# @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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT (ALTERNATE MOD : NONE) MODIFICATION No.: None This page transmits Revision No.03 of Service Bulletin No.A300-53-6042 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No.03 issued to revise the inspection threshold and intervals due to the life extension program. CHANGES SUMMARY MODIFICATIONS Minor editorial or document structure change N REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Minor editorial or document structure change N GENERAL EVALUATION Minor editorial or document structure change N MATERIAL PRICE INFORMATION Minor editorial or document structure change N EFFECTIVITY Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REFERENCES / REPERCUSSIONS Minor editorial or document structure change N NATURE OF THE WORK Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N APPENDICES Minor editorial or document structure change N Fig. A-GSAAA Minor editorial or document structure change N Fig. A-GSAAA Sheet 01 Minor editorial or document structure change N PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 1 6

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Configuration definition Minor editorial or document structure change N CONF 001 Minor editorial or document structure change N Material Effectivity Minor editorial or document structure change N Minor editorial or document structure change N CONCURRENT REQUIREMENTS Minor editorial or document structure change N REASON Minor editorial or document structure change N History Minor editorial or document structure change N Objective/Action Minor editorial or document structure change N Advantages Minor editorial or document structure change N Operational/Maintenance Consequences Minor editorial or document structure change N DESCRIPTION Minor editorial or document structure change N COMPLIANCE Minor editorial or document structure change N Classification Minor editorial or document structure change N Accomplishment Timescale Thresholds and Intervals amended N APPROVAL Minor editorial or document structure change N Minor editorial or document structure change N MANPOWER Minor editorial or document structure change N Minor editorial or document structure change N WEIGHT AND BALANCE Minor editorial or document structure change N ELECTRICAL LOAD DATA Minor editorial or document structure change N REFERENCES Minor editorial or document structure change N Minor editorial or document structure change N PUBLICATION AFFECTED Minor editorial or document structure change N Minor editorial or document structure change N INTERCHANGEABILITY/MIXABILITY Minor editorial or document structure change N SPARES Minor editorial or document structure change N MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N INDUSTRY SUPPORT INFORMATION Minor editorial or document structure change N LIST OF COMPONENTS Minor editorial or document structure change N Kit 536042D01R00 Minor editorial or document structure change N Kit 536042D02R00 Minor editorial or document structure change N Kit 536042D03R00 Minor editorial or document structure change N Kit 536042D04R00 Minor editorial or document structure change N Kit 536042D05R00 Minor editorial or document structure change N Kit 536042D06R00 Minor editorial or document structure change N Kit 536042D07R00 Minor editorial or document structure change N
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 2 6

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N Consumable CMLD01 Minor editorial or document structure change N Components Minor editorial or document structure change N Equipment Minor editorial or document structure change N PARTS TO BE RE-IDENTIFIED BY OPERATOR Minor editorial or document structure change N TOOLING Minor editorial or document structure change N Tooling - Price and Availability Minor editorial or document structure change N Procurement Addresses Minor editorial or document structure change N Price and Availability Minor editorial or document structure change N Tools Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 536042- 832-848-001-Inspection Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Subtask 536042-910-201-001 Minor editorial or document structure change N Subtask 536042-839-201-001 Minor editorial or document structure change N Subtask 536042-941-201-001 Minor editorial or document structure change N Subtask 536042-210-201-001 Minor editorial or document structure change N Subtask 536042-250-201-001 Minor editorial or document structure change N Subtask 536042-250-202-001 Minor editorial or document structure change N Subtask 536042-220-201-001 Minor editorial or document structure change N Subtask 536042-250-204-001 Minor editorial or document structure change N Subtask 536042-250-203-001 Minor editorial or document structure change N TASK 536042- 833-848-001-Repair Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Subtask 536042-941-202-001 Minor editorial or document structure change N Subtask 536042-911-202-001 Minor editorial or document structure change N Subtask 536042-942-202-001 Minor editorial or document structure change N Fig. A-GBAAA Minor editorial or document structure change N Fig. A-GBAAA Sheet 01 Minor editorial or document structure change N Fig. A-GFAAA Minor editorial or document structure change N Fig. A-GFAAA Sheet 01 Minor editorial or document structure change N Fig. A-GFBAA Minor editorial or document structure change N Fig. A-GFBAA Sheet 01 Minor editorial or document structure change N Fig. A-GFBAA Sheet 02 Minor editorial or document structure change N Fig. A-GFCAA Minor editorial or document structure change N Fig. A-GFCAA Sheet 01 Minor editorial or document structure change N Fig. A-GFDAA Minor editorial or document structure change N
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 3 6

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-GFDAA Sheet 01 Minor editorial or document structure change N Fig. A-GFDAA Sheet 02 Minor editorial or document structure change N Fig. A-GFEAA Minor editorial or document structure change N Fig. A-GFEAA Sheet 01 Minor editorial or document structure change N Fig. A-GFEAA Sheet 02 Minor editorial or document structure change N Fig. A-GBBAA Minor editorial or document structure change N Fig. A-GBBAA Sheet 01 Minor editorial or document structure change N Fig. A-GBCAA Minor editorial or document structure change N Fig. A-GBCAA Sheet 01 Minor editorial or document structure change N Fig. A-GBCAA Sheet 02 Minor editorial or document structure change N Fig. A-GBCAA Sheet 03 Minor editorial or document structure change N Fig. A-GBCAA Sheet 04 Minor editorial or document structure change N Fig. A-GBCAA Sheet 05 Minor editorial or document structure change N Fig. A-GBDAA Minor editorial or document structure change N Fig. A-GBDAA Sheet 01 Minor editorial or document structure change N Fig. A-GBEAA Minor editorial or document structure change N Fig. A-GBEAA Sheet 01 Minor editorial or document structure change N Fig. A-GBFAA Minor editorial or document structure change N Fig. A-GBFAA Sheet 01 Minor editorial or document structure change N Fig. A-GBGAA Minor editorial or document structure change N Fig. A-GBGAA Sheet 01 Minor editorial or document structure change N Fig. A-GBHAA Minor editorial or document structure change N Fig. A-GBHAA Sheet 01 Minor editorial or document structure change N Fig. A-GBJAA Minor editorial or document structure change N Fig. A-GBJAA Sheet 01 Minor editorial or document structure change N Fig. A-GBJAA Sheet 02 Minor editorial or document structure change N Fig. A-GBJAA Sheet 03 Minor editorial or document structure change N Fig. A-GBJAA Sheet 04 Minor editorial or document structure change N 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 01 was issued: to change the NTM procedure, for inspection Area 2, from X-ray to Eddy current to change the special Rotating probe procedure, for inspection Area 3, to a general Rotating probe procedure. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 4 6

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET to change the hole diameters, for fasteners which have to be installed after cold expansion, in Area 3. to make reference to the Service Information Letter 5SIL) 53-042 for the removal of possible corrosion in the inspection area after the removal of the anti-chafing plates. Revision 02 was issued to simplify the inspection procedure and to add the corner fitting replacement procedure. REVISION SEQUENCE ORIGINAL: May 06/94 REVISION No. : 01 - Feb 20/95 REVISION No. : 02 - Apr 28/98 REVISION No. : 03 - Aug 30/12

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 5 6

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# @A300-600 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 6 6

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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. 

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 53 

### TITLE: FUSELAGE - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT (ALTERNATE MOD : NONE) **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a full scale fatigue test, after 87675 simulated flights, a crack was found at the lower corner of the assembly of the horizontal-stabilizer cutout, between FR87 and FR89 and between STGR24 and STGR27, LH and RH. This Service Bulletin has been issued: - to inspect visually, without removal of sealant, the lower horizontal-stabilizer cutout longeron, the corner fitting, the skin strap and the skin between FR87 and FR89 and between STGR24 and STGR27, LH and RH, for cracks and corrosion. - to inspect with eddy current the flanges of the lower corner fittings and the edges of the outer skin which is designated Area 1. - to inspect with eddy current the edges of the longeron, the skin strap and the skin at the runout of the corner fitting above the last eight fasteners which is designated Area 2. - to inspect Area 3 by removing the specified fasteners from the assembly of the lower corner fittings, longerons, skin straps and skin, and do a rotating probe inspection of the fastener holes. When the fastener holes prove to be crack free, a cold expansion procedure is to be done as detailed in this Service Bulletin. NOTE: If cracks are detected in any of the affected areas, follow the repair solution as detailed in this Service Bulletin. The accomplishment of this Service Bulletin will prevent undetected cracks that could lead to extensive repairs and could reduce the flight loading residual strength capacity of the structure. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 1 6

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# @A300-600 SERVICE BULLETIN SUMMARY 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. MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 536042D01R00 2 5,700.00 Pin, collar, washer Kit 536042D02R00 2 1,360.00 Pin, collar, washer Kit 536042D03R00 2 8,300.00 Pin, collar, washer Kit 536042D04R00 1 3,870.00 Fitting Kit 536042D05R00 1 3,870.00 Fitting Kit 536042D06R00 2 4,280.00 Pin, collar, washer Kit 536042D07R00 2 7,940.00 Pin, collar, washer TOTAL 35,320.00 EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

83V F2I FDX IRM KAC 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 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 2 6

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# @A300-600 SERVICE BULLETIN SUMMARY SOFT NO OBRM NO MANPOWER Task 536042-832-848-001: Inspection TOTAL MANHOURS 88.00 ELAPSED TIME (HOURS) 44.00 Task 536042-833-848-001: Repair TOTAL MANHOURS 243.00 ELAPSED TIME (HOURS) 121.5 APPENDICES None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 3 6

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

INSPECTION AREA2 INSPECTION AREA1 SKIN STRAP

INSPECTION AREA1 INSPECTION AREA2 INSPECTION AREA3 LONGERON CORNER FITTING LOWER

OUTER SKIN FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH



## A

**C C**  **A**

**NOTE:** Z310



### B

RH SHOWN LH SYMMETRICAL 

## B

RH SHOWN LH SYMMETRICAL **FWD** INSPECTION AREA3
D_SB_536042_6_SAAA_01_00 Figure A-GSAAA - Sheet 01
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 4 6

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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 - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT (ALTERNATE MOD : NONE) 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 C4-620 (2) Effectivity by MSN 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0423 (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. OPERATOR MSN 83V 0423 F2I 0284 0294 0301 0307 0312 0317 0321 0336 0348 0351 FDX 0358 0361 0365 0388 0417 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 1 6

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# @A300-600 SERVICE BULLETIN
OPERATOR MSN IRM 0380 0401 0405 0408 0411 0414 KAC 0344 (4) Configuration by MSN MSN CONFIGURATION 0284 0294 0301 0307 0312 0317 0321 0336 0344 0348 0351 0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0423 001
(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft which do not have Modification No. 06146D5198 (FUSELAGE - TAIL CONE - REINFORCE LOWER TAIL PLACE CUTOUT) embodied. Modification No. 06146D5198 has been embodied, prior to delivery, on aircraft MSN 459 and subsequent. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 536042D01R00 2 Kit 536042D02R00 2 Kit 536042D03R00 2 Kit 536042D04R00 1 Kit 536042D05R00 1 Kit 536042D06R00 2 Kit 536042D07R00 2 Consumable CMLD01 1 NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes). Kit D01 is to do the work on one side only. Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A01 equals 2 Kits D01. NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD andlower anti-chafing plates instead of the complete removal of the antichafing plates. The cutout procedure reduces the manpower for the "Get Access" and "Close-Up" procedures. Kit D02 is to do the work on one side only. Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A02 equals 2 Kits D02. NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 2 6

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# @A300-600 SERVICE BULLETIN holes), if the next oversize is required. This kit should only be ordered if cracks are found during the rotating probe inspection. Kit D03 is to do the work on one side only. Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A03 equals 2 Kits D03. NOTE: Kit D04 is only applicable if the LH lower corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A04 equals 1 Kit D04. NOTE: Kit D05 is only applicable if the RH lower corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A05 equals 1 Kit D05. NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. The quantity of fasteners in this kit is sufficient only for the replacement of one corner fitting. The kit does not include the special bull-nose fasteners which are installed in the cold-expanded holes. These fasteners are to be found in Kit D01. Kit D06 is to do the work on one side only. Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A06 equals 1 Kit D06. NOTE: Kit D07 is only applicable if the lower corner fitting has been removed and a crack found in Area 1 after the fastener holes in Area 3 have been cold expanded. The quantity of fasteners in this kit is sufficient one side only. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 3 6

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# @A300-600 SERVICE BULLETIN This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in Area 1 after the cold expansion of Area 3. Kit D07 is to do the work on one side only. Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A07 equals 1 Kit D07. B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a full scale fatigue test, after 87675 simulated flights, a crack was found at the lower corner of the assembly of the horizontal-stabilizer cutout, between FR87 and FR89 and between STGR24 and STGR27, LH and RH. (2) Objective/Action This Service Bulletin has been issued: - to inspect visually, without removal of sealant, the lower horizontal-stabilizer cutout longeron, the corner fitting, the skin strap and the skin between FR87 and FR89 and between STGR24 and STGR27, LH and RH, for cracks and corrosion. - to inspect with eddy current the flanges of the lower corner fittings and the edges of the outer skin which is designated Area 1. - to inspect with eddy current the edges of the longeron, the skin strap and the skin at the runout of the corner fitting above the last eight fasteners which is designated Area 2. - to inspect Area 3 by removing the specified fasteners from the assembly of the lower corner fittings, longerons, skin straps and skin, and do a rotating probe inspection of the fastener holes. When the fastener holes prove to be crack free, a cold expansion procedure is to be done as detailed in this Service Bulletin. NOTE: If cracks are detected in any of the affected areas, follow the repair solution as detailed in this Service Bulletin. (3) Advantages The accomplishment of this Service Bulletin will prevent undetected cracks that could lead to extensive repairs and could reduce the flight loading residual strength capacity of the structure. (4) Operational/Maintenance Consequences None DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 4 6

