# Airbus Service Bulletin A300-53-6181 Copy: Revision 01 ("FAA-2016-5596_A300-53-6181_R1"), 155 pages: PDF https://openairdocs.org/files/sha256/cb/63/cb6395f159b347226151310faf852bc3b615eb9cc499edb35cf402827176eb0c; text https://openairdocs.org/service-documents/airbus/a300-53-6181/file/cb6395f159b3.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596; AD 2016-20-11 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: A300-53-6181 - Latest revision known: A300-53-6181, Revision 01, dated July 2, 2015 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a300-53-6181 ## ADs that cite it (2) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2017-24-09](https://openairdocs.org/ad/2017-24-09.md), effective Jan 5, 2018: Revision 01 - [AD 2016-20-11](https://openairdocs.org/ad/2016-20-11.md), effective Jan 3, 2017: Revision 01 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-53-6181/proposed.md). ## Text (155 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596; AD 2016-20-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63 MODIFICATION No.: 13745D23357 This page transmits Revision No.01 of Service Bulletin No.A300-53-6181 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision 01 issued to change the standard tools to special AIRBUS tools CHANGES SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R PLANNING INFORMATION EFFECTIVITY Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED R MATERIAL INFORMATION TOOLING Tooling - Price and Availability Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL AVAILABILITY UPDATED MATERIAL PRICE UPDATED MATERIAL SET UPDATED R Tools TOOLS UPDATED R Standard tool TOOLD01 TOOL MATERIAL SET DELETED D Standard tool TOOLD02 TOOL MATERIAL SET DELETED D Standard tool TOOLD03 TOOL MATERIAL SET DELETED D Special Tools SPECIAL TOOLS UPDATED R Kit tool 536181T01R00 TOOL MATERIAL SET ADDED N Kit tool 536181T02R01 TOOL MATERIAL SET ADDED N Kit tool 536181T03R00 TOOL MATERIAL SET ADDED N ACCOMPLISHMENT INSTRUCTIONS TASK 536181- 831-848-001-Modification Subtask 536181-420-201-001 SUBTASK SOLUTION UPDATED TOOL UPDATED SPECIAL TOOL UPDATED NOTE UPDATED KEYWORD UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R Subtask 536181-420-201-002 SUBTASK SOLUTION UPDATED TOOL UPDATED SPECIAL TOOL UPDATED NOTE UPDATED KEYWORD UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Jun 26/15 REVISION No. : 01 - Jul 02/15 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13745D23357 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 In the frame of the FAR26 - Widespread Fatigue Damage compliance study and an dedicated in service occurrence, the area of the AFT Cargo-Door Sill-Beam and adjacent structure needs to be reinforced. This Service Bulletin details the reinforcement of the AFT Cargo Door Lock fitting/torsion plates and Sill Beam Flag/Sill Beam Web interfaces. For Configuration 001 the modification is composed of: - Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface. - Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface. For Configuration 002 the modification is composed of: - Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface. - Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface. - Replacement of lock fittings. NOTE : Some aircraft have been repaired prior to the instruction of this modification at single sill DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A300-600 SERVICE BULLETIN SUMMARY beam flag position by Repair and Design Approval Sheets (RDAS). In these case the sill beam flag/sill beam web interface reinforcement as per this modification is not applicable. The repair by RDAS solution is considered sufficient from the structural integrity point of view. The accomplishment of this Service Bulletin will improve the reliability of the lower Cargo-Door Sill Beam Area structure. The accomplishment of this Service Bulletin cancels the Inspection Service Bulletin A300-53-6179. This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery configuration and modified by the reported incorporation of AIRBUS Service Bulletins). Prior to Service Bulletin embodiment, specific attention must be paid to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. It must be verified that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections that apply with respect to the Service Bulletin configuration. AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is not covered by the SRM and for repairs outside of the SRM covered by an RAS issued by AIRBUS, AIRBUS Customer Services Repair Engineering Support (SEOE) should be contacted. Repair review will be done by AIRBUS at conditions of the Customer Services Catalogue. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB YES 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 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 536181D01R00 1 11,500.00 Doublers, Angels, Fasteners Kit tool 536181T01R00 1 12,670.00 Cold Working Capital Tooling Kit tool 536181T02R01 1 2,150.00 Cold Working Durable Tooling Kit tool 536181T03R00 1 70.00 Cold Working Expendable Tooling TOTAL 26,390.00 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A300-600 SERVICE BULLETIN SUMMARY **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 536181D02R00 1 82,000.00 Doublers, Angles, Fittings, Fasteners Kit tool 536181T01R00 1 12,670.00 Cold Working Capital Tooling Kit tool 536181T02R01 1 2,150.00 Cold Working Durable Tooling Kit tool 536181T03R00 1 70.00 Cold Working Expendable Tooling TOTAL 96,890.00 EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 06P 67Q ABR AHK BCS FDX IRA IRM KAC MNB MRJ MSR SUD TAR THA UQA URS UTP UZB CONCURRENT REQUIREMENTS Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin: Service Bulletin No. A300-53-6179 NOTE : Service Bulletin No. A300-53-6179 (FU SELAGE-REAR FUSEL AGE-INSPECTION OF AFT CARGO DOOR LOWER TORSION BOX AREA) REFERENCES / REPERCUSSIONS TFU 53.17.00.006 OEB None AOT A53W005-14 SIL None ISI 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: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A300-600 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 536181-831-848-001: Modification TOTAL MANHOURS 47.00 ELAPSED TIME (HOURS) 27.00 **CONF 002 Task 536181-831-848-001: Modification TOTAL MANHOURS 68.00 ELAPSED TIME (HOURS) 40.00 APPENDICES **CONF ALL APPENDIX 01: GANTT CHART DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A300-600 SERVICE BULLETIN SUMMARY **CONF 001 FR62 FR61 FR60 FR63 FR59A FR60A FR61A FR62A FR63A STGR46RH STGR43RH A FR63A FR59A B B AFT CARGO DOOR REINFORCED TORSION BOX PLATE Z150 A D_SB_536181_6_SAAA_01_00 Figure A-GSAAA - Sheet 01 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A300-600 SERVICE BULLETIN SUMMARY **CONF 002 Z150 A AFR63A FR59A AFT CARGO DOOR FR59A FR60 FR60A FR61 FR61A FR62 FR62A FR63 DOOR SILL BEAM WEB LOCK FITTING LOCK FITTING C B C B FR62 FR61 FR60 FR63 FR59A FR60A FR61A FR62A FR63A STGR46RH STGR43RH REINFORCED TORSION BOX PLATE D_SB_536181_6_SAAB_01_00 Figure A-GSAAB - Sheet 01 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A300-600 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 53 TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63 