# @A300 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: 57 

### TITLE: WING - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT IN THE GEAR RIB 5 AFT BEARING FORWARD LUG MODIFICATION No.: 13348H5689 This page transmits Revision No.03 of Service Bulletin No.A300-57-0249 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 introduce new Repair Instruction R57240425, a new flowchart and new Accomplishment Instructions (including changes to instructions for bush installation and paint/sealing process). The opportunity is taken to produce this Service Bulletin in the latest format. CHANGES Layout changes due to computerization of this revision are not identified. 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
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 1 7

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-USAAA Minor editorial or document structure change N Fig. A-USAAA Sheet 01 Minor editorial or document structure change N PLANNING INFORMATION EFFECTIVITY Minor editorial or document structure change N 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 Minor editorial or document structure change 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 570249B01R00 Minor editorial or document structure change N LIST OF MATERIALS - OPERATOR SUPPLIED Minor editorial or document structure change N Consumable Materials Minor editorial or document structure change N
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 2 7

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Consumable CMLB01 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 Tools Minor editorial or document structure change N Standard tool TOOLB01 Minor editorial or document structure change N Special Tools Minor editorial or document structure change N ACCOMPLISHMENT INSTRUCTIONS TASK 570249- 831-895-001- MODIFICATION Minor editorial or document structure change N Task associated data - 001 Minor editorial or document structure change N Subtask 570249-910-401-001 Minor editorial or document structure change N Subtask 570249-839-401-001 Minor editorial or document structure change N Subtask 570249-831-403-001 Minor editorial or document structure change N Subtask 570249-020-401-001 Minor editorial or document structure change N Subtask 570249-020-402-001 Minor editorial or document structure change N Subtask 570249-832-401-001 Minor editorial or document structure change N Subtask 570249-410-403-001 Minor editorial or document structure change N Subtask 570249-914-401-001 Minor editorial or document structure change N Subtask 570249-410-402-001 Minor editorial or document structure change N Subtask 570249-930-401-001 Minor editorial or document structure change N Subtask 570249-710-401-002 Minor editorial or document structure change N Subtask 570249-942-401-002 Minor editorial or document structure change N Fig. A-UFAAA Minor editorial or document structure change N Fig. A-UFAAA Sheet 01 Minor editorial or document structure change N Fig. A-UBAAA Minor editorial or document structure change N Fig. A-UBAAA Sheet 01 Minor editorial or document structure change N Fig. A-UBAAA Sheet 02 Minor editorial or document structure change N Fig. A-UBAAA Sheet 03 Minor editorial or document structure change N Fig. A-UCAAA Minor editorial or document structure change N Fig. A-UCAAA Sheet 01 Minor editorial or document structure change N Fig. A-UCAAA Sheet 02 Minor editorial or document structure change N Fig. A-UDAAA Minor editorial or document structure change N Fig. A-UDAAA Sheet 01 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.
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 3 7

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# @A300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS REVISION SEQUENCE ORIGINAL: May 22/07 REVISION No. : 03 - Jan 18/12

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 4 7

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# @A300 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: 57 

### TITLE: WING - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT IN THE GEAR RIB 5 AFT BEARING FORWARD LUG **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 13348H5689 NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During routine maintenance, a crack has been found visually in the MLG Rib 5 on two A310 in-service aircraft. The crack was found in the forward lug of the MLG rib 5 aft bearing attachment. The concerned aircraft had accumulated 24,000 Flight Cycles (FC) and 27,000 FC at the time of finding, refer to OIT 999.0115/06. In both cases the cracks extended through the entire thickness of the forward lug. Inspection of the MLG rib 5 forward lug on the opposite wings was performed after removal of the bushes on the concerned aircraft. The inspection revealed medium to heavy corrosion in the forward lug holes. A laboratory examination of the two cracked ribs confirmed that the origin of the cracks was due to pitting corrosion. Although there have been no crack findings on A300 B4 aircraft so far, the differences in MLG Rib 5 design compared to the A310 do not allow the exclusion of the possibility of cracks. This Service Bulletin introduces new bushes with an increased interference fit in the aft bearing forward lugs. The aft lug of the aft bearing attachment is not affected, as the bush is already installed with an increased interference fit since origin. After removal of the old bushes, a dye penetrant flaw detection inspection is carried out on the lug bores and faces before installation of the new bushes to make sure that the lugs are free of corrosion/damage.
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 1 7