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# @A300-600 SERVICE BULLETIN
D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 536042-832-848-001: Inspection (1) Visual inspection in Areas 1, 2 and 3, LH and RH (2) Eddy current inspection in Area 1, LH and RH (3) Eddy current inspection in Area 2, LH and RH (4) Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold expansion of specified fastener holes (5) Eddy current inspection in area 3 (6) Eddy current inspection of the longeron and outer skin Task 536042-833-848-001: Repair (1) Replacement of the lower corner fitting E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Table 1 (Aircraft with Average Flight Time above 1.5 hours) Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks 1 18000/38100 6000/12700

- 2 18000/38100 6000/12700

- 3 24000/50800

- To be combined with cold expansion, not before 18000FC/38100FH * NOTE: * If for any reason, the cold expansion in Area 3 is to be accomplished before the specified minimum number of flights or hours, contact Airbus for instructions. After reaching the subsequent thresholds, the intervals changes as given in Table 2 Table 2 (Aircraft with Average Flight Time above 1.5 hours) Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks 1 30000/63500 3900/8200

- 2 30000/63500 3900/8200

- 3 42500/89000 3900/8200

- DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 5 6

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# @A300-600 SERVICE BULLETIN
NOTE: For the requirements given in Table 2 a grace period of 1950FC/4100FH is allowed. Table 1 (Aircraft with an Average Flight Time up to or equal to 1.5 hours) Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks 1 19900/29800 6600/9900

- 2 19900/29800 6600/9900

- 3 26600/39800

- To be combined with cold expansion, not before 19900FC/29800FH * NOTE: * If for any reason, the cold expansion in Area 3 is to be accomplished before the specified minimum number of flights or hours, contact Airbus for instructions. After reaching the subsequent thresholds, the intervals changes as given in Table 2 Table 2 (Aircraft with an Average Flight Time up to or equal to 1.5 hours) Inspection Area Threshold (FC/FH) Interval (FC/FH) Remarks 1 33300/49800 4300/6400

- 2 33300/49800 4300/6400

- 3 47100/70500 4300/6400

- NOTE: For the requirements given in Table 2 a grace period of 2150FC/3200FH is allowed. NOTE: These mandatory inspections are required on all aircraft listed in this Service Bulletin not later than the corresponding total flight cycles or total flight hours, whichever comes first, applying to the configuration as detailed in Table 1 and Table 2. Repeat inspections are required at intervals not exceeding the related interval applying to the configuration as detailed in Table 1 and Table 2. NOTE: For area identification, refer to Fig. A-GBAAAof this Service Bulletin. NOTE: Aircraft which are approaching or have exceeded the threshold detailed in Table 1 should be inspected in accordance with the subsequent limits: - If aircraft are between 1500FC/2000FH less than the threshold or have exceeded the threshold by less than 1500FC/2000FH the first inspection is to be done within 1500FC/2000FH after receipt of this Service Bulletin. - For aircraft which have exceeded the threshold by more than 1500FC/2000FH the first inspection is to be done within 750FC/1000FH after receipt of this Service Bulletin. NOTE: The number of "Touch and Go flights" can be ignored when they are less than five percent of the total number of flights between two consecutive inspections. Each "Touch and Go flight" beyond five percent has to be DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 6 6

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# @A300-600 SERVICE BULLETIN
counted as a flight cycle. A "Touch and Go flight" is a landing in which an aircraft touches the runway and does not come to a complete stop prior to commencing an additional flight. 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. 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 536042-832-848-001: Inspection Get Access 58.00 On Aircraft Visual inspection in Areas 1, 2 and 3, LH and RH 2.00 Eddy current inspection in Area 1, LH and RH 8.00 Eddy current inspection in Area 2, LH and RH 2.00 Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold expansion of specified fastener holes 10.00 Eddy current inspection in area 3 2.00 Eddy current inspection of the longeron and outer skin 6.00 TOTAL MANHOURS 88.00 ELAPSED TIME (HOURS) 44.00 NOTE: Add the drying and vacuum process time for the anti-chafing plates to the elapsed time (Refer to SRM 53-19-12 for the recommended times). Task 536042-833-848-001: Repair Get Access 60.00 On Aircraft Replacement of the lower corner fitting 60.00 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 7 6

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# @A300-600 SERVICE BULLETIN Task 536042-833-848-001: Repair Close-Up 123.0 TOTAL MANHOURS 243.00 ELAPSED TIME (HOURS) 121.5 NOTE: Add the drying and vacuum process time for the anti-chafing plates to the elapsed time (Refer to SRM 53-19-12 for the recommended times). H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-31-53 24-00-00 52-41-00 55-12-11 55-15-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 53-19-26 Standards Manual (SM) Structural Repair Manual (SRM) 51-29-00 51-40-21 51-40-30 51-40-41 51-40-44 51-40-47 51-74-10 51-75-10 51-76-10 53-10-00 53-19-12 American Federal Specification: RR-S-366E FTI Tool List: FTI-A300-53-6042-1 Military Specification: MIL-G-9954A, MIL-S-13165B K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 8 6

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# @A300-600 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Kit 536042D01R00 Kit 536042D02R00 Kit 536042D03R00 Kit 536042D04R00 Kit 536042D05R00 Kit 536042D06R00 Kit 536042D07R00 Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability

Kit 536042D01R00 Cost 2,850.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D02R00 Cost 680.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D03R00 Cost 4,150.00 USD Availability 90 calendar days from receipt of order
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 9 6

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# @A300-600 SERVICE BULLETIN The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D04R00 Cost 3,870.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D05R00 Cost 3,870.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D06R00 Cost 2,140.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. Kit 536042D07R00 Cost 3,970.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 10 6

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# @A300-600 SERVICE BULLETIN
B. INDUSTRY SUPPORT INFORMATION Refer to the paragraph: ’Price and Availability’. C. LIST OF COMPONENTS Kit 536042D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 HLT637AP6-14 4 PIN 2 HLT637AP8-13 12 PIN 3 HLT286-6 4 COLLAR 4 HLT286-8 12 COLLAR 5 NAS1149D1165K 4 WASHER (1) 6 NSA5368PD416B 12 WASHER (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. NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes). Kit D01 is to do the work on one side only. Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A01 equals 2 Kits D01. NOTE (1): Install only if necessary. Kit 536042D02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 21 DAN6-5-4 9 PIN 22 DAN8-6-6X 3 PIN 23 DAN8-6-11X 1 PIN 24 DAN8-6-12X 1 PIN 25 DAN8-8-9X 1 PIN 26 DAN8-8-11X 1 PIN 27 DAN8-8-12X 1 PIN 28 DAN8-8-13X 3 PIN (1) 29 DAN12-6X 5 COLLAR 30 DAN12-8X 6 COLLAR 32 HL70-5 9 COLLAR 33 A5398402120000 9 WASHER 34 A5398402120200 5 WASHER 35 A5398402120400 6 WASHER DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 11 6

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# @A300-600 SERVICE BULLETIN
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. NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD and lower anti-chafing plates instead of the complete removal of the anti-chafing plates. The cutout procedure reduces the manpower for the "Get Access" and "Close-Up" procedures. Kit D02 is to do the work on one side only. Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A02 equals 2 Kits D02. NOTE (1): Alternative to Item 27 if a longer fastener is required. Kit 536042D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 11 HLT337AP8-14 4 PIN 12 HLT337AP10-13 12 PIN 13 HLT86-8 4 COLLAR 14 HLT86-10 12 COLLAR 15 NAS1149D0463K 4 WASHER (1) 16 NAS1149D0563K 12 WASHER (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. NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes), if the next oversize is required. This kit should only be ordered if cracks are found during the rotating probe inspection. Kit D03 is to do the work on one side only. Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A03 equals 2 Kits D03. NOTE (1): Install only if necessary. Kit 536042D04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 40 A5398613520290 1 FITTING DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 12 6

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# @A300-600 SERVICE BULLETIN
NOTE: Kit D04 is only applicable if the LH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A04 equals 1 Kit D04. Kit 536042D05R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 50 A5398613520390 1 FITTING NOTE: Kit D05 is only applicable if the RH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A05 equals 1 Kit D05. Kit 536042D06R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 22 DAN8-6-6X 27 PIN 23 DAN8-6-11X 7 PIN 27 DAN8-8-12X 12 PIN 28 DAN8-8-13X 12 PIN (1) 29 DAN12-6X 97 COLLAR 30 DAN12-8X 28 COLLAR 61 DAN7-6-5 10 PIN 62 DAN7-6-6X 16 PIN 63 DAN7-6-7X 11 PIN 64 DAN7-6-8X 7 PIN 66 DAN8-6-8X 17 PIN 67 DAN8-6-9X 22 PIN 69 DAN8-8-8X 16 PIN 72 DAN12-6 10 COLLAR 75 DAN14-6 10 COLLAR 76 LN9198-4012CF 20 RIVET 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. NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be replaced. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 13 6

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# @A300-600 SERVICE BULLETIN This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. The quantity of fasteners in this kit is sufficient only for the replacement of one corner fitting. The kit does not include the special bull-nose fasteners which are installed in the cold-expanded holes. These fasteners are to be found in Kit D01. Kit D06 is to do the work on one side only. Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A06 equals 1 Kit D06. NOTE (1): Alternative to Item 27 if a longer fastener is required. Kit 536042D07R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 100 HLT637AP6-12 2 PIN 101 HLT337AP8-12 2 PIN (1) 102 HLT337AP8-14 4 PIN 103 HLT337AP10-13 22 PIN 104 HLT86-8 6 COLLAR 105 HLT86-10 22 COLLAR 106 HLT286-6 2 COLLAR 107 NAS1149D1165K 2 WASHER (2) 108 NAS1149D0463K 6 WASHER (2) 109 NAS1149D0563K 22 WASHER (2) 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. NOTE: Kit D07 is only applicable if the lower corner fitting has been removed and a crack found in Area 1 after the fastener holes in Area 3 have been cold expanded. The quantity of fasteners in this kit is sufficient one side only. This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in Area 1 after the cold expansion of Area 3. Kit D07 is to do the work on one side only. Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A07 equals 1 Kit D07. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 14 6

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# @A300-600 SERVICE BULLETIN
NOTE (1): Alternative to Item 100 if the next oversize is required. NOTE (2): Install only if necessary. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Rust Inhibitor (for Corrosion Use 15-004) 05-027 As required Corrosion Inhibiting Brush Consistency 09-013 As required Corrosion Inhibitingfillet Consistency 09-016 As required Corrosion Inhibitingsealant Sprayable 09-025 As required Polysulphide Sealant For Interfay 09-048 As required Methyl Alcohol 11-006 As required Solvent General Purpose 11-026 As required Corrosion Preventive compound 15-004 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoatgrey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required Flexible Polyurethane 16-021 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses For the details of the tooling required for the cold expansion procedure of this Service Bulletin, refer to FTI Tool List No. FTI-A300-53-6042-1. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 15 6

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# @A300-600 SERVICE BULLETIN - The tooling details in the FTI Tool List is supplied by: FATIGUE TECHNOLOGY INC. (FTI) 150 ANDOVER PARK WEST P.O. BOX 88388 SEATTLE, WASHINGTON 98188 USA TELEPHONE : (206) 246-2010 TELEX : 321004 TELEFAX : (206) 244-9886 - The tool and the material required to carry out the shot peening process are: 1 shot propellant machine - VACU-Blast PHA 06-2 and Glass Beads Size 70. 0.1778 mm (0.007 in.) dia. - The shot propellant machine and the Glass Beads are supplied by : MUNK AND SCHMITZ Oberflaechentechnik Poller Kirchweg 92-104 51105 Koln Germany Telefon : (49) 0221 83908-33 Telefax : (49) 0221 83908-39 - The circular saw, DESOUTER RC 90, which is necessary to do the cutout procedure at the anti-chafing plates is supplied by : Desouter GmbH Druckluftwerkzeuge Edisonstrasse 1 63477 Maintal Germany Telefon : (49) 06181 4110 Telefax : (49) 06181 411187 NOTE: Any similar circular saw, which is available by local procurement, can be used. (b) Price and Availability None (2) Tools None (3) Special Tools None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 16 6

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# @A300-600 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 536042-832-848-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT CONTROL SURFACES OR ANY MOVING COMPONENTS, MAKE SURE THAT GROUND SAFETY LOCKS AND/OR WARNING NOTICES ARE IN THE CORRECT POSITION TO PREVENT ACCIDENTAL OPERATION. 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. Task Associated Data Zone 310 Manpower TOTAL MANHOURS 88.00 ELAPSED TIME (HOURS) 44.00 A. GENERAL (1) Subtask 536042-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 17 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 NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-21 51-40-30 51-40-44 51-75-10 Fig. A-GFAAA Flow Chart -A- (Visual Inspection - All Areas) Sheet 01 Fig. A-GFBAA Flow Chart -B- (Eddy Current Inspection - Area 1) Sheet 01 Sheet 02 Fig. A-GFCAA Flow Chart -C- (Eddy Current Inspection - Area 2) Sheet 01 Fig. A-GFDAA Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3) Sheet 01 Sheet 02 Fig. A-GFEAA Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion) Sheet 01 Sheet 02 (a) The following standard procedures apply only if a removal of the anti-chafing plates and/or a removal of rivets and/or a repair is required. 1 For the specification of materials (Mat. No.) given in this Service Bulletin (Refer to Consumable Material List (CML)). 2 For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). 3 If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 4 For the removal and installation of the fasteners (Refer to SRM 51-40-21). 5 For alternative and substitute fasteners (Refer to SRM 51-40-30). DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 18 6

