# @ A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : 1 of 4 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 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM : 53 TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN SECTION 13 THRU 18 MODIFICATION No. : NONE This page transmits Revision No. 07 of Service Bulletin No. A300-53-0211. ADDITIONAL WORK There are areas which have been defined as new inspection areas in this Revision. These areas were not included in the previous issues and must be inspected at the next interval. REASON This Revision is issued to : — inform the affected operators that the inspection program detailed in this Service Bulletin has been refined to allow A300 B2/B4/C4 aircraft to reach the Limit Of Validity (LOV), — update the effectivity. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Reason amended. — EFFECTIVITY. Effectivity updatedPLANNING INFORMATION : — EFFECTIVITY . 1.A. Updated. — REASON

# @ A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — Objective/Action . 1.C.(2) Objective/Action amended. — Advantages . 1.C.(3) Advantages amended. — DESCRIPTION . 1.D. Description amended. — COMPLIANCE — Accomplishment Timescale . 1.E.(2) Sentence updated. — APPROVAL . 1.F. First sentence amended. — REFERENCES . 1.J. Updated. — TOOLING - PRICE AND AVAILABILITY . 2.F. References updated. ACCOMPLISHMENT INSTRUCTIONS : — GENERAL . 3.A.(1)(a) Reference changed to AMM 24-00-00. . 3.A.(1)(c) Reference changed to AMM. — Work Breakdown . 3.A.(3) Figure reference updated. . 3.A.(3)(a) Wording changed and NOTES relocated/updated. . 3.A.(3)(b) Revised. — INSPECTION . 3.B.(1) NOTE completed. . 3.B.(1)(a)1 Sentence amended. . 3.B.(1)(a)2 Special areas added . 3.B.(1)(a)2a Workstep amended.

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# @ A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . 3.D.(2) Reference changed to AMM 53-52-11. — Figure 1 . Sheet 1, Amended. — Figure 2 . Sheet 1, Amended. — Figure 3 . Sheets 1 thru 6, Amended. — Figure 4 . Sheet 1, Amended. — Figure 5 . Sheets 1 and 2, Amended. — Figure 6 . Sheets 1 thru 4, Amended. — Figure 7 . Sheet 1, New Figure. — Figure 8 . Sheets 7 and 8, Amended. — Figure 9 . Sheets 1 and 3, Amended. NOTE : Layout changes due to computerization of this revision are not identified. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS This history only describes the previous Revision No. 06 and subsequent. If information is required for revisions issued previous to this, please check your copies of the Revision Transmittal Sheet or contact AIRBUS.

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# @ A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Revision No. 06 was issued to change the inspection interval for bonded lap joints from 6,000 flights to 5,000 flights and to change the standard areas in Section 14 at STGR22 and STGR31 LH/RH to special areas with a threshold of 24,000 flights. REVISION SEQUENCE ORIGINAL : Nov 24/88 REVISION No. : 01 — Apr 10/89 REVISION No. : 02 — Jul 15/89 REVISION No. : 03 — Jan 18/91 REVISION No. : 04 — Jul 08/92 REVISION No. : 05 — Apr 29/99 REVISION No. : 06 — Feb 26/03 REVISION No. : 07 — Dec 01/06

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# @ A300 SERVICE BULLETIN SUMMARY

6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : 1 of 5 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 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM : 53 TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN SECTION 13 THRU 18 MODIFICATION No. : NONE REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES This Service Bulletin contains an inspection program for all longitudinal lap joints and repairs between FR18 and FR80 due to two major damages found at the end of full scale fatigue testing. The joint modifications are covered by Service Bulletins No. A300-53-0126, A300-53-0206, A300-53-0209, A300-53-0215 or A300-53-0216 and A300-53-0306. Test programs performed by the manufacturer on original test structures and specimens have led to a crack inspection which is divided into four categories : — Special Areas, — Standard Areas, — Repaired Areas, — Modified Areas. NOTE : Standard or Special Areas If Service Bulletin No. A300-53-0223 is not accomplished on aircraft up to MSN 0036, the first inspection must be performed as per Service Bulletin No. A300-53-0225. NOTE : Repair Areas If repairs do not correspond to the described solutions 1 thru 10 please contact AIRBUS - SEE81 for an individual inspection program. NOTE : Modified Areas The inspection program detailed in this Service Bulletin allows A300 B2/B4/C4 aircraft to reach the Limit Of Validity (LOV).

