# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14 MODIFICATION No.: 10326H5339 This page transmits Revision No.02 of Service Bulletin No.A300-57-6046 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 include a High Frequency Eddy Current (HFEC) inspection after accomplishment of this modification Service Bulletin. The opportunity is taken to produce this Service Bulletin in the latest format. CHANGES Summary of changes: - part number of washer NAS5353-06A corrected to NSA5353-06A. SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Minor editorial or document structure change N GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-USAAA Minor editorial or document structure change N Fig. A-USAAA Sheet 01 Minor editorial or document structure change N PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N CONF 002 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Minor editorial or document structure change N Objective/Action Minor editorial or document structure change N Advantages Minor editorial or document structure change N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Minor editorial or document structure change N Classification Minor editorial or document structure change N Accomplishment Timescale Minor editorial or document structure change N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N LIST OF COMPONENTS Minor editorial or document structure change N Kit 576046B01R00 Minor editorial or document structure change N Kit 576046B02R00 Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N Consumable CMLB01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N Tooling - Price and Availability Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N Tools Minor editorial or document structure change N Standard tool TOOLB01 Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 576046- 831-895-001- MODIFICATION Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Task associated data - 002 Minor editorial or document structure change N Subtask 576046-910-401-001 Minor editorial or document structure change N Subtask 576046-839-401-001 Minor editorial or document structure change N Subtask 576046-910-401-001 Minor editorial or document structure change N Subtask 576046-839-401-001 Minor editorial or document structure change N Subtask 576046-941-401-001 Minor editorial or document structure change N Subtask 576046-941-401-001 Minor editorial or document structure change N Subtask 576046-831-401-001 Minor editorial or document structure change N Subtask 576046-831-402-001 Minor editorial or document structure change N Subtask 576046-831-403-001 Minor editorial or document structure change N Subtask 576046-750-401-001 New detailed visual and HFEC inspection added N Subtask 576046-831-401-001 Minor editorial or document structure change N Subtask 576046-831-402-001 Minor editorial or document structure change N Subtask 576046-831-403-002 Minor editorial or document structure change N Subtask 576046-750-401-001 New detailed visual and HFEC inspection added N
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 576046-914-401-001 Minor editorial or document structure change N Subtask 576046-942-401-001 Minor editorial or document structure change N Subtask 576046-914-401-001 Minor editorial or document structure change N Subtask 576046-942-401-001 Minor editorial or document structure change N Fig. A-UBAAA Minor editorial or document structure change N Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N Fig. A-UBBAA Minor editorial or document structure change N Fig. A-UBBAA Sheet 01 Minor editorial or document structure change N Fig. A-UBCAA Minor editorial or document structure change N Fig. A-UBCAA Sheet 01 Minor editorial or document structure change N Fig. A-UBDAA Minor editorial or document structure change N Fig. A-UBDAA Sheet 01 Minor editorial or document structure change N APPENDIX 01: INSPECTION REPORT FORM APPENDIX CONTENT Minor editorial or document structure change N Fig. A-URAAA Minor editorial or document structure change N Fig. A-URAAA Sheet 01 Minor editorial or document structure change N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS NOTE: This is only applicable for Revision No. 02 and subsequent. If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS. REVISION SEQUENCE ORIGINAL: Jan 18/94 REVISION No. : 02 - Jun 21/13

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORYMANDATORYMANDATORY
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### TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 10326H5339 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 Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14. Following the introduction of Maintenance Review Board (MRB) document inspection SSI 57-21-64 and SSI 57-21-78, cracks were found on in-service aircraft in the same area. The accomplishment of this Service-Bulletin improves the design of the stringer run-outs by re-profiling. This will reduce the risk of cracks initiating at the stringer run-outs. This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer 19 on the bottom skin. This will relieve stresses from the rear spar at Rib 14. This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out. This modification limits the occurrence of cracks by reducing the stress concentrations in the affected areas. The embodiment of this Service Bulletin cancels the MRB document inspection SSI 57-21-64 and SSI 57-21-78 and changes the inspection requirements of SSI 57-21-66. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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# @A300-600 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 YES VENDOR SB INVOLVED NO DEFUEL/VENTING YES NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit576046B01R00 1 2,250.00 BOLTS, NUTS, WASHERS Standard tool TOOLB01 1 See SB FTI KIT **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit576046B02R00 1 2,250.00 BOLTS, NUTS, WASHERS EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

14S 34Z ABD ABR BCS CES F2I FDX I2L IRA IRM KAC KAL MON MSR OHY QTR RLB SUD TAR THA U1T UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN SUMMARY NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 576046-831-895-001: MODIFICATION TOTAL MANHOURS 63.00 ELAPSED TIME (HOURS) 28.50 **CONF 002 Task 576046-831-895-001: MODIFICATION TOTAL MANHOURS 53.00 ELAPSED TIME (HOURS) 25.50 APPENDICES **CONF ALL APPENDIX 01: INSPECTION REPORT FORM

