# Airbus Service Bulletin A340-57-4137 Copy: No revision named ("A340-57-4137 R01"), 87 pages: PDF https://openairdocs.org/files/sha256/15/8f/158fdc697618179b3cf49a1fc51642eb028363c7853330d1694dc780c16d77bb; text https://openairdocs.org/service-documents/airbus/a340-57-4137/file/158fdc697618.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0113, the docket of AD 2019-16-07. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Service Bulletin) - Number: A340-57-4137 - Page: https://openairdocs.org/service-documents/airbus/a340-57-4137 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-57-4137/proposed.md). ## Text (87 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0113, the docket of AD 2019-16-07. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A340 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 ATA SYSTEM: 57 TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER HOLE NO. 260 AT FRAME 40 MODIFICATION No.: 206050S33790 This page transmits Revision No.01 of Service Bulletin No.A340-57-4137 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to: - Update the EFFECTIVITY paragraph - Modify the Service Bulletin structure further to validation on A330 aircraft with Manufacturer Serial Number (MSN) 0422. CHANGES The main changes of this revision are: - GENERAL EVALUATION table has been updated - EFFECTIVITY paragraph has been updated - REASON paragr aph has been updated - COMPLIANCE paragraph has been updated - MANPOWER table has been updated - REFERENCES paragraph has been updated - MATERIAL INFORMATION paragraph has been updated: . Procurement address for Kit 573130A01R00 and Kit 573130A02R00 has been updated . Price and Availability note has been updated DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET . INDUSTRY SUPPORT INFORMATION paragraph has been updated . Consumable Materials List (CML) has been updated. - ACCOMPLISHMENT INSTRUCTIONS paragraph has been updated and modified: . Warning has been added . Note has been added . STANDARD PRACTICES paragraph has been updated . PREPARATION par agraph has been updated . PROCEDURE paragraph has been updated . TEST paragraph has been updated . CLOSE-UP paragraph has been updated. - Figure A-FBEAA has been created - Figure A-FBDAA and A-FBDAB has been updated - Manpower Gantt Chart has been updated. SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R NATURE OF THE WORK NATURE OF WORK TABLE UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED R REASON Operational/Maintenance Consequences OPERATIONAL/MAINTENANCE CONSEQUENCES UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED R Price and Availability PRICE AND AVAILABILITY UPDATED R INDUSTRY SUPPORT INFORMATION INDUSTRY SUPPORT INFORMATION UPDATED R LIST OF MATERIALS - OPERATOR SUPPLIED Consumable Materials Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED CONSUMABLE UPDATED QUANTITY UPDATED R TOOLING Tooling - Price and Availability Procurement Addresses PROCUREMENT ADDRESSES UPDATED R Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL SET UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 574137- 831-801-001-Modification TASK SOLUTION UPDATED WARNING UPDATED NOTE UPDATED CAUTION UPDATED R Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 002 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 574137-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 574137-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 574137-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED R Subtask 574137-865-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574137-941-002-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574137-010-001-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED PANEL UPDATED REFERENCED DOCUMENTATION UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED QUANTITY UPDATED REFERENCES UPDATED R DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 574137-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED R Subtask 574137-865-001-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574137-941-002-001 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 574137-010-001-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED PANEL UPDATED REFERENCED DOCUMENTATION UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED QUANTITY UPDATED REFERENCES UPDATED R Subtask 574137-020-001-001 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-250-001-001 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-831-001-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-420-001-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-020-002-001 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-250-002-001 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-831-002-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 574137-420-002-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-020-001-002 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-250-001-002 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-831-001-002 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-420-001-002 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-020-002-002 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-250-002-002 SUBTASK SOLUTION UPDATED MANPOWER RESSOURCE UPDATED R Subtask 574137-831-002-002 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-420-002-002 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R Subtask 574137-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIN UPDATED PANEL UPDATED REFERENCES UPDATED NOTE UPDATED R DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 574137-790-001-001 SUBTASK SOLUTION ADDED N Subtask 574137-700-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIN UPDATED PANEL UPDATED REFERENCES UPDATED NOTE UPDATED R Subtask 574137-790-001-001 SUBTASK SOLUTION ADDED N Subtask 574137-410-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED QUANTITY UPDATED PANEL UPDATED REFERENCES UPDATED R Subtask 574137-942-003-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 574137-410-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED QUANTITY UPDATED PANEL UPDATED REFERENCES UPDATED R Subtask 574137-942-003-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Fig. A-FBDAA Fig. A-FBDAA Sheet 01 SHEET UPDATED R Fig. A-FBDAA Sheet 02 SHEET UPDATED R Fig. A-FBDAB Fig. A-FBDAB Sheet 01 SHEET UPDATED R