# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET 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 MANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS 1 AND 7 MODIFICATION No.: None This page transmits Revision No.10 of Service Bulletin No.A300-57-6045 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 10 issued to update the tables in the compliance paragraph. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R COMPLIANCE Accomplishment Timescale Amended inspection time scales R ACCOMPLISHMENT INSTRUCTIONS TASK 576045- 832-895-001-INSPECTION TASK SOLUTION UPDATED NOTE UPDATED CAUTION UPDATED R
Subtask 576045-250-401-001 Amended inspection area R Subtask 576045-833-401-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED PART NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED R

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET FILLING 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 02 was issued to inform operators that this Inspection Service Bulletin has been made mandatory, the effectivity was also updated. Revision 03 was issued to update the effectivity, to add aircraft model C4-605R/F and aircraft MSN 0755 and 0758. The standard sentences for the approval and manpower were also updated. Revision 04 was issued to add the aircraft model F4-622R, update the aircraft effectivity and to add the operator UPS. Revision 05 was issued to update the aircraft effectivity for operator JAS. The effectivity was updated generally. Revision 06 was issued to update the aircraft effectivity for operators UPS and AHK. The effectivity has also been updated generally. Revision 07 was issued to include the latest delivered aircraft for UPS. Revision 08 was issued to include revised thresholds/intervals quoted in Flight Cycles (FC) and Flight Hours (FH), to enable aircraft operation to the relevant Extended Service Goal (ESG). Revision No. 09 issued to update the accomplishment instructions. The inspection area is extended to included the top wing skin overhang forward of the front spar. The required frequency of this mandatory inspection has been updated in line with a new fatigue and damage tolerance analysis. The opportunity is taken to produce this Service Bulletin in the latest format. REVISION SEQUENCE ORIGINAL: Mar 18/93 REVISION No. : 01 - Aug 03/94 REVISION No. : 02 - Apr 21/98 REVISION No. : 03 - Oct 25/99 REVISION No. : 04 - Jan 11/02 REVISION No. : 05 - Jun 13/03 REVISION No. : 06 - Jan 13/05 REVISION No. : 07 - Aug 14/08 REVISION No. : 08 - Jun 06/11 DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET REVISION No. : 09 - May 21/13 REVISION No. : 10 - Nov 13/13

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN SUMMARY 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 MANDATORYMANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS 1 AND 7 **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During full-scale fatigue testing, cracks were found at the wing top skin front spar joints between Rib 1 and Rib 7 at approximately 33,000 to 49,000 simulated flights. The cracks started in clearance fit fastener holes in the skin to spar joint. More recently, seven instances of cracking have been reported to AIRBUS that started at the skin edge or fastener holes close to the skin edge forward of the front spar around Rib 7. The cracks have occurred at between 25,000 and 42,000 Flight Cycles (FC) with crack lengths up to 43.0 mm (1.69 in.). As a result of these in-service findings, a mandatory Detailed Inspection (DI) is required to detect cracks on the wing top skin at the front spar joint and between the front spar joint and the leading edge overhang, between Ribs 1 and 7. The required frequency of this mandatory inspection is altered in line with new fatigue and damage tolerance analysis. Early detection of cracks can prevent the necessity of extensive and costly repairs at a later stage. 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 NOTE (1): Service Bulletin must be accomplished. DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPB01 See SB BOLT (PLUG-REPAIR) EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

ABD ABR AHK BCS CES F2I FDX GBG I2L IRA IRM KAC KAL MGC MNB MON MSR MXU OHY QTR SUD TAR THA TMA UPS URS UZB CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 576045-832-895-001: INSPECTION TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 1.00 APPENDICES APPENDIX 01: INSPECTION REPORT

