# Airbus Service Bulletin A310-57-2105 Copy: No revision named ("SB A310-57-2105"), 108 pages: PDF https://openairdocs.org/files/sha256/0c/3f/0c3f35f15786b5cc3b3ed024accb67dee54bec1bc4bd1a923e47b9a4122b6a47; text https://openairdocs.org/service-documents/airbus/a310-57-2105/file/0c3f35f15786.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0025; AD 2018-11-06 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: A310-57-2105 - Page: https://openairdocs.org/service-documents/airbus/a310-57-2105 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2018-11-06](https://openairdocs.org/ad/2018-11-06.md), effective Jul 3, 2018: No revision named Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a310-57-2105/proposed.md). ## Text (108 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0025; AD 2018-11-06 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 @A310 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: 57 TITLE: WINGS - CENTER SECTION - RIB 1 - LOWER TEE FITTING BETWEEN FR40/47 PERFORM COLD WORKING OF HOLES **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13777S22915 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 Following Widespread Fatigue Damage (WFD) analysis, it has been found that the area of lower wing junction requires some modifications in order to reach the Limit Of Validity (L.O.V. definition from FAR26.21). This Service Bulletin details the work necessary to renew and cold work the holes of the first fasteners row close to RIB1. The fasteners are located stiffener 1 to 14, outer wing between FR40 and FR47 on LH and RH sides. The procedure as described in this Service Bulletin is to be performed if no Airbus repair and/or repair improvement has been previously performed in the same area. In case of repairs performed previously, please contact AIRBUS Repair Support department for further instructions. Accomplishment of this Service Bulletin will reach the L.O.V. for aircraft models A310-200 and A310-300. This Modification Service Bulletin affects the airworthiness limitations of Airworthiness Limitation Section (ALS) Part 2 which shall be introduced within the A/C maintenance program under the operator responsibility. Please download the relevant ALS Variation on Airbus World. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A310 SERVICE BULLETIN SUMMARY 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 ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO DE-FUELLING/VENTILATION YES NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 572105A01R00 2 24,200.00 Bolt, nut Standard tool TOOLA01 1 See SB Capital tool, Durable tool, Expendable tool Standard tool TOOLA02 1 See SB Capital tool, Durable tool, Expendable tool **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 572105A02R00 2 22,600.00 Bolt, nut Standard tool TOOLA01 1 See SB Capital tool, Durable tool, Expendable tool Standard tool TOOLA02 1 See SB Capital tool, Durable tool, Expendable tool **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 572105A03R00 2 24,000.00 Bolt, nut Standard tool TOOLA01 1 See SB Capital tool, Durable tool, Expendable tool Standard tool TOOLA02 1 See SB Capital tool, Durable tool, Expendable tool DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A310 SERVICE BULLETIN SUMMARY **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 572105A02R00 2 22,600.00 Bolt, nut Standard tool TOOLA01 1 See SB Capital tool, Durable tool, Expendable tool Standard tool TOOLA02 1 See SB Capital tool, Durable tool, Expendable tool EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 18T 19U 40T 50W 58X 82Z 98W 99Y AFG BBC CFC DGA F2I FDX GAF I2L IRA IRM IYE K1P KAC KZU PCA PIA QQE R1T RJA ROT RZO SGX SUD TBN THY TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None ISI 00.00.00198 51.48.00001 LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side TOTAL MANHOURS 66.00 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A310 SERVICE BULLETIN SUMMARY Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side ELAPSED TIME (HOURS) 18.00 **CONF 002, 004 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 **CONF 003 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumption DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A310 SERVICE BULLETIN SUMMARY **CONF ALL RIB1LH RIB1RH FR40 FR47 B B A B LH SHOWN RH SYMMETRICAL COLD WORKING OF THE FASTENER HOLES RIB1LH FR47 FR40 Z500 Z600 Z140 A B_SB_572105_5_SAAA_01_02 Figure A-FSAAA - Sheet 01 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A310 SERVICE BULLETIN SUMMARY This Page Intentionally Left Blank DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A310 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: 57 TITLE: WINGS - CENTER SECTION - RIB 1 - LOWER TEE FITTING BETWEEN FR40/47 PERFORM COLD WORKING OF HOLES MODIFICATION No.: 13777S22915 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 modification is applicable by Service Bulletin only. (1) Models 310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0399 0413 0418-0419 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452 0456-0458 0467 0472-0473 0478 0480 0482-0484 0488-0492 0494-0500 0503 0519-0520 0522-0524 0526 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651 0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 1 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A310 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 18T 0473 19U 0399 40T 0413 50W 0498 58X 0431 82Z 0550 0551 98W 0495 99Y 0489 AFG 0496 0497 BBC 0594 0700 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0491 0520 FDX 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0439 0449 0452 0456 0457 0458 0467 0492 0500 0539 0549 0552 0593 GAF 0434 0484 0503 0522 0523 I2L 0661 IRA 0436 0671 IRM 0488 0499 0524 0526 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QQE 0667 R1T 0591 RJA 0445 0490 ROT 0636 0644 RZO 0571 0624 0651 SGX 0519 0562 SUD 0437 TBN 0565 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 2 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A310 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 003 0378 0399 0413 0418 0421 0422 0425 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0449 0452 0456 0457 0458 0467 0472 0473 0478 0480 0482 0483 0484 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0503 0519 0520 0522 0523 0524 0526 0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647 0648 0649 0651 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 002 0394 001 0419 004 (5) Configuration definition **CONF 001 Config. 