# Airbus Service Bulletin A340-52-5023 Copy: Revision 02 ("A340-52-5023 R02"), 107 pages: PDF https://openairdocs.org/files/sha256/aa/12/aa12c7c376abc10d90efc1e838fb5b858dce9ae334feabe93a6c5d380405de0a; text https://openairdocs.org/service-documents/airbus/a340-52-5023/file/aa12c7c376ab.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0713; AD 2018-02-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Service Bulletin) - Number: A340-52-5023 - Latest revision known: A340-52-5023, Revision 02, dated November 27, 2015 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a340-52-5023 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2018-02-17](https://openairdocs.org/ad/2018-02-17.md), effective Mar 16, 2018: Revisions 01 and 02 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-52-5023/proposed.md). ## Text (107 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0713; AD 2018-02-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 52 TITLE: DOORS - AFT CARGO COMPARTMENT DOOR - INSPECT STRUCTURE FOR CRACKS AND LOOSE/LOST/SHEARED RIVETS MODIFICATION No.: None This page transmits Revision No.02 of Service Bulletin No.A340-52-5023 ADDITIONAL WORK **CONF ALL Additional work is required by this revision for aircraft modified by revision 00 of this Service Bulletin. The additional work involves a one time inspection and if necessary an adjustment of the hook gaps, which has to be done before or during the next inspection. Unless otherwise stated by an Airworthiness Directive, AIRBUS recommends the additional work to be accomplished within one year after the issue of this revision. REASON Revision No. 02 issued to: - add the procedure for High Frequency Eddy Current (HFEC) inspection of frame fork areas at beam 4 in the AFT cargo co mpartment door for cracks, - update the accomplishment timescale, - add the alternative fastener information for the part number ASNA2657K3 series in Kit COMPD01, COMPD02, COMPD11, illustrations and appendix. CHANGES The main changes of this revision are: - REASON paragr aph updated to show the HFE C inspection and FAR26.21 informations - EFFECTIVITY paragraph updated for the operators - APPENDICES paragr aph updated to add a new Appendix for th e alternative fastener tables DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET - DESCRIPTION paragraph updated to modify the title of Subtask 525023-210-201-003 - MANPOWER paragraph updated due to the addition of the HFEC inspection - REFERENCES paragraph updated to add the NTM 51-10-08 reference - MATERIAL - PRICE AND AVAIL ABILITY paragraph updated for the KLX Aer ospace Solutions. address - LIST OF MATERIALS - OPERATOR SUPPLIED paragraph updated to attach a note for the alternative fasteners for the part number ASNA2657K3 series - TOOLING paragraph updated to add the NTM 51-10-08 reference for the tools - PROCEDURE paragraph updated in the A CCOMPLISHMENT INSTRUCTIONS: . Subtask 525023-220-201-001 updated to modify the title of Subtask 525023-210-201-003 with revised title . Subtask 525023-210-201-003 updated to add the worksteps for the HFEC inspection . Subtask 525023-280-201-004 updated to add the worksteps for the application of sealant . Subtask 525023-820-201-001 updated to replace illustration A-G BBAA by A-GBAAA. - Illustrations A-GBCAA and A-GBDAA updated to show HFEC inspection information for the frame fork areas at beam 4 of AFT cargo compartment door - Illustrations A-GBEAA, A-GBKAA, AGBLAA, A- GBMAA and A-GBNAA updated to show the alternative fastener information for the part number ASNA2657K3 series - Illustration A-GFAAA updated to show the HFEC inspection in the flowchart - Illustration A-GRBAA updated to show the HFEC inspection in the inspection report - Illustration A-GABAA added to s how the alternative fasteners i nformation for the part number ASNA2657K3 series. SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R MANPOWER MANPOWER UPDATED R APPENDICES APPENDICES UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONFIGURATION LIST UPDATED R CONF 001 CONFIGURATION DEFINITION UPDATED R DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REASON Objective/Action OBJECTIVE/ACTION UPDATED R Advantages ADVANTAGES UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED R LIST OF MATERIALS - OPERATOR SUPPLIED Components Component COMPD01 PART MATERIAL SET UPDATED NOTE UPDATED CONFIGURATION UPDATED R Component COMPD02 PART MATERIAL SET UPDATED NOTE UPDATED CONFIGURATION UPDATED R Component COMPD11 PART MATERIAL SET UPDATED NOTE UPDATED CONFIGURATION UPDATED R TOOLING Tools TOOLS UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 525023- 832-848-001-Inspection Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 525023-210-202-001 SUBTASK SOLUTION UPDATED R Subtask 525023-220-201-001 SUBTASK SOLUTION UPDATED R Subtask 525023-210-201-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 525023-280-201-004 SUBTASK SOLUTION UPDATED NOTE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED QUANTITY UPDATED CONSUMABLE UPDATED REFERENCED DOCUMENTATION UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 525023-832-202-001 SUBTASK SOLUTION UPDATED NOTE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED MATERIAL LIST UPDATED R Subtask 525023-833-203-001 SUBTASK SOLUTION UPDATED NOTE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED MATERIAL LIST UPDATED R Subtask 525023-833-204-001 SUBTASK SOLUTION UPDATED NOTE UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED MATERIAL LIST UPDATED R Subtask 525023-820-201-001 SUBTASK SOLUTION UPDATED FIGURE REFERENCE UPDATED REFERENCES UPDATED R TASK 525023- 832-849-001-Inspection - ADDITIONAL WORK for Aircraft Inspected only by revision 00 of this Service Bulletin TASK SOLUTION UPDATED TASK TITLE UPDATED R Fig. A-GBCAA Fig. A-GBCAA Sheet 01 SHEET UPDATED R Fig. A-GBDAA Fig. A-GBDAA Sheet 01 SHEET UPDATED R Fig. A-GBEAA Fig. A-GBEAA Sheet 01 SHEET UPDATED R Fig. A-GBKAA Fig. A-GBKAA Sheet 01 SHEET UPDATED R Fig. A-GBLAA Fig. A-GBLAA Sheet 01 SHEET UPDATED R Fig. A-GBMAA Fig. A-GBMAA Sheet 01 SHEET UPDATED R Fig. A-GBNAA Fig. A-GBNAA Sheet 01 SHEET UPDATED R Fig. A-GFAAA Fig. A-GFAAA Sheet 01 SHEET UPDATED R DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-GRBAA Fig. A-GRBAA Sheet 01 SHEET UPDATED R Appendix 01 - Affected AFT Cargo Door Part Numbers Fig. A-GAAAA FIGURE SOLUTION UPDATED R Appendix 02 - Alternative Fasteners for ASNA2657K3 Series Fig. A-GABAA FIGURE SOLUTION ADDED N Fig. A-GABAA Sheet 01 SHEET ADDED N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No. 01 issued to: update the inspection process update the accomplishment timescale update the Figures and the Appendix replace the AIRBUS Kits with COMP-Matsets. REVISION SEQUENCE ORIGINAL: Aug 29/13 REVISION No. : 01 - Jul 28/14 REVISION No. : 02 - Nov 27/15 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A340-500/600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET This Page Intentionally Left Blank DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A340-500/600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 52 TITLE: DOORS - AFT CARGO COMPARTMENT DOOR - INSPECT STRUCTURE FOR CRACKS AND LOOSE/LOST/SHEARED RIVETS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES There have been several reports of cracks and loose, missing or sheared rivets found on the AFT Cargo Compartment Door Frame Forks and skin in the area of beam No. 4. Loose, missing or sheared rivets have also been reported on the AFT Cargo Compartment Door Frame Heads and skin in the area of beam No. 1. This Service Bulletin introduces a repetitive detailed inspection, High Frequency Eddy Current (HFEC) inspection of the AFT cargo compartment door frame fork areas at beam 4 and repetitive detailed inspection of the frame head areas at beam 1 from F r a m e6 0t o Frame 64A. A one time adjustment of the hook gaps "U" and "V" is to be done at the first accomplishment of this Service Bulletin. This Service Bulletin also provides repair instructions to be applied to the AFT Cargo Compartment Door Frame Forks, Frame Heads and skin in the event of findings resulting from the inspections. The accomplishment of this Service Bulletin will continue to maintain the structural integrity of the AFT Cargo Compartment Door. The accomplishment of this Service Bulletin will introduce compliance with the Widespread Fatigue Damage requirements of 14 CFR Part FAR26.21. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A340-500/600 SERVICE BULLETIN SUMMARY EVALUATION TABLE STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPD11 1 See SB Pin, Nut, Washer Component COMPD01 1 See SB Pin, Nut, Washer Component COMPD02 1 See SB Pin, Nut, Washer Standard tool TOOLD01 1 See SB Durable Toolkit Standard tool TOOLD02 1 See SB Expendable Toolkit Standard tool TOOLD03 1 See SB Capital Toolkit Kit tool 525023T01R02 1 See SB Bush Insertion Tool, Positioning Tool EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) : 06U 15T 16R 31V 32P 70U 72W 81Q AHY AIB CES DLH ETD HFY I2L IBE IRM QAF QTR SAA TAM THA UAE VIR CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 52.32.00.003 OEB None AOT None SIL 52-060 ISI None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER OIT 14-0008 OTHER OIT 999.0060/14 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A340-500/600 SERVICE BULLETIN SUMMARY MANPOWER Task 525023-832-848-001: Inspection TOTAL MANHOURS 44.50 ELAPSED TIME (HOURS) 44.50 Task 525023-832-849-001: Inspection - ADDITIONAL WORK for Aircraft Inspected only by revision 00 of this Service Bulletin TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00 APPENDICES Appendix 01 - Affected AFT Cargo Door Part Numbers Appendix 02 - Alternative Fasteners for ASNA2657K3 Series DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A340-500/600 SERVICE BULLETIN SUMMARY **CONF ALL Z822 A FR64A FR64 FR63A FR63 FR62A FR62 FR61A FR61 FR60A FR60 BEAM1 BEAM4 INSPECTION AREA NOTE: A F_SB_525023_6_SAAA_01_03 Figure A-GSAAA - Sheet 01 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A340-500/600 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 52 TITLE: DOORS - AFT CARGO COMPARTMENT DOOR - INSPECT STRUCTURE FOR CRACKS AND LOOSE/LOST/SHEARED RIVETS MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 340-541 340-542 340-642 (2) Effectivity by MSN 0371 0376 0383 0391 0410 0416-0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761-0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1102 1122 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A340-500/600 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 06U 1091 1102 15T 0924 16R 0622 31V 0436 32P 0560 70U 0902 72W 0917 81Q 0563 AHY 0779 0886 0894 AIB 0478 0492 0499 CES 0468 0488 0514 0577 0586 DLH 0482 0517 0523 0537 0540 0543 0566 0569 0580 0583 0762 0763 0767 0771 0790 0794 0812 0846 0848 0897 0972 0981 0987 1005 ETD 0748 0757 0761 0783 0829 0837 0870 0929 0933 1030 1040 HFY 0910 0912 I2L 0453 0475 IBE 0431 0440 0460 0601 0604 0606 0617 0619 0672 0702 0727 0744 0960 0993 1017 1079 1122 IRM 0371 0376 0383 0391 0416 0449 0615 QAF 0495 QTR 0715 0740 0766 0798 SAA 0410 0417 0426 0531 0534 0547 0557 0626 0630 TAM 0445 0464 THA 0624 0628 0677 0681 0689 0698 0710 0719 0775 0953 UAE 0457 0471 0485 0520 0572 0608 0611 0685 0694 VIR 0575 0639 0706 0723 0736 0753 0764 0765 0768 0787 0804 (4) Configuration by MSN MSN CONFIGURATION 0371 0376 0383 0391 0410 0416 0417 0426 0431 0436 0440 0445 0449 0453 0457 0460 0464 0468 0471 0475 0478 0482 0485 0488 0492 0495 0499 0514 0517 0520 0523 0531 0534 0537 0540 0543 0547 0557 0560 0563 0566 0569 0572 0575 0577 0580 0583 0586 0601 0604 0606 0608 0611 0615 0617 0619 0622 0624 0626 0628 0630 0639 0672 0677 0681 0685 0689 0694 0698 0702 0706 0710 0715 0719 0723 0727 0736 0740 0744 0748 0753 0757 0761 0762 0763 0764 0765 0766 0767 0768 0771 0775 0779 0783 0787 0790 0794 0798 0804 0812 0829 0837 0846 0848 0870 0886 0894 0897 0902 0910 0912 0917 0924 0929 0933 0953 0960 0972 0981 0987 0993 1005 1017 1030 1040 1079 1091 1102 1122 001 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A340-500/600 SERVICE BULLETIN (5) Configuration definition NOTE : This configuration definition is valid for A/C definition at the time of delivery. In case of door replacement in-service, please refer to Appendix 01 - Affected AFT Cargo Door Part Numbers - to define the applicable configuration. **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPD11 1 Component COMPD01 1 Component COMPD02 1 Consumable CMLD01 As required Standard tool TOOLD01 1 Standard tool TOOLD02 1 Standard tool TOOLD03 1 Kit tool 525023T01R02 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History There have been several reports of cracks and loose, missing or sheared rivets found on the AFT Cargo Compartment Door Frame Forks and skin in the area of beam No. 4. Loose, missing or sheared rivets have also been reported on the AFT Cargo Compartment Door Frame Heads and skin in the area of beam No. 1. (2) Objective/Action This Service Bulletin introduces a repetitive detailed inspection, High Frequency Eddy Current (HFEC) inspection of the AFT cargo compartment door frame fork areas at beam 4 and repetitive detailed inspection of the frame head areas at beam 1 from Frame 60 to Frame 64A. A one time adjustment of the hook gaps "U" and "V" is to be done at the first accomplishment of this Service Bulletin. This Service Bulletin also provides repair instructions to be applied to the AFT Cargo Compartment Door Frame Forks, Frame Heads and skin in the event of findings resulting from the inspections. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A340-500/600 SERVICE BULLETIN (3) Advantages The accomplishment of this Service Bulletin will continue to maintain the structural integrity of the AFT Cargo Compartment Door. The accomplishment of this Service Bulletin will introduce compliance with the Widespread Fatigue Damage requirements of 14 CFR Part FAR26.21. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 525023-832-848-001: Inspection (1) Identify the Part Number of the AFT Cargo Compartment Door (2) Do a Check and if necessary adjust the AFT Cargo Compartment Door Hook Gaps (only at first inspection) (3) Do a Detailed Inspection (DET) and High Frequency Eddy Current (HFEC) Inspection of the AFT Cargo Compartment Door Frame Fork Areas (4) Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas (5) Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas (6) Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment-Door Frame Head Areas (7) Repair the AFT Cargo Compartment Door Frame Fork Area Fastener Holes by Bushing (8) Replace the AFT Cargo Compartment Door Frame Fork (9) Do the Adjustment of the AFT Cargo Compartment Door Hook Gaps Task 525023-832-849-001: Inspection - ADDITIONAL WORK for Aircraft Inspected only by revision 00 of this Service Bulletin (1) Do a Check and if Necessary Adjust the AFT Cargo Compartment Door Hook Gaps E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A340-500/600 SERVICE BULLETIN (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. For the Part Number List of affected Frame Forks and Frame Heads, refer to SRM 53-32-00. For the Part Number List of affected Cargo Doors, refer to Appendix 01 - Affected AFT Cargo Door Part Numbers . Config all: Table 01: Identification of the AFT Cargo Compartment Door part number CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* All aircraft Identify the AFT Cargo Compartment Door part number see Note** None If the AFT Cargo Compartment Door replaced by a post MOD 202790 one. (Part Number F52372315000 and subsequent) No further action None None If the AFT Cargo Compartment Door replaced by pre MOD 202790 one Select the correct config depending on the Cargo Compartment Door Part Number and go to table 02 see Note** None If the AFT Cargo Compartment Door was not replaced Go to table 02 see Note** None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. CONDITION COMPLIANCE TIME Aircraft not inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Whichever occurs later: - Before accumulation of 12000 Flight Cycles (FC) - Within 550 FC after the issue date of this Service Bulletin Rev. 02, but without exceeding 12550 FC since first installation of the AFT cargo compartment door on an aircraft Note** Aircraft inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Within 550 FC, after the last inspection according to Rev. 00 or Rev. 01 of this Service Bulletin DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A340-500/600 SERVICE BULLETIN Config all: Table 02: Check the AFT Cargo Compartment Door Hook Gaps only at first inspection CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* Aircraft from table 01 Do a check of the AFT Cargo Compartment Door hook gaps "U" and "V" see Note** None Record and report findings to AIRBUS and once the inspection is completed do the hook adjustment Before next flight None If the hook gaps "U" or "V" are out of tolerance go to table 03 and 04 see Note** None If the hook gaps "U" and "V" are in tolerance Go to table 03 and 04 see Note** None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. CONDITION COMPLIANCE TIME Aircraft not inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Whichever