introduction manual

Customer : LTMType : TF-NRev. Date : Aug 01, 2015

Manual : AMMSelected applicability : ALL

INTRODUCTION

Print Date: October 08, 2015 of 26© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

** ON A/C ALL

INTRODUCTION

1. GeneralA. Purpose

The data contained in this Aircraft Maintenance Manual (AMM) is in general compliance with ATASpecification 2200 (iSpec2200), Information Standards for Aviation Maintenance and ASD-STE100Simplified Technical English.Document ScopeThe AMM contains the instructions for the on-aircraft maintenance necessary to ensure the continuedairworthiness of the aircraft.NOTE TO USERS:If you cannot find the information you need to ensure the continued airworthiness of the aircraft, or if youthink that the information given is not complete, contact Airbus.The AMM contains information necessary to service, repair, replace, adjust, inspect and check equipmentand systems on the aircraft. These tasks are normally performed on the ramp or in the maintenance hangar.The information necessary for the maintenance of equipment off the A/C (shop maintenance) is given in theVendor or Manufacturer Component Maintenance Manuals (CMMV or CMMM).Where the AMM makes a cross-reference to a CMM, the cross-referenced information is related to off-aircraft maintenance and is not part of the Instructions for Continued Airworthiness that Airbus, as the TypeCertificate Holder, is required to provide.However, in a very small number of cases, AMM tasks may refer to a CMM for on-aircraft maintenance. Inthese cases, the CMM is part of the Instructions for Continued Airworthiness (ICA).The AMM also contains information about inspections and maintenance of aircraft structure. However,repair of structure is contained in the Structural Repair Manual (SRM) or Nacelle Structural Repair Manual(NSRM).Information necessary for trouble shooting is contained in the Trouble Shooting Manual (TSM).The AMM contains the necessary data to cover scheduled maintenance tasks prescribed by theMaintenance Review Board Report (MRBR), respectively the Maintenance Planning Document (MPD) andthe deactivation/reactivation procedures relative to Master Minimum Equipment List (MMEL) respectively tothe Configuration Deviation List (CDL).If a part or all of the AMM is translated, the official version shall be the original English language versionproduced by AIRBUS.AIRBUS Technical Publications use both metric and non-metric systems of measurement. The systemused in the original reference documents is quoted first, followed by the conversion into the other system inbrackets.The instructions and information contained in the AMM are applicable only to the A/C as listed at the end ofthis introduction.

B. Effectivity TableThe Effectivity Table (description and contents) is given in the Manual Front Matter.

C. CorrespondenceCorrespondence related to this publication should be directed to: AIRBUS S.A.S. Technical Data Support and Services 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE FRANCE or by the "Request for Information/Revision" form.

D. Publication FormatThe text is in Standard Generalized Markup Language (SGML) format.The standard illustrations are in Computer Graphics Metafile (CGM) format.



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Airbus has started to introduce 3D animations in the AMM in order to help the engineers and the mechanicsto better understand the scope of the procedure and to facilitate the accomplishment of specific and/orcomplex maintenance operations. The 3D animations will not replace 2D graphics, but are provided incomplement to the traditional procedure text and 2D illustrations. All 3D animations are identified in theirgraphic title by "(3D Animation)". The format used for these 3D animations is the standard VRML 2.0.(Virtual Reality Modeling Language). 3D animations will concern only aircraft equipped with Sharklets orA320 NEO aircraft (for new technical features compared with the current A320 Family).

E. Revision ServiceThe AMM is subject to:· Normal revisions· Temporary Revisions (TR)These are managed as follows:(1) Normal revisions

Normal revisions consist of a complete reissue with differential marking.(2) Temporary Revisions

Temporary revisions are issued to introduce information which cannot wait until the next normalrevision. Each temporary revision remains effective until it is incorporated in the next normal revisionor superseded by another temporary revision (if additional changes are necessary, a replacementtemporary revision is issued).Temporary Revisions must be incorporated as stated on the TR transmittal sheet.

(3) Revision markingsRevised, New and Deleted parts are highlighted in yellow in the AMM.

F. HighlightsThe Highlights identify the revised data, give the reason for revision of text and/or illustrations with a link tothe related data in the manual. They are given in the Manual Front Matter.

2. Breakdown and NumberingA. General Structure

(1) Front MatterThe Front Matter contains the following information:· Title· Legal notice· Highlights· List of Effective Temporary Revisions· Introduction· Effectivity Table· Service Bulletin (SB) List· Customer Originated Change (COC) List· Zone List· Glossary

(2) Standard ATA ChaptersThe AMM is divided into standard ATA chapters:· Aircraft General: ATA 00 up to ATA 12· Airframe Systems: ATA 20 up to ATA 50· Structure: ATA 51 up to 57· Power Plant: ATA 70 up to 80

B. Breakdown(1) List of ATA Chapters

------------------------------------------------------------------------------ CONTENT CHAPTER ------------------------------------------------------------------------------ AIRCRAFT GENERAL INTRODUCTION ........................................................... 00 Time Limits/Maintenance Checks ......................................... 05 Dimensions & Areas ..................................................... 06



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Lifting and Shoring .................................................... 07 Leveling & Weighing .................................................... 08 Towing & Taxiing ....................................................... 09 Parking & Mooring ...................................................... 10 Placards & Markings .................................................... 11 Servicing .............................................................. 12 AIRFRAME SYSTEMS Standard Practices - Airframe .......................................... 20 Air Conditioning ....................................................... 21 Auto Flight ............................................................ 22 Communications ......................................................... 23 Electrical Power ....................................................... 24 Equipment/Furnishings .................................................. 25 Fire Protection ........................................................ 26 Flight Controls ........................................................ 27 Fuel ................................................................... 28 Hydraulic Power ........................................................ 29 Ice & Rain Protection .................................................. 30 Indicating/Recording Systems ........................................... 31 Landing Gear ........................................................... 32 Lights ................................................................. 33 Navigation ............................................................. 34 Oxygen ................................................................. 35 Pneumatic .............................................................. 36 Water/Waste ............................................................ 38 Integrated Modular Avionics (IMA) and Avionics Data Communication Network .................................................. 42 Cabin Systems .......................................................... 44 Onboard Maintenance Systems (OMS) ...................................... 45 Information Systems .................................................... 46 Inert Gas System ....................................................... 47 Airborne Auxiliary Power ............................................... 49 Cargo and Accessory Compartments ....................................... 50 STRUCTURE Standard Practices and Structures ...................................... 51 Doors .................................................................. 52 Fuselage ............................................................... 53 Nacelles/Pylons ........................................................ 54 Stabilizers ............................................................ 55 Windows ................................................................ 56 Wings .................................................................. 57 POWER PLANT Standard Practices - Engines ........................................... 70 Power Plant ............................................................ 71 Engine ................................................................. 72 Engine Fuel and Control ................................................ 73 Ignition ............................................................... 74 Air .................................................................... 75 Engine Controls ........................................................ 76 Engine Indicating ...................................................... 77 Exhaust ................................................................ 78 Oil .................................................................... 79 Starting ............................................................... 80

(2) Breakdown Description



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(a) Each chapter/system is broken down into sections/subsystems (combinations offunctional/physical groups).

Example: 29-00-00 Hydraulic Power - General ! ! ! ------------------------------------------- ! ! ! ! 29-10-00 29-20-00 Main Hydraulic Power Auxiliary Hydraulic Power

(b) Each section/subsystem is broken down into sub-section/sub-subsystems(Installations/Circuits).

