# Airbus Service Bulletin A300-57-0203 Copy: Revision 04 ("SB A300-57-0203_Rev4"), 60 pages: PDF https://openairdocs.org/files/sha256/0b/d0/0bd0178e5d8a9a08c48ebeeab7552cff0fc98c68929e2c60ce3c60012e7c271c; text https://openairdocs.org/service-documents/airbus/a300-57-0203/file/0bd0178e5d8a.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 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: A300-57-0203 - Latest revision known: A300-57-0203, Revision 04, dated February 18, 2015 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/airbus/a300-57-0203 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2017-05-01](https://openairdocs.org/ad/2017-05-01.md), effective Apr 7, 2017: Revision 04 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-57-0203/proposed.md). ## Text (60 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 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 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: 57 TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB 14 AREA AND REMOVAL OF STRINGER 19 TERMINATION PLATE MODIFICATION No.: 10326H5339 This page transmits Revision No.04 of Service Bulletin No.A300-57-0203 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 04 issued: - to change compliance from Recommended to Mandatory - to update the accomplishment timescale. The opportunity is taken to update this Service Bulletin in the latest format. CHANGES FRONT MATTER WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB 14 AREA AND REMOVAL OF STRINGER 19 TERMINATION PLATE CONFIGURATION UPDATED R SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R APPENDICES APPENDICES UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED R MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED R REASON Objective/Action OBJECTIVE/ACTION UPDATED R COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE ADDED N APPROVAL APPROVAL UPDATED R MANPOWER MANPOWER UPDATED CONFIGURATION UPDATED R MANPOWER UPDATED CONFIGURATION UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL PRICE UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 570203- 831-895-001- MODIFICATION TASK SOLUTION UPDATED NOTE UPDATED CAUTION UPDATED R Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 002 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 570203-941-401-001 SUBTASK SOLUTION UPDATED NOTE UPDATED WARNING UPDATED R Subtask 570203-941-401-001 SUBTASK SOLUTION UPDATED NOTE UPDATED WARNING UPDATED R DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 570203-250-401-001 SUBTASK SOLUTION ADDED N Subtask 570203-831-401-001 SUBTASK SOLUTION UPDATED R Subtask 570203-831-402-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 570203-750-401-001 New detailed visual and HFEC inspection added R Subtask 570203-250-401-001 SUBTASK SOLUTION ADDED N Subtask 570203-831-401-002 SUBTASK SOLUTION UPDATED R Subtask 570203-831-403-001 SUBTASK SOLUTION UPDATED R Subtask 570203-831-402-002 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED R Subtask 570203-750-401-001 New detailed visual and HFEC inspection added R Subtask 570203-914-401-001 SUBTASK SOLUTION UPDATED R Subtask 570203-942-401-001 SUBTASK SOLUTION UPDATED R Subtask 570203-914-401-001 SUBTASK SOLUTION UPDATED R Subtask 570203-942-401-001 SUBTASK SOLUTION UPDATED R APPENDIX 02: ELAPSED TIME ASSUMPTION Fig. A-UAAAA FIGURE SOLUTION ADDED N Fig. A-UAAAA Sheet 01 SHEET ADDED N Fig. A-UAAAB FIGURE SOLUTION ADDED N Fig. A-UAAAB Sheet 01 SHEET ADDED N FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No. 03 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. REVISION SEQUENCE ORIGINAL: Jan 21/94 REVISION No. : 03 - Jul 05/13 REVISION No. : 04 - Feb 18/15 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET This Page Intentionally Left Blank DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A300 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB 14 AREA AND REMOVAL OF STRINGER 19 TERMINATION PLATE **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 the Inspection Service Bulletin (ISB) No. A300-57-0148, cracks were found on in-service aircraft in the same area. The accomplishment if 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 details the removal of the stringer and 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 replaces the taper-lok bolts with interference fit parallel bolts. This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out on B4 aircraft only. Before this Service-Bulletin is accomplished, the work recommended by ISB No. A300-57-0148 must be performed. After this Service-Bulletin is accomplished, refer to ISB No. A300-57-0148 for the inspection threshold and the repeat inspection intervals (Post Mod. No. 01559H0365 aircraft only). This modification limits the occurrence of cracks by reducing the stress concentrations in the affected areas. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A300 SERVICE BULLETIN SUMMARY Accomplishment of this Service-Bulletin will also provide an extended inspection threshold for the affected areas. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN NO 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 Kit 570203B01R01 1 2,360.00 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 Kit 570203B02R01 1 2,360.00 BOLTS, NUTS, WASHERS Standard tool TOOLB01 1 See SB FTI KIT EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 001 22P 81T ABR AFG F2I IAW IRA IRM KZU MNB MSR RUN TIW TNO TSY CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.60.12.001 OEB None AOT None DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A300 SERVICE BULLETIN SUMMARY SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER AD No. WB.57, ALI 57-60-12 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 570203-831-895-001: MODIFICATION TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 33.00 **CONF 002 Task 570203-831-895-001: MODIFICATION TOTAL MANHOURS 71.00 ELAPSED TIME (HOURS) 35.50 APPENDICES **CONF ALL APPENDIX 01: INSPECTION REPORT FORM APPENDIX 02: ELAPSED TIME ASSUMPTION DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A300 SERVICE BULLETIN SUMMARY **CONF ALL A VIEW ON PANEL No. 3 BOTTOM SKIN: STRINGERS 10 TO 13, 16 AND 17 EITHER SIDE OF RIB 14 (STRINGER 19 SIMILAR) PROFILE BEFORE PROFILE AFTER STRINGER DATUM RIB14 A_SB_570203_7_SAAA_01_00 REAR FRONT MODIFICATION AREA NOTE: STRINGERS SPAR SPAR RIB14 A LH WING SHOWN RH WING SIMILAR Figure A-USAAA - Sheet 01 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A300 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 57 TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB 14 AREA AND REMOVAL OF STRINGER 19 TERMINATION PLATE 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 (1) Models B2-203 B2K-3C B4-103 B4-203 B4-2C C4-203 F4-203 (2) Effectivity by MSN 0045 0075 0080 0090 0101 0105 0107 0117 0129 0139 0151-0152 0154 0157 0160 0173 0175 0180 0183 0185 0200 0203 0210 0212 0218 0220 0226-0227 0234-0236 0239 0244 0247 0255-0256 0259 0261 0274 0277 0292 0299 0302 (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 001 0203 0218 22P 0236 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A300 SERVICE BULLETIN OPERATOR MSN 81T 0157 0277 0292 ABR 0152 0220 0259 AFG 0180 F2I 0235 IAW 0239 IRA 0080 0139 0151 0173 0185 0226 0256 0299 0302 IRM 0090 0160 0175 0244 KZU 0101 0117 MNB 0212 MSR 0200 0255 RUN 0075 0105 0107 0154 0183 TIW 0234 0261 0274 TNO 0045 0210 0227 0247 TSY 0129 (4) Configuration by MSN MSN CONFIGURATION 0045 0075 0101 0105 0107 0117 0129 0139 0151 0152 0154 0157 0173 0175 0180 0183 0200 0203 0210 0212 0218 0220 0227 0234 0235 0236 0239 0247 0255 0256 0259 0261 0274 0277 0292 0299 0302 002 0080 0090 0160 0185 0226 0244 001 (5) Configuration definition **CONF 001 Config. 001 is applicable to all B2 aircraft. **CONF 002 Config. 002 is applicable to all B4, C4 and F4 aircraft. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 570203B01R01 1 (1) Standard tool TOOLB01 1 Consumable CMLB01 1 NOTE (1) : KITB01 contains the component parts to modify the LH and RH wings. **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 570203B02R01 1 (1) Standard tool TOOLB01 1 Consumable CMLB01 1 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A300 SERVICE BULLETIN 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 the Inspection Service Bulletin (ISB) No. A300-57-0148, cracks were found on in-service aircraft in the same area. (2) Objective/Action The accomplishment if 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 details the removal of the stringer and 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 replaces the taper-lok bolts with interference fit parallel bolts. This Service-Bulletin also details the re-profiling of the Stringer 19 end run-out on B4 aircraft only. Before this Service-Bulletin is accomplished, the work recommended by ISB No. A300-57-0148 must be performed. After this Service-Bulletin is accomplished, refer to ISB No. A300-57-0148 for the inspection threshold and the repeat inspection intervals (Post Mod. No. 01559H0365 aircraft only). (3) Advantages This modification limits the occurrence of cracks by reducing the stress concentrations in the affected areas. Accomplishment of this Service-Bulletin will also provide an extended inspection threshold for the affected areas. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 3 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A300 SERVICE BULLETIN **CONF 001 Task 570203-831-895-001: MODIFICATION (1) INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 (2) RE-PROFILE THE STRINGER RUN-OUTS (3) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 (4) DETAILED VISUAL AND HFEC INSPECTION **CONF 002 Task 570203-831-895-001: MODIFICATION (1) INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 (2) RE-PROFILE THE STRINGER RUN-OUTS (3) RE-PROFILE THE STRINGER 19 RUN-OUT (4) REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 (5) DETAILED VISUAL AND HFEC INSPECTION **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 This Service Bulletin must be accomplished at the thresholds given in the table that follows: Table 01 (Threshold), Config. 001 - A300B2 Aircraft Re-profile Stringer Run-outs Rib 14 Area and Removal of Stringer 19 Termination Plate Compliance time (from first flight) Aircraft Action Threshold A300B2 Modify aircraft in accordance with this Service Bulletin 48000FC DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 4 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A300 SERVICE BULLETIN Table 02 (Grace Period), Config. 001 - A300B2 Aircraft Re-profile Stringer Run-outs Rib 14 Area and Removal of Stringer 19 Termination Plate Aircraft Action Compliance time (from issuance of Revision No. 04) A300B2 beyond the threshold or within 2000 FC below the threshold Inspect aircraft as given in Service Bulletin No. A300-57-0148 (ALI 57-60-12) Before 2000 FC after the original issue date of this Service Bulletin at Revision No. 04 A300B2 with no cracks found Modify aircraft as g i v e ni nt h i s Service Bulletin Before 5200 FC or 5800 FH whichever occurs first after inspection A300B2 with cracks found Contact Airbus Before next flight This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 This Service Bulletin must be accomplished at the thresholds given in the tables that follow: Table 01 (Threshold), Config. 