1. DOCUMENTATION 1.1. GENERAL

Transcription

1 AIRBUS DOCUMENTATION 1. DOCUMENTATION 1.1. GENERAL AIRBUS DOCUMENTATION Links in between SRM & the other Documents/Manuals ADRES - Airbus Documentation Retrieval System AOLS - Airbus On-Line Services Types of Documents Structure Maintenance Documentation Documentation for Structure Repairs DATE: JUNE 2003 Page 1 XSM21A01A

2 AIRBUS DOCUMENTATION Links in between SRM & the other Document/Manuals SRM (Structural repair Manual): The SRM content is usually concerned with those parts of the aircraft that are secured with permanent types of fasteners. It contains information/instructions for the identification / allowable damage and repair procedures on primary and secondary structures. This manual is envelop to each aircraft type. AMM (Aircraft Maintenance Manual): The relationship in between the SRM and the AMM is minimal, because the AMM is considered to be on a higher level than the SRM and the AMM does not refer to the SRM. But the SRM occasionally refers to the AMM. Although it is not usual to refer to the AMM from a repair procedure, it is implicit that the AMM will be used where it is necessary to disconnect system, to get access, to perform the repair. NTM (Non Destructive Testing Manual) NTM general procedures techniques are called up from the SRM where necessary. Either to perform a damage assessment or to perform scheduled inspections on repairs. Links in between SRM & the other Documents/manuals SB Service Bulletin AMM Aircraft Maintenance Manual NTM Non Destructive Testing Manual SM Standard Manual SRM Structural Repair Manual IPC Illustrated Part Catalogue PMS Process & Material Specifications SIL Service Information Letter CML Consumable Materials List CMM Component Maintenance Manual AIRBUS DOCUMENTATION 4 DATE: JUNE 2003 Page XSM21A01

3 AIRBUS DOCUMENTATION Links in between SRM & the other Document/Manuals (cont d) SIL (Service Information Letter) The SIL is used to provide technical information of a non-urgent character and usually in a one-way relationship to the SRM. (See example: SIL Nbr ) CMMM (Component Maintenance Manual Manufacturer ): The CMMM set is a collection of individual maintenance manuals of components manufactured by Airbus. It provides all data, instructions and functional tests necessary for the overhaul of the equipment. The CMMM is envelop to each aircraft type. CML (Consumable Material List): The CML assists the operator in getting additional and detailed information about a consumable material used in the aircraft. (It also gives procurement sources of the materials) This document is Airbus generic. PMS (Process and Material Specifications) A one-way relationship exists between the SRM and the PMS. Where necessary, a cross-reference in the SRM to the PMS provides the operator with information concerning the manufacturing process, materials and material treatments used in production and assembly of all Airbus types. This document is Airbus generic. SM (standard manual) The SM gives Airbus approved design and product standards used for the manufacture of the aircraft. The SM also contains a list of qualified suppliers (Part 3), proprietary parts as well as lists of two-way (Part 4), and one-way(part 5), interchangeable standards. Standard Manual Part 3 Part 3 gives the relationship between original standard part number, vendor part number and Supplier cage/nato code. This manual is Airbus generic. DATE: JUNE 2003 Page XSM21A01

4 AIRBUS DOCUMENTATION Links in between SRM & the other Document/Manuals (cont d) SB (Service Bulletins) The SB conveys to the operators technical information which covers the embodiment of modifications on inservice aircraft. SBs are Airworthiness Authority approved and customized to the operator aircraft MSNs mentioned in the effectivity paragraph of the SB. Occasionally the information contained within a Service Bulletin has a repercussion on the SRM, such as the introduction of additional parts that requires identification. As an alternative to hard-copy form, Airbus provides an access on any new or revised SB issued within ETDS (Engineering Technical Data Service) which are part of the AOLS (Airbus On-line Service). IPC (Illustrated Part Catalogue ): To some extent there may be a limited amount of duplication in between the SRM and the IPC. The SRM is concerned with identifying the constructional details of a part, but the IPC is concerned with the attaching of such parts to the main structure. DATE: JUNE 2003 Page XSM21A01

5 AIRBUS DOCUMENTATION Links in between SRM & the other Document/Manuals (cont d) EXAMPLE OF SIL (e.g.: SIL ) DATE: JUNE 2003 Page XSM21A01

6 AIRBUS DOCUMENTATION DATE: JUNE 2003 Page XSM21A01

7 AIRBUS DOCUMENTATION ADRES - Airbus Documentation Retrieval System Airbus provides a self-contained set of CD-ROMs for the interactive consultation of the AMM and the IPC on stand alone PC. The system offers a multitude of access functions and hyperlinks and can also be used in a network environment. ADRES - Airbus Documentation Retrieval System ADRESS Airbus Documentation Retrieval System AMM IPC Aircraft Maintenance Manual Illustrated Parts Catalogue AIRBUS DOCUMENTATION 9 DATE: JUNE 2003 Page XSM21A01

8 AIRBUS DOCUMENTATION TPCI - Technical Publication Combined Index The TPCI is an electronic index, available on CD-ROM (Windows 2000/Web browser technology-based operating system). It is used for easy identification of the index references and links between the following documents: MOD Modification MP Modification Proposal SB Service Bulletin VSB Vendor Service Bulletin SIL Service Information Letter TFU Technical Follow-Up AOT All Operator Telex OIT Operator Information Telex FOT Flight Operation Telex OEB Operation Engineering Bulletin AD Airworthiness Directives CN Consignes de Navigabilité (the French AD) It also provides easy access to the contents of AOTs, OITs, FOTs, SILs and TFUs. - One Archive CD-ROM covers all data issued up to end of December 97: one-off delivery, - One Monthly CD-ROM covers all data issued since early January 98: revision service is monthly. For further information about this tool, refer to SIL TPCI - Technical Publication Combined Index TPCI Technical Publication Combined Index Easy identification of the index reference and links between the following documents + Easy access to AOT, OIT, FOT and TFU contents MOD Modification MP Modification Proposal SB Service Bulletin VSB Vendor Service Bulletin SIL Service Information Letter TFU Technical Follow-up AOT All Operator Telex OIT Operator Information Telex FOT Flight Operation Telex OEB Operation Engineering Bulletin AD Airworthiness Directives CN Consigne de navigabilite (French AD) AIRBUS DOCUMENTATION 10 DATE: JUNE 2003 Page XSM21A01

9 AIRBUS DOCUMENTATION AOLS - Airbus On-Line Services Airbus On-Line Services is a web portal allowing the customer access to a wide range of services. The aim of which is to optimize the maintenance and operations of Airbus fleets. The services available through Airbus On-Line Services are organized in the following domains: Maintenance and Engineering General information Flight Ops Materi l Training The services are divided into the following categories: Basic services Technical data in PDF format Optional services Use of Airbus On-Line Services is subject to Airbus On-Line Services General Conditions of Licensing. AOLS - Airbus On-Line Services BASIC SERVICES Maintenance & Engineering Training Material General Information ETDS Training Catalogue Spares ordering Customer service Catalogue Quarterly Service Report (QSR) Waranty Claim (CAWA) Repair guide (ARG/AOG) TECHNICAL DATA in PDF FORMAT SRM AM M IP C TSM etc... OPTIONAL SERVICES Maintenance & Engineering Flight OPS Mechanical Drawings - AIDA FCOM Tooling Drawings AIRBUS DOCUMENTATION 11 DATE: JUNE 2003 Page XSM21A0

10 AIRBUS DOCUMENTATION AOLS Basic services Maintenance & Engineering Engineering Technical Data Service (ETDS) ETDS provides access, via a document index, to the contents of: - Service Bulletins issued since beginning of 1993 (SB s after July 1997 in SGML; SB s between 1993 and July 1997 in PDF) - Modification Information Document (MID) - All Operator Telex (AOT) - Flight Operation Telex (FOT) - Service Information Letter (SIL) - Consignes de Navigabilité (CN) - Airworthiness Directives (AD) - Technical Follow-Up (TFU) - Operator Information Telex (OIT) In addition, links between these documents are available through the service. All documents can be downloaded. SB s available in SGML format can be downloaded in SGML. Printing of all documents will be based on PDF format Quarterly Service Report (QSR): refer to description page 49 Repair Guide (ARG/AOG): provides the customers with information about the Airbus Suppliers authorized repair stations and the AOG stock locations. Modification Comparison List (ACCL): provides the customers with the Modification Comparison Lists that are created for each and every aircraft delivered. Training Training Catalog Materiel Spares Ordering DATE: JUNE 2003 Page 1 XSM21A01

11 AIRBUS DOCUMENTATION AOLS Maintenance and Engineering Mechanical Drawings The Mechanical Drawing Service offers: Mechanical Drawings for all Airbus aircraft types: - Data available: Drawing pictures (in raster format [TIFF/CCITTG4]) and Parts List/Parts Usage (in PDF) - Data access: Access control: Information applicable to the user fleet, Direct access by drawing number, Parts List or Part Number, Top down navigation by using the Parts List, Bottom up navigation by using the Part Usage, Printing (format Postscript Level 2) and downloading of any drawing, Back up service: fax copy of the data Tooling Drawings The tooling equipment drawing includes all the vendor equipment and the Tooling Equipment Index (TEI) provided by the Part Number or Drawing Number (26000 picture sheets), except the Airbus and vendor proprietary items such as tooling equipment for engines for example. DATE: JUNE 2003 Page 1 XSM21A01

12 AIRBUS DOCUMENTATION Structure Maintenance Documentation For each new type of aircraft it is necessary to develop a maintenance program prior to its introduction into service. The objectives are: - to maintain Airworthiness throughout the operational life of the aircraft, - to satisfy aircraft type certification. Following MSG-3 (Maintenance Steering Group-3) analysis, the initial minimum scheduled maintenance tasks and frequencies are determined and compiled in the MRB (Maintenance Review Board ) document. The MPD (Maintenance Planning Document) is established (from the MRB) to form a fully workable document for the airlines. The instruction for proper maintenance are also given in other documents such as AMM, CMM, SRM,... In the AMM a specific chapter ( Time Limits & Maintenance Checks) contains service life limits of structural parts or landing gear parts ( safe life designed items). In addition, to the basic tasks defined within the MRB, some additional inspection requirement can also be added following the static / fatigue tests and or according to in-service experience. This is done via ISB or SB. Structure Maintenance Documentation MSG-3 document MSG-3 analysis MRB Maintenance Review Board document Inspection tasks: -ZONAL program - STRUCTURE program MPD Maintenance Planning Document Operator Maintenance Program TESTS (Static / Fatigue / Tear down) SIL SB ISB AOT In-service experience AMM 51 NTM 51 SRM 51 MPD 51 IP C CM M TEM Tools & Equipment Manual CM L Consumable Material List AIRBUS DOCUMENTATION 14 DATE: JUNE 2003 Page 1 XSM21A01

13 AIRBUS DOCUMENTATION Documentation for Structure Repairs Documentation for Structure Repairs SRM - Structure identification - Damage evaluation / classification / Assessment - Allowable damage determination, - Repair selection / instructions - Standard repair practices / Materials / Processes 51 Repairs Replacement Production Drawings Repair Drawings / TD - Technical Dispositions SM - Standard Manual AMM CMM IPC PMS - Process & Material Specifications CML - Consumable Material List CMM - Component Maintenance Manual AIRBUS DOCUMENTATION 15 DATE: JUNE 2003 Page 1 XSM21A01

