# Airbus Service Bulletin A310-24-2105 Copy: Revision 02 ("FAA-2014-0775_SB A310-24-2105_Rev02_Removed Appendices"), 346 pages: PDF https://openairdocs.org/files/sha256/fc/0e/fc0e7ae37a456e901e770b58db9c23ee82830d79623243f4f690efd80ac9e9bb; text https://openairdocs.org/service-documents/airbus/a310-24-2105/file/fc0e7ae37a45.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0775; AD 2016-07-22 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: A310-24-2105 - Latest revision known: A310-24-2105, Revision 02, dated January 5, 2015 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a310-24-2105 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2016-07-22](https://openairdocs.org/ad/2016-07-22.md), effective May 16, 2016: Revisions 01 and 02 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a310-24-2105/proposed.md). ## Text (346 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2014-0775; AD 2016-07-22 incorporates this document by reference. 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 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 24 TITLE: ELECTRIC COMMON INSTALLA TION - WINGS - IMPROVE WIRING INSTALLATION MODIFICATION No.: 13492S22794 13497D23225 This page transmits Revision No.02 of Service Bulletin No.A310-24-2105 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No.02 issued to: - Update the quantity of placards in KIT D01 and D02. CHANGES - The main changes are: . Quantity update of placards in KIT D01 and D02 . Validity of KIT D01 and D03 in the Material Information paragraph SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 002 CONFIGURATION DEFINITION UPDATED R DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET CONF 003 CONFIGURATION DEFINITION UPDATED R CONF 004 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED MATERIAL SET UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED MATERIAL SET UPDATED R MATERIAL INFORMATION LIST OF COMPONENTS Kit 242105D01R08 PART MATERIAL SET UPDATED QUANTITY UPDATED R Kit 242105D02R08 PART MATERIAL SET UPDATED QUANTITY UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 242105- 831-848-001- MODIFICATION Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-211-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-212-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-213-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-214-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-220-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-211-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-211-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-213-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-214-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 242105-831-220-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R 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 Revision No.01 issued to: Update the effectivity. REVISION SEQUENCE ORIGINAL: Mar 20/13 REVISION No. : 01 - Dec 11/13 REVISION No. : 02 - Jan 05/15 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET This Page Intentionally Left Blank DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @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: 24 TITLE: ELECTRIC COMMON INSTALLA TION - WINGS - IMPROVE WIRING INSTALLATION **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13492S22794 13497D23225 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 A310 aircraft operator’s feedback further to the accomplishment of the mandatory Inspection Service Bulletin A310-24-2095 and a review of the wing electrical installation at the AIRBUS final assembly line have shown that the wing electrical installation doesn’t comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations. This Service Bulletin requires: - the installation of new bracket assemblies to improve the electrical harnesses installation and secure the clearance to the structure in identified locations - the installation of protective split sleeve as mechanical protection to the electrical harnesses in areas where the minimum distance to the structure cannot be achieved. Accomplishment of this modification Service Bulletin will improve the wing electrical installation in the identified areas and prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A310 SERVICE BULLETIN SUMMARY EVALUATION TABLE POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO Kit Price (USD) See SB 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 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts TOTAL 18,606.00 **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D01R08 1 3,590.