MODIFICATION No.: 13745D23357 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE : This Service Bulletin is applicable to aircraft with MOD 05438 embodied (A310-A300/600-FUSELAGE SKIN AND FRAME WORK: CARGO DOOR FRAMES AND SILLS-TO CHANGE THE MATERIAL FROM 2024 TO 7075) NOTE : This Service Bulletin is not applicable to aircraft with MOD 12046 embodied (FUSELAGE-REAR FUSELAGE-INTRODUCE ENLARGE REAR LOWER DECK CARGO DOOR). (1) Models B4-603 B4-605R B4-622 B4-622R C4-605R/FF4-605R (2) Effectivity by MSN 0388 0401 0405 0408 0411 0414 0417 0477 0479 0505 0521 0525 0529-0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563 0572 0575 0579 0581 0584 0602-0603 0607-0608 0611 0613 0617-0618 0621 0623 0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766 0768-0775 0777-0794 0797 0799-0804 0836-0838 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 1 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A300-600 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 06P 0788 67Q 0584 0603 0744 0749 0764 ABR 0677 AHK 0683 0770 BCS 0529 0557 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730 0737 0740 0743 0753 0783 0797 0836 0837 FDX 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 IRA 0632 0696 0723 0727 IRM 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0773 0838 KAC 0673 0694 0699 0719 0721 MNB 0521 0525 0532 0734 0739 0755 0756 0758 MRJ 0750 0762 MSR 0561 0607 SUD 0666 0775 TAR 0505 0558 0563 THA 0629 0782 0784 0785 0786 0787 UQA 0626 0643 URS 0733 UTP 0707 0725 0732 0741 0746 0754 0763 UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0388 0401 0405 0408 0411 0414 0417 0477 0479 0505 0521 0525 0529 0530 0532 0536 0543 0546 0553 0555 0557 0558 0559 0561 0563 0572 0575 0579 0581 0584 0602 0603 0607 0608 0611 0613 0617 0618 0621 0623 0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0673 0677 0679 0683 0688 0694 0696 0699 0701 0703 0707 0709 0711 0713 0715 0717 0719 001 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 2 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A300-600 SERVICE BULLETIN MSN CONFIGURATION 0721 0722 0723 0724 0725 0726 0727 0728 0729 0730 0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745 0746 0748 0749 0750 0752 0753 0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764 0766 0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788 0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802 0803 0804 0836 0837 0838 002 (5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft which have not Mod 10319 D20472 embodied. **CONF 002 Config. 002 is valid for all the aircraft which have Mod 10319 D20472 embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 536181D01R00 1 Consumable CMLD01 1 Kit tool 536181T01R00 1 Kit tool 536181T02R01 1 Kit tool 536181T03R00 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 536181D02R00 1 Consumable CMLD01 1 Kit tool 536181T01R00 1 Kit tool 536181T02R01 1 Kit tool 536181T03R00 1 **CONF ALL B. CONCURRENT REQUIREMENTS Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin: Service Bulletin No. A300-53-6179 NOTE : Service Bulletin No. A300-53-6179 (FUSELAGE-REAR FUSELAGE- INSPECTION OF AFT CARGO DOOR LOWER TORSION BOX AREA) DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 3 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A300-600 SERVICE BULLETIN C. REASON (1) History In the frame of the FAR26 - Widespread Fatigue Damage compliance study and an dedicated in service occurrence, the area of the AFT Cargo-Door Sill-Beam and adjacent structure needs to be reinforced. (2) Objective/Action This Service Bulletin details the reinforcement of the AFT Cargo Door Lock fitting/torsion plates and Sill Beam Flag/Sill Beam Web interfaces. For Configuration 001 the modification is composed of: - Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface. - Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface. For Configuration 002 the modification is composed of: - Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface. - Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface. - Replacement of lock fittings. NOTE : Some aircraft have been repaired prior to the instruction of this modification at single sill beam flag position by Repair and Design Approval Sheets (RDAS). In these case the sill beam flag/sill beam web interface reinforcement as per this modification is not applicable. The repair by RDAS solution is considered sufficient from the structural integrity point of view. (3) Advantages The accomplishment of this Service Bulletin will improve the reliability of the lower Cargo-Door Sill Beam Area structure. The accomplishment of this Service Bulletin cancels the Inspection Service Bulletin A300-53-6179. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 4 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A300-600 SERVICE BULLETIN (4) Operational/Maintenance Consequences This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery configuration and modified by the reported incorporation of AIRBUS Service Bulletins). Prior to Service Bulletin embodiment, specific attention must be paid to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. It must be verified that all allowable damage limits and repairs performed (both in accordance with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections that apply with respect to the Service Bulletin configuration. AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is not covered by the SRM and for repairs outside of the SRM covered by an RAS issued by AIRBUS, AIRBUS Customer Services Repair Engineering Support (SEOE) should be contacted. Repair review will be done by AIRBUS at conditions of the Customer Services Catalogue. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 536181-831-848-001: Modification (1) Install the Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo Floor Supports (2) Apply the Surface Protection to the Installation Area **CONF 002 Task 536181-831-848-001: Modification (1) Remove the Eccentric Bolts from the Lock Fittings of the AFT Cargo Compartment Door Frame (2) Install the new Lock Fittings, Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo Floor Supports (3) Apply the Surface Protection to the Installation Area (4) Install the Eccentric Bolts in the Lock Fittings of the AFT Cargo Compartment Door Frame **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 5 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A300-600 SERVICE BULLETIN (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the given thresholds of 19600FC and the grace periods shown in the table 1 below for aircraft which have missed the Structure Modification Point (SMP), but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 1 APPLIED INSPECTION METHODS in accordance with ISB A300-53-6179 or AOT A53W005-14 GRACE PERIODS to implement the MSB A300-53-6181 High Frequency Eddy Current (HFEC) Latest 2300FC after the last HFEC inspection performed before release of the MSB A300-53-6181 or 12 months after release of the MSB A300-53-6181, whichever comes later. Detailed Visual Inspection (DET) Latest 2300FC after the last DET inspection performed before release of the MSB A300-53-6181 or 12 months after release of the MSB A300-53-6181, whichever comes later. Ultrasonic (US) Latest 12 months after release of the MSB A300-53-6181 F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. **CONF 001 Task 536181-831-848-001: Modification Get Access 2.00 On Aircraft Install the Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo Floor Supports 40.00 Apply the Surface Protection to the Installation Area 3.00 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 6 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A300-600 SERVICE BULLETIN Task 536181-831-848-001: Modification Close-Up 2.00 TOTAL MANHOURS 47.00 ELAPSED TIME (HOURS) 27.