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# @A300 SERVICE BULLETIN SUMMARY Accomplishment of this Service Bulletin terminates the mandatory inspection requirements of Inspection Service Bulletin (ISB) A300-57-0251. Aircraft that have applied this Service Bulletin at a previous revision will be required to re-inspect gear rib lugs as per Inspection Service Bulletin (ISB) A300-57-0255. If oversized interference fit bushes have already been installed in a MLG Rib 5 aft bearing forward lug position as per the Repair Instruction R57240425, the intent of this modification can be considered as embodied in those position(s). Accomplishment of this Service Bulletin will significantly reduce the likelihood of corrosion and any subsequent cracks in the forward lug of the MLG Rib 5 aft bearing attachment. Accomplishment of this Service Bulletin at Revision No. 03 will cancel the inspection requirements of Service Bulletins A300-57A0248 and A300-57-0251. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB YES 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 NORMAL JACKING YES 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 570249B01R00 2 9,720.00 Bush Standard tool TOOLB01 1 See SB Tools EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

69X ABR AFG C2A DHL F2I IAW IRA IRM KYE KZU MIX MNB MNG MSR NTR P2A RUN SOP TNO TSY CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.51.34.004 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 2 7

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# @A300 SERVICE BULLETIN SUMMARY
LIFE LIMIT None OTHERS OIT SE 999.0115/06 and OIT SE 999.0062/11 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 570249-831-895-001: MODIFICATION TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 24.50 APPENDICES None

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 3 7

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# @A300 SERVICE BULLETIN SUMMARY

**CONF ALL



### A

FORWARD LUG OF AFT

BEARING FORWARD PINTLE FITTING

GEAR SUPPORT RIB

**FWD** 

## A

A_SB_570249_7_SAAA_01_00 LH SHOWN RH SIMILAR

Figure A-USAAA - Sheet 01
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 4 7

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# @A300 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: 57 

### TITLE: WING - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT IN THE GEAR RIB 5 AFT BEARING FORWARD LUG MODIFICATION No.: 13348H5689 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 B4-103 B4-203 B4-2C C4-203 F4-203 (2) Effectivity by MSN 0041 0045 0047 0053 0055 0075 0083-0085 0095 0100-0101 0105 0107 0116-0117 0123-0126 0129 0134 0139 0141 0147 0149-0152 0154-0155 0157 0173 0175 0180 0183-0184 0189-0190 0196 0199-0200 0203-0204 0208 0210-0212 0216 0218-0220 0227 0234-0236 0239 0247 0249-0250 0255-0256 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 1 7

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# @A300 SERVICE BULLETIN

OPERATOR MSN 69X 0095 ABR 0152 0184 0189 0199 0208 0219 0220 0234 0236 0250 0259 0274 0289 AFG 0180 0190 C2A 0211 0261 DHL 0084 0085 0141 0149 0249 0265 F2I 0083 0235 IAW 0239 IRA 0139 0151 0173 0256 0299 0302 IRM 0055 0175 0204 KYE 0053 0100 0216 KZU 0041 0101 0117 MIX 0125 0134 0157 0196 0203 0218 MNB 0123 0212 0277 0292 0304 MNG 0047 MSR 0200 0255 NTR 0124 0155 P2A 0116 0150 RUN 0075 0105 0107 0147 0154 0183 SOP 0126 TNO 0045 0210 0227 0247 TSY 0129 (4) Configuration by MSN MSN CONFIGURATION 0041 0045 0047 0053 0055 0075 0083 0084 0085 0095 0100 0101 0105 0107 0116 0117 0123 0124 0125 0126 0129 0134 0139 0141 0147 0149 0150 0151 0152 0154 0155 0157 0173 0175 0180 0183 0184 0189 0190 0196 0199 0200 0203 0204 0208 0210 0211 0212 0216 0218 0219 0220 0227 0234 0235 0236 0239 0247 0249 0250 0255 0256 0259 0261 0265 0274 0277 0289 0292 0299 0302 0304 001