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 14,203.00 **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 18,703.00 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A310 SERVICE BULLETIN SUMMARY **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 242105A01R03 1 10,480.00 Protective sleeve, spacer, hardware Kit 242105B01R02 1 36.00 Brackets, nutplate, rivets Kit 242105D02R08 1 8,090.00 Ramp, clamp, spacer, protection sleeve and attachment parts Kit 242105D03R01 1 96.00 Clamp and attachment parts Kit 242105D04R00 1 97.00 Clamp and attachment parts TOTAL 18,799.00 EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 18T 19U 40T 50W 58X 82Z 85Z 98W 99Y AFG AIC BBC CFC DGA F2I FDX GAF HFY IRA IRM IYE K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO SGX SUD THY TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A310 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Task 242105-831-848-001: MODIFICATION TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumption DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A310 SERVICE BULLETIN SUMMARY **CONF 001 thru 003 B_SB_242105_6_SAAB_01_03 ZONES WITH ROUTING TO MODIFY Z573 Z513 Z613 − Z137 Z138 Z673 Z512 Z612 Z524 Z624 Z675 Figure A-GSAAB - Sheet 01 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A310 SERVICE BULLETIN SUMMARY **CONF 004 Z573 Z513 Z613 − Z137 Z138 Z673 ZONES WITH ROUTING TO MODIFY Z512 Z612 Z524 Z624 Z575 B_SB_242105_6_SAAE_01_01 Figure A-GSAAE - Sheet 01 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @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: 24 TITLE: ELECTRIC COMMON INSTALLA TION - WINGS - IMPROVE WIRING INSTALLATION MODIFICATION No.: 13492S22794 13497D23225 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 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 0237 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0378 0394 0399 0407 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 0526-0527 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: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @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 85Z 0527 98W 0495 99Y 0489 AFG 0496 0497 AIC 0407 BBC 0594 0700 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 F2I 0491 0520 FDX 0162 0230 0237 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 HFY 0565 IRA 0436 0671 IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 ROT 0636 0644 RZO 0571 0624 0651 0661 SGX 0519 0562 SUD 0437 THY 0478 0480 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A310 SERVICE BULLETIN OPERATOR MSN WHT 0494 (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0237 0245 0248 0267 0278 0281 0283 0331 0356 0362 0364 0369 0394 002 0378 0439 0449 0452 0456 0457 0458 0467 0489 0492 0500 0539 0549 0568 0574 0576 0591 0594 0624 0636 0644 0660 0672 0674 0676 0678 0682 0687 0689 0700 0702 0704 0706 001 0399 0407 0413 0419 0421 0422 0431 0434 0436 0437 0620 003 0418 0425 0441 0444 0445 0446 0447 0472 0473 0478 0480 0482 0483 0484 0488 0490 0491 0494 0495 0496 0497 0498 0499 0503 0519 0520 0522 0523 0524 0526 0527 0537 0545 0547 0550 0551 0552 0562 0564 0565 0567 0571 0585 0586 0587 0588 0590 0592 0593 0595 0597 0599 0600 0622 0646 0647 0648 0649 0651 0653 0656 0658 0661 0663 0667 0671 0691 004 (5) Configuration definition **CONF 001 Config. 001 is valid for the 310-324 and 310-325 type of aircraft in the effectivity of this Service Bulletin for aircraft without installation of 5082VN and 5084VN on RIB 8 and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 002 Config. 002 is valid for the 310-203, 310-221, 310-222, 310-324 and 310-325 type of aircraft in the effectivity of this Service Bulletin for aircraft with 5082VN and 5084VN on RIB 8 installed and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 003 Config. 003 is valid for the 310-304 and 310-322 type of aircraft in the effectivity of this Service Bulletin with 5082VN and 5084VN on RIB 8 installed and without installation of wires 2612-5017 and 2612-5016 on 2147VC. **CONF 004 Config. 004 is valid for the 310-308 and 310-304 type of aircraft in the effectivity of this Service Bulletin with 5082VN and 5084VN on RIB 8 installed and with wires 2612-5017 and 2612-5016 on 2147VC installed. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A310 SERVICE BULLETIN MATERIAL QTY PER A/C SEE NOTES Kit 242105D02R08 1 Consumable CMLD01 As required **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D01R08 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D02R08 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit 242105A01R03 1 Consumable CMLA01 As required Kit 242105B01R02 1 Consumable CMLB01 As required Kit 242105D02R08 1 Kit 242105D03R01 1 Kit 242105D04R00 1 Consumable CMLD01 As required **CONF ALL B. CONCURRENT REQUIREMENTS None DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A310 SERVICE BULLETIN C. REASON (1) History The A310 aircraft operator’s feedback further to the accomplishment of the mandatory Inspection Service Bulletin A310-24-2095 and a review of the wing electrical installation