# @ A300 SERVICE BULLETIN SUMMARY

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : The inspections (threshold and follow-up inspections) are based on the use of heat-treated rivets as stated in SRM 51-40-30 and that allowable limits (residual thickness) have not been exceeded, if former damages (corrosion and/or scratches) have been removed with SRM 53-10-00 Diagr. 601. NOTE : The use of non-heat-treated aluminium rivets will reduce the inspection threshold significantly. If repairs are accomplished with non-heat-treated aluminium rivets, contact AIRBUS - SEE81 for further instructions. The inspection program detailed in this Service Bulletin allows A300 B2/B4/C4 aircraft to reach the Limit Of Validity (LOV).

EFFECTIVITY This Service Bulletin is applicable to these operator(s) : 50W 73X A2S ABR BCS BHY DHL F2I FLM IRA IRM KZU MNB NTR OHY RUN SGX TCN TDX TNO TSY This Service Bulletin is not applicable on aircraft MSN 0157 and subsequent due to the production embodiment of Mod. No. 2611 that improves the fatigue life of the longitudinal lap joints of the outer skin. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : None OEB : None AOT : None SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : None EVALUATION TABLE COMPLIANCE Mandatory CANCELS INSPECTION SB No AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN Yes VENDOR SB INVOLVED No KIT PRICE (USD) No kit

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# @ A300 SERVICE BULLETIN SUMMARY

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NATURE OF THE WORK AIRCRAFT : YES EQUIPMENT : NO HARD : NO SOFT : NO OBRM : NO MANPOWER MSN 0003 (Special areas)

MSN 0019-0156 (Special areas)

MSN 0003 , 0019-0156 (Standard areas)

NOTE : Estimates are based on one team including two inspectors. If more than one team is used, the manhours decrease accordingly. REPAIRED AREAS All hours listed below are calculated for one frame bay Repair solution 1 : SRM solution without cut out

Repair solution 2 : Old SRM solution with cut out

Repair solution 3 : Old SRM solution without cut out (inner skin only)

Repair solution 4 : SRM solution with cut out TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50

TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00

TOTAL MANHOURS 130.00 ELAPSED TIME (HOURS) 40.00

TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00

TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

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# @ A300 SERVICE BULLETIN SUMMARY

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Repair solution 4A : SRM solution with cut out

Repair solution 7 : Aircraft MSN 0095 at STGR52 LH, in Section 16

Repair solution 9 : Aircraft MSN 007 and 0095 solution at STGR44 LH/RH, in Sections 16 and 17

Repair solution 10 : Repair solution in accordance with repair drawing R53772132, issue C or Inspection Service Bulletin No. A300-53-0336 or A300-53-0341. Post repair inspections have to be carried out in accordance with this Service Bulletin, refer to figure 13.

MODIFIED AREAS All hours listed below are calculated for one frame bay Retrofit solution 1 : Retrofit lap joint (SB No. A300-53-0206 or A300-53-0209 with cut out)

Retrofit solution 2 : Retrofit lower shell (4 panel solution) (SB No. A300-53-0215). Additionally inspect STGR49 LH and STGR47 RH in Section 14

Retrofit solution 3 : Retrofit lower shell (3 panel solution) (SB No. A300-53-0216). Additionally inspect STGR54 LH in Section 14 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00

TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00

TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

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# @ A300 SERVICE BULLETIN SUMMARY

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Retrofit solution 4 : Retrofit lap joint (SB No. A300-53-0209 without cut out)