Fig. A-FBDAB Sheet 02 SHEET UPDATED R Fig. A-FBEAA FIGURE SOLUTION ADDED N Fig. A-FBEAA Sheet 01 SHEET ADDED N Appendix 01 - Manpower Gantt Chart Fig. A-FAAAA Fig. A-FAAAA Sheet 01 SHEET UPDATED R DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET FILING 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 No previous revision REVISION SEQUENCE ORIGINAL: Nov 23/16 REVISION No. : 01 - Feb 16/18 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 7 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET This Page Intentionally Left Blank DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 8 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A340 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. ATA SYSTEM: 57 TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER HOLE NO. 260 AT FRAME 40 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 206050S33790 MINOR None NOTE : As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The area at Frame (FR) 40 is subjected to a specific maintenance program. A new campaign of modifications has been launched to improve the maintenance program, decrease the number of maintenance actions and to improve the structural potential of the aircraft to meet the Extended Service Goal (ESG) / Design Service Goal (DSG). This Service Bulletin recommends the cold expansion of hole 260 at FR40 to improve the fatigue behaviour. Depending on the configuration, this reinforcement consists in doing a second or third cold expansion of fastener hole 260 and installing oversized fastener with high interference. Accomplishment of this Service Bulletin will prevent cracks and will increase the fatigue life on the area of FR40. Accomplishment of this Service Bulletin cancels the requirements of Inspection Service Bulletin No. A340-57-4124 for hole item 260, if accomplished after the lower bound described in the PLANNING INFORMATION paragraph 1.E. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO POTENTIAL AD NO A/C OPERATION AFFECTED NO DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A340 SERVICE BULLETIN SUMMARY EVALUATION TABLE RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO DE-FUELLING/VENTILATION YES VALIDATION ON AIRCRAFT YES NOTE (1) : Service Bulletin recommended to be accomplished to prevent significant operational disruptions. NOTE : Depending on aircraft configuration, defuelling of the center fuel tank may be required before performing the cold working procedure. NOTE : The equivalent of this Service Bulletin has been validated on A330 aircraft with Manufacturer Serial Number (MSN) 0422. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574137A01R00 1 50.00 Bolts, nuts Standard tool TOOLA01 1 See SB FTI cold working tools Standard tool TOOLA02 1 See SB WCI cold working tools **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 574137A02R00 1 50.00 Bolts, nuts Standard tool TOOLA01 1 See SB FTI cold working tools Standard tool TOOLA02 1 See SB WCI cold working tools EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 09M 78U 83V 85Z ABD AFR AIB ALD ARG AXY CAL CPA DLH F2I GAF HFM HFY IBE IRM KMF MAU MDG MRJ PAL PUE ROI S3R SAA SAS SLM SYR THT THY CONCURRENT REQUIREMENTS None DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A340 SERVICE BULLETIN SUMMARY REFERENCES / REPERCUSSIONS TFU 57.11.00.007 OEB None AOT None SIL None ISI None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO MANPOWER **CONF 001 Task 574137-831-801-001: Modification TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 **CONF 002 Task 574137-831-801-001: Modification TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 APPENDICES **CONF ALL Appendix 01 - Manpower Gantt Chart DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A340 SERVICE BULLETIN SUMMARY **CONF ALL A FR40 FR47 VIEW LOOKING AFT RH SHOWN LH SYMMETRICAL BU P INBD CENTER WING BOX LOWER PANEL REFERENCE COLD WORKING OF THE FASTENER HOLE STGR38RH STGR39RH FR40 B C Z141 Z142 LH RH A H260 F_SB_574137_5_SAAA_01_02 Figure A-FSAAA - Sheet 01 Cold Working of the Fastener Hole 260 at FR40 on the Left Hand (LH) and the Right Hand (RH) Side DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A340 SERVICE BULLETIN SUMMARY **CONF ALL DATUMFR40 STGR1 LH SHOWN RH SYMMETRICAL Y1959 C COLD WORKING OF THE FASTENER HOLE H260 F_SB_574137_5_SAAA_02_00 Figure A-FSAAA - Sheet 02 Cold Working of the Fastener Hole 260 at FR40 on the Left Hand (LH) and the Right Hand (RH) Side DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A340 SERVICE BULLETIN SUMMARY This Page Intentionally Left Blank DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A340 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 ATA SYSTEM: 57 TITLE: FUSELAGE - CENTER FUSELAGE - MODIFICATION OF FASTENER HOLE NO. 260 AT FRAME 40 MODIFICATION No.: 206050S33790 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 NOTE : This Service Bulletin is only applicable to aircraft on which modification No. 44360S13013, modification No. 44360S13482 are embodied, Service Bulletin No. A340-57-4138 is accomplished and on which modification No. 49202S16307 is not embodied. (1) Models 340-212 340-213 340-312 340-313 (2) Effectivity by MSN 0178-0180 0185-0186 0190 0192-0194 0197 0199 0201-0202 0204 0207-0208 0210 0212-0215 0217-0218 0221 0227 0233 0236-0237 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0367 0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415 0424 0430 0433-0435 0438 0446-0447 0450 0459 0467 0470 0474 0483 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A340 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 09M 0483 78U 0179 83V 0280 0292 85Z 0263 ABD 0210 AFR 0186 0207 0237 0245 0246 0260 0307 0310 0377 AIB 0192 0243 0264 ALD 0178 ARG 0193 0373 AXY 0374 CAL 0402 0406 0411 0415 0433 CPA 0208 0218 0227 DLH 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 F2I 0214 GAF 0274 0355 HFM 0185 0236 0367 HFY 0190 0202 IBE 0217 0221 0329 IRM 0282 KMF 0278 MAU 0194 0268 MDG 0319 MRJ 0257 PAL 0302 0318 0332 0387 0459 0474 PUE 0212 0215 0399 ROI 0199 0201 S3R 0204 SAA 0197 0378 SAS 0413 0424 0430 0435 0450 0467 0470 SLM 0242 SYR 0381 THT 0385 0395 0438 0446 THY 0180 0270 0331 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A340 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0178 0180 0185 0190 0192 0199 0201 0202 0204 0212 0214 0215 0236 0242 0243 0257 0264 0270 0278 0280 0282 0292 0318 0319 0331 0373 0378 0385 0395 0413 0424 0430 0435 0438 0446 0450 0467 0470 001 002 0179 0186 0193 0194 0197 0207 0208 0210 0213 0217 0218 0221 0227 0233 0237 0245 0246 0252 0260 0263 0268 0274 0297 0302 0304 0307 0310 0321 0325 0327 0329 0332 0335 0347 0352 0354 0355 0367 0374 0377 0379 0381 0387 0390 0399 0402 0406 0411 0415 0433 0434 0447 0459 0474 0483 002 (5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which modification No. 44360S13013, modification No. 44360S13482 are embodied, Service Bulletin No. A340-57-4138 is accomplished and modification No. 49202S16307 is not embodied and on which Service Bulletin No. A340-57-4090 is not accomplished. **CONF 002 Config. 