a330 Aircraft General l2 e

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Training Manual A 330

ATA 00–07 AIRCRAFT GENERAL Level 2 Hangar

14-apr-2009 Maintenance Training Organisation

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THE TRAINING MANUAL IS TO BE USED FOR TRAINING PURPOSES ONLY AND IS NO SUBJECT TO REVISION SERVICE. THIS TRAINING MANUAL SHALL NOT BE USED FOR AIRCRAFT MAINTENANCE OR FLIGHT OPERATIONAL PURPOSES. USE OF THIS TRAINING MANUAL BY OR FOR THIRD PARTIES WITHOUT PRIOR PERMISSION FROM ALITALIA S.P.A. IS PROHIBITED.

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TABLE OF CONTENTS ATA 00-00

CIRCUIT IDENTIFICATION……….………..0 FUNCTIONAL ITEM NUMBER…….……….0

ATA 06-00

GENERAL………………………………………1 AIRCRAFT DIMENSION………………………2 AIRCRAFT REFERENCE AXIS……………….4 AIRCRAFT ZONING………………………….10 MAJOR ZONES………………………………. 10 SUB ZONES……………………………………12 ZONES………………………………………….12 PANELS PRESENTATION……………………14

ATA 07-10

JACKING………………………………………16 AIRCRAFT JACKING…………………………16 JACKING FOR WHEEL CHANGE…………...18

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MAINTENANCE TRAINING ORGANISATION    AIRCRAFT GENERAL CIRCUIT IDENTIFICATION – FUNCTIONAL ITEM NUMBER

ATA 00-00

CIRCUIT IDENTIFICATION FIN – FUNCTIONAL ITEM NUMBER

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CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION Equipment on the A/C is identified by a unique identifier designated the Functional Item Number (FIN). Used in numerous manuals, the FIN uniquely identifies an item performing a function in an A/C system. The FIN is composed of: - a two-letter code indicating to which system and circuit the equipment belongs to, - prefix (sequence number) and/or suffixes which provide the unique identification for individual items of equipment, the prefix indicating the position in the circuit. An item performing the same function in the same system throughout the A/C can have the same basic FIN with different suffix numbers, (generally odd numbers for left hand side, even numbers for right hand side). A complete list of system/circuit identifiers is given in the introduction of the wiring manuals - Aircraft Schematic Manual (ASM)/Aircraft Wiring Manual (AWM). Here is an example of a list of the circuit identifications.

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FIN PRESENTATION

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FIN PRESENTATION

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FIN PRESENTATION

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CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION (continued) ELECTRICAL EQUIPMENT For electrical equipment (any component with an electrical connection), the prefix (sequence number) will be below 5000. Here is an example for the electrical and electro-mechanical systems/circuits.

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FIN PRESENTATION - ELECTRICAL EQUIPMENT

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CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION (continued) CONNECTORS Connectors which are part of an item have the same FIN number as the item, with the addition of a letter after the suffix characters.

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FIN PRESENTATION - CONNECTORS

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CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION (continued) MECHANICAL EQUIPMENT For mechanical equipment (without electrical connection), the prefix will be above 5000. Here is an example for the mechanical equipment.

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FIN PRESENTATION - MECHANICAL EQUIPMENT

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CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION (continued) FICTITIOUS COMPONENTS All components, not specifically related to a circuit, are identified by the fictitious circuit letter V. The circuit letter defines the type of component. The panels and racks are identified by the letters VU or VE.

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FIN PRESENTATION - FICTITIOUS COMPONENTS

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CIRCUIT IDENTIFICATION PRESENTATION (1)

PLACARDS As a general rule, operating or installation instructions, directional movement instructions, servicing, part or position identifications, rescue and evacuation instructions and safety precautions shall be marked with placards, nameplates stencils or markings. Here are various examples: - safety placard, - fin placard, - component placard, - operational placard.

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PLACARDS

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TIME LIMITS AND MAINTENANCE CHECKS (1)

SCHEDULED / UNSCHEDULED MAINTENANCE CHECKS IN THE AMM / MPD This chapter includes the following sections: - scheduled maintenance tasks and checks, - unscheduled maintenance checks.

SCHEDULED MAINTENANCE TASKS & CHECKS - IN MPD This Chapter 05-20-00 "Life Limits and Maintenance Checks" is now covered in the Maintenance Planning Document (MPD). The MPD is the repository document for all repetitive scheduled maintenance tasks promulgated by Airworthiness Directives (AD/CN), All Operator Telex (AOT), Inspection Service Bulletins (ISB), Service Information Letters (SIL), and Modifications (MOD/SB) and analyzed under the Maintenance Review Board (MRB).

UN-SCHEDULED MAINTENANCE - IN AMM SECTION 05-50-00 This Chapter 05-50-00 includes the maintenance checks that you must do when a flight crew report shows abnormal flight conditions. Such maintenance actions are divided into two categories of information: - inspections, - checks.

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SCHEDULED / UNSCHEDULED MAINTENANCE CHECKS IN THE AMM / MPD - SCHEDULED MAINTENANCE TASKS & CHECKS IN MPD & UN-SCHEDULED MAINTENANCE - IN AMM SECTION 05-50-00 GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)  PART 2 OUT OF 2

05 TIME LIMITS AND MAINTENANCE CHECKS (1)

Mar 15, 2007 Page 791

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TIME LIMITS AND MAINTENANCE CHECKS (1)

SCHEDULED REPETITIVE REQUIREMENTS THROUGH MPD The main objective of the MPD document is to provide maintenance planning information necessary for each operator to develop a customized maintenance program. MPD reflects all repetitive scheduled maintenance tasks promulgated by AD/CN, AOT, ISB, SIL, and MOD/SB and analyzed under the MRB. A typical scheduled repetitive task (Integrated Drive Generator (IDG) scavenge filter) is listed with the following data: - the threshold interval, source document, cross-references to other manuals or documents (Aircraft Maintenance Manual (AMM) and SIL), - Man Hours required to accomplish the work, - the applicability in this Envelope document. Note the Zonal inspection, requested by C CHECK interval, on the tension of the fan cowl latches, the AOT, AMM and SIL cross-referenced. Some maintenance tasks have a higher ranking of requirement, when the maintenance requirement is identified as: - "Airworthiness Limitations Item" (ALI) or "Life limit parts", - "Certification Maintenance Requirements" (CMR). The approved document MRB REPORT Appendix 1 lists all these airworthiness approved issues, the ALIs and CMRs. The MPD details these airworthiness related items in the "Time controlled Items" and "Life Limits" sections. It is the responsibility of each operator to adjust his own maintenance program in accordance with his National Authority.