occurs later: - Before accumulation of 12000 Flight Cycles (FC) - Within 550 FC after the issue date of this Service Bulletin Rev. 02, but without exceeding 12550 FC since first installation of the AFT cargo compartment door on an aircraft Note** Aircraft inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Within 550 FC, after the last inspection according to Rev. 00 or Rev. 01 of this Service Bulletin Config all: Table 03: Detailed Inspection and HFEC Inspection of the AFT Cargo Compartment Door Frame Forks and Skin CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A340-500/600 SERVICE BULLETIN All aircraft - Do a detailed inspection of the AFT cargo compartment door frame forks and outer skin areas at beam No. 4 for loose, sheared or missing fasteners - Do a HFEC inspection of the AFT cargo compartment door frame forks at beam No. 4 for cracks see Note** None If no cracks, loose, sheared or missing fasteners on frame forks or skin at beam No. 4 are found Repeat inspection None 1400 FC If any cracks or loose, sheared or missing fasteners are found and the area has an existing repair Contact AIRBUS Before next flight None If any cracks or loose, sheared or missing fasteners are found and there is no existing repair Go to table 05 Before next flight None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. CONDITION COMPLIANCE TIME Aircraft not inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Whichever occurs later: - Before accumulation of 12000 Flight Cycles (FC) - Within 550 FC after the issue date of this Service Bulletin Rev. 02, but without exceeding 12550 FC since first installation of the AFT cargo compartment door on an aircraft Note** Aircraft inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Within 550 FC, after the last inspection according to Rev. 00 or Rev. 01 of this Service Bulletin Config all: Table 04: Detailed Inspection of the AFT Cargo Compartment Door Frame Heads and Skin DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 7 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A340-500/600 SERVICE BULLETIN CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* From table 02 Do a detailed inspection of the AFT Cargo Compartment Door frame heads and skin at beam No. 1 for cracks or loose, sheared or missing fasteners see Note** None If no cracks or loose, sheared or missing fastener on frame heads or skin at beam No. 1 are found Repeat inspection None 1400 FC If any cracks or loose, sheared or missing fasteners are found and the area has an existing repair Contact AIRBUS Before next flight None If any cracks or loose, sheared or missing fasteners are found and there is no existing repair Remove all affected fasteners in accordance with the inspection areas and go to table 06 Before next flight None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. CONDITION COMPLIANCE TIME Aircraft not inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Whichever occurs later: - Before accumulation of 12000 Flight Cycles (FC) - Within 550 FC after the issue date of this Service Bulletin Rev. 02, but without exceeding 12550 FC since first installation of the AFT cargo compartment door on an aircraft Note** Aircraft inspected a c c o r d i n gt oR e v .0 0o r Rev. 01 of this Service Bulletin Within 550 FC, after the last inspection according to Rev. 00 or Rev. 01 of this Service Bulletin Config all: Table 05: Special Detailed Inspection of the AFT Cargo Compartment Door Frame Forks and Skin CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 8 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A340-500/600 SERVICE BULLETIN From table 03 If any cracks, loose, sheared or missing fasteners are found and the area has no previous repair Do a Special Detailed Inspection of affected AFT Cargo Compartment Door frame forks area outer skin at beam No. 4 Before next flight None Replace fasteners Before next flight None If no crack is found during the Special Detailed Inspection Repeat inspection None 1400 FC Contact AIRBUS Before next flight None or Replace AFT Cargo Compartment Door pre Mod 202790 and do the Hook Adjustment Before next flight None Repeat inspection None 1400 FC or If any cracks are found in outer skin during the Special Detailed Inspection Replace AFT Cargo Compartment Door post Mod 202790 and do the Hook adjustment Before next flight None Repair affected frame forks and do the Hook adjustment if needed Before next flight None Repeat inspection None 1400 FC or Replace affected frame forks and do the Hook adjustment Before next flight None Repeat inspection None 1400 FC or Replace AFT Cargo Compartment Door pre Mod 202790 and do the Hook adjustment Before next flight None Repeat inspection None 1400 FC or If any cracks are found in the frame forks Replace AFT Cargo Compartment Door post Mod 202790 and do the Hook adjustment Before next flight None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 9 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A340-500/600 SERVICE BULLETIN Config all: Table 06: Special Detailed Inspection of the AFT Cargo Compartment Door Frame Heads and Skin CONDITION ACTION COMPLIANCE TIME* REPETITIVE INTERVAL NOT TO EXCEED* From table 04 If any cracks or loose, sheared or missing fasteners are found and there is no existing repair Do a Special Detailed Inspection of affected AFT Cargo Compartment Door frame heads area at beam No. 1 Before next flight None Replace fasteners Before next flight None If no cracks are found in outer skin on frame heads at beam No. 1 Repeat inspection None 1400 FC If any cracks are found in outer skin on the frame heads area at beam No. 1 Ream the affected fastener holes up to allow installation of ASNA2657K3 and repeat the Special Detailed Inspection Before next flight None Replace fasteners Before next flight None If no cracks are found on the frame heads area at beam No.1 Repeat inspection None 550 FC If cracks remain after reaming to the maximum repair size and Special Detailed Inspection Ream the affected fastener holes up to allow installation of ASNA2657K3X and repeat the Special Detailed Inspection Before next flight None Replace fasteners Before next flight None If no cracks remain after reaming to the maximum repair size for fastener ASNA2657K3X and Special Detailed Inspection Repeat inspection None 1400 FC If cracks remain after reaming to the maximum repair size for fastener ASNA2657K3X and Special Detailed Inspection Contact AIRBUS Before next flight None Note* All THRESHOLDS, GRACE PERIODS AND INTERVALS given in this Service Bulletin are valid for the Cargo Compartment Doors. If given values between aircraft and Cargo Compartment Doors are different, the limits of the Cargo Compartment Doors have to be taken into account. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 10 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A340-500/600 SERVICE BULLETIN If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 525023-832-848-001: Inspection Get Access 1.00 On Aircraft Identify the Part Number of the AFT Cargo Compartment Door 0.50 Do a Check and if necessary adjust the AFT Cargo Compartment Door Hook Gaps (only at first inspection) 1.00 Do a Detailed Inspection (DET) and High Frequency Eddy Current (HFEC) Inspection of the AFT Cargo Compartment Door Frame Fork Areas 7.00 Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas 2.00 Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas 6.00 Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment-Door Frame Head Areas 6.00 Repair the AFT Cargo Compartment Door Frame Fork Area Fastener Holes by Bushing 4.00 Replace the AFT Cargo Compartment Door Frame Fork 10.00 Do the Adjustment of the AFT Cargo Compartment Door Hook Gaps 5.00 Tests 1.00 Close-Up 1.00 TOTAL MANHOURS 44.50 ELAPSED TIME (HOURS) 44.50 NOTE : The maximum manhours necessary to accomplish this Service Bulletin are those for the Inspection, Repair and Replacement. Depending on the inspection result, the manhours can be reduced. Task 525023-832-849-001: Inspection - ADDITIONAL WORK for Aircraft Inspected only by revision 00 of this Service Bulletin Get Access 0.50 On Aircraft DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 11 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A340-500/600 SERVICE BULLETIN Task 525023-832-849-001: Inspection - ADDITIONAL WORK for Aircraft Inspected only by revision 00 of this Service Bulletin Do a Check and if Necessary Adjust the AFT Cargo Compartment Door Hook Gaps 1.00 Tests 1.00 Close-Up 0.50 TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-00 12-34-24 24-42-00 52-30-00 52-32-00 52-32-11 52-32-15 52-32-18 52-32-21 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 51-90-00 Service Information Letter (SIL) SIL 51-012 52-060 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-42-11 51-43-00 51-44-00 51-44-11 51-46-11 51-47-00 51-48-00 51-49-00 51-73-12 51-75-00 51-75-12 51-76-11 52-32-00 53-32-00 Tool Equipment Manual (TEM) 52-30-00 K. PUBLICATION AFFECTED Aircraft Maintenance Manual (AMM) 52-30-00 Maintenance Planning Document (MPD) 53-32-08-01-1 53-32-08-01-2 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 12 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A340-500/600 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to KLX Aerospace Solutions. The address is: Component COMPD01 Component COMPD02 Component COMPD11 KLX Aerospace Solutions. 