002 is valid for aircraft on which modification No. 44360S13013, modification No. 44360S13482 are embodied, Service Bulletin No. A340-57-4138 is accomplished and modification No. 49202S16307 is not embodied and on which Service Bulletin No. A340-57-4090 is accomplished. (6) Material Effectivity NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 574137A01R00 1 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 574137A02R00 1 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A340 SERVICE BULLETIN **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History The area at Frame (FR) 40 is subjected to a specific maintenance program. A new campaign of modifications has been launched to improve the maintenance program, decrease the number of maintenance actions and to improve the structural potential of the aircraft to meet the Extended Service Goal (ESG) / Design Service Goal (DSG). (2) Objective/Action This Service Bulletin recommends the cold expansion of hole 260 at FR40 to improve the fatigue behaviour. Depending on the configuration, this reinforcement consists in doing a second or third cold expansion of fastener hole 260 and installing oversized fastener with high interference. (3) Advantages Accomplishment of this Service Bulletin will prevent cracks and will increase the fatigue life on the area of FR40. (4) Operational/Maintenance Consequences Accomplishment of this Service Bulletin cancels the requirements of Inspection Service Bulletin No. A340-57-4124 for hole item 260, if accomplished after the lower bound described in the PLANNING INFORMATION paragraph 1.E. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 574137-831-801-001: Modification (1) Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (2) Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (3) Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (4) Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A340 SERVICE BULLETIN (5) Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side (6) Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH side (7) Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side (8) Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side **CONF 002 Task 574137-831-801-001: Modification (1) Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (2) Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (3) Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (4) Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side (5) Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side (6) Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH side (7) Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side (8) Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale AIRBUS recommends not to perform modification before the Flight Cycles (FC)/Flight Hours (FH) values given in the table below. In case of early embodiment, additional inspection of the Center Wing Box (CWB) lower panel might be required before ESG. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A340 SERVICE BULLETIN Lower bound counted from first flight Aircraft Series Aircraft Standard Weight Variant (WV) WV Groups Configuration FC FH A340-300 ST4 020 series except WV 027 Group 43B POST MOD No. 44360 PRE MOD No. 49202 PRE Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 19427 97789 A340-300 ST4 020 series except WV 027 Group 43B POST MOD No. 44360 PRE MOD No. 49202 POST Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 18888 95075 A340-300 ST4 027 Group 43C POST MOD No. 44360 PRE MOD No. 49202 PRE Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 19427 97789 A340-300 ST4 027 Group 43C POST MOD No. 44360 PRE MOD No. 49202 POST Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 18888 95075 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A340 SERVICE BULLETIN A340-200 ST2 000 series Group 42A POST MOD No. 44360 PRE MOD No. 49202 PRE Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 15362 72178 A340-200 ST2 000 series Group 42A POST MOD No. 44360 PRE MOD No. 49202 POST Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 14632 68269 A340-200 ST5 21 Group 42B POST MOD No. 44360 PRE MOD No. 49202 PRE Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 18405 88493 A340-200 ST5 21 Group 42B POST MOD No. 44360 PRE MOD No. 49202 POST Service Bulletin No. A340-57-4090 and POST Service Bulletin No. A340-57-4138 17818 85345 Lower bound table F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 7 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A340 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. **CONF 001 Task 574137-831-801-001: Modification Get Access 18.50 On Aircraft Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 0.50 Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 0.50 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 3.00 Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 1.00 Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 0.50 Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH side 0.50 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 3.00 Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 1.00 Tests 2.00 Close-Up 18.50 TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 NOTE : For an explanation of the man-hours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Manpower Gantt Chart . **CONF 002 Task 574137-831-801-001: Modification Get Access 18.50 On Aircraft Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 0.50 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 8 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A340 SERVICE BULLETIN Task 574137-831-801-001: Modification Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 0.50 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 3.00 Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side 1.00 Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 0.50 Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH side 0.50 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 3.00 Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side 1.00 Tests 2.00 Close-Up 18.50 TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 NOTE : For an explanation of the man-hours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - Manpower Gantt Chart . **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-21-41 21-21-51 25-52-00 25-80-00 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 38-41-00 52-30-00 52-32-11 57-17-11 Elec. Std. Practices Manual (ESPM) 20-55-00 In Service Information (ISI) 51.48.00001 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Bulletin (SB) A340-57-4090 A340-57-4138 Standards Manual (SM) DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 9 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A340 SERVICE BULLETIN Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-48-00 51-70-20 51-75-12 51-76-12 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-21-41 21-21-51 25-52-00 25-80-00 28-00-00 28-10-00 28-11-00 28-25-00 32-12-00 38-41-00 52-30-00 52-32-11 57-17-11 Elec. Std. Practices Manual (ESPM) 20-55-00 In Service Information (ISI) 51.48.00001 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Bulletin (SB) A340-57-4090 A340-57-4138 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-48-00 51-70-20 51-75-12 51-76-12 **CONF ALL K. PUBLICATION AFFECTED Maintenance Planning Document (MPD) 571135-01-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 10 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A340 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Kit 574137A01R00 Kit 574137A02R00 AIRBUS Material, Logistics and Suppliers ATP II B, Hein-Sass-Weg 24 21129 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by E-mail: airbus.kit@airbus.com Telephone Hotline: +49 40 743 51616 (2) Price and Availability Kit 574137A01R00 Cost 50.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the Airbus Spares portal or through a request for quotation to airbus.kit@airbus.com. Kit 574137A02R00 Cost 50.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the Airbus Spares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 11 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A340 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 C. LIST OF COMPONENTS Kit 574137A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 7 EN6115K8-16 2 BOLT 8 ASNA2531-8 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. Kit 574137A02R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 9 EN6115K9-16 2 BOLT 10 ASNA2531-9 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. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 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 Polyurethane Coating - Fuel Vapour Barrier Struct 04PAG2 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Coating Sealant - Fuel Tank Brushable 06HAA1 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 12 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A340 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Adhesion Promoter - For Sealant 06PAG1 As required Non Aqueous Cleaner - General 08BAA9 As required Corrosion Preventive Compound - Water Displacing 12ADB1 As required Textile - Lint Free Cotton 14SBA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. Operators interested in obtaining the Fatigue Technology Inc. (FTI) tool kit should contact: Standard tool TOOLA01 Fatigue Technology Inc. 401 Andover Park East SEATTLE, WA 98188-7605 USA Internet: http://www.fatiguetech.com Phone: (206) 2462010 Fax: (206) 2449886 Operators interested in obtaining the West Coast Industries (WCI) tool kit should contact: DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 13 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A340 SERVICE BULLETIN Standard tool TOOLA02 West Coast Industries Inc. 14900 Whitman Ave. N Seattle, Washington 98133 Tel: (206) 365-7513 Fax: (206) 365-7483 Email: info@coldwork.com Europe, Middle-East, Africa, India and Russia: T e l . :+ 3 356 19 20 49 1( F r a n c e ) Email: customer@capaero.com (b) Price and Availability Standard tool TOOLA01 Procurement to be negotiated directly with FTI. Standard tool TOOLA02 Procurement to be negotiated directly with WCI. (2) Tools NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. 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 - NTM Task 51-10-08. Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) FTIA340574137-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 14 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A340 SERVICE BULLETIN 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. FTI-A340-57-4137-1 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. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) WCIA340574137-1 Capital Tooling 1 (3) NOTE : WCI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. WCI-A340-57-4137-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 15 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A340 SERVICE BULLETIN 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 WCI. (3) Special Tools None DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 16 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A340 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 574137-831-801-001 - Modification WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE TANK EXPLOSION. 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. 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 contains the instructions for the on-aircraft maintenance necessary to ensure the continued airworthiness of the aircraft. For any deviations to the instructions contained herein, contact AIRBUS for further instructions and approval. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 17 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A340 SERVICE BULLETIN NOTE : Discarded parts must be managed at the operator’s discretion. Task Associated Data **CONF 001 Zone 131 132 Manpower TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 **CONF 002 Zone 131 132 Manpower TOTAL MANHOURS 49.00 ELAPSED TIME (HOURS) 23.