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN SUMMARY

**CONF ALL

LH SHOWN RH SIMILAR

TYPICAL SKIN CRACK AT LEADING EDGE OVERHANG

FRONT SPAR

TYPICAL SKIN CRACKS AT FRONT SPAR ATTACHMENT STRINGER WING TOP SKIN

VIEW ON TYPICAL AREA 

## A INSPECTION AREA **NOTE:** Z512 (Z612) RIB7 RIB1 

### A

D_SB_576045_7_SAAA_01_00 Figure A-USAAA - Sheet 01

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN SUMMARY

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# @A300-600 SERVICE BULLETIN
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 MANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS 1 AND 7 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 **CONF ALL A. EFFECTIVITY (1) Models B4-603 B4-605R B4-620 B4-622 B4-622R C4-605R/FC4-620 F4-605R F4-622R (2) Effectivity by MSN 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529-0530 0532 0536 0543 0546 0553-0561 0563 0572 0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613-0614 0617-0618 0621 0623 0625-0626 0629-0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0730 0732-0746 0748-0750 0752-0764 0766-0775 0777-0794 0797 0799-0840 0845-0878 (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. DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN ABD 0529 0557 ABR 0683 0770 AHK 0855 0856 0857 0858 0859 0860 0870 0871 BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730 0737 0740 0753 0783 CES 0525 0532 0707 0725 0732 0741 0746 0754 0763 F2I 0294 0518 FDX 0358 0361 0365 0388 0417 0477 0479 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 0726 0728 0735 0736 0738 0742 0745 0748 0752 0757 0759 0760 0761 0766 0768 0769 0771 0772 0774 0777 0778 0779 0780 0781 0789 0790 0791 0792 0793 0794 0799 0800 0801 0802 0803 0804 0873 0874 0875 0876 0877 0878 GBG 0626 0643 I2L 0677 IRA 0632 0696 0723 0727 IRM 0380 0401 0405 0408 0411 0414 0546 0553 0608 0618 0623 0701 0750 0762 0773 0838 KAC 0344 0673 0694 0699 0719 0721 KAL 0631 0662 MGC 0743 MNB 0521 0734 0739 0755 0756 0758 MON 0556 0604 0605 MSR 0561 0607 MXU 0767 0788 0797 0836 0837 OHY 0584 0603 0744 0749 0764 QTR 0554 0560 0614 SUD 0666 0775 TAR 0505 0558 0563 THA 0464 0577 0629 0681 0705 0782 0784 0785 0786 0787 TMA 0872 UPS 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835 0839 0840 0845 0846 0847 0848 0849 0850 0851 0852 0853 0854 0861 0862 0863 0864 0865 0866 0867 0868 0869 URS 0733 UZB 0717 0722

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 2 7

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# @A300-600 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0294 0344 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505 0518 0521 0525 0529 0530 0532 0536 0543 0546 0553 0554 0555 0556 0557 0558 0559 0560 0561 0563 0572 0575 0577 0579 0581 0584 0602 0603 0604 0605 0607 0608 0611 0613 0614 0617 0618 0621 0623 0625 0626 0629 0630 0631 0632 0633 0637 0641 0643 0657 0659 0662 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721 0722 0723 0724 0725 0726 0727 0728 0729 0730 0732 0733 0734 0735 0736 0737 0738 0739 0740 0741 0742 0743 0744 0745 0746 0748 0749 0750 0752 0753 0754 0755 0756 0757 0758 0759 0760 0761 0762 0763 0764 0766 0767 0768 0769 0770 0771 0772 0773 0774 0775 0777 0778 0779 0780 0781 0782 0783 0784 0785 0786 0787 0788 0789 0790 0791 0792 0793 0794 0797 0799 0800 0801 0802 0803 0804 0805 0806 0807 0808 0809 0810 0811 0812 0813 0814 0815 0816 0817 0818 0819 0820 0821 0822 0823 0824 0825 0826 0827 0828 0829 0830 0831 0832 0833 0834 0835 0836 0837 0838 0839 0840 0845 0846 0847 0848 0849 0850 0851 0852 0853 0854 0855 0856 0857 0858 0859 0860 0861 0862 0863 0864 0865 0866 0867 0868 0869 0870 0871 0872 0873 0874 0875 0876 0877 0878 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPB01 As required Consumable CMLB01 As required B. CONCURRENT REQUIREMENTS None C. REASON (1) History During full-scale fatigue testing, cracks were found at the wing top skin front spar joints between Rib 1 and Rib 7 at approximately 33,000 to 49,000 simulated flights. The cracks started in clearance fit fastener holes in the skin to spar joint.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 3 7