14 2 -AIRBUS DOCUMENTATION 1. DOCUMENTATION 1.1. GENERAL ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICES What is ETDS? Document Formats Document Update Minimum Requirements for ETDS ETDS Access Rights ETDS Home Page ETDS Document Selection ETDS Search Page ETDS Document Index Page ETDS - SB Consultation Example ETDS - TFU Consultation Example DATE: JUNE 2003 Page 1 XSM21B01

15 2 -AIRBUS DOCUMENTATION ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICES What is ETDS? ETDS (Engineering Technical Data Service) is an On-Line service, which provides the following information for all AIRBUS aircraft: Service Bulletins (SB) - all issued since beginning of 1993 Technical follow-up (TFU) - all Modification Information Document (MID) - all All Operators Telex (AOT) - all Operators Information Telex (OIT) - all Flight Operations Telex (FOT) - all Service Information Letter (SIL) - all Consignes de Navigabilité (CN) - all Advisory directives (AD)- all In addition a FORUM allowing customer to post comment on TFU is available WHAT IS ETDS? L S AOLS Airbus On n Line Line Services E Engineering technical Documentation Services Access to the Technical contents of Service Seti issued Bulletins since inning (SB) of all 1993 issued since beginning of 1993 Technical follow-up (TFU) - all - all Modification Information Document (MID) --all All Operators Telex (AOT) (ll - all Operators Information Telex (OIT) --all Flight Operations Telex (FOT) - all Service Information Letter (SIL)( - all - all Consignes de Navigabilité (CN) all Advisory directives (AD)- ()- allsall ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 18 DATE: JUNE 2003 Page 1 XSM21B01

16 2 -AIRBUS DOCUMENTATION Document Formats Through ETDS the documents are available with the following format: All TFU are available in PDF SB issued prior JAN are in paper format and are not available in ETDS All SB issued between JAN and July 1997 are available in PDF All SB issue after July 1997 and all revised SB are available in SGML and PDF All AD, CN, MID, SIL are in PDF All AOT, OIT, FOT are in ASCII All drawings or schematics are in TIFF Document Update As of today the following updates are carried out: For AOT, OIT, FOT, AD, CN, SIL, MID on the fly (as soon as documents are ready) For SB every Friday night For TFU every last Friday of the month Minimum Requirements for ETDS To navigate, perform queries and visualize correctly all documents available in ETDS make sure that: 1.Your workstation is correctly configured: Please refer to the AOLS EU Installation document 2.Acrobat Reader 4.05 and a TIFF viewer are installed in your workstation 3.Your administrator gave you a profile for accessing ETDS service 4.You are familiar with Microsoft WINDOW type application and browser use. ETDS Access Rights The following conventions are applied through ETDS service For AOT, OIT, FOT, SIL, MID, TFU airline end-users access the documents related to the type of aircraft that they operate or documents delegated by AIRBUS or another airline. For SB, airline end-users access all STANDARD SB related to the type of aircraft they operate regardless of MSN effectivity. For RFC/RMO SB airline end-users access the summary and full SB package when SB is purchased. Third Party Maintenance end-users see the documents delegated by AIRBUS or by an airline. DATE: JUNE 2003 Page 1 XSM21B01

17 2 -AIRBUS DOCUMENTATION EDTDS Home Page All screens in ETDS service have basically the same layout consisting of 5 main areas: The User Area located on the top left frame, contains the user name and the user entity. The Content Frame located in the screen center, depicts either the search criteria page, the query results page or the content of a selected document. The TREE applet located on the bottom left (only available with SB), list SB with revision or show chapter and subchapter of a selected SB. The Specific Button Bar located on the top show buttons associated with the content of the Content Frame. The Function Bar located at the button show active buttons clearly labeled providing the function depicted by the label. At least the following buttons are always present. EDTS HOME PAGE User Area Tree applet (SB only) Function bar ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 20 DATE: JUNE 2003 Page XSM21B01

18 2 -AIRBUS DOCUMENTATION ETDS Document Selection The following documents (SB, TFU, MID, AOT, OIT, FOT, SIL, AD, CN) are available in ETDS and are selected by clicking into the pull down menu as shown herewith. DOCUMENT SELECTION Document selection, ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 21 DATE: JUNE 2003 Page XSM21B01

19 2 -AIRBUS DOCUMENTATION ETDS Search Page When a document type is selected, the corresponding search page appears. The Search page into ETDS service varies slightly from one document to another but it is always composed of 3 main zones: 1. Date Search (Zone1) allows searching for any date or with a date range. In this case user shall insert the starting date and the ending date. Make sure to enter the date in the appropriate boxes using the format specified (yyyy mm dd.). ETDS SEARCH PAGE Zone 1 - Date Search ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 22 DATE: JUNE 2003 Page XSM21B01

20 2 -AIRBUS DOCUMENTATION ETDS Search Page (cont d) 2. Other Search Criteria (Zone2) allows searching by attributes such as title, reference, ATA chapter, and MSN or aircraft type. Pick up lists are available providing unambiguous selecting criteria. SHIFT and CTRL buttons allow multiple selections in pick up list. For fields without pick up list, use simple words. Wildcards are available. ("*" used for multiple characters or "?" used for single character). Note that search strings are not case sensitive. Example of acceptable search string: RUDDER RU* *dd RudDER ETDS SEARCH PAGE Zone 2 - Other Search Criteria ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 23 DATE: JUNE 2003 Page 2 XSM21B01

21 2 -AIRBUS DOCUMENTATION ETDS Search Page (cont d) 3. Word or Phrase Search (Zone3) allows performing full text search: Any word or sentence can be inserted here. For syntax please refer to the Appendix II. This appendix explains how to write a query, incorporating VERITY operators and providing Query examples. All criteria selected in the 3 zones can be combined together to make a query. When the selection of search criteria is done, validate the query by clicking into the "Search" button. The result (Document Index page) will be displayed in the center frame and consists of a list of documents matching the query. If the result is unique the corresponding document is immediately displayed on screen IMPORTANT INFORMATION: - Before setting any query make sure to reset all fields by clicking on the Clear button. - Make sure you enter any criteria by following strictly the format depicted next to the field. Queries are memorized. When you log in, your last query is displayed on the screen. When a query returns no result, the query is not memorized and your query screen is reset to your previous query. ETDS SEARCH PAGE Zone 3 - Word or Phrase Search ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 24 DATE: JUNE 2003 Page 2 XSM21B01

22 2 -AIRBUS DOCUMENTATION ETDS Document Index Page Following a search, the result is displayed in the content frame and consists of a list of documents matching the query. This page varies slightly depending of the document selected but the main topics, layouts and functions are common to all documents 1. The number of records matching the query is displayed in the middle of the top frame "Rows 1 to XX of YY" XX represents the number of documents to be displayed at a time YY represents the total number of documents matching the query 2. Each record matching the query is displayed in a row. The column location and content are in accordance with the selection requested in the Display Format page. 3. Using the Display Format button located in the Function bar changes the number of row per page, the number of column and their location. By default the ETDS service display 10 rows per page ETDS INDEX PAGE 1 - Number of records matching the query 4 - tools 2 - List of records matching the query. 5 - Downloading options 3 - Display format change the nb of rows per page ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 25 DATE: JUNE 2003 Page 2 XSM21B01

23 2 -AIRBUS DOCUMENTATION ETDS Document Index Page 4. In this area several buttons are available and provide the following functions: The "Select All" button allows to select all documents for download either the associated PDF or the associated SGML The "Clear" button allows to reset all marks in the Select column The "Go To" button allows to enter a number and to jump directly to this row The "Download List" button allows downloading the query result in an Excel table 5. This area varies slightly from one document to another. Only the active buttons are shown. If the documents contained in the query results are not available in PDF or SGML, the Download PDF or Download SGML buttons shall not appear. The VCR type button () allows going to the first, previous, next and last record of the query results. The Download PDF button allow downloading in PDF all documents selected in the select column. A zipped file is created and a pop up window shall request the location where to save the file. The Download SGML button allow downloading in SGML all documents selected in the select column. A zipped file is created and a pop up window shall request the location where to save the file. ETDS INDEX PAGE 1 - Number of records matching the query 4 - tools 2 - List of records matching the query. 5 - Downloading options 3 - Display format change the nb of rows per page ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 26 DATE: JUNE 2003 Page 2 XSM21B01

24 2 -AIRBUS DOCUMENTATION ETDS - SB Consultation Example Example of search criteria: ATA24 concerned SB number unknown: ---> SB 24.****, A/C concerned: A320 Words or phrase search: drive generator ETDS - SB Consultation Example Criteria: 24.**** Criteria: A320 Criteria: Word or Phrase Search: drive generator ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 27 DATE: JUNE 2003 Page 2 XSM21B01

25 2 -AIRBUS DOCUMENTATION ETDS - SB Consultation Example 1. The Service Bulletin with the latest revision is displayed. As shown here the SB is displayed with rev00 to rev03. Previous revisions are available. On the tree applet the following SB reference could be shown Rev00 SB only available in paper format Rev01 SB only available in paper format Rev02 PDF SB only available in PDF format Rev03 DTD 5.2 SB available in SGML and PDF format ETDS - SB Consultation Example Tree applet ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 28 DATE: JUNE 2003 Page 2 XSM21B01

26 2 -AIRBUS DOCUMENTATION ETDS - SB Consultation Example Rev02 PDF SB only available in PDF format ETDS - SB Consultation Example Rev 02 PDF (680 Kb) SB available on PDF format only ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 29 DATE: JUNE 2003 Page 2 XSM21B01

27 2 -AIRBUS DOCUMENTATION ETDS - SB Consultation Example Rev03 DTD 5.2 SB available in SGML and PDF format ETDS - SB Consultation Example Rev 03 DTD v5.2 SB available in PDF and SGML format only Download the SGML file Display the PDF file ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 30 DATE: JUNE 2003 Page XSM21B01

28 2 -AIRBUS DOCUMENTATION ETDS - TFU Consultation Example ETDS - TFU Consultation Example Display the PDF file ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 31 DATE: JUNE 2003 Page XSM21B01

29 2 -AIRBUS DOCUMENTATION ETDS - TFU Consultation Example ETDS - TFU Consultation Example ETDS - ENGINEERING TECHNICAL DOCUMENTATION SERVICE 32 DATE: JUNE 2003 Page XSM21B01

30 2 -AIRBUS DOCUMENTATION 1. DOCUMENTATION 1.2. SRM - STRUCTURAL REPAIR MANUAL SRM PRESENTATION General Manual Breakdown Manual General Usage Procedure Manual Front Pages Chapter 00 - Introduction Numbering System and Page block Allocation Chapter 51 - Structure General Chapter 52 to 57 Contents Identification Page Block Allowable Damage Page Block Repairs Page Block DATE: JUNE 2003 Page 30 XSD22A01

31 2 -AIRBUS DOCUMENTATION SRM PRESENTATION General The structure repair manual is a non-customised document. It has been prepared in accordance with Air Transport Association ATA specification 100. The SRM includes descriptive information as well as specific instructions and data to perform the assessment of structural damage and to perform repairs. The manual contents is approved by the French Airworthiness Authority DGAC ( Direction Generale de l Aviation Civile ). For most of the damage / Defect discovered on the aircraft structure, the SRM is the first document to be used to assess the damage, to identify the affected structure and to determine the subsequent action or repair to be performed. GENERAL NON CUSTOMIZED DOCUMENT Prepared in accordance with the Air Transport Association (ATA), Specification 100 DGAC (Direction Generale de l Aviation Civile) APPROVED DOCUMENT Main contents: - Materials Identification, - Allowable Damage, - Structural Repairs, - Material and Fastener Information, SRM PRESENTATION 36 DATE: JUNE 2003 Page 31 XSD22A01