002 - B4, C4 and F4 Aircraft Re-profile Stringer Run-outs Rib 14 Area and Removal of Stringer 19 Termination Plate Compliance time (from first flight) Aircraft Action Threshold A300B4-100 Modify aircraft in accordance with this Service Bulletin 40000 FC A300B4-200, A300C4-200 and A300F4-200 Modify aircraft in accordance with this Service Bulletin 34000 FC Table 02 (Grace Period), Config. 002 - B4, C4 and F4 Aircraft Re-profile Stringer Run-outs Rib 14 Area and Removal of Stringer 19 Termination Plate Aircraft Action Compliance time (from issuance of Revision No. 04) A300B4-100, A300B4-200, A300C4-200 and A300F4-200 beyond the threshold or within 2000 FC below the threshold Inspect aircraft as given in Service Bulletin No. A300-57-0148 (ALI 57-60-12) Before 2000 FC after the original issue date of this Service Bulletin at Revision No. 04 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 5 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A300 SERVICE BULLETIN Table 02 (Grace Period), Config. 002 - B4, C4 and F4 Aircraft Re-profile Stringer Run-outs Rib 14 Area and Removal of Stringer 19 Termination Plate Aircraft Action Compliance time (from issuance of Revision No. 04) A300B4-100 with no cracks found Modify aircraft as g i v e ni nt h i s Service Bulletin Before 5200 FC or 7100 FH whichever occurs first after inspection A300B4-200, A300C4-200, A300F4-200 with an Average Flight Time (AFT) of less than 1.5 FH/FC and with no cracks found Modify aircraft as g i v e ni nt h i s Service Bulletin Before 5600 FC or 7600 FH whichever occurs first after inspection A300B4-200, A300C4-200, A300F4-200 with an AFT of more than or equal to 1.5 FH/FC and with no cracks found Modify aircraft as g i v e ni nt h i s Service Bulletin Before 5200 FC or 11800 FH whichever occurs first after inspection A300B4, A300C4, A300F4 with cracks found Contact Airbus Before next flight This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 6 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A300 SERVICE BULLETIN **CONF 001 Task 570203-831-895-001: MODIFICATION Get Access 13.00 On Aircraft INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 3.00 RE-PROFILE THE STRINGER RUN-OUTS 16.00 REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 16.00 DETAILED VISUAL AND HFEC INSPECTION 3.00 Close-Up 15.00 TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 33.00 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-UAAAA given in Appendix 02 - Elapsed Time Assumption. **CONF 002 Task 570203-831-895-001: MODIFICATION Get Access 13.00 On Aircraft INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 3.00 RE-PROFILE THE STRINGER RUN-OUTS 16.00 RE-PROFILE THE STRINGER 19 RUN-OUT 2.00 REMOVE THE STRINGER END RUN-OUT PLATE ON STRINGER 19 19.00 DETAILED VISUAL AND HFEC INSPECTION 3.00 Close-Up 15.00 TOTAL MANHOURS 71.00 ELAPSED TIME (HOURS) 35.50 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-UAAAB given in Appendix 02 - Elapsed Time Assumption. **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. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 7 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A300 SERVICE BULLETIN **CONF 001 AIRCRAFT MEW EFFECT ON BALANCE B2 aircraft Pre Mod. No. 01559H0365 -2.720 kg (-6.00 lb) -85.680 kgm (-619.92 lb.ft.) B2 aircraft Post Mod. No. 01559H0365 -2.268 kg (-5.00 lb) -71.44 kgm (-516.60 lb.ft.) **CONF 002 AIRCRAFT MEW EFFECT ON BALANCE B4, C4 and F4 aircraft Pre Mod. No. 03491H0551 -3.033 kg (-6.69 lb) -95.540 kgm (-691.21 lb.ft.) B4, C4 and F4 aircraft Post Mod. Nos. 01559H0365 and 03491H0551 -3.210 kg (-7.08 lb) -101.110 kgm (-731.50 lb.ft.) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Airworthiness Directive (AD) WB.57 Airworthiness Limitation Item (ALI) 57-60-12 Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00 28-10-00 28-11-00 28-11-14 28-21-19 28-22-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-30-10 57-13-10 Repair Instruction 571-40785 571-40789 Service Bulletin (SB) A300-57-0148 Service Information Letter (SIL) 51-012 57-079 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-30-29 51-30-30 51-30-38 51-30-41 51-30-43 51-31-00 51-40-12 51-40-20 51-40-21 Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Airworthiness Directive (AD) WB.57 Airworthiness Limitation Item (ALI) 57-60-12 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 8 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A300 SERVICE BULLETIN Aircraft Maintenance Manual (AMM) 20-21-12 20-31-00 28-00-00 28-10-00 28-11-00 28-11-14 28-21-19 28-22-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-30-10 57-13-10 Repair Instruction 571-40785 571-40789 Service Bulletin (SB) A300-57-0148 Service Information Letter (SIL) 51-012 57-079 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-00 51-30-29 51-30-30 51-30-38 51-30-41 51-30-43 51-31-00 51-40-12 51-40-20 51-40-21 Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED Structural Repair Manual (SRM) 57-13-11 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 9 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A300 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 10 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A300 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Kit 570203B01R01 Kit 570203B02R01 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 570203B01R01 Cost 2,360.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 570203B02R01 Cost 2,360.