# @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. 

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT FR56A, FR57A & FR73A **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During the aircraft preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 and STGR25, LH/RH. The crack initiation was found on the seal retainer run out rivet hole, near the frame web of door stops No.8. Because the emergency exit and AFT passenger/crew doors have the same structural door frame design, Airbus has decided to do a special detailed inspection of door frame FR56A, FR57A and FR73A. This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC) inspection of the seal retainer run out rivet hole at FR56A, FR57A and FR73A. Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will contribute to ensure the structural integrity of the door frame FR56A, FR57A and FR73A. 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: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A300-600 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION No Material EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

36V 67Q ABR BCS CES F2I FDX GBG I2L IRA IRM KAC MGC MNB MON MRJ MSR MXU SUD TAR THA 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 536175-832-848-001: Inspection TOTAL MANHOURS 10.75 ELAPSED TIME (HOURS) 4.50 APPENDICES Appendix 01 - Elapsed Time Assumption

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 2 6

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# @A300-600 SERVICE BULLETIN SUMMARY
**CONF ALL

Z250 Z260

OF DOOR FRAME HOLES 

### A

INSPECTION

FR76 FR58

LH SHOWN RH SYMMETRICAL 

## A FR73A FR57A
FR56A

D_SB_536175_6_SAAA_01_00 Figure A-GSAAA - Sheet 01
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 3 6

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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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT FR56A, FR57A & FR73A 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 B4-622R (2) Effectivity by MSN 0505 0521 0525 0529-0530 0532 0536 0543 0546 0553 0555 0557-0559 0561 0563 0572 0575 0577 0579 0581 0584 0602-0605 0607-0608 0611 0613 0617-0618 0621 0623 0625-0626 0629-0630 0632-0633 0637 0641 0643 0657 0659 0664 0666 0668 0670 0673 0677 0679 0681 0683 0688 0694 0696 0699 0701 0703 0705 0707 0709 0711 0713 0715 0717 0719 0721-0725 0727 0729-0730 0732-0734 0737 0739-0741 0743-0744 0746 0749-0750 0753-0754 0756 0762-0764 0767 0770 0773 0775 0782-0788 0797 0836-0838 (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: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN 36V 0605 67Q 0584 0603 0744 0749 0764 ABR 0683 0770 BCS 0602 0617 0621 0637 0641 0670 0679 0703 0711 0724 0729 0730 0737 0740 0753 0783 0797 0836 0837 CES 0707 0725 0732 0741 0746 0754 0763 F2I 0529 0557 FDX 0530 0536 0543 0555 0559 0572 0575 0579 0581 0611 0613 0625 0630 0633 0657 0659 0664 0668 0688 0709 0713 0715 GBG 0626 0643 I2L 0677 IRA 0632 0696 0723 0727 IRM 0546 0553 0608 0618 0623 0701 0773 0838 KAC 0673 0694 0699 0719 0721 MGC 0743 MNB 0521 0525 0532 0734 0739 0756 MON 0604 MRJ 0750 0762 MSR 0561 0607 MXU 0767 0788 SUD 0666 0775 TAR 0505 0558 0563 THA 0577 0629 0681 0705 0782 0784 0785 0786 0787 URS 0733 UZB 0717 0722 (4) Configuration by MSN MSN CONFIGURATION 0505 0521 0525 0529 0530 0532 0536 0543 0546 0553 0555 0557 0558 0559 0561 0563 0572 0575 0577 0579 0581 0584 0602 0603 0604 0605 0607 0608 0611 0613 0617 0618 0621 0623 0625 0626 0629 0630 0632 0633 0637 0641 0643 0657 0659 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 0727 0729 0730 0732 0733 0734 0737 0739 0740 0741 0743 0744 0746 0749 0750 0753 0754 0756 0762 0763 0764 0767 0770 0773 0775 0782 0783 0784 0785 0786 0787 0788 0797 0836 0837 0838 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.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 2 6

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# @A300-600 SERVICE BULLETIN (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History During the aircraft preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 and STGR25, LH/RH. The crack initiation was found on the seal retainer run out rivet hole, near the frame web of door stops No.8. Because the emergency exit and AFT passenger/crew doors have the same structural door frame design, Airbus has decided to do a special detailed inspection of door frame FR56A, FR57A and FR73A. (2) Objective/Action This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC) inspection of the seal retainer run out rivet hole at FR56A, FR57A and FR73A. (3) Advantages Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will contribute to ensure the structural integrity of the door frame FR56A, FR57A and FR73A. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 536175-832-848-001: Inspection (1) Do a HFEC inspection for cracks at FR56A LH (2) Do a HFEC Inspection for cracks at FR56A RH (3) Do a HFEC Inspection for cracks at FR57A LH (4) Do a HFEC Inspection for cracks at FR57A RH (5) Do a HFEC Inspection for cracks at FR73A LH (6) Do a HFEC Inspection for cracks at FR73A RH
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 3 6