32 Manual Breakdown The SRM is divided into seven main chapters (From ATA 51 to ATA 57). The manual also contains an introduction chapter (Chap. 00) and some additional information pages (HIGHLIGHTS, RECORD OF REVISIONS ) located just at the beginning of the manual. MANUAL BREAKDOWN Manual Introduction chapter 00 Front Pages INTRODUCTION STRUCTURE REPAIR INSPECTIONS SRI 51 DOORS FUSELAGE PYLONS / NACELLES 54 STABILIZERS 55 WINGS 57 Chapter 51 - Structure General STRUCTURE Chapters Specific chapters SRM PRESENTATION 37 DATE: JUNE 2003 Page 37 XSD22A01

33 2 -AIRBUS DOCUMENTATION Manual General Usage Procedure When a damage is discovered, the first step is to evaluate, classify and accurately measure it. The SRM chapter XX provides useful information to perform this assessment in the best conditions (damage definitions and classification, classification of structures, allowable damage definitions and damage / defect reporting process). The next step is the full identification of the affected area / structure. This is achieved using the identification page block (pages 01-99) of the related specific chapter/section (52-57). According to the original structure data and the actual damage characteristics it is then possible to determine whether the damage is within the defined allowable limits or not. This is done using the Allowable damage page block (pages ) of the related specific chapter/section. If the damage is within the allowable limits, the subsequent actions are generally a slight re-work and a reprotection of the affected area, using the standard procedures of chapter 51. If the damage is above the limits, you must check whether a repair is available and/or applicable within the repair page block (pages ). MANUAL GENERAL USAGE PROCEDURE CHAPT. 51 Damage / Defect discovered Damage/ Defect assessment General information / definitions (damage types / allowable damage / Reporting,..) CHAPT. 51 Standard repair practices / materials / processes YES Rework / Re-protection in accordance with SRM Full identification of affected structure Damage within allowable damage limits Identification page block (0-99) NO Check applicable SRM chapter for existing / applicable repair Allowable damage page block ( ) Repairs page block ( ) SPECIFIC CHAPTERS Embody existing SRM repair YES NO Provide Airbus with a damage/defect report - Provide Airbus with a repair proposal for approval, or - Request for an Airbus approved repair. CHAPT. 51 Embody the approved repair Call up for Std practices/ processes / material, fastener references, etc...) SRM PRESENTATION 38 DATE: JUNE 2003 Page 33 XSD22A01

34 Manual Front Pages The front pages of the manual provides general information related to the manual itself: - Revision Transmittal Sheet -Highlights - Alphanumerical Index - Record of Revisions Approved - Record of Temporary Revisions - List of Effective Temporary Revisions - List of Chapter. FRONT PAGES - GENERAL Highlights Alphanumerical Index Record of Revision Approved by the DGAC 00 WINGS Introduction INTRODUCTION DOORS 53 FUSELAGE PYLONS / NACELLES 54 STABILIZERS STRUCTURE SRM PRESENTATION 39 DATE: JUNE 2003 Page 39 XSD22A01

35 2 -AIRBUS DOCUMENTATION Manual Front Pages (cont d) HIGHLIGHTS PAGES Identification, location of the changes within the SRM from the previous revision. The type of change (page revised, new, deleted) is also presented. FRONT PAGES - HIGHLIGHTS Concerned SRM revision Identification of Changed / Modified Pages in theframe of the manual revision. Reasons for change/modification Type of change: N: New R: Revised D: Deleted SRM PRESENTATION 40 DATE: JUNE 2003 Page 35 XSD22A01

36 2 -AIRBUS DOCUMENTATION Manual Front Pages (cont d) ALPHANUMERICAL INDEX PAGES This document provides a list of all PNs (Part numbers) referenced within the SRM and gives the related ATA chapter, the figure number, the configuration and the item number within the figure. This list is updated at each SRM revision. FRONT PAGES - Alphanumerical Index List of all PNs (Partnumbers) in the SRM. List updated with each revision. Configuration Related figure number ATA reference (location within the manual) Item number in the related figure Partnumber SRM PRESENTATION 41 DATE: JUNE 2003 Page 36 XSD22A01

37 2 -AIRBUS DOCUMENTATION Chapter 00 - INTRODUCTION The introduction chapter contains all the necessary information and explanations to enable a correct use of the manual. It also contains the Aircraft Allocation list, giving for each MSN (Manufacturer Serial Number), the airplane type, the aircraft rank within the customer version, the customer, the customer abbreviation code and the registration number. CHAPTER 00 - INTRODUCTION PART Manual Introduction. Important part of the manual, to be read carefully. Airplane Allocation list DGAC Stamp SRM PRESENTATION 42 DATE: JUNE 2003 Page 37 XSD22A01

38 2 -AIRBUS DOCUMENTATION Numbering System and Page Block Allocation NUMBERING SYSTEM Each subject, within the SRM, is identified using a three-element numbering system Chapter/Section and Sub-section. The first element designates the chapter which is assigned by the ATA spec The second element designates the section within the chapter. The first digit is assigned by the ATA spec The second digit is assigned by Airbus S.A.S. The third element identifies the subsection (subject) within the section and is assigned by Airbus S.A.S. PAGE BLOCK ALLOCATION A standard page block allocation is used for all SRM chapters. - Pages 1 to 98 for Structure Identification - Pages 101 to 198 for Allowable Damage - Pages 201 to 998 for Repairs. Note: Chapter 51 has no identifying block number. In this case the description page block could extend up to 199. NUMBERING SYSTEM & PAGE BLOCK ALLOCATION NUMBERING Assigned by ATA 100 Assigned by Airbus Industrie Page 1 Aug 01/97 CHAPTER SUBJECT within the SECTION PAGE block ALLOCATION SECTION within the CHAPTER IDENTIFICATION Page block (Pages 1 to 99) Page 1 Aug 01/ Page 101 Aug 01/ ALLOWABLE DAMAGE Page block (Page 101 to 199) Page 201 Aug 01/97 REPAIR Page block (Pages 201 to 999) SRM PRESENTATION 43 DATE: JUNE 2003 Page 38 XSD22A01

39 Chapter 51 - STRUCTURE GENERAL Information of a general nature or information which is applicable to more than one chapter is included in chapter 51. CHAPTER 51 Standard practices / information / repair instructions when applicable to more than specific chapter chapter Structures - general STRUCTURES Investigation - Clean up and Aerodynamic Smoothness Processes Materials Fasteners Support of Airplane for repair and Alignment check procedures Control Surface Balancing Repairs SRM PRESENTATION 44 DATE: JUNE 2003 Page 44 XSD22A01

40 2 -AIRBUS DOCUMENTATION Chapter 51 - STRUCTURE GENERAL INVESTIGATION - CLEANUP AND AERODYNAMIC SMOOTHNESS DAMAGE CLASSIFICATION ALLOWABLE DAMAGE STRUCTURE CLASSIFICATION DAMAGE/DEFECT REPORTING CLASSIFICATION - REPAIR APPROVAL PROCESSES PROTECTIVE TREATMENT APPLICATION OF PROT. TREATMENT TO METAL PARTS CORROSION PREVENTION COATINGS APPLICATION - GENERAL PAINT COATINGS SPECIAL COATINGS SEALING - GENERAL HEAT TREATMENT FORMING BENDING JOGGLING CUTTING HEAT DAMAGE EVALUATION HARDNESS TESTING PRESTRESSING OF COMPONENTS FLAP PEENING MATERIALS METALLIC MATERIALS EXTRUDED AND FORMED SECTIONS NON-METALLIC MATERIALS CONSUMABLE MATERIAL HAZARDOUS MATERIALS DATE: JUNE 2003 Page 40 XSD22A01

41 2 -AIRBUS DOCUMENTATION Chapter 51 - STRUCTURE GENERAL FASTENERS FASTENERS - CALL-UP AND DESIGNATION FASTENER SYMBOLS FASTENER INSTALLATION AND REMOVAL FASTENER INSTALLATION AND REMOVAL - METALLIC STRUCTURE FASTENER INSTALLATION AND REMOVAL - COMPOSITE STRUCTURE FASTENER OVERSIZE AND ALTERNATIVE FASTENER OVERSIZE - METALLIC STRUCTURE FASTENER ALTERNATIVE - METALLIC STRUCTURE FASTENER OVERSIZE - COMPOSITE STRUCTURE FASTENER ALTERNATIVE - COMPOSITE STRUCTURE FASTENERS - HOLE AND DRILL DATA FASTENERS - HOLE AND DRILL DATA - METALLIC STRUCTURE FASTENERS - HOLE AND DRILL DATA - COMPOSITE STRUCTURE COUNTERSINKING COUNTERSINKING - METALLIC STRUCTURE SPOT FACING PROCEDURE COUNTERSINKING - COMPOSITE STRUCTURE FASTENER SPACING AND MARGIN DATA COLD EXPANSION OF FASTENER HOLES COLD EXPANSION OF CRACK STOP HOLES BUSHLOC INSTALLATION PROCEDURE STANDARD TORQUE VALUES SUPPORT OF AIRPLANE FOR REPAIR AND ALIGNMENT CHECK PROCEDURES SUPPORT OF AIRPLANE FOR REPAIR CONTROL SURFACE BALANCING DATE: JUNE 2003 Page 41 XSD22A01

42 2 -AIRBUS DOCUMENTATION Chapter 51 - STRUCTURE GENERAL REPAIRS FILLING OF EXISTING COUNTERSINKS REPLACEMENT OF COMPONENTS REPLACEMENT OF STRUCTURAL COMPONENTS REPLACEMENT OF BUSHES IN SITU REPAIR OF MINOR DAMAGE REPAIR BY INSTALLATION OF A FREEZE PLUG REPAIR OF CORRODED AREAS PAINT REPAIR STRIPPING/PAINT REMOVAL REPAIR OF PAINT COATINGS SEALING REPAIRS REPAIR OF SEALING EXCLUDING FUEL TANK REPAIR OF FUEL TANK SEALING STANDARD COMPOSITE REPAIRS COMPOSITE COMPONENTS - ALLOWABLE DAMAGE AND REPAIR CLASSIFICATION MATERIAL HANDLING AND PREPARATION COMPOSITE REPAIRS - SKIN DAMAGE ALL STRUCTURES COMPOSITE REPAIRS - SANDWICH STRUCTURES CLEANING PROCESSES SKYDROL SPILLAGE TITANIUM DAMAGE MERCURY SPILLAGE ACID AND ALKALI SPILLAGE CONTAMINATION BY FISH CONTAINER LEAKAGE DATE: JUNE 2003 Page 42 XSD22A01

43 Chapters 52 to 57 - Contents Chapters 52 to 57 have the same layout which conforms with the defined page block allocation system (PB 1 to 98 - Identification, PB 101 to Allowable Damage, PB 201 to Repairs). In addition, a table of contents and a Service Bulletin list are provided at the beginning of each chapter. Depending on the chapters, the Modification / Service bulletin list is to be found either at the chapter level, or main section level. CHAPTERS CONTENTS Repairs (Chapter, section or main assembly level) 52 Allowable Damage (Chapter, section or main assembly level) 53 Service Bulletin List (beginning of each chapter) Table of Contents (beginning of each chapter) Identification Pages Modification / Service Bulletin List (Chapter, section or main assembly level) (Chapter, section or main assembly level) Page 1 Page 101 Page 201 SRM PRESENTATION 48 DATE: JUNE 2003 Page 48 XSD22A01