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SCHEDULED REPETITIVE REQUIREMENTS THROUGH MPD

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INTRODUCTION 1. PURPOSE This Illustrated Parts Catalog (IPC) is intended only for use in identifying, provisioning, requisitioning, storing and issuing line replaceable aircraft parts and units. This document includes PIPC items related to the AMM tasks. A separate Power Plant Illustrated Parts Catalog is issued for this purpose covering all associated chapters. The IPC is a companion to the Maintenance Manual and includes all parts for which maintenance practice has been provided. AIRBUS expressly disclaims any and all responsibility for data added, deleted and/or revised by airline/operator initiated modifications to this document. Part numbers shown in this document, arrangement and breakdown sequence of items are compatible with Air Transport Association (ATA) specification 100, Rev. 26. 2. CUSTOMIZATION The customized Illustrated Parts Catalog contains only the detailed parts list and numerical index information applicable to a particular customer or group of customers. The illustrations are not customized and may contain parts and item numbers not applicable to a particular customer,therefore these items will not appear in the detailed parts list of this Illustrated Parts Catalog. The customer code and the revision date appear at the top of the screen for the complete manual. The latest revision date for each figure is valid at the figure itself. 3. GENERAL SYSTEM OF ASSEMBLY ORDER - DETAILED PART LIST (DPL) The indenture system used in the detailed parts list shows the relationship of parts and assemblies to next higher assemblies or installations in assembly order as follows: 1

2

3

4

5

6

7

INSTALLATION . DETAILED PARTS FOR INSTALLATION . ASSEMBLY . ATTACHING PARTS FOR ASSEMBLY *** . . DETAILED PARTS FOR ASSEMBLY . . SUB-ASSEMBLY . . ATTACHING PARTS FOR SUB-ASSEMBLY *** . . . DETAILED PARTS FOR SUB-ASSEMBLY file:///F|/ServiceDispatch%208.htm (1 di 8)16/05/2009 19.54.36

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. . . SUB-SUB-ASSEMBLY . . . ATTACHING PARTS FOR SUB-SUB-ASSEMBLY *** NOTE: Dots preceding the item designation indicate the indenture level. 4. AIRBUS PART NUMBERING SYSTEM AIRBUS for its proprietary parts, assemblies establishes part numbers.These part numbers are based on the engineering drawing that defines that part and assembly.The first nine digits of the part number reflect the drawing reference. The next three digits are the sequential part numbers. An addition three digits are available to define a delivery configuration which may be developed for spare parts. Example: DRAWING REFERENCE 27F57551054 BASIC PART NUMBER

F57551054000

FULL PART NUMBER

F5755105400051A

A. PART NUMBER POSITION MEANINGS: 27 F 57 5 5 1054 000 51A XXXX | |

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|__ Additional(see note 4)

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| |___Customized color scheme

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|___Technical specification

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|__Part sequential number in drawing

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|__Drawing sequential number

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| | |__Design office responsibility

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| |__ATA sub system (section)

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|__ATA system (chapter)

number suffix (see note 3)

| |__A/C model drawing set (see note 2) |__Numeric prefix (see note 1)

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NOTE: There may be a numeric prefix preceding the part number which is sometimes used internal to AIRBUS.The prefix is not included in the part number, although it may sometimes be seen on parts or shipping documents.This is typically done in different print styles, and is easily distinguished from the part part number when understood. These prefixes are not reflected in the IPC, and are NOT TO BE USED FOR ORDERING PARTS. NOTE: The initial alpha code indicates which aircraft-model drawing set the part was developed for, but parts may be used on different models of aircraft without changing the alpha code. Thus a part with an alpha code of "A" might be installed on the A340, for example. ALPHA CODES: - A-A300, A310, A300-600 models drawing set - B-A310 model, electrical drawing only. - D,E-A318, A319, A320, A321 models drawing set - F,G-A330, A340 models drawing set - L-A380 model drawing set NOTE: The suffix is normally two or three digits. The 2-digit technical specification number is used to describe delivery configuration for parts, which may be different from the production drawing to facilitate installation as a replacement part. These differences are typically things like: holes left undrilled; consumable hardware included with component; re-usable panels omitted; etc. Specific differences from the production drawing are detailed in the Spares Technical Specification (STS) sheet.

An alpha character may be included, normally in the 13th or 15th position, to indicate a customized color scheme on the component. This color indicator may appear with the 12-digit basic part number, or in conjunction with the Technical Specification Number. NOTE: There may be an alpha/numeric character following the 15 digits part number, which is sometimes used internal to Airbus. The additional characters are not included in the part number as listed in the IPC. This is typically done in different print styles and is easily distinguished from the part number when understood.In all cases the part number will be interchangeable, 2 way with the amended part number. B. IMPLICATIONS OF TECHNICAL SPECIFICATION: Parts which have identical 12 digit basic part numbers are interchangeable provided STS differences are incorporated during part replacement. (For example, re-usable panels must be recovered from the removed component, if that is a specified difference). Parts produced for factory installation, or for spares support and exactly in accordance with the production drawing, are assigned Technical Specification "00". Some of these parts were marked with the 12-digit basic part number only. These parts are equivalent to parts with Technical Specification "00". Therefore the basic part number is not included in the IPC, but is understood to be identical to the 14-digit part number ending in "00". C. CATEGORIES OF TECHNICAL SPECIFICATIONS: Technical Specification Description 00

Items complying with drawings. Procurable parts

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01 to 19 (refer to STS) Items not complying with drawings. Suffix changes each time production makes a definition change. Procurable parts 20 to 24 (refer to STS) Items not complying with drawings. Reserved for suppliers (subcontractors). Procurable parts 25 to 29

Suffix changes each time production makes a definition change (not IPC relevant). Non procurable parts.

30 to 39 (refer to STS) Items not complying with drawings. Procurable parts. 40 to 49

Items complying with drawings. Definition changes that do not require a PN change. Procurable parts.

50

“Spares” complying with drawings rarely used. Procurable parts.

51 to 59 (refer to STS) “Spares” not complying with drawings. Specific definition to facilitate line maintenance. Procurable parts. 60 to 89

Installations not complying with drawings. Non procurable parts.

90 to 94 (refer to STS) Items specific to repair kits. Used to identify a part repaired during a working party. Procurable parts. 95 to 98

Items specific to modification kits. Used to re-identify a part after Service Bulletin retrofit (reworked). Procurable parts.

99

Installations complying with drawings. Non procurable parts.

Letters B,C,D,E

Items subject to harmony. Procurable parts.

AA to ZZ

”Electro-mechanical” and spare constituent assemblies. Procurable parts.

5. HOW TO SEARCH IN THE IPC Main options are available as follows: - *Word search is based on the Detailed Parts List content. *PN location on the A/C is based on the alphanumerical index (IPC menu). *PN valid for the A/C is based on the alphanumerical index. Relation between basic part and parts used as replacement is available on the alphanumerical index (IPC menu). *PN data may be listed and filtered by the user in accordance with the need. The result is available on EXCEL form (IPC menu “Download only”) *PN related to a FIN may be listed and filtered by the user in accordance with the need. The result is available on EXCEL form (IPC menu “Download only”) *PN location based on the FIN (IPC menu) *PN location based on the access door/panel (IPC menu). 6. DESCRIPTION OF IPC CONTENT The Illustrated Parts Catalog (IPC) lists data related to the line maintenance parts. Following data are available: A. Access door / panels This is a specific code allocated that allows the localization of the part in the IPC. B. Airworthiness Directive (AD) The reference of the AD is listed just after the PN concerned by the limitation. It is possible to have the “Consigne de Navigabilite”(CN) in addition. For parts related to engines, refer to specific information given in the manufacturer Service Bulletin. C. Alpha—numerical index This allows the search from a part number to the affected IPC figure where the part number is file:///F|/ServiceDispatch%208.htm (4 di 8)16/05/2009 19.54.36