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 574137-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Task 21-20-00-010-801 Task 21-20-00-410-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-48-00 51-70-20 51-75-12 (a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 18 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A340 SERVICE BULLETIN (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) For the general removal of air-conditioning distribution ducts, refer to AMM Task 21-20-00-010-801. (f) For the general installation of air-conditioning distribution ducts, refer to AMM Task 21-20-00-410-801. (g) Remove and install fasteners in accordance with SRM 51-42-00. (h) Tag all the parts you must remove and retain to make the subsequent installation easier. (i) Get fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) Do the spot facing of the fastener in accordance with SRM 51-70-20. (k) Get alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do a cold working of the fastener holes in accordance with SRM 51-48-00. (m) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (n) Apply sealant in accordance with SRM 51-24-00. (o) Renew the protective finish in accordance with SRM 51-75-12. (p) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (q) 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. (2) Subtask 574137-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 574137-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 19 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A340 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Task 21-20-00-010-801 Task 21-20-00-410-801 Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 51-48-00 51-70-20 51-75-12 (a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) For the general removal of air-conditioning distribution ducts, refer to AMM Task 21-20-00-010-801. (f) For the general installation of air-conditioning distribution ducts, refer to AMM Task 21-20-00-410-801. (g) Remove and install fasteners in accordance with SRM 51-42-00. (h) Tag all the parts you must remove and retain to make the subsequent installation easier. (i) Get fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) Do the spot facing of the fastener in accordance with SRM 51-70-20. (k) Get alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do a cold working of the fastener holes in accordance with SRM 51-48-00. (m) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (n) Apply sealant in accordance with SRM 51-24-00. (o) Renew the protective finish in accordance with SRM 51-75-12. (p) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 20 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A340 SERVICE BULLETIN (q) 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. (2) Subtask 574137-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 574137-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 28-00-00-610-801 Task 28-10-00-910-805 Task 28-25-00-650-801 Task 32-12-00-010-801 Task 52-30-00-010-801 Task 57-17-11-000-801 NOTE : For the basic Aircraft configuration, refer to AMM Chapter "Introduction - Aircraft status for maintenance" in Manual Front Matter section. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put an access platform in position at the cargo door 821. (c) Open the Main Landing Gear (MLG) doors, refer to AMM Task 32-12-00-010-801. (d) Open the 821 FWD cargo-compartment door, refer to AMM Task 52-30-00-010-801. (e) Defuel the center fuel tank, refer to AMM Task 28-25-00-650-801. (f) Degas and ventilate the center fuel tank, refer to AMM Task 28-00-00-610-801 and AMM Task 28-10-00-910-805. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 21 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A340 SERVICE BULLETIN (g) Remove the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-801. (2) Subtask 574137-010-001-001 - Remove/Open for Access in the FWD Cargo- Compartment Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 21-21-41-000-801 Task 21-21-51-000-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo - Compartment) Sheet 01 Fig. A-FBEAA Removal/Installation of the Air Supply Pipe Assembly Sheet 01 CAUTION : DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Remove the partition panels in the FWD cargo compartment 131BX, 131CX, 131DX, 132CX and 132DX, refer to AMM Task 25-52-00-000-801. (b) Remove between Frame 39.1 and Frame 40 on the LH and RH sides as shown on Fig. A-FBAAA and refer to AMM Task 21-20-00-010-801: 2 Duct Item (1) Retain 2 Duct Item (2) Retain (c) Remove as shown on Fig. A-FBAAA and refer to AMM Task 21-21-51-000-801 and AMM Task 21-21-41-000-801: 2 Recirculation Filter Item (3) Retain 2 Recirculation Fan Item (4) Retain (d) Remove as shown on Fig. A-FBEAA : 3 Bolt Item (6 ) Retain 3 Washer Item (7 ) Retain 1 Strip-Bonding Item (9 ) Retain 3 Clamp Item (8 ) Retain DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 22 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A340 SERVICE BULLETIN 1 Air Supply Pipe Assy Item (5 ) Retain (e) Remove the necessary insulation blankets to access the work area, refer to AMM Task 25-80-00-000-801. **CONF 002 (1) Subtask 574137-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 28-00-00-610-801 Task 28-10-00-910-805 Task 28-25-00-650-801 Task 32-12-00-010-801 Task 52-30-00-010-801 Task 57-17-11-000-801 NOTE : For the basic Aircraft configuration, refer to AMM Chapter "Introduction - Aircraft status for maintenance" in Manual Front Matter section. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put an access platform in position at the cargo door 821. (c) Open the Main Landing Gear (MLG) doors, refer to AMM Task 32-12-00-010-801. (d) Open the 821 FWD cargo-compartment door, refer to AMM Task 52-30-00-010-801. (e) Defuel the center fuel tank, refer to AMM Task 28-25-00-650-801. (f) Degas and ventilate the center fuel tank, refer to AMM Task 28-00-00-610-801 and AMM Task 28-10-00-910-805. (g) Remove the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-801. (2) Subtask 574137-010-001-001 - Remove/Open for Access in the FWD Cargo- Compartment Manpower Resources Skills NON SPECIFIC DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 23 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A340 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 21-21-41-000-801 Task 21-21-51-000-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo - Compartment) Sheet 01 Fig. A-FBEAA Removal/Installation of the Air Supply Pipe Assembly Sheet 01 CAUTION : DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Remove the partition panels in the FWD cargo compartment 131BX, 131CX, 131DX, 132CX and 132DX, refer to AMM Task 25-52-00-000-801. (b) Remove between Frame 39.1 and Frame 40 on the LH and RH sides as shown on Fig. A-FBAAA and refer to AMM Task 21-20-00-010-801: 2 Duct Item (1) Retain 2 Duct Item (2) Retain (c) Remove as shown on Fig. A-FBAAA and refer to AMM Task 21-21-51-000-801 and AMM Task 21-21-41-000-801: 2 Recirculation Filter Item (3) Retain 2 Recirculation Fan Item (4) Retain (d) Remove as shown on Fig. A-FBEAA : 3 Bolt Item (6 ) Retain 3 Washer Item (7 ) Retain 1 Strip-Bonding Item (9 ) Retain 3 Clamp Item (8 ) Retain 1 Air Supply Pipe Assy Item (5 ) Retain (e) Remove the necessary insulation blankets to access the work area, refer to AMM Task 25-80-00-000-801. DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 24 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A340 SERVICE BULLETIN **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 574137-020-001-001 - Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner - General 08BAA9 Textile - Lint Free Cotton 14SBA1 References Structural Repair Manual (SRM) 51-42-00 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 (a) Remove as shown on Fig. A-FBDAA and in accordance with SRM 51-42-00: 1 Screw Item (7) Discard 1 Nut Item (8) Discard (b) Remove the old sealant with a non metallic spatula. (c) Clean the work area with: Textile - Lint Free Cotton 14SBA1 As required and DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 25 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A340 SERVICE BULLETIN Non Aqueous Cleaner - General 08BAA9 As required (2) Subtask 574137-250-001-001 - Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 (a) Do a rotating probe test of the fastener hole 260 in accordance with NTM 51-10-01. 1 In case of crack findings in the fastener hole, contact AIRBUS before next flight and follow their instructions. 2 In case of no crack findings, do a cold working of the fastener holes in accordance with SUBTASK 574137-831-001 001 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side . (3) Subtask 574137-831-001-001 - Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 26 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A340 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 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 Non Aqueous Cleaner - General 08BAA9 As required Textile - Lint Free Cotton 14SBA1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) FTIA340574137-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. FTI-A340-57-4137-1 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: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 27 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A340 SERVICE BULLETIN Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) WCIA340574137-1 Capital Tooling 1 (3) NOTE : WCI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. WCI-A340-57-4137-1 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 WCI. References Structural Repair Manual (SRM) 51-44-00 51-48-00 51-70-20 51-75-12 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 28 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A340 SERVICE BULLETIN (a) Do a check of the existing hole diameter and compare with the values as shown on Fig. A-FBDAA . 1 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. 2 In case the hole diameter is less than the minimum starting hole diameter, do the next step. (b) Drill and ream the fastener hole to the correct starting hole diameter as shown on Fig. A-FBDAA and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (c) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (d) If necessary, perform spot facing to the related fastener head depth, in accordance with SRM 51-70-20. (e) Renew the protective finish in accordance with SRM 51-75-12: Wash Primer - Structure 04CMA2 As required and Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required (f) Do the cold working of the fastener hole 260. 1 Install split sleeve as shown on Fig. A-FBDAA . Refer to FTI Tool list No.: EKA340574137-1 Expendable Tooling 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 29 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A340 SERVICE BULLETIN or Refer to WCI Tool list No.: EKA340574137-1 Expendable Tooling 1 2 Do the cold working of the fastener hole 260 in accordance with SRM 51-48-00. Refer to FTI Tool list No.: FTIA340574137-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA340574137-1 Capital Tooling 1 3 Remove the split sleeve. (g) Ream the fastener hole to the final hole diameter, as shown on Fig. A-FBDAA and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (h) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (4) Subtask 574137-420-001-001 - Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 30 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A340 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574137A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 7 EN6115K8-16 1 BOLT 8 ASNA2531-8 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polyurethane Coating - Fuel Vapour Barrier Struct 04PAG2 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Coating Sealant - Fuel Tank Brushable 06HAA1 As required Adhesion Promoter - For Sealant 06PAG1 As required Non Aqueous Cleaner - General 08BAA9 As required Corrosion Preventive Compound - Water Displacing 12ADB1 As required Textile - Lint Free Cotton 14SBA1 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-75-12 51-76-12 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 31 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A340 SERVICE BULLETIN (a) Install the fastener to the aircraft structure. 1 Wet install in accordance with SRM 51-42-00, refer to Fig. A-FBDAA and AMM Task 20-21-11-911-801. 1 Bolt EN6115K8-16 Item 7 1 Nut ASNA2531-8 Item 8 with Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required 2 Clean the work area with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (b) Apply protective finish on the fastener, refer to Fig. A-FBDAA . 