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# @A300-600 SERVICE BULLETIN More recently, seven instances of cracking have been reported to AIRBUS that started at the skin edge or fastener holes close to the skin edge forward of the front spar around Rib 7. The cracks have occurred at between 25,000 and 42,000 Flight Cycles (FC) with crack lengths up to 43.0 mm (1.69 in.). (2) Objective/Action As a result of these in-service findings, a mandatory Detailed Inspection (DI) is required to detect cracks on the wing top skin at the front spar joint and between the front spar joint and the leading edge overhang, between Ribs 1 and 7. The required frequency of this mandatory inspection is altered in line with new fatigue and damage tolerance analysis. (3) Advantages Early detection of cracks can prevent the necessity of extensive and costly repairs at a later stage. (4) Operational/Maintenance Consequences None D. DESCRIPTION NOTE: Inspection results must be reported to AIRBUS on the Inspection Report attached to this Service Bulletin (Appendix 01). If there are findings, a report is to be completed as follows: - if there is damage which is not within the limits given in this Service Bulletin, contact AIRBUS immediately (within 48 hours) and before the next flight for repair instructions - after the corrective action is completed; damage within limits and repaired by the accomplishment of the repair instructions given in this Service Bulletin OR damage is not within limits but repaired by the accomplishment of the repair instructions given by AIRBUS. If there are no findings, the Inspection Report has to be sent as soon as the maintenance check or visit report has been completed by accomplishment of this Service Bulletin. To accomplish this Service Bulletin it is necessary to : Task 576045-832-895-001: INSPECTION (1) DO A DETAILED INSPECTION OF THE WING TOP SKIN AT THE FRONT SPAR JOINT AND BETWEEN THE FRONT SPAR JOINT AND THE LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7 (2) DO AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN OF CRACK(S) (3) REPAIR THE CRACK(S) AS NECESSARY DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 4 7

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# @A300-600 SERVICE BULLETIN
E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Normal Range Operation Inspection Threshold Inspection Interval Grace Period FC FH FC FH FC FH 22,000 49,500 6,500 14,100 1,300 2,800 Table 1: Detailed Inspection Programme for Freighters (F4-600(R)) Normal Range Operation Inspection Threshold Inspection Interval Grace Period FC FH FC FH FC FH 17,100 38,400 5,100 11,000 1,000 2,200 Table 2: Detailed Inspection Programme for Passenger Aircraft (B4-600, B4-600(R), C4-600 and C4-600(R)) Short Range Operation Inspection Threshold Inspection Interval Grace Period FC FH FC FH FC FH 22,000 49,500 7,000 10,600 1,300 2,800 Table 3: Detailed Inspection Programme for Freighters (F4-600(R)) Short Range Operation Inspection Threshold Inspection Interval Grace Period FC FH FC FH FC FH 17,100 38,400 5,500 8,300 1,000 2,200 Table 4: Detailed Inspection Programme for Passenger Aircraft (B4-600, B4-600(R), C4-600 and C4-600(R))
Freighters (F4-600(R)) Passenger Aircraft (B4-600, B4-600(R) and C4-600) FC FH FC FH 50 110 50 110 Table 5: Repeat Detailed Inspection Programme for Temporary Repairs
NOTE: For aircraft already within the inspection programme, the repeat detailed inspection can be done at the next inspection interval. For all other
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 5 7

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# @A300-600 SERVICE BULLETIN aircraft the applicable grace periods identified in Tables 1, 2, 3 and 4 must be used for the first detailed inspection. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. The initial detailed inspections and repeat intervals are specified in Tables 1, 2, 3 and 4. The repeat detailed inspection intervals for aircraft with temporary repairs are specified in Table 5. NOTE: Tables 1 and 2 give figures for normal range, Tables 3 and 4 give figures for short range (average flight time of less than 1.50 hours) operations. F. APPROVAL The technical content of this document is approved under the authority of Design Organization 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. Task 576045-832-895-001: INSPECTION Get Access 0.50 On Aircraft DO A DETAILED INSPECTION OF THE WING TOP SKIN AT THE FRONT SPAR JOINT AND BETWEEN THE FRONT SPAR JOINT AND THE LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7 0.50

DO AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN OF CRACK(S) 0.25 REPAIR THE CRACK(S) AS NECESSARY 0.25 Close-Up 0.50 TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 1.00 H. WEIGHT AND BALANCE Not Changed

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 6 7

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# @A300-600 SERVICE BULLETIN
I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-07 51-10-08 Process and Material Specification (PMS) Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-40 51-75-10 K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 7 7