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listed. D. Alternate This allows the replacement of the basic part number by re-worked one . E. As required (AR) This value is shown in the IPC when the user installs the part in accordance with the need on the A/C. e.g. For certain bulk items such as items cut from raw stock, or common hardware items with large quantity usage and for items such as shims where quantity must be determined upon installation, F. Attaching parts Attaching parts are listed immediately following the item they attach and at the same indenture level. The first item is preceded by the phrase “Attaching parts” and the last one is followed by the symbol “***”. Quantity shown is the quantity required to attached one part. G. BUY "BUY PN XXXXXXXX" identifies an item, which is recommended as spares purposes. H. Buyer Furnished Equipment (BFE) Identifies a part, which is furnished by the customer to AIRBUS to be installed in the A/C such as megaphone, life vest etc…. In accordance with the agreement (availability of data) between the customer and the vendor, all data and documents related to the part have to be available in the IPC J. Component Maintenance Manual (CMM) “CMM XX XX XX” identifies the reference of the document providing detail coverage of the item shown in the part number column. NOTE: Where a CMM exceeds 100 pages, the note is IPC instead of CMM in accordance with the ATA specification. NOTE: The abbreviations TDS (Technical Data Sheet), IPC (Illustrated Parts Catalog), ACMM (Abbreviated Component Maintenance Manual), CMS (Component Maintenance Sheet) and OM (Overhaul Manual) can be found as well. K. Concession the reference of the concession is shown after the part directly concerned by this change. L. Customer Of Change (COC) On customer request, some data will be integrated in the AIRBUS documentation with the customer agreement. The disclaimer clause confirms the customer responsibility. AIRBUS HEREBY EXPRESSLY DISCLAIMS ANY AND ALL WARRANTIES, EXPRESSED OR IMPLIED, ORAL OR WRITTEN, ARISING BY LAW, COURSE OF DEALING, OR OTHERWISE, AND WITHOUT LIMITATION ALL WARRANTIES AS TO QUALITY, OPERATION, MERCHANTABILITY, FITNESS FOR ANY INTENDED PURPOSE, AND ALL OTHER CHARACTERISTICS WHATSOEVER, OF CUSTOMER ORIGINATED CHANGES INCORPORATED INTO THE TECHNICAL DATA ISSUED BY AIRBUS. THE FOREGOING DISCLAIMER SHALL ALSO APPLY TO ANY OTHER PORTION OF AIRBUS TECHNICAL DATA WHICH MAY BE AFFECTED BY SUCH CUSTOMER ORIGINATED CHANGES. The content of the requirement is valid for the customer only. The corresponding AIRBUS definition is invalidated for this customer too.

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M. Detail (SEE XX XX XX FOR DET) This cross-reference indicates where the installation or assembly is broken down to its component parts. N. Detailed Parts List (DPL) The DPL is a part of the IPC where end items parts are listed in accordance with an item sequence. These parts are listed at the first item with the indenture 1. A generic text like “FOR OPERATING LIMITS/DATA, REFER TO xx xx xx xx FOR NHA” is listed after each part. Their respective breakdown parts are listed in cascade in the detailed figure P. Effectivity (EFF) The effectivity shows on which A/C the parts can be installed. The effectivity is given in FSN (Fleet Serial Number). The effectivity shown is called “SPARES Effectivity”. The Spares effectivity is given in accordance with the interchangeability code between the parts and the A/C configuration. The absence of a restrictive effectivity at all items in one IPC figure indicates that the part is effective for all aircraft of a customer’s fleet. The absence of a restrictive effectivity at one item in one IPC figure indicates that the part is effective for the same A/C available at the item above with an effectivity. NOTE: In addition, refer to “Interchangeability”, “Restrictive Usage” (RU) and “Effectivity Engine Serial Number” (EFF//ESN) paragraphs. Q. Effectivity Engine Serial Number (ESN) This concerns only the Power Plant data merged in the AIRBUS IPC. The evolutions of the PIPC data have an effectivity in Engine Serial Number under the engine manufacturer directives. The Spares Effectivity between parts is not shown in FSN in the AIRBUS IPC, but replaced by a standard “EFF//ESN””. Information related to the parts replacement is detailed in the Vendor Service Bulletin only. R. ETOPS To identify parts with a restricted usage on ETOPS (Extended range Twin engine OperaTionS) aircraft, the following notes appear in the IPC as follows: “NOT APPROVED FOR ETOPS” “NOT APPROVED FOR ETOPS AFTER (date)” “NOT APPROVED FOR ETOPS WITHOUT (SB xxxx) AFTER (date)” NOTE: When the ETOPS notes is shown in the IPC immediately below the description corresponding to the basic PN, then the ETOPS information is linked to the basic PN. NOTE: When the ETOPS note is shown in the IPC immediately below the RPLD BY or I/W PN, then the ETOPS information is linked only to this PN. NOTE: ETOPS notes are in accordance with the ETOPS parts list which is extracted from the latest available Configuration, Maintenance and Procedures document (CMP) reference: AI/EA 5000. NOTE: Even though a part may be physically interchangeable with an ETOPS part, it must not be installed on an ETOPS aircraft. S. Figure number (FGN) file:///F|/ServiceDispatch%208.htm (6 di 8)16/05/2009 19.54.36

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The figure number refers to the corresponding illustration. Should modifications or system variants necessitate an additional figure, this will be introduced with a sequential alpha-suffix, for example, a modified version of Figure 1 would be Figure 1A; further variant of the same figure would be Figure 1B, and so on. T. Functional Item Number ( FIN ) Each part with precise function within an A/C system is defined with a specific identifier called FIN . The FIN is unique in the A/C. U. Illustrations (ILL) The illustrations are parts of the IPC where the parts listed in the DPL are illustrated. In addition, the illustrations show: - the location of the item by ribs in pylons, wings, vertical and horizontal stabilizers, by frames in fuselage by zones. - the continuation of the system when the first 6 digits are different. - FIN , access door and panels ref. - the data content of some IPC figures related to the Power Plant Data. Illustrations are not customized and some items are not in the detailed parts list. V. Indenture (IDENT) The indenture shows the relation between an assembly and its breakdown parts. The relation is shown by one or several dots (“.”) in accordance with the structure of the assembly. W. Interchangeability (INC) The spares effectivity shown in the IPC, is the result of the combinations between parts installed at the A/C configuration and the interchangeability code between these parts. The interchangeability code is not available in the IPC. Only the spares effectivity shows on which A/C (in FSN), the part can be installed as spares. The A/C configuration is not affected. NOTE: Refer to EFFECTIVITY paragraph. X. Item number (ITEM) An item number is assigned to each part listed in the detailed parts list. Item numbers are broken in sequence for the insertion of additional items. Item number preceded by “-” is not illustrated. Y. Local Manufacturer (LM) "*LM*" identifies a part which can be locally manufactured by the airlines. Raw materials used are listed in the IPC with their respective quantity or dimensions. AA. Manufacturer code (MNFR) Five-digit code shown for Vendor item. The generic definition is “CAGE” (Commercial And Government Entity). NOTE: The vendor names and addresses corresponding to each ”CAGE” is available. NOTE: when “CAGE” is a standardization office, optional vendors are available AB. Next Higher Assembly (SEE XX XX XX FOR NHA) This cross-reference indicates the figure number where the lead item is listed in quantity.

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AC. Not illustrated part Parts with item numbers preceded by a dash are not illustrated. AD. Not Procurable (NP) NP” indicates that this item is not procurable . The reference shown in the IPC is fictitious and is not systematically based on an existing drawing. Drawing references and effectivity are managed in the Drawing set Part usage data available on AirbusWorld portal in the 'Mechanical Drawings' service. NOTE: In the drawing set , a search based on a “NP” reference in the IPC, will result in a denied access when the drawing is not effective for the concerned MSN or fleet. AE. Optional (OPT) Fully replaceable with the basic part in all locations on the A/C. AF. Overlength Such a part number requires the introduction of a dummy part number with a cross reference to the overlength part number. This will be shown in the parts list as follows: "ORDER OVRLGTH MPN XXXXXXXXXX (VXXXXX)" AG. Oversize/undersize (OVR) Identifies the oversize or undersize part to replace the part installed in line maintenance. Parts shown as "oversize/undersize" in the IPC, indicate the parts which can be used on the A/C in the order given. The order is defined from the part removed. When the part removed has to be changed, the mechanic must select the following part listed in the IPC. To respect correct installation, mechanic has to follow the instructions given on the installation drawings. These parts are listed in the IPC. Except for the basic part, all other parts are listed in the IPC as not illustrated items. The items concerned are in sequence 1 by 1 (e.g. 010, -011, -012). Each part is separated by "OVERSIZE/UNDERSIZE" in the "NOMENCLATURE" column of the DPL. AH. Part Number (PN) Part identifier containing up to 15 digits (combination of alpha, numeric and dash as applicable). When the part identifier is more than 15 digits, refer to Overlength paragraph. AJ. Quantity (QTY) The quantity of the part used in one next higher assembly or installation is available in the DPL. For total quantity per aircraft for one location refer to alpha-numerical index. NOTE: In addition, refer to “As required” AK. Qualified spares (RPLD BY, I/W) " X RPLD BY Y" (replaced by)