10000 NW 15th Terrace Miami FL 33172 USA Tel EMEA: +49 (0) 40 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 40 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-Mail: AOGdesk@klx.com internet: http://www.KLXaerospace.com or, alternatively any other source on the open market (2) Price and Availability Component COMPD01 Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. Component COMPD02 Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. Component COMPD11 Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to the Fatigue Test Integration Program. Refer to the FTIP policy. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 13 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A340-500/600 SERVICE BULLETIN For the organization of this retrofit, you are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France E-mail : monitored.retrofit@airbus.com T e l:( 3 3 )56 71 90 62 2 F a x:( 3 3 )56 19 32 74 5 C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane - External Structure 04JAA3 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant - General Purpose Fillet - 06AAB1 As required Non Aqueous Cleaner - General 08BAA9 As required Surface Pretreatment - Light Alloys Chemical Conver 10ABC1 As required Corrosion Preventive Compound - Heavy Duty Soft Fil 12ACC1 As required Textile-Lint Free Cotton 14SBA1 As required (2) Components Component COMPD01 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 2 ASNA2657K3-5 52 BOLT (1 ) 3 ASNA2657K3-6 52 BOLT (1 ) DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 14 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A340-500/600 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 4 ASNA2657K3-7 34 BOLT (1 ) 5 ASNA2657K3-8 4 BOLT (1 ) 6 NAS1149D0332K 42 WASHER 7 ASNA2538-3 148 NUT 8 ASNA2657K3-4 18 Bolt (1 ) 9 ASNA2536-3 12 NUT NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . Component COMPD02 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 2 ASNA2657K3-5X 52 BOLT (1 ) 3 ASNA2657K3-6X 52 BOLT (1 ) 4 ASNA2657K3-7X 34 BOLT (1 ) 5 ASNA2657K3-8X 4 BOLT (1 ) 6 NAS1149D0332K 42 WASHER 7 ASNA2536-3 12 NUT 7 ASNA2538-3 148 NUT 8 ASNA2657K3-4X 18 BOLT (1 ) NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . Component COMPD11 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 2 ASNA2657K3-5 64 BOLT (1 ) 3 ASNA2657K3-6 14 BOLT (1 ) DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 15 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A340-500/600 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 4 ASNA2657K3-7 98 BOLT (1 ) 5 ASNA2657K3-8 22 BOLT (1 ) 6 NAS1149D0332K 62 WASHER 7 ASNA2538-3 196 NUT 9 ASNA2536-3 2 NUT NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Operators interested in obtaining the Fatigue Technology Inc. (FTI) tool kits should contact Standard tool TOOLD01 Standard tool TOOLD02 Standard tool TOOLD03 Fatigue Technology Inc. 401 Andover Park East SEATTLE, WA 98188-7605 USA Internet: www.fatiguetech.com Phone: (206) 2462010 Fax: (206) 2449886 (b) Price and Availability Standard tool TOOLD01 Standard tool TOOLD02 Standard tool TOOLD03 Procurement to be negotiated directly with Fatigue Technology Inc. (FTI). DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 16 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A340-500/600 SERVICE BULLETIN (2) Tools To accomplish this Service Bulletin it is necessary to use the tools and equipment listed in AMM Task 52-32-11-820-803, NTM Task 51-10-01-250-801 and NTM 51-10-08 . To drill the frame fork locking shaft hole, use the Drilling Tool Locking Shaft SK 2029C221, refer to TEM 52-30-00. To drill the frame fork latching shaft hole, use the Drilling Tool Latching Shaft SK 2030C221, refer to TEM 52-30-00. FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools refer to SIL 51-012. Standard tool TOOLD01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340525023-1 Durable Tooling 1 (1) NOTE (1) : Durable tooling: Ref. DK-A340-52-5023-1. The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to Service Information Letter (SIL) 52-012. Standard tool TOOLD02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES EKA340525023-1 Expendable Tooling 1 (1) NOTE (1) : Expendable tooling: Ref. EK-A340-52-5023-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. Standard tool TOOLD03 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES FTIA340525023-1 Capital Tooling 1 (1) NOTE (1) : Capital tooling: Ref. FTI-A340-52-5023-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 17 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A340-500/600 SERVICE BULLETIN (3) Special Tools NOTE : These tools are recommended by AIRBUS for the installation of the Fork ends. They are not necessary if the installation can be assured without them. Kit tool 525023T01R02 ITEM PART N˚ KEYWORD QTY SEE NOTES 98F52308858000 DEVICE 1 98F52308860000 DEVICE 1 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 18 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A340-500/600 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 525023-832-848-001 - Inspection WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. CAUTION : IF A BUSH REPAIR HAS BEEN DONE ON A FRAME FORK THERE IS A LIFETIME LIMITATION. IF THE LIFETIME LIMITATION IS EXCEEDED, REPLACE THE FRAME FORK OR CARGO COMPARTMENT DOOR, REFER TO Fig. A-GBRAA . NOTE : The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 19 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A340-500/600 SERVICE BULLETIN NOTE : The purpose of the flow chart is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data Zone 822 Access Panel 822AR 822BR 822CR 822DR Manpower TOTAL MANHOURS 44.50 ELAPSED TIME (HOURS) 44.50 A. GENERAL (1) Subtask 525023-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-12 51-42-11 51-43-00 51-44-11 51-46-11 51-47-00 51-48-00 51-49-00 51-75-12 51-76-11 (a) For the material specification (Mat No.) given in this Service Bulletin, refer to Consumable Material List (CML). (b) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) Obtain oversize fastener data in accordance with SRM 51-43-00. (e) Obtain fastener hole diameters and drill and deburr data in accordance with SRM 51-44-11. (f) Torque tighten Hi-Lite and Hi-Lok fasteners in accordance with SRM 51-49-00. (g) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 20 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A340-500/600 SERVICE BULLETIN (h) If alternative and substitute fasteners are to be used, you ensure that the associated nuts/collars are compatible in accordance with SRM 51-40-00. (i) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (j) Remove and install fasteners in accordance with SRM 51-42-11. (k) Check all edge distances before drilling in accordance with SRM 51-47-00. (l) Transfer drill existing holes with a pilot drill and drill bush. (m) Obtain countersinking data in accordance with SRM 51-46-11. (n) Do the removal and installation of sealant in accordance with SRM 51-76-11. (o) For surface protection of reworked areas in accordance with SRM 51-75-12. (p) Do the cold expansion of fastener holes in accordance with SRM 51-48-00. (q) Apply and remove sealant in accordance with SRM 51-76-11. (r) Apply special coatings in accordance with SRM 51-23-12. (s) In case of a special paint build-up, the removal and installation procedure of this special paint build-up must be taken into account. (2) Subtask 525023-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 525023-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Skills NON SPECIFIC DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 21 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A340-500/600 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 24-42-00-861-801 52-30-00, Page Block 201 Task 52-32-15-000-801 CAUTION : FOR THE HOOK