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 11 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A300 SERVICE BULLETIN B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 570203B01R01 ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEE NOTES 1 NSA5475-6K7 20 NUT 2 NSA5476VHK6-11 20 BOLT 3 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 570203B02R01 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. 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 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 12 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A300 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 interested in obtaining the FTI tool kit 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 For kit number FTI-A300-57-0203-1, refer to Fatigue Technology Inc. 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 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 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 13 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A300 SERVICE BULLETIN Standard tool TOOLB01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES DKA300570203-1 Durable Tooling 1 (1) EKA300570203-1 Expendable Tooling 1 (2) FTIA300570203-1 Capital Tooling 1 (3) NOTE (1) : Durable tooling: Ref. DK-A300-57-0203-1 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-A300-57-0203-1 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-A300-57-0203-1 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 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 14 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A300 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 570203-831-895-001 - 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE : The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE : The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE : Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE : This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 15 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A300 SERVICE BULLETIN the aircraft can be put back into a serviceable condition. Task Associated Data **CONF 001 Zone 543 550 643 650 Access Panel 543DB 550BB 643DB 650BB Manpower TOTAL MANHOURS 66.00 ELAPSED TIME (HOURS) 33.00 **CONF 002 Zone 543 550 643 650 Access Panel 543DB 550BB 643DB 650BB Manpower TOTAL MANHOURS 71.00 ELAPSED TIME (HOURS) 35.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 570203-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-30-29 51-30-38 51-40-12 51-40-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (b) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (c) Remove and install fasteners in accordance with SRM 51-30-29. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 16 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A300 SERVICE BULLETIN (d) Apply sealant in accordance with SRM 51-40-20. (e) Renew the protective finish in accordance with SRM 51-40-12. (f) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM 51-30-38. (2) Subtask 570203-839-401-001 - ADMINISTRATIVE Manpower Resources Skills UTILITY Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 570203-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-30-29 51-30-38 51-40-12 51-40-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (b) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (c) Remove and install fasteners in accordance with SRM 51-30-29. (d) Apply sealant in accordance with SRM 51-40-20. (e) Renew the protective finish in accordance with SRM 51-40-12. (f) Obtain fastener hole diameters and drill and ’deburr’ data in accordance with SRM 51-30-38. (2) Subtask 570203-839-401-001 - 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 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 17 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A300 SERVICE BULLETIN **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 570203-941-401-001 - JOB SET-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) 28-00-00, Page Block 301 28-00-00, Page Block 401 28-10-00, Page Block 301 28-11-00, Page Block 101 28-11-14, Page Block 401 28-21-19, Page Block 401 28-22-00, 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. 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: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 18 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A300 SERVICE BULLETIN (a) Defuel the aircraft, refer to AMM 28-22-00, Page Block 301. (b) Put the access platform(s) in position. (c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between Rib 13 and Rib 15, refer to AMM 28-11-14, 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. (e) Remove the vent pipes from the work area as necessary, refer to AMM 28-00-00, Page Block 401. (f) Protect or remove the outboard tank booster pumps, refer to AMM 28-21-19, Page Block 401. **CONF 002 (1) Subtask 570203-941-401-001 - JOB SET-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) 28-00-00, Page Block 301 28-00-00, Page Block 401 28-10-00, Page Block 301 28-11-00, Page Block 101 28-11-14, Page Block 401 28-21-19, Page Block 401 28-22-00, 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. NOTE : The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 19 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A300 SERVICE BULLETIN - Parking brake applied - Aircraft electrical network de-energized - Hydraulic system s depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Defuel the aircraft, refer to AMM 28-22-00, Page Block 301. (b) Put the access platform(s) in position. (c) Remove the manhole covers 543DB (643DB) and 550BB (650BB) from between Rib 13 