# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 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 - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - INSPECTION FOR CRACKS AT BOLT HOLES MODIFICATION No. : None This page transmits Revision No. 03 of Service Bulletin No. A310-57-2002 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. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Inspection thresholds and intervals revised. Evaluation table added. — EFFECTIVITY . Effectivity revised. Models revised. Operators CYP, DAH, DLH, KAC, KLM, MPH, NGA, SAB and SWR deleted. Operators F2I, FDX, and S8G added. — MANPOWER . Configuration layout applied. PLANNING INFORMATION :

# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — EFFECTIVITY . 1.A. Effectivity revised. — REASON — History . 1.C.(1) Inspection thresholds and intervals revised. — Objective/Action . 1.C.(2) Inspection thresholds and intervals revised. — DESCRIPTION . 1.D. Configuration layout applied. Revised description in step (b). — 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 revised. — APPROVAL . 1.F. Approval sentence updated. Effectivity/Modification para added. — MANPOWER . 1.G. Configuration layout applied. Manpower para added. ACCOMPLISHMENT INSTRUCTIONS : — Preparation . 3.A.(1) Configuration Layout applied. Ref to figure 6 added. . 3.A.(1)(a)1 Para revised. — INSPECTION . 3.B. Configuration layout applied. Ref to figure 6 added. . 3.B.(1)(a) Inspection intervals revised. — REPAIR . 3.C. Configuration layout applied. Ref to figure 6 added. . 3.C.(1)(a) Inspection intervals revised.

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# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . 3.C.(1)(b) Inspection intervals revised. — CLOSE-UP . 3.E. Configuration layout applied. — Figure 1 . Configuration layout applied. — Figure 2 . Configuration layout applied. — Figure 3 . Configuration layout applied. — Figure 4 . Configuration layout applied. — Figure 5 . Configuration layout applied. — Figure 6 . 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 : Dec 31/88 REVISION No. : 01 — Jul 02/92 REVISION No. : 02 — Jan 04/96 REVISION No. : 03 — Nov 28/06

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# @ A310 SERVICE BULLETIN SUMMARY

7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 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 - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - INSPECTION FOR CRACKS AT BOLT HOLES MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES On the full scale wing fatigue test, cracking of the skin occurred in the region covered by this inspection. The cracks originated from the leading edge landing strap attachment holes. These attachments, initially rivets, were subsequently changed to interference fit bolts, both on the fatigue specimen and also on all aircraft before delivery. Detail panel tests have shown that with these improved attachments, cracking may still occur on some aircraft within the economic repair life. Modification 05101 has been introduced to improve the fatigue life in the fatigue critical areas, thereby reducing the possibility of expensive repairs being required later in the life of the aircraft. Service Bulletin A310-57-2003 covers retrofit embodiment of Mod. 05101. Where Mod. 05101 has not been embodied, special Mandatory inspections, detailed in this inspection Service Bulletin, will be required, starting at 9,400 flight cycles (FC) or 18,800 flight hours (FH) which ever comes first. Embodiment of modification 05101 (Service Bulletin A310-57-2003) is recommended before the inspection threshold to avoid possible repair situation and the introduction of this special Mandatory inspection procedure. A Mandatory detailed visual inspection of the external surface of the wing lower skin area around each of the bolt positions is required. Where modification 03028 has not been embodied, this Service Bulletin calls for the mandatory inspection of 975 bolt positions. Where modification 03028 has been embodied, this Service Bulletin calls for the mandatory inspection of 972 bolt positions. Where cracks are found extending in a forward direction, they are allowed to continue until they reach the skin edge. When this has occurred, a repair must be carried out within 390 FC or 780 FH, which ever comes first.

# @ A310 SERVICE BULLETIN SUMMARY

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Where cracks are extending rearwards, a High Frequency Eddy Current (HFEC) inspection is required to determine crack length and direction. A repair must then be carried out within 390 FC or 780 FH, which ever comes first. Accomplishment of this Service Bulletin reduces the possibility of expensive and time consuming repairs being required.

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 thru Config. 02 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

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# @ A310 SERVICE BULLETIN SUMMARY

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0

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# @ A310 SERVICE BULLETIN

7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : 1 of 16 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 - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - INSPECTION FOR CRACKS AT BOLT HOLES 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 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 (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

# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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: 0300 0309

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 0303

NOTE : Config. 01 are pre-Modification 05101 aircraft. Config. 02 are pre-Modification 05101 aircraft and have had Modification 03028 embodied. (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History On the full scale wing fatigue test, cracking of the skin occurred in the region covered by this inspection. The cracks originated from the leading edge landing strap attachment holes. These 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