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN SUMMARY

**CONF ALL



## A VIEW ON PANEL No. 3 BOTTOM SKIN: STRINGERS 10, 11, 12 AND 17 EITHER SIDE OF RIB 14 (STRINGER 19 SIMILAR)

PROFILE BEFORE PROFILE AFTER STRINGER DATUM RIB14 REAR FRONT

MODIFICATION AREA **NOTE:** STRINGERS

SPAR SPAR RIB14



### A LH WING SHOWN RH WING SIMILAR

D_SB_576046_7_SAAA_01_00 Figure A-USAAA - Sheet 01

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14 MODIFICATION No.: 10326H5339 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 embodied prior to delivery on A/C MSN 0723 and subsequent. (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-620 (2) Effectivity by MSN 0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529-0530 0532 0536 0543 0546 0553-0561 0563 0566 0569 0572 0575 0577 0579 0581-0582 0584 0602-0605 0607-0609 0611 0613-0614 0617-0618 0621 0623 0625-0633 0635 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0722 (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. DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN

OPERATOR MSN 14S 0609 34Z 0685 0692 ABD 0529 0557 ABR 0683 BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 CES 0521 0525 0532 0707 F2I 0284 0294 0301 0307 0312 0321 0336 0348 0351 0518 FDX 0358 0361 0365 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 I2L 0677 IRA 0632 0696 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 KAC 0344 0673 0694 0699 0719 0721 KAL 0582 0627 0631 0662 MON 0556 0604 0605 MSR 0561 0607 OHY 0584 0603 QTR 0554 0560 0614 RLB 0626 0643 SUD 0666 TAR 0505 0558 0563 THA 0464 0566 0569 0577 0629 0635 0681 0705 U1T 0628 UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 001
0518 0521 0525 0529 0530 0532 0536 0543 0546 0553 0554 0555 0556 0557 0558 0559 0560 0561 0563 0566 0569 0572 0575 0577 0579 0581 0582 0584 0602 0603 0604 0605 0607 0608 0609 0611 0613 0614 0617 0618 0621 0623 0625 0626 0627 0628 0629 0630 0631 0632 0633 0635 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0685 0688 0692 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721 0722 002

(5) Configuration definition **CONF 001 Config. 001 is applicable to aircraft Pre Mod. No. 07207H1066. **CONF 002 Config. 002 is applicable to aircraft Post Mod. No. 07207H1066.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit576046B01R00 1 (1) Standard tool TOOLB01 1 Consumable CMLB01 As required NOTE (1): KITB01 contains the component parts to modify the LH and RH wings. **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit576046B02R00 1 (1) Consumable CMLB01 As required NOTE (1): KITB02 contains the component parts to modify the LH and RH wings. **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History Cracks were found during full-scale fatigue testing in the bottom skin stringers at Rib 14. Following the introduction of Maintenance Review Board (MRB) document inspection SSI 57-21-64 and SSI 57-21-78, cracks were found on in-service aircraft in the same area. (2) Objective/Action The accomplishment of this Service-Bulletin improves the design of the stringer run-outs by re-profiling. This will reduce the risk of cracks initiating at the stringer run-outs. This Service-Bulletin also details the removal of the stringer end run-out plate at Stringer 19 on the bottom skin. This will relieve stresses from the rear spar at Rib 14. This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out. (3) Advantages This modification limits the occurrence of cracks by reducing the stress concentrations in the affected areas. The embodiment of this Service Bulletin cancels the MRB document inspection SSI 57-21-64 and SSI 57-21-78 and changes the inspection requirements of SSI 57-21-66.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 576046-831-895-001: MODIFICATION (1) RE-PROFILE THE STRINGER RUN-OUTS (2) RE-PROFILE THE STRINGER 19 RUN-OUT (3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 (4) DETAILED VISUAL AND HFEC INSPECTION **CONF 002 Task 576046-831-895-001: MODIFICATION (1) RE-PROFILE THE STRINGER RUN-OUTS (2) RE-PROFILE THE STRINGER 19 RUN-OUT (3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 (4) DETAILED VISUAL AND HFEC INSPECTION **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 Aviation Safety Agency (EASA). For B4-600 (R) aircraft operating beyond ESG embodiment of this Service Bulletin, accomplishment is mandatory at or before 42,500 Flight Cycles (FC), or within 2,000 FC from the issue date of the AD. For B4-600 (R) and C4-600 aircraft the recommended accomplishment timescales FC and Flight Hours (FH) are given in Table 1:

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN
Normal Range Short Range Aircraft FC FH FC FH A300 B4-600 (R) A300 C4-600 16,700 36,000 18,000 27,100 Table 1: Recommended Embodiment Time of Modification 10326H5339
F. APPROVAL The technical content of this document is approved under the authority of Design Organization 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 576046-831-895-001: MODIFICATION Get Access 13.00 On Aircraft RE-PROFILE THE STRINGER RUN-OUTS 15.00 RE-PROFILE THE STRINGER 19 RUN-OUT 2.00 REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 15.00 DETAILED VISUAL AND HFEC INSPECTION 3.00 Close-Up 15.00 TOTAL MANHOURS 63.00 ELAPSED TIME (HOURS) 28.50 **CONF 002 Task 576046-831-895-001: MODIFICATION Get Access 13.00 On Aircraft RE-PROFILE THE STRINGER RUN-OUTS 15.00 RE-PROFILE THE STRINGER 19 RUN-OUT 2.00 REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 5.00 DETAILED VISUAL AND HFEC INSPECTION 3.00 DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 5 7