001 is valid for A310-200 aircraft, except MSN 0419, on which modification No. 04977 is embodied. **CONF 002 Config. 002 is valid for A310-300 aircraft. **CONF 003 Config. 003 is valid for A310-200 aircraft on which modification No. 04977 is not embodied. **CONF 004 Config. 004 is valid for A310-200 aircraft MSN 0419. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 572105A01R00 2 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 **CONF 002, 004 MATERIAL QTY PER A/C SEE NOTES Kit 572105A02R00 2 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 3 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A310 SERVICE BULLETIN **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 572105A03R00 2 Consumable CMLA01 1 Standard tool TOOLA01 1 Standard tool TOOLA02 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History Following Widespread Fatigue Damage (WFD) analysis, it has been found that the area of lower wing junction requires some modifications in order to reach the Limit Of Validity (L.O.V. definition from FAR26.21). (2) Objective/Action This Service Bulletin details the work necessary to renew and cold work the holes of the first fasteners row close to RIB1. The fasteners are located stiffener 1 to 14, outer wing between FR40 and FR47 on LH and RH sides. The procedure as described in this Service Bulletin is to be performed if no Airbus repair and/or repair improvement has been previously performed in the same area. In case of repairs performed previously, please contact AIRBUS Repair Support department for further instructions. (3) Advantages Accomplishment of this Service Bulletin will reach the L.O.V. for aircraft models A310-200 and A310-300. (4) Operational/Maintenance Consequences This Modification Service Bulletin affects the airworthiness limitations of Airworthiness Limitation Section (ALS) Part 2 which shall be introduced within the A/C maintenance program under the operator responsibility. Please download the relevant ALS Variation on Airbus World. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 4 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A310 SERVICE BULLETIN Side (1) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side (2) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side **CONF 002 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side (1) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side (2) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side **CONF 003 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side (1) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side (2) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side **CONF 004 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side (1) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side (2) Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 5 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A310 SERVICE BULLETIN (2) Accomplishment Timescale **CONF 001, 003 thru 004 Accomplishment of this Service Bulletin must be done within 47000 Flight Cycles (FC) or 103900 Flight Hours (FH), whichever occurs first. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds given but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 Accomplishment of this Service Bulletin must be done within 42100 FC or 118100 FH, whichever occurs first. This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds given but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. 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 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side Get Access 2.00 On Aircraft Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side 30.00 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 6 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A310 SERVICE BULLETIN Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side 30.00 Tests 2.00 Close-Up 2.00 TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA , given in the Appendix 01 - Elapsed Time Assumption . **CONF 002, 004 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side Get Access 2.00 On Aircraft Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side 30.00 Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side 30.00 Tests 2.00 Close-Up 2.00 TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA , given in the Appendix 01 - Elapsed Time Assumption . **CONF 003 Task 572105-831-801-001: Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side Get Access 2.00 On Aircraft Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side 30.00 Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side 30.00 Tests 2.00 Close-Up 2.00 TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA , given in the Appendix 01 - Elapsed Time Assumption . DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 7 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A310 SERVICE BULLETIN **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-16-00 20-21-12 24-00-00 28-00-00 28-10-00 28-11-22 28-25-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-44 51-40-46 **CONF 002, 004 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-16-00 20-21-12 24-00-00 28-00-00 28-10-00 28-11-22 28-25-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-44 51-40-46 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-16-00 20-21-12 24-00-00 28-00-00 28-10-00 28-11-22 28-25-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 8 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A310 SERVICE BULLETIN Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-44 51-40-46 **CONF 003 Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-16-00 20-21-12 24-00-00 28-00-00 28-10-00 28-11-22 28-25-00 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-44 51-40-46 **CONF ALL K. PUBLICATION AFFECTED Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 