Text continues : see text below

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Text continues : see text above when A/C basically delivered with PN X, the part number X can be replaced by itself or the new PN Y as spares. This replacement by PN X or PN Y is used without any change in the A/ C configuration. When PN Y is installed as spares, it can be replaced by itself or PN X can be re installed on the same A/C (MSN). when A/C basically delivered with PN Y, the part number Y can be replaced by itself only as spares. This replacement is used without any change in the A/C configuration. When PN Y is installed as spares, it can be replaced by itself only on the same A/C (MSN). when A/C basically delivered with PN X is changed with PN Y by AIRBUS SERVICE BULLETIN, the A/C configuration has been changed. Due to the new A/C configuration, the part number Y can be replaced by itself only as spares. "Y I/W Z" (Interchangeable With) When A/C basically delivered with PN Y, the part Y can be replaced by itself or the new PN Z as spares or vice versa when A/C is basically delivered with PN Z. This replacement is used without any change in the A/C configuration. NOTE: In consequence, when a cascade of parts are "X RPLD BY Y" and "Y I/W Z", the data have to be read as follow: when A/C basically delivered with PN X, the part number X can be replaced by itself, by PN Y or the PN Z as spares. This replacement by PN X, PN Y or PN Z is used without any change in the A/C configuration. When PN Y or PN Z is installed as spares, it can be replaced by itself or PN X can be re installed on the same A/C (MSN). when A/C basically delivered with PN Y, the part number Y can be replaced by itself or the PN Z as spares. This replacement is used without any change in the A/C configuration. When PN Z is installed as spares, it can be replaced by itself or PN Y can be re installed on the same A/C (MSN). when A/C basically delivered with PN X is changed with PN Y by AIRBUS SERVICE BULLETIN, the A/C configuration has been changed. Due to the new A/C configuration, the part number Y can be replaced by itself or the PN Z as spares. NOTE: Some parts listed as spares (RPLD BY or I/W) may have particular spare parts with technical conditions. These conditions are available by couple of parts only. The relation between these parts concerned by the condition are: “IF PN A, SEE PN B” / When the A/C definition is PN A, this relation between PN A and PN B has to be read as follows: PN A can be replaced by the PN A. PN A can be replaced by PN B after applying the technical condition. PN B can be replaced by PN B with technical condition maintained. PN B can be replaced by PN A after the technical condition is removed. “IF PN B, REFER TO PN A” / When the A/C definition is PN B, this relation between PN B and PN A has to be read as follows: PN B can be replaced by the PN B. PN B can be replaced by PN A after applying the technical condition. PN A can be replaced by PN A with technical condition maintained. PN A can be replaced by PN B after the technical condition is removed.

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NOTE: Some parts listed as spares (RPLD BY or I/W) may have particular spare parts with technical condition. These conditions are available by couple of parts only. The relation between these parts concerned by the condition are shown as follows: “IF PN A, SEE PN B” / This relation between parts has to be used as follows: When the A/C definition is PN A, as spares the PN A can be replaced by the PN A itself, or by the PN B after applying the technical condition. Having installed PN B as defined previously, PN B can be replaced by itself or PN A after removing the condition authorising the installation of PN B. “IF PN B, REFER TO PN B” / These relations between parts have to be used as follows: When the A/C definition is PN B, as spares the PN B can be replaced by the PN B itself, or by the PN A after applying the technical condition. Having installed PN A as defined previously, PN A can be replaced by itself or PN B after removing the condition authorising the installation of PN A. AL. Re identification (RE-IDENT) This shows the final partnumber from a preliminary part given for information only. AM. Reference item (REF) Item 001/or 002 are the lead items of the figure.These items are listed for reference purposes with the RF. AN. Restrictive Usage (Ruxxx) When assemblies appearing at indenture 2 level are combined and therefore interchangeable, detail parts indenture level 3 not common to all combined assemblies are so noted. RU 010A (RU= Restricted usage, 010A= Item 010A) means “only used on the assembly defined with item 010A” AP. Revision date of the manual(REVM) This is the date available on the top of the IPC. AQ. Revision date for the latest change (REVF) This date defines the latest revision of the IPC figure. AR. Revision indicator (REVI) Data revised for the latest revision date of the manual are highlighted. AS. “SEL FROM” (SEL) Identifies the part, which is to be selected from a collection of parts. Parts shown as "sel from" in the IPC, indicate the combination of parts or the choice of parts which can be used to install assemblies or main parts on the A/C. To achieve correct installation / adjustment as defined on installation drawings, the mechanic will select parts (e.g. shims with different thicknesses) accordingly. These parts are listed in the IPC. Except for the basic part, all other parts concerned are listed in the IPC as not illustrated items. The items concerned are in sequence 1 by 1 (e.g. 010, -011, -012). Each part is separated by "SEL FROM" in the "NOMENCLATURE" column of the DPL. AT. Service Bulletin reference (AISB) The integration of the PRE/POST AISB in the IPC is in accordance with the policy between AIRBUS and AIRLINES. The reference of the PRE AISB or POST AISB is in the IPC to help users about the redundant effectivity. After airlines reporting the interim PRE/POST AISB configuration is changed in POST AISB only to be consistent with the new A/C configuration.

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AU. Service Information Letter (SIL) The SIL contains additional technical information related to a particular part listed in the IPC. AV. Storage parts (STO) Parts needed to store the next higher assembly are comprised between the words “storage part” and symbol “***”.Quantity shown is the quantity required to store one part. AW. Symmetry (LH) or (RH) A) Parts used on left hand or right hand of symmetrical installations are designated by (LH) or (RH). B) Parts, assemblies or installations used only on one side of the aircraft are designated by "(LH SIDE)" or "(RH SIDE)" AX. Table of Content (TOC) All figures are listed by ATA chapters. AY. Usage Category / Material Group (UC) Usage Category / Material Group values classify the types of parts listed in the IPC as follows: 1. 00 – Ground support equipment 1x – Airbus proprietary parts 2x – Equipment 3x – Standard parts 4x –Tool 5x – Raw material 6x – consumable material (not available from IPC) 7x – Equipment detail parts 8x – AIRBUS mod kits (not available from IPC) 9x – Shop maintenance units (not available from IPC) xx Fictitious references not used as replacement BA. Usage range (UR) Used with “AR” in the “UNIT PER ASSY” column indicates the minimum quantity which may be needed for this location. BB. Variant item number A variant item number is used in order to show a new evolution of a part number. Only the basic item is illustrated 7. INSTALLATION BREAKOUT To aid in rapid location of an illustration, the "subject" part of the CSN (digit 5 and 6) has been assigned as follows: 8. SECTION CHAP. SECT. SUBJ.