(5) Configuration definition **CONF 001 Config. 01 is valid for all aircraft that have not had oversized interference fit bushes installed by Repair Instruction R57240425. If oversized interference fit bushes are found to have been installed by Repair Instruction R57240425 on one wing only, then only 1 Kit 570249B01R00 will be necessary. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 570249B01R00 2 Consumable CMLB01 As required Standard tool TOOLB01 1 DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 2 7

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# @A300 SERVICE BULLETIN
B. CONCURRENT REQUIREMENTS None C. REASON (1) History During routine maintenance, a crack has been found visually in the MLG Rib 5 on two A310 in-service aircraft. The crack was found in the forward lug of the MLG rib 5 aft bearing attachment. The concerned aircraft had accumulated 24,000 Flight Cycles (FC) and 27,000 FC at the time of finding, refer to OIT 999.0115/06. In both cases the cracks extended through the entire thickness of the forward lug. Inspection of the MLG rib 5 forward lug on the opposite wings was performed after removal of the bushes on the concerned aircraft. The inspection revealed medium to heavy corrosion in the forward lug holes. A laboratory examination of the two cracked ribs confirmed that the origin of the cracks was due to pitting corrosion. Although there have been no crack findings on A300 B4 aircraft so far, the differences in MLG Rib 5 design compared to the A310 do not allow the exclusion of the possibility of cracks. (2) Objective/Action This Service Bulletin introduces new bushes with an increased interference fit in the aft bearing forward lugs. The aft lug of the aft bearing attachment is not affected, as the bush is already installed with an increased interference fit since origin. After removal of the old bushes, a dye penetrant flaw detection inspection is carried out on the lug bores and faces before installation of the new bushes to make sure that the lugs are free of corrosion/damage. Accomplishment of this Service Bulletin terminates the mandatory inspection requirements of Inspection Service Bulletin (ISB) A300-57-0251. Aircraft that have applied this Service Bulletin at a previous revision will be required to re-inspect gear rib lugs as per Inspection Service Bulletin (ISB) A300-57-0255. If oversized interference fit bushes have already been installed in a MLG Rib 5 aft bearing forward lug position as per the Repair Instruction R57240425, the intent of this modification can be considered as embodied in those position(s). (3) Advantages Accomplishment of this Service Bulletin will significantly reduce the likelihood of corrosion and any subsequent cracks in the forward lug of the MLG Rib 5 aft bearing attachment. Accomplishment of this Service Bulletin at Revision No. 03 will cancel the inspection requirements of Service Bulletins A300-57A0248 and A300-57-0251. (4) Operational/Maintenance Consequences None DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 3 7

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# @A300 SERVICE BULLETIN
D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 570249-831-895-001: MODIFICATION (1) Remove LH/RH MLG (2) Removal of Bushes (3) Inspection of Lug Faces and Bores (4) Installation of Bushes (5) Permanent Seal of Bush/Lug Interface (6) Install LH/RH MLG (7) Re-identification E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Accomplishment of this Service Bulletin at Revision No. 03 is expected to be rendered 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 mandatory 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 570249-831-895-001: MODIFICATION Get Access 1.00 DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 4 7

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# @A300 SERVICE BULLETIN

Task 570249-831-895-001: MODIFICATION On Aircraft Remove LH/RH MLG 10.00 Removal of Bushes 3.00 Inspection of Lug Faces and Bores 2.00 Installation of Bushes 6.00 Permanent Seal of Bush/Lug Interface 5.00 Install LH/RH MLG 10.00 Re-identification 1.00 Tests 6.00 Close-Up 1.00 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 24.50 NOTE: If the Repair Instruction R57240425, "Removal of Corrosion from the Gear Rib 5 Lugs and the Installation of Oversized Bushes" is necessary, then approximately 56.00 manhours for each wing will need to be added for Modification. H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 07-11-00 32-11-11 Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-40-11 51-60-00 Structural Repair Manual (SRM) 51-10-50 51-40-12 51-40-20 51-40-21 K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 57-51-34 Illustrated Parts Catalog (IPC) 57-51-34 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 5 7

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# @A300 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 6 7