Retrofit solution 5 : Retrofit lap joint (SB No. A300-53-0223)

Retrofit solution 6 : Retrofit lap joint (SB No. A300-53-0306)

MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES NoneTOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

5

# @ A300 SERVICE BULLETIN

6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : 1 of 54 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 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM : 53 TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN SECTION 13 THRU 18 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 the 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 B2-1C B2-203 B2K-3C B4-103 B4-120 B4-203 B4-2C C4-203 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0003 0019 0035 0041 0044 0045 0047 0053 0055 0063 0073-0075 0078-0080 0082-0085 0090 0093-0095 0100 0101 0105-0107 0116 0117 0121 0123-0126 0128 0129 0133-0141 0146-0152 0154-0156 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (c) Effectivity by MSN and Kit/Configuration No AIRBUS kit is required for the accomplishment of this Service Bulletin. (3) Spares None B. CONCURRENT REQUIREMENTS None C. REASON (1) History This Service Bulletin contains an inspection program for all longitudinal lap joints and repairs between FR18 and FR80 due to two major damages found at the end of full scale fatigue testing. The joint modifications are covered by Service Bulletins No. OPERATOR MSN 50W 0003 73X 0146 A2S 0063 ABR 0148 BCS 0095 0116 0150 0152 BHY 0094 0128 DHL 0084 0085 0141 0149 F2I 0079 0093 0133 0135 0136 0137 0156 FLM 0082 0151 IRA 0080 IRM 0035 0055 KZU 0041 0044 0101 0106 0117 0139 0140 MNB 0019 0047 0123 0126 NTR 0124 0155 OHY 0138 RUN 0083 0105 0107 0121 0147 SGX 0090 TCN 0073 0125 0134 TDX 0053 0075 0100 0154 TNO 0045 0074 0078 TSY 0129

2

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved A300-53-0126, A300-53-0206, A300-53-0209, A300-53-0215 or A300-53-0216 and A300-53-0306. (2) Objective/Action Test programs performed by the manufacturer on original test structures and specimens have led to a crack inspection which is divided into four categories : — Special Areas, — Standard Areas, — Repaired Areas, — Modified Areas. NOTE : Standard or Special Areas If Service Bulletin No. A300-53-0223 is not accomplished on aircraft up to MSN 0036, the first inspection must be performed as per Service Bulletin No. A300-53-0225. NOTE : Repair Areas If repairs do not correspond to the described solutions 1 thru 10 please contact AIRBUS - SEE81 for an individual inspection program. NOTE : Modified Areas The inspection program detailed in this Service Bulletin allows A300 B2/B4/C4 aircraft to reach the Limit Of Validity (LOV). NOTE : The inspections (threshold and follow-up inspections) are based on the use of heat-treated rivets as stated in SRM 51-40-30 and that allowable limits (residual thickness) have not been exceeded, if former damages (corrosion and/or scratches) have been removed with SRM 53-10-00 Diagr. 601. NOTE : The use of non-heat-treated aluminium rivets will reduce the inspection threshold significantly. If repairs are accomplished with non-heat-treated aluminium rivets, contact AIRBUS - SEE81 for further instructions. (3) Advantages The inspection program detailed in this Service Bulletin allows A300 B2/B4/C4 aircraft to reach the Limit Of Validity (LOV). (4) Operational/Maintenance Consequences None

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# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Do the crack inspection. (2) Do the damage evaluation. (3) Do the crack classification and follow-up action. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale To allow a sufficient planning an application tolerance of 2000FC counted from receipt of this Service Bulletin is applicable as long as these values do not exceed 50% of the intervals. 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 given in this Service Bulletin but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under 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 operators' circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying time for paints, sealants, etc. and general administration work are also not included. MSN 0003 (Special areas) Inspection 7.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 7.50

4

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved MSN 0019-0156 (Special areas)

MSN 0003 , 0019-0156 (Standard areas)