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# @A300-600 SERVICE BULLETIN

Task 576046-831-895-001: MODIFICATION Close-Up 15.00 TOTAL MANHOURS 53.00 ELAPSED TIME (HOURS) 25.50 **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 the Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight -3.210 KG (-7.077 LB) Effect on Balance -101.115 KGM (-731.364 LB.FT) I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00 28-10-00 28-11-00 28-11-22 28-25-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 57-21-64 Process and Material Specification (PMS) Service Information Letter (SIL) 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-20 51-24-00 51-35-00 51-40-20 51-40-21 51-40-40 51-40-41 51-40-46 51-43-00 51-75-10 51-76-10 51-76-20 Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00 28-10-00 28-11-00 28-11-22 28-25-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 57-21-64 Process and Material Specification (PMS) Service Information Letter (SIL) 51-012 Standards Manual (SM)
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 6 7

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# @A300-600 SERVICE BULLETIN Structural Repair Manual (SRM) 51-23-20 51-24-00 51-35-00 51-40-20 51-40-21 51-40-40 51-40-41 51-40-44 51-40-46 51-43-00 51-75-10 51-76-10 51-76-20 Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) SSI 57-21-64 SSI 57-21-66 SSI 57-21-78 Structural Repair Manual (SRM) 57-20-14 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 7 7

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# @A300-600 SERVICE BULLETIN

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# @A300-600 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:
Kit576046B01R00 Kit576046B02R00 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

Kit576046B01R00 Cost 2,250.00 USD Availability 180 calendar days from receipt of order The Kit 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. Kit576046B02R00 Cost 2,250.00 USD Availability 180 calendar days from receipt of order The Kit 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.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 9 7

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# @A300-600 SERVICE BULLETIN
B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 576046B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 NSA5475-6K7 20 NUT 2 NSA5476VHK6-11 10 BOLT 3 NSA5476VHK6-14 10 BOLT 4 NSA5353-06A 40 WASHER NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 576046B02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 NSA5475-5K7 20 NUT 2 NSA5478VHK5-11 10 BOLT 3 NSA5478VHK5-14 10 BOLT 4 SL4087-05A 40 WASHER NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti Corrosion Primer Epoxy 04DAB2 As required Brushable Fuel Resistant Coating 06HAA1 As required Non Aqueous Cleaner 08BAA9 As required Chemical Conversion Coating Yellow Aluminum 10ABC1 As required (2) Components None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 10 7

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# @A300-600 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Operators in Config. 001 interested in obtaining the FTI tool kits should contact: Standard tool TOOLB01 Fatigue Technology Inc 401 Andover Park East SEATTLE WA 98188-7605 USA Internet: www.fatiguetech.com Phone: (206) 2462010 Fax: (206) 2449886 (b) Price and Availability Operators in Config. 001 who require kit number FTI-A300-57-6046-1, refer to Fatigue Technology Inc. For operators in Config. 001, supply terms for the Start Drill Block part number CHS371J-10-3-N are to be negotiated with: AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY internet: http://spares.airbus.com fax: +49 40 50 76 2590 E-mail: airbus.kit@airbus.com (2) Tools For operators in Config. 001, AIRBUS Spares Support and Services with FTI have allocated the following tool kit numbers for cold expansion: For the definition of capital, durable and expendable tools refer to SIL 51-012.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 11 7

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# @A300-600 SERVICE BULLETIN
Standard tool TOOLB01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA300576046-1 Durable Tooling 1 (1) EKA300576046-1 Expendable Tooling 1 (2) FTIA300576046-1 Capital Tooling 1 (3) NOTE (1): Durable tooling: Ref. DK-A300-57-6046-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2): Expendable tooling: Ref. EK-A300-57-6046-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3): Capital tooling: Ref. FTI-A300-57-6046-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. (3) Special Tools None

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 12 7

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 576046-831-895-001 - MODIFICATION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 543 550 643 650 Access Panel 543DB 550BB 643DB 650BB Manpower TOTAL MANHOURS 63.00 ELAPSED TIME (HOURS) 28.50 **CONF 002 Zone 543 550 643 650 Access Panel 543DB 550BB 643DB 650BB

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 13 7

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# @A300-600 SERVICE BULLETIN
Manpower TOTAL MANHOURS 53.00 ELAPSED TIME (HOURS) 25.50 **CONFALL A. GENERAL **CONF 001 (1) Subtask 576046-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Consumable Material List (CML) Process and Material Specification (PMS) Structural Repair Manual (SRM) 51-24-00 51-40-20 51-40-40 51-75-10 (a) If you find process and material specifications that you do not know in the design drawings, refer to the cross-reference list in the Process and Material Specification (PMS). (b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-40-20. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-10. (g) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM 51-40-40. (2) Subtask 576046-839-401-001 - ADMINISTRATIVE Manpower Resources Skills UTILITY Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 14 7