Example: 29-10-00 Main Hydraulic Power ! ! ! ------------------------------------- ! ! ! 29-11-00 ! 29-12-00 Green Main ! Blue Main Hydraulic Power ! Hydraulic Power ! ! 29-13-00 Yellow Main Hydraulic power

(c) Each sub-section/sub-subsystem is broken down into subjects.Example: 29-11-00 Green Main Hydraulic Power ! ! !--- 29-11-14 Main HP Manifold 1011GM ! ! !--- 29-11-15 PTU Manifold 1013GM ! ! !--- 29-11-32 Relief Valve 1063GM ! ! !--- 29-11-33 Priority Valve 1064GM Subject numbering is as follows: AIRCRAFT MAINTENANCE MANUAL XX-XX-Y0 ! Subdivision of complex where Y = 1 to 9 ! installations/circuits XX-XX-YZ ! Significant item identification number where Y = 1 to 9 ! which is also used in related manuals where Z = 1 to 9 ! like IPC and CMM.

(3) Page Block AssignmentThe information contained in the AMM is divided into two main categories:· Description and Operation



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· Maintenance Procedure(a) Description and Operation (D/O) - Page Block 001

The purpose of the D/O is to familiarize maintenance personnel with the aircraft systems and givethem sufficient information to understand how the systems operate:· Component Location· System/Component Description· Power Supply (if applicable)· Interface with other systems (if applicable)· Operation/Control and Indicating· BITE Test

(b) Maintenance Practices (Page Block 201)These topics give the procedures related to general Maintenance Practices such as:· Aircraft jacking· Aircraft leveling· Application of electrical, pneumatic, hydraulic power· Opening/closing of engine cowling, MLG doors, etc...· Installation of complex safety devices

(c) Servicing (Page Block 301)1 Procedures covering replenishment (hydraulic fluid, fuel, etc.) are listed in

chapters 12-13-XX. The last two digits give the ATA reference of the relatedsystem.

2 At subject/component level (XX-XX-XX), procedures covering e.g. filters,magnetic plug, lamp replacement, etc.

(d) Removal/Installation and Deactivation/Reactivation (Page Block 401)1 Removal/Installation

At subject/component level (XX-XX-17), this topic provides all data necessary to remove, installor replace a component.These procedures have two independent tasks, one for the removal and one for the installation.Removal task:Because there is usually an installation task after the removal task, there is generally no Close-up paragragh in the removal task.Where there is a time separation between the removal and installation tasks, it is anticipatedthat the operator will use common sense to determine the applicable close-up procedures to beadopted.Installation task:The Job Set-up is only a reminder of the main operations done during the job set-up of theremoval task such as opening of the circuit breakers, installation of the warning notices andaccess platform(s), etc.The sentence "Aircraft Maintenance Configuration" reminds the operators that they must ensurethat the aircraft configuration resulting from the job set-up of the removal must be verified beforethey start the installation procedure.

NOTE: All equipment removed, or zones behind access panels removed to get access during amaintenance operation, must also be examined before re-installation. This requirement isnot specially quoted in each procedure as it is a part of standard maintenance practices.

When a component and directly related parts require in-situ adjustment or check/test which doesnot involve complex, time-consuming operations, the related work is included in the Installationtask.Cross-reference to tasks in Page Block 501 (Adjustment/Test) is kept to a minimum.

2 Deactivation/ReactivationThe deactivation procedures describe the maintenance actions necessary to permit continuedflight operations with a system or a part of a system failed, in compliance with the MMEL andCDL requirements.These procedures are given at Chapter/Section level (XX-XX-00).



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The AMM provides EASA MMEL tasks and FAA MMEL tasks. An FAA MMEL task is highlightedby "(FAA only)", and this task is not included in the Airbus MMEL.

NOTE: Non-FAA operators can use the AMM task related to an FAA MMEL task if the AMM tasksatisfies their MEL requirements

NOTE: Some Deactivation/Reactivation tasks do not include a reference to an MMEL/CDL item.This is because they are not related to the dispatch conditions quoted in these docu-ments.

The deactivation tasks related to an MMEL or CDL item have a "Task Summary" table whichgives:· MMEL or CDL Ref.: reference(s) of the related MMEL or CDL item(s).· ACCESS: opening of access door(s)/panel(s) other than the avionics compartment is

necessary (YES/NO).· TEST: the procedure is done via a test (YES/NO).· SPECIFIC TOOLS: specific tools are necessary to do the task (YES/NO).· Manhours (Mhr): Estimated hours necessary to do the task (in hours and hundredths of hours).

This value is based on the quantity of work that an average worker can do in one hour.· Elapsed Time (E/T): Estimated total time (elapsed) necessary to do the task (in hours and

hundredths of hours). The elapsed time can be, but is not always, the number of manhoursnecessary to do the task divided by the number of men that can work simultaneously.

· Number of Men (Nb Men): The number of persons that can work simultaneously to do the task. The data in the Task Summary table comes from the deactivation task andthe task(s) to which there is a direct cross-reference (e.g. for access, tooldata, etc.). Reactivation:The reactivation procedures describe the maintenance actions necessaryto restore the system to normal operation after removal or deactivation ofthe faulty component or system.

(e) Adjustment/Test (Page Block 501)1 Operational Test

This test is required to ascertain only that a system or unit is operational. This test normallydoes not require special equipment or facilities other than that installed on the aircraft and iscomparable to the test performed by the flight crews.

2 Functional TestThis test is required to ascertain that a system or unit is functioning in all aspects in accordancewith minimum acceptable system or unit design specifications. This test may requiresupplemental ground support equipment and is more specific and detailed than an operationaltest.

3 System TestThis test contains all adjustment specifications and tolerances required to maintain system and/orunit performance at maximum efficiency and design specifications.

4 BITE TestThere are two types of BITE Tests: Main BITE Test and Interactive BITE Test.

(f) Inspection/Check (Page Block 601)1 General

Inspection/Check (I/C) topics are divided into two categories:· I/C without removal of components from the aircraft.· I/C after removal of components from the aircraft.a I/C without component removal, like:

· visual I/C (for cracks, damage, oxidation, paint condition, etc.)· measurements (displacement, travel, overall clearances, leak measurements).



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b I/C with component removal, like:· original manufacturer's dimensions· maximum and minimum clearances and in-service wear limits (given in table form).

2 There are three types of Inspections:a Detailed Inspection (DI):

An intensive examination of a specific item, installation or assembly to detect damage,failure or irregularity. Available lighting is normally supplemented with a direct source of goodlighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifyinglenses etc.. may be necessary. Surface cleaning and elaborate access procedures may berequired.

b General Visual Inspection (GVI):A visual examination of an interior or exterior area, installation or assembly to detect obviousdamage, failure or irregularity. This level of inspection is made from within touching distanceunless otherwise specified. A mirror may be necessary to ensure visual access to all surfacesin the inspection area. This level of inspection is made under normally available lightingconditions such as daylight, hangar lighting, flashlight or drop-light and may require removalor opening of access panels or doors. Stands, ladders or platforms may be required to gainproximity to the area being checked.

c Special Detailed Inspection (SDI):An intensive examination of a specific item, installation, or assembly to detect damage, failureor irregularity. The examination is likely to make extensive use of specialized InspectionTechniques and/or equipment. Intricate cleaning and substantial access or disassemblyprocedure may be required.

(g) Cleaning/Painting (Page Block 701)Cleaning/painting procedures which require special precautions (parts contaminated by hydraulicfluid, battery acid, etc.) are included in the relevant chapter.

