# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : None This page transmits Revision No. 04 of Service Bulletin No. A310-57-2038 ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON This Service Bulletin has been issued at Revision 04 to update the inspection thresholds and intervals to be in line with the Extended Service Goal (ESG) requirements. Other minor changes to the new Service Bulletin format have been added. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Reference to Airworthiness Directive 92-106-032(B) removed. Evaluation table added. — EFFECTIVITY . Operator KYV added. Operator THY deleted. — MANPOWER . Config. 01 added. PLANNING INFORMATION : — EFFECTIVITY . 1.A. Operator KYV added. Operator THY deleted. Effectivity by MSN and Kit/Configuration added. Airbus Industrie changed to AIRBUS.

# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — DESCRIPTION . 1.D. Config. 01 added. — COMPLIANCE — Accomplishment Timescale . 1.E.(2) Inspection thresholds and intervals updated. — APPROVAL . 1.F. Approval statement updated. — MANPOWER . 1.G. Sentence updated. Config. 01 added. — REFERENCES . 1.J. ESPM 20-55-00 added. — PUBLICATIONS AFFECTED . 1.K. Maintenance Planning Document added. ACCOMPLISHMENT INSTRUCTIONS : — GENERAL — Preparation . 3.A.(1) Config. 01 added. — INSPECTION . 3.B. Config. 01 added. . 3.B.(1)(a)2 Inspection intervals updated. . 3.B.(1)(b)2 Inspection intervals updated. — REPAIR . 3.C. Config. 01 added. . 3.C.(1)(a) Airbus Industrie changed to AIRBUS. — CLOSE-UP . 3.E. Config. 01 added. Paragraph reference updated. . 3.E.(1)(g) Airbus Industrie changed to AIRBUS. — Figure 1

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# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . Config. 01 added. 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. 02 and subsequent. If information is required for Revisions issued previous to this, please check your copies of the Revision Transmittal Sheets or contact AIRBUS. Revision No. 02 was issued to include the use of High Frequency Eddy Current (HFEC) inspection as an alternative to X-ray inspection. Revision No. 03 was 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). REVISION SEQUENCE ORIGINAL : Nov 06/89 REVISION No. : 01 — Dec 05/90 REVISION No. : 02 — Jan 04/96 REVISION No. : 03 — Sep 04/98 REVISION No. : 04 — Oct 19/06

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# @ A310 SERVICE BULLETIN SUMMARY

7 DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : 1 of 2 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : None 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.

EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) : FDX KYV EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION SB No 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 DEFUELLING/VENTILLATION Yes KIT PRICE (USD) No AIRBUS Kit

# @ A310 SERVICE BULLETIN SUMMARY

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None NATURE OF THE WORK AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No MANPOWER Config. 01

MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0

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# @ A310 SERVICE BULLETIN

7 DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : 1 of 11 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM : 57 TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : None 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 A. EFFECTIVITY (1) Models 310-203 310-222 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 (b) 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.

# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264

NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this Service Bulletin. (3) Spares None B. CONCURRENT REQUIREMENTS None C. 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. OPERATOR MSN FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 KYV 0172

KIT No. QTY PER A/C CONFIGURATION 01

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Defuel the aircraft. (b) Gain access to the LH and RH outer wing fuel tanks. (c) Remove sealant from the inspection area. (d) Do an X-ray or HFEC inspection of the bottom skin stringer runouts adjacent to rib 14. (e) Repair as necessary. (f) Replace any removed sealant. (g) Close up. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. 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 and FH which follow: NOTE : The tables that follow list all the inspection periods in flight cycles and flight hours. Inspections should be carried out either at FC or FH limit whichever comes first.
Inspection Method Inspection Threshold Inspection Interval FC FH FC FH

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (b) For aircraft which have exceeded the first inspection threshold detailed in paragraph (2)(a), this inspection is required within 1,100 FC or 2,300 FH from the receipt of this Service Bulletin without exceeding already planned inspections according to revision 03 of this Service Bulletin. (c) 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. F. APPROVAL Approved under the EASA 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. Config. 01

H. WEIGHT AND BALANCE Not changed X-Ray 12,000 24,000 7,200 14,500 HFEC 12,000 24,000 9,400 18,800

Gain Access 2.0 Inspection 2.0 Close up 2.0 TOTAL MANHOURS 6.0 ELAPSED TIME (HOURS) 3.0

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

K. PUBLICATIONS AFFECTED

L. INTERCHANGEABILITY/MIXABILITY None Aircraft Maintenance Manual (AMM) : 12-11-28 28-11-22 28-11-24 28-25-00 Elec. Std. Practices Manual (ESPM) : 20-55-00 Nondestructive Testing Manual (NTM) : Part 2, 57-25-66 Part 6, 57-25-66 Structural Repair Manual (SRM) : 51-76-20

Maintenance Planning Document (MPD)

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS None D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP Sealant 09-002 As required

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. 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. 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. (1) Preparation (a) Config. 01 1 Defuel the aircraft (Refer to AMM 28-25-00 Page block 301). 2 Put the access platforms in position. 3 Remove access doors 540HB, 550AB (LH) and 640HB, 650AB (RH) (Refer to AMM 28-11-22 Page block 401 and AMM 28-11-24 Page block 401). 4 Remove sealant from the inspection area with a nonmetalic spatula (Refer to SRM 51-76-20 Page block 201 and refer to Figure 1 ). (2) Standard Practices None B. INSPECTION (1) Config. 01 (a) For the X-ray inspection do the instructions that follow : 1 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).

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2 If no cracks are found, repeat the inspection at intervals of no more than 7,200 FC or 14,500 FH. 3 If a crack is found, refer to the REPAIR paragraph. (b) For the HFEC inspection do the instructions that follow : 1 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). 2 If no cracks are found, repeat the inspection at intervals of no more than 9,400 FC or 18,800 FH. 3 If a crack is found, refer to the REPAIR paragraph. C. REPAIR (1) Config. 01 (a) If a crack is found, contact AIRBUS and carry out an approved repair before further flight. D. TEST None E. CLOSE UP (1) Config. 01 (a) Reseal the fuel tanks by applying a fillet of Sealant (Mat No. 09-002) at the junction of the rib and the stringer runout where sealant has been removed in paragraph 3.A.(1)(a)4 (Refer to Figure 1 and SRM 51-76-20 Page block 201). (b) Replace access doors 540HB, 550AB (LH) and 640HB, 650AB (RH) (Refer to AMM 28-11-22 Page block 401 and AMM 28-11-24 Page block 401). (c) Make sure that the work areas are clean and clear of tools and other items of equipment. (d) Refuel the aircraft (Refer to AMM 12-11-28 Page block 301). (e) Do an external inspection of any repaired areas for leaks. (f) Remove the access platforms. (g) Report all findings including nil findings to AIRBUS. F. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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# @ A310 SERVICE BULLETIN

DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Config. 01: Inspection Area

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# @ A310 SERVICE BULLETIN REPORTING SHEET

7 DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : WINGS - STRINGER FLANGES AT RIB 14 WING BOTTOM SKIN - INSPECT FOR CRACKS MODIFICATION No. : None
Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:..........................

........................................

........................................ B - SB HAS BEEN embodied on aircraft:.....................

........................................

........................................ Operator comments :..............................

.......................................

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

# @ A310 SERVICE BULLETIN QUALITY PERCEPTION FORM

7 DATE : Nov 06/89 SERVICE BULLETIN No. : A310—57—2038 REVISION No. : 04 — Oct 19/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - 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 X Mod/Inspection X Manpower Operator Supplied 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 Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.