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart,Fig. A-GAAAA given in Appendix 01. **CONF 002 Task 536181-831-848-001: Modification Get Access 2.00 On Aircraft Remove the Eccentric Bolts from the Lock Fittings of the AFT Cargo Compartment Door Frame 2.00 Install the new Lock Fittings, Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo Floor Supports 56.00 Apply the Surface Protection to the Installation Area 3.00 Install the Eccentric Bolts in the Lock Fittings of the AFT Cargo Compartment Door Frame 2.00 Tests 1.00 Close-Up 2.00 TOTAL MANHOURS 68.00 ELAPSED TIME (HOURS) 40.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart,Fig. A-GAAAB given in Appendix 01. **CONF ALL H. WEIGHT AND BALANCE **CONF 001 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight 0.756 KG (+1.6666 LB) Effect on Balance 30.756 KGM (+222.458 LB.FT ) **CONF 002 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight 0.116 KG (+0.2557 LB) Effect on Balance 4.730 KGM (+34.212 LB.FT ) DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 7 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A300-600 SERVICE BULLETIN **CONF ALL I. ELECTRICAL LOAD DATA Not Applicable J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-21-12 24-00-00 25-50-21 25-52-22 25-52-26 25-55-10 52-30-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 In Service Information (ISI) ISI 51.48.00001 Non Destructive Test Manual (NTM) 51-10-01 53-17-33 Standards Manual (SM) Structural Repair Manual (SRM) 51-10-00 51-23-20 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-41 51-40-44 51-40-50 51-75-10 51-76-10 53-17-18 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-21-12 24-00-00 25-50-21 25-52-22 25-52-26 25-55-10 52-30-00 52-30-31 52-32-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 In Service Information (ISI) ISI 51.48.00001 Non Destructive Test Manual (NTM) 51-10-01 53-17-33 Standards Manual (SM) Structural Repair Manual (SRM) 51-10-00 51-23-20 51-24-00 51-40-20 51-40-21 51-40-30 51-40-40 51-40-41 51-40-44 51-40-50 51-75-10 51-76-10 53-17-18 **CONF ALL K. PUBLICATION AFFECTED Maintenance Planning Document (MPD) 531725-01-2 Structural Repair Manual (SRM) 53-17-18 L. INTERCHANGEABILITY/MIXABILITY Not Applicable DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 8 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A300-600 SERVICE BULLETIN M. SPARES Fitting Assy-Lock A5397823600200 Fitting Assy-Lock A5397823700200 Fitting Assy-Lock A5397823800200 Fitting Assy-Lock A5397823900200 Fitting Assy-Lock A5397824000200 Fitting Assy-Lock A5397824100200 Fitting Assy-Lock A5397824200200 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 9 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A300-600 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 10 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A300-600 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. 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 536181D01R00 Kit 536181D02R00 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 2590 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability Kit 536181D01R00 Cost 11,500.00 USD Availability 120 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 536181D02R00 Cost 82,000.00 USD Availability 220 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 not provide industry support for accomplishment of this Service Bulletin. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 11 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A300-600 SERVICE BULLETIN For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France T e l:( 3 3 )56 71 90 62 2 E-mail : monitored.retrofit@airbus.com F a x:( 3 3 )56 19 32 74 5 C. LIST OF COMPONENTS Kit 536181D01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 1 A5398104820000 1 ANGLE 2 A5398104820100 1 ANGLE 3 A5398104821600 3 DOUBLER 4 A5398104821400 3 DOUBLER 5 A5398104822000 2 DOUBLER 6 A5398104821800 2 DOUBLER 7 A5398104820200 1 ANGLE 8 A5398104820300 1 ANGLE 9 A5398104820400 1 ANGLE 10 A5398104820500 1 ANGLE 11 A5398104820600 1 ANGLE 12 A5398104820700 1 ANGLE 13 A5398104820800 1 ANGLE 14 A5398104820900 1 ANGLE 15 A5398104822400 1 DOUBLER 16 A5398104822200 1 DOUBLER 17 A5398104821000 1 ANGLE 18 A5398104821100 1 ANGLE 19 A5398104822800 1 DOUBLER 20 A5398104822600 1 DOUBLER 21 A5398104821200 1 ANGLE 22 A5398104821300 1 ANGLE 23 DAN5-6-6X 14 PIN 24 DAN5-6-7X 12 PIN 25 DAN5-6-4 12 PIN 26 DAN5-6-6 51 PIN 27 DAN5-6-7 8 PIN 28 DAN7-6-9 28 PIN 29 DAN12-6X 26 COLLAR 30 DAN12-6 28 COLLAR 31 EN6115K3-5 14 BOLT 32 NSA5075-6 71 COLLAR DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 12 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A300-600 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 33 ASNA2528-3 14 NUT NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 536181D02R00 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 1 A5398104820000 1 ANGLE 2 A5398104820100 1 ANGLE 3 A5398104821600 3 DOUBLER 4 A5398104821400 3 DOUBLER 5 A5398104822000 2 DOUBLER 6 A5398104821800 2 DOUBLER 7 A5398104820200 1 ANGLE 8 A5398104820300 1 ANGLE 9 A5398104820400 1 ANGLE 10 A5398104820500 1 ANGLE 11 A5398104820600 1 ANGLE 12 A5398104820700 1 ANGLE 13 A5398104820800 1 ANGLE 14 A5398104820900 1 ANGLE 15 A5398104822400 1 DOUBLER 16 A5398104822200 1 DOUBLER 17 A5398104821000 1 ANGLE 18 A5398104821100 1 ANGLE 19 A5398104822800 1 DOUBLER 20 A5398104822600 1 DOUBLER 21 A5398104821200 1 ANGLE 22 A5398104821300 1 ANGLE 23 DAN5-6-6X 14 PIN 24 DAN5-6-7X 12 PIN 25 DAN5-6-4 12 PIN 26 DAN5-6-6 51 PIN 27 DAN5-6-7 8 PIN 28 DAN7-6-9 28 PIN 29 DAN12-6X 120 COLLAR 30 DAN12-6 84 COLLAR 31 EN6115K3-5 14 BOLT 32 NSA5075-6 88 COLLAR 33 ASNA2528-3 14 NUT 34 DAN12-8X 28 COLLAR 35 DAN8-6-7X 66 PIN 36 DAN5-6-3 17 PIN DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 13 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A300-600 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 37 DAN8-6-7 2 PIN 38 DAN8-6-8X 28 PIN 39 DAN8-8-13X 28 PIN 40 DAN7-6-7 54 PIN 41 A5397823600295 1 FITTING 42 A5397823700295 1 FITTING 43 A5397823800295 1 FITTING 44 A5397823900295 1 FITTING 45 A5397824000295 1 FITTING 46 A5397824100295 1 FITTING 47 A5397824200295 1 FITTING 48 A5397821320000 7 SHIM 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 CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Wash Primer-Structure 04CMA2 As required Primer Polyurethane Paint- Corrosion Inhibiting 04EAC2 As required Top Coat Polyurethane-External Structure 04JAA3 As required Top Coat Polyurethane-Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Interfay 06AAC1 As required Adhesion Promoter-For Polysulfide Sealant 06PAG1 As required Non Aqueous Cleaner-General 08BAA9 As required Corrosion Preventive Compound- Water Displacing 12ABC1 As required Corrosion Preventive Compound- Heavy Duty Soft Fil 12ACC1 As required (1) Textile-Lint Free Cotton 14SBA1 As required NOTE (1) : For Material No. 12ACC1 you can use Material No. 12ADB1 as an alternative. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 14 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A300-600 SERVICE BULLETIN (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Operators interested in obtaining the Cold Working Tool Kits should contact: Kit tool 536181T01R00 Kit tool 536181T02R01 Kit tool 536181T03R00 AIRBUS Material, Logistics and Suppliers IFD - In Flight Desk 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 (b) Price and Availability Kit tool 536181T01R00 Cost 12,670.00 USD Availability 85 calendar days from receipt of order Procurement to be negotiated directly with AIRBUS. Kit tool 536181T02R01 Cost 2,150.00 USD Availability 100 calendar days from receipt of order Procurement to be negotiated directly with AIRBUS. Kit tool 536181T03R00 Cost 70.00 USD Availability 50 calendar days from receipt of order Procurement to be negotiated directly with AIRBUS. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 15 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A300-600 SERVICE BULLETIN (2) Tools None (3) Special Tools AIRBUS has allocated the following tool numbers for cold expansion: For the definition of capital, durable and expendable tools refer to ISI 51.48.00001. NOTE : The listed tools can be ordered as complete kits or as single parts to the customer needs. Kit tool 536181T01R00 ITEM PART N˚ KEYWORD QTY SEE NOTES FT20 POWERPAK 1 FTBXA9 BOX 1 LB20 PULLUNIT 1 LBRA7 PULLADAP 1 NOTE : Capital tooling: Kit Tool 536181T01R00 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from AIRBUS. If the right angle adapter extension is not available in the operators stock, it can be ordered separately. Kit tool 536181T02R01 ITEM PART N˚ KEYWORD QTY SEE NOTES CBCE73-044F CAP 1 CBG4-4N1 COMBIGAG 1 CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE 1 CBR4-4NRA1860 SLEEVE 1 CBSD4-4NRA SLEEVE 1 CBSR4-4NRA SLEEVE 1 FTBXC1 BOX 1 NOTE : Durable tooling: Kit Tool 536181T02R01 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to ISI 51.48.00001. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 16 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A300-600 SERVICE BULLETIN Kit tool 536181T03R00 ITEM PART N˚ KEYWORD QTY SEE NOTES CBS4-4N8F SLEEVE 14 NOTE : Expendable tooling: Kit Tool 536181T03R00 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 17 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A300-600 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 18 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A300-600 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 536181-831-848-001 - Modification WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : WHEN YOU OPEN AND CLOSE THE CARGO DOORS, MAKE SURE THAT THE ACCESS PLATFORM IS AT THE CORRECT HEIGHT. IF IT IS TOO HIGH, IT WILL PREVENT FREE MOVEMENT OF THE DOORS. CAUTION : MAKE SURE THAT THE AUTOMATIC ANTI-ROLL-OUT LATCHES ARE IN THE FULLY UP POSITION BEFORE YOU CLOSE THE CARGO DOOR(S). IF THEY ARE NOT, DAMAGE TO THE DOOR(S) CAN OCCUR. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF 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 a procedure accepted by the local procedure he belongs to, the accepted alternative procedure can be used. When the words ’in accordance with’ are used the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 19 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A300-600 SERVICE BULLETIN 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. Task Associated Data **CONF 001 Zone 153 Access Door 812 Manpower TOTAL MANHOURS 47.00 ELAPSED TIME (HOURS) 27.00 **CONF 002 Zone 153 Access Door 812 Manpower TOTAL MANHOURS 68.00 ELAPSED TIME (HOURS) 40.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 536181-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-20 51-40-30 51-40-40 51-75-10 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 20 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A300-600 SERVICE BULLETIN (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) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-40-20. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with SRM 51-75-10. (h) Obtain fastener hole diameter and drill data in accordance with SRM 51-40-40. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (j) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’ column. (k) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (l) Do the eddy current rotating probe inspection in accordance NTM 51-10-01. (m) Refer to the AIRBUS Standards Manual (SM) if you find numbers for the hardware components which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relation. (n) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 536181-839-201-001 - 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 536181-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 21 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A300-600 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) Non Destructive Test Manual (NTM) 51-10-01 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-20 51-40-30 51-40-40 51-75-10 (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) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-40-20. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with SRM 51-75-10. (h) Obtain fastener hole diameter and drill data in accordance with SRM 51-40-40. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (j) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’ column. (k) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (l) Do the eddy current rotating probe inspection in accordance NTM 51-10-01. (m) Refer to the AIRBUS Standards Manual (SM) if you find numbers for the hardware components which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin. The SM will give you the correct part number to part number relation. (n) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 22 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A300-600 SERVICE BULLETIN (2) Subtask 536181-839-201-001 - 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 536181-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 25-50-21, Page Block 401 25-52-22, Page Block 401 25-52-26, Page Block 401 25-55-10, Page Block 201 52-30-00, Page Block 001 52-30-00, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 23 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A300-600 SERVICE BULLETIN (b) Open the Aft Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001. (c) Put an access platform in position at the AFT cargo Compartment Door. (d) Install the door actuator lock on the AFT Cargo Compartment Door actuator, refer to AMM 52-30-00, Page Block 001 and refer to AMM 52-30-00, Page Block 301. (e) Remove the linings 154CR, 154BR and 154AR of the AFT Cargo Compartment Door frame, refer to AMM 