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# @A300-600 SERVICE BULLETIN
6 For the repair of the paint coatings (Refer to SRM 51-75-10). 7 For the drill and deburr data (Refer to SRM 51-40-44). 8 Before you do the rotating probe inspection, clean all holes with: Solvent General Purpose 11-026 As required
9 Wet install fasteners with: Corrosion Inhibiting Brush Consistency 09-013 As required (b) Work Breakdown 1 For the various inspection/repair phases described in this Inspection Service Bulletin (ISB), refer to the Flow Charts Fig. A-GFAAA, Fig. A-GFBAA, Fig. AGFCAA, Fig. A-GFDAAand Fig. A-GFEAA

. (2) Subtask 536042-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 536042-941-201-001 - Preparation Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 52-41-00, Page Block 001 55-12-11, Page Block 401 55-15-11, Page Block 401 Structural Repair Manual (SRM) 53-19-12 Fig. A-GBBAA Preparation of Circular Saw Sheet 01

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 19 6

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# @A300-600 SERVICE BULLETIN
References Fig. A-GBCAA Make Cutouts in the FWD and Lower Anti-Chafing Plates Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page Block 301). (b) Open, safety/lock and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 21VU FAC1/28VDC 306CC1 103/G3 21VU FAC1/115VAC 309CC1 103/G5 21VU FAC1/26VAC 305CC1 103/G7 21VU FAC2/26VAC 305CC2 103/G8 21VU FAC2/115VAC 309CC2 103/G10 21VU FAC2/28VDC 306CC2 103/G12 (c) Put an access platform in position at the access door 312AR and at the horizontal stabilizer. (d) Open the access door 312AR (Refer to AMM 52-41-00, Page Block 001). (e) If the inspection in Area 3 is to be done using Solution 1 (Removal of the FWD and lower anti-chafing plates completely for access to the inspection area): 1 Remove and retain the Trimmable Horizontal Stabilizer (THS) aprons (LH and RH) adjacent to the inspection area (Refer to AMM 55-15-11, Page Block 401). 2 Remove and retain the THS leading edges (LH and RH) adjacent to the inspection area (Refer to AMM 55-12-11, Page Block 401). 3 CAUTION: TO PREVENT DAMAGE DURING THE REMOVAL OF THE ANTI-CHAFING PLATES, A HOT-AIR BLOWER MUST BE USED TO SOFTEN THE SEALANT. Remove the FWD and lower anti-chafing plates (LH and RH) (Refer to SRM 53-19-12). (f) If the inspection in Area 3 is to be done using Solution 2 (Make cutouts in the FWD and lower anti-chafing plates for access to the inspection area): Refer to Fig. A-GBCAA NOTE: The following worksteps are applicable for both sides of the aircraft (LH and RH).
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 20 6

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# @A300-600 SERVICE BULLETIN
1 Remove and retain the trimmable horizontal stabilizer aprons (LH and RH) adjacent to the inspection area (Refer to AMM 55-15-11, Page Block 401). 2 On the FWD and lower anti-chafing plates, draw the cut lines using the dimensions shown in Detail C. Use a soft lead pencil. 3 From the area of the FWD and lower cutouts, remove and discard the existing fasteners. 4 Prepare the circular saw to cut to the correct depth: Refer to Fig. A-GBBAA
a Remove the cutting disc from the circular saw. b Grind the edge of the cutting disk to an angle of 15 degrees.
c Install the cutting disc in the circular saw. d Adjust the depth of cut so that it does not exceed 0.55 mm (0.0217 in.).
e To make sure that the depth of cut is correct, make a sample cut in a strip of metal which is 0.6 mm (0.0236 in.) thick. 5 CAUTION: MAKE SURE THAT THE DEPTH OF CUT IS DEEPER ON THE ANTI-CHAFING PLATE SIDE OF THE CUT THAN THE CUTOUT SIDE. THIS WILL ENSURE THAT A CLEAN BREAK WILL BE MADE AT THE ANTI-CHAFING PLATE. THE EXCESS MATERIAL ATTACHED TO THE CUTOUT WILL BE REMOVED BEFORE RE-INSTALLATION. CAUTION: TO GUIDE THE CIRCULAR SAW, IT IS RECOMMENDED TO CLAMP STRAIGHT EDGES PARALLEL TO THE CUT LINES. Cut the FWD and lower anti-chafing plates as shown in Detail B, Sections A-A and B-B. 6 CAUTION: MAKE SURE THAT THE CUTOUTS ARE NOT DAMAGED DURING REMOVAL. THEY WILL BE RE-INSTALLED AFTER THE INSPECTION. Remove and retain the cutouts:
a Heat the edge of the cutout with a hot-air blower. b Carefully insert non-metallic wedges under the edge of the cutout. Continue heating the area directly in front of the wedges until the cutout is completely removed. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 21 6

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# @A300-600 SERVICE BULLETIN
7 Remove any old sealant from the fuselage skin with a non-metallic scraper. 8 Clean the fuselage skin with Solvent General Purpose 11-026 As required
C. PROCEDURE NOTE: For the accomplishment of the cold working procedures, as necessary forthis inspection, use the tools as listed in the Tool List Kit Number FTIA300-53-6042-1. NOTE: Inspection results must be reported to Airbus. If cracks are found, report in accordance with the related Service Bulletin instructions: - immediately (maximum 48 hours) if the damage exceeds allowable or rework limits. For more instructions contact Airbus before the next flight. - after completion of the corrective action when damage is within allowable or rework limits, or repaired in accordance with the related Service Bulletin instructions. If no cracks are found, the inspection record has to be sent as soon as the maintenance check or visit report, which involves the related Service Bulletin, has been completed. NOTE: All inspections are to be done in accordance with the thresholds given in Para. 1.E.(2) Compliance, Table 1 or Table 2. NOTE: The visual inspections have to be done every time a NDT inspection in Area 1, 2 or 3 has to be done. Only if the NDT inspection in Area 3 has to be done, the anti-chafing plates in the inspection area must be removed and the outer skin in this area visually inspected. NOTE: If corrosion is found on the outer skin in the inspection area, remove the corrosion (Refer to SRM 51-74-10 and SRM 53-10-00). NOTE: If an anti-chafing plate has not been removed and the corrosion extends under it, remove the anti-chafing plate and remove the corrosion (Refer to SRM 51-74-10 and SRM 53-10-00). (1) Subtask 536042-210-201-001 - Visual inspection in Areas 1, 2 and 3, LH and RH Work Zones and Access Panels Zone Access/Work location 310

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 22 6

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# @A300-600 SERVICE BULLETIN Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Rust Inhibitor (for Corrosion Use 15-004) 05-027 As required Corrosion Inhibitingfillet Consistency 09-016 As required Corrosion Inhibitingsealant Sprayable 09-025 As required Solvent General Purpose 11-026 As required Flexible Polyurethane 16-021 As required References Structural Repair Manual (SRM) 51-74-10 51-76-10 53-10-00 Fig. A-GBAAA Areas to be Inspected Sheet 01 Fig. A-GFAAA Flow Chart -A- (Visual Inspection - All Areas) Sheet 01

NOTE: Only if the rotating probe inspection in Area 3 has to be done, the antichafing plates must be removed and the outer skin in this area can be visually inspected. (a) Clean the inspection area with: Solvent General Purpose 11-026 As required (b) Visually inspect for cracks and corrosion, without the removal of the sealant, the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap and the skin between Frame 87 and Frame 89 and between STGR24 and STGR27, LH and RH. NOTE: This visual inspection has to be done every time a Non Destructive Testing (NDT) inspection in Area 1, 2 or 3 has to be done. Only if the inspection in Area 3 has to be done, then the FWD and lower anti-chafing plates have to be removed (or cutouts made in the FWD and lower anti-chafing plates) and the visual inspection of DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 23 6

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# @A300-600 SERVICE BULLETIN the outer skin in this area is required. 1 If corrosion is found on the outer skin in the inspection area it is recommended to remove the corrosion (Refer to SRM 51-74-10 and SRM 53-10-00). 2 If an anti-chafing plate is not removed and the corrosion extends under it, remove the anti-chafing plate and remove the corrosion (Refer to SRM 51-74-10 and SRM 53-10-00). 3 If cracks are detected, contact Airbus for instructions before the next flight. (c) Visually inspect for damaged sealant between Frame 87 and Frame 89 and between STGR24 and STGR27, LH and RH. 1 If the sealant is damaged, carefully remove the damaged sealantapproximately 100.0 mm (3.9 in.) from both sides of the damage. Use a nonmetallic scraper (Refer to SRM 51-76-10). 2 Clean the area, where the sealant has been removed, with Solvent General Purpose 11-026 As required
3 Apply Corrosion Inhibitingfillet Consistency 09-016 As required

or Corrosion Inhibitingsealant Sprayable 09-025 As required
to the areas where the sealant has been removed and apply Flexible Polyurethane 16-021 As required to the sealing beads (Refer to SRM 51-76-10). 4 Apply Rust Inhibitor (for Corrosion Use 15-004) 05-027 As required
to the inspection area.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 24 6

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# @A300-600 SERVICE BULLETIN (2) Subtask 536042-250-201-001 - Eddy current inspection in Area 1, LH and RH Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 8.00 Minimum number of person 2 Subtask elapsed time 4.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibitingfillet Consistency 09-016 As required Corrosion Inhibitingsealant Sprayable 09-025 As required Solvent General Purpose 11-026 As required Corrosion Preventive compound 15-004 Flexible Polyurethane 16-021 As required References Non Destructive Test Manual (NTM) 53-19-26, Page Block 601 Structural Repair Manual (SRM) 51-76-10 Fig. A-GFBAA Flow Chart -B- (Eddy Current Inspection - Area 1) Sheet 01 Sheet 02 Fig. A-GBAAA Areas to be Inspected Sheet 01 Fig. A-GBFAA Example of Crack Removal in Inspection Area 1 Sheet 01
(a) Do an eddy current inspection of inspection Area 1 (Refer to NTM 53-19-26, Page Block 601). (b) Compare the results of the inspection with the Flow Chart Refer to Fig. A-GBAAA Refer to Fig. A-GFBAA

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 25 6

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# @A300-600 SERVICE BULLETIN
1 If no crack(s) is (are) found:
a Clean the inspection area with Solvent General Purpose 11-026 As required
b Apply Corrosion Inhibitingfillet Consistency 09-016 As required

or Corrosion Inhibitingsealant Sprayable 09-025 As required
to the areas where the sealant has been removed and apply Flexible Polyurethane 16-021 As required to the sealing beads (Refer to SRM 51-76-10).
c Apply Corrosion Preventive compound 15-004 As required
to the inspection area where the corrosion preventive compound has been removed. d Repeat the inspection at the interval specified in Para. 1.E.(2) Compliance, Table 1 or Table 2. 2 If crack(s) is (are) found:
a Cracks are less than or equal to 2.0 mm (0.079 in.) long and not more than 2 cracks with a minimum distance of 50.0 mm (1.969 in.) between the cracks: <1> Remove the crack damage by milling a radius of between 10.0 mm (0.394 in.) minimum and 20.0 mm (0.787 in.) maximum, refer to Fig. A-GBFAA

. <2> Clean the reworked area. <3> Do an eddy current inspection of the reworked area (Refer to NTM 53-19-26, Page Block 601).
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 26 6

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# @A300-600 SERVICE BULLETIN <4> Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFBAA

. <a> If no crack(s) is (are) found: [1] Shot peen the reworked area, refer to Fig. A-GBFAA, as detailed in TASK 536042-833-848 001 Repair . [2] Repeat the inspection at the intervals detailed in Para. 1.E.(2) Compliance, Table 1 or Table 2. <b> If crack(s) is (are) found: [1] If the radius of the rework is less than the 20.0 mm (0.787 in.) minimum, increase the radius to 20.0 mm (0.787 in.), refer to Fig. A-GBFAA

. [2] Clean the reworked area with: Solvent General Purpose 11-026 As required [3] Do an eddy current inspection of the reworked area (Refer to NTM 53-19-26, Page Block 601). [4] Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFBAA

. [a] If no crack(s) is (are) found: - Shot peen the reworked area, refer to Fig. AGBFAA, as detailed in TASK 536042-833-848 001 Repair . - Repeat the inspection at the intervals detailed in Para. 1.E.(2) Compliance, Table 1 or Table 2. [b] If crack(s) is (are) found in the outer skin: - Contact Airbus for further instructions. [c] If crack(s) is (are) found in the corner fitting: - Remove the corner fitting as described in TASK 536042-833-848 001 Repair . [d] If Area 3 has not been cold expanded: - Install the new corner fitting as detailed in TASK 536042-833-848 001 Repair . Do not install the fasteners in Area 3.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 27 6

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# @A300-600 SERVICE BULLETIN - Do a rotating probe inspection in Area 3 as detailed in SUBTASK 536042-220-201 001 Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold expansion of specified fastener holes . [e] If Area 3 has been cold expanded: - Do an eddy current inspection of the longeron and outer skin as detailed in SUBTASK 536042-250-203 001 Eddy current inspection of the longeron and outer skin . [5] Cracks are longer than 2.0 mm (0.08 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.97 in.) between the cracks. [a] Remove the corner fitting as described in TASK 536042-833-848 001 Repair . [b] If Area 3 has not been cold expanded: - Install the new corner fitting as detailed in TASK 536042-833-848 001 Repair . Do not install the fasteners in Area 3. - Do a rotating probe inspection in Area 3 as detailed in SUBTASK 536042-220-201 001 Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold expansion of specified fastener holes . [c] If Area 3 has been cold expanded: - Do an eddy current inspection of the longeron and outer skin as detailed in SUBTASK 536042-250-203 001 Eddy current inspection of the longeron and outer skin . (3) Subtask 536042-250-202-001 - Eddy current inspection in Area 2, LH and RH Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 28 6