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses None (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No AIRBUS kit will be provided. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Lubricant 03RBB1 As required Anti Corrosion Primer Epoxy 04DAB2 As required Polyurethane Finish Paint 04JAA3 As required General Purpose Solvent 08BAA9 As required Chemical Conversion Coating (Yellow Aluminum) 10ABC1 As required Lint-Free Cotton Cloth 14SBA1 As required (2) Components Component COMPB01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES EN6114-3-8 1 BOLT (1) 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.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 9 7

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# @A300-600 SERVICE BULLETIN
NOTE (1): For each crack found (that is between 6.0 and 75.0 mm (0.24 and 2.95 in. in length), you will require one EN6114-3-8 Bolt to fill the crack-stop drill hole. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 10 7

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 576045-832-895-001 - INSPECTION WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 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 refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. 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 the aircraft can be put back into a serviceable condition. Task Associated Data Zone 512 612

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 11 7

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# @A300-600 SERVICE BULLETIN Manpower TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 1.00 A. GENERAL (1) Subtask 576045-910-401-001 - STANDARD PRACTICES Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 Consumable Material List (CML) Non Destructive Test Manual (NTM) 51-10-07 51-10-08 Process and Material Specification (PMS) Structural Repair Manual (SRM) 51-24-00 51-40-40 51-75-10 (a) For the Process and Material Specification (PMS) (Refer to Process and Material Specification (PMS)). (b) For the specification of materials (Mat. No.) given in this Service Bulletin refer to Consumable Materials List (CML). (c) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (d) For High Frequency Eddy Current (HFEC) inspection for surface cracks in aluminum refer to NTM 51-10-08. (e) For ultrasonic evaluation of crack lengths refer to NTM 51-10-07. (f) For the apply of sealant refer to SRM 51-24-00. (g) For the renewal of the protective finish refer to SRM 51-75-10. B. PREPARATION (1) Subtask 576045-941-401-001 - JOB SET-UP Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7 Manpower Resources Skills NON SPECIFIC

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 12 7

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# @A300-600 SERVICE BULLETIN (a) Put a WARNING NOTICE in position in the cockpit to tell persons not to operate the flight controls. (b) Put the SAFETY GUARD PN 98A27503003000 in position on the flap/slat control lever quadrant. (c) Put an Access Platform 3.0 m (10.0 ft.) in position below the applicable inspection area in Zone 512 (612) between Rib 1 and Rib 7. (d) Put the safety barriers in position. (2) Subtask 576045-110-401-001 - PREPARE THE AREA FOR INSPECTION Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7 Manpower Resources Skills AIRFRAME CLEANING Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES General Purpose Solvent 08BAA9 As required Lint-Free Cotton Cloth 14SBA1 As required References Fig. A-UBAAA TYPICAL SKIN CRACKS AT THE FRONT SPAR ATTACHMENT/SKIN OVERHANG Sheet 01

(a) Use Lint-Free Cotton Cloth 14SBA1 As required

made moist with General Purpose Solvent 08BAA9 As required to clean the wing top skin between the front spar joint and the leading edge overhang, between Rib 1 and Rib 7 (Refer to Fig. A-UBAAA Sheet 01 ).

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 13 7

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# @A300-600 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 576045-832-401-001 - DO A DETAILED INSPECTION OF THE WING TOP SKIN AT THE FRONT SPAR JOINT AND BETWEEN THE FRONT SPAR JOINT AND THE LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7 Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Fig. A-UBAAA TYPICAL SKIN CRACKS AT THE FRONT SPAR ATTACHMENT/SKIN OVERHANG Sheet 01

NOTE: The worksteps that follows are to be accomplished on the LH and RH wings. (a) Do a detailed inspection of the wing top skin in the area adjacent to its attachment at the front spar, and between the front spar joint and the leading edge overhang between Rib 1 and Rib 7 (Refer to Fig. A-UBAAA Sheet 01 ): 1 If there are no cracks, repeat the detailed inspection at the applicable intervals specified in Para. 1.E.(2). Fill in the reporting sheet and return to AIRBUS. Go to SUBTASK 576045-942-401 001 CLOSE-UP . 2 If you find cracks or signs of cracks, go to SUBTASK 576045-250-401 001 DO AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN OF CRACK(S) . (2) Subtask 576045-250-401-001 - DO AN EDDY CURRENT INSPECTION OF THE CRACK(S) OR AT THE SIGN OF CRACK(S) Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 14 7