(h) Approved Repairs (Page Block 801)Repairs included in these topics are non-structural repairs that can be performed on the aircraft.Other repair procedures are given in the CMMM/CMMV or in the SRM/NSRM.The repair procedures given in the AMM are not submitted to the airworthiness authorities forapproval, but are technically approved by:· The aircraft manufacturer, for manufacturer components· The related vendor, for vendor componentsIMPORTANT : Record of Temporary RepairsIf Temporary Repairs are made, it is the responsibility of the operator to record the following:· location of the damage· nature of the damage· nature of the repair· service life limit of the temporary repair.

C. AMTOSS (Aircraft Maintenance Task Oriented Support System) Task/Subtask NumberingThe functional arrangement of data and the numbering system form the basis for the assignment ofmaintenance Task/Subtask numbers to each maintenance operation (Task) described in the AMM.(1) Task/Subtask Numbering

Maintenance Procedures are broken down into tasks and subtasks. The TASK/Subtask number canhave five, six or seven elements.Task and subtask numbers are structured as follows: (a) Task Element

Task Element / TASK XX-XX-XX-XXX-XXX-XXX-XXX 1 2 3 4 5 6 7 ------------------------------------------------------------------------------- ELEMENT FUNCTION -------------------------------------------------------------------------------



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1 to 3 ATA six-digit number 4 The three-digit numeric function code is used to indicate the particular maintenance function involved. 5 The three-digit numeral used to give a unique identification number to each Task/Subtask similarly numbered throughout the the preceding elements. To provide numerical separation between Task and Subtask, Task identification begins at 001 and rises, in sequence, to 049 (maximum) within the procedure. Subtask identification begins at 50 and rises, in sequence, to 800 (maximum) within the procedure. Illustrations and tables are considered as tasks. 6 The three-digit alphanumeric indicator comprises of: - First digit alpha to identify different Technical configurations (modification(s), service bulletin(s), etc..) - Second and third digit numerals to identify alternative methods/techniques of maintenance. Example: -78-31-00-710-040-A 01 ! ! ! ! ! ! This alpha digit-! ! identifies the ! technical ! configuration ! (SB, etc.) ! ! ! These two numerical-! digits identify a method/technique - Technical configurations: 78-31-00-710-040-A - ! ! -------------------------------- * when there is only one configuration, always letter A * when there are several configurations, this digit changes as follows: 78-31-00-710-040-A first configuration 78-31-00-710-040-B second configuration 78-31-00-710-040-C third configuration The technical configurations always have different effectivities. - Alternative methods/techniques: 78-31-00-710-040- 01 -- ! ------------------------------------- * these two digits are blank



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when there is only one method/technique * when there are several methods/techniques, these digits change as follows: 78-31-00-710-040 first configuration 78-31-00-710-040- 01 second configuration 78-31-00-710-040- 02 third configuration The alternative methods/techniques always have the same effectivities. 7 A three-digit alphanumeric indicator that can be assigned by the airline to highlight specific airline data. This is not included in the TASK/Subtask number unless specifically requested by the airline in the COC dossier.

NOTE: Unless otherwise specified, MPD, MMEL/MCDL, ISB/SB and other external documents referto the basic AMTOSS reference, i.e. up to the fifth element. All the configurations related tothe task answer to the external manual requirement(s).

(b) Subtask Element Subtask Element / XX-XX-XX-XXX-XXX-XXX-XXX 1 2 3 4 5 6 7 ------------------------------------------------------------------------------- ELEMENT FUNCTION ------------------------------------------------------------------------------- 1 to 4 Identical functions as for a TASK 5 The three-digit numeral used to give a unique identification number to each subtask similarly numbered throughout the preceding elements. To provide numerical separation between TASK and subtask, Subtask identification begins at 050 and rises, in sequence, to 800 (maximum) within the procedure. 6 An alpha digit is used to indicate a different variant of Subtask due to embodiment of modification(s), service bulletin(s). 7 Three-digit alphanumeric indicator that can be assigned by the airline to highlight specific airline data. This is not included in the subtask number unless specifically requested by the airline in the COC dossier.

(2) AMTOSS Function CodesThe first two digits of the numbering system fourth element are in accordance with the ATASpecification, although in some instances a third digit has been added for further breakdown of the basicfunction.

FUNC-TIONCODE

DEFINITION APPLI.

000 REMOVAL T, ST010 REMOVE/OPEN FOR ACCESS T, ST020 REMOVE UNIT/COMPONENT DISCONNECT/LOOSEN/RMV ITEM T, ST040 DEACTIVATION T, ST080 REMOVE TEST/SUPPORT EQUIPMENT T, ST081 REMOVE SAFETY LOCKS T, ST100 CLEANING T, ST



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FUNC-TIONCODE

DEFINITION APPLI.

110 CHEMICAL T, ST120 ABRASIVE T, ST130 ULTRASONIC ST140 MECHANICAL T, ST150 PAINT STRIPPING ST160 MISCELLANEOUS CLEANING T, ST170 FLUSHING T, ST200 INSPECTION/CHECK T, ST210 GENERAL VISUAL INSPECTION/CHECK T, ST220 DETAILED/DIMENSIONAL INSPECTION/CHECK T, ST230 PENETRANT INSPECTION T, ST240 MAGNETIC INSPECTION ST250 EDDY CURRENT INSPECTION T, ST260 X-RAY/HOLOGRAPHIC INSPECTION T, ST270 ULTRASONIC INSPECTION T, ST280 SPECIFIC/SPECIAL INSPECTION/CHECK T, ST281 SAMPLING T, ST290 BORESCOPE INSPECTION T, ST300 CORRECTION/REPAIR T, ST310 WELDING/BRAZING ST320 MACHINING/REAMING/BLENDING T, ST330 COMPOSITE T, ST340 FIBERGLAS/PLASTIC/HONEYCOMB/EPOXY T, ST350 MISCELLANEOUS REPAIR T, ST360 LEAKAGE REPAIR T, ST370 PAINTING T, ST380 PLATING T, ST390 SEALING T, ST400 INSTALLATION T, ST410 INSTALL/CLOSE ITEMS REMOVED/OPENED FOR ACCESS T, ST420 INSTALL UNIT/COMPONENT/ITEM/RECONNECT T, ST440 REACTIVATION T, ST480 INSTALL TEST/SUPPORT EQUIPMENT T, ST481 INSTALL SAFETY LOCKS T, ST500 MATERIAL AND AIRCRAFT HANDLING T, ST510 SHIPPING T, ST520 RECEIVING ST530 PACKING T, ST540 UNPACKING T, ST550 STORAGE/RETURN TO SERVICE T, ST551 COMPONENT STORAGE ST552 COMPONENT RETURN TO SERVICE ST553 AIRCRAFT STORAGE T, ST554 AIRCRAFT RETURN TO SERVICE T, ST555 PARKING T, ST556 MOORING T, ST560 MARSHALLING T, ST



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FUNC-TIONCODE

DEFINITION APPLI.

