainly comprising the circuit breaker panel.
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UFD4200
GLARESHIELD The Flight Control Unit (FCU), includes the Electronic Flight Instrument System (EFIS) controls, and is used for control and monitoring of the Auto Flight System (AFS). It is located on the glareshield. The "Master Caution" and the "Master Warning" lights are also located on the glareshield.
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01 GENERAL
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01 GENERAL
COCKPIT PRESENTATION CENTER PEDESTAL Several control panels are located on the center pedestal as shown on the screen. The mainly control panels are: - thrust levers and thrust reverser levers, - pitch trim wheels, - flaps and slats control, - brakes controls, - MCDUs. SIDE CONSOLES
TMUESCP01-T02 LEVEL 1
UFD4200
The side sticks and nose wheel steering handles are mounted on the side consoles. The side consoles provide documentation stowage, oxygen masks and communication devices.
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01 GENERAL
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UFD4200
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01 GENERAL
31 - INDICATING/RECORDING SYSTEMS 31-16-00 AVIONICS COMPARTMENT
TMUEIAC03 LEVEL 1
UFD4200
CONTENTS: Description
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01 GENERAL
AVIONICS COMPARTMENT DESCRIPTION
TMUEIAC03-T01 LEVEL 1
UFD4200
The electronic avionics compartment is located below the cockpit and cabin floors. It includes: - the electronic racks (90VU and 80VU), - the weather radar shelf (109VU), - the relay and contactor boxes (103VU and 107VU), - the annunciator light test unit (70VU), - AC and DC emergency power center (106VU).
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01 GENERAL
AVIONICS COMPARTMENT EFFECTIVITY EFFECTIVITY ALL
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UFD4200
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01 GENERAL
31 - INDICATING/RECORDING SYSTEMS 31-10-00 COCKPIT PHILOSOPHY
TMUEIAB01 LEVEL 1
UFD4200
CONTENTS: Philosophy Push buttons Indications Color Philosophy
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01 GENERAL
COCKPIT PHILOSOPHY PHILOSOPHY
TMUEIAB01-T01 LEVEL 1
UFD4200
All the aircraft and system controls are arranged to be within easy reach of the two crew members. The concentration of system controls on the overhead panel is achieved by extensive use of illuminated pushbuttons directly installed on the system synoptic panel. In normal operation, no lights are illuminated in the cockpit. This is called the "lights out philosophy".
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01 GENERAL
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01 GENERAL
COCKPIT PHILOSOPHY PUSHBUTTONS
TMUEIAB01-T02 LEVEL 1
UFD4200
Status and failure indications are integrated whenever possible into the relevant illuminated pushbuttons which must be operated for corrective action. Most of the illuminated pushbuttons have two stable positions: pressed in and released out; each position corresponding to a control signal sent to a system. Pressed in (Recessed): - Normally used system activation (AUTO or ON) - Temporarily used system activation (ON) - System activated for maintenance operation (ON) or override (OVRD). Released out (flush with the panel): - System deactivation (OFF) - Manual activation of a system (ON) - Activation of an alternate system (ALTN). Some pushbuttons have only one stable position: - released out. When pushed they send a control signal to the system. NOTE: When a part of the pushbutton is not used, it is identified by two dots.
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01 GENERAL
COCKPIT PHILOSOPHY - PUSH BUTTONS EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
COCKPIT PHILOSOPHY INDICATIONS
TMUEIAB01-T03 LEVEL 1
UFD4200
The indications lights which appeared on the screen are not push buttons. The lower part is not dedicated to a control. These lights are not surrounded by a lighted border.
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01 GENERAL
COCKPIT PHILOSOPHY - INDICATIONS EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
COCKPIT PHILOSOPHY COLOR PHILOSOPHY
TMUEIAB01-T04 LEVEL 1
UFD4200
The illuminated pushbutton and annunciator lights are of different colors according to their function. In normal operation, only green lights and sometimes blue lights are illuminated.