KIT No. QTY PER A/C CONFIGURATION 02

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved attachments, initially rivets, were subsequently changed to interference fit bolts, both on the fatigue specimen and also on all aircraft before delivery. Detail panel tests have shown that with these improved attachments, cracking may still occur on some aircraft within the economic repair life. Modification 05101 has been introduced to improve the fatigue life in the fatigue critical areas, thereby reducing the possibility of expensive repairs being required later in the life of the aircraft. Service Bulletin A310-57-2003 covers retrofit embodiment of Mod. 05101. Where Mod. 05101 has not been embodied, special Mandatory inspections, detailed in this inspection Service Bulletin, will be required, starting at 9,400 flight cycles (FC) or 18,800 flight hours (FH) which ever comes first. Embodiment of modification 05101 (Service Bulletin A310-57-2003) is recommended before the inspection threshold to avoid possible repair situation and the introduction of this special Mandatory inspection procedure. (2) Objective/Action A Mandatory detailed visual inspection of the external surface of the wing lower skin area around each of the bolt positions is required. Where cracks are found extending in a forward direction, they are allowed to continue until they reach the skin edge. When this has occurred, a repair must be carried out within 390 FC or 780 FH, which ever comes first. Where modification 03028 has not been embodied, this Service Bulletin calls for the mandatory inspection of 975 bolt positions. Where modification 03028 has been embodied, this Service Bulletin calls for the mandatory inspection of 972 bolt positions. Where cracks are extending rearwards, a High Frequency Eddy Current (HFEC) inspection is required to determine crack length and direction. A repair must then be carried out within 390 FC or 780 FH, which ever comes first. (3) Advantages Accomplishment of this Service Bulletin reduces the possibility of expensive and time consuming repairs being required. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to :

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (1) Config. 01 thru Config. 02 (a) Gain access to wing bottom skin. (b) Carry out a detailed visual inspection (DVI) of the leading edge access panels for cracks at the bolt holes. (c) Carry out repair as necessary. (d) Close up. E. COMPLIANCE (1) Classification Mandatory (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) Inspection thresholds and intervals are given below. 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.

(c) Where aircraft have exceeded the inspection threshold given in paragraph 1.E.(2) (b), then this inspection must be carried out within 1,500 FC or 3,000 FH, whichever comes first, from the issue date of Revision 03 of this Service Bulletin without exceeding the already planned inspections in accordance with Service Bulletin 57-2002 revision 02. (d) Where Modification 03028 has not been embodied, this Service Bulletin calls for the mandatory inspection of 975 bolt positions. Where Modification 03028 has been embodied, this Service Bulletin calls for the mandatory inspection of 972 bolt positions. Threshold Interval FC FH FC FH 9,400 18,800 2,300 4,700

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (e) 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. NOTE : The inspection requirements described in this Service Bulletin are cancelled by the embodiment of Service Bulletin 57-2003. 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 thru Config. 02

H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed Gain Access 0.0 Inspection 8.0 Close up 0.0 TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved J. REFERENCES

K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None Non destructive Testing Manual (NTM) : Part 6, 51-10-08 Structural Repair Manual (SRM) : 51-10-13 Service Bulletin (SB) : A310-57-2003

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 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 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 : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 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 thru Config. 02 Refer to figure 1 thru figure 6 1 Gain access to the bottom wing skin on the underside of the leading edge. (2) Standard Practices None B. INSPECTION (1) Config. 01 thru Config. 02 Refer to figure 1 thru figure 6 (a) Carry out a detailed visual inspection (DVI) of the external surface of the wing bottom skin around the bolts at the access panel positions. Where no cracks are found, repeat this inspection at intervals not exceeding 2,300 FC or 4,700 FH, which ever comes first. C. REPAIR (1) Config. 01 thru Config. 02 Refer to figure 1 thru figure 6 (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 DVIs every 390 FC or 780 FH, which ever comes firstto monitor the cracks progress until it reaches the skin edge. When this has occurred contact SER1 and report complete details of the crack (Refer to SRM 51-10-13 Page block 001). A repair must be carried out within 390 FC or 780 FH, which ever comes first, after the crack has reached the skin edge. (b) Where a crack is found extending in an rearward direction, (Refer to NTM 51-10-08 part 6 Page block 601) and carry out a HFEC inspection around the bolt position affected. 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 390 FC or 780 FH, which ever comes first, after crack detection.

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved AI/SE-E1 are to be informed of any changes in the length and direction of the crack which may have occurred between the HFEC inspection and the time of the repair, so that the repair solution can be modified if necessary. D. TEST None E. CLOSE UP (1) Config. 01 thru Config. 02 (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 : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Access Panel General Location (Config 01 and 02)

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 2 Sheet 1 LH Wing, Root Rib 1 to Slat Track 3 Bolting Arrangement (Config 01 and 02)

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 1 LH Wing, Slat Track 3 to Slat Track 5 Bolting Arrangement (Config 01 and 02)

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 4 Sheet 1 LH Wing, Slat Track 5 to Slat Track 7 Bolting Arrangement (Config 01 and 02)

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 5 Sheet 1 LH Wing, Slat Track 7 to Slat Track 9 Bolting Arrangement (Config 01 and 02)

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# @ A310 SERVICE BULLETIN

DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 6 Sheet 1 RH Wing, Refuel Panel, After Mod.AM 3028 Only, Bolting Arrangement (Config 02)

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# @ A310 SERVICE BULLETIN REPORTING SHEET

7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : WINGS - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - INSPECTION FOR CRACKS AT BOLT HOLES 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 : Dec 31/88 SERVICE BULLETIN No. : A310—57—2002 REVISION No. : 03 — Nov 28/06 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.