at the AIRBUS final assembly line have shown that the wing electrical installation doesn’t comply with the minimum distance inspection criteria to the surrounding structure in a few wing locations. (2) Objective/Action This Service Bulletin requires: - the installation of new bracket assemblies to improve the electrical harnesses installation and secure the clearance to the structure in identified locations - the installation of protective split sleeve as mechanical protection to the electrical harnesses in areas where the minimum distance to the structure cannot be achieved. (3) Advantages Accomplishment of this modification Service Bulletin will improve the wing electrical installation in the identified areas and prevent possible chafing and subsequent damage to the electrical harnesses and surrounding structure. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A310 SERVICE BULLETIN (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2 (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2 (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (16) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. **CONF 002 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A310 SERVICE BULLETIN (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. **CONF 003 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (16) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 7 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A310 SERVICE BULLETIN **CONF 004 Task 242105-831-848-001: MODIFICATION (1) Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 (2) Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. (3) Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. (4) Modify the routing in the LH forward wing to fuselage fairing. (5) Modify the routing in the RH forward wing to fuselage fairing. (6) Modify the routing on the LH shroud box leading edge. (7) Modify the routing on the RH shroud box leading edge. (8) Install new nutplate on the RH wing Leading edge (9) Modify the electrical routing installation at the LH front spar in the area of RIB 2. (10) Modify the electrical routing installation at the RH front spar in the area of RIB 2. (11) Modify the electrical routing installation at the LH front spar in the area of RIB 3. (12) Modify the electrical routing installation at the RH front spar in the area of RIB 3. (13) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. (14) Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. (15) Modify the electrical routing installation at the RH front spar in the area of RIB 8. (16) Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. (17) Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. (18) Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. (19) Modify the electrical routing installation at the LH rear spar in the area of RIB 9. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 8 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A310 SERVICE BULLETIN **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. F. APPROVAL The technical content of this document is approved under the authority of the 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. For an explanation of the manhours and elapsed time, refer to Appendix 01 - Elapsed Time Assumption . **CONF 001 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 9 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A310 SERVICE BULLETIN Task 242105-831-848-001: MODIFICATION Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 10 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A310 SERVICE BULLETIN Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.75 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 1.75 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.75 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.75 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 0.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 11 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A310 SERVICE BULLETIN Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Task 242105-831-848-001: MODIFICATION Get Access 8.00 On Aircraft Install Adhesive Clipping Bracket on the LH and RH Wing Leading Edge in the Area of Rib 7 1.00 Attach the routes 1E and 1G with the lacing tape in the LH shroud box leading edge. 0.50 Attach the routes 2E and 2G with the lacing tape in the RH shroud box leading edge. 0.50 Modify the routing in the LH forward wing to fuselage fairing. 2.00 Modify the routing in the RH forward wing to fuselage fairing. 2.00 Modify the routing on the LH shroud box leading edge. 6.00 Modify the routing on the RH shroud box leading edge. 6.00 Install new nutplate on the RH wing Leading edge 1.00 Modify the electrical routing installation at the LH front spar in the area of RIB 2. 1.5 Modify the electrical routing installation at the RH front spar in the area of RIB 2. 