9 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A310 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 10 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A310 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 572105A01R00 Kit 572105A02R00 Kit 572105A03R00 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 Hotlines: A330/340, A300/310: +49 40 743 51616 (2) Price and Availability Kit 572105A01R00 Cost 12,100.00 USD Availability 320 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 AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 572105A02R00 Cost 11,300.00 USD Availability 320 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 AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 572105A03R00 Cost 12,000.00 USD Availability 320 calendar days from receipt of order DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 11 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A310 SERVICE BULLETIN 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 AirbusSpares 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. C. LIST OF COMPONENTS Kit 572105A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 10 EN6114V8Y18 9 BOLT 11 EN6114V8Y19 11 BOLT 12 EN6114V8Y20 2 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 1 BOLT 16 EN6114V8Y24 1 BOLT 17 EN6114V8Y25 3 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 2 BOLT 20 EN6114V8Y28 2 BOLT 21 EN6114V8Y29 2 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 1 BOLT 24 EN6114V8Y32 2 BOLT 26 EN6114V8Y34 2 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT 33 NAS1149D0863K 2 WASHER 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 572105A02R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 11 EN6114V8Y19 18 BOLT 12 EN6114V8Y20 3 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 2 BOLT 17 EN6114V8Y25 3 BOLT DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 12 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A310 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 1 BOLT 20 EN6114V8Y28 3 BOLT 21 EN6114V8Y29 1 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 2 BOLT 24 EN6114V8Y32 1 BOLT 26 EN6114V8Y34 4 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 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 572105A03R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 10 EN6114V8Y18 12 BOLT 11 EN6114V8Y19 9 BOLT 13 EN6114V8Y21 1 BOLT 14 EN6114V8Y22 2 BOLT 16 EN6114V8Y24 3 BOLT 17 EN6114V8Y25 1 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 2 BOLT 20 EN6114V8Y28 2 BOLT 21 EN6114V8Y29 2 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 1 BOLT 24 EN6114V8Y32 2 BOLT 26 EN6114V8Y34 2 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT 33 NAS1149D0863K 2 WASHER 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. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 13 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A310 SERVICE BULLETIN D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required Non Aqueous Cleaner-General 08BAA9 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 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 Inc. (WCI) tool kit should contact: DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 14 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A310 SERVICE BULLETIN Standard tool TOOLA02 West Coast Industries Inc. 14900 Whitman Ave. N Seattle, Washington 98133 USA Phone: (206) 365-7513 Fax: (206) 365-7483 Email: info@coldwork.com Europe, Middle-east, Africa, India and Russia: customer@capaero.com / +33 5 61 92 04 91 (France) (b) Price and Availability Standard tool TOOLA01 Procurement to be negotiated directly with Fatigue Technology Inc. (FTI). Standard tool TOOLA02 Procurement to be negotiated directly with West Coast Industries Inc. (WCI). (2) Tools NOTE : To accomplish this Service Bulletin it is necessary to use the tools listed in the subsequent referenced task: - NTM 51-10-01, Page Block 601 - AMM 28-10-00, Page Block 301 - AMM 28-11-22, Page Block 401 Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) FTIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 15 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A310 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: FTI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from FTI. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) WCIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: WCI-A310-57-2105-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 16 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A310 SERVICE BULLETIN The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from WCI. (3) Special Tools None DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 17 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A310 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 18 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A310 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 572105-831-801-001 - Cold Work the Lower Tee Fitting Fastener Holes, on the Wing Side 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. 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. 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 repair DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 19 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A310 SERVICE BULLETIN instructions and approval. NOTE : Discarded parts must be managed at the operator’s discretion. Task Associated Data **CONF 001 Zone 540 640 Access Panel 540AB 640AB Manpower TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 **CONF 002 Zone 540 640 Access Panel 540AB 640AB Manpower TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 **CONF 003 Zone 540 640 Access Panel 540AB 640AB Manpower TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 **CONF 004 Zone 540 640 Access Panel 540AB 640AB Manpower TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 18.00 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 20 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A310 SERVICE BULLETIN **CONF ALL A. GENERAL **CONF 001 (1) Subtask 572105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-16-00, Page Block 201 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-46 (a) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) To torque and tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (k) 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.