LOCATION

DESCRIPTION

XX

XX

01

FR1–FR19

NOSE FUSELAGE

XX

XX

02

FR19–FR38

FORWARD FUSELAGE

XX

XX

03

FR38–FR54

MID (LOWER DECK) FUSELAGE

XX

XX

04

FR38–FR54 and FR54– FR106

MID (UPPER DECK), AFTER FUSELAGE INCLUDING VERTICAL STABILIZER

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XX

XX

05

WING AND WING CENTER BOX

XX

XX

06

PYLONS

XX

XX

07

HORIZONTAL STABILIZER

XX

XX

08

VU panels

COCKPIT AND AVIONIC COMPARTMENT

XX

XX

09

FR1–FR106 (1)

FUSELAGE (GENERAL)

NOTE: (1) used with parts in several subjects or for continuation of subjects 01 to07 NOTE: Subject 00 is not used for IPC figures related to installation. 9. MODEL DESIGNATION ST6 - A330-301: Medium to long-range series with GE CF6-80E1A2 engine - A330-321: Medium to long-range series with PW PW4164 engine - A330-322: Medium to long-range series with PW PW4168 engine - A330-341: Medium to long range series with RR TRENT 768-60 engine - A330-342: Medium to long range series with RR TRENT 772 engine ST7 - A330-201: Medium to long range series with GE CF6-80E1A2 engine - A330-202: Medium to long range series with GE CF6-80E1A4/A3 engine - A330-203: Medium to long range series with GE CF6-80E1A3 engine - A330-223: Medium to long range series with PW PW4168A engine - A330-243: Medium to long range series with RR TRENT 772B/C engine ST8 - A330–301: Medium to long range series with GE CF6–80E1A2 engine - A330-302: Medium to long range series with GE CF6-80E1A4/3 engine - A330–303: Medium to long range series with GE CF6–80E1A3 engine. - A330-323: Medium to long range series with PW PW4168A engine - A330–342: Medium to long range series with RR TRENT772 - A330-343: Medium to long range series with RR TRENT 772B/C engine 10. POWER PLANT DATA The Power Plant Data are shown in specific figures into the AIPC. Specific figures are identified as follows: - By the note 'POWER PLANT DATA' at the bottom of each illustration. The quantity available in the Detailed Parts List indicates the number of part used in one next higher assembly or at the installation level for the aircraft engine set. - By the identification of engine type at the 'REF' level in detail Parts List. Power Plant Data effectivities are normally expressed in engine serial number instead of FSN / MSN. Consequently, the 'USAGE FROM TO' column should not be considered for determining spares effectivities / interchangeability. All variants configurations existing for a type of engine, are described in the same Detail Parts List. Interchangeability related to these parts, is available in the engine or nacelle service bulletin only. These Service Bulletins are mentioned in Detail Parts List so all items associated to an engine or nacelle Service Bulletin have an “EFF//ESN” effectivity expression in the “USAGE FROM TO” column. NOTE: EFF//ESN means EFFectivity//Engine Serial Number. 11. LAVATORIES LOCATION

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-

3E APU generator energization 6E Emergency excitation

C. Electronic Wiring Three main route functions are provided in electronic wiring: R, T, U ROUTES FUNCTION - 1R System 1 radio communication and radio navigation - 1T VHF 1 - 2T VHF 2 - 3T ATC 1 and ATC 2 - 4T DME 1 and DME 2 - 5T Radio altimeter 1 - 6T Radio altimeter 2 - 7T HF 1 - 8T HF 2 - 9T VHF 3 - 1U VOR 1 - 2U VOR 2 - 3U Glide GP 1 - GP 2 - 4U Localizer GP 1 - GP 2 - 5U Marker - 7U ADF 1 - 8U ADF 2 D. Route Segments (1) In general, identification of the route is sufficient to specify without risk of confusion, the routing of an electrical cable between two points provided that both ends are designated (e.g. the case illustrated below: for routing from A to B).

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(Item A) (2) Where a number of possibilities exist, the wire segments must be called up. (Item B) Called up are the route segments described below: - 1M-C : Rear of LH side rack routing to flight compartment ceiling - 1M-B : Junction in turbine containment zone - 2M-C : Same as 1MC - 2M-B : Same as 1MB E. Routing representation

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** ON A/C ALL 9. Ground Point Identification Grounding is achieved in two ways: - direct - ground loop circuit (s). In the case of ground loop circuits grounding can be accomplished through several circuits. These circuits are filed under chap. 24. DC as well as AC grounds are identified in the same way as DC and AC circuit: - DC1 power supply & distribution (SYS1). - DC2 power supply & distribution (SYS2). - AC1 power supply (system 1 in normal operation). - AC2 power supply (system 2 in normal operation). - B1 for screen and box bonding (SYS1) (except audio communication). - B2 for screen and box bonding (SYS2) (except audio communication). - S for the intercommunication system Single Point Audio System Equipment (SPASE). Example:

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** ON A/C ALL 8. Wire Identification A. Identification by Number Codes (1) Wire identification Wire idenfication is numerical plus a colour identification when used, dependent on its circuit and independent of its location on the aircraft. Each wire is identified by an 8 digit number composed as follows: Example: 2322-0121R - 2322 : Circuit identification prefix corresponding to ATA 100 numbering (chapter, section). - 0121 : Wire number in circuit (different for each segment) - R : Color (if used). NOTE: The circuit wire number alone shall be shown on the wiring diagram. The ATA 100 correspondence for total identification shall be given in a general note. (2) Ground wire identification Ground wires shall be numbered from 0001 to 8999. These wires shall be shown on circuit VN wiring diagram, i.e. their identification will include the ATA 100 designator for circuit VN: 2491. Example: 2491-1610 NOTE: All direct ground wires are identified by the ATA number of the circuit to which they belong. (3) Spare wire identification Spare wires shall be numbered from 0001 to 8999 with ATA 100 prefix 2499. Example: 2499-1611 (4) Wires added or modified in the aircraft by the customer The wires added or modified in the aircraft by the customer shall be numbered from 9000 to 9999 with the ATA 100 prefix of the corresponding system. Example: 2411-9010 (5) Wires added or modified in the aircraft by product support The wires added or modified in the aircraft by product support shall be numbered from 8000 to 8999 with the ATA 100 prefix of the corresponding system. Example: 2212-8021

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(6) Identification of shielding or shielded wires/ cables (a) Shielding or shielded wires/cables shall be numbered from 7000 to 7999 with ATA 100 prefix of the corresponding systems. Examples: 3411-7500; 7832-7800 (b) Shielding or shielded wires/cables added or modified in the aircraft by the customer. The shielding or shielded wires/cables added or modified in the aircraft by the customer shall be numbered from 9900 to 9999 with the ATA 100 prefix of the corresponding system. Example: 3443-9905 (7) Wires supplied by vendor. Some bundles are supplied by a vendor. They are identified by a FIN, the corresponding PN can be found in the IPC/CMM. Their type is always replaced by YY. In the AIRCRAFT WIRING MANUAL they are identified with special symbols described as follow: - for bundles without vendor wire identification ) - for bundles with vendor wire identification B. Identification by Color Codes A Amber B Blue BK Black BR Brown C Clear G Green GY Grey O Orange P Purple PK Pink R Red V Violet W White Y Yellow C. Types and Gauges Ref. Electrical Standard Practices Manual. (ESPM) Each wire is identified by an alphanumerical code comprising 2 alpha digits followed by 2 numerical digits. Example CF24 where CF = Type and 24 = Gauge.

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D. Sensitive Wires The sensitive wires are identified either by pink sleeves with black printing at their ends or directly on the wire with the S letter indicated after each wire identification (e.g.:2231 0015S) on all wire length. In the WDM, these wires are identified by letter S. NOTE: The presence of this marking indicates to the maintenance personnel that these wires must not be modified. In the event ofan action on these wires, a test of the concerned system is required. E. Wire Connection An upper-case letter preceded by " Example :

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** ON A/C ALL 5. Aircraft Configuration The diagram shall represent the aircraft in the following configurations: - Aircraft on the ground resting on landing gear, - Engines shut down, thrust reversers locked and closed, - Flaps, slats and speed brakes retracted, - Doors and gear doors closed, - Parking brake applied, - Aircraft electrical network deenergized, - All controls in normal, AUTO or OFF position. If, for clarity, it is necessary to depict the equipment in any other configuration, a NOTE must state this specific configuration.