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# @A300-600 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 53-19-26, Page Block 601 Fig. A-GBAAA Areas to be Inspected Sheet 01 Fig. A-GFCAA Flow Chart -C- (Eddy Current Inspection - Area 2) Sheet 01

Refer to Fig. A-GBAAA Refer to Fig. A-GFCAA (a) Do an eddy current inspection of inspection Area 2 (Refer to NTM 53-19-26, Page Block 601). (b) Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFCAA

. 1 If no crack(s) is (are) found:
a Repeat the inspection at the interval specified in Para. 1.E.(2) Compliance, Table 1 or Table 2. 2 If crack(s) is (are) found:
a Contact Airbus before the next flight. (4) Subtask 536042-220-201-001 - Rotating probe inspection of specified fastener holes in Area 3, LH and RH, and cold expansion of specified fastener holes Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Kit 536042D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 HLT637AP6-14 4 PIN 2 HLT637AP8-13 12 PIN 3 HLT286-6 4 COLLAR 4 HLT286-8 12 COLLAR 5 NAS1149D1165K 4 WASHER (1) 6 NSA5368PD416B 12 WASHER (1) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 29 6

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# @A300-600 SERVICE BULLETIN
NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes). Kit D01 is to do the work on one side only. Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A01 equals 2 Kits D01. NOTE (1): Install only if necessary. Kit 536042D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 HLT337AP8-14 4 PIN 12 HLT337AP10-13 12 PIN 13 HLT86-8 4 COLLAR 14 HLT86-10 12 COLLAR 15 NAS1149D0463K 4 WASHER (1) 16 NAS1149D0563K 12 WASHER (1) NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes), if the next oversize is required. This kit should only be ordered if cracks are found during the rotating probe inspection. Kit D03 is to do the work on one side only. Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A03 equals 2 Kits D03. NOTE (1): Install only if necessary. Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 Structural Repair Manual (SRM) 51-40-41 Fig. A-GBAAA Areas to be Inspected Sheet 01 Fig. A-GFDAA Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3) Sheet 01 Sheet 02
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 30 6

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# @A300-600 SERVICE BULLETIN
References Fig. A-GBDAA Inspection Area 3 - Cold Expansion of the Fastener Holes Sheet 01

Refer to Fig. A-GBAAA Refer to Fig. A-GFDAA Refer to Fig. A-GBDAA NOTE: It is recommended that all inspections, as detailed in this Service Bulletin, be completed before cold expanding the holes. This will avoid having to install the next oversize fasteners in the event of a crack being found in the corner fitting, which would then have to be replaced. (a) From inspection Area 3, remove and discard: 4 Pins Item (1) 12 Pins Item (2) 4 Collars Item (3) 12 Collars Item (4) (b) Clean the fastener holes with: Solvent General Purpose 11-026 As required (c) Do a rotating probe inspection of the fastener holes (Refer to NTM 51-10-01, Page Block 601). (d) Compare the results of the inspection with the Flow Chart, refer to Fig. A-GFDAA

. 1 If no crack(s) is (are) found:
a Drill/ream the fastener holes to the applicable start diameters STDN 6-1- N and 8-1-N. NOTE: The minimum permitted fastener spacing, up to a fastener diameter of 6.4 mm (0.252 in.), is 14.0 mm (0.551 in.) measured from rivet hole center to rivet hole center. If the fastener diameter is equal to or exceeds 6.4 mm (0.252 in.), with a minimum spacing of 14.0 mm (0.551 in.), contact Airbus for instructions. NOTE: The distance between the hole center and the material edge should not be less than 1.5 x hole diameter. If this distance cannot be kept, contact Airbus for instructions. NOTE: If the distance between fastener holes to be cold DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 31 6

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# @A300-600 SERVICE BULLETIN expanded is less than 2 x hole diameter, install skin clamps in the adjacent holes and do the cold working procedure, step by step, one fastener hole after the other. b Cold expand the fastener holes and countersinks (Refer to SRM 51-40-41). c Ream the fastener holes with the applicable gage finish reamer. d Clean the fastener holes with: Solvent General Purpose 11-026 As required

e In the applicable fastener holes, wet install: 4 Pin HLT637AP6-14 Item 1 12 Pin HLT637AP8-13 Item 2 4 Collar HLT286-6 Item 3 12 Collar HLT286-8 Item 4 with: Corrosion Inhibiting Brush Consistency 09-013 As required
f If necessary, install: 4 Washer NAS1149D1165K Item 5 12 Washer NSA5368PD416B Item 6 under the collars, Item 3 and Item 4, to allow for slight variations in the structure. 2 If crack(s) is (are) found:
a Drill/ream the fastener holes to the applicable start diameters STDN 6-3- N and 8-3-N. NOTE: The minimum permitted fastener spacing, up to a fastener diameter of 6.4 mm (0.252 in.), is 14.0 mm (0.551 in.) measured from rivet hole center to rivet hole center. If the fastener diameter is equal to or exceeds 6.4 mm (0.252 in.), with a minimum spacing of 14.0 mm (0.551 in.), contact Airbus for instructions. NOTE: The distance between the hole center and the material edge should not be less than 1.5 x hole diameter. If this distance cannot be kept, contact Airbus for instructions. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 32 6

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# @A300-600 SERVICE BULLETIN
NOTE: If the distance between fastener holes to be cold expanded is less than 2 x hole diameter, install skin clamps in the adjacent holes and do the cold working procedure, step by step, one fastener hole after the other. b Clean the fastener holes with: Solvent General Purpose 11-026 As required

c Do a rotating probe inspection of the fastener holes (Refer to NTM 51-10-01, Page Block 601). d Compare the results of the inspection with the Flow Chart, refer to Fig. AGFDAA

. <1> If no crack(s) is (are) found: <a> Cold expand the fastener holes and countersinks (Refer to SRM 51-40-41). <b> Ream the fastener holes with the applicable gage finish reamer. <c> Clean the fastener holes with: Solvent General Purpose 11-026 As required <d> In the applicable fastener holes, wet install: 4 Pin HLT337AP8-14 Item 11 12 Pin HLT337AP10-13 Item 12 4 Collar HLT86-8 Item 13 12 Collar HLT86-10 Item 14 with: Corrosion Inhibiting Brush Consistency 09-013 As required <e> If necessary, install: 4 Washer NAS1149D0463K Item 15 12 Washer NAS1149D0563K Item 16 under the collars, Item 13 and Item 14, to allow for slight variations in the structure.
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 33 6

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# @A300-600 SERVICE BULLETIN <2> If crack(s) is (are) found: <a> Contact Airbus for further instructions before the next flight. (5) Subtask 536042-250-204-001 - Eddy current inspection in area 3 Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 References Non Destructive Test Manual (NTM) 53-19-26, Page Block 601 Structural Repair Manual (SRM) 53-19-12 Fig. A-GBAAA Areas to be Inspected Sheet 01
Refer to Fig. A-GBAAA NOTE: Eddy current inspection in area 3 at the threshold and interval as given in table 2 in para. E.(2) Accomplishment Timescale. (a) Completely remove the FWD and lower anti-Chafing plates as per SRM 53-19-12. (b) Clean the area to be inspected with: Solvent General Purpose 11-026 As required (c) Do an Eddy current inspection around each fastener head in area 3 (Refer to NTM 53-19-26, Page Block 601). 1 If no crack(s) is (are) found:
a Install the FWD and lower Anti-Chafing plates as per SRM 53-19-12. 2 If crack(s) is (are) found:
a Contact Airbus for further instructions before the next flight. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 34 6

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# @A300-600 SERVICE BULLETIN (6) Subtask 536042-250-203-001 - Eddy current inspection of the longeron and outer skin Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 536042D07R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 100 HLT637AP6-12 2 PIN 101 HLT337AP8-12 2 PIN (1) 102 HLT337AP8-14 4 PIN 103 HLT337AP10-13 22 PIN 104 HLT86-8 6 COLLAR 105 HLT86-10 22 COLLAR 106 HLT286-6 2 COLLAR 107 NAS1149D1165K 2 WASHER (2) 108 NAS1149D0463K 6 WASHER (2) 109 NAS1149D0563K 22 WASHER (2) NOTE: Kit D07 is only applicable if the lower corner fitting has been removed and a crack found in Area 1 after the fastener holes in Area 3 have been cold expanded. The quantity of fasteners in this kit is sufficient one side only. This kit should only be ordered if a crack, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in Area 1 after the cold expansion of Area 3. Kit D07 is to do the work on one side only. Kit A07 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A07 equals 1 Kit D07. NOTE (1): Alternative to Item 100 if the next oversize is required. NOTE (2): Install only if necessary.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 35 6

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# @A300-600 SERVICE BULLETIN
Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-10-01, Page Block 601 53-19-26, Page Block 601 Structural Repair Manual (SRM) 51-40-41 Fig. A-GBAAA Areas to be Inspected Sheet 01 Fig. A-GFEAA Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion) Sheet 01 Sheet 02 Fig. A-GBEAA Inspection Area 3 - Secondary Cold Expansion of the Fastener Holes if a Crack is Found in Area 1 after Primary Cold Expansion in Area 3 Sheet 01

Refer to Fig. A-GBAAA Refer to Fig. A-GFEAA Refer to Fig. A-GBEAA NOTE: This inspection is only required if the corner fitting has to be replaced and the fastener holes in Area 3 have already been cold expanded. (a) Clean the area to be inspected with: Solvent General Purpose 11-026 As required (b) Do an eddy current inspection (Refer to NTM 53-19-26, Page Block 601), in the area of three fastener holes, of each fastener row, both sides of the crack, where the corner fitting was attached to the longeron. 1 If no crack(s) is (are) found:
a Install the new corner fitting as detailed in TASK 536042-833-848 001 Repair . Do not install the fasteners in the area which has just been inspected. b Clean the fastener holes in the inspection area with: Solvent General Purpose 11-026 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 36 6

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# @A300-600 SERVICE BULLETIN

c Do a rotating probe inspection of the fastener holes (Refer to NTM 51-10-01, Page Block 601). <1> If no crack(s) is (are) found: <a> Drill/ream the fastener holes to the applicable start diameters STDN 6-1-N, 6-3-N and 8-3-N. <b> Cold expand the fastener holes and countersinks (Refer to SRM 51-40-41). <c> Ream the fastener holes with the applicable gage finish reamer. <d> Clean the fastener holes with: Solvent General Purpose 11-026 As required <e> In the applicable fastener holes, wet install: 2 Pin HLT637AP6-12 Item 100 4 Pin HLT337AP8-14 Item 102 22 Pin HLT337AP10-13 Item 103 2 Collar HLT286-6 Item 106 4 Collar HLT86-8 Item 104 22 Collar HLT86-10 Item 105 with: Corrosion Inhibiting Brush Consistency 09-013 As required <f> If necessary, install: 2 Washer NAS1149D1165K Item 107 6 Washer NAS1149D0463K Item 108 22 Washer NAS1149D0563K Item 109 under the collars, Item 106, Item 104 and Item 105, to allow for slight variations in the structure. <2> If crack(s) is (are) found in either or both of the two holes where it is possible to go to the next oversize: <a> Drill/ream the fastener holes to the applicable start diameters STDN 6-3-N. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 37 6

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# @A300-600 SERVICE BULLETIN
<b> Clean the fastener holes with: Solvent General Purpose 11-026 As required <c> Do a rotating probe inspection of the fastener holes (Refer to NTM 51-10-01, Page Block 601). [1] If no crack(s) is (are) found: [a] Cold expand the fastener holes and countersinks (Refer to SRM 51-40-41). [b] Ream the fastener holes with the applicable gage finish reamer. [c] Clean the fastener holes with: Solvent General Purpose 11-026 As required [d] In the applicable fastener holes, wet install: 2 Pin HLT337AP8-12 Item 101 2 Collar HLT86-8 Item 104 with: Corrosion Inhibiting Brush Consistency 09-013 As required [2] If crack(s) is (are) found: [a] Contact Airbus for further instructions before the next flight. <3> If crack(s) is (are) found in any of the other holes: <a> Contact Airbus for further instructions before the next flight. D. TEST None E. CLOSE-UP None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 38 6

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# @A300-600 SERVICE BULLETIN Task 536042-833-848-001 - Repair WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THE MATERIALS SPECIFIED IN THE PROCEDURE. 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. Task Associated Data Zone 310 Manpower TOTAL MANHOURS 243.00 ELAPSED TIME (HOURS) 121.5 A. GENERAL None B. PREPARATION (1) Subtask 536042-941-202-001 - Preparation Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Methyl Alcohol 11-006 As required
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 39 6

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# @A300-600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoatgrey (for Internal Applic.) 16-002 As required Wash Primer 16-020 As required References Structural Repair Manual (SRM) 51-29-00 51-75-10 Fig. A-GBFAA Example of Crack Removal in Inspection Area 1 Sheet 01 Fig. A-GBHAA Deflection Measurement Tool for Almen Test Piece Sheet 01 Fig. A-GBGAA Holding Fixture for Almen Test Piece Sheet 01
Refer to Fig. A-GBFAA Refer to Fig. A-GBGAA Refer to Fig. A-GBHAA NOTE: If necessary, flap peening, as detailed in SRM 51-29-00, can be used as an alternative to shot peening with the same intensity. NOTE: Operators who for any reason cannot accomplish the shot peening procedure or the alternative flap peening must contact Airbus for instructions. NOTE: Operators must be specifically trained to use the shot peening machine and to check test specimen deflection. NOTE: Crack detection inspection must be done prior to shot peening. NOTE: Where the name shot peening is given in the subsequent procedures, it refers to shot manufactured from glass. The specification for glass is given in MIL-G-9954A and MIL-S-13165B. NOTE: Shot must only be used again on materials that are of the same type. (a) Preparation 1 Make sure that the equipment and materials to be used are in good condition and that the machine keeps a constant blast pressure, to ensure the necessary precision.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 40 6