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# @A300-600 SERVICE BULLETIN
E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 01: Config 001 - Inspection of seal retainer run out rivet hole at frame 56A, 57A and 73A Compliance Time Whichever occurs later Condition Action Threshold: Grace Period: Repetitive interval
Aircraft not covered by Special Detailed Inspection (SDI) TD_K4_S1_43707 _2013 at frame 56A, 57A and 73A Do a HFEC inspection of the seal retainer run out rivet hole at frame 56A, 57A and 73A 32000 FC from aircraft first flight Whichever occurs first between a) and b) a) 36000 FC from aircraft first flight or b) 36 months after the Service Bulletin issue date 7500 FC

Aircraft covered by Special Detailed Inspection (SDI) TD_K4_S1_43707 _2013 at frame 56A, 57A and 73A Do a HFEC inspection of the seal retainer run out rivet hole at frame 56A, 57A and 73A 7500 FC from TD’s embodiment none 7500 FC

Contact AIRBUS Repair Support Before the next flight none none Crack findings Report inspection result to AIRBUS Within 10 days none none Report inspection result to AIRBUS Within 1 month none none No crack findings Next HFEC inspection of the seal retainer run out rivet hole none none 7500FC

NOTE: TD_K4_S1_43707_2013 is applicable for MSN 0553 only F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031.
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 4 6

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# @A300-600 SERVICE BULLETIN 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 536175-832-848-001: Inspection Get Access 3.00 On Aircraft Do a HFEC inspection for cracks at FR56A LH 0.50 Do a HFEC Inspection for cracks at FR56A RH 0.50 Do a HFEC Inspection for cracks at FR57A LH 0.50 Do a HFEC Inspection for cracks at FR57A RH 0.50 Do a HFEC Inspection for cracks at FR73A LH 0.50 Do a HFEC Inspection for cracks at FR73A RH 0.50 Tests 4.50 Close-Up 0.25 TOTAL MANHOURS 10.75 ELAPSED TIME (HOURS) 4.50 NOTE: For a breakdown of the manhours and elapsed time, refer to the Gantt Chart Fig. A-GAAAA as given in Appendix 01 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-21-12 24-00-00 24-41-00 25-00-00 25-12-11 25-22-11 25-23-41 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-52-10 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 Structural Repair Manual (SRM) 51-24-00 51-40-20
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 5 6

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# @A300-600 SERVICE BULLETIN
K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531618-01-1 531814-01-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 6 6

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY No Material Set B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner-General - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools To accomplish this Service Bulletin it is necessary to use the tools listed in NTM 51-10-08, Page Block 601. (3) Special Tools None DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 7 6

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# @A300-600 SERVICE BULLETIN

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 536175-832-848-001 - 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. IN CASE OF 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. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin.
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 9 6

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# @A300-600 SERVICE BULLETIN
Task Associated Data Zone 250 260 Manpower TOTAL MANHOURS 10.75 ELAPSED TIME (HOURS) 4.50 A. GENERAL (1) Subtask 536175-910-201-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-52-10 Structural Repair Manual (SRM) 51-24-00 51-40-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML).. (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (e) Do a check of the electrical connectors before you connect them, refer to ESPM 20-52-10. (f) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) Use a non-metallic spatula to remove the sealant and clean the surface. (i) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 536175-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 10 6

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# @A300-600 SERVICE BULLETIN Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 536175-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH/RH 250 Work location Frame 57A LH/RH Frame 56A LH/RH Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 25-00-00, Page Block 801 25-22-11, Page Block 401 25-23-41, Page Block 401 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (c) Energize the ground service network, refer to AMM 24-41-00, Page Block 301. (d) Put an access platform in position of the MID and AFT doors 834, 844, 833 and 843. DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 11 6

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# @A300-600 SERVICE BULLETIN (e) Open, safety/lock and tag the applicable circuit breakers as specified in the removal of door frame linings, refer to AMM 25-23-41, Page Block 401. (f) At Frame 56A, Frame 57A and Frame 73A LH/RH , remove the door frame linings for access, refer to AMM 25-23-41, Page Block 401. (g) Put blanking caps on the disconnected electrical connectors. (h) Between Frame 56 and Frame 56A, Frame 57 and Frame 57A and between Frame 73 and Frame 73A, remove the heat and sound insulation blankets for access, refer to AMM 25-22-11, Page Block 401. (i) If necessary for repair of insulation blankets, refer to AMM 25-00-00, Page Block 801. C. PROCEDURE (1) Subtask 536175-250-202-001 - Do a HFEC inspection for cracks at FR56A LH Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 56A LH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBBAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 12 6