1 Apply to the bolt head outside the center fuel tank in accordance with SRM 51-75-12: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polyurethane Coating - Fuel Vapour Barrier Struct 04PAG2 As required Corrosion Preventive Compound - Water Displacing 12ADB1 As required 2 Apply to the nut inside the center fuel tank in accordance with SRM 51-76-12: Adhesion Promoter - For Sealant 06PAG1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 32 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A340 SERVICE BULLETIN Coating Sealant - Fuel Tank Brushable 06HAA1 As required (5) Subtask 574137-020-002-001 - Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 132 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 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 References Structural Repair Manual (SRM) 51-42-00 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 (a) Remove as shown on Fig. A-FBDAA and in accordance with SRM 51-42-00: 1 Screw Item (7) Discard 1 Nut Item (8) Discard (b) Remove the old sealant with a non metallic spatula. (c) Clean the work area with: Textile - Lint Free Cotton 14SBA1 As required and DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 33 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A340 SERVICE BULLETIN Non Aqueous Cleaner - General 08BAA9 As required NOTE : Do a check of the actual diameter and compare with the dimension given in Fig. A-FBDAA . If the values are not correct, contact AIRBUS. (6) Subtask 574137-250-002-001 - Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH side Work Zones and Access Panels Zone Access/Work location 132 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 (a) Do a rotating probe test of the fastener hole 260 in accordance with NTM 51-10-01. 1 In case of crack findings in the fastener hole, contact AIRBUS before next flight and follow their instructions. 2 In case of no crack findings, do a cold working of the fastener holes in accordance with SUBTASK 574137-831-002 001 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side . (7) Subtask 574137-831-002-001 - Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 132 Work location Frame 40 from Stringer 37 to Stringer 38 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 34 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A340 SERVICE BULLETIN Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 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 Non Aqueous Cleaner - General 08BAA9 As required Textile - Lint Free Cotton 14SBA1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) FTIA340574137-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. FTI-A340-57-4137-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 35 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A340 SERVICE BULLETIN 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. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) WCIA340574137-1 Capital Tooling 1 (3) NOTE : WCI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. WCI-A340-57-4137-1 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 WCI. References Structural Repair Manual (SRM) 51-44-00 51-48-00 51-70-20 51-75-12 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 36 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A340 SERVICE BULLETIN (a) Do a check of the existing hole diameter and compare with the values as shown on Fig. A-FBDAA . 1 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. 2 In case the hole diameter is less than the minimum starting hole diameter, do the next step. (b) Drill and ream the fastener hole to the correct starting hole diameter as shown on Fig. A-FBDAA and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (c) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (d) If necessary, perform spot facing to the related fastener head depth, in accordance with SRM 51-70-20. (e) Renew the protective finish in accordance with SRM 51-75-12: Wash Primer - Structure 04CMA2 As required and Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required (f) Do the cold working of the fastener hole 260. 1 Install split sleeve as shown on Fig. A-FBDAA . Refer to FTI Tool list No.: EKA340574137-1 Expendable Tooling 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 37 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A340 SERVICE BULLETIN or Refer to WCI Tool list No.: EKA340574137-1 Expendable Tooling 1 2 Do the cold working of the fastener hole 260 in accordance with SRM 51-48-00. Refer to FTI Tool list No.: FTIA340574137-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA340574137-1 Capital Tooling 1 3 Remove the split sleeve. (g) Ream the fastener hole to the final hole diameter, as shown on Fig. A-FBDAA and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (h) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (8) Subtask 574137-420-002-001 - Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the RH Side Work Zones and Access Panels Zone Access/Work location 132 Work location Frame 40 from Stringer 37 to Stringer 38 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 38 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A340 SERVICE BULLETIN Manpower Resources Manhours 1.00 Minimum number of person 2 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Kit 574137A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 7 EN6115K8-16 1 BOLT 8 ASNA2531-8 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polyurethane Coating - Fuel Vapour Barrier Struct 04PAG2 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required Coating Sealant - Fuel Tank Brushable 06HAA1 As required Adhesion Promoter - For Sealant 06PAG1 As required Non Aqueous Cleaner - General 08BAA9 As required Corrosion Preventive Compound - Water Displacing 12ADB1 As required Textile - Lint Free Cotton 14SBA1 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-75-12 51-76-12 Fig. A-FBDAA Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 39 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A340 SERVICE BULLETIN (a) Install the fastener to the aircraft structure. 1 Wet install in accordance with SRM 51-42-00, refer to Fig. A-FBDAA and AMM Task 20-21-11-911-801. 