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# @A300-600 SERVICE BULLETIN
2 Pass the shot through the applicable series of sieves fitted with screens (Refer to the subsequent table). The screens must conform to American Federal Specification RR-S-366E. This will make sure that the shot is correct. NOMINAL BEAD SIZE SCREEN SIZE 70 (1) SCREEN SIZE 80 (1) SCREEN SIZE 120 (1) SCREEN SIZE 140 (1)(2) 70 0.1778 mm (0.007 in.) dia. 100% SHALL PASS THRU SIEVE 98% SHALL PASS THRU SIEVE MAX 8% SHALL PASS THRU SIEVE 0% SHALL PASS THRU SIEVE
NOTE (1): THE NUMBERS IN THESE COLUMNS ARE THE SCREEN SIZES TO BE USED IN THE SIEVES (REFER TO FED. SPEC. RR-S-366E). NOTE (2): WHEN THE SHOT IS IN USE IT MUST BE CHECKED ONCE EVERY 2 HOURS. IF MORE THAN 15% (BY WEIGHT) PASSES THROUGH THE SIEVE, CHANGE THE SHOT. 3 If the shot has been used before, one of the conditions which follow must be applied: - If the shot is to be used in a machine which has a continuous removal separator, make sure that the separator is correct for the shot dimension. - If the machine does not have a continuous removal separator, check of the shot at least once every 2 hours that it is in use. - If more than 15% (by weight) pass through the 0% sieve change the shot. 4 To shot peen the affected area correctly, blast it with the correct dimension shot to the correct intensity. To establish the correct intensity of 0.25 N, do a test on an Almen test strip. The result of this test gives an arc height, usually in millimeters (mm). Saturation time is the period of time in minutes that is required to peen the area to get: - the required intensity - the required coverage. The minimum time required is that time which, if doubled, would only give a 10% or less increase to the arc height (intensity). For example, if 4 minutes gives an arc height of 0.25 mm, after 8 minutes the arc height should not be more than 0.275 mm. If its is, repeat the test but with an increase of the first time (4 minutes). Repeat the test until the correct saturation time is found. NOTE: Use the Almen test strip once only for this test.

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 41 6

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# @A300-600 SERVICE BULLETIN Full coverage of the peened area must be checked visually, if necessary use a 10X magnifying glass. Coverage is specified as all the surface in the area showing identations which overlap. A repair procedure will usually specify a 100% coverage, this means that at least 98% of the surface must show evidence of peening. 5 Remove the paint/primer from the specified area (Refer to SRM 51-75-10). 6 Mask the structure around the specified area. Use masking tape (several layers), or rubber mats held in position with adhesive tape. (b) CAUTION: MAKE SURE THAT THERE IS NO RISK OF STRAY SHOT DAMAGING THE SURROUNDING STRUCTURE. Procedure for finding the intensity and saturation point required. 1 Put the applicable Almen test strip on the deflection measuring tool, refer to Fig. A-GBHAA. Set the dial test indicator of the tool to zero. 2 Put the test strip in the holding fixture, refer to Fig. A-GBGAA

. 3 Adjust the shot propellant machine to give the shot velocity specified in the repair procedure. If the velocity is not specified, adjust the machine to the manufacturer’s recommended working pressure or wheel speed. 4 WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS FOR THE MACHINE AND WEAR APPROVED PROTECTIVE CLOTHING. SHOT PEENING CAN BE DANGEROUS. Peen the test strip. To do this, for example, pass the shot stream across the test strip for 2 minutes. NOTE: Pass the shot stream across the test strip at a constant and continuous speed. 5 Remove the test strip from the holding tool and put it on the deflection measuring tool. Put the side of the strip which is not peened nearest to the indicator stem. Note this reading on the dial test indicator, this is the arc height. 6 Plot the graph to verify the arc height and exposure time. 7 If necessary, do the test procedure again but with a reduced or increased velocity as indicated by the graph. Use a new test strip for every test. Do the procedure again until you have the correct arc height. To make sure that the saturation point is correct (to give full coverage), do the test again but with double the final exposure time. The arc height should not increase more than 10%, if it does, start the test procedure again but with a longer exposure time.
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 42 6

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# @A300-600 SERVICE BULLETIN
8 Make a record of the arc height, saturation point, velocity and exposure time. Pass this record with the test strips to Quality Assurance Department for approval. (c) Peening the repaired area(s). 1 Load the shot propellent machine with shot that is the correct dimension and has been checked that it is free from defects. Fit the specified nozzle to the machine. Adjust the machine to give the shot the same velocity as in the test. 2 Peen the specified area. Make sure that the nozzle moves over the area at the same speed and time as in the test. 3 Examine the peened area to make sure that the correct coverage has been obtained. Continue the peening operation if necessary. NOTE: It is recommended to use a 10X magnifying glass or equivalent aid to do the examination. 4 Use a vacuum cleaner to remove any loose shot from the surrounding area, including the peened surface and any hidden areas. 5 Remove the tools from the work area. 6 Remove the masking tape and rubber mats. 7 WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIAL(S). YOU MUST OBEY THE OPERATOR’S AND MANUFACTURER’S HEALTH AND SAFETY INSTRUCTIONS. Clean the treated area using Methyl Alcohol 11-006 As required and apply Wash Primer 16-020 As required

, Anti-Corrosion Primer (polyurethane) 16-001 As required

and Polyurethane Topcoatgrey (for Internal Applic.) 16-002 As required

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 43 6

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# @A300-600 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 536042-911-202-001 - Replacement of the lower corner fitting Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 60.00 Minimum number of person 1 Subtask elapsed time 60.00 Skills AIRFRAME Material necessary to do the job Kit 536042D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 HLT637AP6-14 4 PIN 2 HLT637AP8-13 12 PIN 3 HLT286-6 4 COLLAR 4 HLT286-8 12 COLLAR NOTE: Kit D01 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes). Kit D01 is to do the work on one side only. Kit A01 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A01 equals 2 Kits D01. Kit 536042D03R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 11 HLT337AP8-14 4 PIN 12 HLT337AP10-13 12 PIN 13 HLT86-8 4 COLLAR 14 HLT86-10 12 COLLAR NOTE: Kit D03 is applicable for the accomplishment of the inspection in Area 3 (rotating probe inspection and cold expansion of specified fastener holes), if the next oversize is required. This kit should only be ordered if cracks are found during the rotating probe inspection. Kit D03 is to do the work on one side only.
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 44 6

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# @A300-600 SERVICE BULLETIN
Kit A03 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A03 equals 2 Kits D03. Kit 536042D04R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 40 A5398613520290 2 FITTING NOTE: Kit D04 is only applicable if the LH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A04 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A04 equals 1 Kit D04. Kit 536042D05R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 50 A5398613520390 2 FITTING NOTE: Kit D05 is only applicable if the RH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. Kit A05 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A05 equals 1 Kit D05. Kit 536042D06R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 22 DAN8-6-6X 27 PIN 23 DAN8-6-11X 7 PIN 27 DAN8-8-12X 12 PIN 28 DAN8-8-13X 12 PIN (1) 29 DAN12-6X 97 COLLAR 30 DAN12-8X 28 COLLAR 61 DAN7-6-5 10 PIN 62 DAN7-6-6X 16 PIN 63 DAN7-6-7X 11 PIN 64 DAN7-6-8X 7 PIN 66 DAN8-6-8X 17 PIN 67 DAN8-6-9X 22 PIN 69 DAN8-8-8X 16 PIN 72 DAN12-6 10 COLLAR 75 DAN14-6 10 COLLAR 76 LN9198-4012CF 20 RIVET DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 45 6

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# @A300-600 SERVICE BULLETIN
NOTE: Kit D06 is only applicable if the LH or RH corner fitting has to be replaced. This kit should only be ordered if cracks, longer than 2.0 mm (0.079 in.) or more than 2 cracks or 2 cracks with a distance of less than 50.0 mm (1.969 in.) between the cracks, are found in the fitting. The quantity of fasteners in this kit is sufficient only for the replacement of one corner fitting. The kit does not include the special bull-nose fasteners which are installed in the cold-expanded holes. These fasteners are to be found in Kit D01. Kit D06 is to do the work on one side only. Kit A06 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A06 equals 1 Kit D06. NOTE (1): Alternative to Item 27 if a longer fastener is required. Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Corrosion Inhibitingfillet Consistency 09-016 As required Solvent General Purpose 11-026 As required Anti-Corrosion Primer (polyurethane) 16-001 As required Polyurethane Topcoatgrey (for Internal Applic.) 16-002 As required
References Structural Repair Manual (SRM) 51-40-41 51-40-47 53-19-12 Fig. A-GBJAA Replacement of the Lower Corner Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 CAUTION: TO PREVENT DAMAGE DURING THE REMOVAL OF THE ANTICHAFING PLATES, A HOT-AIR BLOWER MUST BE USED TO SOFTEN THE SEALANT. NOTE: For the replacement of a LH corner fitting, use Kit D04 and Kit D06. NOTE: For the replacement of a RH corner fitting, use Kit D05 and Kit D06. NOTE: The procedure for the replacement of a corner fitting, is the same for DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 46 6

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# @A300-600 SERVICE BULLETIN
both sides. Refer to Fig. A-GBJAA (a) Remove the FWD anti-chafing plate, if not already removed (Refer to SRM 53-19-12). (b) Remove the lower anti-chafing plate, if not already removed (Refer to SRM 53-19-12) or make a cutout in the lower anti-chafing plate as described in SUBTASK 536042-941-201 001 Preparation . (c) Remove all old sealant from the work area with a non-metallic scraper. (d) Clean the work area with: Solvent General Purpose 11-026 As required (e) Remove: 4 Pin-Rivet HLT637AP6-14 Item (1) Discard 4 Collar-Hi-Lok HLT286-6 Item (3) Discard 12 Pin-Rivet HLT637AP8-13 Item (2) Discard 12 Collar-Hi Lok HLT286-8 Item (4) Discard 10 Pin-Rivet DAN7-6-5 Item (61) Discard 16 Pin-Rivet DAN7-6-6X Item (62) Discard 11 Pin-Rivet DAN7-6-7X Item (63) Discard 7 Pin-Rivet DAN7-6-8X Item (64) Discard 27 Pin-Rivet DAN8-6-6X Item (65) Discard 17 Pin-Rivet DAN8-6-8X Item (66) Discard 21 Pin-Rivet DAN8-6-9X Item (67) Discard 7 Pin-Rivet DAN8-6-11X Item (68) Discard 16 Pin-Rivet DAN8-8-8X Item (69) Discard 12 Pin-Rivet DAN8-8-12 Item (70) Discard 10 Collar DAN12-6 Item (72) Discard
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 47 6

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# @A300-600 SERVICE BULLETIN 97 Collar DAN12-6X Item (73) Discard 28 Collar DAN12-8X Item (74) Discard 10 Collar-Hi-Lok DAN14-6 Item (75) Discard (f) Remove: 20 Rivet LN9198-4012CF Item (76) Discard (g) Remove and retain the connecting angle, Item (41) (LH) or Item (51) (RH). (h) Remove and retain the T-profile, Item (42) (LH) or Item (52) (RH). (i) Remove and retain the fitting, Item (43) (LH) or Item (53) (RH). (j) Remove all the old sealant from the retained items with a non-metallic scraper. (k) Clean the retained items with: Solvent General Purpose 11-026 As required (l) CAUTION: TO AVOID DAMAGE TO THE FUSELAGE STRUCTURE, USE NON-METALLIC TOOLS TO REMOVE THE CORNER FITTING. Remove and discard the corner fitting, Item (40) (LH) or Item (50) (RH). (m) Remove all the old sealant from the fuselage structure with a non-metallic scraper. (n) Clean the fuselage structure with: Solvent General Purpose 11-026 As required (o) Temporarily install: 1 Fitting (LH) A5398613520290 Item 40 or 1 Fitting (RH) A5398613520390 Item 50 NOTE: Make sure that the corner fitting aligns with the contour of the horizontal stabilizer cutout. (p) Mark the fastener hole positions with a soft-lead pencil. (q) Remove the corner fitting and make sure there is enough edge clearance. (r) Install the corner fitting in the same position. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 48 6

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# @A300-600 SERVICE BULLETIN (s) Transfer drill the holes from the fuselage structure to the corner fitting with a pilot drill bush. (t) Open up the holes, which will not be cold-expanded, as necessary for the specified fasteners. (u) Remove the corner fitting, deburr the fastener holes and clean with: Solvent General Purpose 11-026 As required (v) Wet install: 1 Fitting (LH) A5398613520290 Item 40 1 Connecting angle (LH) Item (41) (Retained at removal) 1 T-Profile (LH) Item (42) (Retained at removal) 1 Fitting (LH) Item (43) (Retained at removal) or 1 Fitting (RH) A5398613520390 Item 50 1 Connecting angle (RH) Item (51) (Retained at removal) 1 T-Profile (RH) Item (52) (Retained at removal) 1 Fitting (RH) Item (53) (Retained at removal) with: Corrosion Inhibiting Brush Consistency 09-013 As required

NOTE: Use skin clamps to hold all items in the correct position (w) Drill/ream the fastener holes, which are to be cold expanded, to the correct start diameters. DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 49 6