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# @A300-600 SERVICE BULLETIN (a) At Frame 56A, LH, between STGR 25 and STGR 25A as shown on Fig. A-GBBAA Sheet 01 , View A and Fig. A-GBBAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole at Frame 56A LH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBBAA Sheet 01 , View A, Fig. A-GBBAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBBAA Sheet 02, View B. 2 If there are no cracks: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. (2) Subtask 536175-250-201-001 - Do a HFEC Inspection for cracks at FR56A RH Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 56A RH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 13 6

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# @A300-600 SERVICE BULLETIN Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBBAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 (a) At Frame 56A RH, between STGR 25 and STGR 25A as shown on Fig. A-GBBAA Sheet 01 , View A and Fig. A-GBBAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole at Frame 56A RH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBBAA Sheet 01 , View A, Fig. A-GBBAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBBAA Sheet 02, View B. 2 If there are no crack: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 14 6

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# @A300-600 SERVICE BULLETIN (3) Subtask 536175-250-203-001 - Do a HFEC Inspection for cracks at FR57A LH Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 57A LH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBAAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 (a) At Frame 57A LH, between STGR 25 and STGR 25A as shown on Fig. A-GBAAA Sheet 01 , View A and Fig. A-GBAAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 15 6

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# @A300-600 SERVICE BULLETIN (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole atFrame 57A LH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBAAA Sheet 01 , View A, Fig. A-GBAAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet 02, View B. 2 If there are no crack: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. (4) Subtask 536175-250-204-001 - Do a HFEC Inspection for cracks at FR57A RH Work Zones and Access Panels Zone Access/Work location 250 Work location Frame 57A RH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 16 6

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# @A300-600 SERVICE BULLETIN
References Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBAAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 (a) At Frame 57A, RH, between STGR 25 and STGR 25A as shown on Fig. A-GBAAA Sheet 01 , View A and Fig. A-GBAAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole, at Frame 57A RH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBAAA Sheet 01 , View A, Fig. A-GBAAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet 02, View B. 2 If there are no cracks: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. (5) Subtask 536175-250-205-001 - Do a HFEC Inspection for cracks at FR73A LH Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH from Stringer 24 to Stringer 25

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 17 6

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBCAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 (a) At Frame 73A, LH, between STGR 24 and STGR 25 as shown on Fig. A-GBCAA Sheet 01 , View A and Fig. A-GBCAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole, at Frame 73A LH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBCAA Sheet 01 , View A, Fig. A-GBCAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBCAA Sheet 02, View B. 2 If there are no cracks: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 18 6

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# @A300-600 SERVICE BULLETIN
b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. (6) Subtask 536175-250-206-001 - Do a HFEC Inspection for cracks at FR73A RH Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 53A RH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 Fig. A-GBCAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 (a) At Frame 73A, RH, between STGR 24 and STGR 25 as shown on Fig. A-GBCAA Sheet 01 , View A and Fig. A-GBCAA Sheet 02, View B, clean the inspection surface area with: Textile-Lint Free Cotton - 14SBA1 As required

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 19 6

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# @A300-600 SERVICE BULLETIN Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of seal retainer run out hole, at Frame 73A RH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBCAA Sheet 01 , View A, Fig. A-GBCAA Sheet 02, View B and as shown on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBCAA Sheet 02, View B. 2 If there are no cracks: a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks: a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. D. TEST (1) Subtask 536175-720-201-001 - Functional Test Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH/RH 250 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401 25-23-41, Page Block 401 (a) BetweenFrame 56 and Frame 56A, Frame 57 and Frame 57A and between, Frame 73 and Frame 73A LH/RH, install the heat and insulation blankets, refer to AMM 25-12-11, Page Block 401. (b) Remove the blanking caps from the disconnected electrical connectors. (c) At Frame 56A, Frame 57A and Frame 73A, install the door frame linings , refer to AMM 25-23-41, Page Block 401.
DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 20 6

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# @A300-600 SERVICE BULLETIN (d) Remove the safety clips and/or the tags and close/unlock the applicable circuit breakers as specified after installation of door frame linings, refer to AMM 25-23-41, Page Block 401. (e) Do the applicable tests of exit lights as specified after installation of door frame linings, refer to AMM 25-23-41, Page Block 401. E. CLOSE-UP (1) Subtask 536175-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 260 Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the passenger MID and AFT passenger/crew doors 834, 844, 833 and 843. (c) Remove the access platforms.