1 Bolt EN6115K8-16 Item 7 1 Nut ASNA2531-8 Item 8 with Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required 2 Clean the work area with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (b) Apply protective finish on the fastener, refer to Fig. A-FBDAA . 1 Apply to the bolt head outside the center fuel tank in accordance with SRM 51-75-12: Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required Polyurethane Coating - Fuel Vapour Barrier Struct 04PAG2 As required Corrosion Preventive Compound - Water Displacing 12ADB1 As required 2 Apply to the nut inside the center fuel tank in accordance with SRM 51-76-12: Adhesion Promoter - For Sealant 06PAG1 As required Polysulfide Sealant - Fuel Tank Brushable 06ABA1 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 40 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A340 SERVICE BULLETIN Coating Sealant - Fuel Tank Brushable 06HAA1 As required **CONF 002 (1) Subtask 574137-020-001-002 - Remove the Fastener from the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 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 References Structural Repair Manual (SRM) 51-42-00 Fig. A-FBDAB Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 (a) Remove as shown on Fig. A-FBDAB and in accordance with SRM 51-42-00: 1 Screw Item (9) Discard 1 Nut Item (10) Discard (b) Remove the old sealant with a non metallic spatula. (c) Clean the work area with: Textile - Lint Free Cotton 14SBA1 As required and DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 41 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A340 SERVICE BULLETIN Non Aqueous Cleaner - General 08BAA9 As required (2) Subtask 574137-250-001-002 - Do an Inspection of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 0.50 Minimum number of person 2 Subtask elapsed time 0.25 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-01 (a) Do a rotating probe test of the fastener hole 260 in accordance with NTM 51-10-01. 1 In case of crack findings in the fastener hole, contact AIRBUS before next flight and follow their instructions. 2 In case of no crack findings, do a cold working of the fastener holes in accordance with SUBTASK 574137-831-001 002 Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side . (3) Subtask 574137-831-001-002 - Do a Cold Working of the Fastener Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 42 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A340 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 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 Non Aqueous Cleaner - General 08BAA9 As required Textile - Lint Free Cotton 14SBA1 As required Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) FTIA340574137-1 Capital Tooling 1 (3) NOTE : FTI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. FTI-A340-57-4137-1 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: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 43 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A340 SERVICE BULLETIN Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA340574137-1 Durable Tooling 1 (1) EKA340574137-1 Expendable Tooling 1 (2) WCIA340574137-1 Capital Tooling 1 (3) NOTE : WCI has allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools, refer to ISI 51.48.00001 NOTE : Only 1 TOOL Kit is necessary to perform the Cold Working, either TOOLA01 or TOOLA02 depending on the supplier chosen. NOTE (1) : Durable tooling: Ref. DK-A340-57-4137-1 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 ISI 51.48.00001. NOTE (2) : Expendable tooling: Ref. EK-A340-57-4137-1 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. NOTE (3) : Capital tooling: Ref. WCI-A340-57-4137-1 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 WCI. References Structural Repair Manual (SRM) 51-44-00 51-48-00 51-70-20 51-75-12 Fig. A-FBDAB Removal/Installation of the Fasteners at Holes 260 between STGR37 and STGR38 at FR40 on the LH and the RH Side Sheet 01 Sheet 02 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 44 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A340 SERVICE BULLETIN (a) Do a check of the existing hole diameter and compare with the values as shown on Fig. A-FBDAB . 1 In case the existing hole diameter is more than or equal to the minimum starting hole diameter, please contact AIRBUS for further instructions before next flight. 2 In case the hole diameter is less than the minimum starting hole diameter, do the next step. (b) Drill and ream the fastener hole to the correct starting hole diameter as shown on Fig. A-FBDAB and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (c) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (d) If necessary, perform spot facing to the related fastener head depth, in accordance with SRM 51-70-20. (e) Renew the protective finish in accordance with SRM 51-75-12: Wash Primer - Structure 04CMA2 As required and Primer Polyurethane Paint - Corrosion Inhibiting 04EAC2 As required (f) Do the cold working of the fastener hole 260. 1 Install split sleeve as shown on Fig. A-FBDAB . Refer to FTI Tool list No.: EKA340574137-1 Expendable Tooling 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 45 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A340 SERVICE BULLETIN or Refer to WCI Tool list No.: EKA340574137-1 Expendable Tooling 1 2 Do the cold working of the fastener hole 260 in accordance with SRM 51-48-00. Refer to FTI Tool list No.: FTIA340574137-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA340574137-1 Capital Tooling 1 3 Remove the split sleeve. (g) Ream the fastener hole to the final hole diameter, as shown on Fig. A-FBDAB and in accordance with SRM 51-44-00 and SRM 51-48-00. Refer to FTI Tool list No.: DKA340574137-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA340574137-1 Durable Tooling 1 (h) Clean the drilled holes with: Textile - Lint Free Cotton 14SBA1 As required and Non Aqueous Cleaner - General 08BAA9 As required (4) Subtask 574137-420-001-002 - Install the Fastener in the Hole 260 between STGR37 and STGR38 at FR40, on the LH Side Work Zones and Access Panels Zone Access/Work location 131 Work location Frame 40 from Stringer 37 to Stringer 38 DATE: Nov 23/16 SERVICE BULLETIN No.: A340-57-4137 REVISION No.: 01 - Feb 16/18 Page: 46 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a340-57-4137/file/158fdc697618.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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