a320 chapter 01 general

A319/A320/A321TECHNICAL 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.

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...............

_A319/A320/A321 TECHNICAL TRAINING MANUAL01 GENERALMECHANICS / ELECTRICS & AVIONICS COURSE

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01 GENERAL

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01 CONTENTSPage i

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01 CONTENTSPage ii

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01 - GENERAL

01-00-00 AIRCRAFT GENERAL

CONTENTS :Lateral ViewTop ViewFront ViewDoor Heights

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AIRCRAFT GENERAL - LATERAL VIEW



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AIRCRAFT GENERAL - TOP VIEWTMUGENA01-P02 LEVEL 3



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AIRCRAFT GENERAL - FRONT VIEWTMUGENA01-P03 LEVEL 3



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AIRCRAFT GENERAL - DOOR HEIGHTSTMUGENA01-P04 LEVEL 3



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01 - GENERAL

01-00-00 AIRCRAFT DIMENSIONS

CONTENTS :Lateral ViewTop ViewFront ViewDoor Heights

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AIRCRAFT DIMENSIONS - LATERAL VIEW



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AIRCRAFT DIMENSIONS - FRONT VIEWTMUGENA03-P03 LEVEL 3



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AIRCRAFT DIMENSIONS - DOOR HEIGHTSTMUGENA03-P04 LEVEL 3



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01 - GENERAL

01-00-00 AIRCRAFT DIMENSIONS

CONTENTS:Lateral ViewTop ViewFront ViewDoor Heights

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AIRCRAFT DIMENSIONS (LATERAL VIEW)



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AIRCRAFT DIMENSIONS (FRONT VIEW)



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AIRCRAFT DIMENSIONS (DOOR HEIGHTS)TMUGENA02-P04 LEVEL 1



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51 - STRUCTURE

51-00-00 - A320 STRUCTURE GENERAL

CONTENTS:Metallic MaterialsComposite MaterialsAircraft DrainageSurface PretreatmentPaint SystemNo Step AreasJacking Points

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A320 STRUCTURE GENERAL

METALLIC MATERIALS

The basic aircraft structure is made of aluminiumalloys with stainless steel and titanium alloys inspecific areas.

COMPOSITE MATERIALS

Composite materials are used for primary and secondarystructure.Composite materials represents about 15% of theaircraft structural weight. CFRP is mainly used forprimary structures, whilst AFRP and GFRP are only usedfor secondary structures.

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A320 STRUCTURE GENERALTMUST0101-P01 LEVEL 1



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AIRCRAFT DRAINAGE

Wings and fuselage are equipped with different typesof drains.Holes and gaps are provided to ensure natural drainageof the fluid collection points. Drain holes are drilledbefore application of pretreatments. Remote drains areused when natural drainage is not possible.

SURFACE PRETREATMENT

The protection of the structure against corrosion isachieved by means of appropriate surface pretreatmentof the metallic parts.

Aluminium Alloys :The primary protection is generally a pure aluminiumcladding. The main pretreatment used is the unsealedchromic acid anodizing (CAA).

Titanium Alloys :Surface interfaying with aluminium alloy parts arezinc sprayed. The other titanium alloy surfaces areleft bare.Titanium fasteners are either sulphuric acid anodizedor aluminium coated.Composite materials are left bare.




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PAINT SYSTEM

Before the final paint system, all aluminium parts areprimed.The paint system used includes polyurethane primersand paint on the external surfaces, and epoxy primersand polyurethane paint on the internal surfaces.Anti-slip paint is the overwing escape zones.




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NO STEP AREAS

Wing and tailplane no step areas.Protective mats are required on the horizontalstabilizer as it is a carbon fiber structure.

JACKING POINTS

There are three jacking points provided.Three jacking points are provided, one below each wingoutboard of the pylon and one in front of the noselanding gear bay.




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TMUST0101 LEVEL 1



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51 - STRUCTURE

51-00-00 A320 STRUCTURAL BREAKDOWN ANDZONING

CONTENTS:Reference AxesATA ChaptersSection NumbersStation NumbersZone Numbers

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A320 STRUCTURAL BREAKDOWN AND ZONING

REFERENCE AXES

The structure elements are localized according to thefollowing reference axis.

Note : The reference (station 0) for all structuralmeasurements 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 Zplanes. Section A-A at frame 55.These are the major aircraft reference axis.




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A320 STRUCTURAL BREAKDOWN AND ZONINGTMUST0201-P01 LEVEL 1



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ATA CHAPTERS

The aircraft structure is divided according to the ATA100 specifications.