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# @A300-600 SERVICE BULLETIN (x) Cold expand the fastener holes (Refer to SRM 51-40-41). (y) Ream the fastener holes to the correct finish diameters. (z) Re-countersink the fastener holes as necessary (Refer to SRM 51-40-47). (aa) Clean the fastener holes with: Solvent General Purpose 11-026 As required (ab) Wet install the fasteners: 4 Pin HLT637AP6-14 Item 1 4 Collar HLT286-6 Item 3 12 Pin HLT637AP8-13 Item 2 12 Collar HLT286-8 Item 4 4 Pin HLT337AP8-14 Item 11 12 Pin HLT337AP10-13 Item 12 4 Collar HLT86-8 Item 13 12 Collar HLT86-10 Item 14 27 Pin DAN8-6-6X Item 22 7 Pin DAN8-6-11X Item 23 12 Pin DAN8-8-12X Item 27 12 Pin DAN8-8-13X Item 28 97 Collar DAN12-6X Item 29 28 Collar DAN12-8X Item 30 10 Pin DAN7-6-5 Item 61 16 Pin DAN7-6-6X Item 62 11 Pin DAN7-6-7X Item 63 7 Pin DAN7-6-8X Item 64 17 Pin DAN8-6-8X Item 66 22 Pin DAN8-6-9X Item 67 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 50 6

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# @A300-600 SERVICE BULLETIN
16 Pin DAN8-8-8X Item 69 10 Collar DAN12-6 Item 72 10 Collar DAN14-6 Item 75 20 Rivet LN9198-4012CF Item 76 with: Corrosion Inhibiting Brush Consistency 09-013 As required (ac) Clean the work area with: Solvent General Purpose 11-026 As required (ad) Apply: Anti-Corrosion Primer (polyurethane) 16-001 As required

and Polyurethane Topcoatgrey (for Internal Applic.) 16-002 As required

to the heads and collars of the fasteners. (ae) Apply: Corrosion Inhibitingfillet Consistency 09-016 As required

around all edges of the corner fitting, connecting angle, T-profile and fitting. (af) Install the FWD anti-chafing plate (Refer to SRM 53-19-12). (ag) Install the lower anti-chafing plate or cutout as applicable (Refer to SRM 53-19-12). D. TEST None

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 51 6

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# @A300-600 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 536042-942-202-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Skills NON SPECIFIC Material necessary to do the job Kit 536042D02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 21 DAN6-5-4 9 PIN 22 DAN8-6-6X 3 PIN 23 DAN8-6-11X 1 PIN 24 DAN8-6-12X 1 PIN 25 DAN8-8-9X 1 PIN 26 DAN8-8-11X 1 PIN 27 DAN8-8-12X 1 PIN 28 DAN8-8-13X 3 PIN (1) 29 DAN12-6X 5 COLLAR 30 DAN12-8X 6 COLLAR 32 HL70-5 9 COLLAR 33 A5398402120000 9 WASHER 34 A5398402120200 5 WASHER 35 A5398402120400 6 WASHER NOTE: Kit D02 is only applicable if cutouts are to be made in the FWD andlower anti-chafing plates instead of the complete removal of the antichafing plates. The cutout procedure reduces the manpower for the "Get Access" and "Close-Up" procedures. Kit D02 is to do the work on one side only. Kit A02 from revision 02 or earlier of this Service Bulletin is still valid for this revision. The content of 1 Kit A02 equals 2 Kits D02. NOTE (1): Alternative to Item 27 if a longer fastener is required. Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting Brush Consistency 09-013 As required Polysulphide Sealant For Interfay 09-048 As required
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 52 6

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# @A300-600 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Aircraft Maintenance Manual (AMM) 52-41-00, Page Block 001 55-12-11, Page Block 401 55-15-11, Page Block 401 Structural Repair Manual (SRM) 51-75-10 53-19-12 Fig. A-GBCAA Make Cutouts in the FWD and Lower Anti-Chafing Plates Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 NOTE: Only if the rotating probe inspection in Area 3 has been done is the reinstallation of the removed anti-chafing plates or the re-installation of the removed cutouts necessary.(a) If the inspection in Area 3 has been done using Solution 1 (FWD and lower antichafing plates removed completely for access to the inspection area). 1 Do a visual inspection of the fuselage skin protective treatment in area of the anti-chafing plates (LH and RH). Repair the protective treatment if necessary (Refer to SRM 51-75-10). 2 Install the retained anti-chafing plates (LH and RH) (Refer to SRM 53-19-12). 3 Install the retained THS aprons (LH and RH) (Refer to AMM 55-15-11, Page Block 401). 4 Install the retained THS leading edges (LH and RH) (Refer to AMM 55-12-11, Page Block 401). 5 Make sure that the work area is clean and clear of tools and other items of equipment. 6 Close the access door 312AR (Refer to AMM 52-41-00, Page Block 001). 7 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 21VU FAC1/28VDC 306CC1 103/G3 21VU FAC1/115VAC 309CC1 103/G5 21VU FAC1/26VAC 305CC1 103/G7 21VU FAC2/26VAC 305CC2 103/G8 21VU FAC2/115VAC 309CC2 103/G10 21VU FAC2/28VDC 306CC2 103/G12 8 Remove the access platform(s). DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 53 6

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# @A300-600 SERVICE BULLETIN (b) If the inspection in Area 3 has been done using Solution 2 (Cutouts made in the FWD and lower anti-chafing plates for access to the inspection area). NOTE: The following worksteps are applicable for both sides of the aircraft (LH and RH). 1 Do a visual inspection of the fuselage skin protective treatment in area of the cutouts. Repair the protective treatment if necessary (Refer to SRM 51-75-10). 2 Mark on the fuselage skin, with a soft-lead pencil, the positions for the four fasteners indicated with NOTE 2 (Refer to Fig. A-GBCAA Sheet 02). 3 Pilot drill the dour new holes. 4 Open up the four holes to 4.12 mm (0.162 in.) minimum 4.16 mm (0.164 in.) maximum diameter. 5 Remove the existing fasteners from the three holes indicated with NOTES 1 and 5 (Refer to Fig. A-GBCAA Sheet 02). 6 Make the new attachment hole in the FWD anti-chafing plate:
a Insert a thin sheet of metal between the skin and the FWD anti-chafing plate in the area of the existing fastener indicated with the NOTES 1 and 6 (Refer to Fig. A-GBCAA Sheet 02). b Back drill through the existing fastener.
c Open up the hole in the FWD anti-chafing plate to 13.5 mm (0.53 in.). NOTE: Use a spot facing tool to open up the hole in the antichafing plate. d Remove the metal sheet and the remains of the fastener. 7 Make the new attachment hole in the lower anti-chafing plate:
a Insert a thin sheet of metal between the skin and the lower anti-chafing plate in the area of the pilot hole indicated with the NOTES 2, 3 and 7 (Refer to Fig. A-GBCAA Sheet 02). b Open up the hole in the fuselage to 4.12 mm (0.162 in.) minimum 4.16 mm (0.164 in.) maximum diameter. c Open up the hole in the lower anti-chafing plate to 10.0 mm (0.39 in.). NOTE: Use a spot facing tool to open up the hole in the antichafing plate. d Remove the metal sheet. 8 Temporarily install the cutouts.
DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 54 6

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# @A300-600 SERVICE BULLETIN
9 Transfer drill the new fastener holes to the cutouts. NOTE: Use a pilot drill bush to prevent damage to the existing holes. 10 Remove the cutouts. 11 Open up the holes in the cutouts marked with NOTE 4 to 10.0 mm (0.39 in.) (Refer to Fig. A-GBCAA Sheet 02). 12 Open up the holes in the cutouts marked with NOTE 5 to 13.5 mm (0.53 in.) (Refer to Fig. A-GBCAA Sheet 02). 13 Deburr the holes and edges of the cutouts. 14 Clean the cutouts and the fuselage skin with: Solvent General Purpose 11-026 As required

15 Apply: Polysulphide Sealant For Interfay 09-048 As required
to the contact surfaces of the cutouts. 16 Put the cutouts in position on the fuselage and remove any air trapped between the cutouts and the skin with a roller. 17 Wet install: 9 Pin DAN6-5-4 Item 21 9 Collar HL70-5 Item 32 9 Washer A5398402120000 Item 33 3 Pin DAN8-6-6X Item 22 3 Collar DAN12-6X Item 29 3 Washer A5398402120200 Item 34 1 Pin DAN8-6-11X Item 23 1 Collar DAN12-6X Item 29 1 Washer A5398402120200 Item 34 1 Pin DAN8-6-12X Item 24 1 Collar DAN12-6X Item 29 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 55 6

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# @A300-600 SERVICE BULLETIN
1 Washer A5398402120200 Item 34 1 Pin DAN8-8-9X Item 25 1 Collar DAN12-8X Item 30 1 Washer A5398402120400 Item 35 1 Pin DAN8-8-11X Item 26 1 Collar DAN12-8X Item 30 1 Washer A5398402120400 Item 35 1 Pin DAN8-8-12X Item 27 1 Collar DAN12-8X Item 30 1 Washer A5398402120400 Item 35 3 Pin DAN8-8-13X Item 28 3 Collar DAN12-8X Item 30 3 Washer A5398402120400 Item 35 with: Corrosion Inhibiting Brush Consistency 09-013 As required

18 Remove any excess sealant. 19 Vacuum clamp the cutouts to the fuselage (Refer to SRM 53-19-12). 20 Install the retained THS apron (Refer to AMM 55-15-11, Page Block 401). 21 Make sure that the work area is clean and clear of tools and other items of equipment. 22 Close the access door 312AR (Refer to AMM 52-41-00, Page Block 001). 23 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s) PANEL DESIGNATION FIN LOCATION SEE NOTES 21VU FAC1/28VDC 306CC1 103/G3 21VU FAC1/115VAC 309CC1 103/G5 21VU FAC1/26VAC 305CC1 103/G7 21VU FAC2/26VAC 305CC2 103/G8 21VU FAC2/115VAC 309CC2 103/G10 21VU FAC2/28VDC 306CC2 103/G12 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 56 6

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# @A300-600 SERVICE BULLETIN
24 Remove the access platform(s).

DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 57 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

SKIN STRAP

RH SHOWN LH SYMMETRICAL LONGERON CORNER FITTING LOWER

OUTER SKIN



## B **C A**  Z310 FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH 

### B



## A

INSPECTION AREA2 INSPECTION AREA1

INSPECTION AREA3 VISUAL INSPECTION

INSPECTION AREA1 INSPECTION AREA2 INSPECTION AREA3 **NOTE:**

VISUAL INSPECTION 20.0 mm (0.787 in) 20.0 mm (0.787 in)

STGR24RH

STGR26RH

STGR27RH 20.0 mm (0.787 in)

FR87 FR88 FR89 20.0 mm (0.787 in)



## C RH SHOWN LH SYMMETRICAL **FWD**
D_SB_536042_6_BAAA_01_00 Figure A-GBAAA - Sheet 01 Areas to be Inspected DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 58 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK (S) FOUND CLEAN THE AREAS TO BE INSPECTED

YES CORROSION FOUND 01 VISUAL INSPECTION IN AREAS 1, 2 AND 3 (LH/RH) NO KIT REQUIRED

01 VISUALLY INSPECT AREAS 1, 2 AND 3 FOR CRACKS AND CORROSION

SEALANT DAMAGED REMOVE CORROSION NO NO YES

01 VISUALLY INSPECT AREAS 1, 2 AND 3 FOR DAMAGED SEALANT

YES NO
REPAIR SEALANT

REPEAT THE INSPECTIONS AT THE INTERVALS DETAILED IN PARA. 1.E. (2)

AND THE OUTER SKIN IN THIS AREA VISUALLY INSPECTED CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

**NOTE:** ONLY IF THE ROTATING PROBE INSPECTION IN AREA 3 HAS TO BE DONE, 01 THE ANTI−CHAFING PLATES MUST BE REMOVED D_SB_536042_6_FAAA_01_01 Figure A-GFAAA - Sheet 01 Flow Chart -A- (Visual Inspection - All Areas) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 59 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

CLEAN THE AREA TO BE INSPECTED EDDY CURRENT INSPECTION IN AREA 1 (LH/RH) NO KIT REQUIRED

DO AN EDDY CURRENT INSPECTION IN AREA 1 CORNER FITTING FLANGE AND EDGE OF OUTER SKIN

CRACK (S)

FOUND NO YES

REPEAT THE INSPECTIONS AT THE INTERVALS DETAILED IN PARA. 1.E. (2) CRACK LENGTH LESS THAN OR EQUAL TO 2.0 mm (0.079 in) AND NOT MORE THAN TWO CRACKS WITH A

MINIMUM DISTANCE OF 50.0 mm (1.968 in) BETWEEN THE CRACKS CRACK LENGTH MORE THAN 2.0 mm (0.079 in) OR MORE THAN TWO CRACKS OR TWO CRACKS WITH A DISTANCE OF LESS THAN 50.0 mm (1.968 in) BETWEEN THE CRACKS

REMOVE DAMAGE FROM CORNER FITTING FLANGE OR EDGE OF OUTER SKIN BY MILLING A RADIUS OF BETWEEN 10.0 mm (0.394 in) MIN AND 20.0 mm (0.787 in) MAX

CLEAN THE REWORKED AREA SEE SHEET 2

SEE SHEET 2 D_SB_536042_6_FBAA_01_01 Figure A-GFBAA - Sheet 01 Flow Chart -B- (Eddy Current Inspection - Area 1) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 60 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

REPEAT THE EDDY CURRENT INSPECTION OF THE REWORKED AREA

CRACK (S)

FOUND NO YES

SHOT PEEN THE REWORKED AREA SEE SHEET 1

REPEAT THE INSPECTIONS

**NOTE:** IF, FOR ANY REASON, SHOT OR FLAP PEENING CANNOT BE 01 01

ACCOMPLISHED, CONTACT AIRBUS CLEAN THE REWORKED AREA

IF RADIUS IS LESS THAN THE 20.0 mm (0.787 in) MAX, INCREASE THE RADIUS TO 20.0 mm (0.787 in)