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** ON A/C ALL 6. Electrical and Electronic System and Circuit Identification The marking of systems and circuits is in accordance with the following coding system. A. System identification letters - The letters A and B are reserved for special request by an airline for system references where the system is considered likely to be unique to that airline and not covered by the system letters shown in the table. C - Flight control systems D - De-icing E - Engine monitoring F - Flight instrumentation G - Landing gear H - Air conditioning J - Hydraulics K - Engine/APU control and starting L - Lighting M - Interior arrangement/Passenger service system N - Wiring for negative and/or neutral polarity P - DC generation Q - Fuel R - Radio (navigation & communications) S - Radar , navigation T - Recording V - Fictitious circuits W - Fire protection & warning system X - AC Generation B. Circuit identification The identification number of a circuit consists of 2 letters: the letter of the system followed by a letter identifying the circuit within a system. Example: CA - C : System Identification - A : Circuit Identification C. Identification of circuits (1) C - Flight control systems CA - FMGES - Electrical power supply CB - FMGES - Discretes/analog interfaces CC - FMGES - ARINC bus interfaces CD - EFCS - ARINC buses and discretes interfaces CE - EFCS - Control inputs & power supply

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CF - Flaps position indicating CN - Slats position indicating CS - EFCS - Electrical contol and monitoring of actuation CV - Flaps electrical control & monitoring CW - Slats electrical control & monitoring (2) D - Deicing DA - Probe ice protection DB - Windshield rain protection DD - Ice detection DG - Windshield anti-icing & defogging DH - Escape slide locking mechanism ice protection DL - Wing ice protection DN - Engine air intake ice protection DR - Flight crew foot warmers DS - Ancillary equipment DU - Waste water ice protection DV - Water servicing panels heating DW - Potable water ice protection (3) E - Engine monitoring EG - Thrust reverser opening mechanism EH - Ignition starting and continuous relight EN - Oil indicating & power supply EV - Engine indicating accelerometers (4) F - Flight instrumentation FA - Angle of attack indicating FC - Attitude and heading standby data FH - Head up display (HUD) FN - Radio magnetic information switching and indicating FP - Sensors, power supply and switching FS - Electrical clock FV - Altitude and airspeed standby data FW - Paravisual indicating (PVI) (5) G - Landing gear GA - Normal extension & retraction GB - Indicating and warning GC - Steering GD - Brake cooling GF - Free fall extension GG - Normal braking GH - Nose landing gear - Steering angle protection GK - Alternate braking without anti skid GT - Weight and balance system (WBS) GV - Tire pressure indicating system (TPIS) GW - Brake system temperature

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GY - Alternate braking with anti skid GZ - Parking braking (6) H - Air conditioning HA - Engine bleed air supply system HB - Flow control & indicating HC - Lower deck cargo compartment heating (FWD,AFT and bulk) HD - Avionics equipment ground cooling HE - Cockpit air ventilation HF - Leak detection HG - Cabin air distribution & recirculation HH - Pack control and indicating HK - Cockpit & cabin temperature control HL - Pressure control & monitoring HN - Lower deck cargo compartment ventilation and cooling (FWD,AFT and bulk) HQ - Avionics equipment ventilation HR - Air conditioning compartment ventilation HS - Therapeutic oxygen HT - Control and indicating HU - Lavatory/galley ventilation HV - APU bleed air supply and crossbleed systems HZ - Emergency ram air inlet (7) J Hydraulics JB - Blue main hydraulic power JC - Blue auxiliary power (electic pump) JG - Green main hydraulic power JJ - Yellow auxiliary hydraulic power (electric/hand pump) JL - Ground internal leak test sustem JR - Green auxiliary hydraulic power (ram air turbine) JS - Hydraulic system data acquisition interface and indicating JV - Green auxiliary hydraulic power (electric pump) JX - Power transfer JY - Yellow main hydraulic power (8) K - Engine/APU control & starting KA - Starting KB - Air intake system KC - Engine master control KD - Control and monitoring KL - Emergency shutdown KS - Functional interfaces (FADEC) KT - APU oil heating (9) L Lighting LA - Navigation lights LB - Landing lights LC - Runway turnoff lights

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LE - General illumination LF - Instrument and panel integral lighting LG - General illumination LJ - Service area lighting LK - Air conditioning duct and accessory compt lighting LL - Wheel well lighting LP - Annunciator light test and dimming LQ - Lavatory lighting LR - Taxi and take off lights LS - Avionics compartment lighting LU - Lower deck cargo compartment lighting (FWD,AFT and bulk) LV - Anti-collision/strobe lighting LW - Passenger and cabin attendant lights LX - Wing and engine scan lighting LY - Logo lights (10) M - Interior arrangement/Passenger service system MA - Quantity indicating MB - Distribution MC - Galley supply MD - Air supply boost system ME - Electrical service supply MF - Supplementary medical equipment MG - Toilet system MH - Passenger video entertainment MJ - Door and escape slide contol system MK - Passenger music entertainment ML - Galley cooling MM - Passenger information system MP - Water draining (dump) MQ - Passenger compartment fixed partitions interior doors MR - Passenger compartment seats MS - Cockpit seats MT - Razor supply MU - Main deck cargo loading system MX - Miscellaneous emergency equipment MY - Lower deck cargo loading system (11) N - Wiring for negative and/or neutral polarity NA - Cockpit additional electrical supply NC - Curtains and partitions/Electrical class dividers NG - Cabin escape facilities (12) P - DC generation PB - Battery DC generation PC - DC essential & normal generation switching PE - DC emergency generation (TR) PH - DC essential distribution PN - DC main distribution

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PP - DC ancillary equipment PR - Refuelling on battery PU - DC main generation (TR) PV - DC generation monitoring & indicating PX - DC ground service bus control (13) Q Fuel QA - Main fuel pump system QB - Tanks QC - APU fuel pump system QE - Crossfeed system QF - APU LP fuel shut off QG - Engine LP fuel shut off QH - Additional center tank transfer system QJ - Tank level sensing QL - Main transfer system QM - Fuel control and monitoring system QN - Trim transfer system QQ - Water scavenge QR - Fuel temperature measurement QT - Quantity indicating QU - Refuel/defuel system QV - Jettison system (14) R - Radio (navigation & communications) RB - Aircraft communication addressing & reporting system (ACARS) RC - VHF system RD - Passenger air-to-ground telephone system RE - HF system RF - Cabin management system RF - Cabin information network system RG - Radio management RH - Cabin intercommunication DATA system (CIDS) RJ - Service interphone RK - Cockpit voice recorder (CVR) RM - External video monitoring RN - Audio management (integrating/flight interphone/selcal/call) RP - ADF RQ - Omega navigation system RR - Passenger AM/FM radio system facility RS - VOR/MARKER RT - ILS (MMR) RU - Microwave landing system (MLS) RV - Satellite communication RW - Cabin monitoring RX - Announcement and music tape reproducer system RY - Cabin communications system RZ - Voice privacy system