NOTE : Estimates are based on one team including two inspectors. If more than one team is used, the manhours decrease accordingly. REPAIRED AREAS All times listed below calculated for one frame bay Repair solution 1 : SRM solution without cut out

Repair solution 2 : Old SRM solution with cut out

Repair solution 3 : Old SRM solution without cut out (inner skin only)

Repair solution 4 : SRM solution with cut out

Repair solution 4A : SRM solution with cut out Inspection 3.00 TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00
Inspection 130.00 TOTAL MANHOURS 130.00 ELAPSED TIME (HOURS) 40.00

Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75
Inspection 1.00 TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00
Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75
Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75
Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

5

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Repair solution 7 : Aircraft MSN 0095 at STGR52 LH, in Section 16

Repair solution 9 : Aircraft MSN 0073 and 0095 solution at STGR44 LH/RH, in Sections 16 and 17

Repair solution 10 : Repair solution in accordance with repair drawing R53772132, issue C or Inspection Service Bulletin No. A300-53-0336 or A300-53-0341. Post repair inspections have to be carried out in accordance with this Service Bulletin, refer to figure 13.

MODIFIED AREAS All times listed below calculated for one frame bay Retrofit solution 1 : Retrofit lap joint (SB No. A300-53-0206 or A300-53-0209 with cut out)

Retrofit solution 2 : Retrofit lower shell (4 panel solution) (SB No. A300-53-0215). Additionally inspect STGR49 LH and STGR47 RH in Section 14

Retrofit solution 3 : Retrofit lower shell (3 panel solution) (SB No. A300-53-0216). Additionally inspect STGR54 LH in Section 14

Retrofit solution 4 : Retrofit lap joint (SB No. A300-53-0209 without cut out) Inspection 1.00 TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00

Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75

Inspection 1.00 TOTAL MANHOURS 1.00 ELAPSED TIME (HOURS) 1.00

Inspection 0.50 TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

Inspection 0.50 TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

6

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Retrofit solution 5 : Retrofit lap joint (SB No. A300-53-0223)

Retrofit solution 6 : Retrofit lap joint (SB No. A300-53-0306)

H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES

K. PUBLICATIONS AFFECTED None Inspection 0.75 TOTAL MANHOURS .75 ELAPSED TIME (HOURS) 0.75
Inspection 0.50 TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50
Inspection 0.50 TOTAL MANHOURS .50 ELAPSED TIME (HOURS) 0.50

Aircraft Maintenance Manual (AMM) : 24-00-00 53-15-63 Nondestructive Testing Manual (NTM) : PART 1, 51-21-05 PART 1, 51-31-05 PART 1, 51-31-08 Nondestructive Testing Manual (NTM) : PART 4, 53-30-10, Config. 1 PART 4, 53-30-10, Config. 3 Nondestructive Testing Manual (NTM) : PART 6, 53-30-10, Config. 1 PART 6, 53-30-10, Config. 2 PART 6, 53-38-00 Structural Repair Manual (SRM) : 53-10-20 Service Bulletin (SB) : A300-53-0126 A300-53-0206 A300-53-0209 A300-53-0215 A300-53-0216 A300-53-0223 A300-53-0225 A300-53-0306 A300-53-0336 A300-53-0341

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# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved L. INTERCHANGEABILITY/MIXABILITY Not applicable

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# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — 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 To accomplish this Service Bulletin it is necessary to use the tools listed in : NTM PART 1, 51-21-05, 51-31-05, and 51-31-08 NTM PART 4, 53-30-10, Config. 01 and 03 NTM PART 6, 53-30-10, Config. 01, and 02, and 53-38-00 G. SPECIAL TOOLS None

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# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