REPEAT THE EDDY CURRENT INSPECTION OF THE REWORKED AREA

NO

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS REMOVE CORNER FITTING

NO YES SEE SHEET 1

INSTALL NEW CORNER FITTING DO NOT INSTALL THE FASTENER IN INSPECTION AREA 3

DO A ROTATING PROBE INSPECTION IN AREA 3 (REFER TO FLOW CHART− FIGURE FDAA−01) DO AN EDDY CURRENT INSPECTION OF THE LONGERON AND OUTER

SKIN, IN THE AREA OF THREE FASTENER HOLES OF EACH FASTENER ROW, BOTH SIDES OF THE CRACK, WHERE THE CORNER

FITTING WAS ATTACHED TO THE

LONGERON (REFER TO FLOW

CHART−FIGURE A−GFEAA)

CRACK (S) FOUND IN CORNER FITTING CRACK (S) FOUND IN OUTER SKIN CRACK (S)

FOUND AREA 3 CLOD EXPANDED

AT THE INTERVALS

IN PARA. 1. E. (2)

D_SB_536042_6_FBAA_02_02 Figure A-GFBAA - Sheet 02 Flow Chart -B- (Eddy Current Inspection - Area 1) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 61 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK (S) FOUND CLEAN THE AREAS TO BE INSPECTED EDDY CURRENT INSPECTION IN AREAS 2(LH/RH) NO KIT REQUIRED

NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT REPEAT THE INSPECTIONS DO AN EDDY CURRENT INSPECTION IN AREA 2

AT THE INTERVALS DETAILED IN PARA. 1.E. (2)

D_SB_536042_6_FCAA_01_01 Figure A-GFCAA - Sheet 01 Flow Chart -C- (Eddy Current Inspection - Area 2) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 62 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

ROTATING PROBE INSPECTION OF SPECIFIED FASTENER HOLES IN AREA 3 (LH/RH)

REMOVE THE FASTENERS FROM THE SPECIFIED HOLES CRACK (S) FOUND NO YES
DRILL/REAM THE FASTENER HOLES TO THE NEXT APPLICABLE START DIAMETER

COLD EXPAND THE FASTENER

HOLES AND COUNTERSINKS CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

CRACK (S)

FOUND NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT DRILL/REAM THE FASTENER HOLES TO THE APPLICABLE START DIAMETER

DRILL/REAM THE FASTENER HOLES TO THE APPLICABLE FINAL DIAMETER

CLEAN THE FASTENER HOLES

WET INSTALL THE APPLICABLE FASTENERS CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION COMPLETELY REMOVE THE FWD AND LOWER ANTI−CHAFING PLATES OR MAKE CUTOUTS IN THE FWD AND LOWER ANTI−CHAFING PLATES

FURTHER INSPECTIONS ARE REQUIRED IN AREA 3 AT THE THRESHOLD AND INTERVALS GIVEN IN TABLE 2

SEE SHEET 2 D_SB_536042_6_FDAA_01_02 Figure A-GFDAA - Sheet 01 Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 63 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK (S) FOUND NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT PERFORM HFEC INSPECTION

IN AREA 3 AROUND EACH FASTENER HEAD COMPLETELY REMOVE THE

FORWARD AND LOWER ANTI−CHAFING PLATES

REPEAT INSPECTION AT INTERVALS GIVEN IN TABLE 2 HFEC INSPECTION IN AREA 3 AROUND EACH FASTENER HEAD (LH/RH) SEE SHEET 1

D_SB_536042_6_FDAA_02_01 Figure A-GFDAA - Sheet 02 Flow Chart -D- (Rotating Probe Inspection and Cold Expansion - Area 3) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 64 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

NO

DRILL/REAM THE FASTENER HOLES TO THE NEXT APPLICABLE START DIAMETER COLD EXPAND THE FASTENER

HOLES AND COUNTERSINKS

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

CRACK (S)

FOUND NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT DRILL/REAM THE FASTENER HOLES TO THE APPLICABLE START DIAMETER

DRILL/REAM THE FASTENER HOLES TO THE APPLICABLE FINAL DIAMETER

CLEAN THE FASTENER HOLES

WET INSTALL THE APPLICABLE FASTENERS

FURTHER INSPECTIONS ARE REQUIRED

IN AREA 3 AT THE THRESHOLD AND INTERVALS GIVEN IN TABLE 2 CRACK (S)

FOUND NO YES EDDY CURRENT INSPECTION OF THE LONGERON AND OUTER SKIN

CLEAN THE AREA TO BE INSPECTED

DO AN EDDY CURRENT INSPECTION IN THE AREA OF THREE FASTENER HOLES OF EACH FASTENER ROW, BOTH SIDES OF THE CRACK, WHERE THE CORNER FITTING WAS ATTACHED TO THE LONGERON

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT

CLEAN THE FASTENER HOLES

DO A ROTATING PROBE INSPECTION

INSTALL THE NEW CORNER FITTING BUT DO NOT INSTALL THE FASTENERS IN THE HOLES WHICH WILL BE COLD EXPANDED IF CRACK(S) ARE FOUND IN ANY OF THE OTHER HOLES IF CRACK(S) ARE FOUND IN EITHER OR BOTH OF THE TWO HOLES WHERE IT IS POSSIBLE TO GO TO THE NEXT OVERSIZE CRACK (S)

FOUND YES

SEE SHEET 2 D_SB_536042_6_FEAA_01_04 Figure A-GFEAA - Sheet 01 Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 65 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

CRACK (S) FOUND NO YES

CONTACT AIRBUS FOR FURTHER INSTRUCTIONS

BEFORE THE NEXT FLIGHT PERFORM HFEC INSPECTION

IN AREA 3 AROUND EACH FASTENER HEAD COMPLETELY REMOVE THE

FORWARD AND LOWER ANTI−CHAFING PLATES

REPEAT INSPECTION AT INTERVALS GIVEN IN TABLE 2 HFEC INSPECTION IN AREA 3 AROUND EACH FASTENER HEAD (LH/RH) SEE SHEET 1

D_SB_536042_6_FEAA_02_01 Figure A-GFEAA - Sheet 02 Flow Chart -E- (Eddy Current Inspection and Secondary Cold Expansion) DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 66 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL CIRCULAR SAW (DESOUTER RC90 OR SIMILAR)

0.55 mm (0.022 in)

CUTTING DISC GROUND TO AN ANGLE OF 15° DEPTH OF CUT

01 **NOTE:** TEST STRIP FOR SAMPLE CUT

200.0 mm (7.87 in)50.0 mm(1.968 in)

0.60 mm (0.024 in) 0.55 mm (0.022 in)

CORRECT METHOD OF CUTTING AN ANTI−CHAFING PLATE

CUTOUT ANTI−CHAFING PLATE STRAIGHT EDGE 

### A **A**



## A **A**

15° 01

0.55 mm (0.022 in)

D_SB_536042_6_BBAA_01_00 Figure A-GBBAA - Sheet 01 Preparation of Circular Saw DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 67 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

CUTOUT

REMOVE THIS WEDGE OF MATERIAL AFTER THE REMOVAL MAKE THE CUTS AS SHOWN IN SECTION B−B TO MAKE CUTOUT CUTLINE CUTLINE LOWER FWD ANTI−CHAFING PLATE ANTI−CHAFING PLATE

LOWER FWD CUTOUT CUTOUT ANTI−CHAFING PLATE

ANTI−CHAFING PLATE

OF THE CUTOUTS SURE THE WEDGES ARE ATTACHED TO THE CUTOUTS AND NOT TO THE REMAINING ANTI−CHAFING PLATES. FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH 

### A Z310



### B

01 02 **NOTE:** 

### A **A B**  **B B**  **B A**  **A** 

## A

01 02



## B 0.60 mm (0.024 in) 0.55 mm (0.022 in)
RH SHOWN LH SYMMETRICAL 

## A **A**

**B B**  TYPICAL TYPICAL 

### C **D**

D_SB_536042_6_BCAA_01_00 Figure A-GBCAA - Sheet 01 Make Cutouts in the FWD and Lower Anti-Chafing Plates DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 68 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

PLATE ATTACHMENT HOLESREMARKS

PLATE ATTACHMENT EXISTING FASTENERS HOLES 20.0 mm (0.787 in) 20.0 mm (0.787 in) 15.0 mm (0.59 in)

= = 20.0 mm (0.787 in)

20.0 mm (0.787 in) 20.0 mm (0.787 in)

NEW ANTI−CHAFING EXISTING ANTI−CHAFING

STGR29LH

STGR30LH FR88

01 02 03 04 05 06

07 **NOTE:** USE EXISTING FASTENER HOLE NEW FASTENER HOLE OPEN UP TO 4.12 mm (0.162 in) MIN 4.16 mm (0.164 in) MAX IN FUSELAGE OPEN UP TO 10.0 mm (0.39 in) IN ANTI−CHAFING PLATE OPEN UP TO 13.5 mm (0.53 in) IN ANTI−CHAFING PLATE BACK DRILL THROUGH EXISTING FASTENER INSERT THIN METAL SHEET BETWEEN SKIN AND ANTI−CHAFING PLATE OPEN UP HOLE IN ANTI−CHAFING PLATE TO 13.5 mm (0.53 in). USE SPOT FACING TOOL REMOVE METAL SHEET AND REMAINS OF FASTENER INSERT THIN METAL SHEET BETWEEN SKIN AND ANTI−CHAFING PLATE OPEN UP HOLE IN ANTI−CHAFING PLATE TO 10.0 mm (0.39 in). USE SPOT FACING TOOL REMOVE METAL SHEET 02 03 07 02 03 04 01 05 01 06 01 05 01 05



### D **D**

02 03 04

02 03 04 

## BEFORE



## C **C C** 

HOLE SYMBOL **FWD**

D_SB_536042_6_BCAA_02_00 Figure A-GBCAA - Sheet 02 Make Cutouts in the FWD and Lower Anti-Chafing Plates DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 69 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL



## C **C BEFORE** 

2.5 mm (0.10 in) 13.5 mm DIA (0.53 in)

0.3 mm (0.01 in)

2.5 mm (0.10 in) 10.0 mm DIA (0.39 in)

0.3 mm (0.01 in) 

## D **D** TYPICAL

TYPICAL

D_SB_536042_6_BCAA_03_00 Figure A-GBCAA - Sheet 03 Make Cutouts in the FWD and Lower Anti-Chafing Plates DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 70 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR29LH

STGR30LH FR88 

## AFTER

**FWD** 

## D

FOR FASTENER SYMBOLS, REFER TO SHEET 5 **NOTE:** D_SB_536042_6_BCAA_04_01 Figure A-GBCAA - Sheet 04 Make Cutouts in the FWD and Lower Anti-Chafing Plates DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 71 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

HOLE SYMBOL ITEM DESCRIPTION P/N

NSA5075−5 PIN COLLAR DAN6−5−4 A5393402120000 WASHER DAN12−6X PIN COLLAR DAN8−6−6X A5398402120200 WASHER DAN12−6X PIN COLLAR DAN8−6−11X A5398402120200 WASHER DAN12−6X PIN COLLAR DAN8−6−12X A5398402120200 WASHER DAN12−8X PIN COLLAR DAN8−8−9X A5398402120400 WASHER DAN12−8X PIN COLLAR DAN8−8−11X A5398402120400 WASHER DAN12−8X PIN COLLAR DAN8−8−12X A5398402120400 WASHER DAN12−8X PIN COLLAR DAN8−8−13X A5398402120400 WASHER EXISTING ANTICHAFING PLATE FASTENERS KIT

D02 QTY

9 21 32 33 22 29 34 3
23 29 34 1
24 29 34 1
25 30 35 1

1

1

3 26 30 35 27 30 35

FASTENERS NOT AFFECTED 28 30 35

D_SB_536042_6_BCAA_05_00 Figure A-GBCAA - Sheet 05 Make Cutouts in the FWD and Lower Anti-Chafing Plates DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 72 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

INSPECTION AREA2 INSPECTION AREA1

INSPECTION AREA3 FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH



## A **A** Z310



### B



## B

REMARKS MIN MAX 5.45 mm (0.215 in) 5.49 mm (0.216 in) FIT FINAL HOLE DIAMETER HOLE SYMBOL ITEM DESCRIPTION P/N

HLT286−6 PIN COLLAR HLT637AP6−14

AN960KD11 WASHER

HLT86−8 PIN COLLAR HLT337AP8−14 AN960KD416 WASHER

HLT286−8 PIN COLLAR HLT637AP8−13 NSA368PD416B WASHER HL86−10 PIN COLLAR HLT337AP10−13

AN960KD516 WASHER UNAFFECTED ANTI−CHAFING PLATE ATTACHMENT HOLES KIT

D03 QTY

4 11 13

12

HOLES NOT AFFECTED D01

D01

D03 1 (1) 3 (3) 5

INSTALL IF NECESSARY 01 **NOTE:** 01

15 01

12 14 2 (2) 4 (4) 6 01

16 01 1ST OVERSIZE INTERFERENCE

FIT 2ND OVERSIZE INTERFERENCE

FIT 1ST OVERSIZE INTERFERENCE

FIT 2ND OVERSIZE INTERFERENCE 6.25 mm (0.246 in) 6.29 mm (0.248 in)
7.04 mm (0.277 in) 7.08 mm (0.279 in)
7.85 mm (0.309 in) 7.88 mm (0.310 in) 6−3−N 6−1−N