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) 51-10-08 Fig. A-UCAAA SPECIFICATION FOR THE MAXIMUM PERMITTED CRACK LENGTH Sheet 01 Sheet 02 (a) Do an Eddy Current inspection of the cracks or of the signs of cracks refer to NTM 51-10-08 (b) If there are cracks in the top skin in the area forward of the front spar attachment, report to AIRBUS for repair instructions before the subsequent flight. (c) If there are no cracks, do a repeat detailed inspection at the applicable intervals specified in Para. 1.E.(2). (d) If there are crack(s) at the spar attachment (or aft of the spar attachment), measure the length of the crack(s) (Refer to Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02): 1 If the crack(s) is/are less than 6.0 mm (0.236 in.) in length, do a repeat detailed inspection of the crack(s) at the intervals specified in Table 5 of Para. 1.E.(2) Do not stop drill the crack(s). 2 If the crack(s) is/are more than 6.0 mm (0.236 in.) in length but less than the maximum permitted length of 75.0 mm (2.953 in.):
a Do a temporary repair (stop drill and plug the crack(s)), go to SUBTASK 576045-833-401 001 REPAIR THE CRACK(S) AS NECESSARY . b Do a repeat detailed inspection of the temporary repair(s) at the intervals specified in Table 5 of Para. 1.E.(2) but not more than 250 FC / 550 FH after the initial repair. No later than 250 FC / 550 FH after the initial repair, a permanent repair must be embodied. 3 If the crack(s) is/are more than the maximum permitted length of 75.0 mm (2.953 in.), contact AIRBUS before next flight for an approved repair(s). (e) Complete the Inspection Report (Refer to APPENDIX 01: INSPECTION REPORT ) with inspection results or NIL findings.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 15 7

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# @A300-600 SERVICE BULLETIN (3) Subtask 576045-833-401-001 - REPAIR THE CRACK(S) AS NECESSARY Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Component COMPB01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES EN6114-3-8 1 BOLT (1) NOTE (1): For each crack found (that is between 6.0 and 75.0 mm (0.24 and 2.95 in. in length), you will require one EN6114-3-8 Bolt to fill the crack-stop drill hole. Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Lubricant 03RBB1 As required Anti Corrosion Primer Epoxy 04DAB2 As required Renew the protective finish 04JAA3 As required Chemical Conversion Coating (Yellow Aluminum) 10ABC1 As required
References Non Destructive Test Manual (NTM) 51-10-08 Structural Repair Manual (SRM) 51-24-00 51-40-40 51-75-10 Fig. A-UDAAA TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS Sheet 01 Sheet 02 Sheet 03 NOTE: This repair is not applicable to crack(s) found on the wing top skin leading edge overhang. Any crack(s) found on wing top skin leading edge overhang, contact AIRBUS.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 16 7

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# @A300-600 SERVICE BULLETIN (a) General 1 A crack from a fastener hole must be at least 6.0 mm (0.236 in.) in length before it can be stop drilled. The minimum distance from the edge of the crack-stop drill hole to the edge of any adjacent fastener countersink must not be less than 6.0 mm (0.236 in.). 2 If a crack is too near to an adjacent fastener to be crack-stop drilled, contact AIRBUS before the next flight for an approved repair. 3 A crack that ends in unsupported wing skin must be crack-stop drilled and the hole plugged with a blind plug. 4 A crack that ends near the edge of the spar boom may have a crack-stop hole that overlaps the spar boom edge, only if a blind plug is installed. 5 When a crack-stop hole has been plugged, the total length that must be recorded on the inspection report is the length of the crack plus the diameter of the plug. NOTE: The direction of the cracks is usually chord wise. (b) Temporary Repair (Stop Drill and Plug) of a Crack in the Specified Inspection Areas Refer to Fig. A-UDAAA Sheet 01 , Fig. A-UDAAA Sheet 02 and Fig. A-UDAAA Sheet 03

. 1 Obtain fastener hole diameters, drill and de-burr the crack-stop hole, refer to SRM 51-40-40. NOTE: Make sure that the crack-stop hole is in line with the direction of the crack. NOTE: Make sure that you position the crack-stop hole at a distance that equals the thickness ’T’ in front of the end of the crack. 2 Do an Eddy Current inspection to make sure that the crack does not continue through the crack-stop hole refer to NTM 51-10-08. 3 End-mill the crack-stop hole to the correct dimensions. 4 Ream the crack-stop hole to the correct diameter. NOTE: Make sure that the crack-stop hole is reamed over the full depth and that it has a surface finish of 1.6 micrometers (63 micro-inches). 5 De-burr the crack-stop hole. 6 Make a plug to the correct dimensions, as shown on Fig. A-UDAAA Sheet 03

