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REVISION No. : 7 -2038 03 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : NONE ATA SYSTEM : 57 This page transmits Revision No. 03 of Service Bulletin No. A310-57-2038. ADDITIONAL WORK No additional work is required by this revision for aircraft inspected by any previous revision. REASON Revision No. 03 is issued to cancel the Airworthiness Directive (Consigne de Navigabilite) No. 89-195-100(B) and to add the Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132(B). The effectivity has also been updated. CHANGES Lay-out changes due to computerization of this revision are not identified. SUMMARY - REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES : The Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132(B) is added. - EFFECTIVITY : The effectivity is updated. SERVICE BULLETIN Planning Information - EFFECTIVITY : The effectivity is updated. The Standard sentence concerning Airbus Industrie proprietary information is added. - REASON, para.(5)(a) : The Airworthiness Directive (Consigne de Navigabilite) No. 89-195-100(B) is replaced by the Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132(B). - REASON, para.(5)(c) : The MRB document reference is amended. - APPROVAL : The approval sentence is updated. Accomplishment Instructions - GENERAL : A WARNING is added to make sure that the aircraft is electrically grounded. A WARNING is added to make sure that all the warnings and all the cautions given in the referenced procedures are obeyed. - CLOSE-UP : The CML reference for the sealant is specified.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 1 of 2 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Material Information - LIST OF MATERIALS - OPERATOR SUPPLIED : The sealant and the CML reference for the sealant is specified. 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 This is only applicable for Revision No. 2 and subsequent. If information is required for Revisions issued previous to this, please check your copies of the Revision Transmittal Sheets or contact Airbus Industrie. Revision No. 2 was issued to include the use of High Frequency Eddy Current (HFEC) inspection as an alternative to X-ray inspection. REVISION SEQUENCE ORIGINAL : Nov 06/89 REVISION No. : 01 - Dec 05/90 REVISION No. : 02 - Jan 04/96 REVISION No. : 03 - Sep 04/98

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 2 Printed in FranceA310 

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REVISION No. : 7 -2038 03 SERVICE BULLETIN SUMMARY AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 FThis summary is for information only and is not approved for modification of the aircraft TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : NONE ATA SYSTEM : 57 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During full scale fatigue testing, cracks were discovered in the bottom skin stringers adjacent to rib 14 at 50,000 simulated flight cycles (FC). There is a possibility of similar cracks appearing in service which will lead to rupture of the stringers. This may be followed by cracking of the bottom skin which will require extensive repairs. At rib 14 on the bottom skin, mandatory X-ray or HFEC inspections of the stringer runouts are required at stringers 6, 7, 8 and 9. Accomplishment of this Inspection Service Bulletin is mandatory in accordance with Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132(B). EFFECTIVITY This Service Bulletin is applicable to these customer(s): FDX, THY SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY None REFERENCES/REPERCUSSIONS None TFU :None OEB :None AOT :None SIL : LIFE LIMIT : None LINE MAINTENANCE AFFECTED : None None OTHER : NATURE OF THE WORK AIRCRAFT : YES EQUIPMENT : NO

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 1 of 2 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN SUMMARY HARD : NO SOFT : NO OBRM : NO COMPLIANCE Mandatory MANPOWER MANHOURS TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0 MATERIAL INFORMATION AIRCRAFT DATA None EQUIPMENT DATA None APPENDICES None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 2 Printed in FranceA310 

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REVISION No. : 7 -2038 03 SERVICE BULLETIN
AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : NONE ATA SYSTEM : 57 1. PLANNING INFORMATION A. EFFECTIVITY (1) Aircraft models : A310-203, A310-222 (2) Aircraft Customer and Fleet No. MSN Kit No. Qty of kits Config No. 572038 THY008 172 FDX401-405 191,201,230,233,237 407-408 254,257 424-426 241,264,245 428 248 446-450 224,251,260,217,162 This document contains Airbus Industrie PROPRIETARY INFORMATION and shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie 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 purpose of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie’s prior written consent. (3) Spares None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 1 of 9 Printed in FranceInspection Method Inspection Threshold Inspection Interval X-Ray 12,000 FC 9,200 FC HFEC 12,000 FC 12,000 FC

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REVISION No. : -2038 03 SERVICE BULLETIN
B. REASON (1) History During full scale fatigue testing, cracks were discovered in the bottom skin stringers adjacent to rib 14 at 50,000 simulated flight cycles (FC). There is a possibility of similar cracks appearing in service which will lead to rupture of the stringers. This may be followed by cracking of the bottom skin which will require extensive repairs. (2) Objective/Action Mandatory X-ray or High Frequency Eddy Current (HFEC) inspections of the stringer runouts are required at stringers 6, 7, 8 and 9 adjacent to rib 14. (3) Advantages Early detection of cracks can prevent costly and time consuming repairs. (4) Operational/Maintenance Consequences None (5) Accomplishment Timescale (a) Accomplishment of this Inspection Service Bulletin is mandatory in accordance with Airworthiness Directive (Consigne de Navigabilite) No. 92-106-132(B). At rib 14 on the bottom skin, mandatory X-ray or HFEC inspections of the stringer runouts are required at stringers 6, 7, 8 and 9 within the number of FC which follow:

(b) For aircraft which have exceeded the first inspection threshold detailed in paragraph (5)(a), this inspection is required within 1,500 FC from the receipt of this Service Bulletin. (c) Thresholds and intervals given in this Service Bulletin are established and valid for aircraft operated with the individual average airborne flight time of 96 min (1.6h). Therefore when aircraft are operated with an average airborne flight time greater than 96 min (1.6h), inspection thresholds and intervals should be adjusted in accordance with the instructions given in the A310 Maintenance Review Board Document, Section D, para. 8.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 2 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN
NOTE : When an aircraft is operated with an average airborne flight time of less than 96 min (1.6h), inspection thresholds and intervals are valid and should not be adjusted. For this Service Bulletin, the Fatigue Rating (FR) to be applied to determine the adjustment factor is 0.13. Additional flight flexibility, as given in paragraph (5)(b) for aircraft over the inspection threshold, is not to be adjusted by this adjustment factor. (d) The number of touch and go flights can be neglected when they are less than five percent of the total number of flights between two consecutive inspections. When the percentage of touch and go flights is more than five percent of the total number of flights between two consecutive inspections, each touch and go flight beyond five percent has to be counted as a flight cycle. A touch and go is a landing in which an aircraft touches the runway and does not come to a complete stop before commencing an additional flight. C. DESCRIPTION To accomplish this Service Bulletin it is necessary to: (1) Defuel the aircraft. (2) Gain access to the LH and RH outer wing fuel tanks. (3) Remove sealant from the inspection area. (4) Do an X-ray or HFEC inspection of the bottom skin stringer runouts adjacent to rib 14. (5) Repair as necessary. (6) Replace any removed sealant. (7) Close up. D. APPROVAL The technical content of this Service Bulletin has been approved under the Authority of the DGAC Design Organisation Approval No. F.JA.02. E. MANPOWER This Service Bulletin is written for an aircraft in a maintenance status. The manhours/elapsed time estimates do not include the time to prepare for the inspection, non-productive elapsed time or administration. MANHOURS Gain Access 2.0 Inspection 2.0 Close up 2.0

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 3 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN
TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0 F. MATERIAL - COST AND AVAILABILITY None G. TOOLING - PRICE AND AVAILABILITY None H. WEIGHT AND BALANCE None I. REFERENCES Aircraft Maintenance Manual (AMM) : 12-11-28, 28-11-22, 28-11-24, 28-25-00 Nondestructive Testing Manual (NTM) : Part 2, 57-25-66, Part 6, 57-25-66 Structural Repair Manual (SRM) : 51-76-20 J. PUBLICATIONS AFFECTED None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 4 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN
2. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: MAKE SURE THAT THE AIRCRAFT IS ELECTRICALLY GROUNDED. (1) Preparation (a) Defuel the aircraft (Refer to AMM: 28-25-00, P. Block 301). (b) Put the access platforms in position. (c) Remove access doors 540HB, 550AB (LH) and 640HB, 650AB (RH) (Refer to AMM: 28-11-22, P. Block 401 andAMM: 28-11-24, P. Block 401). (d) Remove sealant from the inspection area with a nonmetalic spatula (Refer to SRM: 51-76-20, P. Block 201 and Refer to Figure 1 ). (2) Standard Practices None B. INSPECTION (1) For the X-ray inspection do the instructions that follow : (a) Do an X-ray inspection of the stringer runouts at stringers 6, 7, 8 and 9 (Refer to Figure 1 and NTM Part 2: 57-25-66). (b) If no cracks are found, repeat the inspection at intervals of no more than 9 200 FC. (c) If a crack is found, refer to the REPAIR paragraph. (2) For the HFEC inspection do the instructions that follow : (a) Do an HFEC inspection of the stringer runouts at stringers 6, 7, 8 and 9 (Refer to Figure 1 and NTM Part 6: 57-25-66). (b) If no cracks are found, repeat the inspection at intervals of no more than 12 000 FC. (c) If a crack is found, refer to the REPAIR paragraph. C. REPAIR If a crack is found, contact AIRBUS INDUSTRIE and carry out an approved repair before further flight. D. TEST None E. CLOSE-UP (1) Reseal the fuel tanks by applying a fillet ofSealant (Mat. No. 09-002) at the junction of the rib and the stringer runout where sealant has been removed in paragraph A.(1)(d) (Refer to Figure 1

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 5 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN and SRM: 51-76-20, P. Block 201). (2) Replace access doors 540HB, 550AB (LH) and 640HB, 650AB (RH) (Refer toAMM: 28-11-22, P. Block 401 andAMM: 28-11-24, P. Block 401). (3) Make sure that the work areas are clean and clear of tools and other items of equipment. (4) Refuel the aircraft (Refer to AMM: 12-11-28, P. Block 301). (5) Do an external inspection of any repaired areas for leaks. (6) Remove the access platforms. (7) Report all findings including nil findings to AIRBUS INDUSTRIE. F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 6 Printed in FranceA310 

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REVISION No. : -2038 03 SERVICE BULLETIN

Figure 1 Sheet 1

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 7 Printed in France Inspection AreaA310 

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REVISION No. : -2038 03 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 8 Printed in France This Page Intentionally Left BlankA310 

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REVISION No. : -2038 03 SERVICE BULLETIN
3. MATERIAL INFORMATION A. LIST OF COMPONENTS None B. SPECIAL TOOLS None C. LIST OF MATERIAL - OPERATOR SUPPLIED DESCRIPTION REFERENCE TO CML QTY PER A/C Sealant (Mat. No. 09-002) As required D. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 9 Printed in FranceA310 

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REVISION No. : 7 -2038 03 SERVICE BULLETIN ACCEPTANCE/REJECTION SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : NONE ATA SYSTEM : 57

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW Please fill : ...REJECTED ...WILL BE EMBODIED ...EFFECTIVITY

This SB can only be incorporated in your "customized" documentation within the agreed time schedule in so far as this sheet returned to us on purchase date and signed by a duly authorized and empowered officer or representative.

FROM : AIRLINE :

NAME :

DATE : Please return to : AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : AI/SE-D32 Technical Data and Documentation Services FAX : (+33) 5 61 93 28 06

DATE : Nov 06/89 SERVICE BULLETIN No. : -57 - Sep 04/98 PAGE : 1 of 1 Printed in France