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 21 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A310 SERVICE BULLETIN (l) 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 fasteners grip length in accordance with SRM, Chapter 51. (m) Obtain the countersinking data in accordance with SRM 51-40-46. (n) Do the cold expansion of fastener holes in accordance with SRM 51-40-41. (o) Apply sealant in accordance with SRM 51-24-00. (p) Renew the protective finish in accordance with SRM 51-23-00. (2) Subtask 572105-839-001-001 - 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 572105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-16-00, Page Block 201 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-46 (a) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 22 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A310 SERVICE BULLETIN (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) To torque and tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (k) 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. (l) 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 fasteners grip length in accordance with SRM, Chapter 51. (m) Obtain the countersinking data in accordance with SRM 51-40-46. (n) Do the cold expansion of fastener holes in accordance with SRM 51-40-41. (o) Apply sealant in accordance with SRM 51-24-00. (p) Renew the protective finish in accordance with SRM 51-23-00. (2) Subtask 572105-839-001-001 - 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 003 (1) Subtask 572105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 23 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A310 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-16-00, Page Block 201 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-46 (a) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) To torque and tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (k) 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. (l) 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 fasteners grip length in accordance with SRM, Chapter 51. (m) Obtain the countersinking data in accordance with SRM 51-40-46. (n) Do the cold expansion of fastener holes in accordance with SRM 51-40-41. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 24 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A310 SERVICE BULLETIN (o) Apply sealant in accordance with SRM 51-24-00. (p) Renew the protective finish in accordance with SRM 51-23-00. (2) Subtask 572105-839-001-001 - 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 004 (1) Subtask 572105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-16-00, Page Block 201 20-21-12, Page Block 001 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-24-00 51-40-00 51-40-20 51-40-30 51-40-40 51-40-41 51-40-46 (a) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For circuit breaker safety practices, refer to AMM 20-16-00, Page Block 201. (e) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) To torque and tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 25 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A310 SERVICE BULLETIN (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (j) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (k) 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. (l) 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 fasteners grip length in accordance with SRM, Chapter 51. (m) Obtain the countersinking data in accordance with SRM 51-40-46. (n) Do the cold expansion of fastener holes in accordance with SRM 51-40-41. (o) Apply sealant in accordance with SRM 51-24-00. (p) Renew the protective finish in accordance with SRM 51-23-00. (2) Subtask 572105-839-001-001 - 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 572105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-22, Page Block 401 28-25-00, Page Block 301 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) DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 26 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A310 SERVICE BULLETIN - 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 that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Defuel the necessary fuel tanks, refer to AMM 28-25-00, Page Block 301. (c) Degas and ventilate the tank, refer to AMM 28-00-00, Page Block 301 and AMM 28-10-00, Page Block 301. (d) Put an access platform in position at zones 510 and 610. (e) Remove the wing tank manholes 540AB and 640AB, refer to AMM 28-11-22, Page Block 401. **CONF 002 (1) Subtask 572105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-22, Page Block 401 28-25-00, Page Block 301 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 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 27 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A310 SERVICE BULLETIN - 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 that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Defuel the necessary fuel tanks, refer to AMM 28-25-00, Page Block 301. (c) Degas and ventilate the tank, refer to AMM 28-00-00, Page Block 301 and AMM 28-10-00, Page Block 301. (d) Put an access platform in position at zones 510 and 610. (e) Remove the wing tank manholes 540AB and 640AB, refer to AMM 28-11-22, Page Block 401. **CONF 003 (1) Subtask 572105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-22, Page Block 401 28-25-00, Page Block 301 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 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 28 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A310 SERVICE BULLETIN - 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 that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Defuel the necessary fuel tanks, refer to AMM 28-25-00, Page Block 301. (c) Degas and ventilate the tank, refer to AMM 28-00-00, Page Block 301 and AMM 28-10-00, Page Block 301. (d) Put an access platform in position at zones 510 and 