25-55-10, Page Block 201. (f) Remove the Ball Mats in the entrance area of the AFT Cargo Compartment, refer to AMM 25-52-22, Page Block 401. (g) Remove the insulation mats in the entrance area of the AFT Cargo Compartment, refer to AMM 25-50-21, Page Block 401. **CONF 002 (1) Subtask 536181-941-201-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 25-50-21, Page Block 401 25-52-22, Page Block 401 25-52-26, Page Block 401 25-55-10, Page Block 201 52-30-00, Page Block 001 52-30-00, Page Block 301 NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 24 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A300-600 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (b) Open the Aft Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001. (c) Put an access platform in position at the AFT cargo Compartment Door. (d) Install the door actuator lock on the AFT Cargo Compartment Door actuator, refer to AMM 52-30-00, Page Block 001 and refer to AMM 52-30-00, Page Block 301. (e) Remove the linings 154CR, 154BR and 154AR of the AFT Cargo Compartment Door frame, refer to AMM 25-55-10, Page Block 201. (f) Remove the Ball Mats in the entrance area of the AFT Cargo Compartment, refer to AMM 25-52-22, Page Block 401. (g) Remove the insulation mats in the entrance area of the AFT Cargo Compartment, refer to AMM 25-50-21, Page Block 401. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 536181-420-201-001 - Ins tall the Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo Floor Supports Work Zones and Access Panels Zone Access/Work location 153 Access Door 812 Work location from Frame 60 to Frame 63 Stringer 45RH Manpower Resources Manhours 40.00 Minimum number of person 2 Subtask elapsed time 20.00 Skills AIRFRAME Material necessary to do the job Kit 536181D01R00 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 1 A5398104820000 1 ANGLE 2 A5398104820100 1 ANGLE 3 A5398104821600 3 DOUBLER 4 A5398104821400 3 DOUBLER 5 A5398104822000 2 DOUBLER 6 A5398104821800 2 DOUBLER DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 25 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A300-600 SERVICE BULLETIN ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 7 A5398104820200 1 ANGLE 8 A5398104820300 1 ANGLE 9 A5398104820400 1 ANGLE 10 A5398104820500 1 ANGLE 11 A5398104820600 1 ANGLE 12 A5398104820700 1 ANGLE 13 A5398104820800 1 ANGLE 14 A5398104820900 1 ANGLE 15 A5398104822400 1 DOUBLER 16 A5398104822200 1 DOUBLER 17 A5398104821000 1 ANGLE 18 A5398104821100 1 ANGLE 19 A5398104822800 1 DOUBLER 20 A5398104822600 1 DOUBLER 21 A5398104821200 1 ANGLE 22 A5398104821300 1 ANGLE 23 DAN5-6-6X 14 PIN 24 DAN5-6-7X 12 PIN 25 DAN5-6-4 12 PIN 26 DAN5-6-6 51 PIN 27 DAN5-6-7 8 PIN 28 DAN7-6-9 28 PIN 29 DAN12-6X 26 COLLAR 30 DAN12-6 28 COLLAR 31 EN6115K3-5 14 BOLT 32 NSA5075-6 71 COLLAR 33 ASNA2528-3 14 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-General Purpose Interfay 06AAC1 As required Non Aqueous Cleaner- General 08BAA9 As required Textile-Lint Free Cotton 14SBA1 As required Kit tool 536181T01R00 ITEM PART N˚ KEYWORD QTY SEE NOTES FT20 POWERPAK 1 FTBXA9 BOX 1 LB20 PULLUNIT 1 LBRA7 PULLADAP 1 NOTE : Capital tooling: Kit Tool 536181T01R00 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 26 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A300-600 SERVICE BULLETIN The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operators’ stock as a long- term investment or can be loaned from AIRBUS. If the right angle adapter extension is not available in the operators stock, it can be ordered separately. Kit tool 536181T02R01 ITEM PART N˚ KEYWORD QTY SEE NOTES CBCE73-044F CAP 1 CBG4-4N1 COMBIGAG 1 CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE 1 CBR4-4NRA1860 SLEEVE 1 CBSD4-4NRA SLEEVE 1 CBSR4-4NRA SLEEVE 1 FTBXC1 BOX 1 NOTE : Durable tooling: Kit Tool 536181T02R01 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to ISI 51.48.00001. Kit tool 536181T03R00 ITEM PART N˚ KEYWORD QTY SEE NOTES CBS4-4N8F SLEEVE 14 NOTE : Expendable tooling: Kit Tool 536181T03R00 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. References Non Destructive Test Manual (NTM) 51-10-01 53-17-33 Structural Repair Manual (SRM) 51-10-00 51-24-00 51-40-21 51-40-40 51-40-41 51-40-44 51-40-50 53-17-18 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 27 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A300-600 SERVICE BULLETIN References Fig. A-GBAAA Reinforcement of the Lower AFT Cargo Door Frame Structure Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Sheet 06 Sheet 07 Sheet 08 Sheet 09 Sheet 10 Sheet 11 Sheet 12 Sheet 13 Sheet 14 (a) Clean the installation area with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required (b) Check the affected aircraft struct ure for cracks, other damages and applied repairs in accordance with SRM 51-10-00, in accordance with SRM 53-17-18 and in accordance with NTM 53-17-33. NOTE : Some aircraft have been repaired prior to the instruction of this modification at single sill beam flag position by Repair and Design Approval Sheets (RDAS). In these case the sill beam flag/sill beam web interface reinforcement as per this modification is not applicable. The repair by RDAS solution is considered sufficient from the structural integrity point of view. (c) Install the reinforcement doublers and angles to the sill beam and main frames/cargo door support at FR60 as shown on Fig. A-GBAAA Sheet 01 , Fig. A- GBAAA Sheet 02 , Fig. A-GBAAA Sheet 05 , Fig. A-GBAAA Sheet 07 and Fig. A- GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 7 Collar DAN12-5 Item (10) Discard 3 Pin-Rivet DAN7-5A4 Item (16) Discard 4 Rivet NSA5411-40-000 Item (17) Discard DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 28 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A300-600 SERVICE BULLETIN 9 Rivet LN9198-4000CF Item (18) Discard 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 3 and item 4 and the angles, item 1 and item 2 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 07 . 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 3 and item 4. 6 Transfer drill the existing fastener holes with a drill bush to diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to the reinforcement angles, item 1 and item 2. 7 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 . 8 Remove the reinforcement doublers, item 3 and item 4. 9 Deburr the two fastener holes for cold working. 10 Remove the drill chippings from the installation area. 11 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 29 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A300-600 SERVICE BULLETIN 12 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41. Use tool list No. FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 30 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A300-600 SERVICE BULLETIN with FT20 POWERPAK 1 LB20 PULLER UNIT 1 LBRA7 PULLER - 90 DEG ADAPTER 1 and FTBXC1 BOX 1 with CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE - MANDREL, WEAR 1 CBCE73-044F CAP - NOSE 1 f Remove the sleeves. g Ream the holes to the final diameter between 4.723mm (0.186in) and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on Fig. A-GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 . Use tool list No. FTBXC1 BOX 1 with CBG4-4N1 GAGE - COMBINATION 1 CBR4-4NRA1860 GAGE - FINISH REAMER 1 NOTE : Holes shall be free of damage, spiral ridges, cuts and reamer removal markings. A last reaming pass will be 0.2 mm as maximum. NOTE : It is permissible for a post reamed hole to exhibit a region at hole entry, exit or interface that does not clean up (partial ridge remains in hole). A hole in this condition is considered to be acceptable providing the total length of the ridge does not exceed 0.5 mm (0.197 in). 