GAP CHECK AND ADJUSTMENT, MAKE SURE THAT THE AIRCRAFT IS IN THE CORRECT CONDITION AS GIVEN IN AMM Task 52-32-11-820-803. NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Make sure the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put the access platform in position below the AFT Cargo Compartment Door. (c) Energize the ground service network, refer to AMM Task 24-42-00-861-801. (d) Open the AFT Cargo Compartment Door, refer to AMM 52-30-00, Page Block 201 (e) Remove access panels 822AR, 822BR, 822CR and 822DR from the AFT Cargo Compartment Door. (f) Remove the linings as necessary for access to the inspection areas, refer to AMM Task 52-32-15-000-801. C. PROCEDURE NOTE : Paint peeling at fasteners head is an indicator of potential loose fasteners. Before reporting as loose, check in accordance with the SRM 51-42-11. During the cargo door inspection, it is necessary to look for loose, sheared or missing fasteners as an indicator of fatigue. Sheared or missing fasteners can DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 22 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A340-500/600 SERVICE BULLETIN be quickly identified as the result of the detailed inspection from outside, for the loose fasteners however it could be more difficult. In particular, based on the in-service experience, some fasteners affected by paint peeling can be wrongly considered loose due to the black marks around the fastener head, the so called "fastener rash" phenomenon. Recommendation to detect loose fasteners: - Paint chipping of fastener head detected from outside is a good indicator, but must not be the only evidence. - Check for abnormal gap under the fastener heads on both sides. - Fastener movement (play) confirm the fastener is loose. However, sometimes the fastener can be loose and stuck (between skin and frame), that is why it is necessary to check on both sides of the cargo door. (1) Subtask 525023-210-202-001 - Identify the Part Number of the AFT Cargo Compartment Door Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME (a) Has the AFT Cargo Compartment Door already been replaced in service. 1 If no go to SUBTASK 525023-220-201 001 Do a Check and if necessary adjust the AFT Cargo Compartment Door Hook Gaps (only at first inspection) . 2 If Yes a Has the AFT Cargo Compartment Door been replaced by the post Mod: 202790 cargo door Part Number (PN) F52372315000 and up. <1> If yes, no further action is necessary in accordance with this Service Bulletin. <2> If no, refer to Appendix 01 - Affected AFT Cargo Door Part Numbers and go to SUBTASK 525023-220-201 001 Do a Check and if necessary adjust the AFT Cargo Compartment Door Hook Gaps (only at first inspection) . DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 23 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A340-500/600 SERVICE BULLETIN (2) Subtask 525023-220-201-001 - Do a Check and if necessary adjust the AFT Cargo Compartment Door Hook Gaps (only at first inspection) Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 52-30-00-410-801 Task 52-32-11-820-803 Fig. A-GBAAA Hook Gaps "U" and "V" Sheet 01 NOTE : Check of hook gaps to be performed only at first inspection. (a) Make sure the AFT Cargo Compartment Door is correctly closed and locked, refer to AMM Task 52-30-00-410-801. (b) At the subsequent locations: Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A. Measure and record the hook gaps "U" and "V" in accordance with the dimensions given in the AMM Task 52-32-11-820-803 and as shown on Fig. A-GBAAA Sheet 01 ,V i e wB . (c) If the hook gaps "U" and "V" are within the specified tolerances, continue with SUBTASK 525023-210-201 003 Do a Detailed Inspection (DET) and High Frequency Eddy Current (HFEC) Inspection of the AFT Cargo Compartment Door Frame Fork Areas and SUBTASK 525023-832-201 001 Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas . (d) If the hook gaps "U" or "V" are out of tolerances, continue with SUBTASK 525023-210-201 003 Do a Detailed Inspection (DET) and High Frequency Eddy Current (HFEC) Inspection of the AFT Cargo Compartment Door Frame Fork Areas and SUBTASK 525023-832-201 001 Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas . 1 After the inspection and when any resulting repairs are completed, accomplish SUBTASK 525023-820-201 001 Do the Adjustment of the AFT Cargo Compartment Door Hook Gaps . DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 24 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A340-500/600 SERVICE BULLETIN (e) If the values are out of tolerances, report hook gaps "U" and "V" values to AIRBUS when this Service Bulletin is accomplished. (3) Subtask 525023-210-201-003 - Do a Detailed Inspection (DET) and High Frequency Eddy Current (HFEC) Inspection of the AF T Cargo Compartment Door Frame Fork Areas Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Manhours 7.00 Minimum number of person 1 Subtask elapsed time 7.00 Skills AIRFRAME NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-General Purpose Fillet 06AAB1 As required Non Aqueous Cleaner- General 08BAA9 As required References Non Destructive Test Manual (NTM) 51-10-08 51-90-00 Structural Repair Manual (SRM) 51-42-11 51-76-11 Fig. A-GBBAA Inspection Areas Sheet 01 Fig. A-GBCAA Frame Fork Inspection/Removal Area Sheet 01 Fig. A-GBDAA Frame Fork Inspection/Removal Area at FR60A thru FR64A Sheet 01 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 25 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A340-500/600 SERVICE BULLETIN (a) Do a detailed inspection of the frame forks and outer skin areas at beam 4 in Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A in the AFT cargo compartment door for loose, sheared or missing fasteners as show on Fig. A-GBBAA Sheet 01 , Fig. A- GBCAA Sheet 01 , Fig. A-GBDAA Sheet 01 and in accordance with NTM 51-90-00. NOTE : Do a detailed inspection from inside and outside of the AFT cargo compartment door. NOTE : Paint peeling at fastener heads is an indicator of potential loose fasteners. Before reporting as loose, check in accordance with SRM 51-42-11 During the cargo door inspection, it is necessary to look for loose, sheared or missing fasteners as an indicator of fatigue. Sheared or missing fasteners can be quickly identified as the result of the detailed inspection from outside, for the loose fasteners it could be however more difficult. In particular, based on the in- service experience, some fasteners affected by paint peeling can be wrongly considered loose due to the black marks around the fastener head, the so called "fastener rash" phenomenon. Recommendation to detect loose fasteners: - Paint chipping of fastener head detected from outside is a good indicator, but must not be the only evidence. - Check for abnormal gap under the fastener heads on both sides. - Fastener movement (play) confirms the fastener is loose. However, sometimes the fastener can be loose and stuck (between skin and frame), that is why it is necessary to check on both sides of the cargo door. (b) Remove the sealant as necessary as shown on Fig. A-GBCAA Sheet 01 , Fig. A- GBDAA Sheet 01 and in accordance with SRM 51-76-11. (c) Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 26 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A340-500/600 SERVICE BULLETIN (d) Do a HFEC inspection of the frame forks at beam 4 in Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A in the AFT cargo compartment door for cracks as shown on Fig. A-GBBAA Sheet 01 , Fig. A-GBCAA Sheet 01 , Fig. A-GBDAA Sheet 01 and in accordance with NTM 51-10-08. 1 If no cracks, loose, sheared or missing fasteners on frame forks or skin at beam No. 4 are found: a Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required b Apply to the edges of the beams, frame fork and splice as shown on Fig. A-GBCAA Sheet 01 , Fig. A-GBDAA Sheet 01 and in accordance with SRM 51-76-11: Polysulfide Sealant- General Purpose Fillet 06AAB1 As required c Go to SUBTASK 525023-832-201 001 Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas . 2 If a crack is found or there are loose, sheared or missing fasteners: a Check the inspection area for existing repairs. <1> If there is: An existing repair or the frame fork has been replaced previously, contact AIRBUS for further instructions before next flight. No existing repair, go to SUBTASK 525023-832-201 001 Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas and SUBTASK 525023-280-201 004 Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas . (4) Subtask 525023-832-201-001 - Do A Detailed Inspection (DET) of the AFT Cargo Compartment Door Frame Head Areas Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 27 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A340-500/600 SERVICE BULLETIN Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-90-00 Structural Repair Manual (SRM) 51-42-11 Fig. A-GBFAA Frame Head Fastener Inspection/Removal Area at FR60, FR60A, FR64 and FR64A Sheet 01 Fig. A-GBGAA Frame Head Inspection/Removal Area at FR61 and FR63A Sheet 01 Fig. A-GBHAA Frame Head Inspection/Removal Area at FR61A, FR62A and FR63 Sheet 01 Fig. A-GBJAA Frame Head Inspection/Removal Area at FR62 Sheet 01 (a) Do a Detailed inspection of the outer skin and inner surfaces of the AFT Cargo Compartment Door frame heads area at beam 1 for cracks, l oose, sheared or missing fasteners at the subsequent locations in accordance with NTM 51-90-00 and as shown on Fig. A-GBFAA Sheet 01 , Fig. A-GBGAA Sheet 01 , Fig. A-GBHAA Sheet 01 and Fig. A-GBJAA Sheet 01 : Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A. (b) If no cracks, loose, sheared or missing fasteners are found, go to SUBTASK 525023-820-201 001 Do the Adjustment of the AFT Cargo Compartment Door Hook Gaps and repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). (c) If a crack is found or there are loose, sheared or missing fasteners: 1 Check the inspection area for existing repairs. a If there is an existing repair or the frame head has been replaced previously, contact AIRBUS for further instructions before next flight. b If there is no existing repair, go to SUBTASK 525023-832-202 001 Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment-Door Frame Head Areas . DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 28 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A340-500/600 SERVICE BULLETIN (5) Subtask 525023-280-201-004 - Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Component COMPD11 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 2 ASNA2657K3-5 32 BOLT (1 ) 3 ASNA2657K3-6 7 BOLT (1 ) 4 ASNA2657K3-7 49 BOLT (1 ) 5 ASNA2657K3-8 11 BOLT (1 ) 6 NAS1149D0332K 31 WASHER 7 ASNA2538-3 98 NUT 9 ASNA2536-3 1 NUT NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 Top Coat Polyurethane - External Structure 04JAA3 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-General Purpose Fillet 06AAB1 As required DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 29 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A340-500/600 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required Standard tool TOOLD01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340525023-1 Durable Tooling 1 (1) NOTE (1) : Durable tooling: Ref. DK-A340-52-5023-1. The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to Service Information Letter (SIL) 52-012. Standard tool TOOLD02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES EKA340525023-1 Expendable Tooling 1 (1) NOTE (1) : Expendable tooling: Ref. EK-A340-52-5023-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. Standard tool TOOLD03 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES FTIA340525023-1 Capital Tooling 1 (1) NOTE (1) : Capital tooling: Ref. FTI-A340-52-5023-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) Task 52-32-11-000-801 Task 52-32-11-400-801 Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Structural Repair Manual (SRM) 51-76-11 Fig. A-GBCAA Frame Fork Inspection/Removal Area Sheet 01 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 30 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A340-500/600 SERVICE BULLETIN References Fig. A-GBDAA Frame Fork Inspection/Removal Area at FR60A thru FR64A Sheet 01 Fig. A-GBEAA Frame Fork Fastener Installation at FR60 thru FR64A Sheet 01 Sheet 02 Fig. A-GRAAA Hook Gaps Report Sheet Sheet 01 Fig. A-GRBAA Frame Fork Report Sheet Sheet 01 NOTE : Do this subtask on affected frame forks areas if a crack is found or there are any loose, sheared or missing fasteners. (a) At beam 4, on Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A. Refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBDAA Sheet 01 . 1 Remove the fasteners as specified. 2 Make sure the holes are clean and smooth. 3 Do the Special Detailed Inspection - rot ating probe method (procedure "A") - on the specified holes in accordance with NTM Task 51-10-01-250-801. a If no crack is found: <1> Replace the fasteners after cold expansion of the holes. <2> At first inspection only and if gaps were out of tolerances, refer to SUBTASK 525023-820-201 001 Do the Adjustment of the AFT Cargo Compartment Door Hook Gaps . b If a crack is found on the skin: <1> Contact AIRBUS before next flight. or <2> Replace the AFT Cargo Compartment Door, refer to AMM Task 52-32-11-000-801 and AMM Task 52-32-11-400-801. NOTE : The door must be serviceable and interchangeable with the removed cargo compartment door. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 31 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A340-500/600 SERVICE BULLETIN If the AFT Cargo Compartment Door has been replaced by the Post Mod. 202790 (serial cargo door Part Number (PN) F52372315000 and up): No further action is necessary in accordance with this Service Bulletin. If the AFT Cargo Compartment Door has been replaced by the pre-Mod. 202790 (cargo door PN F52371000004 thru F52372300116): Repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). c If a crack is found on the frame fork: <1> Go to SUBTASK 525023-833-203 001 Repair the AFT Cargo Compartment Door Frame Fork Area Fastener Holes by Bushing . NOTE : Bush repair is possible for a crack up to a maximum length of 2 mm (0.078 in.) only. Lifetime limitation starts from the bush repair accomplishment. For lifetime limitation refer to Fig. A-GRAAA Sheet 01 .I f the lifetime limitation is exceeded, replace the frame fork or cargo compartment door. NOTE : Only 1 bush per frame fork is allowed. NOTE : This repair is applicable to outer flanges only. or <2> Replace the frame fork, go to SUBTASK 525023-833-204 001 Replace the AFT Cargo Compartment Door Frame Fork . or <3> Replace the AFT Cargo Compartment Door, refer to AMM Task 52-32-11-000-801 and AMM Task 52-32-11-400-801. NOTE : The door must be interchangeable with the removed cargo compartment door and inspected as described in this Service Bulletin after its installation. 4 In all cases where frame fork fasteners are removed, do the cold expansion of the fastener holes. Refer to Fig. A-GBEAA Sheet 01 and Fig. A-GBEAA Sheet 02 . Use FTI tool list No.: DKA340525023-1 Durable Tooling 1 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 32 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A340-500/600 SERVICE BULLETIN a Clean the drilled area with: Non Aqueous Cleaner - General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required b Install the sleeves. c Do the cold expansion of the holes. Use FTI too No’s: DKA340525023-1 Durable Tooling 1 EKA340525023-1 Expendable Tooling 1 FTIA340525023-1 Capital Tooling 1 d Remove the sleeves. e Ream the hole to the final diameter. f Close the affected fastener holes with Hi-Lite fasteners, wet installed with: Polysulfide Sealant- General Purpose Brushable 06AAA1 As required <1> On Frame 60 install, refer to Fig. A-GBEAA Sheet 01 : 2 Bolt ASNA2657K3-5 Item 2 1 Bolt ASNA2657K3-6 Item 3 2 Bolt ASNA2657K3-7 Item 4 4 Bolt ASNA2657K3-8 Item 5 1 Nut ASNA2536-3 Item 9 8 Nut ASNA2538-3 Item 7 <2> On Frame 60A install, refer to Fig. A-GBEAA Sheet 01 : 2 Bolt ASNA2657K3-5 Item 2 2 Bolt ASNA2657K3-6 Item 3 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 33 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A340-500/600 SERVICE BULLETIN 6 Bolt ASNA2657K3-8 Item 5 10 Nut ASNA2538-3 Item 7 <3> On Frame 61 install, refer to Fig. A-GBEAA Sheet 01 : 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 10 Nut ASNA2538-3 Item 7 <4> On Frame 61A, refer to Fig. A-GBEAA Sheet 01 , install: 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 5 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <5> On Frame 62 install, refer to Fig. A-GBEAA Sheet 01 : 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 5 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <6> On Frame 62A install, refer to Fig. A-GBEAA Sheet 01 and Fig. A- GBEAA Sheet 02 : 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <7> On Frame 63 install, refer to Fig. A-GBEAA Sheet 01 and Fig. A- GBEAA Sheet 02 : 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 34 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A340-500/600 SERVICE BULLETIN <8> On Frame 63A install, refer to Fig. A-GBEAA Sheet 01 and Fig. A- GBEAA Sheet 02 : 4 