610. (e) Remove the wing tank manholes 540AB and 640AB, refer to AMM 28-11-22, Page Block 401. **CONF 004 (1) Subtask 572105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-22, Page Block 401 28-25-00, Page Block 301 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 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 29 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A310 SERVICE BULLETIN - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Defuel the necessary fuel tanks, refer to AMM 28-25-00, Page Block 301. (c) Degas and ventilate the tank, refer to AMM 28-00-00, Page Block 301 and AMM 28-10-00, Page Block 301. (d) Put an access platform in position at zones 510 and 610. (e) Remove the wing tank manholes 540AB and 640AB, refer to AMM 28-11-22, Page Block 401. **CONF ALL C. PROCEDURE NOTE : It is allowed to perform the modification on the LH and RH side at the same time. **CONF 001 (1) Subtask 572105-831-001-001 - Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB Work location from Frame 40 to Frame 47 Manpower Resources Manhours 30.00 Minimum number of person 2 Subtask elapsed time 15.00 Skills AIRFRAME Material necessary to do the job Kit 572105A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V8Y18 9 BOLT 11 EN6114V8Y19 11 BOLT 12 EN6114V8Y20 2 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 1 BOLT 16 EN6114V8Y24 1 BOLT DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 30 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A310 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 17 EN6114V8Y25 3 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 2 BOLT 20 EN6114V8Y28 2 BOLT 21 EN6114V8Y29 2 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 1 BOLT 24 EN6114V8Y32 2 BOLT 26 EN6114V8Y34 2 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT 33 NAS1149D0863K 2 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 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 DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) FTIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 31 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A310 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: FTI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from FTI. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) WCIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: WCI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from WCI. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 32 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A310 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-41 51-40-44 51-40-46 Fig. A-FBAAA Cold Working of the Lower Tee Fitting Fastener Holes, on the Wing Side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 CAUTION : ALL THE COLD WORKING STEPS ARE TO BE DONE ON ONE HOLE OUT OF TWO PER SIDE AT THE SAME TIME. THIS IS TO PREVENT DAMAGE TO THE AIRCRAFT. (a) Cold work the lower Tee fitting fastener holes on the LH wing, between Frame 40 and Frame 47: Refer to Fig. A-FBAAA . 1 Remove the fasteners, as shown on Fig. A-FBAAA Sheet 01 , Views A and B and Fig. A-FBAAA Sheet 02 , View C, in accordance with SRM 51-40-20: 42 Bolt Item (1) Discard 42 Nut Item (2) Discard 2 Remove the old sealant with a non metallic spatula. 3 Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required and if necessary, use a non metallic scraper. 4 Do a rotating probe test of the fastener holes in accordance with NTM 51-10-01, Page Block 601, as shown on Fig. A-FBAAA Sheet 02 ,V i e wC : a In case of crack findings in the fastener holes, contact AIRBUS before next flight and follow their instructions. b In case of no crack findings, continue with the next workstep. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 33 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A310 SERVICE BULLETIN 5 Do a check of the existing hole diameters and compare with the values given on Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 : a 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. b In case the hole diameter is less than the minimum starting hole diameter, do the next step. 6 Drill and ream the fastener holes to the correct starting hole diameter, as shown on Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 and in accordance with SRM 51-40-44 and SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 7 Deburr and clean the drilled areas. 8 Do the cold working of the 42 holes, in accordance with SRM 51-40-41, as shown on Fig. A-FBAAA Sheet 03 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 : a Install the split sleeves as shown on Fig. A-FBAAA Sheet 03 . Refer to FTI Tool list No.: EKA310572105-1 Expendable Tooling 1 or Refer to WCI Tool list No.: EKA310572105-1 Expendable Tooling 1 b Do a cold working of the 42 fastener holes in accordance with SRM 51-40-41. Refer to FTI Tool list No.: FTIA310572105-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA310572105-1 Capital Tooling 1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 34 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A310 SERVICE BULLETIN c Remove the split sleeves. 9 Ream the cold worked holes to the final hole diameter, as shown on Fig. A- FBAAA Sheet 03 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 and in accordance with SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 10 Deburr and clean the drilled areas. 11 Countersink the holes in accordance with SRM 51-40-46. 12 Deburr and clean the countersunk holes. 13 Wet install, as shown on Fig. A-FBAAA Sheet 01 , Views A and B, Fig. A- FBAAA Sheet 03 ,V i e wD , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 , in accordance with SRM 51-40-20: 9 Bolt EN6114V8Y18 Item 10 11 Bolt EN6114V8Y19 Item 11 2 Bolt EN6114V8Y20 Item 12 1 Bolt EN6114V8Y22 Item 14 1 Bolt EN6114V8Y23 Item 15 1 Bolt EN6114V8Y24 Item 16 3 Bolt EN6114V8Y25 Item 17 1 Bolt EN6114V8Y26 Item 18 2 Bolt EN6114V8Y27 Item 19 2 Bolt EN6114V8Y28 Item 20 2 Bolt EN6114V8Y29 Item 21 2 Bolt EN6114V8Y30 Item 22 1 Bolt EN6114V8Y31 Item 23 2 Bolt EN6114V8Y32 Item 24 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 35 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A310 SERVICE BULLETIN 2 Bolt EN6114V8Y34 Item 26 6 Nut ASNA2531-8 Item 31 36 Nut ASNA2532-8 Item 32 2 Washer NAS1149D0863K Item 33 with: Polysulfide Sealant- Fuel Tank Brushable 06ABA1 As required 14 Torque standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. 