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# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. (1) Preparation (a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00 Page block 301. (b) Put access platforms in position in the inspection areas. (c) Remove the wing-to-fuselage fairings, refer to AMM 53-52-11 Page block 401). (2) Standard Practices None (3) Work Breakdown (a) Repaired areas
TABLE 1A REPAIR SOLUTION DESCRIPTION THRESHOLD (FLIGHT CYCLES) FOR THE FIRST INSPECTION AFTER APPLICATION OF CORRESPONDING REPAIR SOLUTION FOLLOW-UP INSPECTIONS (FLIGHT CYCLES)

1 * SRM solution without cut out, refer to SRM 53-10-20 , Figure 701, Sheet 1 Refer to SRM 53-10-20 , Figure 701, Sheet 1A Refer to SRM 53-10-20 , Figure 701, Sheet 1A 4 SRM solution with cut out, refer to SRM 53-10-20 up to revision 49 (before Jan 01/88), Figure 701, Sheet 3 32,000 5,000

4A SRM solution with cut out, refer to SRM 53-10-20 revision 50 (Jan 01/88) and subsequent, Figure 701, Sheets 2 and 3 Refer to SRM 53-10-20 , Figure 701, Sheets 2A or 3A Refer to SRM 53-10-20 , Figure 701, Sheets 2A or 3A
7 Aircraft MSN 0095 at STGR52 LH, in Section 16 37,000 12,000

11

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved * Solution 1 is also applicable to the solution with removed inner doubler. NOTE : Sections of the Repair solutions are shown in Figure 8 and 13 ; except solution 4A. NOTE : The repair solution 4 can be determined from the inside only. 9 Aircraft MSN 0073 and 0095 solution at STGR44 LH/RH, in Sections 16 and 17 36,000 5,000

10 Repair solution in accordance with repair drawing R53772132, issue C or Inspection Service Bulletin No. A300-53-0336 or A300-53-0341. Post repair inspections have to be carried out in accordance with this Service Bulletin. Refer to Figure 13 20,000 11,000 REPAIR SOLUTION DESCRIPTION THRESHOLD (FLIGHT CYCLES) FOR THE FIRST INSPECTION AFTER APPLICATION OF CORRESPONDING REPAIR SOLUTION FOLLOW-UP INSPECTIONS (FLIGHT CYCLES)

12

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved TABLE 1B

NOTE : For extended repair solutions, refer to Figure 13 . NOTE : It is not necessary to inspect the repaired areas of solutions 2 and 3 until replacement by extended repairs. NOTE : The new repair solution has to be extended by one additional rivet row at both longitudinal sides, refer to Figure 8 , Sheet 7 thru Sheet 9 . NOTE : Sections of the repair solutions are shown in Figure 8 . The repair solutions 2 and 3 can be determined from the inside only. (b) Modified areas REPAIR SOLUTION DESCRIPTION : THRESHOLD (FLIGHT CYCLES) FOR REPAIR CHANGE THRESHOLD (FLIGHT CYCLES) FOR THE FIRST INSPECTION AFTER APPLICATION OF EXTENDED REPAIR SOLUTION FOLLOW-UP INSPECTIONS (FLIGHT CYCLES)

2 Old SRM solution with cut out 16,000 Refer to SRM 53-10-20 , Figure 701, Sheet 3A Refer to SRM 53-10-20 , Figure 701, Sheet 3A 3 Old SRM solution without cut out (outer skin) 16,000 Refer to SRM 53-10-20 , Figure 701, Sheet 2A Refer to SRM 53-10-20 , Figure 701, Sheet 2A

13

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved TABLE 2

NOTE : Sections of the retrofit solutions are shown in Figure 9 RETROFIT SOLUTION DESCRIPTION : THRESHOLD (FLIGHT CYCLES) FOR THE FIRST INSPECTION AFTER APPLICATION OF CORRESPONDING RETROFIT SOLUTION FOLLOW-UP INSPECTIONS (FLIGHT CYCLES) 1 Retrofit lap joint (SB No. A300-53-0206 or 53-0209 with cut out) 32,000 5,000
2 Retrofit lower shell (4 panel solution) (SB No. A300-53-0215) STGR43 LH (FR26-FR39), STGR43 RH (FR26-FR38) and STGR49 RH (FR26-FR38) 32,000 3,000