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <9> On Frame 64 install, refer to Fig. A-GBEAA Sheet 01 and Fig. A- GBEAA Sheet 02 : 2 Bolt ASNA2657K3-5 Item 2 2 Bolt ASNA2657K3-6 Item 3 6 Bolt ASNA2657K3-7 Item 4 5 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <10>On Frame 64A install, refer to Fig. A-GBEAA Sheet 01 and Fig. A- GBEAA Sheet 02 : 2 Bolt ASNA2657K3-5 Item 2 2 Bolt ASNA2657K3-6 Item 3 5 Bolt ASNA2657K3-7 Item 4 1 Bolt ASNA2657K3-8 Item 5 4 Washer NAS1149D0332K Item 6 10 Nut ASNA2538-3 Item 7 <11>After the installation of fasteners you must apply: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Wash Primer - Structure 04CMA2 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 35 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A340-500/600 SERVICE BULLETIN Top Coat Polyurethane - External Structure 04JAA3 As required on the affected area(s). <12>Apply to the edges of the beams, frame fork and splice as shown on Fig. A-GBCAA Sheet 01 , Fig. A-GBDAA Sheet 01 and in accordance with SRM 51-76-11: Polysulfide Sealant- General Purpose Fillet 06AAB1 As required <13>Report findings to AIRBUS, refer to Fig. A-GRBAA Sheet 01 <14>Repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). (6) Subtask 525023-832-202-001 - Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment-Door Frame Head Areas Work Zones and Access Panels Zone Access/Work location 822 Access Panel 822AR, Panel 822BR, Panel 822CR, Panel 822DR Work location from Frame 60 to Frame 64A Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Component COMPD01 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 2 ASNA2657K3-5 52 BOLT (1 ) 3 ASNA2657K3-6 52 BOLT (1 ) 4 ASNA2657K3-7 34 BOLT (1 ) 5 ASNA2657K3-8 4 BOLT (1 ) 6 NAS1149D0332K 42 WASHER 7 ASNA2538-3 148 NUT 8 ASNA2657K3-4 18 Bolt (1 ) 9 ASNA2536-3 12 NUT NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 36 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A340-500/600 SERVICE BULLETIN NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . Component COMPD02 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 2 ASNA2657K3-5X 52 BOLT (1 ) 3 ASNA2657K3-6X 52 BOLT (1 ) 4 ASNA2657K3-7X 34 BOLT (1 ) 5 ASNA2657K3-8X 4 BOLT (1 ) 6 NAS1149D0332K 42 WASHER 7 ASNA2536-3 12 NUT 7 ASNA2538-3 148 NUT 8 ASNA2657K3-4X 18 BOLT (1 ) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane - External Structure 04JAA3 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Structural Repair Manual (SRM) 51-42-11 51-43-00 51-44-11 51-46-11 Fig. A-GBFAA Frame Head Fastener Inspection/Removal Area at FR60, FR60A, FR64 and FR64A Sheet 01 Fig. A-GBGAA Frame Head Inspection/Removal Area at FR61 and FR63A Sheet 01 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 37 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A340-500/600 SERVICE BULLETIN References Fig. A-GBHAA Frame Head Inspection/Removal Area at FR61A, FR62A and FR63 Sheet 01 Fig. A-GBJAA Frame Head Inspection/Removal Area at FR62 Sheet 01 Fig. A-GBKAA Frame Head Fastener Installation at FR60, FR60A, FR64 and FR64A Sheet 01 Fig. A-GBLAA Frame Head Fastener Installation at FR61 and FR63A Sheet 01 Fig. A-GBMAA Frame Head Fastener Installation at FR61A, FR62A and FR63 Sheet 01 Fig. A-GBNAA Frame Head Fastener Installation at FR62 Sheet 01 Fig. A-GRCAA Frame Heads Report Sheet Sheet 01 NOTE : Do this subtask on an affected frame head only if a crack is detected or there are any loose, sheared or missing fasteners and the area has no existing repair. If the affected area has existing repair(s) or the frame head has previously been replaced, contact AIRBUS before next flight. (a) On beam 1, at: Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A. Refer to Fig. A-GBFAA Sheet 01 , Fig. A-GBGAA Sheet 01 , Fig. A-GBHAA Sheet 01 and Fig. A-GBJAA Sheet 01 . 1 If you have one or more finding in the inspection area you must remove all fasteners in the inspection area, refer to Fig. A-GBFAA Sheet 01 , Fig. A- GBGAA Sheet 01 , Fig. A-GBHAA Sheet 01 and Fig. A-GBJAA Sheet 01 . 2 If you have one finding at the two lower fasteners remove the two fasteners below, refer to Fig. A-GBFAA Sheet 01 , Fig. A-GBGAA Sheet 01 , Fig. A- GBHAA Sheet 01 and Fig. A-GBJAA Sheet 01 . 3 Within the inspection area open the holes to the applicable diameter for the fasteners ASNA2657K3 in accordance with the SRM. 4 If additional fasteners have been removed as requested in work step 2, these fasteners must be replaced in accordance with the SRM. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 38 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A340-500/600 SERVICE BULLETIN 5 Do the Special Detailed Inspection - rotating probe method, procedure A - on the affected holes and in accordance with NTM Task 51-10-01-250-801. a If no crack is found in outer skin: <1> Ream the affected hole(s) to a size which allows the installation of fastener PN ASNA2657K3-4, ASNA2657K3-5, ASNA2657K3-6, ASNA2657K3-7 or ASNA2657K3-8. <2> Close each affected fastener hole with Bolt PN ASNA2657K3-4, ASNA2657K3-5, ASNA2657K3-6, ASNA2657K3-7, ASNA2657K3-8 or alternate in accordance with SRM 51-43-00, wet installed with: Polysulfide Sealant- General Purpose Brushable 06AAA1 As required <3> On Frame 60 install, refer to Fig. A-GBKAA Sheet 01 : 10 Bolt ASNA2657K3-4 Item 8 2 Bolt ASNA2657K3-5 Item 2 4 Bolt ASNA2657K3-6 Item 3 12 Nut ASNA2536-3 Item 9 4 Nut ASNA2538-3 Item 7 <4> On Frame 60A install, refer to Fig. A-GBKAA Sheet 01 : 8 Bolt ASNA2657K3-4 Item 8 4 Bolt ASNA2657K3-5 Item 2 4 Bolt ASNA2657K3-6 Item 3 16 Nut ASNA2538-3 Item 7 <5> On Frame 61 install, refer to Fig. A-GBLAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 39 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A340-500/600 SERVICE BULLETIN <6> On Frame 61A install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <7> On Frame 62 install, refer to Fig. A-GBNAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <8> On Frame 62A install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-6 Item 3 10 Bolt ASNA2657K3-7 Item 4 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <9> On Frame 63 install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <10>On Frame 63A install, refer to Fig. A-GBLAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 40 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A340-500/600 SERVICE BULLETIN 4 Bolt ASNA2657K3-7 Item 4 2 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <11>On Frame 64 install, refer to Fig. A-GBKAA Sheet 01 : 10 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <12>On Frame 64A install, refer to Fig. A-GBKAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 2 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Bolt ASNA2657K3-8 Item 5 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 <13>After the installation of fasteners you must apply: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Wash Primer - Structure 04CMA2 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Top Coat Polyurethane - External Structure 04JAA3 As required <14>Report findings to AIRBUS. <15>Repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 41 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A340-500/600 SERVICE BULLETIN b If a crack is found: <1> Ream affected hole(s) up to a size which allows the installation of Bolt PN ASNA2657K3-4, ASNA2657K3-5, ASNA2657K3-6, ASNA2657K3-7 or ASNA2657K3-8. <2> Do the Special Detailed Inspection - rotating probe method (procedure "A") - on the affect ed holes in accordance with NTM Task 51-10-01-250-801. If no crack is found during SDI, close each affected fastener hole with Bolt PN ASNA2657K3-4, ASNA2657K3-5, ASNA2657K3-6, ASNA2657K3-7, ASNA2657K3-8 or alternate in accordance with SRM 51-43-00, wet installed with: Polysulfide Sealant- General Purpose Brushable 06AAA1 As required [1] On Frame 60 install, refer to Fig. A-GBKAA Sheet 01 : 10 Bolt ASNA2657K3-4 Item 8 2 Bolt ASNA2657K3-5 Item 2 4 Bolt ASNA2657K3-6 Item 3 12 Nut ASNA2536-3 Item 9 4 Nut ASNA2538-3 Item 7 [2] On Frame 60A install, refer to Fig. A-GBKAA Sheet 01 : 8 Bolt ASNA2657K3-4 Item 8 4 Bolt ASNA2657K3-5 Item 2 4 Bolt ASNA2657K3-6 Item 3 16 Nut ASNA2538-3 Item 7 [3] On Frame 61 install, refer to Fig. A-GBLAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 42 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A340-500/600 SERVICE BULLETIN [4] On Frame 61A install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [5] On Frame 62 install, refer to Fig. A-GBNAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [6] On Frame 62A install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-6 Item 3 10 Bolt ASNA2657K3-7 