44 Chapters 52 to 57 - Contents (cont d) SERVICE BULLETIN LIST Located at the beginning of each chapter, List of all the service bulletins referenced within the chapter. The user can refer to this list to get more information regarding a specific service bulletin in terms of: - Revision status of the SB - Date of introduction within SRM - Description. CHAPTERS CONTENTS - SERVICE BULLETIN LIST Repairs (Chapter, section or main assembly level) 52 Allowable Damage (Chapter, section or main assembly level) 53 Service Bulletin List (beginning of each chapter) Table of Contents (beginning of each chapter) Identification Pages Modification / Service Bulletin List (Chapter, section or main assembly level) (Chapter, section or main assembly level) Page 1 Page 101 Page 201 SRM PRESENTATION 49 DATE: JUNE 2003 Page 49 XSD22A01

45 2 -AIRBUS DOCUMENTATION DATE: JUNE 2003 Page 50 XSD22A01

46 Chapters 52 to 57 - Contents (cont d) MODIFICATION / SERVICE BULLETIN LIST Located at: - Door level for Chapter 52 - Fuselage Section level for Chapter 53 - Chapter level for chapter 54 - Main Assembly level for chapter 55 - Wing section level for chapter 57. This list is provided to enable the user to determine the effectivities of the modification/sb. CHAPTERS CONTENTS - MODIFICATIONS / SERVICE BULLETIN LIST Repairs (Chapter, section or main assembly level) 52 Allowable Damage (Chapter, section or main assembly level) 53 Service Bulletin List (beginning of each chapter) Table of Contents (beginning of each chapter) Identification Pages Modification / Service Bulletin List (Chapter, section or main assembly level) (Chapter, section or main assembly level) Page 1 Page 101 Page 201 SRM PRESENTATION 51 DATE: JUNE 2003 Page 51 XSD22A01

47 2 -AIRBUS DOCUMENTATION Effectivities of the modification in MSN numbers (ref.: Aircraft Allocation Tables in SRM introduction part) Suffix column: Identifies the different effectivities of a same modification Concerned a/c model Modification number Location within the chapter: 52 : Door level 53 : Fuselage section level 54 : Chapter level 55 : Main assembly level 57 : Wing section level Corresponding SB if any DATE: JUNE 2003 Page 52 XSD22A01

48 Identification Page Block (pages 01 to 99) In the identification pages, the individual parts of the major components are illustrated and listed in tabular form. Each identification topic begins with an introduction page which includes a general information paragraph. The item number is the key in between the illustration and the identification table. EXAMPLE: COMPOSITE STRUCTURES IDENTIFICATION PAGES - Example: COMPOSITE STRUCTURES Ply orientation references Item number ILLUSTRATIONS IDENTIFICATION TABLE Plies identification eg ply nbr : - 6 Plies orientations SRM PRESENTATION - Identification Pages - General - 53 DATE: JUNE 2003 Page 53 XSD22A01

49 Identification Page Block (pages 01 to 99) EXAMPLE: METALLIC STRUCTURES. IDENTIFICATION PAGES - Example: METALLIC STRUCTURES Item number Nominal thicknesses Max. thickness SRM PRESENTATION - Identification Pages - General - 54 DATE: JUNE 2003 Page 54 XSD22A01

50 Identification Page Block (cont d) IDENTIFICATION TABLE The typical identification table associated with the illustration(s) contains different columns: - ITEM - NOMENCLATURE - SPECIFICATION AND/OR SECTION CODE - THICKNESS IN MM (IN.) AND/OR PARTNUMBER - IC: INTERCHANGEABILITY - ACTION OR REPAIR - STATUS (MOD/PROP) SB/RC - MOD / PROP: MODIFICATION / PROPOSAL - SB / RC: SERVICE BULLETIN / RECORDABLE CONCESSION. The effectivities of the table (page) is shown at the bottom left hand corner (e.g.: EFFECTIVITY: A320, A321). In addition: The relevant assembly drawings are listed at the end of the table (ASSY DRAWINGS:..) IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED Specification and/or Section Code Action or Repair Thickness and/or Partnumber Item Modification Status Interchangeability Relevant next higher Assembly drawings SRM PRESENTATION 55 DATE: JUNE 2003 Page 55 XSD22A01

51 Identification Page Block (cont d)) IDENTIFICATION TABLE DETAILED - ITEM COLUMN IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED ITEM Basic version of the item 1 Evolution(s) of Item 1 (Panel, skin) Linked to production modification / SB SRM PRESENTATION - Identification Pages - Identification Table (cont d) 56 DATE: JUNE 2003 Page 56 XSD22A01

52 Identification Page Block (cont d) IDENTIFICATION TABLE - SPECIFICATION / SECTION CODE COLUMN This column provides information related to the type of material used (material specification) and when possible / available the appropriate standards. To get more information regarding the material specifications the user can refer to the SRM chapter for Metallic materials For Non-metallic materials (composites) When the appropriate standard in shown the user can refer to the Airbus S.A.S. Standard Manual(SM). IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED SPECIFICATION AN/OR SECTION CODE Material type / Specification Standard T351 code / Semi-finished product standard code DAN26H10 (Materials / Profiles / sections, ) SRM Metallic Materials SRM Non-Metallic Materials EXAMPLE SM Standards M anual EXAMPLE SRM PRESENTATION 57 DATE: JUNE 2003 Page 57 XSD22A01

53 Identification Page Block (cont d) CHAPTER EXAMPLE IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED Table Number SRM Metallic Materials SRM PRESENTATION - 58 DATE: JUNE 2003 Page 58 XSD22A01

54 Identification Page Block (cont d) CHAPTER EXAMPLE IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED SRM PRESENTATION - 59 DATE: JUNE 2003 Page 59 XSD22A01

55 Identification Page Block (cont d) STANDARD MANUAL EXTRACT IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED SM DAN26 SRM PRESENTATION - 60 DATE: JUNE 2003 Page 60 XSD22A01

56 Identification Page Block (cont d) IDENTIFICATION TABLE - THICKNESS/PARTNUMBER COLUMN The Part-Number (PN) corresponding to the structural component is shown in this column. Within the PN, the first nine characters give the Detailed Drawing number of the component, which is an entry key to the Airbus Drawing set. In general the as drawn parts are LH and are provided with an even part number (eg. 202). In the SRM, the identification table always states the LH part number on the first line and the RH part number (when indicated) on the second line. IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED THICKNESS IN MM (IN.) AND/OR PARTNUMBER D Detailed Drawing Number D Part Number (PN). (200 to 999 for detailed parts PN : Left Hand side (always first line, even numbers ) SRM PRESENTATION 61 DATE: JUNE 2003 Page 61 XSD22A01

57 Identification Page Block (cont d) IDENTIFICATION TABLE - IC COLUMN This column shows the Interchangeability status of the structural part. IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED Interchangeability of the part I C One way interchangeable (post-mod part to be used to replace pre-mod part) Two ways interchangeable (post-mod or pre-mod part can be used) No interchangeability SRM PRESENTATION 62 DATE: JUNE 2003 Page 62 XSD22A01

58 Identification Page Block (cont d) IDENTIFICATION TABLE - ACTION OR REPAIR COLUMN This column gives indication concerning the action or repair to be performed. For existing general or specific repairs, the Chapter/Section/Sub-Section is inserted. For a recommendation to replace the part, the word Replace is inserted. Where left blank, a case by case assessment has to be performed to determine the relevant corrective action (part replacement, repair as per SRM or specific repair as per Airbus SAS definition). IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED ACTION OR REPAIR - PB201 - Existing repair within the specific chapter or - Replace or - left black - a case by case assessment is necessary to determine the action tp be performed SRM PRESENTATION 63 DATE: JUNE 2003 Page 63 XSD22A01

59 Identification Page Block (cont d) IDENTIFICATION TABLE - STATUS MOD/PROP SB/RC COLUMN Linked with the Item column, the STATUS MOD/PRP, SB/RC column gives the modification or service Bulletin driving the different evolutions of a structural component (listed in column Item). A prefix letter is used to identify the status BEFORE ( B letter) or AFTER ( A letter) SB or Modification. The suffix letter (A, B, C, D ) indicated at the end of the MOD / PROP (and column S of the MOD / SB list) shows the different effectivities within the same MOD / PROP number. IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED Refer to relevant: Modification/Service Bulletin List to find effectivity. STATUS (MOD/PROP) SB/RC Different evolutions of Item 1. Linked to production modification / SB A P0868 A A: After Modification. Mod. Proposal B: Before Modification... Mod. Number A: After SB... B: Before SB... A SB Modification suffix (A, B, C, ) SB Number Refer to relevant Service Bulletin List SRM PRESENTATION 64 DATE: JUNE 2003 Page 64 XSD22A01

60 Identification Page Block (cont d) IDENTIFICATION TABLE - STATUS MOD/PROP SB/RC COLUMN (CONT D) To find the relevant effectivity linked to a modification shown in the STATUS column, the user must refer to the Modification/Service bulletin list. Note: the status Before or After modification/sb and the relevant modification solution (suffix letter) should not be forgotten. Within the mod/sb list the effectivities are expressed in MSN (Manufacturer Serial Number). Note: to find the relationship in between Customer Version number (e.g.. SWR ) and the MSN, the user can refer to the Aircraft Allocation list of the INTRODUCTION chapter of the SRM. IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED MODIFICATION Refer to relevant: Modification/Service Bulletin List to find effectivity. SRM PRESENTATION 65 DATE: JUNE 2003 Page 65 XSD22A01

61 Identification Page Block (cont d) IDENTIFICATION TABLE - STATUS MOD/PROP SB/RC COLUMN (CONT D) RECORDABLE CONCESSIONS IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED RC : RECORDABLE CONCESSIONS SRM PRESENTATION 66 DATE: JUNE 2003 Page 66 XSD22A01

62 Identification Page Block (cont d) IDENTIFICATION TABLE - STATUS MOD/PROP SB/RC COLUMN (CONT D) SERVICE BULLETIN IDENTIFICATION PAGES - IDENTIFICATION TABLE DETAILED SB : SERVICE BULLETIN SRM PRESENTATION 67 DATE: JUNE 2003 Page 67 XSD22A01

63 Configurations GENERAL When modification or Service Bulletin are extensive and the preceding method of reflecting effectivity becomes cumbersome, thus distracting from the continuity of subject matter, additional page blocks are established. These additional page blocks are further identified by the introduction of a configuration code (CONFIG-1, CONFIG-2), etc ) following the Chapter/Section/Sub-section. Configuration codes are always in ascending, sequential numerical order, I.e., CONFIG-1, CONFIG-2, CONFIG-3, etc The first example shown below illustrate the change in the A320 Vertical stabilizer spar box design and manufacturing following modification 26500K4924H. CONFIGURATIONS CONFIGURATION CONFIGURATION 1 CONFIGURATION 2 SRM PRESENTATION 68 DATE: JUNE 2003 Page 68 XSD22A01