Retrofit lower shell (4 panel solution) (SB No. A300-53-0215) STGR46 RH (FR19-FR26) and STGR47 LH (FR26-FR39) and STGR51 LH (FR19-FR26) 32,000 5,700

3 Retrofit lower shell (3 panel solution) (SB No. A300-53-0216) STGR43 LH (FR26-FR39) and STGR43 RH (FR26-FR38) 32,000 3,000

Retrofit lower shell (3 panel solution) (SB No. A300-53-0216) STGR46 RH (FR19-FR26), STGR51 LH (FR19-FR26) STGR54 LH (FR26-FR39) 32,000 5,700

3A STGR43 LH/RH between FR37 and FR39 in Section 14 32,000 5,000 4 Retrofit lap joint (SB No. A300-53-0209 without cut out) 42,000 5,000 5 Retrofit lap joint (SB No. A300-53-0223) 42,000 5,000 6 Retrofit lap joint (SB No. A300-53-0306) 34,000 12,000 7 Retrofit lap joint (SB No. A300-53-0126) Refer to SRM 53-10-20, Figure 708, sheets 4, 5

14

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved B. INSPECTION (1) Crack inspection NOTE : All inspection results have to be forwarded to AIRBUS, Customer Service Directorate SEE81. (a) Inspection areas 1 Special areas Refer to Figure 4 , Sheet 1 and Sheet 2 2 Special and standard areas a MSN 0003 , 0019-0156 — Refer to Figure 3 , Figure 5 and Figure 6 — The areas with an inspection period given in Figure 3 must be modified by accomplishment of Modification Service Bulletins when the application period has been reached. The areas without an application period given in Figure 3 can be inspected by repetitive inspections till the Limit Of Validity (LOV) has been reached. No modification is necessary for these areas. 3 Repaired areas Refer to Table 1, Figure 8 , Sheet 1 to Sheet 9 and Figure 13 , Sheet 1 and Sheet 2 4 Modified areas Refer to Table 2 and Figure 9 (b) Inspection method 1 Special and standard areas Refer to Figure 1 and Figure 3 thru 6 . — Perform a manual eddy current test on all longitudinal lap joints (except in Section 17 <9> and the lap joint at STGR47 RH, between FR58 and FR65 and Section 18 <7>) according to NTM PART 6, 53-30-10, Config. 1 and Figure 4 , Figure 5 and Figure 6 . Section 17 <9> and the lap joint at STGR47 RH, between FR58 and FR65 have to be inspected in accordance with the NTM PART 6, 53-30-10, Config. 2.

15

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

Section 18 <7> has to be inspected in accordance with the NTM PART 6, 53-38-00. — The verification of cracks and determination of crack length have to be performed in accordance with NTM PART 6, 53-30-10, Config. 1 (except in Section 13 <4> and Section 17 <9>). Section 13 <4> and Section 17 <9> have to be inspected in accordance with the NTM PART 4, 53-30-10, Config. 3. — These areas have to be inspected in accordance with NTM PART 4, 53-30-10, Config. 1 : Where longitudinal joints and circumferential joints intersect, where rivets manufactured from steel or aluminium and rivets without countersunk heads are installed. 2 Repaired and modified areas Refer to Figure 2 and Figure 3 , Sheet 2 In principle there are two areas which have to be inspected depending on the repair/retrofit solution : — The area where cracks are to be expected is located in the concealed position in the lower layer. An inspection in accordance with the NTM PART 4, PART 4, 53-30-10, Config. 1 must be carried out. — The area where cracks are to be expected is located in the upper layer. An inspection in accordance with the NTM PART 1, 51-31-05 must be carried out. Refer to Figure 13 — The areas 1 and 2 have to be inspected in accordance with the NTM PART 1, 51-21-05). — The area 3 has to be inspected in accordance with the NTM PART 1, 51-31-08). (c) Inspection frequency Refer to Para. A.(3), Table 1A, 1B and 2. (2) Damage evaluation (a) If a crack is detected, inspect with ultrasonic test method the complete frame bay, plus the area on both sides of the frame bay for a distance of 8 rivet pitches.