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# @A300 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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 by fax: +49 40 50 76 25 90 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 570249B01R00 Cost 4,860.00 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 the Kit(s) 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. B. INDUSTRY SUPPORT INFORMATION AIRBUS will provide a 50 percent reduction to the applicable sales prices given in paragraph 2A(2) for orders placed before 31 December 2013. C. LIST OF COMPONENTS Kit 570249B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 A5724085320200 1 Bush (1) A5724085320000 2 A5724078620400 1 Bush (2) A5724078620200

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 7 7

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# @A300 SERVICE BULLETIN
D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Honing Fluid 06-010 As required Varnish 07-018 As required (1) Anaerobic Sealant 08-003 As required Fuel Tank Sealant Polysulfide 09-002 As required Low Adhesion Polysulfide Sealant 09-019C As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Epoxy Primer 16-006 As required External Top Coat (polyurethane) 16-018 As required Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required Lint-Free Cotton Cloth 19-003 As required Marker Pen 8404 As required (2) NOTE (1): Mat. No. 07-018 is an alternative to Mat. No. 16-021B when used to protect written part numbers. NOTE (2): The Marker pen 8404 can be procured from: - Edding (UK) Ltd. - Merlin Centre - Acrewood Way - St. Albans - Herts. - England (2) Components None (3) Equipment None
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 8 7

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# @A300 SERVICE BULLETIN
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR Re-identify the gear Rib 5 by marking this SB No. and Revision No. (A300-57-0249 R 03) adjacent to the PN. F. TOOLING (1) Tooling - Price and Availability Gear Rib 5 Toolkit 0044A411058D (2) Tools Gear Rib 5 Toolkit 0044A411058D NOTE: The tool kit contains the following items for the removal of the bushes, Items (1) and (2): - Qty 1 0044A411058D-33 Split Location Ring - Qty 1 0044A411058D-35 Bolt - Qty 1 0044A411058D-43 Enerpac Cylinder - Qty 1 0044A411058D-44 Enerpac Hand Pump - Qty 1 0044A411058D-45 Enerpac Connector Hose - Qty 1 0044A411058D-46 Spherical Washer - Qty 1 0044A411058D-47 Location Block - Qty 4 0044A411058D-48 Bolt (for Item 47) - Qty 1 0044A411058D-49 Thrust Washer - Qty 2 0044A411058D-50 Nut - Qty 1 0044A411058D-51 Reaction Clamp (Aft Bush Item (1)) - Qty 1 0044A411058D-86 Captive Washer - Qty 1 0044A411058D-87 Shoulder Screw (for Item 86) - Qty 1 0044A411058D-90 Reaction Clamp (Fwd Bush Item (2)) The tool kit contains the following items for the installation of the bushes, Items 1 and 2: - Qty 1 0044A411058D-35 Bolt - Qty 1 0044A411058D-38 Installation Block - Qty 1 0044A411058D-43 Enerpac Cylinder DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 9 7

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# @A300 SERVICE BULLETIN - Qty 1 0044A411058D-44 Enerpac Hand Pump - Qty 1 0044A411058D-45 Enerpac Connector Hose - Qty 1 0044A411058D-46 Spherical Washer - Qty 2 0044A411058D-50 Nut - Qty 1 0044A411058D-51 Reaction Clamp (Fwd Bush Item 2) - Qty 1 0044A411058D-86 Captive Washer - Qty 1 0044A411058D-87 Shoulder Screw (for Item 86) - Qty 1 0044A411058D-90 Reaction Clamp (Aft Bush Item 1) The tool kit will also contain an In-Line Honing Tool PN MT58133-195 to line hone the bushes to the finished internal diameter after installation. Also in the tool kit is a shorter In-Line Honing Tool PN MT58133-197 which can be used as an alternative and an Alignment Tool (truing sleeve) PN MT19048 to set up the In-Line Honing Tools. Also included are additional tools required in case a repair is necessary. Heaters (Optional). Standard tool TOOLB01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 0044A411058D MLG Rib 5 Toolkit 1 (3) Special Tools None

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 10 7

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# @A300 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 570249-831-895-001 - MODIFICATION 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 730 740 Manpower TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 24.50 A. GENERAL (1) Subtask 570249-910-401-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-10-50 51-40-12 51-40-20 51-40-21 (a) For application of protective treatments, refer to SRM 51-40-12. (b) For application of sealant, refer to SRM 51-40-20 or SRM 51-40-21. (c) For removal and installation of bushes, refer to SRM 51-10-50.