13 Install the reinforcement doublers, item 3 and item 4 as shown on Fig. A- GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 . 14 Drill all the fastener holes to the final diameter in accordance with SRM 51-40-44. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 31 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A300-600 SERVICE BULLETIN 15 Remove the reinforcement doublers, item 3 and item 4 and the angles, item 1 and item 2. 16 Deburr the fastener holes. 17 Clean the installation area and the reinforcement doublers, item 3 and item 4 and the angles, item 1 and item 2 with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 18 Apply to the faying surfaces of the structure parts in accordance with SRM 51-24-00. Polysulfide Sealant- General Purpose Interfay 06AAC1 As required 19 Install to the sill beam and main frames/cargo door supports at FR60 as shown on Fig. A-GBAAA Sheet 07 and Fig. A-GBAAA Sheet 14 and in accordance with SRM 51-40-21: 1 Angle A5398104820000 Item 1 1 Angle A5398104820100 Item 2 1 Doubler A5398104821600 Item 3 1 Doubler A5398104821400 Item 4 with 3 Pin DAN5-6-4 Item 25 6 Pin DAN5-6-6 Item 26 2 Pin DAN5-6-7 Item 27 11 Collar NSA5075-6 Item 32 3 Pin DAN5-6-7X Item 24 2 Pin DAN5-6-6X Item 23 5 Collar DAN12-6X Item 29 2 Bolt EN6115K3-5 Item 31 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 32 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A300-600 SERVICE BULLETIN 2 Nut ASNA2528-3 Item 33 4 Pin DAN7-6-9 Item 28 4 Collar DAN12-6 Item 30 20 Remove unwanted sealant from the installation area. (d) Install the reinforcement doublers and angles to the sill beam and main frames/cargo door supports at FR60A as shown on Fig. A-GBAAA Sheet 01 , Fig. A-GBAAA Sheet 02 , Fig. A-GBAAA Sheet 06 , Fig. A-GBAAA Sheet 08 and Fig. A- GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 4 Collar DAN12-5 Item (10) Discard 7 Rivet NSA5411-40-000 Item (17) Discard 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 5 and item 6 and the angles, item 7 and item 8 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 08 . 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the reinforcement doublers, item 5 and item 6 to the main frames/cargo door supports. 6 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 5 and item 6. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 33 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A300-600 SERVICE BULLETIN 7 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to reinforcement angles, item 7 and item 8. 8 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 9 Remove the reinforcement doublers, item 5 and item 6. 10 Deburr the two fastener holes for cold working. 11 Remove the drill chippings from the installation area. 12 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 13 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41. Use tool list No. FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 34 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A300-600 SERVICE BULLETIN d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 with FT20 POWERPAK 1 LB20 PULLER UNIT 1 LBRA7 PULLER - 90 DEG ADAPTER 1 and FTBXC1 BOX 1 with CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE - MANDREL, WEAR 1 CBCE73-044F CAP - NOSE 1 f Remove the sleeves. g Ream the holes to the final diameter between 4.723mm (0.186in) and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on Fig. A-GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 . Use tool list No. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 35 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A300-600 SERVICE BULLETIN FTBXC1 BOX 1 with CBG4-4N1 GAGE - COMBINATION 1 CBR4-4NRA1860 GAGE - FINISH REAMER 1 NOTE : Holes shall be free of damage, spiral ridges, cuts and reamer removal markings. A last reaming pass will be 0.2 mm as maximum. NOTE : It is permissible for a post reamed hole to exhibit a region at hole entry, exit or interface that does not clean up (partial ridge remains in hole). A hole in this condition is considered to be acceptable providing the total length of the ridge does not exceed 0.5 mm (0.197 in). 14 Install the reinforcement doublers, item 5 and item 6 as shown on Fig. A- GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 . 15 Drill all the fastener holes to the final diameter in accordance with SRM 51-40-44. 16 Remove the reinforcement doublers, item 5 and item 6 and the angles, item 7 and item 8. 17 Deburr the fastener holes. 18 Clean the installation area and the reinforcement doublers, item 5 and item 6 and the angles, item 7 and item 8 with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 19 Apply to the faying surfaces of the structure parts in accordance with SRM 51-24-00. Polysulfide Sealant- General Purpose Interfay 06AAC1 As required 20 Install to the sill beam and main frames/cargo door supports at FR60A as shown on Fig. A-GBAAA Sheet 08 and Fig. A-GBAAA Sheet 14 and in accordance with SRM 51-40-21: 1 Angle A5398104820200 Item 7 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 36 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A300-600 SERVICE BULLETIN 1 Angle A5398104820300 Item 8 1 Doubler A5398104822000 Item 5 1 Doubler A5398104821800 Item 6 with 9 Pin DAN5-6-6 Item 26 9 Collar NSA5075-6 Item 32 2 Bolt EN6115K3-5 Item 31 2 Nut ASNA2528-3 Item 33 2 Pin DAN5-6-6X Item 23 2 Collar DAN12-6X Item 29 4 Pin DAN7-6-9 Item 28 4 Collar DAN12-6 Item 30 21 Remove unwanted sealant from the installation area. (e) Install the reinforcement doublers and angles to the sill beam and main frames/cargo door supports at FR61 as shown on Fig. A-GBAAA Sheet 01 , Fig. A- GBAAA Sheet 03 , Fig. A-GBAAA Sheet 05 , Fig. A-GBAAA Sheet 09 and Fig. A- GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 7 Collar DAN12-5 Item (10) Discard 3 Pin-Rivet DAN7-5A4 Item (16) Discard 4 Rivet NSA5411-40-000 Item (17) Discard 9 Rivet LN9198-4000CF Item (18) Discard 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 37 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A300-600 SERVICE BULLETIN 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 3 and item 4 and the angles, item 9 and item 10 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 09 . 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 3 and item 4. 6 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to the reinforcement angles, item 9 and item 10. 7 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 . 8 Remove the reinforcement doublers, item 3 and item 4. 9 Deburr the two fastener holes for cold working. 