2.00 Modify the electrical routing installation at the LH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the RH front spar in the area of RIB 3. 1.00 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 5 and RIB 6. 2.50 Modify the electrical routing installation at the LH and RH front spars in the area of RIB 7 and RIB 8. 1.00 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 12 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A310 SERVICE BULLETIN Task 242105-831-848-001: MODIFICATION Modify the electrical routing installation at the RH front spar in the area of RIB 8. 0.50 Modify the electrical routing installation at the LH front spar in the area of RIB 20 and RIB 21. 3.25 Modify the electrical routing installation at the RH front spar in the area of RIB 20 and RIB 21. 2.50 Modify the electrical routing installation at the RH front spar in the area of RIB 28 and RIB 28A. 1.50 Modify the electrical routing installation at the LH rear spar in the area of RIB 9. 0.75 Tests 1.00 Close-Up 10.00 TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25 **CONF ALL H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. **CONF 001 Manufacturers Empty Weight +0.668 KG (+1.4726 LB) Effect on Balance +21.454 KGM (+155.176 LB.FT ) **CONF 002 Manufacturers Empty Weight +0.319 KG (+0.7032 LB) Effect on Balance +10.741 KGM (+77.689 LB.FT ) **CONF 003 Manufacturers Empty Weight +0.668 KG (+1.4726 LB) Effect on Balance +21.454 KGM (+155.176 LB.FT ) **CONF 004 Manufacturers Empty Weight +0.018 KG (+0.0396 LB) Effect on Balance +0.621 KGM (+4.491 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 13 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A310 SERVICE BULLETIN J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 003 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 14 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A310 SERVICE BULLETIN Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 004 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 06-41-53 06-41-57 20-21-12 20-23-12 20-27-00 24-00-00 27-50-00 27-61-00 27-80-00 29-00-00 29-10-00 29-14-00 29-25-00 32-12-11 36-11-00 53-15-63 71-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-33 20-33-41 20-33-44 20-55-00 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-50 51-43-00 51-75-10 51-77-10 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED Illustrated Parts Catalog (IPC) 24-92-02 24-92-03 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 15 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A310 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 16 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @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 242105A01R03 Kit 242105B01R02 Kit 242105D01R08 Kit 242105D02R08 Kit 242105D03R01 Kit 242105D04R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 4012 For ordering by E-mail: ifd.spares@airbus.com (2) Price and Availability Kit 242105A01R03 Cost 10,480.00 USD Availability 90 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 242105B01R02 Cost 36.00 USD Availability 90 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 242105D01R08 Cost 3,590.00 USD Availability 90 calendar days from receipt of order DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 17 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @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. Kit 242105D02R08 Cost 8,090.00 USD Availability 90 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 242105D03R01 Cost 96.00 USD Availability 90 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 242105D04R00 Cost 97.00 USD Availability 90 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. B. INDUSTRY SUPPORT INFORMATION AIRBUS will provide a 10% reduction to the applicable kits sales prices given in the paragraph ’Price and Availability’ for orders placed before Dec 31/2015. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 18 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A310 SERVICE BULLETIN C. LIST OF COMPONENTS Kit 242105A01R03 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 51 NSA8420-5 2( M ) CORD 52 EN6049-007-08-5 56 (M) SLEEVE 53 NSA935401-05 344 TIE 55 A9201346420000 2 GROMMET 56 NAS1801-3-17 12 SCREW 57 NAS1149D0316H 34 WASHER 60 NAS1801-3-13 8 SCREW 61 NSA5527-03-03 8 SPACER 62 NSA935401-13 15 TIE 63 NSA5527-03-01 16 SPACER 64 NSA5527-03-02 10 SPACER 65 A9222505750000 2 SPACER 66 EN6049-007-13-5 56 (M) SLEEVE 67 EN6049-007-19-5 56 (ME) SLEEVE 69 NSA939510BN 4( M ) STRIP 85 NSA5516-08ND 32 CLAMP 86 NSA5516-18ND 32 CLAMP 91 A0041113620000 3 BRACKET 92 A0041113620100 3 BRACKET 93 A0041113720000 3 BRACKET 94 A0041113720100 3 BRACKET 96 NSA5516-10ND 16 CLAMP 97 NAS1801-3-14 6 SCREW 98 NAS1801-3-8 6 SCREW 99 NAS1801-3-16 2 SCREW 