15 Protect the fasteners inside the wing, in accordance with SRM 51-23-00 and SRM 51-24-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and Polysulfide Sealant- Fuel Tank Fillet 06ABB1 As required 16 Protect the head of the fasteners, in accordance with SRM 51-23-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and Top Coat Polyurethane-- External Structure 04JAA3 As required (2) Subtask 572105-831-002-001 - Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side Work Zones and Access Panels Zone Access/Work location 640 Access Panel 640AB Work location from Frame 40 to Frame 47 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 36 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A310 SERVICE BULLETIN Manpower Resources Manhours 30.00 Minimum number of person 2 Subtask elapsed time 15.00 Skills AIRFRAME Material necessary to do the job Kit 572105A01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 10 EN6114V8Y18 9 BOLT 11 EN6114V8Y19 11 BOLT 12 EN6114V8Y20 2 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 1 BOLT 16 EN6114V8Y24 1 BOLT 17 EN6114V8Y25 3 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 2 BOLT 20 EN6114V8Y28 2 BOLT 21 EN6114V8Y29 2 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 1 BOLT 24 EN6114V8Y32 2 BOLT 26 EN6114V8Y34 2 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT 33 NAS1149D0863K 2 WASHER Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 37 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A310 SERVICE BULLETIN Standard tool TOOLA01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) FTIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: FTI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from FTI. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) WCIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 38 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A310 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: WCI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from WCI. References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-41 51-40-44 51-40-46 Fig. A-FBAAA Cold Working of the Lower Tee Fitting Fastener Holes, on the Wing Side Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 CAUTION : ALL THE COLD WORKING STEPS ARE TO BE DONE ON ONE HOLE OUT OF TWO PER SIDE AT THE SAME TIME. THIS IS TO PREVENT DAMAGE TO THE AIRCRAFT. (a) Cold work the lower Tee fitting fastener holes on the RH wing, between Frame 40 and Frame 47: Refer to Fig. A-FBAAA . 1 Remove the fasteners, as shown on Fig. A-FBAAA Sheet 01 , Views A and B and Fig. A-FBAAA Sheet 02 , View C, in accordance with SRM 51-40-20: 42 Bolt Item (1) Discard 42 Nut Item (2) Discard 2 Remove the old sealant with a non metallic spatula. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 39 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A310 SERVICE BULLETIN 3 Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required and if necessary, use a non metallic scraper. 4 Do a rotating probe test of the fastener holes in accordance with NTM 51-10-01, Page Block 601, as shown on Fig. A-FBAAA Sheet 02 ,V i e wC : a In case of crack findings in the fastener holes, contact AIRBUS before next flight and follow their instructions. b In case of no crack findings, continue with the next workstep. 5 Do a check of the existing hole diameters and compare with the values given on Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 : a 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. b In case the hole diameter is less than the minimum starting hole diameter, do the next step. 6 Drill and ream the fastener holes to the correct starting hole diameter, as shown on Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 and in accordance with SRM 51-40-44 and SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 7 Deburr and clean the drilled areas. 8 Do the cold working of the 42 holes, in accordance with SRM 51-40-41, as shown on Fig. A-FBAAA Sheet 03 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 : a Install the split sleeves as shown on Fig. A-FBAAA Sheet 03 . Refer to FTI Tool list No.: EKA310572105-1 Expendable Tooling 1 or DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 40 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A310 SERVICE BULLETIN Refer to WCI Tool list No.: EKA310572105-1 Expendable Tooling 1 b Do a cold working of the 42 fastener holes in accordance with SRM 51-40-41. Refer to FTI Tool list No.: FTIA310572105-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA310572105-1 Capital Tooling 1 c Remove the split sleeves. 9 Ream the cold worked holes to the final hole diameter, as shown on Fig. A- FBAAA Sheet 03 , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 and in accordance with SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 10 Deburr and clean the drilled areas. 11 Countersink the holes in accordance with SRM 51-40-46. 12 Deburr and clean the countersunk holes. 13 Wet install, as shown on Fig. A-FBAAA Sheet 01 , Views A and B, Fig. A- FBAAA Sheet 03 ,V i e wD , Fig. A-FBAAA Sheet 04 and Fig. A-FBAAA Sheet 05 , in accordance with SRM 51-40-20: 9 Bolt EN6114V8Y18 Item 10 11 Bolt EN6114V8Y19 Item 11 2 Bolt EN6114V8Y20 Item 12 1 Bolt EN6114V8Y22 Item 14 1 Bolt EN6114V8Y23 Item 15 1 Bolt EN6114V8Y24 Item 16 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 41 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A310 SERVICE BULLETIN 3 Bolt EN6114V8Y25 Item 17 1 Bolt EN6114V8Y26 Item 18 2 Bolt EN6114V8Y27 Item 19 2 Bolt EN6114V8Y28 Item 20 2 Bolt EN6114V8Y29 Item 21 2 Bolt EN6114V8Y30 Item 22 1 Bolt EN6114V8Y31 Item 23 2 Bolt EN6114V8Y32 Item 24 2 Bolt EN6114V8Y34 Item 26 6 Nut ASNA2531-8 Item 31 36 Nut ASNA2532-8 Item 32 2 Washer NAS1149D0863K Item 33 with: Polysulfide Sealant- Fuel Tank Brushable 06ABA1 As required 14 Torque standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. 