10 Remove the drill chippings from the installation area. 11 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 12 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41 Use tool list No. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 38 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A300-600 SERVICE BULLETIN FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 with FT20 POWERPAK 1 LB20 PULLER UNIT 1 LBRA7 PULLER - 90 DEG ADAPTER 1 and DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 39 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A300-600 SERVICE BULLETIN FTBXC1 BOX 1 with CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE - MANDREL, WEAR 1 CBCE73-044F CAP - NOSE 1 f Remove the sleeves. g Ream the holes to the final diameter between 4.723mm (0.186in) and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on Fig. A-GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 . Use tool list No. FTBXC1 BOX 1 with CBG4-4N1 GAGE - COMBINATION 1 CBR4-4NRA1860 GAGE - FINISH REAMER 1 NOTE : Holes shall be free of damage, spiral ridges, cuts and reamer removal markings. A last reaming pass will be 0.2 mm as maximum. NOTE : It is permissible for a post reamed hole to exhibit a region at hole entry, exit or interface that does not clean up (partial ridge remains in hole). A hole in this condition is considered to be acceptable providing the total length of the ridge does not exceed 0.5 mm (0.197 in). 13 Install the reinforcement doublers, item 3 and item 4 as shown on Fig. A- GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 . 14 Drill all the fastener holes to the final diameter in accordance with SRM 51-40-44. 15 Remove the reinforcement doublers, item 3 and item 4 and the angles, item 9 and item 10. 16 Deburr the fastener holes. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 40 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A300-600 SERVICE BULLETIN 17 Clean the installation area and the reinforcement doublers, item 3 and item 4 and the angles, item 9 and item 10 with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 18 Apply to the faying surfaces of the structure parts in accordance with SRM 51-24-00. Polysulfide Sealant- General Purpose Interfay 06AAC1 As required 19 Install to the sill beam and main frames/cargo door supports at FR61 as shown on Fig. A-GBAAA Sheet 09 and Fig. A-GBAAA Sheet 14 and in accordance with SRM 51-40-21: 1 Angle A5398104820400 Item 9 1 Angle A5398104820500 Item 10 1 Doubler A5398104821600 Item 3 1 Doubler A5398104821400 Item 4 with 3 Pin DAN5-6-4 Item 25 6 Pin DAN5-6-6 Item 26 2 Pin DAN5-6-7 Item 27 11 Collar NSA5075-6 Item 32 3 Pin DAN5-6-7X Item 24 2 Pin DAN5-6-6X Item 23 5 Collar DAN12-6X Item 29 2 Bolt EN6115K3-5 Item 31 2 Nut ASNA2528-3 Item 33 4 Pin DAN7-6-9 Item 28 4 Collar DAN12-6 Item 30 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 41 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A300-600 SERVICE BULLETIN 20 Remove unwanted sealant from the installation area. (f) Install the reinforcement doublers and angles to the sill beam and main frames/cargo door supports at FR61A as shown on Fig. A-GBAAA Sheet 01 , Fig. A-GBAAA Sheet 03 , Fig. A-GBAAA Sheet 06 , Fig. A-GBAAA Sheet 10 and Fig. A- GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 4 Collar DAN12-5 Item (10) Discard 7 Rivet NSA5411-40-000 Item (17) Discard 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 5 and item 6 and the angles, item 11 and item 12 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 10 . 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the reinforcement doublers, item 5 and item 6 to the main frames/cargo door supports. 6 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 5 and item 6. 7 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to the reinforcement angles, item 11 and item 12. 8 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 . DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 42 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A300-600 SERVICE BULLETIN 9 Remove the reinforcement doublers, item 5 and item 6. 10 Deburr the two fastener holes for cold working. 11 Remove the drill chippings from the installation area. 12 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 13 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41. Use tool list No. FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 43 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A300-600 SERVICE BULLETIN NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 with FT20 POWERPAK 1 LB20 PULLER UNIT 1 LBRA7 PULLER - 90 DEG ADAPTER 1 and FTBXC1 BOX 1 with CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE - MANDREL, WEAR 1 CBCE73-044F CAP - NOSE 1 f Remove the sleeves. g Ream the holes to the final diameter between 4.723mm (0.186in) and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on Fig. A-GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 . Use tool list No. FTBXC1 BOX 1 with CBG4-4N1 GAGE - COMBINATION 1 CBR4-4NRA1860 GAGE - FINISH REAMER 1 NOTE : Holes shall be free of damage, spiral ridges, cuts and DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 44 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A300-600 SERVICE BULLETIN reamer removal markings. A last reaming pass will be 0.2 mm as maximum. NOTE : It is permissible for a post reamed hole to exhibit a region at hole entry, exit or interface that does not clean up (partial ridge remains in hole). A hole in this condition is considered to be acceptable providing the total length of the ridge does not exceed 0.5 mm (0.197 in). 14 Install the reinforcement doublers, item 5 and item 6 as shown on Fig. A- GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 . 15 Drill all the fastener holes to the final diameter in accordance with SRM 51-40-44. 16 Remove the reinforcement doublers, item 5 and item 6 and the angles, item 11 and item 12. 17 Deburr the fastener holes. 18 Clean the installation area and the reinforcement doublers, item 5 and item 6 and the angles, item 11 and item 12 with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 19 Apply to the faying surfaces of the structure parts in accordance with SRM 51-24-00. Polysulfide Sealant- General Purpose Interfay 06AAC1 As required 20 Install to the sill beam and main frames/cargo door supports at FR61A as shown on Fig. A-GBAAA Sheet 10 and Fig. A-GBAAA Sheet 14 and in accordance with SRM 51-40-21: 1 Angle A5398104820600 Item 11 1 Angle A5398104820700 Item 12 1 Doubler A5398104822000 Item 5 1 Doubler A5398104821800 Item 6 with 9 Pin DAN5-6-6 Item 26 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 45 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A300-600 SERVICE BULLETIN 9 Collar NSA5075-6 Item 32 2 Bolt EN6115K3-5 Item 31 2 Nut ASNA2528-3 Item 33 2 Pin DAN5-6-6X Item 23 2 Collar DAN12-6X Item 29 4 Pin DAN7-6-9 Item 28 4 Collar DAN12-6 Item 30 21 Remove unwanted sealant from the installation area. (g) Install a new lock fitting, the reinforcement doublers and angles to the sill beam and main frames/cargo door supports at FR62 as shown on Fig. A-GBAAA Sheet 01 , Fig. A-GBAAA Sheet 03 , Fig. A-GBAAA Sheet 05 , Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 7 Collar DAN12-5 Item (10) Discard 3 Pin-Rivet DAN7-5A4 Item (16) Discard 5 Rivet NSA5411-40-000 Item (17) Discard 9 Rivet LN9198-4000CF Item (18) Discard 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 3 and item 4 and the angles, item 13 and item 14 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 11 . DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 46 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A300-600 SERVICE BULLETIN 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 3 and item 4. 