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 242105D01R08 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 5 WASHER 4 NSA5527-03-03D 2 SPACER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 9 MS21919WCH3 3 CLAMP 10 MS21919WCH2 2 CLAMP 18 MS21919WCH12 3 CLAMP DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 19 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A310 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 19 MS21919WCH4 8 CLAMP 20 EN6049-007-05-5 2( M E ) SLEEVE 21 EN6049-007-19-5 2( M E ) SLEEVE 23 NAS1801-3-16 4 SCREW 24 MS21042-3 2 NUT 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 29 MS21919WCH11 6 CLAMP 30 MS21919WCH5 1 CLAMP 31 NAS1801-3-13 2 SCREW 32 NSA5527-03-07D 4 SPACER 42 A9249252400400 2 RAMP 43 NSA935401-03 32 TIE 100 B9239030000200 15 PLACARD 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 242105D02R08 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 2 MS21919WCH10 2 CLAMP 3 NAS1149D0332K 9 WASHER 4 NSA5527-03-03D 2 SPACER 6 NAS1801-3-10 2 SCREW 7 NSA5527-03-05D 2 SPACER 8 NSA5527-03-01D 4 SPACER 9 MS21919WCH3 15 CLAMP 10 MS21919WCH2 6 CLAMP 11 NAS1801-3-18 4 SCREW 18 MS21919WCH12 5 CLAMP 19 MS21919WCH4 11 CLAMP 20 EN6049-007-05-5 2( M E ) SLEEVE 21 EN6049-007-19-5 2( M E ) SLEEVE 23 NAS1801-3-16 4 SCREW 24 MS21042-3 6 NUT 25 NAS1096-3-24 4 SCREW 26 NAS1096-3-22 4 SCREW 27 NSA5527-03-15D 2 SPACER 28 NAS1801-3-30 1 SCREW 29 MS21919WCH11 5 CLAMP 30 MS21919WCH5 2 CLAMP 31 NAS1801-3-13 2 SCREW DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 20 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A310 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 32 NSA5527-03-07D 10 SPACER 40 A9249252400000 2 RAMP 41 A9249252400200 2 RAMP 42 A9249252400400 2 RAMP 43 NSA935401-03 56 TIE 100 B9239030000200 19 PLACARD 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 242105D03R01 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 10 MS21919WCH2 2 CLAMP 15 NAS1801-3-35 1 SCREW 16 NSA5527-03-11D 1 SPACER 100 B9239030000200 1 PLACARD 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 242105D04R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 3 NAS1149D0332K 1 WASHER 6 NAS1801-3-10 1 SCREW 9 MS21919WCH3 1 CLAMP 24 MS21042-3 1 NUT 100 B9239030000200 1 PLACARD 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 242105B01R02 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 102 ABS1546B3C12 2 BRACKET 106 NSA5456-3-8 1 NUTPLATE 111 ANSA2050DCJ3210 2 RIVET DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 21 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A310 SERVICE BULLETIN 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 Polyvinylacetat Pvac 05-034 As required Aluminium Foil 05-169 As required Stainless Steel Lockwire 05-289 As required 68 Epoxy Resin 08-051 As required Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Two Part Paste Adhesive 08-078 As required Multi Purpose Thixotropic Paste 09-016J As required Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 22 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A310 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 242105-831-848-001 - MODIFICATION WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. 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 ELECTRICAL W IRING 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 refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 23 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A310 SERVICE BULLETIN Task Associated Data **CONF 001 Zone 120 137 138 500 512 520 524 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 30.75 **CONF 002 Zone 120 137 138 500 512 520 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 49.50 ELAPSED TIME (HOURS) 29.50 **CONF 003 Zone 120 137 138 500 512 520 524 573 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 54.25 ELAPSED TIME (HOURS) 34.00 **CONF 004 Zone 120 137 138 500 512 520 524 573 575 600 612 620 624 673 Access Panel 512HB 513QL 513RR 612HB 613QL 613RR 624KB 672AZ 672BZ Manpower TOTAL MANHOURS 55.50 ELAPSED TIME (HOURS) 31.25 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 24 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A310 SERVICE BULLETIN **CONF ALL A. GENERAL **CONF 001 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 25 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A310 SERVICE BULLETIN (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and too ling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 26 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A310 SERVICE BULLETIN (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 27 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A310 SERVICE BULLETIN Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Par t Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 28 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A310 