**CUSTOMER SERVICES DIRECTO RATE**  **1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE**  **TELEPHONE + 33 (0)5 61 93 33 33** 

# A L E R T O P E R A T O R S T R A N S M I S S I O N - A O T

AOT ref: A32L004 - 14 Page 1 of 5 Date: 28 - JUL - 2014

© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SUBJECT: ATA 32 – MAIN LANDING GEAR (MLG) BOGIE BEAM BORE INSPECTION AIRCRAFT TYPE: A330,A340 OUR REF.: A32L004 - 14 dated 28 - JUL - 2014

. 1. AIRCRAFT AFFECTED A330 - 200/3 00 and A340 - 200/300 fitted with PN 201252 series or PN 201490 series Main Landing Gear that are Pre - Modification 58896 (Ref

. 2 embodied by Ref

. 15 and Ref

. 16) And Whose last overhaul was pre CMM 32 - 11 - 74 Rev.26 (201252 series - issued 1st October 2010) or CMM 32 - 12 - 05 Rev.21 (201490 series - issued 1st October 2010) Note: i f the operator has carried out Bogie bore inspection in accordance with A33/34 - 32 - 272 (Ref

. 9) since or concurrently with the last application of A33/34 - 32 - 285 (Ref

. 14), then the MLG is not affected by this AOT

. If VSB A33/34 - 32 - 285 has been carried out after the application of the VSB A33/34 - 32 - 272 (Ref. 9), then the MLG is affected by this AOT

. 2. REFERENCED DOCUMENTATION 2.1 APPENDIX Appendix 1: Flow chart Appendix 2 : Proforma for reporting Appendix 3 : Area to be cleaned and inspected Appendix 4 : Method of repair 2.2 REFERENCES Ref. 1: AMM 32 - 11 - 14 - 010 - 801A Removal of the MLG Bogie Beam assembly for access, complete with wheels and brakes. Ref. 2: Modification 58896 - Improved 2 part paint scheme for Basic, Growth and Enhanced MLG Bogie Beam. Ref. 3: CMM 32 - 11 - 74, Basic MLG, Bogie Assembly, Messier - Bugatti - Dowty Ref. 4: CMM 32 - 12 - 05, Growth MLG, Bogie Assembly, Messier - Bugatti - Dowty Ref. 5: 20 - 00 - 10, Messier - Bugatti - Dowty Standard Practices Manual Ref. 6: PCS - 2700, Paint Stripping, Messier - Dowty Ref. 7: P CS - 2800, Temporary Corrosion and damage protection of parts, Messier - Bugatti - Dowty Ref. 8: PCS - 2500, Polyurethane Paint

– Two - Coat Process, Messier - Bugatti - Dowty Ref. 9: A33/34 - 32 - 272 Inspection of the Bogie Beam Internal Diameter for Corrosion, Messier B ugatti Dowty (Service Bulletin) Ref. 10: PCS - 2141, LHE Cadmium Brush Plating, Messier - Bugatti - Dowty

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AOT ref: A32L004 - 14 Page 2 of 5 Date: 28 - JUL - 2014

IRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Ref. 11: M - DLPS1004 - 4 - 1, Machining Requirements for Ultra High Tensile Steels 1760MPa (255 KSI) Tensile Strength and Above, Dow ty Aerospace Gloucester Limited Ref 12: M - DLNDT 17 Eddy Current Flaw Detection Method, Messier - Dowty Ref 13: PCS - 2302 Rotary Flap Peenin g of Metal Parts, Messier - Dowty Ref 14: A33/34 - 32 - 285 Inspection of the Bogie Pivot Pin, Messier - Bugatti - Dowty (Service Bulletin). Ref 15: SB A330 - 32 - 3237 , A340 - 32 - 4279, Improved 2 part paint scheme for Basic, Growth and Enhanced MLG Bogie Beam, Airbus, Oct 14/11. Ref 16: A33/34 - 32 - 283 (Enhanced), SB A33/34 - 32 - 284 (Basic, Growth) , I ntroduction of a new Bogie and Dressings with a new two coat pai nt procedure, Messier - Bugatti - Dowty (Service Bulletin). 3. REASON From in - service experience it was found that the inner bore of some bogie beams had been insufficiently re - protected against corrosion after inspection and/or possible maintenance actions performed in this area (absence of corrosion inhibitor and damage to paint protection has been found in some specific areas) The purpose of this AOT is to request operators to accomplish a one - off clean, removal of the temporary corrosion inhibiting prot ection and inspection of the paint. Furthermore if paint is found to be damaged the operator is requested to inspect for corrosion on the MLG Bogie Beam internal bore over an area around the Bogie Pivot pin (Appendix 3). 3.1 FACTS Evidence from In - Servi ce Experience of Bogie Pivot Pin inspections has shown that the Bogie Beam internal bore corrosion protection may be damaged or missing in the area of the bogie pivot pin bore. 3.2 CONSEQUENCES Insufficient corrosion protection can lead to corrosion of t he bogie bore base metal and potentially lead to the rupture of the Bogie Beam if left undetected. 3.3 AIM This AOT requests operators to inspect and restore any damaged paint in the area shown in Appendix 3, with a two part paint scheme in accordance with Appendix 4, and to restore the temporary corrosion inhibiting compound in accordance with Ref