64 Configurations DATE: JUNE 2003 Page 69 XSD22A01

65 Configurations Configurations are also used in chapter 54 for identifying different pylons and nacelles for specific engines. In the example shown below: - Configuration 1 covers the pylons and nacelles for CFM56-5 engines - Configuration 2 covers the pylons and nacelles for V2500 engines. CONFIGURATIONS - PYLONS CONFIGURATION 1 for CFM56 engine CONFIGURATION 2 for IAE V2500 engine SRM PRESENTATION 70 DATE: JUNE 2003 Page 70 XSD22A01

66 Configurations Example: A320 Pylons & Nacelles: - Configuration 1 covers engine & pylon for CFM56-5 engines - Configuration 2 covers engine & pylon for V2500 engines. CONFIGURATIONS - PYLONS SRM PRESENTATION 71 DATE: JUNE 2003 Page 71 XSD22A01

67 Allowable Damage Page block The information to be found within allowable Damage Page Block enables the operator to define whether a damaged airplane may be returned into service without repair. An allowable damage permitted has no significant effect on the strength or fatigue life of the structure, which must still be capable of fulfilling its function. Allowable damage may require minimal rework such as cleanup or drilling of stop holes. Basically the allowable page block contains different page types: - General information pages, including repair applicability, - Damage data/criteria tables, - Damage localization (zoning) figures, - Allowable damage diagram. ALLOWABLE DAMAGE PAGE BLOCK (PB 101) APPLICABILITY PARAGRAPH 4.A. SRM PRESENTATION 72 DATE: JUNE 2003 Page 72 XSD22A01

68 Allowable Damage Page Block (cont d) USAGE PRINCIPLE After a careful reading of the first information page(s), the first step in the allowable damage determination consists in the use of Damage Data table. The Damage Data /criteria Table gives enables the operator to determine the relevant figures and diagram which have to be used. ALLOWABLE DAMAGE PAGE BLOCK (PB 101) FIG. 101 SRM PRESENTATION 73 DATE: JUNE 2003 Page 73 XSD22A01

69 Allowable Damage Page Block (cont d) USAGE PRINCIPLE (CONT D) The damage localization (area) figures enable the operators to select the applicable Allowable Damage diagram depending on the damage location within the part. ALLOWABLE DAMAGE PAGE BLOCK (PB 101) SRM PRESENTATION - Allowable Damage Pages (cont d) 74 DATE: JUNE 2003 Page 74 XSD22A01

70 Allowable Damage Page Block (cont d) TYPICAL ALLOWABLE DAMAGE DIAGRAM As a last step of the damage investigation, the use of the Allowable Damage Diagrams provides the necessary information concerning the actions to be performed depending on damage extent. ALLOWABLE DAMAGE PAGE BLOCK (PB 101) SRM PRESENTATION 75 DATE: JUNE 2003 Page 75 XSD22A01

71 Repairs Page Block GENERAL The Repairs Page block (PB 201), contains necessary information to carry out permissible repairs. Each of the repairs is described with illustrations and procedure instructions which includes repair applicability data and repair materials lists. REPAIRS PAGE BLOCK (PB 201) Safety Precautions List of available repair schemes SRM PRESENTATION -Repairs 76 DATE: JUNE 2003 Page 76 XSD22A01

72 Repairs Page Block (cont d) LIST AVAILABLE REPAIR SCHEMES At the beginning of each repair page block, a list of available repair schemes is provided for a quick assess to the repairs. REPAIRS PAGE BLOCK (PB 201) List of available repair schemes Reference to standard fuselage skin repairs (Chapter ) Reference to a repair specific to this fuselage section (Chapter PB 201 Paragraph 5.A. fig. 201) SRM PRESENTATION - Repairs (cont d) 77 DATE: JUNE 2003 Page 77 XSD22A01

73 Repairs Page Block (cont d) REPAIR INSTRUCTIONS The relevant paragraph of the repair instructions contain information related to: - The applicability of the concerned repair, - General reminders linked to repair principles and rules. REPAIRS PAGE BLOCK (PB 201) REPAIR APPLICABILITY GENERAL REPAIR RULES REMINDERS SRM PRESENTATION 78 DATE: JUNE 2003 Page 78 XSD22A01

74 Repairs Page Block (cont d) REPAIR INSTRUCTIONS All the materials (repair materials and consumable materials) are listed within the concerned repair instructions. Consumable materials are call-up using their CML code (e.g ). For more information on these materials the user can refer to the SRM chapter consumable materials and/or the CML document. REPAIRS PAGE BLOCK (PB 201) REPAIR MATERIALS CALL-UP FOR CONSUMABLE MATERIALS USING CML References SRM AND / OR EXAMPLE EXAMPLE CML Sealants Chapter SRM PRESENTATION 79 DATE: JUNE 2003 Page 79 XSD22A01

75 Repairs Page Block (cont d) REPAIR INSTRUCTIONS SRM Consumable Material example REPAIRS PAGE BLOCK (PB 201) Chapter Consumable Materials EXAMPLE SRM SRM PRESENTATION 80 DATE: JUNE 2003 Page 80 XSD22A01

76 Repairs Page Block (cont d) REPAIR INSTRUCTIONS CML extract REPAIRS PAGE BLOCK (PB 201) CML SRM PRESENTATION 81 DATE: JUNE 2003 Page 81 XSD22A01

77 Repairs Page Block (cont d) REPAIR INSTRUCTIONS Repair Procedure with all the steps to be performed with references to the standard processes and practices covered within the chapter 51. REPAIRS PAGE BLOCK (PB 201) REPAIR INSTRUCTIONS SRM PRESENTATION 82 DATE: JUNE 2003 Page 82 XSD22A01

78 Repairs Page Block (cont d) REPAIR ILLUSTRATIONS REPAIRS PAGE BLOCK (PB 201) REPAIR ILLUSTRATION(S) SRM PRESENTATION 83 DATE: JUNE 2003 Page 83 XSD22A01

79 THIS PAGE INTENTIONALLY LEFT BLANK DATE: JUNE 2003 Page 84 XSD22A01

80 STRUCTURE REPAIR COURSE FOR ENGINEERS 1. DOCUMENTATION 1.2. SRM - STRUCTURAL REPAIR MANUAL STRUCTURE REPAIR INSPECTIONS (SRI) General Layout IIR - Inspection Instruction Reference Inspection Call-up Within Specific Chapters SRI Chapter Contents DATE: JUNE 2003 Page 85 XSD22B01

81 STRUCTURE REPAIR COURSE FOR ENGINEERS STRUCTURE REPAIR INSPECTIONS (SRI) General For permanent repairs with inspection program, inspections are quoted along with the repair. Due to the amount of inspections, these requirements have been transferred in a separate appendix to the SRM: - For more clarity of the SRM - For better handling of the inspection requirements. GENERAL SRI Chapter 00 INTRODUCTION STRUCTURE REPAIR INSPECTIONS SRI 51 DOORS 52 FUSELAGE 53 PYLONS / NACELLES 54 STABILIZERS 55 WINGS 57 STRUCTURE SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 86 DATE: JUNE 2003 Page 86 XSD22B01

82 STRUCTURE REPAIR COURSE FOR ENGINEERS Layout LAYOUT SRI STRUCTURE REPAIR INSPECTIONS Inspection Reference SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 87 DATE: JUNE 2003 Page 87 XSD22B01

83 STRUCTURE REPAIR COURSE FOR ENGINEERS IIR - Inspection Instruction Reference I.I.R. - INSPECTION INSTRUCTION REFERENCE Inspection Instruction Reference (I IR) SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 88 DATE: JUNE 2003 Page 88 XSD22B01

84 STRUCTURE REPAIR COURSE FOR ENGINEERS Inspection Call-Up Within Specific Chapters This inspection reference number first appears within the list of available repair scheme, column inspection instruction reference instead of a simple cross. (e.g.: ). INSPECTION CALL-UP WITHIN SRM SPECIFIC CHAPTERS Related Repair Page Bloc of concerned specific chapter EG. Fuselage PB AVAILABLE REPAIR SCHEME list. REPAIR PROCEDURE Aft Lavatory Vent outlet External repair from stringer 30RH thru 33RH between FR69 and FR70 PARAGRAPH FIGURE INSPECTION INSTRUCTION REFRENCE 5. D Structural repair inspections SRI SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 89 DATE: JUNE 2003 Page 89 XSD22B01

85 STRUCTURE REPAIR COURSE FOR ENGINEERS Inspection Call-Up Within Specific Chapters (cont d) The caution note in the repair instructions and associated illustration clearly specifies the inspection reference. The inspection instruction are to be found within the Structural Repair Inspections Chapter of the SRM. INSPECTION CALL-UP WITHIN SRM SPECIFIC CHAPTERS REPAIR INSTRUCTIONS Paragraph 5. D. Inspection Instruction Reference (I IR) SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 90 DATE: JUNE 2003 Page 90 XSD22B01

86 STRUCTURE REPAIR COURSE FOR ENGINEERS INSPECTION CALL-UP WITHIN SRM SPECIFIC CHAPTERS REPAIR ILLUSTRATION Fig. 205 Figure 205 SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 91 DATE: JUNE 2003 Page 91 XSD22B01

87 STRUCTURE REPAIR COURSE FOR ENGINEERS SRI Contents At the beginning of the SRI Chapter, a table of content provides the list of repairs concerned by special inspections requirements. SRI CONTENTS SRI Table Of Contents SRI STRUCTURE REPAIR INSPECTIONS SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 92 DATE: JUNE 2003 Page 92 XSD22B01

88 STRUCTURE REPAIR COURSE FOR ENGINEERS SRI Contents (cont d) Within the introduction section of the SRI, the Inspection Instruction Schemes table enables the operator to locate the inspection instruction within the SRI. (for inspection ref instructions are to be found in paragraph 1.A.). SRI CONTENTS List Inspection Instruction Scheme SRI STRUCTURE REPAIR INSPECTIONS SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 93 DATE: JUNE 2003 Page 93 XSD22B01

89 STRUCTURE REPAIR COURSE FOR ENGINEERS SRI Contents (cont d) Within the concerned paragraph, the inspection instruction are divided into three main parts: - The general information part, which reminds the inspection location - The Inspection Information Table (a/c concerned, inspection threshold, interval, required inspection methods) - The Inspection areas illustration. SRI CONTENTS INSPECTION INSTRUCTIONS SRI STRUCTURE REPAIR INSPECTIONS General Information Inspection location Inspection Information Table -A/C, - Threshold, -intervals, - Inspection method(s), SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 94 DATE: JUNE 2003 Page 94 XSD22B01

90 STRUCTURE REPAIR COURSE FOR ENGINEERS SRI Contents (cont d) SRI CONTENTS SRI STRUCTURE REPAIR INSPECTIONS Inspection Areas Illustration SRI - STRUCTURE REPAIR INSPECTIONS CHAPTER 95 DATE: JUNE 2003 Page 95 XSD22B01

91 1. DOCUMENTATION 1.3. AIRBUS DRAWING SET DRAWING SET PRESENTATION Drawing Set General Drawing Set Package Drawing Aperture Card Drawing Picture Drawing Number / Part Number Schedule Sheet (Parts List) Parts Usage (PU) DATE: JUNE 2003 Page 97 XSD23A01