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01 GENERAL
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UFD4200
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01 GENERAL
20 - STANDARD PRACTICES 20-00-00 ELECTROSTATIC DISCHARGE
TMUGENC01 LEVEL 1
UFD4200
CONTENTS: ESD Problems ESD Protection LRU Removal LRU Test Work Station Self Examination
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01 GENERAL
ELECTROSTATIC DISCHARGE ESD PROBLEMS
TMUGENC01-T01 LEVEL 1
UFD4200
ESD stands for ELECTROSTATIC DISCHARGE which is generated by rubbing materials with each other. By moving over plastic materials (synthetic fibers), wearing synthetic fiber clothing, electrical charges build up on the body. Thus voltages of 12000 to 35000 volts can develop on a person. Touching connector pins of computer units (Fig. 1), a discharge path is formed through wiring and components. Integrated Circuit(IC) chips can be partly damaged or totally destroyed. Here is the so-called "tribo-electric" series of materials (Fig. 2). Rubbing materials from this series against each other and then separating them from each other causes a build-up of electrostatic charges. If the materials are far apart in the series, there will be a higher electric charge.
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01 GENERAL
ELECTROSTATIC DISCHARGE - ESD PROBLEMS EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
ELECTROSTATIC DISCHARGE ESD PROTECTION
TMUGENC01-T02 LEVEL 1
UFD4200
Here are some precautions to avoid damage of electronic equipment by ELECTROSTATIC DISCHARGE.
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01 GENERAL
ELECTROSTATIC DISCHARGE - ESD PROTECTION EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
ELECTROSTATIC DISCHARGE LRU REMOVAL
TMUGENC01-T03 LEVEL 1
UFD4200
Replacing an LRU (LINE-REPLACEABLE UNIT) bearing this label, requires these precautions.
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01 GENERAL
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01 GENERAL
ELECTROSTATIC DISCHARGE LRU TEST following
TMUGENC01-T04 LEVEL 1
UFD4200
Testing of installed LRUs requires the precautions.
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01 GENERAL
ELECTROSTATIC DISCHARGE - LRU TEST EFFECTIVITY EFFECTIVITY ALL
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01 GENERAL
ELECTROSTATIC DISCHARGE WORK STATION
TMUGENC01-T05 LEVEL 1
UFD4200
The removal and testing of PRINTED-CIRCUIT BOARDS from an LRU bearing this label, is carried out as follows.
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01 GENERAL
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01 GENERAL
SELF EXAMINATION How does electrostatic electricity build up ? A - By touching electrical circuits under tension. B - By rubbing materials with each other or separating plastic sheets or tapes. C - By moving metals over plastic surfaces. How is electrostatic discharge sensitive equipment identified ? A - By a circular red label. B - By an orange triangular label. C - By a black-and-yellow label.
TMUGENC01 LEVEL 1
UFD4200
Which are some basic precautions to be taken in the case of electrostatic discharge sensitive equipement ? A - Cover the unit with plastic material. B - Do not touch connector pins, place protective caps on them. C - Test circuits with dielectric testers if necessary.
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01 GENERAL
31 - INDICATING/RECORDING SYSTEMS 31-00-00 COMPUTER REMOVAL/INSTALLATION
TMUGEND01 LEVEL 1
UFD4200
CONTENTS: Computer Removal/Installation
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01 GENERAL
COMPUTER REMOVAL/INSTALLATION COMPUTER REMOVAL/INSTALLATION
TMUGEND01-T01 LEVEL 1
UFD4200
Before starting a computer removal installation procedure, the aircraft has to be set in maintenance configuration. The first task is to make sure that the ground service network is energized and the access door is open and accessible. Then make sure that the circuit breaker listed in the removal of the computer procedure of the AMM is open. The first action is to loosen the nut and then to lower the nut. When the nut is lowered, pull the computer on its rack to disconnect the electrical connectors and remove the computer from its rack. Before starting a computer installation procedure, clean and do a visual inspection of the component interface and of the adjacent area. The first task is to remove the blanking caps from the electrical connectors and make sure that the electrical connectors are clean and in the correct condition. Then install the computer on its rack and push it on its rack to connect the electrical connectors.