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 21 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR26 STGR27 STGR25A

STGR30

STGR29 STGR25

FR56A FR57A

FR58

FR57.3

FR57.2

FR57.1

FR57

FR56 STGR28 Z250



## A LH SHOWN RH SYMMETRICAL SEAL RETAINER 

### A

**B**

D_SB_536175_6_BAAA_01_03 Figure A-GBAAA - Sheet 01 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 22 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR25

STGR25A

STGR26 FR57A

DOOR STOP 8 10.0 mm (0.39 in)

AREA TO BE INSPECTED. MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD. LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD SEALANT RETAINER STGR24



## B

D_SB_536175_6_BAAA_02_02 Figure A-GBAAA - Sheet 02 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 23 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR26 STGR27 STGR25A

STGR30

STGR29 STGR25

FR56A FR57A

FR58

FR57.3

FR57.2

FR57.1

FR57

FR56 STGR28



## A LH SHOWN RH SYMMETRICAL SEAL RETAINER



### B Z250


### A

D_SB_536175_6_BBAA_01_00 Figure A-GBBAA - Sheet 01 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 24 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

AREA TO BE INSPECTED. MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD. DOOR STGR23A

STGR24

STGR25
STGR25A
STOP 8 10.0 mm (0.39 in)

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFT SEAL RETAINER FR56A



## B

D_SB_536175_6_BBAA_02_00 Figure A-GBBAA - Sheet 02 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 25 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR18

STGR22X STGR22A STGR23 STGR24 STGR25 STGR26
STGR27 STGR28 STGR29 FR73 FR73A FR74 FR75 FR75A FR76

LH SHOWN RH SYMMETRICAL SEAL REATAINER Z260



### A



## A **B**

D_SB_536175_6_BCAA_01_00 Figure A-GBCAA - Sheet 01 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 26 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR22A

STGR23

STGR24

STGR25 FR73A

AREA TO BE INSPECTED. MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD. DOOR STOP 8

10.0 mm (0.39 in)

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFT SEAL RETAINER



## B

D_SB_536175_6_BCAA_02_00 Figure A-GBCAA - Sheet 02 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 27 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

NO CRACKS FOUND

CONTACT AIRBUS REPAIR SUPPORT BEFORE NEXT FLIGHT

REPORT INSPECTION RESULT WITHIN 10 DAYS TO AIRBUS 1 MONTH TO AIRBUS REPORT INSPECTION RESULT WITHIN

AT INTERVAL DO A REPETITIVE INSPECTION DO A SPECIAL DETAILED INSPECTION OF THE HOLES AT THRESHOLD DETAILED IN PARA. 1.E.(2)

YES

DETAILED IN PARA. 1.E.(2) FOR THE CRACKED FRAME(S)

ON NON−REPAIRED FRAME(S)

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE

D_SB_536175_6_FAAA_01_02 Figure A-GFAAA - Sheet 01 HFEC Inspection Flow Chart DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 28 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

YES NO RESULT OF INSPECTION CRACK ON FRAME No LEFT SIDE RIGHT SIDE 73A YES NO
57A 56A **INSPECTION REPORT**

DISCRIPTION OF FINDINGS SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A300−53−6175

DATE OF INSPECTION : INSPECTION METHOD : GENERAL INSPECTION DETAILED INSPECTION DETAILED INSPECTION VISUAL SPECIAL x RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Structure.sbinspectionresult@airbus.com FAX +33 (0)5 61 93 36 14 E−mail: CENTER WING BOX (WB/LR)

D_SB_536175_6_RAAA_01_02 Figure A-GRAAA - Sheet 01 HFEC inspection Reporting Sheet DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 29 6

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# @A300-600 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 30 6

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# @A300-600 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumption
**CONF ALL

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300−53−6175**

ON DOOR 843 MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 10.75 4.50 STEPS

0.50 0.50

10 0 INSPECTION DOOR 833 0.50 0.50

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 **NOTE:** PER

1

1

: : SB ELAPSED TIME (HOURS) 2 4 6 8 12

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. REMOVE FRAME LININGS
ON DOOR 834 2 REMOVE FRAME LININGS

INSPECTION DOOR 843 ON DOOR 844 0.50 2

INSPECTION DOOR 834 1.00 1.00 1 1.00 0.50

0.50 0.50 1 1.00 REMOVE FRAME LININGS

ON DOOR 833 0.75 0.375 1 INSTALL FRAME LININGS INSPECTION DOOR 844 1.00 1.00 1

ON DOOR 843 0.75 0.375 1 INSTALL FRAME LININGS ON DOOR 833 0.50 0.50 1 REMOVE FRAME LININGS

ON DOOR 844 1.50 0.75 2 INSTALL FRAME LININGS ON DOOR 834 1.50 0.75 2 INSTALL FRAME LININGS

CLOSE UP 0.25 0.25 1

D_SB_536175_6_AAAA_01_02

Figure A-GAAAA - Sheet 01 Gantt chart DATE: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES AT FR56A, FR57A & FR73A 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: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 1 6

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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: May 28/14 SERVICE BULLETIN No.: A300-53-6175 REVISION No.: 00 - May 28/14 Page: 1 6

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