92 DRAWING SET PRESENTATION Drawing Set General The drawing set delivered is customized. It includes mechanical drawings. All data related to aircraft wiring and equipment are contained in the wiring manual. The drawing set generally is delivered in two stages: - The basic set at first aircraft delivery - Complementary drawings six months after first delivery. The drawing set is not subject to a regular revision service but will be updated to incorporate additional aircraft, so as to reflect the complete fleet configuration of an airline. Two categories of drawings are delivered: - Installation and Assembly Drawings (IAD) - Detailed Drawings (DD). DRAWING SET GENERAL BASIC SET FIRST A/C DELIVERY COMPLEMENTARY DRAWINGS 6 Months after first A/C delivery AIRBUS DRAWING SET No regular revisions, but updated to incorporate additional A/C Reflects the complete fleet configuration of a given Airline AID - INSTALLATION & ASSEMBLY DRAWINGS DD - DETAILED DRAWINGS DRAWING SET PRESENTATION 98 DATE: JUNE 2003 Page 98 XSD23A01

93 Drawing Set General (cont d) Airbus drawings are divided into aircraft families as follows: - one set for A300, A310, A one set for A319, A320, A321 - one set for A330, A340. DRAWING SET GENERAL Wide body AIRBUS DRAWING SET Aisle Family Divided into A/C families DRAWING SET PRESENTATION 99 DATE: JUNE 2003 Page 99 XSD23A01

94 Drawing Set General (cont d) The drawing set package contains: - one set of drawings called picture sheets on aperture cards including Assembly and Installation drawings and depending on agreements, detailed drawings - one set of associated parts lists (called Schedules) - one set of data for parts effectivity identification (called part usage - PU) - one Drawing Numerical Index (DNI) which is the list of drawings supplied. DRAWING SET PACKAGE AIRBUS DRAWING SET PACKAGE PICTURE SHEET SCHEDULE PART USAGE DNI DRAWING NUMERICAL INDEX Book DRAWING SET PRESENTATION 100 DATE: JUNE 2003 Page 100 XSD23A01

95 Drawing Set Package (cont d) AIDA (Airbus Drawing Access) represents a new way of distributing drawings, which will replace drawing supplied on microfilm aperture cards and film cartridges for associated schedule and part usage. AIDA is available trough AOLS (Airbus On Line Services). AIDA provides the operators with on line access to mechanical drawings for all major aircraft assemblies, subassemblies and installations, for the whole fleet of Airbus aircraft. Access to detail part drawings is the subject of contract negotiations. Drawings available within AIDA service reflect the latest production drawing issue. DRAWING SET PACKAGE AIRBUS DRAWING SET PACKAGE PICTURE SHEET SCHEDULE PART USAGE DNI DRAWING NUMERICAL INDEX Book AIRBUS on-line services MECHANICAL DRAWINGS SERVICE AIDA DRAWING SET PRESENTATION 101 DATE: JUNE 2003 Page 101 XSD23A01

96 Drawing Set Package (cont d) PARTS LIST (Schedule sheet) PICTURE SHEET Geometrical dimensions of a part or assembly. DATE: JUNE 2003 Page 102 XSD23A01

97 Drawing Set Package (cont d) PARTS USAGE Provides effectivity and part number of the Next Higher Assembly DATE: JUNE 2003 Page 103 XSD23A01

98 Drawing Number / Part Number A drawing numbering chart is available by project: A300, A310, A see drawing A A319, A320, A321 see drawing D A330, A340 see drawing F This chart explains the drawing number breakdown up to the 4th digit after the aircraft project code letter, in accordance with ATA breakdown. DRAWING NUMBER/PART NUMBER AIRBUS DRAWING NUMBERING CHART A drawing numbering chart is available per project: A D F DRAWING SET PRESENTATION 104 DATE: JUNE 2003 Page 104 XSD23A01

99 Aircraft Identification AIRCRAFT FAMILIES A300, A , A310 - Wide Bodies W A320, A321, A319, A318 - Single Aisle N A330, A340 - Long Range L CERTIFICATION: Type: Relates to the specific design definition for certification purposes (e.g A300, A310,...) Series: Designates specific structure and systems design characteristic within an aircraft type (e.g A ,...) Model: Designates a series with a particular engine installation (e.g A : CF6-80EA2 (GE engine)). DERIVATIVE: Development of an existing type for a specialized role (e.g.: F=Freighter, C=Combi(A340) or convertible(a300/a310)). VARIANT: Designates a specific model definition (e.g.: modified design fight) TYPE-MODEL VARIANT VARIANT DEFINITION MTOW MLW MZFW A (GROWTH) A A MSN - MANUFACTURER S SERIAL NUMBER: Individual identifier allocated to a complete aircraft within each Aircraft Family. A , A300, A310: MSN 0001 to 9999 A320, A321, A319, A318: MSN 0001 to 9999 A330, A340: MSN 0001 to 9999 PRODUCTION STANDARD: IDENTIFIER WIDEBODY (W) SINGLE AISLE (N) LONG RANGE (L) A300 A310 A319 A320 A321 A330 A340 ST1 A300B2 A A A ST2 A300B4 A A ST3 A A C ST4 A (GROWTH) ST5 A A (8000NM) ST6 A A A R ST7 A A ST8 A (GROWTH) STB A STA A DATE: JUNE 2003 Page 105 XSD23A01

100 Drawing Aperture Card When Picture sheets are supplied under 35 mm film aperture cards, the complete description of the drawing is printed on the top of the card including drawing number, sheet number, total number of sheets, frame number and drawing title. DRAWING APERTURE CARD A/C LETTER DRW ISSUE CARD CODE ATA 100 CHAPTER ATA 100 SECTION SHEET NUMBER TOTAL OF FRAMES SIZE CODE CARD CODE GEO. IDENT A/C LETTER CHAP ATA 100 DRAWING NUMBER ISSUE SHEET No. Nb OF SHEETS FRAME No NB OF FRAMES DRAWING TITLE SIZE CODE AIRBUS DESIGN OFFICE ORIGIN Drawing system DRW SEQUENCE No GEOGRAPHICAL (REF TO REFERENCE ABD0004) AIRBUS PROPERTY (C1979) BP No BLAGNAC-FRANCE TOTAL NUMBER OF SHHETS FRAME NUMBER DRAWING TITLE 6 MUST NOT BE COPIED WITHOUT PERMISSION OF THE OWNERS 7 8 DOC. CATEG SHEET No. Nb OF SHEETS FRAME No Nb OF FRAMES DRAWING NUMBER ISSUE DRAWING TITLE IN ENGLISH DRAWING SET PRESENTATION 106 DATE: JUNE 2003 Page 106 XSD23A01

101 Drawing Picture The picture area of the drawing shows the geometric or dimensional representation of parts, assemblies or installations. The picture sheet of parts and assemblies is to be read in conjunction with the corresponding separate schedule sheet(s). Fields explanation: Modification: Indication of the drawing issue index (capital letter) and the ECN (Engineering Change Note) number starting from the top of the column. The ECN is an issue/authorization document for Airbus internal use only and is not part of the drawing set supplied to the Operators. Interchangeable Part: In case of interchangeable part the field (YES-NO) is crossed out and the drawing number is indicated. Limits not stated: Dimensions tolerances according to ABD0001 are applicable if no special indication are given on the drawing. Identification Marking: Identification marking of parts and assemblies according to ABD0003. Surface Finish: According to ABD0002. Note: Airbus internal specifications, ABD0001, ABD0002 and ABD0003 are covered in the Standard Manual (SM). PICTURE SHEET - GENERAL Modification column MODIFICATIONS ISSUE ECN A DRN Drawing Field ISSUE ECN 29995NW1 K DRN DWG ZONE 2 Interchangeable Parts Dimensions / Tolerances Surface finish DWG Issue LIMITS NOT STATED ABD 0001 INDENTIFICATION MARKINGS ABD 0003 SURFACE FINISH ABD 0002 INTERCHANGEABLE PART DRAWING No YES NO SCALE VALID FOR MASTER DRAWING ONLY 1 DTN CHK STRESS DRW SYSTEM Identification & Marking DO ORIGIN APP Drawing title First angle projection WTS PROJECTION D PROCESS G K SHEET ISSUE B Drawing Number A DRAWING SET PRESENTATION 107 DATE: JUNE 2003 Page 107 XSD23A01

102 Drawing Number / Part Number The drawing number is made of nine digits starting with the aircraft project letter. The Part Number: three digits are added to the drawing number - Sub assemblies, assemblies and installation have a suffix in the range 000 to Detail parts have a suffix in the range 200 to 999. The part number may be completed by a two digit suffix + one additional character for domestic use in the IPC to comply with manufacturing or spares requirements. PICTURE SHEET - DRAWING NUMBER/PART NUMBER AIRBUS DRAWING NUMBER / PART NUMBERS (P/N) AIRBUS DOMESTIC DRAWING NUMBER PART NUMBER A Geographical Reference A/C Project Code Letter Part Number 000 to 199 for sub-assemblies, assemblies and installation. 200 to 999 for detail parts ATA Chapter Number Section (Within ATA Chapter) Design Office Identification A and B = A300,A310,A D = A319,A320,A321 F = A330,A340 Sequence Number DRAWING SET PRESENTATION 108 DATE: JUNE 2003 Page 108 XSD23A01

103 DATE: JUNE 2003 Page 109 XSD23A01

104 Picture Sheet - Projection Angles PICTURE SHEET - PROJECTION ANGLE AIRBUS S DRAW DRAWINGS 4 First Angle Projection Third Angle Projection DRAWING SET PRESENTATION 110 DATE: JUNE 2003 Page 110 XSD23A01

105 Schedule Sheet (Parts List) The schedule contains the list of parts called-up (items) on the corresponding picture sheet(s). The schedule (parts list) enables to go down from an assembly or installation drawing to a detail drawing. Related picture sheets and schedules bear the same drawing number. Some schedules may not have a related picture sheet. The schedule set is not customized. It is supplied as an envelop set per aircraft family. SCHEDULE SHEET A ALT ALT ALT ALT ALT ALT ALT ALT ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP 0H004 G E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY Issue mod index D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 Zone Item Part Number Part Issue PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. DATE 20/1993 Drawing title PIC. K SHT. 001 TITLE: AIRBUS MECHANISM INSTL FLAP Drawing number Description Material Specification Hand Picture/schedule sheet issue index Protec tion Id In Rem Sheet nb DRAWING NO: G1 D SHEET S001 ISSUE F CONTD Schedule issue DRAWING SET PRESENTATION 111 DATE: JUNE 2003 Page 111 XSD23A01

106 Schedule Sheet (Parts List) (cont d) FIELDS EXPLANATION: Sheet: Sheet number e.g S01, S02. Issue: For each modification a schedule is reissued completely (no differential issue). Issue/Mod Index: On sheet one only. Record of schedule sheet 1 issue indexes and the related Engineering Change Note(ECN) number for each issue. The issue is indicated with 3 characters and the ECN number with 13 characters. (ECN number for domestic use only). The record starts at the bottom left hand corner. Further and subsequent entries are horizontally to the right in sequence before commencing again on the next horizontal line. Picture and Schedule Sheet/Issue Index: This record only appears on sheet one of the schedule. It is the master record for the drawings. This index shows the number of picture and schedule sheet(s) at the latest issue. Example: PIC B A SHT The drawing picture is composed of two sheets, sheet 001 is issue A, sheet 002 is issue B. In case of schedule without a related picture sheet, the field PIC is not filled. SCHEDULE SHEET A ALT ALT ALT ALT ALT ALT ALT ALT ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY 18 D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D at the A LEVER latest FLAP issue. CONTROL 4 D B LEVER FLAP CONTROL D Example: A LINK ELBOW PIC. B A 000 D A LINK 000 Zone Item Part Number Part Issue Show the number of picture sheet(s) SHT F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP 0H004 G Picture: E MECHANISM 2 sheets, INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 Description Material Specification sheet 001: issue B sheet 002: issue A Hand Protec tion Id In Rem D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 PIC. K SHT. 001 Picture/schedule sheet issue index PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. TITLE: AIRBUS MECHANISM INSTL FLAP DRAWING NO: G1 D SHEET S001 ISSUE F DATE 20/1993 CONTD DRAWING SET PRESENTATION 112 DATE: JUNE 2003 Page 112 XSD23A01