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# @A300-600 SERVICE BULLETIN
**CONF 002 (1) Subtask 576046-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Consumable Material List (CML) Process and Material Specification (PMS) Structural Repair Manual (SRM) 51-24-00 51-40-20 51-40-40 51-75-10 (a) If you find process and material specifications that you do not know in the design drawings, refer to the cross-reference list in the Process and Material Specification (PMS). (b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (c) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (d) Remove and install fasteners in accordance with SRM 51-40-20. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-10. (g) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM 51-40-40. (2) Subtask 576046-839-401-001 - ADMINISTRATIVE Manpower Resources Skills UTILITY Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 15 7

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# @A300-600 SERVICE BULLETIN
**CONFALL B. PREPARATION **CONF 001 (1) Subtask 576046-941-401-001 - JOB SET-UP Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-00, Page Block 101 28-11-22, Page Block 401 28-25-00, Page Block 301 WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE (REFER TO AMM 28-00-00, PAGE BLOCK 301). (a) Defuel the aircraft (Refer to AMM 28-25-00, Page Block 301). (b) Put the access platform(s) in position. (c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block 101). (d) Vent the fuel tanks (Refer to AMM 28-10-00, Page Block 301). **CONF 002 (1) Subtask 576046-941-401-001 - JOB SET-UP Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-00-00, Page Block 301 28-10-00, Page Block 301 28-11-00, Page Block 101 28-11-22, Page Block 401 28-25-00, Page Block 301 WARNING: OBEY THE SAFETY PROCEDURES WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT INJURY OR DAMAGE (REFER TO AMM 28-00-00, PAGE BLOCK 301). (a) Defuel the aircraft (Refer to AMM 28-25-00, Page Block 301). (b) Put the access platform(s) in position. DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 16 7

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# @A300-600 SERVICE BULLETIN (c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block 101). (d) Vent the fuel tanks (Refer to AMM 28-10-00, Page Block 301). **CONFALL C. PROCEDURE NOTE: The procedures that follow must be accomplished on the LH and RH wings. **CONF 001 (1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 643 Work location from Rib 13 to Rib 14 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Manpower Resources Manhours 15.00 Minimum number of person 2 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti Corrosion Primer Epoxy 04DAB2 As required Non Aqueous Cleaner 08BAA9 As required Chemical Conversion Coating Yellow Aluminum 10ABC1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-20 51-35-00
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 17 7

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# @A300-600 SERVICE BULLETIN

References Fig. A-UBAAA LOCATION AND AREA OF MODIFICATION Sheet01

NOTE: The procedures that follow must be accomplished on the LH and RH wings. Refer to Fig. A-UBAAA Sheet 01 (a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14 to the new contour as follows: 1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the new profile to the contour shown on Fig. A-UBAAA Sheet 01

. 2 Cut the stringers to the new contour, take care to remove only unwanted material. 3 Deburr, blend and polish all cut edges. WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with Non Aqueous Cleaner 08BAA9 As required (Refer to SRM 51-35-00 and AMM 20-31-00). 5 Apply Chemical Conversion Coating Yellow Aluminum 10ABC1 As required

and Anti Corrosion Primer Epoxy 04DAB2 As required to the cut surfaces (Refer to SRM 51-23-20 and Consumable Material List (CML)). (2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 Stringer 19 643 Work location from Rib 13 to Rib 14 Stringer 19
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 18 7

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# @A300-600 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti Corrosion Primer Epoxy 04DAB2 As required Non Aqueous Cleaner 08BAA9 As required Chemical Conversion Coating Yellow Aluminum 10ABC1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Structural Repair Manual (SRM) 51-23-20 51-35-00 Fig. A-UBCAA MODIFICATION TO END OF STRINGER 19 Sheet01

NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the new contour as follows: 1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the new profile to the contour shown on Fig. A-UBCAA Sheet 01

. 2 Cut the end of stringer 19 to the new contour, take care to remove only unwanted material. 3 Deburr, blend and polish all cut edges. WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with: Non Aqueous Cleaner 08BAA9 As required (Refer to SRM 51-35-00 and AMM 20-31-00).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 19 7

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# @A300-600 SERVICE BULLETIN
5 Apply Chemical Conversion Coating Yellow Aluminum 10ABC1 As required

and Anti Corrosion Primer Epoxy 04DAB2 As required to the cut surfaces (Refer to SRM 51-23-20 and AMM 20-31-00). (3) Subtask 576046-831-403-001 - REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 Stringer 19 643 Work location from Rib 13 to Rib 14 Stringer 19 Manpower Resources Manhours 15.00 Minimum number of person 2 Subtask elapsed time 7.50 Skills AIRFRAME Material necessary to do the job Kit 576046B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 NSA5475-6K7 20 NUT 2 NSA5476VHK6-11 10 BOLT 3 NSA5476VHK6-14 10 BOLT 4 NSA5353-06A 40 WASHER Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Brushable Fuel Resistant Coating 06HAA1 As required Non Aqueous Cleaner 08BAA9 As required Standard tool TOOLB01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA300576046-1 Durable Tooling 1 (1) DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 20 7