and Rib 15, refer to AMM 28-11-14, 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. (e) Remove the vent pipes from the work area as necessary, refer to AMM 28-00-00, Page Block 401. (f) Protect or remove the outboard tank booster pumps, refer to AMM 28-21-19, Page Block 401. **CONF ALL C. PROCEDURE NOTE : The procedures that follow must be accomplished on the LH and RH wings. **CONF 001 (1) Subtask 570203-250-401- 001 - INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 Work Zones and Access Panels Zone Access/Work location 543 Access Panel 543DB , Panel 550BB 643 Access Panel 643DB , Panel 650BB Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME References Service Bulletin (SB) A300-57-0148 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 20 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A300 SERVICE BULLETIN (a) Inspect the Stringer Runouts at Stringers 10 thru 17 in accordance with Service Bulletin No. A300-57-0148. 1 If cracks are found, contact AIRBUS before next flight. 2 If there are no findings, continue with the worksteps that follow. (2) Subtask 570203-831-401-001 - 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 Stringer 13 Stringer 16 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 13 Stringer 16 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 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 Service Information Letter (SIL) 57-079 Structural Repair Manual (SRM) 51-23-00 51-40-12 Fig. A-UBAAA LOCATION AND AREA OF MODIFICATION Sheet 01 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 21 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A300 SERVICE BULLETIN NOTE : The worksteps that follow are to be accomplished on both the LH and RH wings. Refer to Fig. A-UBAAA Sheet 01 (a) Cut the stringers 10, 11, 12 and 17 (and on aircraft Pre Mod. No. 01559H0365, stringers 13 and 16) on bottom skin panel No. 3, adjacent to Rib 14, to the new contour as follows: NOTE : It is not necessary to cut stringers 13 and 16, if the instructions in SIL 57-079 have been done previously. 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 AG ENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with Non Aqueous Cleaner 08BAA9 As required in accordance with SRM 51-23-00 and refer to 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 in accordance with SRM 51-40-12 and refer to AMM 20-31-00. (3) Subtask 570203-831-402-001 - 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 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 22 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A300 SERVICE BULLETIN Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Kit 570203B01R01 ITEM NEW PART N˚ QTY (UM) KEYWORD SEE NOTES 1 NSA5475-6K7 20 NUT 2 NSA5476VHK6-11 20 BOLT 3 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 DKA300570203-1 Durable Tooling 1 (1) EKA300570203-1 Expendable Tooling 1 (2) FTIA300570203-1 Capital Tooling 1 (3) NOTE (1) : Durable tooling: Ref. DK-A300-57-0203-1 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-A300-57-0203-1 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-A300-57-0203-1 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. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 23 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A300 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 20-31-00 Non Destructive Test Manual (NTM) 51-30-10 Part 1 Structural Repair Manual (SRM) 51-23-00 51-30-30 51-30-41 51-30-43 51-31-00 51-40-20 51-40-21 Fig. A-UBBAA STRINGER END RUN-OUT PLATE REMOVAL Sheet 01 Fig. A-UBDAA SPLIT SLEEVE POSITION ON REAR SPAR Sheet 01 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 Bolt-Hi Lok NSA5476VHK6-11 Item 2 20 Nut NSA5475-6K7 Item 1 40 Washer-Special NSA5353-06A Item 3 (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) in accordance with SRM 51-40-21. 2 Remove and discard these items in accordance with SRM 51-30-30: 10 Nut Item (1) 10 Taperlock Bolt Item (2) 1 Stringer End Run-Out Plate Item (4) WARNING : USE SOLVENTS/CLEANING AG ENTS, 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 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 24 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A300 SERVICE BULLETIN to clean the surfaces of the rear spar and the stringer flange which were connected to the Stringer End Run-Out Plate, Item (4) in accordance with SRM 51-40-21 and SRM 51-23-00 and refer to AMM 20-31-00. 4 Use procedure C of the Eddy Current Technique NTM 51-30-10 Part 1 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: FTIA300570203-1 Capital Tooling 1 DKA300570203-1 Durable Tooling 1 EKA300570203-1 Expendable Tooling 1 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. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 25 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A300 SERVICE BULLETIN 10 Cold expand and final ream the holes. Use the tools given as follows, refer to Fig. A-UBDAA Sheet 01 and in accordance with SRM 51-30-41: 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 CBSD-10-3-N-1-.3695 11 Countersink the holes to 100 degrees for the new Bolts, Item 2 in accordance with SRM 51-30-43. 12 Deburr the edges of the holes. 13 Apply Brushable Fuel Resistant Coating 06HAA1 As required under the head of the new Bolts, Item 2, refer to AMM 20-31-00. 14 On each wing, assemble in each of the non-slave bolted holes the interference fit 5 Bolt-Hi Lok NSA5476VHK6-11 Item 2 and the 5 Nut NSA5475-6K7 Item 1 with a maximum quantity of 2 Washer-Special NSA5353-06A Item 3 for each of the five Bolts, Item 2. a Torque tighten the Nuts, Item 1 to between 2.373 and 2.599 m.daN (210 and 230 lbf.in.) in accordance with SRM 51-30-30 and SRM 51-31-00. 