. Use: 1 Bolt EN6114-3-8 DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 17 7

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# @A300-600 SERVICE BULLETIN
NOTE: Make sure that the plug has a surface finish of 1.6 micrometers (63 micro-inches). 7 Apply a layer of Lubricant 03RBB1 As required to the plug. 8 Install the plug in the crack-stop hole. NOTE: Make sure that the plug is engaged over the full depth of the crack-stop hole. 9 If necessary, mill the plug so that it is flush with the surface of the wing top skin. 10 Apply Chemical Conversion Coating (Yellow Aluminum) 10ABC1 As required

Anti Corrosion Primer Epoxy 04DAB2 As required
and Renew the protective finish 04JAA3 As required to the milled surface of the plug and the area around the plug as necessary, in accordance with SRM 51-75-10 and SRM 51-24-00 D. TEST None E. CLOSE-UP (1) Subtask 576045-942-401-001 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 512 Work location from Rib 1 to Rib 7 612 Work location from Rib 1 to Rib 7 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 18 7

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# @A300-600 SERVICE BULLETIN (b) Remove the safety barriers. (c) Remove the access platforms. (d) Remove the SAFETY GUARD PN 98A27503003000 from the flap/slat control lever quadrant. (e) Remove the WARNING NOTICE from the cockpit. (2) Subtask 576045-839-401-001 - ADMINISTRATIVE Manpower Resources Skills UTILITY (a) Send the completed Inspection Report (Refer to APPENDIX 01: INSPECTION REPORT ) with inspection results or NIL findings to AIRBUS. (b) Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 19 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

LH SHOWN RH SIMILAR

TYPICAL SKIN CRACK AT LEADING EDGE OVERHANG

FRONT SPAR

TYPICAL SKIN CRACKS AT FRONT SPAR ATTACHMENT STRINGER WING TOP SKIN

VIEW ON TYPICAL AREA 

## A INSPECTION AREA **NOTE:** Z512 (Z612) RIB7 RIB1 

### A

D_SB_576045_7_BAAA_01_00 Figure A-UBAAA - Sheet 01 TYPICAL SKIN CRACKS AT THE FRONT SPAR ATTACHMENT/SKIN OVERHANG
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 20 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_CAAA_01_03 FRONT SPAR (A)

(B)

DIAGRAM (B) SHOWS THE MAXIMUM PERMITTED LENGTH OF A MULTIPLE CRACK. DIAGRAM (A) SHOWS THE MAXIMUM PERMITTED LENGTH OF A SINGLE CRACK. 75.0 mm (2.95 in)

75.0 mm (2.95 in)

**NOTE:** TEMPORARY REPAIRS OF CRACKS IN THIS AREA ARE NOT PERMITTED. **F W**  **D** TOP SKIN LEADING EDGE

TYPICAL CRACK

TYPICAL CRACK FROM A FASTENER HOLE ADJACENT TO THE TOP SKIN LEADING EDGE. 01 FRONT SPAR TOP SKIN LEADING EDGE

**F W**  **D** 01

TYPICAL CRACK 01

Figure A-UCAAA - Sheet 01 SPECIFICATION FOR THE MAXIMUM PERMITTED CRACK LENGTH
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 21 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_CAAA_02_00 (C2) (C1)

DIAGRAMS (C1) AND (C2) SHOW THE MAXIMUM PERMITTED CRACK LENGTHS WHEN ADJACENT HOLES ARE CRACKED. 75.0 mm (2.95 in)

A + B < 40.0 mm (1.57 in) A B FRONT SPAR

75.0 mm (2.95 in)

40.0 mm (1.57 in) TOP SKIN LEADING EDGE

TYPICAL CRACK 01

TOP SKIN LEADING EDGE

TYPICAL CRACK 01 FRONT SPAR **F W**  **D F**  **W D** 

**NOTE:** TEMPORARY REPAIRS OF CRACKS IN THIS AREA ARE NOT PERMITTED. TYPICAL CRACK FROM A FASTENER HOLE ADJACENT TO THE TOP SKIN LEADING EDGE. 01 Figure A-UCAAA - Sheet 02 SPECIFICATION FOR THE MAXIMUM PERMITTED CRACK LENGTH
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 22 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_DAAA_01_00 6.21 mm TO 6.26 mm