570 ENGINE FERRY/POD MAINTENANCE T, ST580 AIRCRAFT HANDLING T, ST581 LIFTING T, ST582 JACKING T, ST583 SHORING T, ST584 TOWING T, ST585 TAXIING T, ST586 LOWERING T, ST589 GROUND HANDLING OPERATION T, ST600 SERVICING/PRESERVING/LUBRICATION T, ST610 SERVICING T, ST611 HYDRAULIC REPLENISHING T, ST612 OIL REPLENISHING T, ST613 MISCELLANEOUS REPLENISHING T, ST614 GAS CHARGING/DISCHARGING T, ST615 AIRCRAFT CLEANING T, ST616 DATA LOADING T, ST618 AIR PRE-CONDITIONING T, ST620 PRESERVING T, ST630 DEPRESERVING T, ST640 LUBRICATING T, ST650 FUELING/DEFUELING T, ST660 DEICING/ANTI-ICING T, ST670 DESINFECT/SANITIZE T, ST680 DRAIN FLUID T, ST700 TESTING T, ST710 OPERATIONAL T, ST720 FUNCTIONAL T, ST730 SYSTEM T, ST740 BITE T, ST750 SPECIAL T, ST760 ELECTRICAL T, ST780 PRESSURE T, ST790 LEAK T, ST800-900 MISCELLANEOUS T, ST810 FAULT ISOLATION T, ST811 COMPONENT REPLACEMENT ST812 WIRING CHECK ST820 ADJUSTING/ALIGNING/CALIB./RIGGING T, ST840 PREPARE FOR, RESTORE TO T, ST850 OPERATOR MODIFICATION T, ST860 AIRCRAFT/SYSTEM CONFIGURATION T, ST861 ENERGIZE ELECTRICAL NETWORK T, ST862 DE-ENERGIZE ELECTRICAL NETWORK T, ST863 PRESSURIZE HYDRAULICS T, ST864 DEPRESSURIZE HYDRAULICS T, ST865 C/B OPENING/CLOSING T, ST



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FUNC-TIONCODE

DEFINITION APPLI.

866 FLIGHT CONTROL SURFACES MOVEMENT T, ST867 LANDING GEAR MOVEMENT T, ST869 AIRCRAFT/SYSTEM CONFIG. - MISCELLANEOUS T, ST870 BLEEDING T, ST875 C/B OPENING/CLOSING ST880 HEATING COOLING ST890 AIRLINE MAINTENANCE PROGRAM T, ST910 STANDARD PRACTICES T, ST911 MECHANICAL PARTS T, ST912 ELECTRICAL PARTS T, ST913 CARGO LOADING/UNLOADING T, ST914 SEALANTS ST915 ADHESIVES T, ST916 PROTECTIVE TREATMENTS T, ST917 PIPEWORK T, ST918 MISCELLANEOUS METALLIC/NON-METAL. PARTS T, ST920 SCHEDULED REPLACEMENT T, ST930 MARKING T, ST940 JOB SET-UP/CLOSE-UP T, ST941 JOB SET-UP ST942 CLOSE-UP T, ST950 MASKING ST960 REPLACE T, ST970 DATA RECORDING/CALCULATING T, ST980 MANUAL OPERATION OR POSITIONING T, ST990 ILLUSTRATIONS, TABLES ST991 ILLUSTRATIONS T992 IDENTIFIABLE TABLES T

D. Paragraph numberingCapital letters "I" and "O" are not used for paragraph numbering. This is because there can be confusionbetween these letters and the numbers "1" and "0". Thus the level 2 paragraph numbering sequence is: A.,B., C., D., E., F., G., H., J., K., M., N., P., Q.,

3. Structure and ContentA. Front Matter

(1) TitleProvides the name of the manual, the revision date and the revision number.

(2) Legal NoticeProvides the Manufacturer contact address.

(3) HighlightsThe Highlights provide the reason for the revision of text and/or illustrations. They are sorted by ATAChapter.

(4) List of Effective Temporary RevisionsThis list is always empty at the delivery of each normal revision. A list of Effective Temporary Revisions(LETR) is dispatched with each Temporary Revision (TR) issued.Temporary Revisions are supplied in digital format via Airbus-World and in CD format. The TRs mustbe loaded in AirNav/Maintenance as soon as received. Refer to Airnav/Maintenance User Guide forupdating and management.

(5) Introduction



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The Introduction gives general information on how to use the manual.(6) Effectivity Table

This table gives the correspondence between Fleet Serial Number (FSN) and Manufacturer SerialNumber (MSN) for your fleet. Only the aircraft identified in this table are covered in the AMM.

(7) Service Bulletin (SB) ListThis is the List of the Service Bulletins which are applicable for at least one aircraft of the fleet.

(8) Customer Originated Change (COC) ListThis is a list of the Customer Originated Changes (COCs) which are applicable for at least one aircraft ofthe fleet. Where applicable, PRE and POST COC are clearly indicated in the AMM. POST COC data isshown in green color to differentiate it from the original Manufacturer's data.

(9) Zone ListThis is a list of the aircraft zones. It gives their description and their boundaries.The boundaries with "/" (e.g. FR 44/45) indicate that the zone starts or ends between two frames.

(10) GlossaryThe glossary gives a list of all the approved abbreviations.The abbreviations are defined in the Airbus Approved Abbreviations Handbook (AAAH).

B. Standard Chapters(1) Description & Operation (D/O)

(a) The information contained in the D/O is covered at three levels:1 At Chapter/System level (example XX-00-00)

Describes the relationship of functional/physical groups of the system, together with scope andoutstanding features.Relationship between subsystems and other systems is also explained.As a rule, illustrations at this level are simplified block diagrams or general views of the aircraftgiving the location of the main components (e.g. flight controls, landing gears, etc.).

2 At section/subsystem level (XX-X0-00)Details the functional/physical groups of the subsystem, the relationship between the groups andother systems, and the scope of each group.

3 At sub-section/sub-subsystem level (XX-XX-00)Installation/circuit level or at XX-XX-X0 for subdivision of complex Installation/circuits.

(b) The Description and Operations are broken down as follows:1 General

Main functions are described for functional/physical groups and their relationship with othergroups or systems.

2 Component LocationDetails the major components within an installation/circuit with following information:· Component electrical or mechanical Functional Item Number (FIN).· Functional Designation (Component name).· Instrument panel which accommodates the controls/indicators, if applicable.· The zone in which the component is located.· Access Door numbers.· ATA reference which contains the Removal/Installation procedure of the component.

3 System DescriptionThe system description is detailed as follows:· Power supply (if applicable)

This paragraph provides essentially an illustration showing electrical circuitsupply. e.g. Block diagram, simplified schematic.

· Interface (if applicable)A block diagram or a simplified schematic is provided to show therelationship between the system and the other systems.

· Component DescriptionBroad descriptive and operational information for major components of thefunctional/physical group.

· Operation



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Detailed operational information related to installation/circuit is given. Theassociated schematic shows the Functional Identification Numbers (FIN)of each component and associated electrical connections. The aim is tofacilitate fault isolation and to ease cross-reference to the Aircraft WiringManual (AWM).

· Test (if applicable)This paragraph gives a brief description of BITE or special test system.

(2) Maintenance Procedure (MP)A Maintenance Procedure is made up of Task(s) and Subtasks. Each Task is broken down into thefollowing paragraphs:· Title· Reason for the Job· Job Set-Up Information· Job Set-Up· Procedure· Close-Up (If applicable)

(a) Title

It is the title of the Task followed by the FIN Number(s) if applicable.

(b) Reason for the JobThe paragraph "Reason for the Job" is used to explain the reason for the task.This paragraph can refer to:· an Airbus MMEL, CDL or MPD task.

NOTE: Each MPD task is identified by a specific MPD task number. The MPD task number com-prises 9 digits organized as follow : XX XX XX - XX - X (ATA reference or Zone - sequencenumber identifier - applicability index). The MPD applicability index digit is not shown in theAMM task.

· an FAA MMEL task, highlighted by (FAA only), if this task is not included in the Airbus MMEL.

NOTE: Non-FAA operators can use the AMM task related to an FAA MMEL task if the AMM tasksatisfies their MEL requirement.