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# @A300-600 SERVICE BULLETIN

ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES EKA300576046-1 Expendable Tooling 1 (2) FTIA300576046-1 Capital Tooling 1 (3) NOTE (1): Durable tooling: Ref. DK-A300-57-6046-1 The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2): Expendable tooling: Ref. EK-A300-57-6046-1 The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3): Capital tooling: Ref. FTI-A300-57-6046-1 The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. References Aircraft Maintenance Manual (AMM) 20-31-00 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Structural Repair Manual (SRM) 51-35-00 51-40-20 51-40-21 51-40-41 51-40-46 51-43-00 51-76-10 51-76-20 Fig. A-UBBAA STRINGER END RUN-OUT PLATE REMOVAL Sheet01 Fig. A-UBDAA SPLIT SLEEVE POSITION ON REAR SPAR Sheet01

NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. Refer to Fig. A-UBBAA Sheet 01 (a) Get these items from KITB01 to modify the LH and RH wings: 20 Nut NSA5475-6K7 Item 1 DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 21 7

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# @A300-600 SERVICE BULLETIN

10 Bolt-Hi Lok NSA5476VHK6-11 Item 2 10 Bolt-Hi Lok NSA5476VHK6-14 Item 3 40 Washer-Special NSA5353-06A Item 4 (b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3, adjacent to Rib 14 as follows: 1 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) (Refer to SRM 51-76-20). 2 Remove and discard these items (Refer to SRM 51-40-20): 10 Nut Item (1) 5 Taperlock Bolt Item (2) 5 Taperlock Bolt Item (3) 1 Stringer End Run-Out Plate Item (5)
WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 3 Remove all traces of sealant. Use Non Aqueous Cleaner 08BAA9 As required to clean the surfaces of the rear spar and the stringer flange which were connected to the Stringer End Run-Out Plate, Item (5) (Refer to SRM 51-76-20, SRM 51-35-00 and AMM 20-31-00). 4 Use procedure C of the Eddy Current Technique NTM 51-10-01 Part 6 to do an inspection of the ten fastener holes. Report any defects to AIRBUS for repair instructions. Do not continue until repair instructions have been received. 5 Install slave bolts in each second hole of the ten fastener holes to hold the bottom skin to the stringer and the rear spar. 6 Use the FTI Tools: FTIA300576046-1 Capital Tooling 1 DKA300576046-1 Durable Tooling 1 EKA300576046-1 Expendable Tooling 1

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 22 7

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# @A300-600 SERVICE BULLETIN Drill and ream the holes through the spar to the cold expansion start drill diameter of 8.789 to 8.864 mm (0.346 to 0.349 in.). Use the tools given as follows: Tool Name Tool Part No. Start Drill Block CHS371J-10-3-N Start Reamer CXSR-.3460/.3260-1 Start Drill CBSD-10-3-N-1 7 Examine the reamed start holes through the rear spar. Use the combination plug gage, Part No. CXG-.3460/.3490/.3500. NOTE: If a hole is found oversize or oval, report the defect to AIRBUS. 8 Drill and ream the holes through the stringer 19 to the cold expansion start size diameter of 8.738 to 8.813 mm (0.344 to 0.347 in.). Use the tools given as follows: Tool Name Tool Part No. Start Drill Block CHS371J-10-3-N Start Reamer CBSR-10-3-N-1 Start Drill CBSD-10-3-N-1 9 Examine the reamed start holes through stringer 19. Use the combination plug gage, Part No. CBG-10-3-N-1. NOTE: If a hole is found oversize or oval, report the defect to AIRBUS. 10 Cold expand and final ream the holes. Use the tools given as follows (Refer to Fig. A-UBDAA Sheet 01 and SRM 51-40-41): Tool Name Tool Part No. Split Sleeve CBS-10-3-N-23F Mandrel CBM-10-3-N-1-40-V1 Nose Cap CBCE-14B-1023F Mandrel Checking Fixture CBMG-10-3-N Finish Reamer CBR-10-3-N-1-.3695 11 Countersink the holes to 100 degrees for the new Bolts, Items 2 and 3 (Refer to SRM 51-40-46). 12 Deburr the edges of the holes. 13 Apply Brushable Fuel Resistant Coating 06HAA1 As required under the head of the new Bolts, Items 2 and 3 (Refer to AMM 20-31-00). DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 23 7

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# @A300-600 SERVICE BULLETIN

14 On each wing, assemble in each of the non-slave bolted holes the interference fit 2 Bolt-Hi Lok NSA5476VHK6-11 Item 2 and 3 Bolt-Hi Lok NSA5476VHK6-14 Item 3 and the 5 Nut NSA5475-6K7 Item 1 with a maximum quantity of 2 Washer-Special NSA5353-06A Item 4 for each of the Bolts, Items 2 and 3.
a Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210 and 230 lbf.in.) (Refer to SRM 51-40-21 and SRM 51-43-00). 15 Remove the five slave bolts. 16 Do worksteps 6_ thru 13_ for the holes that remain. 17 On each wing, for the five holes that remain, assemble the interference fit 3 Bolt-Hi Lok NSA5476VHK6-11 Item 2 and 2 Bolt-Hi Lok NSA5476VHK6-14 Item 3 and the 5 Nut NSA5475-6K7 Item 1 with a maximum quantity of 2 Washer-Special NSA5353-06A Item 4 for each of the Bolts, Items 2 and 3.
a Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210 and 230 lbf.in.) (Refer to SRM 51-40-21 and SRM 51-43-00). (4) Subtask 576046-750-401-001 - DETAILED VISUAL AND HFEC INSPECTION Work Zones and Access Panels Zone Access/Work location 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 24 7