SECTION NUMBERS

Each major part of the aircraft, corresponding toproduction receives a section number. The fuselagesection base number is 10.The fuselage is divided into various sections formanufacturing reasons.




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SECTION NUMBERS

The general wing section base number is 20.The general tail plane section base number is 30.




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SECTION NUMBERS

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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STATION NUMBERS

The station number is the distance in centimeters ofa cross section from a reference point.The station/frame numbers shown correspond to thesection boundaries.Here are the engine station numbers.

Note : For the vertical stabilizer the referencestation is z=0 at the VTZ axis.




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STATION NUMBERS

Horizontal stabilizer station numbers.

Note : For the horizontal stabilizer the referencestation is y=0 at the A/C Y axis.

Wings station numbers.

Note : For wings the reference station is wingreference axis (WY). WY is located at 1868 mm(73.54 in) from A/C X axis.




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ZONE NUMBERS

There are 8 major zones in the aircraft.Each major zone is identified by the first digit of athree digit number.Fuselage and vertical stabilizer zones.




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ZONE NUMBERS

Belly fairing zones.

Landing gear zones.

Wings and horizontal stabilizer zones.




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ZONE NUMBERS

Nacelles and pylon zones.

Door zones.




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ZONE NUMBERS

Access doors and panels are identified by the numberof the zone in which the panel is located followed bya two-letter suffix which locates it within the zone.Here is an example of access panel doors on the leftwing lower surface.




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01 - GENERAL

01-00-00 GROUND HANDLING

CONTENTS :Servicing pointsA/C Servicing Arrangement 1Turning Radii

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AIRCRAFT GENERAL - SERVICING POINTSTMUGENB03-P01 LEVEL 3



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AIRCRAFT GENERAL - A/C SERVICING ARRANGEMENTTMUGENB03-P02 LEVEL 3



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AIRCRAFT GENERAL - TURNING RADIITMUGENB03-P03 LEVEL 3



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SIMULATOR COCKPIT SAFETY CHECK LIST

BEFORE POWER UP

1. PLACARDS............................... CHECK 2. CIRCUIT BRAKERS ........................ CHECK 3. BAT 1.2 ...................OFF (CHECK VOLTAGE) 4. FIRE HANDLE (ENGINE/APU) ............IN/LATCHED 5. WIPERS .................................. OFF 6. LANDING GEAR LEVER ...................... DOWN 7. THRUST LEVERS ..............IDLE/REVERSE STOWED 8. ENGINE MASTER LEVERS...................... OFF 9. ENGINE START ROTARY SELECTOR ........... NORMAL10. SLAT/FLAPS LEVER ............... CHECK POSITION11. SPEED BRAKE LEVER .............. CHECK POSITION12. PARKING BRAKE ............................. ON13. WEATHER RADAR/ATC TRANSPONDER ............. OFF14. EXTERNAL POWER (IF AVAILABLE) .............. ON15. BAT 1.2 .................................. ON

AFTER POWER UP

1. VENT PANEL...................CHECK NO LIGHTS ON2. PROBE HEAT/WINDOW HEAT.............. AS REQUIRED3. EXTERIOR LIGHTS .................... AS REQUIRED4. ANNUNCIATOR LIGHT TEST..................PERFORM5. FUEL PUMPS................................ OFF6. LANDING GEARS INDICATION............ DOWN LOCKED

BEFORE LEAVING THE SIMULATOR

1. ADIR’S ................................... OFF2. EXTERIOR LIGHTS ........................... OFF3. APU BLEED P/B ............................. OFF4. APU MASTER SW ............................. OFF5. EMERGENCY EXIT LIGHT....................... OFF6. CRT’S (ECAM-EFIS) ......................... OFF7. BAT 1.2 .................................. OFF8. EXTERNAL POWER ............................ OFF

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25 - EQUIPMENT/FURNISHING

25-10-00 COCKPIT PRESENTATION

CONTENTS:GeneralOverhead PanelGlareshieldMain Instrument PanelCenter PedestalSide Consoles

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COCKPIT PRESENTATION

GENERAL

The cockpit is equipped with adjustable seats for twocrew members, a third occupant seat and depending ofconfiguration a folding seat for a fourth occupant.Various furnishings and equipment are fitted in thecockpit for the comfort, convenience and safety ofthe occupants.

OVERHEAD PANEL

The controls of most aircraft systems are located onthe overhead panel.The overhead panel is divided into two main sections:

- a FWD section including the system panels.- an AFT section mainly comprising the circuitbreaker panel.