Now you can engage the nuts on the studs and tighten them. The installation is finished. You can close the circuit breaker. The last actions of the computer installation are to do a test through the MCDU and close the access. Make sure that the work area is clean and clear of tools and other items, close the access door and remove the access platform.
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01 GENERAL
24 - ELECTRICAL POWER 24-00-00 OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST AND POWER SUPPLY FOR MAINTENANCE PURPOSES
TMUELT004 LEVEL 3
UFD4200
CONTENTS: 1 - Nose Station 2 - Right Main Landing Gear Station 3 - Right Engine Station 4 - Right Wing Station 5 - Left Wing Station 6 - Left Engine Station 7 - Left Main Landing Gear Station 8 - Aircraft Area 9 - Nose Station-EXT PWR Receptacle 10 - Cockpit Station
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01 GENERAL 5 - LEFT WING STATION Flaps/slats...................... check position Ground spoilers .................. check position 6 - LEFT ENGINE STATION
Note: this module presents an A/C powered by CFM engines but the procedure is also valid for IAE engines. 1- NOSE STATION Nose landing gear chocks ................in place Nose landing gear doors.................. closed Nose landing gear safety pin ........... installed Nose landing gear steering pin ....... as required Aircraft .................. electrically grounded 2 - RIGHT MAIN LANDING GEAR STATION Main landing gear door................... closed Main landing gear safety sleeve ........ installed Main landing gear chocks ................in place
TMUELT004-T01 LEVEL 3
UFD4200
3 - RIGHT ENGINE STATION Engine Engine Engine Engine
right side access doors ...........secured left side access doors ............secured fan cowls ........................secured thrust reverser cowls .............secured
4 - RIGHT WING STATION Flaps/slats..................... check position Ground spoilers .................. check position
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Engine Engine Engine Engine
right side access doors .......... left side access doors ........... fan cowls ....................... thrust reverser cowls ............
secured secured secured secured
7 - LEFT MAIN LANDING GEAR STATION RAT safety device Main landing gear Main landing gear Main landing gear
............... stowed position door................... closed safety sleeve.........installed chocks ............... in place
8 - AIRCRAFT AREA Aircraft area ....................... clear/clean 9 - NOSE STATION-EXT PWR RECEPTACLE External power ...............connected/available 10 - COCKPIT STATION Cockpit safety check-list Rear and overhead C/B panels .......... Emergency equipment : escape ropes ....................... fire extinguisher................... smoke hood ......................... fire protective gloves .............. crash axe .......................... life vests .........................
24-00-00
checked checked checked checked checked checked checked
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TMUELT004-T01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
01 GENERAL
oxygen masks ........................checked flash lights ........................checked Wipers .................................. OFF BAT1 and 2 pushbutton switches ............ OFF Check voltage above 25Volts. BAT1 and 2 pushbutton switches ........... AUTO Check R/H dome light on. Speed brake handle ............. RETRACT-DISARM If speed brake handle disagrees with surface position, maintenance action due. Thrust levers ........................... IDLE Engine master switches 1 and 2 ............ OFF Engine ignition mode selector ............ NORM Flap handle... set according to surface position Set flap handle according to surface position. If engine reverser cowls have to be opened for maintenance action, the slats must be retracted. Radar ................................... OFF ATC transponder .......................... OFF Gravity gear extension............ RESET/STOWED Landing gear lever ........... DOWN/THREE GREEN Controls Safety C/L ................. COMPLETED Power supply EXT PWR .................................. ON GEN1 and GEN2 ............................. ON Scan and check no amber lights (except GEN 1 and 2 fault lights). GALLEY ...............................AS RQRD Ventilation panel ................... no lights
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TMUELT004-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
01 GENERAL
OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST AND POWER SUPPLY FOR MAINTENANCE PURPOSES EFFECTIVITY EFFECTIVITY ALL
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