When the Task title is self explanatory, this paragraph shows "Self explanatory"(c) Job Set-Up Information

The paragraph "Job Set-Up Information" can contain the following data:1 Fixtures, Tools, Test and Support Equipment

The Special Tools and Support Equipment required for the maintenance operations areidentified:· either by their Part Numbers when they are listed in the Illustrated Tool and Equipment Manual

(TEM).· or by their main features.· The use by the airline of equivalent tools/equipment is permitted on the condition that the

equivalent has the technical characteristics required to correctly performe the maintenanceprocedure described. Special procedures associated with the use by the airlines of "equivalent"tools fall under their own responsibility.

· Total quantity of special tools for the tasks is indicated.2 Consumable Materials

This table gives a list of all the materials called up in the maintenance procedure. They arerecorded in the Consumable Material List (CML) for general use on Airframe, in AMM 20-34-00for APU-specific materials and in AMM 70-30-00 for engine-specific materials.To know the characteristics of the consumable materials used on the Airframe, refer to the CMLavailable in AirNav/Associated Data.



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3 Work Zones and Access PanelsThis table gives all location and access panel information required to do the task.The zones are identified by a three-digit numerical code (example: 131). The access panel codecontains zone identification with additional alphabetical characters (example: 131AMG).Zone information is given in the AMM Front Matter.Access panel information is given in AMM Chapter 6.

4 Expendable PartsTo facilitate the preparation of the job, the IPC CSN (Catalog Sequence Number) or PIPCCSN of expendable parts is listed in the paragraph "Job Set-Up Information" under the title"Expendable Parts".Use the Illustrated Parts Catalog (IPC) or the Power Plant Illustrated Parts Catalog (PIPC) to findthe corresponding Part Numbers.

5 Referenced InformationAny additional information which is necessary to do the maintenance procedure (task) is listed inthe paragraph "Job Set-up Information" under the title "Referenced Information".For cross-reference to tasks in the AMM, only the task reference is shown with a hyperlink to thereferenced Task(s).References to other manuals are made by the manual abbreviation and the reference:· Task number for the TSM (e.g. TSM 77-00-00-810-802)· ATA-references for all the other manuals (e.g. ASM 441100, CMM 323258)

(d) Job Set-UpThis section gives the information that is required for job preparation. It is broken down into Subtasksthat indicate:· Aircraft Maintenance Configuration, e.g. the required aircraft attitude (jacking), installation of safety

locks, grounding of aircraft, connection of electrical, hydraulic and air supplies, etc.· Get access, e.g. to Avionics Compartment (for circuit breakers)· Safety Precautions

(e) ProcedureThe paragraph is also broken down into Subtasks and its contents varies according to the PageBlock.

(f) Close-UpThis paragraph gives all the worksteps necessary to put the aircraft back into its initial configuration,e.g.:· Close Access· Remove access platform(s), warning notice(s), etc.· De-energize the aircraft electrical circuits, etc.

4. Power Plant ChaptersA. Engine Data - Introduction

** ON A/C 151-200, 246-300, 351-352, 356-356, 358-450, 501-535, 540-550, 561-568, 571-571, 581-600(1) General

(a) This portion of the manual covers the maintenance that can be performed while theengine installed on the aircraft.

It is recommended that the operators avoid performing maintenance on multiple engines installed onthe same aircraft at the same time if at all possible.If it is not possible to avoid maintenance on more than one engine at the same time, it isrecommended that different maintenance teams service each engine.

NOTE: The above recommendation is an extract of the Special Airworthiness Information Bulletin(SAIB) No. NE-00-12, issued by the Federal Aviation Administration (FAA). It is recommen-ded to consult this FAA bulletin for details and background information.

(b) Data related to line maintenance of the engine and its subsequent ground handlingcover the following points:

1 Servicing



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2 Fault Isolation (Refer to the Trouble Shooting Manual)3 Controlling parameters and acceptable operation limits.4 Replacement, inspection, adjustment and test of Line Replaceable Units

(LRU's).(c) All information covering description, location, operation of the engine, its components

or systems, although not directly related to a specific maintenance task, is alsoincluded.

(d) Welding repair on engine WARNING: DO NOT WELD ENGINE COMPONENTS WHILE THEY ARE INSTALLED ON THE AIRFRAME OR ENGINE BECAUSE THERE IS A RISK OF FIRE. ALL THE WELD REPAIRS GIVEN BY THE ENGINE MANUFACTURER ARE FOR ENIGNES OR COMPONENTS IN A WORKSHOP.

(e) Observe standard shop practice safety procedures and precautionary measures at alltimes to avoid damage to equipment or injury to personnel.

(f) These instructions neither purport to cover all details or variations in equipmentnor provide for every possible contigency to be met in connection with installation,operation or maintenance.

(g) Where required the data are completed by Nacelle and Airframe information.(h) Not Applicable

** ON A/C 001-009, 011-050, 101-150, 301-350, 601-710, 712-712, 717-750, 801-850(2) General

(a) This portion of the manual covers the maintenance that can be performed while theengine installed on the aircraft.

It is recommended that the operators avoid performing maintenance on multiple engines installed onthe same aircraft at the same time if at all possible.If it is not possible to avoid maintenance on more than one engine at the same time, it isrecommended that different maintenance teams service each engine.

NOTE: The above recommendation is an extract of the Special Airworthiness Information Bulletin(SAIB) No. NE-00-12, issued by the Federal Aviation Administration (FAA). It is recommen-ded to consult this FAA bulletin for details and background information.

(b) Data related to line maintenance of the engine and its subsequent ground handlingcover the following points:

1 Servicing2 Fault Isolation (Refer to the Trouble Shooting Manual)3 Controlling parameters and acceptable operation limits.4 Replacement, inspection, adjustment and test of Line Replaceable Units

(LRU's).(c) All information covering description, location, operation of the engine, its components

or systems, although not directly related to a specific maintenance task, is alsoincluded.

(d) Welding repair on engine WARNING: DO NOT WELD ENGINE COMPONENTS WHILE THEY ARE INSTALLED ON THE AIRFRAME OR ENGINE BECAUSE THERE IS A RISK OF FIRE. ALL THE WELD REPAIRS GIVEN BY THE ENGINE MANUFACTURER ARE FOR ENIGNES OR COMPONENTS IN A WORKSHOP.

(e) Observe standard shop practice safety procedures and precautionary measures at alltimes to avoid damage to equipment or injury to personnel.

(f) These instructions neither purport to cover all details or variations in equipmentnor provide for every possible contigency to be met in connection with installation,operation or maintenance.

(g) Where required the data are completed by Nacelle and Airframe information.(h) Not Applicable



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** ON A/C 151-200, 246-300, 351-352, 356-356, 358-450, 501-535, 540-550, 561-568, 571-571, 581-600(3) Organization of Manual

(a) Shared Chapters ------------------------------------------------------------------------------ CHAPTER CHAPTER NUMBER CHAPTER DESIGNATION NUMBER CHAPTER DESIGNATION ------------------------------------------------------------------------------ 06 Dimensions and Areas 70 Standard Practices - Engines 11 Placards and Markings 71 Power Plant 12 Servicing 72 Engine 23 Communications 73 Engine Fuel and Control 24 Electrical Power 74 Ignition 26 Fire Protection 75 Air 29 Hydraulic Power 76 Engine Controls 30 Ice and Rain Protection 77 Engine Indicating 36 Pneumatic 78 Exhaust 54 Nacelles/Pylons 79 Oil 80 Starting

** ON A/C 001-009, 011-050, 101-150, 301-350, 601-710, 712-712, 717-750, 801-850(4) Organization of Manual

(a) Shared Chapters ------------------------------------------------------------------------------ CHAPTER CHAPTER NUMBER CHAPTER DESIGNATION NUMBER CHAPTER DESIGNATION ------------------------------------------------------------------------------ 06 Dimensions and Areas 70 Standard Practices - Engines 11 Placards and Markings 71 Power Plant 12 Servicing 72 Engine 23 Communications 73 Engine Fuel and Control 24 Electrical Power 74 Ignition 26 Fire Protection 75 Air 29 Hydraulic Power 76 Engine Controls 30 Ice and Rain Protection 77 Engine Indicating 36 Pneumatic 78 Exhaust 54 Nacelles/Pylons 79 Oil 80 Starting

** ON A/C 151-200, 246-300, 351-352, 356-356, 358-450, 501-535, 540-550, 561-568, 571-571, 581-600(5) Supporting Publications

The following is a list of publications which directly support this maintenance publication:(a) Operating Instructions (OI)

The operating instructions give operating limits and special operating procedures useful for pilotsand maintenance personnel who will operate the engines. These instructions are not to be used fortesting the engines after line maintenance.