GLARESHIELD

The Flight Control Unit (FCU), includes the ElectronicFlight Instrument System (EFIS) controls, and is usedfor control and monitoring of the Auto Flight System(AFS).It is located on the glareshield.The "Master Caution" and the "Master Warning" lightsare also located on the glareshield.

MAIN INSTRUMENT PANEL

Six interchangeable Cathode Ray Tubes are located onthe main instrument panel.Two of them are dedicated to the ECAM.The others are two Primary Flight Displays and twoNavigation Displays.Stand-by instruments and landing gear controls arealso located on the main instrument panel.

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COCKPIT PRESENTATION

CENTER PEDESTAL

Several control panels are located on the centerpedestal 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

The side sticks and nose wheel steering handles aremounted on the side consoles.The side consoles provide documentation stowage,oxygen masks and communication devices.

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31 - INDICATING/RECORDING SYSTEMS

31-16-00 AVIONICS COMPARTMENT

CONTENTS:Description

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AVIONICS COMPARTMENT

DESCRIPTION

The electronic avionics compartment is located belowthe cockpit and cabin floors.It includes:

- the electronic racks (90VU and 80VU),- the weather radar shelf (109VU),- the relay and contactor boxes (103VU and107VU),

- the annunciator light test unit (70VU),- AC and DC emergency power center (106VU).

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AVIONICS COMPARTMENTTMUEIAC03-P01 LEVEL 1



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31-10-00 COCKPIT PHILOSOPHY

CONTENTS:PhilosophyPush buttonsIndicationsColor Philosophy

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COCKPIT PHILOSOPHY

PHILOSOPHY

All the aircraft and system controls are arranged tobe within easy reach of the two crew members. Theconcentration of system controls on the overhead panelis achieved by extensive use of illuminated pushbuttonsdirectly installed on the system synoptic panel.In normal operation, no lights are illuminated in thecockpit. This is called the "lights out philosophy".

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COCKPIT PHILOSOPHY

PUSHBUTTONS

Status and failure indications are integrated wheneverpossible into the relevant illuminated pushbuttonswhich must be operated for corrective action.Most of the illuminated pushbuttons have two stablepositions: pressed in and released out; each positioncorresponding 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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COCKPIT PHILOSOPHY - PUSH BUTTONSTMUEIAB01-P02 LEVEL 1



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COCKPIT PHILOSOPHY

INDICATIONS

The indications lights which appeared on the screenare not push buttons. The lower part is not dedicatedto a control. These lights are not surrounded by alighted border.




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COCKPIT PHILOSOPHY

COLOR PHILOSOPHY

The illuminated pushbutton and annunciator lights areof different colors according to their function.In normal operation, only green lights and sometimesblue lights are illuminated.




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COCKPIT PHILOSOPHY - COLOR PHILOSOPHY



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20 - STANDARD PRACTICES

20-00-00 ELECTROSTATIC DISCHARGE

CONTENTS:ESD ProblemsESD ProtectionLRU RemovalLRU TestWork StationSelf Examination

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ELECTROSTATIC DISCHARGE

ESD PROBLEMS

ESD stands for ELECTROSTATIC DISCHARGE which isgenerated by rubbing materials with each other.By moving over plastic materials (synthetic fibers),wearing synthetic fiber clothing, electrical chargesbuild up on the body.Thus voltages of 12000 to 35000 volts can develop ona person.Touching connector pins of computer units (Fig. 1), adischarge path is formed through wiring and components.Integrated Circuit(IC) chips can be partly damaged ortotally destroyed.Here is the so-called "tribo-electric" series ofmaterials (Fig. 2).Rubbing materials from this series against each otherand then separating them from each other causes abuild-up of electrostatic charges.If the materials are far apart in the series, therewill be a higher electric charge.

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ESD PROTECTION

Here are some precautions to avoid damage of electronicequipment by ELECTROSTATIC DISCHARGE.




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LRU REMOVAL

Replacing an LRU (LINE-REPLACEABLE UNIT) bearing thislabel, requires these precautions.




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LRU TEST

Testing of installed LRUs requires the followingprecautions.




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WORK STATION

The removal and testing of PRINTED-CIRCUIT BOARDS froman LRU bearing this label, is carried out as follows.




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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 equipmentidentified ?

A - By a circular red label.B - By an orange triangular label.C - By a black-and-yellow label.

Which are some basic precautions to be taken inthe case of electrostatic discharge sensitiveequipement ?