8−1−N

8−3−N START DRILL

CBSD−6−1−N−1

CBSD−6−3−N−1

CBSD−8−1−N−1

CBSD−8−3−N−1 START REAMER

CBSR−6−1−N−1

CBSR−6−3−N−1

CBSR−8−1−N−1

CBSR−8−3−N−1 STDN GAGE FINISH REAMER

CBR−6−1−N−1−.2146

CBR−6−3−N−1−.2461

CBR−8−1−N−1−.2773

CBR−8−3−N−1−.3088

D_SB_536042_6_BDAA_01_01 Figure A-GBDAA - Sheet 01 Inspection Area 3 - Cold Expansion of the Fastener Holes DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 73 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

INSPECTION AREA2 INSPECTION AREA1

INSPECTION AREA3 FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH



## A **A** Z310



### B



## B

REMARKS MIN MAX 5.45 mm (0.215 in) 5.49 mm (0.216 in) FIT FINAL HOLE DIAMETER HOLE SYMBOL ITEM DESCRIPTION P/N

HLT286−6 PIN COLLAR HLT637AP6−12

AN960KD11 WASHER

HLT86−8 PIN COLLAR HLT337AP8−12 AN960KD416 WASHER

HLT86−8 PIN COLLAR HLT337AP8−14

AN960KD416 WASHER

HLT86−10 PIN COLLAR HLT337AP10−13

AN960KD516 WASHER UNAFFECTED ANTI−CHAFING PLATE ATTACHMENT HOLES KIT

D07 QTY

2

22

HOLES NOT AFFECTED 107

INSTALL IF NECESSARY 01 **NOTE:** 01

01

01

01 1ST OVERSIZE INTERFERENCE

FIT 2ND OVERSIZE INTERFERENCE

FIT 2ND OVERSIZE INTERFERENCE

FIT 2ND OVERSIZE INTERFERENCE 6.25 mm (0.246 in) 6.29 mm (0.248 in)
6.25 mm (0.246 in) 6.29 mm (0.248 in)
7.85 mm (0.309 in) 7.88 mm (0.310 in) 6−3−N 6−1−N

6−3−N

8−3−N START DRILL

CBSD−6−1−N−1

CBSD−6−3−N−1

CBSD−6−3−N−1

CBSD−8−3−N−1 START REAMER

CBSR−6−1−N−1

CBSR−6−3−N−1

CBSR−6−3−N−1

CBSR−8−3−N−1 STDN GAGE FINISH REAMER

CBR−6−1−N−1−.2146

CBR−6−3−N−1−.2461

CBR−6−3−N−1−.2461

CBR−8−3−N−1−.3088 4 106 100

108

104 101

108

104 102

109

105 103

D_SB_536042_6_BEAA_01_00 Figure A-GBEAA - Sheet 01 Inspection Area 3 - Secondary Cold Expansion of the Fastener Holes if a Crack is Found in Area 1 after Primary Cold Expansion in Area 3 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 74 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

THE REPAIRED AREA PLUS 10.0 mm (0.394 in) AROUND THE REPAIR IS BE SHOT PEENED

AREA TO BE SHOT PEENED OF 50.0 mm (1.969 in) BETWEEN EACH CRACK MAX 2 CRACKS WITH MIN TOTAL LENGTH OF CRACK TO BE REPAIRED MUST NOT EXCEED 2.0 mm (0.079 in) EXAMPLE OF CRACK REPAIR MAX 2.0 mm (0.079 in) MIN R 10.0 mm (0.394 in) MAX R 20.0 mm (0.787 in) SKIN STRAP

RH SHOWN LH SYMMETRICAL LONGERON CORNER FITTING LOWER

OUTER SKIN 

## B **A** Z310

01 MIN R 10.0 mm (0.394 in) MAX R 20.0 mm (0.787 in)



## BEFORE **AFTER**

**NOTE:** FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH



### A **A**



## E **D C**  **A A** 

01 01 

### E **B**



## A **C D** 

D_SB_536042_6_BFAA_01_00 Figure A-GBFAA - Sheet 01 Example of Crack Removal in Inspection Area 1 DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 75 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL24.0 mm(0.944 in)38.0 mm(1.496 in)

ALTERNATIVELY A NEAREST EQUIVALENT ROUND HEAD BOLTS CAN BE USED (THE BOLT HEADS MUST BE HARDENED). ONLY TIGHTEN THE BOLTS ENOUGH TO HOLD BOLTS 5.0 mm DIA (0.197 in) ALMEN TEST STRIP

THE TEST STRIP IN POSITION. 01 **NOTE:** 01 1.265 mm TO 1.315 mm (0.050 in TO 0.052 in)

19.0 mm (0.748 in)

75.82 mm TO 76.58 mm (2.985 in TO 3.015 in) (0.709 in) 18.0 mm (0.709 in) 18.0 mm (1.575 in) 40.0 mm 18.92 mm TO 19.05 mm (0.745 in TO 0.750 in) (0.275 in) 7.0 mm (0.275 in) 7.0 mm

D_SB_536042_6_BGAA_01_01 Figure A-GBGAA - Sheet 01 Holding Fixture for Almen Test Piece DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 76 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

ALMEN TEST PIECE. THE FACE WHICH IS NOT PEENED IS PUT NEAREST TO THE DIAL INDICATOR THE DIAL TEST INDICATOR SHOULD BE THIS ILLUSTRATION SHOWS THE GENERAL ARRANGEMENT DIMENSIONS ARE SHOWN).

GRADUATED TO 0.025 mm (0.001 in) FOR CHECKING THE DEFLECTION OF AN ALMEN TEST PIECE WITH A DIAL INDICATOR (ONLY THE IMPORTANT DIAL TEST INDICATOR

CONTACT SURFACE OF ALL BALLS TO BE IN ONE PLANE

GUIDE PINS

GUIDE PINS 6.0 mm DIA (0.236 in)
HARDENED STEEL BALLS

01 **NOTE:** 02

01

5.0 mm (0.197 in) HARDENED STEEL BALLS 5.0 mm (0.197 in) GUIDE PINS 6.0 mm DIA (0.236 in)

02 (0.366 in TO 0.374 in) 9.4 mm TO 9.6 mm

(0.366 in TO 0.374 in) 9.4 mm TO 9.6 mm (0.0788 in TO 0.0792 in) 1.95 mm TO 2.05 mm

(0.624 in) MAX 15.874 mm MAX (1.575 in) 40.0 mm

(0.622 in TO 0.626 in) 15.78 mm TO 15.97 mm

(0.624 in) MAX 15.874 mm MAX

(2.520 in) 64.0 mm (1.246 in TO 1.248 in) 31.70 mm TO 31.75 mm (0.307 in TO 0.317 in) 7.81 mm TO 8.06 mm

D_SB_536042_6_BHAA_01_00 Figure A-GBHAA - Sheet 01 Deflection Measurement Tool for Almen Test Piece DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 77 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

EDGE BEAM STRAP

LOWER CORNER FITTING SKIN

ARE TO BE COLD EXPANDED IN LOWER CORNER FITTING ONLY FASTENER HOLES WITH A SQUARE SYMBOL LONGERON



## B **A** Z310

01 **NOTE:** FR86 FR91

FR87 FR89 STGR24LH STGR27LH STGR24RH STGR27RH 

### B



## A

**A A**  FR87

(41)



### B

**B C** 

**C A**  **A D**  **C**

5.6 mm TO 5.9 mm DIA (0.220 in TO 0.232 in) DIA

MIN 5.11 mm (0.201 in) DIA MAX 5.15 mm (0.203 in) DIA



## C **C**

**B B** 

FOR FASTENER SYMBOLS, REFER TO SHEET 3 AND 4 LH SYMMETRICAL RH SHOWN 5.2 mm TO 5.5 mm DIA (0.205 in TO 0.217 in) DIA

MIN 5.11 mm (0.201 in) DIA MAX 5.15 mm (0.203 in) DIA 01

01 LH (51)RH

LH RH 40 (40) LH 50 RH (50)

D_SB_536042_6_BJAA_01_02 **FWD** VIEW LOOKING OUTBOARD Figure A-GBJAA - Sheet 01 Replacement of the Lower Corner Fitting DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 78 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

STGR21

STGR22

STGR23

STGR24

STGR25

STGR26 

### E



## C **D**

**E** 42 43 FR87

FR87 FR88

**NOTE:** FOR FASTENER SYMBOLS, REFER TO SHEET 4 

## D **D D** 

**D** 52 53 LH RH LH RH

D_SB_536042_6_BJAA_02_00 Figure A-GBJAA - Sheet 02 Replacement of the Lower Corner Fitting DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 79 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @A300-600 SERVICE BULLETIN

**CONF ALL

REMARKS MIN MAX 5.45 mm (0.215 in) 5.49 mm (0.216 in) FINAL HOLE DIAMETER HOLE SYMBOL ITEM DESCRIPTION P/N

HLT286−6 PIN COLLAR HLT637AP6−14

HLT86−8 PIN COLLAR HLT337AP8−14 KIT QTY

4 1ST OVERSIZE INTERFERENCE FIT 6−1−N START DRILL
CBSD−6−1−N−1 START REAMER
CBSR−6−1−N−1 STDN GAGE FINISH REAMER
CBR−6−1−N−1−.2146

13 11 1 (1) 3 (3) D01 D03 6−3−N CBSD−6−3−N−1 CBSR−6−3−N−1 CBR−6−3−N−1−.2461 6.25 mm (0.246 in) 6.29 mm (0.248 in) 2ND OVERSIZE INTERFERENCE FIT 7.04 mm (0.277 in) 7.08 mm (0.279 in) HLT286−8 PIN COLLAR HLT637AP8−13

HL86−10 PIN COLLAR HLT337AP10−13 12 1ST OVERSIZE INTERFERENCE FIT 8−1−N CBSD−8−1−N−1 CBSR−8−1−N−1 CBR−8−1−N−1−.2773

14 12 2 (2) 4 (4) D01 D03 8−3−N CBSD−8−3−N−1 CBSR−8−3−N−1 CBR−8−3−N−1−.3088 7.85 mm (0.309 in) 7.88 mm (0.310 in) 2ND OVERSIZE INTERFERENCE FIT
DAN12−8X PIN COLLAR DAN8−8−12X

DAN12−8X PIN COLLAR DAN8−8−13X 12 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 74 71 70(70) 74(74) D06 6.71 mm (0.264 in) 6.75 mm (0.265 in) OVERSIZE LONG TRANSITION FIT 6.71 mm (0.264 in) 6.75 mm (0.265 in) DAN12−8X PIN COLLAR DAN8−8−8X

DAN14−6 PIN COLLAR DAN8−6−11X 16 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 69(69) 74(74) D06 D06 5.11 mm (0.201 in) 5.15 mm (0.203 in) 1ST OVERSIZE TRANSITION FIT 68(68) 75(75) 7 HOLE NOT COLD EXPANDED ALT. 1ST

5.11 mm (0.201 in) 5.15 mm (0.203 in) DAN12−6X PIN COLLAR DAN8−6−9X

DAN14−6 PIN COLLAR DAN8−6−9X 19 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 67(67) 73(73) D06 D06 5.11 mm (0.201 in) 5.15 mm (0.203 in) 1ST OVERSIZE TRANSITION FIT 67(67) 75(75) 3 HOLE NOT COLD EXPANDED 5.11 mm (0.201 in) 5.15 mm (0.203 in) DAN12−6X PIN COLLAR DAN8−6−8X

DAN12−6X PIN COLLAR DAN8−6−6X 17 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 66(66) 73(73) D06 D06 5.11 mm (0.201 in) 5.15 mm (0.203 in) 1ST OVERSIZE TRANSITION FIT 65(65) 73(73) 27 HOLE NOT COLD EXPANDED

D_SB_536042_6_BJAA_03_00 Figure A-GBJAA - Sheet 03 Replacement of the Lower Corner Fitting DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 80 6

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# @A300-600 SERVICE BULLETIN

**CONF ALL

ANTI−CHAFING PLATE ATTACHMENT HOLES

TOOLING AND DRAIN HOLES REMARKS MIN MAX FINAL HOLE DIAMETER HOLE SYMBOL ITEM DESCRIPTION P/N KIT QTY START DRILL START REAMER STDN GAGE FINISH REAMER 5.11 mm (0.201 in) 5.15 mm (0.203 in) DAN12−6X PIN COLLAR DAN7−6−8X

DAN12−6X PIN COLLAR DAN7−6−7X 7 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 64(64) 73(73) D06 D06 5.11 mm (0.201 in) 5.15 mm (0.203 in) 1ST OVERSIZE TRANSITION FIT 63(63) 73(73) 11 HOLE NOT COLD EXPANDED 5.11 mm (0.201 in) 5.15 mm (0.203 in) DAN12−6X PIN COLLAR DAN7−6−6X

DAN12−6 PIN COLLAR DAN7−6−5 16 1ST OVERSIZE TRANSITION FIT HOLE NOT COLD EXPANDED 62(62) 73(73) D06 D06 4.78 mm (0.188 in) 4.82 mm (0.190 in) STANDARD TRANSITION FIT 61(61) 72(72) 10 HOLE NOT COLD EXPANDED LN9198−4012CF RIVET D06 4.06 mm (0.160 in) 4.17 mm (0.164 in) STANDARD 76(76) 20 HOLE NOT COLD EXPANDED

HOLES NOT AFFECTED

D_SB_536042_6_BJAA_04_01 Figure A-GBJAA - Sheet 04 Replacement of the Lower Corner Fitting DATE: May 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 81 6

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# @A300-600 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - TAIL CONE - INSPECT LOWER TAIL PLANE CUT-OUT (ALTERNATE MOD : NONE) 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 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 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 06/94 SERVICE BULLETIN No.: A300-53-6042 REVISION No.: 03 - Aug 30/12 Page: 1 6

Printed in FRANCE ©AIRBUS S.A.S. 2007. All rights reserved.