15 Protect the fasteners inside the wing, in accordance with SRM 51-23-00 and SRM 51-24-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and Polysulfide Sealant- Fuel Tank Fillet 06ABB1 As required 16 Protect the head of the fasteners, in accordance with SRM 51-23-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 42 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A310 SERVICE BULLETIN Top Coat Polyurethane-- External Structure 04JAA3 As required **CONF 002 (1) Subtask 572105-831-001-002 - Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the LH Side Work Zones and Access Panels Zone Access/Work location 540 Access Panel 540AB Work location from Frame 40 to Frame 47 Manpower Resources Manhours 30.00 Minimum number of person 2 Subtask elapsed time 15.00 Skills AIRFRAME Material necessary to do the job Kit 572105A02R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 11 EN6114V8Y19 18 BOLT 12 EN6114V8Y20 3 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 2 BOLT 17 EN6114V8Y25 3 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 1 BOLT 20 EN6114V8Y28 3 BOLT 21 EN6114V8Y29 1 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 2 BOLT 24 EN6114V8Y32 1 BOLT 26 EN6114V8Y34 4 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 43 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A310 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 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 DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) FTIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: FTI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from FTI. Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) WCIA310572105-1 Capital Tooling 1 (3) DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 44 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A310 SERVICE BULLETIN NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: WCI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from WCI. References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-41 51-40-44 51-40-46 Fig. A-FBAAB Cold Working of the Lower Tee Fitting Fastener Holes, on the Wing Side Sheet 01 Sheet 02 Sheet 03 Sheet 04 CAUTION : ALL THE COLD WORKING STEPS ARE TO BE DONE ON ONE HOLE OUT OF TWO PER SIDE AT THE SAME TIME. THIS IS TO PREVENT DAMAGE TO THE AIRCRAFT. (a) Cold work the lower Tee fitting fastener holes on the LH wing, between Frame 40 and Frame 47: Refer to Fig. A-FBAAB . DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 45 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A310 SERVICE BULLETIN 1 Remove the fasteners, as shown on Fig. A-FBAAB Sheet 01 , Views A and B and Fig. A-FBAAB Sheet 02 , View C, in accordance with SRM 51-40-20: 42 Bolt Item (1) Discard 42 Nut Item (2) Discard 2 Remove the old sealant with a non metallic spatula. 3 Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required and if necessary, use a non metallic scraper. 4 Do a rotating probe test of the fastener holes in accordance with NTM 51-10-01, Page Block 601, as shown on Fig. A-FBAAB Sheet 02 ,V i e wC : a In case of crack findings in the fastener holes, contact AIRBUS before next flight and follow their instructions. b In case of no crack findings, continue with the next workstep. 5 Do a check of the existing hole diameters and compare with the values given on Fig. A-FBAAB Sheet 04 : a 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. b In case the hole diameter is less than the minimum starting hole diameter, do the next step. 6 Drill and ream the fastener holes to the correct starting hole diameter, as shown on Fig. A-FBAAB Sheet 04 and in accordance with SRM 51-40-44 and SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 7 Deburr and clean the drilled areas. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 46 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A310 SERVICE BULLETIN 8 Do the cold working of the 42 holes, in accordance with SRM 51-40-41, as shown on Fig. A-FBAAB Sheet 03 and Fig. A-FBAAB Sheet 04 : a Install the split sleeves as shown on Fig. A-FBAAB Sheet 03 . Refer to FTI Tool list No.: EKA310572105-1 Expendable Tooling 1 or Refer to WCI Tool list No.: EKA310572105-1 Expendable Tooling 1 b Do a cold working of the 42 fastener holes in accordance with SRM 51-40-41. Refer to FTI Tool list No.: FTIA310572105-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA310572105-1 Capital Tooling 1 c Remove the split sleeves. 9 Ream the cold worked holes to the final hole diameter, as shown on Fig. A- FBAAB Sheet 03 and Fig. A-FBAAB Sheet 04 and in accordance with SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 10 Deburr and clean the drilled areas. 11 Countersink the holes in accordance with SRM 51-40-46. 12 Deburr and clean the countersunk holes. 13 Wet install, as shown on Fig. A-FBAAB Sheet 01 , Views A and B, Fig. A- FBAAB Sheet 03 , View D and Fig. A-FBAAB Sheet 04 , in accordance with SRM 51-40-20: 18 Bolt EN6114V8Y19 Item 11 DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 47 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A310 SERVICE BULLETIN 3 Bolt EN6114V8Y20 Item 12 1 Bolt EN6114V8Y22 Item 14 2 Bolt EN6114V8Y23 Item 15 3 Bolt EN6114V8Y25 Item 17 1 Bolt EN6114V8Y26 Item 18 1 Bolt EN6114V8Y27 Item 19 3 Bolt EN6114V8Y28 Item 20 1 Bolt EN6114V8Y29 Item 21 2 Bolt EN6114V8Y30 Item 22 2 Bolt EN6114V8Y31 Item 23 1 Bolt EN6114V8Y32 Item 24 4 Bolt EN6114V8Y34 Item 26 6 Nut ASNA2531-8 Item 31 36 Nut ASNA2532-8 Item 32 with: Polysulfide Sealant- Fuel Tank Brushable 06ABA1 As required 14 Torque standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. 