C/L OF PLUG HOLE LOCAL THICKNESS ’T’ EXTREMITY OF VISIBLE CRACK SKIN T

(0.2445 in TO 0.2465 in) (0.035 in TO 0.040 in)

TOP BOOM OF FRONT SPAR CRACK IN UNSUPPORTED SKIN

CSK 100° x 0.89 mm TO 1.02 mm

SEE SHEET 3 FOR DETAILS OF PLUG. **NOTE:**

Figure A-UDAAA - Sheet 01 TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 23 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_DAAA_02_00 OPERATION 1

OPERATION 2

OPERATION 3

RADIUS 0.76 mm TO 1.02 mm 1.14 mm TO 1.27 mm DRILL Ø 4.76 mm (0.1875 in)

0.64 mm TO 0.89 mm

1.02 mm TO 1.14 mm END MILL Ø 5.95 mm (0.2343 in)

REAM Ø 6.21 mm TO 6.26 mm RADIUS 0.76 mm TO 1.02 mm (0.025 in TO 0.035 in)

(0.040 in TO 0.045 in)

(0.2445 in TO 0.2465 in)

(0.045 in TO 0.050 in) (0.030 in TO 0.040 in) (0.030 in TO 0.040 in) DETAILS OF CRACK−STOP HOLE ABOVE SPAR BOOM

CSK 100° x 0.89 mm TO 1.02 mm (0.035 in TO 0.040 in)

Figure A-UDAAA - Sheet 02 TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 24 7

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# @A300-600 SERVICE BULLETIN

**CONF ALL

D_SB_576045_7_DAAA_03_00 SPAR B00M LUBRICANT HOLE (IF PLUG IS TO BE FITTED INTO UNSUPPORTED SKIN, DO NOT DRILL THIS HOLE.) 1.27 mm

0.76 mm
0.89 mm LENGTH AS SKIN THICKNESS

Ø 0.79 mm (0.031 in) DETAIL OF CRACK−STOP PLUG



### A



## A

PLUG TO BE MADE FROM BOLT EN6114−3−8 PLAIN LENGTH OF PLUG MUST BE IN CONTACT WITH FULL LENGTH OF THE HOLE IN THE SKIN PANEL. 01 **NOTE:** 01
(0.030 in)(0.050 in)

(0.035 in)

SKIN SKIN

Figure A-UDAAA - Sheet 03 TEMPORARY REPAIR OF A CRACK IN THE SPECIFIED INSPECTION AREAS
DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 25 7

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# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 26 7

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# @A300-600 SERVICE BULLETIN APPENDIX 01: INSPECTION REPORT **CONF ALL AIRBUS AIRBUS CUSTOMER SERVICES Structural Engineering E-mail: structure.sbinspectionresult@airbus.com FAX: +33 (0)5 61 93 36 14 Write the results of the inspection on the INSPECTION REPORT below and send them to AIRBUS SEES2. INSPECTION REPORT A/C MSN: FLIGHT CYCLES: FLIGHT HOURS: FINDINGS: YES/NO* SKETCH OF DAMAGE FOUND (INCLUDE CRACK LENGTH, CRACK DEPTH, EDGE DISTANCE, ETC): RECORD OF DAMAGE (INCLUDE HOLE LOCATION AND NUMBER, REPAIR METHOD, ETC)
SERVICE BULLETIN No.: DATE OF INSPECTION: SERVICE BULLETIN No.: DATE OF INSPECTION: SERVICE BULLETIN No.: DATE OF INSPECTION: PLEASE GIVE DETAILS OF ANY OTHER FINDINGS: AREA REPAIRED IN ACCORDANCE WITH:

WINGS - INSPECTION OF THE WING TOP SKIN BETWEEN THE FRONT SPAR JOINT AND THE LEADING EDGE OVERHANG BETWEEN RIBS 1 AND 7 * Delete as applicable

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - INSPECTION OF TOP SKIN AT FRONT SPAR BETWEEN RIBS 1 AND 7 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(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 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.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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# @A300-600 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 FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Mar 18/93 SERVICE BULLETIN No.: A300-57-6045 REVISION No.: 10 - Nov 13/13 Page: 1 7

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