(b) Engine Illustrated Parts Catalog (EIPC)1 The Illustrated Parts Catalog lists and illustrates all parts and assemblies of

the engine. It is intended only for requisitioning, storing, issuing, and identifyingparts and for illustrating relationship for disassembly, where applicable. It is notto be used as the authority for procedures of assembly or disassembly.

2 The catalog is also a historical record of parts used, superseded, and/ordiscontinued.

(c) Power Plant Illustrated Parts Catalog (PPIPC)



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· The integrated Power Plant Illustration Parts Catalog identifies and illustrates line replaceableparts of the Power Plant.

· Provides interchangeability information between parts.· Presents various modifications and configurations resulting from Service Bulletin

accomplishments.· Intended only for requisitioning, storing, issuing and identifying part relationship for disassembly,

where applicable. Not to be used as the authority for procedures of assembly or disassembly.(d) Illustrated Tool and Equipment Manual (ITEM)

The Illustrated Tool and Equipment Manual provides information on the special tools and equipmentrequired for the engine. The tools and equipment are illustrated with a brief description of the tooland its use.

(e) Non-destructive Test Manual (NTM)This manual provides information on non-destructive testing methods of inspecting the engine, itscomponents, and individual parts. This manual is to be used in conjunction with the MaintenanceManual and other applicable inspection equipment manufacturer's Operating and ServiceInstructions. All results of these inspections shall be interpreted according to limits of serviceabilityshown in the maintenance manual.

(6) Supplementary PublicationsThe following list includes additional publications that support the engine but do not directly relate to theon-aircraft maintenance of the engine:(a) Engine Shop Manual (ESM)

1 The Engine Shop Manual presents detailed information required to support theengine at shop level.

2 Inspection, repair procedures, testing and trouble-shooting comprise themajor portion of this publication. Description of the engine sections, andcomponents, are included to familiarize personnel with the terminology andphysical appearance of the various components.

(b) Component Maintenance Manuals (CMM)1 The Component Manuals contain detailed maintenance or overhaul

instructions for the accessories furnished on the engine.2 The manuals cover disassembly, cleaning, inspection, approved repairs and

repair methods, assembly and testing of the accessories. The manuals alsoinclude an Illustrated Parts Catalog for each of these accessories.

(c) General Facilities StudyThis manual contains installation design data for the engine. The data is specifically related to powerplant installation such as dimensions, weights, location and design of customer attachment points,and mounting configurations.

(d) Standard Practices Manual (SPM)This Manual covers frequently used processes and procedures that are used in the maintenanceand repair of engine parts.

(e) Consumable Products Manual (CPM)The Consumable Products Manual presents technical data on all products used in maintenance ofthe engine.

(f) Nacelle Structural Repair Manual (NSRM)This manual provides structural identification,allowable damage and repair instructions of thenacelle.

** ON A/C 001-009, 011-050, 101-150, 301-350, 601-710, 712-712, 717-750, 801-850(7) Related Publications

(a) The publications listed as follows are connected to and used with this manual:1 Propulsion System Operating Instructions (Refer to Flight Crew Operating

Manual).2 There is no Power Plant Illustrated Parts Catalog (PPIPC) for IAE engine. All

data are covered in the Airframe IPC (AIPC).



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3 Illustrated Tool and Equipment Manual (Refer to Illustrated Tool andEquipment Manual) - The Illustrated Tool and Equipment Manual gives dataon the special tools and equipment necessary for the engine. The tools andequipment are illustrated together with a description of purpose and usage.

4 Non-Destructive Test Manual (Refer to NDT).5 Engine Manual - The engine manual does not relate directly to the on-aircraft

maintenance of the engine, but it does contain the data necessary for work tobe completed on an engine in the workshop.

6 IAE - Component Maintenance Manuals - These four manuals (Tubes/Hoses/Ducts, Miscellaneous Mechanical, Electrical Harness and Cables, Fuel Nozzleand Support) are related to the Engine Manual and contain data for work to beaccomplished in the workshop.

7 Wiring Data (Refer to AWM) - The Aircraft Wiring Manual provides datanecessary for support of the various electrical cables and harnesses that areinstalled on the Propulsion System.

8 Vendor Component Maintenance Manuals - The various Vendor ComponentMaintenance Manuals, which cover the proprietary components/accessoriesthat are installed in the Propulsion System, contain data for work to beaccomplished in the workshop. A complete listing of these Vendor ComponentMaintenance Manuals is contained in the: Technical Publications Index andList of Overhaulable Components (TPI/LOC).

9 Engine/Nacelle Service Bulletins - Engine Service Bulletins and NacelleService Bulletins are issued to provide instructions for the advancement of aconfiguration or for the accomplishment of a one-time inspection, etc.

(8) Engine Area Identification(a) Clock position, left, right and other direction instructions refer to an engine in a

horizontal position, viewed from the rear and with the engine mounts at the top.(9) Engine Consumable Product

(a) All the engine consumable products are included in the chapter 70-30-00. A "*"symbol indicates that no national reference for material is available.

(10) The approved repair procedures linked to engine are controlled by an internal Repair Scheme(VRS) number.

** ON A/C ALL5. Effectivity Statement

A. General(1) Text

The effectivity in the manual is expressed in Fleet Serial Number (FSN).The Task and Subtask numbers are preceded by the associated A/C effectivity statements.There is nolink between a Task variant letter (6th element) and a Subtask variant letter not even when Task andSubtask have the same A/C effectivity.This means for the reader of the AMM that the selection of information for a specific A/C must beperformed according to the A/C effectivity statements on Sub-task level.

(2) Service Bulletin (SB)Service Bulletins are incorporated automatically in the AMM if at least one aircraft is potentiallyapplicable and quoted in the Service Bulletin.Data related to Service Bulletins are only incorporated upon notice from the customer that subjectService Bulletins have or will be embodied on the aircraft.The effectivity statement will provide the following status:EXAMPLE: ** ON A/C 001-001 PRE SB 46-XXXX for A/C 001-001 Subtask 45-20-00-860-019-A A. Get Access to the SPP Display Function



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(1) On the OMT, on the OMS Home page, in the Advanced Functions pull-down menu, select: DLCS - Software Pin Prog. ** ON A/C 002-100 POST SB 46-XXXX for A/C 001-001 Subtask 45-20-00-860-019-B A. Get Access to the SPP Display Function (1) On the OMT, on the OMS Home page, in the Advanced Functions pull-down menu, select: DLCS - Software Pin Programming. The above statement indicates that the information is valid for A/C 002-100 as the modification wasembodied before delivery. For A/C 001-001 the information is only valid after accomplishment of the SB.After embodiment of the SB 46-XXXX on A/C 001, the PRE SB configuration will be deleted and thePOST SB configuration will become: ** ON A/C 001-100 EMB SB 46-XXXX for A/C 001-001 Subtask 45-20-00-860-019-B A. Get Access to the SPP Display Function (1) On the OMT, on the OMS Home page, in the Advanced Functions pull-down menu, select: DLCS - Software Pin Programming.