107 Schedule Sheet (Parts List) (cont d) SCHEDULE SHEET Picture / Schedule sheets issue index - Example SCHEDULE DRAWING Leader sheet Assembly Sheet 1 Sheet 2 Sheet 3 Sheet 4 Parts list List A - A A A - First release (leader sheet and parts list). Drawing sheet 1, 2, 3 new. B - A B A - First modification. Only drawing sheet 2 affected. C - A B A C Second modification. Drawing sheet 4 new. D D D B D C Third modification. Schedule, assembly list new. Drawing sheets 1 and 3 modified. E E D B D C Fourth modification. Only schedule assembly list is affected. DRAWING SET PRESENTATION 113 DATE: JUNE 2003 Page 113 XSD23A01

108 Schedule Sheet (Parts List) (cont d) FIELDS EXPLANATION (CONT D): Item Number: All parts included in an assembly or installation drawing are allocated with an item number (into circles on the drawing) which is listed in this column. Part Number: List of parts, assemblies, installations, standard parts, etc called up in the assemblies. Part Issue: show the latest issue of the parts detailed on the drawing. Identifiable part: The letter X in this column indicates that the part is identifiable. Interchangeable and Replaceable Part: - Letter I : part contractually interchangeable, (applies to parts detailed on the corresponding drawing only. - Letter R : Replaceable parts. - Letter L : parts listed as spares (which are not coded as I or R). Zone: A five digit character reference shown at the item number indicates the picture sheet number and the reference of the zone containing the part onto this drawing. E.g: O1B05 Picture sheet 01 and zone B05 on the drawing. SCHEDULE SHEET A29998 DRAWING PICTURE ALT ALT ALT ALT ALT ALT ALT ALT ALT Item Number MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY 31 I ABS0114V3-4 : Part contractually SCREW - HEXAGONAL HEAD 30 NAS interchangeable. SCREW - HEXAGONAL HEAD Interchangeable & R : Replaceable part. 22 D B WASHER 000 Replaceable 3 22 L : D Part listed as A spare WASHER (not coded I or R). 18 D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK 000 Identifiable part 007 F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G01 Part 005 Issue E MECHANISM INSTL FLAP 0H004 G E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 Part Number Zone Item Part Number Part Issue Description Material Specification Hand Protec tion Id In Rem Part D00 HG20018ST1AA93 location on E00 Picture NG20468ST1AR01 sheet F00 HG23013ST1AA01 A00 NG20018ST1AJ77 ( 01B05 : Sheet B00 NG29001EF1AB80 01 Zone B05 ) C00 NG20018ST1AL90 PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. DATE 20/1993 PIC. K SHT. 001 Description / Mat. Spec. / Handling TITLE: AIRBUS DRAWING NO: MECHANISM INSTL FLAP G1 D SHEET ISSUE S001 F CONTD DRAWING SET PRESENTATION 114 DATE: JUNE 2003 Page 114 XSD23A01

109 Schedule Sheet (Parts List) (cont d) Within the part number column reference to standard parts can be made. The user can refer to the Airbus Standard Manual which contain the collection of standard used in Airbus projects. SCHEDULE SHEET A Item 2 Number ALT ALT ALT ALT ALT ALT ALT ALT ALT ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER DRAWING PICTURE MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY 18 D A WASHER E D B BUSH E01 SM 2S 14 D A BUSH SHOULDERED Production E01 Standard 3 12 D A SPACER E06 2 Basic Standard 10 D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK 000 Zone Item Part Number Part Issue 007 F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP 0H004 G E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 Description Material Specification Hand Protec tion Id In Rem PIC. K D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 SHT. 001 PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. TITLE: AIRBUS MECHANISM INSTL FLAP DRAWING NO: G1 D SHEET S001 ISSUE F DATE 20/1993 CONTD DRAWING SET PRESENTATION 115 DATE: JUNE 2003 Page 115 XSD23A01

110 Schedule Sheet (Parts List) (cont d) FIELDS EXPLANATION: Quantity per assembly: SCHEDULE SHEET Item Number A ALT ALT ALT ALT ALT ALT ALT ALT ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER Quantity per Assy D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP 0H004 G E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY Zone Item Part Number Part Issue Description Material Specification Hand Protec tion Id In Rem Drawing Sub -Assembly D00 HG20018ST1AA93 E00 NG20468ST1AR01 Numbers F00 HG23013ST1AA01 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 Identification PIC. K Identification of of different different variants variants of of the the basic SHT. basic assembly 001 assembly drawing drawing (000) (000) PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. TITLE: AIRBUS MECHANISM INSTL FLAP DRAWING NO: G1 D SHEET S001 ISSUE F DATE 20/1993 CONTD DRAWING SET PRESENTATION 116 DATE: JUNE 2003 Page 116 XSD23A01

111 Schedule Sheet (Parts List) (cont d) FIELDS EXPLANATION (CONT D): Modification Reference Number: When the modification above the storable assembly level introduces a choice Before/After mod control or reference code control is used to minimize the repercussions of drawing changes. The effectivity of the variant is explained in the relevant Part Usage. When a modification number is used, a prefix indicates if the status referred to is Before or After modification. A : After Mod, (e.g: A29998) B : Before Mod. (e.g: B29903) When a reference code number is used, the prefix REF is used (e.g: Ref 0200). SCHEDULE SHEET A ALT ALT ALT ALT ALT ALT ALT ALT Modification 1 1 Ref. Number ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP 0H004 G E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY Zone Item Part Number Part Issue Description Material Specification Hand Protec tion Id In Rem PIC. K D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 SHT. 001 PROT. TREAT. CHART: THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. TITLE: AIRBUS MECHANISM INSTL FLAP DRAWING NO: G1 D SHEET S001 ISSUE F DATE 20/1993 CONTD DRAWING SET PRESENTATION 117 DATE: JUNE 2003 Page 117 XSD23A01

112 Schedule Sheet (Parts List) (cont d) FIELDS EXPLANATION (CONT D): Protective Treatment Chart: The reference of the document explaining the protective treatment codes (indicated in protective treatment column). Most of the cases, the reference to the PMS (process & Materials Specification) technical Note A is made. In some cases the standard reference ASNA2101 can be found in this field. The user can refer to the Standard manual where the list of codes (e.g.: E01) are listed and explained. Protective Treatment: Indicates the protective treatment code number (e.g: E01 or 701) for the corresponding part. It has to be used in accordance with the reference document/chart indicated in the Protective treatment Chart field. SCHEDULE SHEET A ALT ALT ALT ALT ALT ALT ALT ALT Protective Treatment code within referenced treatment chart ( PMS or SM ) 31 ABS0114V3-4 SCREW - HEXAGONAL HEAD within 30 NAS referenced treatment SCREW - HEXAGONAL chart HEAD 22 D B WASHER D A WASHER D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK 000 MOD. NO BEFORE/AFTER QUANTITY PER ASSEMBLY Protective treatment Chart Zone Item Part Number Part Issue PIC. K within ( PMS or SM ) Reference to PMS Technical Note D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 SHT. 001 e.g. A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 A PROT. TREAT. CHART: TITLE: AIRBUS THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED WITHOUT THE EXPRESS PRIOR WRITTEN ASNA2101 AUTHORIZATION OF AEROSPATIALE AND ITS CONTENTS SHALL NOT BE DISCLOSED. D.O. RESP. MECHANISM INSTL FLAP Reference to SM DATE 20/1993 Chart e.g: ASNA F MECHANISM INSTL Code FLAP within 0H006 PMS G01 Code within SM 006 F MECHANISM INSTL Technical FLAP G01 Note chart 005 E MECHANISM INSTL FLAP 0H004 G01 e.g: 004 E MECHANISM INSTL FLAP 701 e.g: G01 E D MECHANISM INSTL FLAP 0H002 G D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP 0H000 G D MECHANISM INSTL FLAP G01 Description Hand Material Specification PMS DRAWING NO: SM G1 D Protec tion TN SHEET S001 Id In Rem ISSUE F CONTD DRAWING SET PRESENTATION 118 DATE: JUNE 2003 Page 118 XSD23A01

113 Schedule Sheet (Parts List) (cont d) Protective Treatment Chart: PMS PROTECTIONS - TN A SCHEDULE SHEET PMS PROTECTIONS A DRAWING SET PRESENTATION 119 DATE: JUNE 2003 Page 119 XSD23A01

114 Schedule Sheet (Parts List) (cont d) Protective Treatment Chart: PMS PROTECTIONS - TN A SCHEDULE SHEET A DRAWING SET PRESENTATION 120 DATE: JUNE 2003 Page 120 XSD23A01

115 Schedule Sheet (Parts List) (cont d) Protective Treatment Chart: ASNA Protections SCHEDULE SHEET ASNA2101 Process Specification DRAWING SET PRESENTATION 121 DATE: JUNE 2003 Page 121 XSD23A01

116 Parts Usage (PU) The parts usage gives the effectivity of the parts listed in the drawing schedule and enables the user to find from any part number the next higher assembly (NHA) up to the desired customized aircraft general assembly drawing. The parts usage set is not customized. It is supplied as an envelope set per aircraft family. FIELD EXPLANATIONS (CONT D): Part: Concerned part defined on the corresponding schedule. Modification Number: Indication of the Before/After mod reference number as explained in the drawing schedule. Next Assembly: Indicates the NHA (Next Higher Assembly). Quantity: Quantity of parts required to complete the NHA. Effectivity: Effectivity of a part. Is stated at the level of each NHA number. PARTS USAGE (PU) Issue index of the part Quantity of parts to complete the NHA PART ISS NBR. 000 D00 DESCRIPTION MOD. NUMBER NEXT ASSEMBLY MECHANISM INSTL FLAP D D00 MECHANISM INSTL FLAP D Partnumber 004 E00 MECHANISM INSTL FLAP D NHA Drawing number QTY Aircraft Type / Family: Single Aisle Version From To... 1 AAA BCA PAA AAA BCA PAA AAA ALK CYP IAC K2W OHY ACA ADR AFR AFR CYP IAC ITF NWA Effectivity ACA ADR AFR AFR CYP IAC ITF NWA ACA AMC DLH IBE LUR ADR ANA GFA ITF MSR PAA AFR BCA G2P I2L MXA RJA AFR CDN G2X KAC NWA SAA E00 AIRBUS PROPERTY BLAGNAC FRANCE, BP No33 DATE: MAY 5/2000 MECHANISM INSTL FLAP D AAA ACA ALK AMC CYP DLH IAC IBE K2W LUR OHY PARTS USAGE ADR ANA GFA ITF MSR PAA This document must not be copied without permission of the owner AFR BCA G2P I2L MXA RJA Drawing Number: G1 D AFR CDN G2X KAC NWA SAA Page U002 DRAWING SET PRESENTATION 122 DATE: JUNE 2003 Page 122 XSD23A01

