# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 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 - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR CRACKS MODIFICATION No. : None This page transmits Revision No. 04 of Service Bulletin No. A310-57-2032 ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON This revision is issued to make the main changes that follow: — Accomplishment timescale to include inspection threshold, interval and the grace periods to Extended Service Goal (ESG) requirements. — Aircraft configurations added. — Effectivity revised. — Operators revised. — Models revised. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Inspection thresholds and intervals revised. Evaluation table added. — EFFECTIVITY . Operators F2I, FDX and S8G have been added. Operators CYP, DAH, DLH, KAC, KLM, MPH, NGA, SAB and SWR have been deleted. Effectivity revised. — MANPOWER . Configuration layout applied.

# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved PLANNING INFORMATION : — EFFECTIVITY . 1.A. Model A310-221 has been deleted. Effectivity revised. Configuration layout applied to Kit/Configuration. — REASON — Objective/Action . 1.C.(2) Inspection thresholds and intervals revised. — DESCRIPTION . 1.D. Configuration layout applied. . 1.D.(1)(b) Step rewitten. — COMPLIANCE — Accomplishment Timescale . 1.E.(2)(a) Mandatory sentence updated. . 1.E.(2)(b) Inspection thresholds and intervals revised. . 1.E.(2)(c) Inspection thresholds and intervals revised. — APPROVAL . 1.F. Approval sentence updated. Approval paras added. — MANPOWER . 1.G. Configuration layout applied. ACCOMPLISHMENT INSTRUCTIONS : — Preparation . 3.A.(1) Configuration layout applied. . 3.A.(1)(a)1 Step rewitten. — INSPECTION . 3.B. Configuration layout applied. . 3.B.(1)(a) Inspection intervals revised. — REPAIR . 3.C. Configuration layout applied.

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# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . 3.C.(1)(a) Inspection intervals revised. . 3.C.(1)(b) Page block added to step. — CLOSE-UP . 3.E. Configuration layout applied. — Figure 1 . Configuration layout applied. — Figure 2 . Configuration layout applied. 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 If information is required for Revisions issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS. REVISION SEQUENCE ORIGINAL : Apr 30/89 REVISION No. : 01 — Jan 06/93 REVISION No. : 02 — Apr 23/93 REVISION No. : 03 — Jan 04/96 REVISION No. : 04 — Dec 01/06

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# @ A310 SERVICE BULLETIN SUMMARY

7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 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 This summary is for information only and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 57 TITLE : WINGS - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR CRACKS MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Cracks have been found during full scale fatigue tests at various positions in the wing top skin between rib 7 and rib 14, where there are discontinuities in the leading edge to the top skin joint strap. These cracks were found emanating from bolt holes running forward to the skin edge and rearwards towards the front spar at 41,000 simulated flight cycles (FC). If the cracks are allowed to extend beyond the limits of normal repairs, extensive and time consuming repair actions will be required. Modification 05026H0878 (Service Bulletin A310-57-2005) was introduced to prevent the cracks and is recommended to be embodied before the inspection threshold. When modification 05026H0878 has been embodied, no further inspections are required in accordance with this Service Bulletin. The following mandatory inspection is required not later than 10,500 flight cycles (FC) or 21,000 flight hours (FH) whichever comes first, on aircraft which are Pre modification 05026H0878. Repeat inspections are required at intervals not exceeding 3,900 FC or 7,900 FH, whichever comes first. A Detailed Visual inspection of the wing top skin upper surface forward of the front spar is required between rib 7 and rib 28. Where a crack is suspected a high frequency Eddy current (HFEC) inspection is required. Where cracks are verified by a HFEC inspection, all details found must be reported to Airbus (AI/SE-E1) as soon as possible. Where a crack is running forwards, a repair must be carried out within 220 FC or 440 FH, whichever comes first, after the crack has reached the skin edge. Where a crack is running rearward, a repair must be carried out within 220 FC or 440 FH, whichever comes first or before further flights depending on the crack length.

# @ A310 SERVICE BULLETIN SUMMARY

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Timely detection of cracks may reduce the necessity of carrying out extensive and time consuming repairs.

EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) : F2I FDX S8G 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 EVALUATION TABLE

COMPLIANCE Mandatory 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 KIT PRICE (USD) No AIRBUS Kit

TOTAL MANHOURS 5.0 ELAPSED TIME (HOURS) 2.5

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# @ A310 SERVICE BULLETIN SUMMARY

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None

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# @ A310 SERVICE BULLETIN

7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : 1 of 14 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 - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION 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 A310-203 A310-222 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0297 0300 0303 0309 NOTE : Modification 05026H0878 is embodied prior to delivery on aircraft MSN 0172, 0288, 0291, 0293, 0311 and subsequent. (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

# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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.