15 Remove the five slave bolts. 16 Do worksteps 6_ thru 14_ for the holes that remain. (c) Do the detailed visual and HFEC inspection of the stringer run-outs as per SUBTASK 570203-750-401 001 DE TAILED VISUAL AND H FEC INSPECTION . DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 26 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A300 SERVICE BULLETIN (4) Subtask 570203-750- 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 13 from Stringer 16 to Stringer 17 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 13 from Stringer 16 to 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) 57-13-10 Repair Instruction 571-40785 571-40789 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, 13, 16 and 17, refer to NTM 57-13-10. (c) If there are signs of cracks or damage: - for stringer 13, refer to Repair Instruction 571-40785 - for stringer 16, refer to Repair Instruction 571-40789 - for 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 st ringer damage (cra cks), refer to APPENDIX 01: INSPECTION REPORT FORM . DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 27 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A300 SERVICE BULLETIN **CONF 002 (1) Subtask 570203-250-401- 001 - INSPECT THE STRINGER RUN-OUTS AT STRINGERS 10 THRU 17 Work Zones and Access Panels Zone Access/Work location 543 Access Panel 543DB , Panel 550BB 643 Access Panel 643DB , Panel 650BB Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME References Service Bulletin (SB) A300-57-0148 (a) Inspect the Stringer Runouts at Stringers 10 thru 17 in accordance with Service Bulletin No. A300-57-0148. 1 If cracks are found, contact AIRBUS before next flight. 2 If there are no findings, continue with the worksteps that follow. (2) Subtask 570203-831-401-002 - 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 Stringer 13 Stringer 16 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 13 Stringer 16 Manpower Resources Manhours 16.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 28 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A300 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 Service Information Letter (SIL) 57-079 Structural Repair Manual (SRM) 51-23-00 51-40-12 Fig. A-UBAAB LOCATION AND AREA OF MODIFICATION Sheet 01 NOTE : The worksteps that follow are to be accomplished on both the LH and RH wings. Refer to Fig. A-UBAAB Sheet 01 (a) Cut the stringers 10, 11, 12 and 17 (and on aircraft Pre Mod. No. 01559H0365, stringers 13 and 16) on bottom skin panel No. 3, adjacent to Rib 14, to the new contour as follows: NOTE : It is not necessary to cut stringers 13 and 16, if the instructions in SIL 57-079 have been done previously. 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-UBAAB Sheet 01 . NOTE : Dimension ’X’ is 31.50 mm (1.24 in.) for stringers 10, 11, 12 and 17 and 25.40 mm (1.00 in.) for stringers 13 and 16 (aircraft Pre Mod. No. 01559H0365 only). 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 AG ENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with: Non Aqueous Cleaner 08BAA9 As required DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 29 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A300 SERVICE BULLETIN in accordance with SRM 51-23-00 and refer to 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 in accordance with SRM 51-40-12 and refer to AMM 20-31-00. (3) Subtask 570203-831-403-001 - 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) 51-23-00 51-40-12 Fig. A-UBCAA MODIFICATION TO END OF STRINGER 19 Sheet 01 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 30 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A300 SERVICE BULLETIN 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 AG ENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. 4 Clean the cut surfaces with: Non Aqueous Cleaner 08BAA9 As required in accordance with SRM 51-23-00 and refer to 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 in accordance with SRM 51-40-12 and refer to AMM 20-31-00. (4) Subtask 570203-831-402-002 - 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 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 31 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A300 SERVICE BULLETIN Manpower Resources Manhours 19.00 Minimum number of person 2 Subtask elapsed time 9.50 Skills AIRFRAME Material necessary to do the job Kit 570203B02R01 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 DKA300570203-1 Durable Tooling 1 (1) EKA300570203-1 Expendable Tooling 1 (2) FTIA300570203-1 Capital Tooling 1 (3) NOTE (1) : Durable tooling: Ref. DK-A300-57-0203-1 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-A300-57-0203-1 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-A300-57-0203-1 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. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 32 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A300 SERVICE BULLETIN References Aircraft Maintenance Manual (AMM) 20-31-00 Non Destructive Test Manual (NTM) 51-30-10 Part 1 Structural Repair Manual (SRM) 51-23-00 51-30-30 51-30-41 51-30-43 51-31-00 51-40-20 51-40-21 Fig. A-UBBAB STRINGER END RUN-OUT PLATE REMOVAL Sheet 01 Fig. A-UBDAA SPLIT SLEEVE POSITION ON REAR SPAR Sheet 01 NOTE : The worksteps that follow are to be accomplished on both the LH and RH wings. Refer to Fig. A-UBBAB Sheet 01 (a) Get these items from KITB02 to modify the LH and RH wings: 10 Bolt-Hi Lok NSA5476VHK6-11 Item 2 10 Bolt-Hi Lok NSA5476VHK6-14 Item 3 20 Nut NSA5475-6K7 Item 1 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) in accordance with SRM 51-40-21. 