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(15) S - Radar navigation SA - Radio altimeter SD - DME SG - Traffic collision avoidance system (TCAS) SH - ATC/Mode S (select) SN - Satellite navigation SQ - Weather radar system (16) T Recording TA - Maintenance access terminal system TD - Up and down data loading system acquisition/interface TL - Aicraft information network system (AINS) TM - Central maintenance system acquisition/interface TP - Printer TT - Gate link TU - (FDIU, DFDR, LA, QAR) DFDRS TV - ACMS (DMU, DAR) TX - Air traffic and information management system TY - Tail strike indications (17) V - Fictitious circuits VB - Main wire routing VC - A/C electrical connectors VD - Diode module VE - Panel (Commercial) VG - Ground terminal block VN - Ground points VP - Pressure seal feedthrough VR - Resistor modules VS - Splices VT - Terminal blocks VU - Panels VX - Printed circuit board assembly VZ - Spare wires (18) W - Fire protection & warning system WA - Avionics compartment smoke detection WC - Cockpit to ground crew call system WD - Engine fire & overheat detection WE - Engine fire extinguishing WF - APU fire extinguishing WG - APU fire & overheat detection WH - Lower deck cargo compartment smoke detection (FWD, AFT, bulk) WJ - Lavatory lighted signs WK - DMC /CRT control and interconnection WL - Cabin emergency lighting WM - Ecam control WP - MLG bay fire and overheat detection file:///F|/ServiceDispatcher%202.htm (6 di 7)16/05/2009 19.58.58

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WQ - Lavatory smoke detection WR - Oxygen control and indicating WS - EIS switching WT - DMC - acquisition/interface WU - Main deck cargo compartment smoke detection WV - SDAC - acquisition/interface WW - FWC - acquisition/interface WX - Lower deck cargo compartment fire extinguishing (FWD, AFT, bulk) WZ - Ground proximity warning system (GPWS) (19) X - AC generation XA - Galley supply control XB - Static inverter AC generation XC - AC essential generation switching XD - Circuit breaker monitoring XE - AC emergency generation (CSM/G, GCU) XG - AC external power control (GPCU) XH - AC essential distribution XM - Electrical contactor management system (ECMS) XN - AC main distribution XP - AC ancillary equipment XS - AC auxiliary generation (APU generator GCU) XT - Integrated drive generator system (IDG, GCU) XU - AC main generation XX - AC ground service bus control

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** ON A/C ALL 7. Equipment Identification/Functional Item Numbers (FIN) A. Functional Item Numbers (FIN) The equipment on the A/C is identified by a unique identifier designated Functional Item Number (FIN). The basic element of the FIN is a two letter code indicating to which system circuit the equipment belongs. To this code are added prefixes and/or suffixes which provide the unique identification for individual items of equipment. For electrical equipment (any component with an electrical connection) the FIN is of the form 2CA1 where: - 2 = Second component in circuit CA - CA = Circuit two letter code - 1 = Suffix - First of several similar systems (System 1) NOTE: Several identical components which perform the same function in the same circuit can be differenciated by the suffix number. The general rule is that an even suffix is identifies a component on the right hand side and an odd suffix identifies a component on the left hand side. For mechanical equipment the FIN is similar to the electrical FIN. The FIN sequence number serves to differenciate between mechanical and electrical equipment. The sequence number below 5000 are reserved for electrical FINs and the sequence numbers equal or above 5000 are reserved for mechanical FINs. B. Connectors Connections to components shall be identified by a suffix letter (or two for multiple connection parts) following the circuit identification. Example: 14CA-A - 14 : Component number - CA : Circuit code - A : Plug identification This will identify plug A on the 14th component in the circuit CA. If there are several connections, the other plugs shall be identified A, B, C, D, etc... Example 1: 11CA-B - 11CA : Component identification - B : Plug identification letter Example 2: 14CA-AA - 14 : Component number - CA : Circuit code - AA : Multiple connection identification NOTE: Connectors on equipment fitted on mountings are identified with reference to the equipment but not with reference to the mounting.. As a general rule, the connector PNs given are for connector without contacts. For computers, plug identifications comply with ARINC 600.

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C. Fictitious Components All components not specifically related to a circuit are identified by fictitious circuit letter V. The second letter defines the type of component. (1) VC A/C electrical connectors The electrical connector is identified in a fictitious circuit VC by a numerical designator. This identification shall be preceded by a group of numbers. Example: 19VC-A - 19 : Component number - VC : Fictitious circuit code - A : Plug identification letter - 19VC associated receptacle. (2) VD diode module The diode module is identified in fictitious circuit VD by a numerical designator. Example: 138VD - 138 : Component number - VD : Fictitious circuit code (3) VE panel VE panels are similar to VU except that they are for commercial circuits and all the wires in the VE are identified by ATA chapter 31-18. (4) VG ground terminal block The ground terminal block is identified in fictitious circuit VG by a numerical designator taken from the complete aircraft. (5) VN groud points The ground point is identified in fictitious circuit VN by a numerical designator taken from the complete aircraft. NOTE: The P/Ns of the wire contacts connected to a FIN belonging to the circuit VN are given in chapter 91-50 " Hook up List/Ground Points " in the field " Contact P/N " . (6) VP pressure seal/feed thru The pressure seal/feed thru is identified in fictitious circuit VP by a numerical designator. Terminal identifications are indicated to define a precise feed thru identifier for each wire (in the case of wire to wire feed thru). (7) VS splices Splices are identified like equipment, being grouped by route and by type. Such grouping shall not be systematic, but only accomplished where a priority is required. Identification shall consist of a numeric designator, identifying the group in fictitious circuit VS, and an alpha designator giving connection identification per unit. Example: 24VS A

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-

24 : Component group number VS : Fictitious circuit code A : Identification per unit

(8) VT terminal blocks (a) The terminal block is identified in fictitious circuit VT by a numerical designator. Example: 494VT1224 - 494 : Component number - VT : Fictitious circuit code - 12 : The two digits following the circuit code will be reserved for identification of repetitive item numbers. - 24 : The two digits following the repetitive item number will be reserved for identification of the module number within the repetitive circuit concerned. (b) Shunt connections for modular type terminals are identified in the shunt (SHT) column of the hookup 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. (9) VU panels & racks The panels & racks are identified in fictitious circuit VU by a numerical designator. Example: 123VU - 123 : Component number - VU : Fictitious circuit code There are several panels and racks (circuit VU) with the same function but different configuration in the A/ C. The FIN of these components have one or two additional letters between the circuit letter and the suffix. Example: - 2040VU A 010 - 2040VU B 010 - 2040VU AB 010 component identification: 2040VU configuration letter: - A first configuration - B second configuration - AB third configuration - suffix ( position number on the A/C): 010 That means:there are several Passenger Service Unit (PSU) in the aircraft with 1, 2 or 3 reading lights. These PSUs all have the same basic layout and function but different features. Example: --------------------------------------------------------file:///F|/ServiceDispatcher.htm (3 di 5)16/05/2009 19.58.21

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|

PSU with

|

PSU with

|

PSU with

|

| 1 reading light | 2 reading lights | 3 reading lights | |-------------------------------------------------------| PSUs in the same

|

2040VUA5

|

2040VUB5

|

2040VUAB5

|

column have one P/N

|

2040VUA88

|

2040VUB64

|

2040VUAB99

|

and they are inter-

|

2040VUA123

|

2040VUB112

|

2040VUAB106

|

changable

--------------------------------------------------------PSUs in different columns have different P/N and they are not interchangeable.