NOTE: For multiple SB effectivity EXAMPLE: ** ON A/C 051-099, POST SB 32-X001 for A/C 001-006POST SB 32-X002 for A/C 001-006

SB documents must be consulted to detect if these SBs are linked or not. If they are not linked,effectivity should be managed separately.

NOTE: For the task/subtask with effectivity covered only through SB, the first line (** ON A/C) is blank.** ON A/C POST SB 22-1361 for A/C 001-005, 007-020

(3) COC(a) COC Identification

COCs incorporated into the AMM at Customer request to reflect data or procedures originated byand peculiar to that specific customer, will be permanently identified by the COC reference numberfollowed the COC effectivity.The data affected or introduced by the COC are identified in green.Some COCs are also identified by the customer documentation code at the beginning and again atthe end of the COC data.

(b) COCs can be of two different types:1 Editorial COC

Editorial COCs" impact AMM procedures. The related AMM data is shown in permanent pre andpost COC configuration.

2 Modification COCModification COCs" install or remove equipment(s) on the A/C.They will be shown in pre and post configuration until the EO is embodied on all involved A/C.Once the EO is reported as embodied, data will be shown in post configuration only.

(c) ResponsibilityWhere the Customer requests Airbus to incorporate the Customer's originated data or that of anyother party into the technical data issued by Airbus ("Technical Data") relating to the operation,maintenance, overhaul, repair or modification of the aircraft, Airbus shall do so on the conditionthat the use of the COC data shall be entirely at the Customer's risk, Airbus being under no liabilitywhatsoever in respect of either the contents of any COC data, or the effect which the incorporation ofsuch COC data may have on the Technical Data issued by Airbus.

(d) Disclaimer ClauseAIRBUS HEREBY EXPRESSLY DISCLAIMS ANY AND ALL WARRANTIES, EXPRESSEDOR IMPLIED, ORAL OR WRITTEN, ARISING BY LAW, COURSE OF DEALING, OR



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OTHERWISE, AND WITHOUT LIMITATION ALL WARRANTIES AS TO QUALITY,OPERATION, MERCHANTABILITY, FITNESS FOR ANY INTENDED PURPOSE, AND ALLOTHER CHARACTERISTICS WHATSOEVER, OF CUSTOMER ORIGINATED CHANGESINCORPORATED INTO THE TECHNICAL DATA ISSUED BY AIRBUS. THE FOREGOINGDISCLAIMER SHALL ALSO APPLY TO ANY OTHER PORTION OF THE TECHNICAL DATAWHICH MAY BE AFFECTED BY SUCH CUSTOMER ORIGINATED CHANGES.

6. Special Procedure and Standard Maintenance PracticesSpecial procedures specific to AIRBUS are considered as AIRBUS standard maintenance practices when theyare applicable to several systems. These procedures are described in chapters 20 and 70.Procedures applicable to one system only are described in the relevant chapter.

NOTE: Industry standard maintenance practices are not given in the AMM. Thus, procedures related to simplecomponents (including replacement/reinstallation) that do not require:- A specific aircraft configuration- Safety precautions- Specific tests after installation,

are not given in the AMM.

NOTE: When it is necessary to go on a surface of the aircraft (e.g. wing, THS) to do maintenance tasks, Airbusrecommends protection of the surface. This is to prevent a possible risk of damage to the surface fromtools or parts that fall, objects below shoes, etc.

All standard torque values are given in chapters 20 and 70 Standard Practices.For the standard torque values, the term "tighten" is generally used in the procedures.Non-standard torque values are specified in the procedure concerned.For the non-standard torque values, the term "torque" is used followed by the specific torque value.

7. Definition of TermsAn AMM Task can contain WARNING/CAUTIONs. They are located directly before the text to which they relate.· WARNING/CAUTIONs at the beginning of a Task (immediately after the Task title) are applicable to all the

Task.· WARNING/CAUTIONs at the beginning of a Procedure paragraph are applicable to all the Procedure.· WARNING/CAUTIONs immediately before a work step are applicable to that specific work step.

The following terms are used in the AMM and are defined as follows:

NOTE: Calls attention to methods which make the job easier or provide supplementary or explanatory informa-tion.

WARNING : CALLS ATTENTION TO USE OF MATERIAL, PROCESSES, METHODS, PROCEDURES OR LIMITS WHICH MUST BE FOLLOWED PRECISELY TO AVOID INJURY OR DEATH TO PERSONS. CAUTION : CALLS ATTENTION TO METHODS AND PROCEDURES WHICH MUST BE FOLLOWED TO AVOID DAMAGE TO EQUIPMENT.

8. Aircraft Status for MaintenanceThe following items shall be considered as the basic A/C configuration, before you start a maintenance task:· Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position

on the landing gear).· Engine shut down, thrust reversers closed and locked.· Aircraft in clean configuration· Parking brake applied.· Aircraft electrical network de-energized.· Hydraulic systems depressurized.· Access to the cockpit and cabin is available.· All circuit breakers are in closed position.· All controls in NORM, AUTO or OFF position.



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In case a specific aircraft configuration is required during a maintenance procedure, a specific paragraph"aircraft configuration" is provided at task level.

9. Replacement of EquipmentThe instructions for the replacement of equipment are given in the Removal/Installation topics.However, it is necessary to make sure that the replacement equipment has either the same PN as the removedequipment or an approved interchangeable PN.For some computers, the "LRU IDENT" function on the MCDU gives the P/N in addition to the identificationplate on the front face of the computer.

10. General recommendations related to the risk of human error during maintenanceAIRBUS makes these general recommendations because:· if a maintenance team does the same task on different components of the same type during the same

maintenance event and:· if the team makes a maintenance error,

there is a risk that the same error and the same failure will occur on all these components at the sametime.Thus, AIRBUS recommends:

· that operators do not do maintenance on different engines or redundant components installed on the sameaircraft at the same time unless it is not possible to do differently.

· that, if it is necessary to do maintenance on more than one engine or on redundant components at the sametime, different maintenance teams do the work on each engine or component.

If an engine run is necessary to perform a maintenance task, make sure that only the related (one) engine is inoperation at the time unless the task gives other specific instructions.

11. Functional Item Number (FIN)A. General Description

The equipment on the A/C is identified by a unique identifier designated Functional Item Number (FIN). Thebasic element of the FIN is a two letter code indicating to which System/Circuit the equipment belongs. Tothis code are added prefixes and/or suffixes which provide the unique identification for individual items ofequipment.

NOTE: Several identical components which perform the same function in the same circuit can be differenti-ated by the suffix number. The general rule is that an even suffix identifies a component on the righthand side and an odd suffix identifies a component on the left hand side.

NOTE: A complete list of system/circuit letter codes and an explanation of the FIN breakdown can be foundin the Introduction of the Aircraft Schematic Manual (ASM), Aircraft Wiring Manual (AWM) and Air-craft Wiring List (AWL).