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 11 7

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# @A300 SERVICE BULLETIN (2) Subtask 570249-839-401-001 - Administrative Manpower Resources Skills NON SPECIFIC (a) Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. B. PREPARATION (1) Subtask 570249-831-403-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001 (a) Lift the aircraft on jacks (Refer to AMM 07-11-00, Page Block 001). (b) Put access platforms in position in Zones 730/740. C. PROCEDURE NOTE: The worksteps that follow are applicable to the LH and RH wings. (1) Subtask 570249-020-401-001 - Remove LH/RH MLG Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 32-11-11, Page Block 401 (a) Remove the LH and RH MLG legs (Refer to AMM 32-11-11, Page Block 401).

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 12 7

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# @A300 SERVICE BULLETIN (2) Subtask 570249-020-402-001 - Removal of Bushes Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME Material necessary to do the job Standard tool TOOLB01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES 0044A411058D MLG Rib 5 Toolkit 1 References Fig. A-UFAAA Process Flowchart Sheet 01 Fig. A-UBAAA Replacement of Gear Support Rib Bushes Sheet 01 Sheet 02 Sheet 03 Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02 and Fig. A-UBAAA Sheet 03

. (a) Use the removal/installation tool from the MLG Rib 5 Toolkit: 0044A411058D MLG Rib 5 Toolkit 1 to remove these items: 1 Bush A5724085320000 Item (1) Discard 1 Bush A5724078620200 Item (2) Discard

(3) Subtask 570249-832-401-001 - Inspection of Lug Faces and Bores Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 13 7

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# @A300 SERVICE BULLETIN
Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required References Non Destructive Test Manual (NTM) 51-40-11 Part 1 51-60-00 (No etch) Fig. A-UBAAA Replacement of Gear Support Rib Bushes Sheet 01 Sheet 02 Sheet 03 Fig. A-UCAAA Line Honing Details Sheet 01 Sheet 02 Fig. A-UFAAA Process Flowchart Sheet 01
Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01 ,Fig. A-UBAAA Sheet 02 ,Fig. A-UBAAA Sheet 03, Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02

. (a) Visually inspect the gear rib forward lug bore to ensure no liner bushes are installed. If there are, report the details to AIRBUS for further instructions. (b) Clean the bores, spotfaces and chamfer of the forward lug with a plastic spatula and Solvent General Purpose 11-026 As required (c) Visually inspect the bore, spotfaces and chamfer of the forward lug to make sure there is no corrosion and/or damage (Refer to NTM 51-40-11 Part 1). (d) Do a dye penetrant flaw detection test of the bore, spotfaces and chamfer of the forward lug to make sure there is no corrosion and/or damage (Refer to NTM 51-60-00). (e) Do a check to make sure that the forward lug thickness is greater than 57.20 to 57.40 mm (2.252 to 2.260 in.). If not, report all details to AIRBUS for further instructions. (f) Do a check to make sure that the diameter of the bore of the lug (dimension Y) is within the tolerance of 5.1900 to 5.1916 in. (131.826 to 131.866 mm) and proceed with standard bushes. If not, report all details to AIRBUS for further instructions. (g) Check the bore for ovality; if ovality is found, report all findings to AIRBUS for further instructions. (h) If no damage and/or corrosion is found and dimension Y is within the tolerance go to SUBTASK 570249-410-403 001 Installation of Bushes .

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 14 7

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# @A300 SERVICE BULLETIN (i) If there is damage and/or corrosion found, or if the lug thickness is below the given tolerance, or dimension Y is more than the given tolerance, report the findings to AIRBUS and wait for advice for repair R57240425 and re-boring tool 044A411058D. (4) Subtask 570249-410-403-001 - Installation of Bushes Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Manhours 6.00 Minimum number of person 2 Subtask elapsed time 3.00 Skills AIRFRAME Material necessary to do the job Kit 570249B01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 A5724085320200 1 Bush 2 A5724078620400 1 Bush Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Honing Fluid 06-010 As required Anaerobic Sealant 08-003 As required Low Adhesion Polysulfide Sealant 09-019C As required Solvent General Purpose 11-026 As required Chemical Conversion Coating Yellow Aluminum 13-002 As required Anti-Corrosion Primer 16-006 As required Lint-Free Cotton Cloth 19-003 As required References Fig. A-UBAAA Replacement of Gear Support Rib Bushes Sheet 01 Sheet 02 Sheet 03 Fig. A-UCAAA Line Honing Details Sheet 01 Sheet 02 Fig. A-UFAAA Process Flowchart Sheet 01