Item 4 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [7] On Frame 63 install, refer to Fig. A-GBMAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [8] On Frame 63A install, refer to Fig. A-GBLAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 43 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A340-500/600 SERVICE BULLETIN 4 Bolt ASNA2657K3-7 Item 4 2 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [9] On Frame 64 install, refer to Fig. A-GBKAA Sheet 01 : 10 Bolt ASNA2657K3-5 Item 2 6 Bolt ASNA2657K3-6 Item 3 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [10] On Frame 64A install, refer to Fig. A-GBKAA Sheet 01 : 6 Bolt ASNA2657K3-5 Item 2 2 Bolt ASNA2657K3-6 Item 3 4 Bolt ASNA2657K3-7 Item 4 4 Bolt ASNA2657K3-8 Item 5 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [11] After the installation of fasteners you must apply: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Wash Primer - Structure 04CMA2 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Top Coat Polyurethane - External Structure 04JAA3 As required [12] Report the results to AIRBUS. [13] Repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 44 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A340-500/600 SERVICE BULLETIN If a crack is found: [1] Ream the affected holes up to the maximum repair size for Bolt PN ASNA2657K3-4X, ASNA2657K3-5X, ASNA2657K3-6X, ASNA2657K3-7X or ASNA2657K3-8X, [2] Do the Special Detailed Inspection - rotating probe method (procedur e "A") - on the a ffected holes in accordance with NTM Task 51-10-01-250-801 [3] If a crack remains evident, contact AIRBUS for further instructions before next flight. [4] If no crack is evident: [a] Countersink the affected fastener hole in accordance with SRM 51-46-11. [b] Close each affected fastener hole with Bolt PN ASNA2657K3-4X ,ASNA2657K3-5X, ASNA2657K3-6X, ASNA2657K3-7X, ASNA2657K3-8X,or alternate in accordance with SRM 51-43-00, wet installed with: Polysulfide Sealant- General Purpose Brushable 06AAA1 As required [c] On Frame 60, refer to Fig. A-GBKAA Sheet 01 , install: 10 Bolt ASNA2657K3-4X Item 8 2 Bolt ASNA2657K3-5X Item 2 4 Bolt ASNA2657K3-6X Item 3 12 Nut ASNA2536-3 Item 7 4 Nut ASNA2538-3 Item 7 [d] On Frame 60A, Refer to Fig. A-GBKAA Sheet 01 , install: 8 Bolt ASNA2657K3-4X Item 8 4 Bolt ASNA2657K3-5X Item 2 4 Bolt ASNA2657K3-6X Item 3 16 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 45 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A340-500/600 SERVICE BULLETIN [e] On Frame 61, Refer to Fig. A-GBLAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [f] On Frame 61A, refer to Fig. A-GBMAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [g] On Frame 62, refer to Fig. A-GBNAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [h] On Frame 62A, refer to Fig. A-GBMAA Sheet 01 , install: 6 Bolt ASNA2657K3-6X Item 3 10 Bolt ASNA2657K3-7X Item 4 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 46 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A340-500/600 SERVICE BULLETIN [i] On Frame 63, refer to Fig. A-GBMAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 4 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [j] On Frame 63A, refer to Fig. A-GBLAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 2 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [k] On Frame 64, refer to Fig. A-GBKAA Sheet 01 , install: 10 Bolt ASNA2657K3-5X Item 2 6 Bolt ASNA2657K3-6X Item 3 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 [l] On Frame 64A, refer to Fig. A-GBKAA Sheet 01 , install: 6 Bolt ASNA2657K3-5X Item 2 2 Bolt ASNA2657K3-6X Item 3 4 Bolt ASNA2657K3-7X Item 4 4 Bolt ASNA2657K3-8X Item 5 8 Washer NAS1149D0332K Item 6 16 Nut ASNA2538-3 Item 7 DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 47 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A340-500/600 SERVICE BULLETIN [m] After the installation of fasteners you must apply: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Wash Primer - Structure 04CMA2 As required Top Coat Polyurethane - Grey Internal Structure 04JME4 As required Top Coat Polyurethane - External Structure 04JAA3 As required [n] Report findings to AIRBUS. [o] Repeat the inspection in accordance with the accomplishment timescale given in Para 1.E.(2). (7) Subtask 525023-833-203-001 - Repair the AFT Cargo Compartment Door Frame Fork Area Fastener Holes by Bushing Manpower Resources Manhours 4.00 Minimum number of person 1 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Component COMPD11 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 2 ASNA2657K3-5 32 BOLT (1 ) 3 ASNA2657K3-6 7 BOLT (1 ) 4 ASNA2657K3-7 49 BOLT (1 ) 5 ASNA2657K3-8 11 BOLT (1 ) 6 NAS1149D0332K 31 WASHER 7 ASNA2538-3 98 NUT 9 ASNA2536-3 1 NUT NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE (1) : For the alternative part number, refer to the Fig. A-GABAA given in Appendix 02 - Alternative Fasteners for ASNA2657K3 Series . DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 48 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A340-500/600 SERVICE BULLETIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer - Structure 04CMA2 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant - General Purpose Fillet - 06AAB1 As required Non Aqueous Cleaner - General 08BAA9 As required References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Structural Repair Manual (SRM) 51-73-12 51-76-11 Fig. A-GBCAA Frame Fork Inspection/Removal Area Sheet 01 Fig. A-GBDAA Frame Fork Inspection/Removal Area at FR60A thru FR64A Sheet 01 Fig. A-GBPAA Bush Repair Sheet 01 Fig. A-GBRAA Flight Cycle Table Following Repair by Bush (lifetime limitation) Sheet 01 Fig. A-GBEAA Frame Fork Fastener Installation at FR60 thru FR64A Sheet 01 Sheet 02 CAUTION : FOLLOWING A BUSH REPAIR TO A FRAME FORK, A LIMITED NUMBER OF FLIGHT CYCLES IS PERMITTED BEFORE THE FRAME FORK MUST BE REPLACED. (FOR LIFETIME LIMITATION, SEE TABLE IN Fig. A-GBRAA Sheet 01 ). CAUTION : TAKE CARE NOT TO DAMAGE ANY UNDERLAYING OR ADJACENT STRUCTURE DURING THE FOLLOWING WORKSTEPS. NOTE : This repair principle is applicable for damage on existing fasteners and is effective for cargo compartment doors. NOTE : A maximum of one bush only is allowed to be fitted to a frame fork. NOTE : This repair is applicable to frame fork outer flanges only. (a) Remove the affected fastener and other fasteners as necessary to remove the splice, refer to Fig. A-GBCAA Sheet 01 , Fig. A-GBDAA Sheet 01 and Fig. A- GBPAA Sheet 01 . 1 Remove sealant as necessary in accordance with SRM 51-76-11. 2 Remove the splice. DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 49 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A340-500/600 SERVICE BULLETIN 3 Remove any remaining sealant. (b) For all other fastener positions, remove the affected fastener in the damaged area. (c) Remove adjacent fasteners as necessary to position a metal plate for protection of underlaying structure. (d) Clean the work area and the holes to be inspected with: Non Aqueous Cleaner - General 08BAA9 As required (e) Do the special detailed i nspection - rotating probe me thod (procedure "A") - on the affected hole in accordance with NTM Task 51-10-01-250-801. 1 If no cracks are found: - Continue with the modification. 2 If a crack is found: NOTE : The maximum allowable crack length for a bush repair is 2 mm (0.078 in.). - Open up the hole to a maximum diameter of 9 mm (0.354 in.). 3 Repeat the special detailed i nspection - rotating pr obe method (p rocedure "A") - on the affected hole in accordance with NTM Task 51-10-01-250-801. 4 If no cracks are found: - Continue with the modification. 5 If a crack is found: - Replace the affected frame fork, go to SUBTASK 525023-833-204 001 Replace the AFT Cargo Compartment Door Frame Fork . (f) Drill or countersink the damaged flange area with a reverse drill from inside then deburr. NOTE : If the damaged hole is located below the skin or above an internal doubler which is not to be drilled and/or reamed up to the bush diameter, a plastic wedge must be inserted between the skin and the inner structure. Remove adjacent fasteners as necessary to separate the structure. The underlying structure must be protected by a metal plate during the reaming process. (g) Clean the repair area with: Non Aqueous Cleaner - General 08BAA9 As required DATE: Aug 29/13 SERVICE BULLETIN No.: A340-52-5023 REVISION No.: 02 - Nov 27/15 Page: 50 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a340-52-5023/file/aa12c7c376ab.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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