B. Electrical FIN(1) Format

For electrical equipment (any component with an electrical connection) the FIN could be for example1CC1 which is broken down as follows: · 1: Sequence number (4 digits)· CC: System circuit letter (2 digits)· 1: Suffix (3 digits)

(2) ConnectorsConnections to components shall be identified by a suffix letter (or two for multiple connection parts)following the circuit identification. Example: 10CC1-A· 10: Sequence number· CC: System circuit code· 1: Suffix· A: Plug identification



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This will identify plug A on the 10th component in the circuit CC. If there are several connections, theother plugs shall be identified A, B, C, D, etc.. Example 1: 10CC-B· 10CC: Component identification· B: Plug identificationExample 2: 10CC-AA· 10CC: Component identification· AA: Multiple connection identification

NOTE: Connectors on equipment fitted on mountings are identified with reference to the equipment butnot with reference to the mounting. As a general rule, the connector PNs given are for connectorwithout contacts.

(3) Fictitious componentsAll components not specifically related to a circuit are identified by fictitious circuit letter V. The secondletter defines the type of component.(a) VC A/C electrical connector

Example: 12VCAThe electrical connector is identified in fictitious circuit VC by a numerical designator. Example: 3003VC013-A· 3003: Sequence Number· VC: Fictitious circuit letter· 013: Location / suffix· A: Plug identification letter

(b) VN ground pointsThe ground point is identified in fictitious circuit VN by a numerical designator taken from thecomplete aircraft.

(c) VG ground terminal blockThe ground terminal block is identified in fictitious circuit VG by a numerical designator taken fromthe complete aircraft.

(d) VP pressure seal/feed thruThe pressure seal/feed thru is identified in fictitious circuit VP by a numerical designator. Terminalidentifications are indicated to define a precise feed thru identifier for each wire (in the case of wire towire feed thru).

(e) VS SplicesSplices are identified like equipment, being grouped by route and by type. Such grouping shall notbe systematic, but only accomplished where a priority is required. Identification shall consist of anumerical designator, identifying the group in fictitious circuit VS, and an alpha designator givingconnection identification per unit.

(f) VT terminal blocks1 The terminal block is identified in fictitious circuit VT by a numerical designator.2 Shunt connections for modular type terminals are identified in the Extended

Wire List by the letter M followed by a sequence number.Interconnected pins of a terminal block module have the same sequence number.On Wiring diagrams these pins are shown together in one square.

(g) VD diode moduleThe diode module is identified in fictitious circuit VD by a numerical designator. Example: 3100VD.

(h) VE, VU, VM (ICP/ Integrated Control Panel) Panel & racksThe panels & racks are identified in fictitious circuit VU/VE/VM by a numerical designator. Example: 2416VU· 2416: Component number· VU: Fictitious circuit code for panel



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There are several panels and racks (circuit VE/VU) with the same function butdifferent configuration in the A/C. The FIN of these components have one or twoadditional letters between the circuit letter and the suffix.

Example:· 2040VU A 010· 2040VU B 010· 2040VU AB 010Component identification: 2040VU· A: first configuration· B: second configuration· AB: third configuration

suffix (position number on the A/C): 010That means: There are several Passenger Service Unit (PSU) in the aircraft with 1, 2 or 3 readinglights. These PSUs all have the same basic layout and function but different features. Example:· PSU with 1 reading light: 2040VUA5, 2040VUA88, 2040VUA123; PSUs have same PN and they

are interchangeable.

· PSU with 2 reading lights: 2040VUB5, 2040VUB64, 2040VUB112;PSUs have same PN and they are interchangeable.

· PSU with 3 reading lights: 2040VUAB5, 2040VUAB99, 2040VUAB106;PSUs have same PN and they are interchangeable.

(i) VX Printed Circuit BoardPrinted Circuit Board (PCB) made by an Aircraft Manufacturer is a Drawn Part Assembly whichcomprises Active and Passive Items/Components.

C. Mechanical FINFor mechanical equipment, the FIN is similar to electrical FIN.The circuit letter serves to differentiate between mechanical and electrical equipment. The circuit letter M isreserved for mechanical FINs.Example: 2381HM (mechanical FIN has "M" as second letter).

12. Units of MeasurementA. Symbols

------------------------------------------------------------------------------- ! US. CUSTOMARY SYSTEM ! SI-METRIC MEASUREMENT SYSTEM ! !-----------------------------------------------------------------------------! ! ABBREVIATION ! DEFINITION ! ABBREVIATION ! DEFINITION ! !------------------!--------------------!------------------!------------------! ! deg.F ! Degrees Fahrenheit ! deg.C ! Degrees Celsius ! ! ft. ! Foot ! m ! Meter ! ! USgal ! US Gallon ! l ! Liter ! ! USquart ! US Quart ! l ! Liter ! ! in. ! Inch ! mm ! Millimeter ! ! in.2 ! Square Inch ! mm2 ! Square Millimeter! ! in.2 ! Square Inch ! cm2 ! Square Centimeter! ! lb ! Pound ! kg ! Kilogram ! ! lbf ! Pound Force ! daN ! Deca Newton ! ! lbf.in ! Pound Force-Inch ! m.daN ! Meter deca Newton! ! ! (Torque) ! ! ! ! lbf.ft ! Pound Force-Foot ! m.daN ! Meter deca Newton! ! ! (Torque) ! ! !



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! in.Hg ! Inch of Mercury ! hPa ! Hecto Pascal ! ! oz ! Ounce (Weight) ! g ! Gram ! ! psi ! Pound Square Inch ! bar ! Bar ! ! USgal.min ! US Gallon per ! l.min ! Liter per minute ! ! ! minute ! ! ! ! lb.min ! Pound per minute ! kg.min ! Kilogram per ! ! ! ! ! minute ! ! USgal.min ! US Gallon per ! l.min ! Liter per minute ! ! ! minute ! ! ! ! ! ! cc ! Cubic Centimeter ! ! ! ! ! ! -------------------------------------------------------------------------------

B. Conversion Tables ------------------------------------------------------------------------------ FROM: S.I.MEASUREMENT TO: US CUSTOMARY SYSTEM SYSTEM ----------------------------------------------------------------------------- 1 bar = 14.5037 psi 1 mm2 = 0.0016 in.2 1 cm2 = 0.1550 in.2 1 daN = 2.2481 lbf 1 g = 0.0353 oz 1 hPa = 0.0295 in.Hg 1 kg = 2.2046 lb 1 kg.min = 2.2046 lb.min 1 l = 0.2641 USgal 1 l = 1.057 USquart 1 l.min = 0.2641 USgal.min 1 mdaN = 88.4956 lbf.in 1 mdaN = 7.3801 lbf.ft 1 m = 3.2809 ft 1 mm = 0.0394 in 1 cm3 = 0.06102 in3 1 hPa = 0.0145 psi Temperature conversion from degrees Celsius (deg.C) to degrees Fahrenheit (deg.F): deg.F = 1.8 x deg.C + 32 ------------------------------------------------------------------------------- FROM: US CUSTOMARY SYSTEM TO: S.I. MEASUREMENT SYSTEM ------------------------------------------------------------------------------- 1 psi = 0.0689 bar 1 in.2 = 645.1600 mm2 1 in.2 = 6.4516 cm2 1 lbf = 0.4448 daN 1 oz = 28.3495 g 1 in.Hg = 33.8640 hPa 1 lb = 0.4536 kg 1 lb.min = 0.4536 kg.min 1 USgal = 3.7854 l 1 USgal.min = 3.7854 l.min 1 USquart = 0.9464 l 1 lbf.in = 0.0113 mdaN 1 lbf.ft = 0.1356 mdaN



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1 ft = 0.3048 m 1 in = 25.4 mm 1 in3 = 16.3871 cm3 1 in.Hg = 0.491 psi Temperature conversion from degrees Fahrenheit (deg.F) to degrees Celsius (deg.C): deg.C = 0.5555 x (deg.F - 32)

End of document

introduction manual

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