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 15 7

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# @A300 SERVICE BULLETIN
Refer to Fig. A-UFAAA Sheet 01, Fig. A-UBAAA Sheet 01, Fig. A-UBAAA Sheet 02, Fig. A-UBAAA Sheet 03, Fig. A-UCAAA Sheet 01 and Fig. A-UCAAA Sheet 02

. (a) Before installing the bushes check that the dimension Z is likely to be achieved. This can be done by measuring the thickness of the lug and the thickness of the flange on the two bushes and adding them together. Dimension Z should be between 68.96 and 69.27 mm (2.715 and 2.727 in.). If the dimension Z is outside the tolerance, contact AIRBUS. (b) Re-protect surface finishes if there is visible damage to the surface protection or the surface protection has been removed during inspection. 1 Apply: Chemical Conversion Coating Yellow Aluminum 13-002 As required
to the chamfer and the spotfaces of the lug. 2 Wash off excess Chemicals and make sure sufficient drying time is allowed. 3 Apply: Anti-Corrosion Primer 16-006 As required to the chamfer and spotfaces of the lug and the mating surface for the seat of the bush flange. Leave until no longer tacky. (c) Apply: Anaerobic Sealant 08-003 As required

to the lug bore. (d) WARNING: LIQUID NITROGEN IS DANGEROUS. OBEY THE MANUFACTURERS INSTRUCTIONS AND WEAR THE CORRECT PROTECTIVE CLOTHING WHEN YOU USE LIQUID NITROGEN. CAUTION: DO NOT PUT MORE THAN ONE BUSH AT A TIME INTO THE LIQUID NITROGEN, USE CLEAN TONGS TO REMOVE THE BUSH FROM THE LIQUID NITROGEN AND TO INSTALL IT IN THE BORE OF THE LUG. Install: 1 Bush A5724085320200 Item 1 1 Bush A5724078620400 Item 2

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 16 7

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# @A300 SERVICE BULLETIN

1 To make sure that the bush remains cold enough so that the risk of the bush interfering with the bore on installation is minimized, the bush and mandrel (assembled) must be immersed in liquid nitrogen for at least 30 minutes immediately prior to installation. 2 Freeze each bush in sequence in liquid nitrogen for not less than 30 minutes. 3 Use the Installation Block PN 0044A411058D-38, Reaction Clamp PN 0044A411058D-90 (for Item 1) and Reaction Clamp PN 0044A411058D-51 (for item 2) to install each bush in sequence in the applicable end of the bore of the forward lug of the aft gear-rib bearing. Make sure that the bushes are fully installed. 4 Clamp each bush firmly immediately after installation and then allow the assembly to return to ambient temperature, allow the sealant to cure fully to prevent any bush migration. (e) Make sure that the dimension Z is within the tolerance of 68.96 to 69.27 mm (2.715 to 2.727 in.). If outside limits, contact AIRBUS and await instructions. (f) Make sure that the clearance dimension between the bushes, Item 1 and Item 2 is free of sealant. (g) Prior to honing it is recommended that the permanent four stage sealing procedure is applied, refer to SUBTASK 570249-914-401 001 Permanent Seal of Bush/Lug Interface and the full cure time of the surface protection and sealants is allowed, before proceeding further. However, it is acceptable to continue immediately with the repair (honing the bushes) provided a temporary fillet seal is applied as follows: 1 Apply a temporary fillet seal around the bush heads. Use: Low Adhesion Polysulfide Sealant 09-019C As required
and leave until no longertacky. (h) Assemble the in-line honing tool. (i) Use the alignment tool to set up the in-line honing tool. (j) Use the in-line honing tool to finish the internal diameter (dimension X) of the bushes, Item 1 and Item 2, within the tolerance of 124.993 to 125.034 mm (4.9210 to 4.9226 in.) and to a surface finish of 0.8 microns (32 micro inches). Use: Honing Fluid 06-010 As required (k) Thoroughly clean area before removal of the temporary seal from around the bush heads. Use: Lint-Free Cotton Cloth 19-003 As required