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# @A300-600 SERVICE BULLETIN

650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-21-64 NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Make sure that the inspection area is sufficiently clean to do an eddy current inspection. (b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10, 11, 12 and 17 (Refer to NTM 57-21-64). (c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact AIRBUS. (d) Use the results from the eddy current inspection to complete the Inspection Report Form to identify areas of stringer damage (cracks) (Refer to APPENDIX 01: INSPECTION REPORT FORM ). **CONF 002 (1) Subtask 576046-831-401-001 - RE-PROFILE THE STRINGER RUN-OUTS Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 643 Work location from Rib 13 to Rib 14 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Manpower Resources Manhours 15.00 Minimum number of person 2 Subtask elapsed time 7.50 Skills AIRFRAME DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 25 7

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# @A300-600 SERVICE BULLETIN
Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti Corrosion Primer Epoxy 04DAB2 As required Non Aqueous Cleaner 08BAA9 As required Chemical Conversion Coating Yellow Aluminum 10ABC1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-20 51-35-00 Fig. A-UBAAA LOCATION AND AREA OF MODIFICATION Sheet01

NOTE: The procedures that follow must be accomplished on the LH and RH wings. Refer to Fig. A-UBAAA Sheet 01 (a) Cut the stringers 10, 11, 12 and 17 on bottom skin panel No. 3, adjacent to Rib 14 to the new contour as follows: 1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the new profile to the contour shown on Fig. A-UBAAA Sheet 01

. 2 Cut the stringers to the new contour, take care to remove only unwanted material. 3 Deburr, blend and polish all cut edges. WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with Non Aqueous Cleaner 08BAA9 As required (Refer to SRM 51-35-00 and AMM 20-31-00). 5 Apply Chemical Conversion Coating Yellow Aluminum 10ABC1 As required

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 26 7

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# @A300-600 SERVICE BULLETIN
and Anti Corrosion Primer Epoxy 04DAB2 As required to the cut surfaces (Refer to SRM 51-23-20 and Consumable Material List (CML)). (2) Subtask 576046-831-402-001 - RE-PROFILE THE STRINGER 19 RUN-OUT Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 Stringer 19 643 Work location from Rib 13 to Rib 14 Stringer 19 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti Corrosion Primer Epoxy 04DAB2 As required Non Aqueous Cleaner 08BAA9 As required Chemical Conversion Coating Yellow Aluminum 10ABC1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Structural Repair Manual (SRM) 51-23-20 51-35-00 Fig. A-UBCAA MODIFICATION TO END OF STRINGER 19 Sheet01

NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Cut the end of stringer 19 on bottom skin panel No. 3, adjacent to Rib 14, to the new contour as follows: 1 Go into the fuel tank. Use a non-metallic or graphite marker and mark out the new profile to the contour shown on Fig. A-UBCAA Sheet 01

. DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 27 7

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# @A300-600 SERVICE BULLETIN

2 Cut the end of stringer 19 to the new contour, take care to remove only unwanted material. 3 Deburr, blend and polish all cut edges. WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with: Non Aqueous Cleaner 08BAA9 As required (Refer to SRM 51-35-00 and AMM 20-31-00). 5 Apply Chemical Conversion Coating Yellow Aluminum 10ABC1 As required

and Anti Corrosion Primer Epoxy 04DAB2 As required to the cut surfaces (Refer to SRM 51-23-20 and AMM 20-31-00). (3) Subtask 576046-831-403-002 - REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 Work Zones and Access Panels Zone Access/Work location 543 Work location from Rib 13 to Rib 14 Stringer 19 643 Work location from Rib 13 to Rib 14 Stringer 19 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 576046B02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 NSA5475-5K7 20 NUT 2 NSA5478VHK5-11 10 BOLT 3 NSA5478VHK5-14 10 BOLT DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 28 7

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# @A300-600 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 SL4087-05A 40 WASHER Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Brushable Fuel Resistant Coating 06HAA1 As required Non Aqueous Cleaner 08BAA9 As required References Aircraft Maintenance Manual (AMM) 20-31-00 Non Destructive Test Manual (NTM) 51-10-01 Part 6 Structural Repair Manual (SRM) 51-35-00 51-40-20 51-40-21 51-40-41 51-40-44 51-40-46 51-43-00 51-76-10 51-76-20 Fig. A-UBBAA STRINGER END RUN-OUT PLATE REMOVAL Sheet01

NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. Refer to Fig. A-UBBAA Sheet 01 (a) Get these items from KITB02 to modify the LH and RH wings: 20 Nut NSA5475-5K7 Item 1 10 Bolt-Hi Lok NSA5478VHK5-11 Item 2 10 Bolt-Hi Lok NSA5478VHK5-14 Item 3 40 Washer SL4087-05A Item 4 (b) Remove the stringer end run-out plate on stringer 19 on bottom skin panel No. 3, adjacent to Rib 14 as follows: 1 Go into the fuel tank. Remove the sealant from the ten Nuts, Item (1) (Refer to SRM 51-76-20). 2 Remove and discard these items (Refer to SRM 51-40-20): 10 Nut Item (1)
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 29 7

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# @A300-600 SERVICE BULLETIN

5 Interference Fit Bolt Item (2) 5 Interference Fit Bolt Item (3) 1 Stringer End Run-Out Plate Item (5)
WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 3 Remove all traces of sealant. Use Non Aqueous Cleaner 08BAA9 As required to clean the surfaces of the rear spar and the stringer flange which were connected to the Stringer End Run-Out Plate, Item (5) (Refer to SRM 51-76-20, SRM 51-35-00 and AMM 20-31-00). 4 Use procedure B of the Eddy Current Technique NTM 51-10-01 Part 6 to do an inspection of the ten fastener holes. Report any defects to AIRBUS for repair instructions. Do not continue until repair instructions have been received. 5 Drill and ream the holes through the stringer 19 to between 8.738 to 8.813 mm (0.344 to 0.347 in.) for second oversize interference fit bolts (Refer to SRM 51-40-44). 6 Deburr the edges of the holes. 7 Apply Brushable Fuel Resistant Coating 06HAA1 As required under the head of the new Bolts, Items 2 and 3 (Refer to AMM 20-31-00). 8 On each wing, install second oversize interference fit 5 Bolt-Hi Lok NSA5478VHK5-11 Item 2 and 5 Bolt-Hi Lok NSA5478VHK5-14 Item 3 and the 10 Nut NSA5475-5K7 Item 1 with a maximum quantity of 2 Washer SL4087-05A Item 4 for each of the Bolts, Items 2 and 3. DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 30 7

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# @A300-600 SERVICE BULLETIN

a Torque tighten the Nuts, Item 1 to between 1.413 and 1.525 m.daN (125 and 135 lbf.in.) (Refer to SRM 51-40-20 and SRM 51-43-00). (4) Subtask 576046-750-401-001 - DETAILED VISUAL AND HFEC INSPECTION Work Zones and Access Panels Zone Access/Work location 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 57-21-64 NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Make sure that the inspection area is sufficiently clean to do an eddy current inspection. (b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10, 11, 12 and 17 (Refer to NTM 57-21-64). (c) If there are signs of cracks or damage at stringers 10, 11, 12 or 17, contact AIRBUS. (d) Use the results from the eddy current inspection to complete the Inspection Report Form to identify areas of stringer damage (cracks) (Refer to APPENDIX 01: INSPECTION REPORT FORM ). **CONFALL D. TEST **CONF 001 None **CONF 002 None
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 31 7

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# @A300-600 SERVICE BULLETIN
**CONFALL E. CLOSE-UP **CONF 001 (1) Subtask 576046-914-401-001 - APPLY SEALANTS Work Zones and Access Panels Zone Access/Work location 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 19 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 19 Manpower Resources Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Brushable Fuel Resistant Coating 06HAA1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Structural Repair Manual (SRM) 51-76-10 51-76-20 NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Apply Brushable Fuel Resistant Coating 06HAA1 As required

(Refer to AMM 20-31-00) as a bead along the stringer flange edges and also to fully cover all the Nuts, Item 1 and the Special Washers, Item 4 (Refer to SRM 51-76-20). (b) Allow the sealant to cure (Refer to SRM 51-76-10).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 32 7

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# @A300-600 SERVICE BULLETIN (2) Subtask 576046-942-401-001 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 543 Access Panel 543DB 643 Access Panel 643DB 550 Access Panel 550BB 650 Access Panel 650BB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 101 28-11-00, Page Block 501 28-11-22, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 543DB (643DB) and 550BB (650BB) between RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block 101). (c) Remove the access platform(s). (d) Refuel the aircraft and inspect for leaks (Refer to AMM 28-11-00, Page Block 501). **CONF 002 (1) Subtask 576046-914-401-001 - APPLY SEALANTS Work Zones and Access Panels Zone Access/Work location 550 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 19 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 19 Manpower Resources Skills AIRFRAME

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 33 7

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# @A300-600 SERVICE BULLETIN
Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Brushable Fuel Resistant Coating 06HAA1 As required
References Aircraft Maintenance Manual (AMM) 20-31-00 Structural Repair Manual (SRM) 51-76-10 51-76-20 NOTE: The worksteps that follow are to be accomplished on both the LH and RH wings. (a) Apply Brushable Fuel Resistant Coating 06HAA1 As required

(Refer to AMM 20-31-00) as a bead along the stringer flange edges and also to fully cover all the Nuts, Item 1 and the Special Washers, Item 4 (Refer to SRM 51-76-20). (b) Allow the sealant to cure (Refer to SRM 51-76-10). (2) Subtask 576046-942-401-001 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 543 Access Panel 543DB 643 Access Panel 643DB 550 Access Panel 550BB 650 Access Panel 650BB Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 28-11-00, Page Block 101 28-11-00, Page Block 501 28-11-22, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access panels 543DB (643DB) and 550BB (650BB) between RIBS Rib 13 and Rib 15 (Refer to AMM 28-11-22, Page Block 401 and AMM 28-11-00, Page Block 101).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 34 7

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# @A300-600 SERVICE BULLETIN (c) Remove the access platform(s). (d) Refuel the aircraft and inspect for leaks (Refer to AMM 28-11-00, Page Block 501).