2 Remove and discard these items in accordance with SRM 51-30-30: 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 AG ENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 33 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A300 SERVICE BULLETIN 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) in accordance with SRM 51-40-21 and SRM 51-23-00 and refer to AMM 20-31-00. 4 Use procedure C of the Eddy Current Technique NTM 51-30-10 Part 1 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: FTIA300570203-1 Capital Tooling 1 DKA300570203-1 Durable Tooling 1 EKA300570203-1 Expendable Tooling 1 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 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 34 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A300 SERVICE BULLETIN 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 in accordance with SRM 51-30-41: 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 CBSD-10-3-N-1-.3695 11 Countersink the holes to 100 degrees for the new Bolts, Items 2 and 3 in accordance with SRM 51-30-43. 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. 14 On each wing, assemble in each of the non-slave bolted holes 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.) in accordance with SRM 51-30-30 and SRM 51-31-00. 15 Remove the five slave bolts. 16 Do worksteps 6_ thru 12_ for the holes that remain. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 35 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A300 SERVICE BULLETIN 17 On each wing, for the five holes that remain, assemble 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.) in accordance with SRM 51-30-30 and SRM 51-31-00. (c) Do the detailed visual and HFEC inspection of the stringer run-outs as per SUBTASK 570203-750-401 001 DE TAILED VISUAL AND H FEC INSPECTION . (5) Subtask 570203-750- 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 13 from Stringer 16 to Stringer 17 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 13 from Stringer 16 to 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) 57-13-10 Repair Instruction 571-40785 571-40789 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. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 36 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A300 SERVICE BULLETIN (b) Do a detailed visual and a HFEC inspection of the stringer run-outs at stringers 10, 11, 12, 13, 16 and 17, refer to NTM 57-13-10. (c) If there are signs of cracks or damage: - for stringer 13, refer to Repair Instruction 571-40785 - for stringer 16, refer to Repair Instruction 571-40789 - for 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 st ringer damage (cra cks), refer to APPENDIX 01: INSPECTION REPORT FORM . **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 570203-914-401-001 - APPLY SEALANT 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 13 Stringer 16 Stringer 19 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 13 Stringer 16 Stringer 19 Manpower Resources Skills AIRFRAME DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 37 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A300 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) 51-40-21 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 Washers, Item 4 in accordance with SRM 51-40-21. (b) Allow the sealant to cure in accordance with SRM 51-40-21. (2) Subtask 570203-942-401-001 - 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) 28-00-00, Page Block 401 28-11-00, Page Block 501 28-11-14, Page Block 401 28-21-19, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the vent pipes in the work area as necessary, refer to AMM 28-00-00, Page Block 401. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 38 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A300 SERVICE BULLETIN (c) Remove the protection or install the outboard tank booster pumps, refer to AMM 28-21-19, Page Block 401. (d) Install the manhole covers 543DB (643DB) and 550BB (650BB) between Rib 13 and Rib 15, refer to AMM 28-11-14, Page Block 401. (e) Remove the access platform(s). (f) Refuel the aircraft and inspect for leaks, refer to AMM 28-11-00, Page Block 501. (g) Put the aircraft back to its initial configuration. **CONF 002 (1) Subtask 570203-914-401-001 - APPLY SEALANT 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 13 Stringer 16 Stringer 19 650 Work location from Rib 14 to Rib 15 from Stringer 10 to Stringer 12 Stringer 17 Stringer 13 Stringer 16 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) 51-40-21 NOTE : The worksteps that follow are to be accomplished on both the LH and RH wings. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 39 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A300 SERVICE BULLETIN (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 Washers, Item 4 in accordance with SRM 51-40-21. (b) Allow the sealant to cure in accordance with SRM 51-40-21. (2) Subtask 570203-942-401-001 - 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) 28-00-00, Page Block 401 28-11-00, Page Block 501 28-11-14, Page Block 401 28-21-19, Page Block 401 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the vent pipes in the work area as necessary, refer to AMM 28-00-00, Page Block 401. (c) Remove the protection or install the outboard tank booster pumps, refer to AMM 28-21-19, Page Block 401. (d) Install the manhole covers 543DB (643DB) and 550BB (650BB) between Rib 13 and Rib 15, refer to AMM 28-11-14, Page Block 401. (e) Remove the access platform(s). (f) Refuel the aircraft and inspect for leaks, refer to AMM 28-11-00, Page Block 501. (g) Put the aircraft back to its initial configuration. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 40 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A300 SERVICE BULLETIN **CONF 001 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 (PRE MOD. No. 01559H0365 AND PRE SIL 57−079 STRINGER RUN−OUTS A_SB_570203_7_BAAA_01_00 AIRCRAFT ONLY) A Figure A-UBAAA - Sheet 01 LOCATION AND AREA OF MODIFICATION DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 41 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A300 SERVICE BULLETIN **CONF 002 XX A_SB_570203_7_BAAB_01_00 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 CONTOUR BEFORE MODIFICATION RIB14 DATUM A EXAMPLE FOR ALL AFFECTED STRINGERS 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 (PRE MOD. No. 01559H0365 AND PRE SIL 57−079 STRINGER RUN−OUTS AIRCRAFT ONLY) A Figure A-UBAAB - Sheet 01 LOCATION AND AREA OF MODIFICATION DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 42 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A300 SERVICE BULLETIN **CONF 001 A PLAN VIEW LH WING BOTTOM SKIN PANEL No. 3 A REAR SPAR DATUM INBD STRINGER END RUN−OUT PLATE A_SB_570203_7_BBAA_01_00 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 (1) 1 (2) 2 3 (4)(1) 1 (2) 2 3 RIB14 STGR19 DATUM DATUM Figure A-UBBAA - Sheet 01 STRINGER END RUN-OUT PLATE REMOVAL DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 43 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A300 SERVICE BULLETIN **CONF 002 INBD A STRINGER END RUN−OUT PLATE A_SB_570203_7_BBAB_01_00 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) Figure A-UBBAB - Sheet 01 STRINGER END RUN-OUT PLATE REMOVAL DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 44 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A300 SERVICE BULLETIN **CONF 002 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 A_SB_570203_7_BCAA_01_00 FRONT SPAR DATUM REAR SPAR DATUM A STGR10 STGR11 STGR12 STGR13 STGR16 STGR17 STGR19 F W D INBD LH WING SHOWN RH WING SIMILAR Figure A-UBCAA - Sheet 01 MODIFICATION TO END OF STRINGER 19 DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 45 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A300 SERVICE BULLETIN **CONF ALL OR OUTBOARD PERMITTED. SPAR DATUM PLAN VIEW SPLIT SLEEVE POSITION ± 10° SPLIT SLEEVE ON INBOARD IN RELATION TO SPAR DATUM. A_SB_570203_7_BDAA_01_00 Figure A-UBDAA - Sheet 01 SPLIT SLEEVE POSITION ON REAR SPAR DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 46 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A300 SERVICE BULLETIN APPENDIX 01: INSPECTION REPORT FORM **CONF ALL Record the location of cracks on the Inspection Report Form shown below: DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A300 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 A300−57−0203 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 13 STRINGER 16 STRINGER 17 CRACKS FOUND YES: PROVIDE DETAILS BELOW NO A_SB_570203_7_RAAA_01_00 Figure A-URAAA - Sheet 01 INSPECTION REPORT FORM DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A300 SERVICE BULLETIN APPENDIX 02: ELAPSED TIME ASSUMPTION **CONF 001 ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300−57−0203 SB ELAPSED TIME (HOURS) MH ET/S TOTAL MANHOURS SB ELAPSED TIME 66.00 33.00 STEPS MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02 THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01 02 NOTE: PER : : IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. 5 1 01 52 02 53 03 50 15.00 7.502 DETAILED VISUAL AND HFEC INSPECTION 3.00 1.502 REMOVE THE STRINGER END CLOSE−UP 3.00 1.502 16.00 8.002 16.00 8.002RE−PROFILE THE STRINGER RUN−OUTS RUN−OUT PLATE ON STGR19 13.00 6.502JOB SET−UP INSPECT THE STRINGER RUN−OUTS AT STGR10 THRU STGR17 A_SB_570203_7_AAAA_01_01 Figure A-UAAAA - Sheet 01 ELAPSED TIME ASSUMPTION DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A300 SERVICE BULLETIN APPENDIX 02: ELAPSED TIME ASSUMPTION **CONF 002 ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300−57−0203 SB ELAPSED TIME (HOURS) MH ET/S TOTAL MANHOURS SB ELAPSED TIME 71.00 35.50 STEPS MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02 THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01 02 NOTE: PER : : IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. 51 0 1 5 2 0 2 5 3 0 3 50 3.00 1.502DETAILED VISUAL AND HFEC INSPECTION 19.00 9.502REMOVE THE STRINGER END 15.00 7.502CLOSE−UP 13.00 6.502JOB SET−UP 2.00 1.002RE−PROFILE THE STGR19 RUN−OUT 3.00 1.502 RUN−OUT PLATE ON STRG19 16.00 8.002RE−PROFILE THE STRINGER RUN−OUTS INSPECT THE STRINGER RUN−OUTS AT STGR10 THRU STGR17 40 A_SB_570203_7_AAAB_01_01 Figure A-UAAAB - Sheet 01 ELAPSED TIME ASSUMPTION DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 2 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A300 SERVICE BULLETIN REPORTING SHEET TITLE: WINGS - OUTER WING - RE-PROFILE STRINGER RUN-OUTS RIB 14 AREA AND REMOVAL OF STRINGER 19 TERMINATION PLATE 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 concer ned (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 F A X :( + 3 3 )56 19 32 80 6 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 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A300 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 F A X:( 3 3 )56 19 34 25 1 Or via your Resident Customer Support Office. DATE: Jan 21/94 SERVICE BULLETIN No.: A300-57-0203 REVISION No.: 04 - Feb 18/15 Page: 1 7 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. --- 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.