made moist with: DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 17 7

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# @A300 SERVICE BULLETIN

Solvent General Purpose 11-026 As required (5) Subtask 570249-914-401-001 - Permanent Seal of Bush/Lug Interface Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Fuel Tank Sealant Polysulfide 09-002 As required Adhesion Promoter For Polysulfide Sealant 09-028 As required Solvent General Purpose 11-026 As required External Top Coat (polyurethane) 16-018 As required Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required Lint-Free Cotton Cloth 19-003 As required References Fig. A-UDAAA Sealing Details Sheet 01
Refer to Fig. A-UDAAA Sheet 01

. NOTE: The procedure below is a four stage procedure to make sure there is a robust sealing of the bush to the lug. Deviation from this procedure can allow the integrity of the seal to be compromized. (a) Use: Lint-Free Cotton Cloth 19-003 As required

made moist with:

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 18 7

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# @A300 SERVICE BULLETIN

Solvent General Purpose 11-026 As required
to clean the area. (b) Apply: Adhesion Promoter For Polysulfide Sealant 09-028 As required

around the flanges of the bushes, Items 1 and 2 and the lug face. (c) Apply a continuous bead of sealant around the edges of the bushes, Item 1 and Item 2 to form a fillet seal, use: Fuel Tank Sealant Polysulfide 09-002 As required

leave until no longertacky. (d) Use: Lint-Free Cotton Cloth 19-003 As required

made moist with: Solvent General Purpose 11-026 As required to remove any unwanted sealant. (e) Apply: External Top Coat (polyurethane) 16-018 As required to the fillet seals to protect the sealant from hydraulic fluid. (f) Apply: Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required
to the fillet seals to protect the sealant from hydraulic fluid. NOTE: To prevent contamination/damage to the sealant it is required that the assembly is left to fully cure. Heaters (optional) may be used to reduce sealant cure time.

DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 19 7

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# @A300 SERVICE BULLETIN (6) Subtask 570249-410-402-001 - Install LH/RH MLG Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 32-11-11, Page Block 401 (a) Install the LH and RH MLG legs (Refer to AMM 32-11-11, Page Block 401). (7) Subtask 570249-930-401-001 - Re-identification Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLB01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Varnish 07-018 As required (1) Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required Marker Pen 8404 As required (2) NOTE (1): Mat. No. 07-018 is an alternative to Mat. No. 16-021B when used to protect written part numbers. NOTE (2): The Marker pen 8404 can be procured from: - Edding (UK) Ltd. - Merlin Centre - Acrewood Way - St. Albans - Herts. DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 20 7

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# @A300 SERVICE BULLETIN - England (a) Re-identify the gear Rib 5 by marking this SB No. and Revision No. (A300-57-0249 R03) adjacent to the PN. Use: Marker Pen 8404 As required Apply: Polyurethane Gloss Finish (Clear Basecoat) 16-021B As required

or Varnish 07-018 As required

to protect the written SB No. from hydraulic fluid. D. TEST (1) Subtask 570249-710-401-002 - Test Manpower Resources Skills AIRFRAME (a) The test procedure necessary for the LH and RH MLG is referenced in Close-up SUBTASK 570249-942-401 002 CLOSE-UP . E. CLOSE-UP (1) Subtask 570249-942-401-002 - CLOSE-UP Work Zones and Access Panels Zone Access/Work location 730 740 Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 07-11-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Remove the access platforms from zones 730/740. (c) Lower the aircraft off jacks (Refer to AMM 07-11-00, Page Block 001).
DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 21 7

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# @A300 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING A_SB_570249_7_FAAA_01_00 BORE AND SPOTFACE

VISUALLY INSPECT CLEAN BORE OF LUG

REMOVE BUSHES

FOUND? CORROSION

OF TOLERANCE? GEOMETRY OUT INSPECTION OF DO A DYE PENETRANT BORE/CHAMFER/SPOTFACE

BORE GEOMETRY CHECK LUG FOUND? CORROSION YES

YES

YES NO

INTERFERENCE FIT BUSHES INSTALL HIGH FOR REPAIR CONTACT AIRBUS

INSTRUCTIONS NO

NO

Figure A-UFAAA - Sheet 01 Process Flowchart DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 22 7