SERVICE BULLETIN References Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and too ling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 29 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A310 SERVICE BULLETIN - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 30 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A310 SERVICE BULLETIN (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 31 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A310 SERVICE BULLETIN (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Par t Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 32 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A310 SERVICE BULLETIN (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and too ling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 33 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @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 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 34 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A310 SERVICE BULLETIN - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Par t Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 35 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A310 SERVICE BULLETIN **CONF 004 (1) Subtask 242105-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 06-41-57, Page Block 001 20-23-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-25-51 20-33-41 20-33-44 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-50 51-43-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML). (b) For the frames (FR) identification (Refer to AMM 06-31-53, Page Block 001). (c) For the identification of zones (Refer to AMM 06-21-00, Page Block 001). (d) For the identification of the access panels (Refer to AMM 06-41-53, Page Block 001 and AMM 06-41-57, Page Block 001). (e) Tag all the parts you must remove and retain to make the subsequent installation easier. (f) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (g) 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 the Standards Manual (SM). The SM will give you the correct part number to part number relationship. (h) To torque tighten the hydraulic line unions (Refer to AMM 20-23-12, Page Block 001). (i) Use a non-metallic spatula to remove the sealant. (j) Remove/install the fasteners (Refer to SRM 51-40-21). (k) For standard torque value (Refer to SRM 51-43-00). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 36 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A310 SERVICE BULLETIN (l) For fasteners spacing and margin (Refer to SRM 51-40-50). (m) For alternative and substitute fasteners (Refer to SRM 51-40-30). (n) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-51). (o) For the cable support and too ling (Refer to ESPM 20-33-41). (p) When you install protective electrical conduit : - Deburr the ends after you have cut it to the correct size. - At the lowest part of a cable loop make two cut-outs in the conduit to give drainage. - Cut the conduit before installation to make sure you do not damage the electrical cables. - Where necessary, install cable ties from between 13 mm and 15 mm (0.51 and 0.59 in.) from the cut ends of the conduit, to give support. - Where necessary, attach the conduit to the aircraft structure or to existing cable harnesses, with the cable ties supplied. (q) Install Service Bulletin identification placards at each end of new or modified electrical wires in a position where they can be easily seen and at approximately every 1.50 m (59.0 in.). (2) Subtask 242105-910-401-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-00 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 37 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A310 SERVICE BULLETIN (d) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-12, Page Block 001. (f) Remove and install fasteners in accordance with SRM 51-40-20. (g) Obtain fastener hole diameters and drill data in accordance with SRM 51-40-40. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-40-30. (i) Remove and install fasteners in accordance with SRM 51-40-20. (j) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes. - Make sure that you have the correct edge clearance before you drill the fastener holes. - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in). - Transfer-drill the existing holes with a pilot drill and a drill bush. - Deburr the holes after you have drilled them. - Cut the rivets to the correct length, as necessary. - When you remove fasteners you must be careful that you do not damage the holes in the structure. - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in) diameter. Increase the hole diameter to the correct size for the fastener which you must install. (k) Apply sealant in accordance with SRM 51-24-00. (l) Apply interfay sealant