Any component and wire which performs the same function in different PSU's have the same identification. (10) VX A VX is an Electric/Electronic Printed Board made by the aircraft manufacturer. It has a P/N and is replaceable ; it is covered by a specific document. This assembly is identified in its functional circuit or in the VX circuit when used for multifunctions. D. Busbar Busbars are identified with: - A sequence number - Letters XP for AC busbars and PP for DC busbars - A phase letter as applicable Example: - 12XP-A : AC busbar, phase A - 2PP : 28 VDC busbar NOTE: If a terminal strip fulfills the function of a busbar identified within the fictitious circuit VT : reference is made to the busbar supplying the terminal strip. E. Equipment Added in the Aircraft by the Customer. The equipment added in the aircraft by the customer shall be numbered from 9000 to 9999. Example: Repair of the wires - The splice shall be identified by a FIN in 9XXXVS serie (E.G 9001VS for the first splice installed on A/C by the customer). - A sleeve shall be installed on each side of the splice and shall be print numbered in the 9XXXVS serie, in accordance with splice FIN. - A Customer Originated Change (COC) shall be raised by the customer to incorporate the VS identified into the WDM (AWM/ASM/AWL). F. Equipment Location

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Equipment are located in reference to zones and stations. Stations numbers are in CENTIMETERS. Zones are depicted in ATA 9100 of the AWM. When an equipment is fitted on a VU panel, the FIN of VU panel is referred. Panels are depicted in ATA 9110 of the AWM.

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DIMENSIONS AND AREAS GENERAL

A330

MAINTENANCE TRAINING ORGANISATION 

DIMENSIONS AND  AREAS

06–00

GENERAL

For Training Purposes Only

ATA 06

06–00

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DIMENSIONS AND AREAS GENERAL

A330

MAINTENANCE TRAINING ORGANISATION   

For Training Purposes Only

AIRCRAFT DIMENSIONS

06–00

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DIMENSIONS AND AREAS GENERAL

A330

MAINTENANCE TRAINING ORGANISATION 

06–00

For Training Purposes Only

 

Figure 1 F

Dimensions General Page: 3

Page: 3

DIMENSIONS AND AREAS GENERAL

A330

MAINTENANCE TRAINING ORGANISATION 

06–00

  AIRCRAFT REFERENCE AXIS REFERENCE AXES The structure elements are localized according to the following reference axes.

For Training Purposes Only

The reference (station 0) for all structural measurements in the X axis is located 683,2 cm forward of the aircraft nose.

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DIMENSIONS AND AREAS GENERAL

A330

MAINTENANCE TRAINING ORGANISATION 

06–00

For Training Purposes Only

 

Figure 2 F

Aircraft Reference Axis Page: 5

Page: 5

DIMENSIONS AND AREAS STATIONS

A330

MAINTENANCE TRAINING ORGANISATION 

06–30

 

For Training Purposes Only

STATION NUMBERS The station number is the distance in centimeters of a cross section from a reference point.

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DIMENSIONS AND AREAS STATIONS

A330

MAINTENANCE TRAINING ORGANISATION 

06–30

For Training Purposes Only

 

Figure 3 F

Station Numbers Page: 7

Page: 7

DIMENSIONS AND AREAS STATIONS

A330

MAINTENANCE TRAINING ORGANISATION   

For Training Purposes Only

Example X=18168 Y=1410 Z=1410

06–30

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DIMENSIONS AND AREAS STATIONS

A330

MAINTENANCE TRAINING ORGANISATION 

06–30

 

Z 1410

For Training Purposes Only

Y 1410

Figure 4 F

Fuselage Stations Page: 9

DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION  AIRCRAFT ZONING

06–00

 

The aircraft is divided into zones in order to facilitate maintenance and component location. Each area is identified by major zones (hundreds), sub zones (tens) and zones units.

MAJOR ZONES

For Training Purposes Only

The aircraft is divided into 8 major zones. Major zones listing : S 100 : Lower Fuselage S 200 : Upper Fuselage S 300 : Stabilizers S 400 : Nacelles/Pylons S 500 : Left Wing S 600 : Right Wing S 700 : Landing Gear S 800 : Doors

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DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION 

06–00

For Training Purposes Only

 

Figure 5 F

Major Zones Page: 11

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DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION  SUB ZONES

06–00

 

Each major zone is divided into sub zones. Here is shown the fuselage for example. 100 identifies the fuselage major zones below the cabin floor: S starting with 120 behind the FWD Pressure bulkhead S ending with 170 before the AFT Pressure bulkhead

ZONES Each sub zone is divided into zones. Here are shown the zones in FWD– and MID lower fuselage section.

For Training Purposes Only

When two numbers are at the same place,the odd one is for the left hand side and the other for the right hand side.

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DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION 

06–00

For Training Purposes Only

 

SUB–ZONES

ZONES

Figure 6 F

Sub Zones–Fuselage and Zones Seite: Page: 13

DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION 

For Training Purposes Only

PANEL PRESENTATION

 

General An identification is given to the items below: – access doors for the maintenance – service doors – fillets – fairings – removable access panels of the radio rack – removable floor panels – removable partition panels – removable ceiling panels – removable sidewall panels. NOTE : Electrical panels are not included here since a special rule applies to them. The identification method is as follows: (1) The first three digits identify the smallest zone in which the door/panel is found. (a) The first letter or identifier shows the position of the access doors and panels in a logical sequence: – forward to aft, for the fuselage – inboard to outboard, for the wing and horizontal stabilizer – bottom to top, for the vertical stabilizer. (b) The second letter or locator identifies the access door or panel in its relation to the aircraft: T = TOP (upper surface) B = Bottom (lower surface) L = Left hand R = Right hand Z = Internal F = Floor panel W = Sidewall panel C = Ceiling panel.

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06–00

(2) When all the letters of the alphabet have been used up for the first letter (identifier), the sequence starts again with letter A and the other letters below are used for the locator: U = Top (upper surface) D = Bottom (lower surface) P = Left hand S = Right hand G = Floor panel X = Sidewall panel Y = Ceiling panel.

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DIMENSIONS AND AREAS GENERAL

A 330

MAINTENANCE TRAINING ORGANISATION 

06–00

For Training Purposes Only

 

Figure 7 F

Access Panel Location Page: 15

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LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION 

ATA 07

  LIFTING AND SHORING

07–10

JACKING

07–10

AIRCRAFT JACKING The aircraft has three jacking points and one safety point to lift the aircraft completly. The aircraft can be jacked using the nose jack only, for maintenance. For wheel change or brake removal/installation there are jacking points at the axle.

For Training Purposes Only

Jacking the aircraft with Wing Jacks (TASK 07–11–00–581–801) Maximum permitted A/C weight is 152000 Kg. Mximum load at forward jacking point is 12300Kg (12300daN) Maximum load at the wing jacking points is 73200Kg (73200daN) Maximum load on the safety point is 4500 Kg (4500daN) Before jacking the aircraft position it in a level position. Using the level indicator which is part of the jacking equipment or the level indicator accessable through access panel 149BB,observe that the aircraft remains in a level position during jacking. After jacking bring the safety stand in to position. Note: The Safety Stand must be removed during landing gear operations!

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LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION 

07–10

For Training Purposes Only

 

Figure 8 F

Jacking Points Page: 17

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LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION  JACKING FOR WHEEL CHANGE

07–10

 

For Training Purposes Only

Main Gear Jacking Put the axle jack under the axle jacking point. If there are four flat tires on one main gear start at the aft axle replacing the wheels to prevent damage on the landing gear.

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LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION 

07–10

 

For Training Purposes Only

cm

Figure 9 F

Jacking Points – Main Landing Gear Seite: Page: 19

LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION 

07–10

 

For Training Purposes Only

Nose Landing Gear Jacking Nose gear jacking is can be used either for replacing a wheel,or to level the aircraft.

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LIFTING AND SHORING JACKING

A330

MAINTENANCE TRAINING ORGANISATION 

07–10

For Training Purposes Only

 

Nose Landing Gear

Figure 10 F

Jacking Point – Nose Landing Gear Seite: Page: 21