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 35 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

**F W**  **D INBD** 

REAR SPAR

DATUM FRONT SPAR DATUM LH WING SHOWN RH WING SIMILAR

PLAN VIEW LH WING BOTTOM SKIN PANEL No. 3 STGR8 STGR10 STGR11 STGR12 STGR13
STGR16 STGR17 STGR19 RIB12 RIB9 RIB10 RIB11

RIB13 RIB14 RIB15

CONTOUR BEFORE

MODIFICATION 31.50 mm (1.24 in) CONTOUR BEFORE

MODIFICATION RIB14 DATUM



## A EXAMPLE FOR ALL AFFECTED STRINGERS 31.50 mm (1.24 in)

CONTOUR AFTER MODIFICATION CONTOUR AFTER

MODIFICATION 25° 25° R 50.80 mm (2.00 in) R 50.80 mm

(2.00 in) STRINGER 13 AND 16 NOT AFFECTED STRINGER RUN−OUTS 

### A

D_SB_576046_7_BAAA_01_00 Figure A-UBAAA - Sheet 01 LOCATION AND AREA OF MODIFICATION
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 36 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

**INBD** 

## A STRINGER END RUN−OUT PLATE 

### A PLAN VIEW LH WING BOTTOM SKIN PANEL No. 3 **F W**  **D INBD** 

REAR SPAR

DATUM FRONT SPAR DATUM LH WING SHOWN RH WING SIMILAR STGR8 STGR10 STGR11 STGR12 STGR13
STGR16 STGR17 STGR19 RIB12 RIB9 RIB10 RIB11

RIB13 RIB14 RIB15

REAR SPAR DATUM RIB14

STGR19 DATUM DATUM (1) 1 (2) 2 4

(1) 1 (3) 3 4 (5)

D_SB_576046_7_BBAA_01_00 Figure A-UBBAA - Sheet 01 STRINGER END RUN-OUT PLATE REMOVAL
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 37 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

PLAN VIEW LH WING BOTTOM SKIN PANEL No. 3 RIB13 RIB14 RIB15



## A CONTOUR BEFORE

MODIFICATION

CONTOUR AFTER

MODIFICATION 30° R 76.20 mm

(3.00 in)

R 15.20 mm (0.60 in) 30.50 mm (1.20 in)

STGR19 FRONT SPAR DATUM

REAR SPAR

DATUM 

### A STGR10 STGR11 STGR12 STGR13
STGR16 STGR17 STGR19 **F W**  **D INBD**  LH WING SHOWN RH WING SIMILAR

D_SB_576046_7_BCAA_01_00 Figure A-UBCAA - Sheet 01 MODIFICATION TO END OF STRINGER 19
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 38 7

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# @A300-600 SERVICE BULLETIN

**CONF 001

OR OUTBOARD PERMITTED. SPAR DATUM

PLAN VIEW

SPLIT SLEEVE POSITION ± 10° SPLIT SLEEVE ON INBOARD
IN RELATION TO SPAR DATUM.

D_SB_576046_7_BDAA_01_00 Figure A-UBDAA - Sheet 01 SPLIT SLEEVE POSITION ON REAR SPAR
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 39 7

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# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 40 7

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# @A300-600 SERVICE BULLETIN APPENDIX 01: INSPECTION REPORT FORM **CONF ALL Record the location of cracks on the Inspection Report Form shown below:

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN APPENDIX 01: INSPECTION REPORT FORM

**CONF ALL 

## INSPECTION REPORT
SERVICE BULLETIN NO:

FINDINGS: RETURN TO: AIRBUS

FAX +33 (0)5 61 93 36 14 A300−57−6046

LOCATION OF FINDINGS STRINGER 10 MSN: AIRCRAFT FLIGHT CYCLES: FLIGHT HOURS: CUSTOMER SERVICE ENGINEERING − SEES2 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE YES NO Structure.sbinspectionresult@airbus.com DATE OF INSPECTION: INSPECTION METHOD: HIGH FREQUENCY EDDY CURRENT

STRINGER 11 STRINGER 12 STRINGER 17 CRACKS FOUND YES: PROVIDE DETAILS BELOW NO

D_SB_576046_7_RAAA_01_00 Figure A-URAAA - Sheet 01 INSPECTION REPORT FORM
DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB14 MODIFICATION No.: 10326H5339 Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Jan 18/94 SERVICE BULLETIN No.: A300-57-6046 REVISION No.: 02 - Jun 21/13 Page: 1 7

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