in accordance with SRM 51-24-00. (m) Renew the protective in accordance with SRM 51-23-00. (3) Subtask 242105-910-201-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 120 Manpower Resources Skills NON SPECIFIC DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 38 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A310 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Consumable Material List (CML) Structural Repair Manual (SRM) 51-77-10 (a) If necessary, clean the work area with: Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required (b) Use the curing cycle of the Two Par t Paste Adhesive, Mat. No. 08-078, in accordance with SRM 51-77-10. (4) Subtask 242105-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 39 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A310 SERVICE BULLETIN (a) The following items 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 systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (c) Put access platform(s) in position. (d) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 40 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A310 SERVICE BULLETIN (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE : This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . NOTE : Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 41 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A310 SERVICE BULLETIN NOTE : Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE : Retain the hardware. NOTE : Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE : Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE : Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 42 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A310 SERVICE BULLETIN 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE : Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE : Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE : Retain the hardware. (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 43 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A310 SERVICE BULLETIN NOTE : This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 , Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain 2 Bolt Item (80) Retain 2 Washer Item (81) Retain 2 Block Clamp Item (82) Retain (b) Remove the two Hydraulic Pipes : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 and Fig. A-FCBAA Sheet 03 Refer to AMM 29-00-00, Page Block 401 1 Hydraulic Pipes Item (78) Retain 1 Hydraulic Pipes Item (79) Retain (6) Subtask 242105-941-401-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 612 Access Panel 612HB 512 Access Panel 512HB 624 Access Panel 624KB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-80-00, Page Block 301 29-10-00, Page Block 301 Structural Repair Manual (SRM) 51-40-21 51-40-40 51-75-10 (a) Fully extend slats, refer to AMM 27-80-00, Page Block 301. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 44 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A310 SERVICE BULLETIN (b) Depressurize the hyd raulic system, refer to AM M 29-10-00, Page Block 301. (c) Make sure the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (d) In the cockpit, place warning notices in position not to operate the slats. (e) Put access platforms in position at zone(s) 512, 612 and 624. (f) Remove panels 612HB, 512HB and 624KB. (7) Subtask 242105-941-201-002 - JOB SET-UP Work Zones and Access Panels Zone Access/Work location 600 500 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 WARNING : PUT WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS. THE MOVEMENT CAN CAUSE INJURY TO PERSONS. (a) The following items 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 systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Install the safety guard (PN 98A27503003000) on the flap and slat control lever. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 45 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A310 SERVICE BULLETIN (c) Put access platforms in position below the leading-edges of: - the LH wing at Zone 512 - the LH wing at Zone 524 - the RH wing at Zone 612 - the RH wing at Zone 624 (d) On the lower surface of the LH wing, remove the leading-edge access panels 512BB, 512CB, 512DB, 512GB and 512JB, refer to AMM 06-41-57, Page Block 001 as necessary. (e) On the lower surface of the LH wing, remove the leading-edge access panels 524BB, 524CB and 524KB, refer to AMM 06-41-57, Page Block 001 as necessary. (f) On the lower surface of the RH wing, remove the leading-edge access panels 612BB, 612CB, 612DB, 612GB, 612JB, refer to AMM 06-41-57, Page Block 001 as necessary. (g) On the lower surface of the RH wing, remove the leading-edge access panels 624BB and 624CB, refer to AMM 06-41-57, Page Block 001 as necessary. **CONF 002 (1) Subtask 242105-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 27-50-00, Page Block 301 29-10-00, Page Block 301 29-14-00, Page Block 301 (a) The following items 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 systems depressurized. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 46 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A310 SERVICE BULLETIN - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (c) Put access platform(s) in position. (d) Depressurize the Yellow Hydraulic System (Refer to AMM 29-10-00, Page Block 301 and AMM 29-14-00, Page Block 301). (e) Do the Job Set-up procedure as specified in the Extension and Retraction of Flaps with Aircraft System (Refer to AMM 27-50-00, Page Block 301). (2) Subtask 242105-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 27-50-00, Page Block 301 32-12-11, Page Block 301 53-15-63, Page Block 401 (a) Open the Main Landing Gear (MLG) door (Refer to AMM 32-12-11, Page Block 301). (b) Fully extend the flaps (Refer to AMM 27-50-00, Page Block 301). (c) Remove the access panels 572AB, 672AB, 572AZ, 572BZ, 572CZ, 572DZ, 572EZ, 572FZ, 572GZ, 672AZ, 672BZ, 672CZ, 672DZ, 672EZ, 672FZ and 672GZ (Refer to AMM 06-41-57, Page Block 001). (d) Remove the access panels 512FB, 612FB, 512BB, 612BB, 612DB, 513RR and 613RR (Refer to AMM 06-41-57, Page Block 001). (e) Remove all the necessary fairing panels (Refer to AMM 53-15-63, Page Block 401). (f) If necessary, remove the access panels 571BB, 571CB, 671BB and 671CB (Refer to AMM 06-41-57, Page Block 001). (g) If necessary, remove the access panels 513BL, 513DL, 513CL, 513EL, 513FL, 513ML, 613BR, 613DR, 613CR, 613ER, 613FR and 613HR (Refer to AMM 06-41-57, Page Block 001). DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 47 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A310 SERVICE BULLETIN (3) Subtask 242105-010-003-001 - Remove the Air Ducts and the Deflector in the LH Wings for access. Work Zones and Access Panels Zone Access/Work location 512 Access Panel 513RR, Panel 513QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE : This workstep is necessary to be done to access the raceway box to accomplish SUBTASK 242105-831-003 001 Modify the routing in the LH forward wing to fuselage fairing. . NOTE : Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE : Retain the hardware. (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 48 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A310 SERVICE BULLETIN NOTE : Retain the hardware. NOTE : Two persons necessary (one on the above and one on the lower side of the panel). (c) Remove the access panel 513QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE : Retain the hardware. (4) Subtask 242105-010-002-001 - Remove the Air Ducts and the Deflector in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 612 Access Panel 613RR, Panel 613QL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-57, Page Block 001 36-11-00, Page Block 401 Fig. A-FCAAA Removal of Air Ducts and Reflector in the Wings for access Sheet 01 Sheet 02 Sheet 03 NOTE : Two persons are necessary for this access. (a) Remove the Air Ducts : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM 36-11-00, Page Block 401 1 Duct Assy Item (70) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (72) Retain 1 Insulation Item (71) Retain 1 Tube Assy Item (73) Retain NOTE : Retain the hardware. DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 49 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A310 SERVICE BULLETIN (b) Remove the Deflector : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 1 Shield Item (75) Retain 1 Bracket Item (74) Retain 1 Shield Assy Item (76) Retain NOTE : Retain the hardware. (c) Remove the access panel 613QL (Refer to AMM 06-41-57, Page Block 001). (d) Remove the cover of the Raceway Box : Refer to Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 03 1 Cover Item (77) Retain NOTE : Retain the hardware. (5) Subtask 242105-010-004-001 - Remove two Hydraulic Pipes in the RH Wings for access. Work Zones and Access Panels Zone Access/Work location 673 Access Panel 672AZ, Panel 672BZ Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-00-00, Page Block 401 Fig. A-FCBAA Removal of Hydraulic Pipes for access Sheet 01 Sheet 02 Sheet 03 Sheet 04 NOTE : This workstep is necessary before accomplishment of SUBTASK 242105-831-006 001 Modify the routing on the RH shroud box leading edge. . (a) Remove the hardware : Refer to Fig. A-FCBAA Sheet 01 , Fig. A-FCBAA Sheet 02 , Fig. A-FCBAA Sheet 03 and Fig. A-FCBAA Sheet 04 1 Tie-Cable Item (62) Discard 1 Block Isolator Item (83) Retain DATE: Mar 20/13 SERVICE BULLETIN No.: A310-24-2105 REVISION No.: 02 - Jan 05/15 Page: 50 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a310-24-2105/file/fc0e7ae37a45.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. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.