117 Parts Usage (PU) (cont d) In the parts usage the effectivity are expressed in customer version or production standard. Note: A cross reference table which gives correspondence between the MSN (Manufacturer Serial Number) and customer version is available in the AMM (Aircraft Maintenance Manual). The user can also refer to the Aircraft Allocation table to be found within the Introduction pages of the SRM (Structural Repair Manual). PARTS USAGE (PU) EFFECTIVITY CUSTOMER VERSION PRODUCTION STANDARD E.g: E.g: LH LH1 = Customer version 001 = From A/C 1 within the version 005 = To A/C 5 within the version ST ST5 = Production standard 230 = From A/C MSN = To A/C MSN 251 OPEN EFFECTIVITY: CUSTOMER VERSION PRODUCTION STANDARD LH1 001 bbb or LH ST5 230 bbb or ST DRAWING SET PRESENTATION 123 DATE: JUNE 2003 Page 123 XSD23A01

118 Parts Usage (PU) (cont d) How to use the parts usage: PARTS USAGE (PU) PART ISS NBR. 000 D00 Issue index of the part DESCRIPTION MOD. NUMBER NEXT ASSEMBLY MECHANISM INSTL FLAP D Partnumber 001 D00 MECHANISM INSTL FLAP D E00 MECHANISM INSTL FLAP D QTY Aircraft Type / Family: Single Aisle Version From To... 1 AAA BCA PAA AAA BCA PAA AAA ALK NHA Drawing CYP number IAC K2W OHY ACA ADR AFR AFR CYP IAC ITF NWA ACA ADR AFR AFR CYP IAC ITF NWA ACA AMC DLH IBE LUR ADR ANA GFA ITF MSR PAA Effectivity AFR BCA G2P I2L MXA RJA AFR CDN G2X KAC NWA SAA E00 AIRBUS PROPERTY BLAGNAC FRANCE, BP No33 DATE: MAY 5/2000 MECHANISM INSTL FLAP D AAA ACA ALK AMC CYP DLH IAC IBE K2W LUR OHY PARTS USAGE ADR ANA GFA ITF MSR PAA This document must not be copied without permission of the owner AFR BCA G2P I2L MXA RJA Drawing Number: G1 D AFR CDN G2X KAC NWA SAA Page U002 DRAWING SET PRESENTATION 124 DATE: JUNE 2003 Page 124 XSD23A01

119 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL 1 - DOCUMENTATION 1.4. OTHER MANUALS PMS - PROCESS & MATERIAL SPECIFICATIONS PRESENTATION Manual Purpose Manual Breakdown Numbering System Cross Reference List Alphabetical Index Alphanumerical Index Chapter 1 - Processes Contents Chapter 2 - Materials Contents DATE: JUNE 2003 Page 127 XSD24A01

120 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL PMS - PROCESS & MATERIAL SPECIFICATIONS PRESENTATION Manual Purpose The Process and Material Specification (PMS) provides Airlines with Guidance information on the manufacturing processes, materials and mate-rial treatment used for construction of AIRBUS aircraft. This PMS is a compilation of AIRBUS INDUSTRIE Members and Associated Partner's data and provides basic information on manufacturing processes and materials which are called up in engineering drawings and AIRBUS S.A.S. documentation. It is designed to assist Airlines to produce their own workshop docu-ments necessary to perform work on in-service AIRBUS S.A.S. aircraft. The quality of such work is the responsibility of the Operator. This PMS shall not be used as a basic for manufactures and supply of original and replacement parts to AIRBUS S.A.S. unless specifically required in a contract or purchase agreement. All manufacturing processes and materials within the Alphabetical Index with title and referenced section of the manual. Manufacturing Processes References to manufacturing processes are normally to be found in design drawings. The referred specification can be located in the Cross Reference List, where the English title and the reference are given in which chapter/section/subsection of the manual the process is included. Additionally alphabetical and alphanumerical indexes are provided to assist users to locate the required data. MANUAL PURPOSE DRAWING PICTURE ALT ALT ALT ALT ALT ALT ALT ALT A QUANTITY PER ASSEMBLY 31 ABS0114V3-4 SCREW - HEXAGONAL HEAD 30 NAS SCREW - HEXAGONAL HEAD 22 D B WASHER D A WASHER D A WASHER E D B BUSH E01 2S 14 D A BUSH SHOULDERED E D A SPACER E D A SPACER E D A PIVOT FITTING A D C LEVER FLAPCONTROL 4 D A LEVER FLAP CONTROL 4 D B LEVER FLAP CONTROL D A LINK ELBOW 000 D A LINK F MECHANISM INSTL FLAP 0H006 G F MECHANISM INSTL FLAP G E MECHANISM INSTL FLAP G01 0H E MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP G01 0H D MECHANISM INSTL FLAP G D MECHANISM INSTL FLAP G01 0H D MECHANISM INSTL FLAP G01 SCHEDULE Code within PMS Technical Note e.g: 701 SRM Structure Repair Manual MOD. NO BEFORE/AFTER Zone Item Part Number Part Issue Description Hand Protec Material Specification tion Id In Rem PIC. K D00 HG20018ST1AA93 E00 NG20468ST1AR01 F00 HG23013ST1AA01 SHT. 001 A00 NG20018ST1AJ77 B00 NG29001EF1AB80 C00 NG20018ST1AL90 THIS DOCUMENT IS THE PROPERTY OF AEROSPATIALE. NO PART OF IT SHALL BE REPRODUCED OR TRANSMITTED PROT. TREAT. CHART: TITLE: AIRBUS WITHOUT THE EXPRESS PRIOR WRITTEN AUTHORIZATION OF ASNA2101 AEROSPATIALE AND ITS CONTENTS SHALL NOT BE D.O. RESP. MECHANISM INSTL FLAP DISCLOSED. DATE 20/1993 DRAWING NO: SHEET G1 D S001 ISSUE F CONTD Reference to PMS Technical Note e.g. A SM Standard Manual ASNA2101 References to MATERIALS & PROCESSES PMS PMS - PROCESS & MATERIAL SPECIFICATIONS 150 DATE: JUNE 2003 Page 128 XSD24A01

121 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Manual Breakdown The contents of the PMS is subdivided as follows : CONTENTS INTRODUCTION: Pr ovides information on purpose, usage and presentation of the PMS. CROSS REFERENCE LIST: A list in alphanumerical order of all spe-cifications, covered by short descriptions with the relevant PMS-Reference. ALPHABETICAL INDEX: A summarized table of contents sorted by the process title in alphabetical order. ALPHANUMERIC INDEX: A List of PMS-Reference specifications and numbers. CHAPTER 1 - PROCESSES: Provides descriptions of manufacturing processes applied on AIRBUS aircraft. CHAPTER 2 - MATERIALS: Provides information on materials for the construction of AIRBUS aircraft. LAYOUT CHAPTER 2 MATERIALS ALPHANUMERICAL LIST CHAPTER 1 PROCESSES ALPHABETICAL LIST CROSS REFERENCE LIST INTRODUCTION PMS - PROCESS & MATERIAL SPECIFICATIONS 151 DATE: JUNE 2003 Page 129 XSD24A01

122 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Numbering System Each subject, within the PMS, is identified by a three-element numbering system, divided into Chapter/Section/Subsection. NOTE: The PMS numbering system is given in a logical sequential order but does not correspond with the ATA breakdown. NUMBERING SYSTEM Example for chapter 1: Chapter: PROCESSES Section: eg. SURFACE PRETREATMENTS Subsection: eg. SHOT PEENING Example for chapter 2: Chapter: MATERIALS Section: eg. SEALANTS Subsection: eg. FUEL TANK SEALANTS PMS - PROCESS & MATERIAL SPECIFICATIONS 152 DATE: JUNE 2003 Page 130 XSD24A01

123 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Cross Reference List Material or Process Specification PMS Chapter DATE: JUNE 2003 Page 131 XSD24A01

124 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Alphabetical Index PMS Chapter DATE: JUNE 2003 Page 132 XSD24A01

125 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Alphanumerical Index PMS Chapter Material or Process Specification DATE: JUNE 2003 Page 133 XSD24A01

126 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Chapter 1 - Processes Contents CHAPTER 1 - PROCESSES - Contents Surface Pretreatment Surface Treatment and Protection Heat Treatment, Machining and Forming Bonding, Welding and Riveting Assembling and Installation Methods Identification Marking Electric PMS - PROCESS & MATERIAL SPECIFICATIONS 156 DATE: JUNE 2003 Page 134 XSD24A01

127 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Chapter 1 - Processes Contents DATE: JUNE 2003 Page 135 XSD24A01

128 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Chapter 2 - Materials Contents Material information is included in Chapter 2 of the PMS. All materials approved for design of AIRBUS INDUSTRIE aircraft are included in form of Technical Notes (TN's). All "In-House-Standards" which are included in the Technical Notes are identified in the chapter (Subsection). CHAPTER 2 - MATERIALS -Content Protections Lubricants Metallic Materials Sealing Paint Coatings Rubbers Structural Adhesives Non-Structural Adhesives Non-Metallic Materials for Sandwich Structures Non-Metallic Materials (Miscellaneous) Pre-Impregnated Glass Fabrics Thermoplastic Materials Cured Composite Materials Carbon and Kevlar Composites Glass Fibres Materials Specification for corrosion prevent. temp. protective coumpounds Characteristics of grey color BAC707 top coat Coating systems for protection against erosion due to rain PMS - PROCESS & MATERIAL SPECIFICATIONS 158 DATE: JUNE 2003 Page 136 XSD24A01

129 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Chapter 2 - Materials Contents EXAMPLE 2: METALLIC MATERIALS - TN A DATE: JUNE 2003 Page 137 XSD24A01

130 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL 1- DOCUMENTATION 1.3. OTHER MANUALS STANDARD MANUAL PRESENTATION General Standards Identifications Codes National / International Specifications Manual Layout Part 1 Contents Part 2 Contents Part 3 Contents Part 4 Contents Part 4 Contents Supplement 1 DATE: APR 2003 Page 139 XSD24B01

131 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL General The Standards Manual (SM) is effective for all AIRBUS models. It assists all relevant design offices to choose the appropriate standards and to achieve an agreed aircraft design. The SM contains information about all US, European, national, AIRBUS and domestic product/semi-finished product standards agreed by the Airbus S.A.S. for the AIRBUS program, as well as about the related proprietary parts and the suppliers qualified for these parts by Airbus S.A.S. Moreover, the SM contains a selection of the basic standards used on the AIRBUS program. Standard parts which are not found in the SM shall not be used without prior approval by AIRBUS S.A.S. The SM assists the customers with respect to information about and the indentification of standard parts as well as their procurement in coorperation with the Airbus Support Materiel. GENERAL US, European, National, Airbus Industrie, Domestic, product/semi finished product standards agreed by AIRBUS INDUSTRIE STANDARD MANUAL Effective for all Airbus models Information about : of standard parts. - Identification, - Procurements, IMPORTANTE NOTICE: National / International Specifications (e.g. DIN, etc..). Copyright protected Not covered within the SM. To be requested from their respective National / International holders. STANDARD MANUAL 162 DATE: APR 2003 Page 140 XSD24B01

132 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Standards Identification Codes (1/2) DATE: APR 2003 Page 141 XSD24B01

133 STRUCTURE MAINTENANCE COURSE TECHNICAL TRAINING MANUAL Standards Identification Codes (1/2) DATE: APR 2003 Page 142 XSD24B01