16

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (3) Crack classification and follow-up action (a) Single and multiple cracks 1 A single crack is defined as one crack indication within 6 rivet pitches. 2 All other cracks are to be classified as multiple cracks. (b) Follow-up action 1 Special areas and standard areas with bonded doublers — Follow-up action after crack findings at longitudinal lap joints with bonded doublers, refer to Flow Chart 2, Figure 10 . 2 Standard areas without bonded doublers — Follow-up action after crack findings at longitudinal lap joints without bonded doublers, refer to Flow Chart 3, Figure 11 . 3 Repaired and modified areas — Follow-up action after crack findings, refer to Flow Chart 4, Figure 12 . C. TEST None D. CLOSE UP (1) Make sure that the work areas are clean and clear of tools and other items of equipment. (2) Install the wing-to-fuselage fairings, refer to AMM 53-52-11 Page block 401. (3) Remove the access platforms. E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

17

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 1 Sheet 1 Inspection Method for Standard and Special Areas

18

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 2 Sheet 1 Inspection Method for Repaired/Modified Areas and Areas where Eddy Current cannot be used

19

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 1 Inspection Threshold

20

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 2 Inspection Threshold

21

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 3 Inspection Threshold

22

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 4 Inspection Threshold

23

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 5 Inspection Threshold

24

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 3 Sheet 6 Inspection Threshold

25

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 4 Sheet 1 Inspection of Special Areas in Sections 14, 16 and 17

26

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 4 Sheet 2 Inspection of Special Areas in Sections 14, 16 and 17

27

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 5 Sheet 1 Inspection of Standard Areas in Sections 13 thru 15

28

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 5 Sheet 2 Inspection of Standard Areas in Sections 13 thru 15

29

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 6 Sheet 1 Inspection of Standard Areas in Sections 16 thru 18

30

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 6 Sheet 2 Inspection of Standard Areas in Sections 16 thru 18

31

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 6 Sheet 3 Inspection of Standard Areas in Sections 16 thru 18

32

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 6 Sheet 4 Inspection of Standard Areas in Sections 16 thru 18

33

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 7 Sheet 1 Additional Inspection of Upper Rivet Row in Sections 13 thru 18

34

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 1

Repaired Areas

35

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 2

Repaired Areas

36

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 3

Repaired Areas

37

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 4

Repaired Areas

38

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 5

Repaired Areas

39

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 6

Repaired Areas

40

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 7

Repaired Areas

41

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 8

Repaired Areas

42

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 8 Sheet 9

Repaired Areas

43

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 1 Inspection of Modified Areas

44

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 2 Inspection of Modified Areas

45

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 3 Inspection of Modified Areas

46

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 4 Inspection of Modified Areas

47

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 5 Inspection of Modified Areas

48

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 9 Sheet 6 Inspection of Modified Areas

49

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 10 Sheet 1 Flow Chart 2

50

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 11 Sheet 1 Flow Chart 3

51

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 12 Sheet 1 Flow Chart 4

52

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 13 Sheet 1

Repaired Areas

53

# @ A300 SERVICE BULLETIN

DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Figure 13 Sheet 2

Repaired Areas

54

# @ A300 SERVICE BULLETIN REPORTING SHEET

6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — Dec 01/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : FUSELAGE - INSPECT LONGITUDINAL LAP JOINTS FOR CRACKS IN SECTION 13 THRU 18 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.

# @ A300 SERVICE BULLETIN QUALITY PERCEPTION FORM

6 DATE : Nov 24/88 SERVICE BULLETIN No. : A300—53—0211 REVISION No. : 07 — 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.