(c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0297 0300 0303 0309

(3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History Cracks have been found during full scale fatigue tests at various positions in the wing top skin between rib 7 and rib 14, where there are discontinuities in the leading edge to the top skin joint strap. These cracks were found emanating from bolt holes running forward to the skin edge and rearwards towards the front spar at 41,000 simulated flight cycles (FC). If the cracks are allowed to extend beyond the limits of normal repairs, extensive and time consuming repair actions will be required. Modification 05026H0878 (Service Bulletin A310-57-2005) was introduced to prevent the cracks and is recommended to be embodied before the inspection threshold. OPERATOR MSN F2I 0309 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0297 0303 S8G 0300

KIT No. QTY PER A/C CONFIGURATION 01

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved When modification 05026H0878 has been embodied, no further inspections are required in accordance with this Service Bulletin. (2) Objective/Action The following mandatory inspection is required not later than 10,500 flight cycles (FC) or 21,000 flight hours (FH) whichever comes first, on aircraft which are Pre modification 05026H0878. Repeat inspections are required at intervals not exceeding 3,900 FC or 7,900 FH whichever comes first. A Detailed Visual inspection of the wing top skin upper surface forward of the front spar is required between rib 7 and rib 28. Where a crack is suspected a high frequency Eddy current (HFEC) inspection is required. Where cracks are verified by a HFEC inspection, all details found must be reported to Airbus (AI/SE-E1) as soon as possible. Where a crack is running forwards, a repair must be carried out within 220 FC or 440 FH, whichever comes first, after the crack has reached the skin edge. Where a crack is running rearward, a repair must be carried out within 220 FC or 440 FH, whichever comes first or before further flights depending on the crack length. (3) Advantages Timely detection of cracks may reduce the necessity of carrying out extensive and time consuming repairs. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Gain access to wing top skin, forward. (b) Carry out a detailed visual inspection (DVI) of the top skin forward of the front spar for cracks. (c) Carry out repair as necessary. (d) Close up. E. COMPLIANCE (1) Classification Mandatory

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (2) Accomplishment Timescale (a) 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 above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. (b) Inspections are to be carried out at or before the completion of 10,500 FC or 21,000 FH, whichever comes first. Repeat inspections are required at intervals not exceeding 3,900 FC or 7,900 FH, whichever comes first. (c) For aircraft that have already exceeded the inspection threshold, the first inspection is to be carried out no later than 850 FC or 1,700 FH, whichever comes first, from the receipt of this Service Bulletin and without exceeding existing planned next inspection according to revision 03 of this Service Bulletin. (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 is to be counted as a flight cycle. A touch and go is a landing in which the aircraft does not come to a compleat standstill 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.

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Config. 01

H. WEIGHT AND BALANCE None I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None Gain Access 0.0 Inspection 5.0 Close up 0.0 TOTAL MANHOURS 5.0 ELAPSED TIME (HOURS) 2.5

Non destructive Testing Manual (NTM) : Part 6, 51-10-08 Structural Repair Manual (SRM) : 51-10-13 Service Bulletin (SB) : A310-57-2005

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION None C. LIST OF COMPONENTS None D. LIST OF MATERIALS — OPERATOR SUPPLIED None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL NOTE : These instructions are applicable to the left and right hand wings. (1) Preparation (a) Config. 01 Refer to figure 1 and figure 2 1 Gain access to the upper wing skin forward of the front spar. (2) Standard Practices None B. INSPECTION (1) Config. 01 Refer to figure 1 and figure 2 (a) Carry out a detailed visual inspection (DVI) of the wing top skin upper surface, at all areas detailed, around the bolt denoted 'X'. Where no cracks are found, repeat this inspection at intervals not exceeding 3,900 FC or 7,900 FH, whichever comes first. C. REPAIR (1) Config. 01 Refer to figure 1 and figure 2 (a) Where a crack is found to be extending from a bolt hole towards the skin edge, it can be allowed to continue with repeat detailed visual inspections every 220 FC or 440 FH, whichever comes first, to monitor the cracks progress until it reaches the skin edge. When this has occurred, contact SER1 and report complete details of the crack for a repair solution (Refer to SRM 51-10-13 Page block 001). A repair must be carried out within 220 FC or 440 FH, whichever comes first, after the crack has reached the skin edge. (b) Where a crack is found to be extending in an rearward direction, carry out a HFEC inspection around the bolt position affected (Refer to NTM 51-10-08, part 6 Page block 601).

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Contact AI.SE-E1 with complete details of the crack (Refer to SRM 51-10-13 Page block 001) for an approved repair. The repair must be carried out within 220 FC or 440 FH, whichever comes first, after crack detection or when the crack has extended to a maximum of 10.0mm in length whichever occurs first. Mandatory repeat inspections at 40 FC or 80 FH, whichever comes first, intervals are required from the initial crack detection up to the maximum of 220 FC or 440 FH, whichever comes first, to monitor the crack length. Where the crack exceeds 10.0mm in length, a repair must be carried out before the next flight. D. TEST None E. CLOSE UP (1) Config. 01 (a) Make certain that the work area is clean and clear of tools and miscellaneous items of equipment. 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 : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1 (Goto A3 section) Wing Leading Edge (Config 01)

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# @ A310 SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1 (Goto A3 section) Bolt Positions at Skin Strap (Config 01)

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# @ A310 SERVICE BULLETIN REPORTING SHEET

7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : WINGS - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR CRACKS MODIFICATION No. : None

Please complete the appropriate item (A or B): A - SB WILL BE embodie d............. 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 : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032 REVISION No. : 04 — Dec 01/06 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.@ A310SERVICE BULLETINDATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032REVISION No. : 04 — Dec 01/06 Page : 11/12Printed in FRANCE © AIRBUS, 2006 All rights reservedFigure 1 Sheet 1Wing Leading Edge (Config 01)@ A310SERVICE BULLETINDATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032REVISION No. : 04 — Dec 01/06 Page : 13/14Printed in FRANCE © AIRBUS, 2006 All rights reservedFigure 2 Sheet 1Bolt Positions at Skin Strap (Config 01)