15 Protect the fasteners inside the wing, in accordance with SRM 51-23-00 and SRM 51-24-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and Polysulfide Sealant- Fuel Tank Fillet 06ABB1 As required DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 48 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A310 SERVICE BULLETIN 16 Protect the head of the fasteners, in accordance with SRM 51-23-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and Top Coat Polyurethane-- External Structure 04JAA3 As required (2) Subtask 572105-831-002-002 - Cold Work the Lower Tee Fitting Fastener Holes between FR40 and FR47, on the RH Side Work Zones and Access Panels Zone Access/Work location 640 Access Panel 640AB Work location from Frame 40 to Frame 47 Manpower Resources Manhours 30.00 Minimum number of person 2 Subtask elapsed time 15.00 Skills AIRFRAME Material necessary to do the job Kit 572105A02R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 11 EN6114V8Y19 18 BOLT 12 EN6114V8Y20 3 BOLT 14 EN6114V8Y22 1 BOLT 15 EN6114V8Y23 2 BOLT 17 EN6114V8Y25 3 BOLT 18 EN6114V8Y26 1 BOLT 19 EN6114V8Y27 1 BOLT 20 EN6114V8Y28 3 BOLT 21 EN6114V8Y29 1 BOLT 22 EN6114V8Y30 2 BOLT 23 EN6114V8Y31 2 BOLT 24 EN6114V8Y32 1 BOLT 26 EN6114V8Y34 4 BOLT 31 ASNA2531-8 6 NUT 32 ASNA2532-8 36 NUT DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 49 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A310 SERVICE BULLETIN Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Polyurethane Paint-- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-- External Structure 04JAA3 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 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 DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) FTIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: FTI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from FTI. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 50 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A310 SERVICE BULLETIN Standard tool TOOLA02 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA310572105-1 Durable Tooling 1 (1) EKA310572105-1 Expendable Tooling 1 (2) WCIA310572105-1 Capital Tooling 1 (3) NOTE : The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. 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 (1) : Durable tooling: DK-A310-57-2105-1 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-A310-57-2105-1 The expendable tool kit contains the quantity for 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: WCI-A310-57-2105-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as long- term investment or can be loaned from WCI. References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-41 51-40-44 51-40-46 Fig. A-FBAAB Cold Working of the Lower Tee Fitting Fastener Holes, on the Wing Side Sheet 01 Sheet 02 Sheet 03 Sheet 04 CAUTION : ALL THE COLD WORKING STEPS ARE TO BE DONE ON ONE HOLE OUT OF TWO PER SIDE AT THE SAME TIME. THIS IS TO PREVENT DAMAGE TO THE AIRCRAFT. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 51 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A310 SERVICE BULLETIN (a) Cold work the lower Tee fitting fastener holes on the RH wing, between Frame 40 and Frame 47: Refer to Fig. A-FBAAB . 1 Remove the fasteners, as shown on Fig. A-FBAAB Sheet 01 , Views A and B and Fig. A-FBAAB Sheet 02 , View C, in accordance with SRM 51-40-20: 42 Bolt Item (1) Discard 42 Nut Item (2) Discard 2 Remove the old sealant with a non metallic spatula. 3 Clean the work area with: Non Aqueous Cleaner-General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required and if necessary, use a non metallic scraper. 4 Do a rotating probe test of the fastener holes in accordance with NTM 51-10-01, Page Block 601, as shown on Fig. A-FBAAB Sheet 02 ,V i e wC : a In case of crack findings in the fastener holes, contact AIRBUS before next flight and follow their instructions. b In case of no crack findings, continue with the next workstep. 5 Do a check of the existing hole diameters and compare with the values given on Fig. A-FBAAB Sheet 04 : a 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. b In case the hole diameter is less than the minimum starting hole diameter, do the next step. 6 Drill and ream the fastener holes to the correct starting hole diameter, as shown on Fig. A-FBAAB Sheet 04 and in accordance with SRM 51-40-44 and SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 52 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A310 SERVICE BULLETIN DKA310572105-1 Durable Tooling 1 7 Deburr and clean the drilled areas. 8 Do the cold working of the 42 holes, in accordance with SRM 51-40-41, as shown on Fig. A-FBAAB Sheet 03 and Fig. A-FBAAB Sheet 04 : a Install the split sleeves as shown on Fig. A-FBAAB Sheet 03 . Refer to FTI Tool list No.: EKA310572105-1 Expendable Tooling 1 or Refer to WCI Tool list No.: EKA310572105-1 Expendable Tooling 1 b Do a cold working of the 42 fastener holes in accordance with SRM 51-40-41. Refer to FTI Tool list No.: FTIA310572105-1 Capital Tooling 1 or Refer to WCI Tool list No.: WCIA310572105-1 Capital Tooling 1 c Remove the split sleeves. 9 Ream the cold worked holes to the final hole diameter, as shown on Fig. A- FBAAB Sheet 03 and Fig. A-FBAAB Sheet 04 and in accordance with SRM 51-40-41. Refer to FTI Tool list No.: DKA310572105-1 Durable Tooling 1 or Refer to WCI Tool list No.: DKA310572105-1 Durable Tooling 1 10 Deburr and clean the drilled areas. 11 Countersink the holes in accordance with SRM 51-40-46. 12 Deburr and clean the countersunk holes. DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 53 5 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A310 SERVICE BULLETIN 13 Wet install, as shown on Fig. A-FBAAB Sheet 01 , Views A and B, Fig. A- FBAAB Sheet 03 , View D and Fig. A-FBAAB Sheet 04 , in accordance with SRM 51-40-20: 18 Bolt EN6114V8Y19 Item 11 3 Bolt EN6114V8Y20 Item 12 1 Bolt EN6114V8Y22 Item 14 2 Bolt EN6114V8Y23 Item 15 3 Bolt EN6114V8Y25 Item 17 1 Bolt EN6114V8Y26 Item 18 1 Bolt EN6114V8Y27 Item 19 3 Bolt EN6114V8Y28 Item 20 1 Bolt EN6114V8Y29 Item 21 2 Bolt EN6114V8Y30 Item 22 2 Bolt EN6114V8Y31 Item 23 1 Bolt EN6114V8Y32 Item 24 4 Bolt EN6114V8Y34 Item 26 6 Nut ASNA2531-8 Item 31 36 Nut ASNA2532-8 Item 32 with: Polysulfide Sealant- Fuel Tank Brushable 06ABA1 As required 14 Torque standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. 15 Protect the fasteners inside the wing, in accordance with SRM 51-23-00 and SRM 51-24-00, with: Primer Polyurethane Paint- - Corrosion Inhibiting 04EAC2 As required and DATE: Nov 23/16 SERVICE BULLETIN No.: A310-57-2105 REVISION No.: 00 - Nov 23/16 Page: 54 5 Printed in FRANCE © AIRBUS S.A.S. 2007. 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