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# @A300 SERVICE BULLETIN

**CONF ALL



### C X

Z Y

THIS SPACE TO BE FREE OF SEALANT

A_SB_570249_7_BAAA_01_00 

### A

LH SHOWN RH SIMILAR

**FWD** 

## A **B**

GEAR SUPPORT RIB

(2) 2 (1) 1



### D **F E**  **G**

**FWD I**  **N B**  **D** 

## B **C**

Figure A-UBAAA - Sheet 01 Replacement of Gear Support Rib Bushes DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 23 7

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# @A300 SERVICE BULLETIN

**CONF ALL

46 86 51 47 49 43 50 35

50 43

49 47 86

46 35 90 87 48 44 45

87 48 44 45

**NOTE:** TOOL KIT IDENTS. 33

33

BUSH (ITEM (2)) REMOVAL
A_SB_570249_7_BAAA_02_00 BUSH (ITEM (1)) REMOVAL (2) (1)

(2) 

## D

**E**

Figure A-UBAAA - Sheet 02 Replacement of Gear Support Rib Bushes DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 24 7

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# @A300 SERVICE BULLETIN

**CONF ALL

46 86 51

35 50 43 86

46
35

38 44 45 87

87 43 44 45

50 90

38

**NOTE:** TOOL KIT IDENTS. BUSH (ITEM 2) INSTALLATION A_SB_570249_7_BAAA_03_00 1 2 1

BUSH (ITEM 1) INSTALLATION 

## F

**G**

Figure A-UBAAA - Sheet 03 Replacement of Gear Support Rib Bushes DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 25 7

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# @A300 SERVICE BULLETIN

**CONF ALL

STONE DRIVE FORK STONE

ALUMINIUM GUIDE ADJUSTER NUT ALIGNMENT HONE BODY

LOCK COLLAR

PULL THE LOCK COLLAR TO REVEAL THE SPLINED SHAFT. INSERT NYLON GUIDE SET INTO BODY AND RESET THE LOCK COLLAR. **NOTE:** TO ASSEMBLE STONES AND GUIDES TO BODY:− PIVOT DRIVE FORK THROUGH 90° AND WITHDRAW CENTER SPINDLE. INSERT STONE AND ALUMINIUM GUIDE SET INTO BODY AND REPLACE CENTER SPINDLE. NYLON GUIDE SET SPLINED SHAFT CENTER SPINDLE

A_SB_570249_7_CAAA_01_00 Figure A-UCAAA - Sheet 01 Line Honing Details DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 26 7

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# @A300 SERVICE BULLETIN

**CONF ALL

**NOTE:** USE OF ALIGNMENT TOOL TO ALIGN FACES OF THE TWO STONES OF THE LINE − HONING TOOL. ALIGNMENT TOOL

LINE − HONING TOOL HAND HELD POWER TOOL

A_SB_570249_7_CAAA_02_00 Figure A-UCAAA - Sheet 02 Line Honing Details DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 27 7

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# @A300 SERVICE BULLETIN

**CONF ALL



### A

A_SB_570249_7_DAAA_01_00 BUSH

STEP 1 SPOTFACE AND CHAMFER− ALODINE MAT NO. 13−002 AND PRIMER MAT NO. 16−006

STEP 2 FILLET SEAL MAT NO. 09−002 − PROMOTER MAT NO. 09−028 USED ON GEAR RIB AND BUSH STEP 3 PAINT MAT NO. 16−018

STEP 4 POLYURETHANE GLOSS FINISH MAT NO. 16−021B



## A LUG

Figure A-UDAAA - Sheet 01 Sealing Details DATE: May 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 28 7

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# @A300 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WING - MAIN LANDING GEAR ATTACHMENT - INTRODUCTION OF BUSHES WITH INCREASED INTERFERENCE FIT IN THE GEAR RIB 5 AFT BEARING FORWARD LUG MODIFICATION No.: 13348H5689 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 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 1 7

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# @A300 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 22/07 SERVICE BULLETIN No.: A300-57-0249 REVISION No.: 03 - Jan 18/12 Page: 1 7

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