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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31-00-00 COMPUTER REMOVAL/INSTALLATION

CONTENTS:Computer Removal/Installation

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COMPUTER REMOVAL/INSTALLATION

COMPUTER REMOVAL/INSTALLATION

Before starting a computer removal installationprocedure, the aircraft has to be set in maintenanceconfiguration.The first task is to make sure that the ground servicenetwork is energized and the access door is open andaccessible.Then make sure that the circuit breaker listed in theremoval of the computer procedure of the AMM is open.The first action is to loosen the nut and then to lowerthe nut.When the nut is lowered, pull the computer on its rackto disconnect the electrical connectors and remove thecomputer from its rack.Before starting a computer installation procedure,clean and do a visual inspection of the componentinterface and of the adjacent area.The first task is to remove the blanking caps from theelectrical connectors and make sure that the electricalconnectors are clean and in the correct condition.Then install the computer on its rack and push it onits rack to connect the electrical connectors.

Now you can engage the nuts on the studs and tightenthem.The installation is finished. You can close the circuitbreaker.The last actions of the computer installation are todo a test through the MCDU and close the access.Make sure that the work area is clean and clear oftools and other items, close the access door and removethe access platform.

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24 - ELECTRICAL POWER

24-00-00 OUTSIDE SAFETY INSPECTION,COCKPIT CHECK-LIST AND POWERSUPPLY FOR MAINTENANCE PURPOSES

CONTENTS:1 - Nose Station2 - Right Main Landing Gear Station3 - Right Engine Station4 - Right Wing Station5 - Left Wing Station6 - Left Engine Station7 - Left Main Landing Gear Station8 - Aircraft Area9 - Nose Station-EXT PWR Receptacle10 - Cockpit Station

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OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST ANDPOWER SUPPLY FOR MAINTENANCE PURPOSES

Note: this module presents an A321 but the procedureis also valid for both A319 and A320.

Note: this module presents an A/C powered by CFMengines but the procedure is also valid for IAEengines.

1- NOSE STATION

Nose landing gear chocks................in placeNose landing gear doors.................. closedNose landing gear safety pin ...........installedNose landing gear steering pin ....... as requiredAircraft ..................electrically grounded

2 - RIGHT MAIN LANDING GEAR STATION

Main landing gear door................... closedMain landing gear safety sleeve ........installedMain landing gear chocks................in place

3 - RIGHT ENGINE STATION

Engine right side access doors ...........securedEngine left side access doors ............securedEngine fan cowls ........................securedEngine thrust reverser cowls .............secured

4 - RIGHT WING STATION

Flaps/slats..................... check position Ground spoilers .................. check position

5 - LEFT WING STATION

Flaps/slats...................... check positionGround spoilers .................. check position

6 - LEFT ENGINE STATION

Engine right side access doors .......... securedEngine left side access doors ........... securedEngine fan cowls ....................... securedEngine thrust reverser cowls ............ secured

7 - LEFT MAIN LANDING GEAR STATION

RAT safety device ............... stowed positionMain landing gear door................... closedMain landing gear safety sleeve.........installedMain landing gear 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-listRear and overhead C/B panels .......... checkedEmergency equipment :escape ropes ....................... checkedfire extinguisher................... checkedsmoke hood ......................... checkedfire protective gloves .............. checkedcrash axe.......................... checkedlife vests ......................... checked

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oxygen masks ........................checkedflash lights ........................checked

Wipers .................................. OFFBAT1 and 2 pushbutton switches ............ OFFCheck voltage above 25Volts.

BAT1 and 2 pushbutton switches ........... AUTOCheck R/H dome light on.

Speed brake handle ............. RETRACT-DISARMIf speed brake handle disagrees with surfaceposition, maintenance action due.

Thrust levers ........................... IDLEEngine master switches 1 and 2 ............ OFFEngine ignition mode selector ............ NORMFlap handle... set according to surface positionSet flap handle according to surfaceposition.If engine reverser cowls have to be openedfor maintenance action, the slats must beretracted.

Radar ................................... OFFATC transponder .......................... OFFGravity gear extension............ RESET/STOWEDLanding gear lever ........... DOWN/THREE GREENControls Safety C/L .................COMPLETED

Power supplyEXT PWR .................................. ONGEN1 and GEN2 ............................. ONScan and check no amber lights (except GEN 1and 2 fault lights).

GALLEY ...............................AS RQRDVentilation panel ...................no lights

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OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST AND POWER SUPPLY FOR MAINTENANCE PURPOSESTMUELT004-P01 LEVEL 3



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