6 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to the reinforcement angles, item 13 and item 14. 7 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . 8 Remove the reinforcement doublers, ite, 3 an ditem 4. 9 Deburr the two fastener holes for cold working. 10 Remove the drill chippings from the installation area. 11 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 12 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41. Use tool list No. FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 47 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A300-600 SERVICE BULLETIN and Textile-Lint Free Cotton 14SBA1 As required d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 with FT20 POWERPAK 1 LB20 PULLER UNIT 1 LBRA7 PULLER - 90 DEG ADAPTER 1 and FTBXC1 BOX 1 with CBM4-4N7-243V1 MANDREL 1 CBMG4-4N GAGE - MANDREL, WEAR 1 CBCE73-044F CAP - NOSE 1 f Remove the sleeves. DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 48 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A300-600 SERVICE BULLETIN g Ream the holes to the final diameter between 4.723mm (0.186in) and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . Use tool list No. FTBXC1 BOX 1 with CBG4-4N1 GAGE - COMBINATION 1 CBR4-4NRA1860 GAGE - FINISH REAMER 1 NOTE : Holes shall be free of damage, spiral ridges, cuts and reamer removal markings. A last reaming pass will be 0.2 mm as maximum. NOTE : It is permissible for a post reamed hole to exhibit a region at hole entry, exit or interface that does not clean up (partial ridge remains in hole). A hole in this condition is considered to be acceptable providing the total length of the ridge does not exceed 0.5 mm (0.197 in). 13 Install the reinforcement doublers, item 3 and item 4 as shown on Fig. A- GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 . 14 Drill all the fastener holes to the final diameter in accordance with SRM 51-40-44. 15 Remove the reinforcement doublers, item 3 and item 4 and the angles, item 13 and item 14. 16 Deburr the fastener holes. 17 Clean the installation area and the reinforcement doublers, item 3 and item 4 and the angles, item 13 and item 14 with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 18 Apply to the faying surfaces of the structure parts in accordance with SRM 51-24-00. Polysulfide Sealant- General Purpose Interfay 06AAC1 As required DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 49 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A300-600 SERVICE BULLETIN 19 Install to the sill beam and main frames/cargo door supports at FR62 as shown on Fig. A-GBAAA Sheet 11 and Fig. A-GBAAA Sheet 14 and in accordance with SRM 51-40-21: 1 Angle A5398104820800 Item 13 1 Angle A5398104820900 Item 14 1 Doubler A5398104821600 Item 3 1 Doubler A5398104821400 Item 4 with 3 Pin DAN5-6-4 Item 25 6 Pin DAN5-6-6 Item 26 2 Pin DAN5-6-7 Item 27 11 Collar NSA5075-6 Item 32 3 Pin DAN5-6-7X Item 24 2 Pin DAN5-6-6X Item 23 5 Collar DAN12-6X Item 29 2 Bolt EN6115K3-5 Item 31 2 Nut ASNA2528-3 Item 33 4 Pin DAN7-6-9 Item 28 4 Collar DAN12-6 Item 30 20 Remove unwanted sealant from the installation area. (h) Install the reinforcement doublers and angles to the sill beam and main frames/cargo door supports at FR62A as shown on Fig. A-GBAAA Sheet 01 , Fig. A-GBAAA Sheet 04 , Fig. A-GBAAA Sheet 06 , Fig. A-GBAAA Sheet 12 and Fig. A- GBAAA Sheet 14 . 1 Remove from the sill beam, fuselage skin and main frames/cargo door support in accordance with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06 : 4 Pin-Rivet DAN7-5A7 Item (9) Discard 4 Collar DAN12-5 Item (10) Discard 7 Rivet NSA5411-40-000 Item (17) Discard DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 50 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A300-600 SERVICE BULLETIN 2 Pin-Rivet HL1012VF6-2 Item (19) Discard 2 Collar DAN12-6 Item (15) Discard 2 Clean the working area with a none-metallic spatula and with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required 3 Temporary put in position the doublers, item 15 and item 16 and the angles, item 17 and item 18 on the sill beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 12 . 4 Check the edge margin of the fastener holes in accordance with SRM 51-40-50 5 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the reinforcement doublers, item 15 and item 16 to the main frames/cargo door supports. 6 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the main frames/cargo door supports to the reinforcement doublers, item 15 and item 16. 7 Transfer drill the existing fastener holes with a drill bush to a diameter of 2.5mm (0.098in) from the sill beam and main frames/cargo door supports to the reinforcement angles, item 17 and item 18. 8 Drill the two holes for the cold working to the diameter between 4.29mm (0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 12 and Fig. A-GBAAA Sheet 14 . 9 Remove the reinforcement doublers, item 15 and item 16. 10 Deburr the two fastener holes for cold working. 11 Remove the drill chippings from the installation area. 12 Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 51 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A300-600 SERVICE BULLETIN 13 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA Sheet 12 and Fig. A-GBAAA Sheet 14 . a Do the eddy current rotating probe inspection in the two fastener holes to avoid crack propagation in accordance with NTM 51-10-01. b Oversize the holes to the starting diameter in accordance with SRM 51-40-41. Use tool list No. FTBXC1 BOX 1 with CBSD4-4NRA DRILL - STARTING 1 CBSR4-4NRA REAMER - STARTING 1 c Clean the installation areas with: Non Aqueous Cleaner-General 08BAA9 As required and Textile-Lint Free Cotton 14SBA1 As required d Install the sleeves in accordance with SRM 51-40-41 Use tool list No. CBS4-4N8F SLEEVE 2 NOTE : The split within the installed split sleeve shall be aligned inside the hole in accordance with Fig. A-GBAAA Sheet 12 and Fig. A-GBAAA Sheet 14 . The permissible angular tolerance for the alignment of the split is 10 degrees. NOTE : Ensure that the split sleeve length is at least 0.8 mm (1/32 in) longer than the combined stack thickness to be cold expanded. Only one sleeve is allowed, it is not acceptable to combine sleeves to achieve the length required. e Do the cold expansion of the fastener holes in accordance with SRM 51-40-41 Use tool list No. FTBXA9 BOX 1 DATE: Jun 26/15 SERVICE BULLETIN No.: A300-53-6181 REVISION No.: 01 - Jul 02/15 Page: 52 6 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. The text continues at https://openairdocs.org/service-documents/airbus/a300-53-6181/file/cb6395f159b3.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.