. 7 if no corrosion is found. If corrosion is found, this shall be repaired in accordance with Appendix 4 and the corrosion protection restored in accordance with Appendix 4 & Ref

. 7. 4. SHORT TERM ACTION 4.1 PLANNING AND MANPOWER 4.1.1 ACCOMPLISHMENT TIMESCALE

- The accomplishment of the Cleaning, inspection and restoration of the corrosion protection called for in Para 4.2 must be performed no later than 12 months after the issuance of this AOT.

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AOT ref: A32L004 - 14 Page 3 of 5 Date: 28 - JUL - 2014

IRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT - Embodiment of VSB A33/34 - 32 - 272 (SB 32 - 4268 or S B 32 - 3225) within the 12 months , which follows the issuance of this AOT , constitutes an acceptable method to comply with the requirements of this AOT. 4.1.2 MANPO WER It is estimated that it will take approximately 4 man - hours to do this instruction for each Main Landing Gear leg. Note 1: It is assumed that the equipment has been placed in a maintenance status and man - hour estimates do not include preparation, close - out or administrative functions. Note 2: AV100D takes a minimum of 8 hours to cure, refer to PCS - 2800 (Ref

. 7). It is important to comply with the protective treatment curing time. AV100D should be fully cured before reassembly of the Bogie Pivot pi n. 4.2 DESCRIPTION 4.2.1 ACCESS Note: This inspection check can be done with the Bogie, Dressings, Wheels and Brakes attached to the Bogie Beam Assembly and the Bogie Beam assembly aligned with the Sliding tube. The procedure for the preparation of the inspection is found in Ref

. 1. Remove the bogie pivot pin in accordance with Ref

. 1 procedures. Note: This AOT can be accomplished without disconnecting the middle part of the Brake Rods or moving the Bogie Beam away from the aircraft. 4.2.2 INSPECTION REQUIREMENTS WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR:  THE FLIGHT CONTROLS  THE FLIGHT CONTROL SURFACES

- 4.2.2.1 Detailed Clean: Use a clean dry lint free cloth to remove any build - up of grease and to clean the area around the interface between the Bogie Pivot pin and the Bogie Beam bore (Appendix 3) ensuring that the area of inspection extends beyond the Bogie Bore change in internal profile (minimum 200mm from the Bogie Pivot Centre - Line). Carefully remove the temporary corrosion inhibiting compound in the area as defined in Ap pendix 3 in accordance with Ref. 7 by swabbing using a clean, dry lint free cloth and White Spirit only. NOTE: Application of White Spirit is to be onto the cloth prior to cleaning and must not be poured directly into the Bogie Beam bore.

- 4.2.2.2 Detailed Inspection:

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AOT ref: A32L004 - 14 Page 4 of 5 Date: 28 - JUL - 2014

IRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT - Carry out detailed visual inspection of the paint over the area defined in Appendix 3

o NOTE: The detailed visual inspection can be made using a light source and mirror or a b or o scope to ensure full coverage of the area defined in Appendix 3

.

- If the paint is found to be missing or damaged locally remove in accordance with Appendix 4 paragraph 1.(1) and:

o Carry out detailed visual surface inspection of the Cadmium plate / base metal over the affected area in accordance with Appendix 4 paragraph 1. ( 2 ) and repair any corrosion or damage in accordance with Appendix 4 paragraph 1.( 3 )

. o Record condition of any corroded area s in Appendix 2.

- Restore paint in accordance with Appendix 4 paragraph 1.(2) or 1. (3) as appropriate and restore temporary corrosion inhibiting compound in accordance with Appendix 4 paragraph 1. ( 3 )(j) and Ref

. 7 .

- If paint is not found to be missing or damaged then restore temporary corrosion inhibiting compound in accordance with Appendix 4 paragraph 1. ( 3 )(j) and Ref

. 7 . 4.2.3 FINDINGS Proforma (Appendix 2) to be returned to Airbus within 90 days of completion of inspection. 4.3 SPARES AND TOOLING See Appendix 4 5. FURTHER INFORMATION It is anticipated that this AOT will be rendered mandatory by issuance of an EASA Airworthiness Directive (AD). 6. AOT APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.031. 7. REPORTING Questions about this AOT and inspection results with or without findings are to be sent to Airbus Customer Services engineering as soon as possible, after the AOT application, to the att ention of: Philippe Kerangueven Product Leader A330/340 ATA 32 - Landing Gear Systems Customer Services

– SEEL1 AIRBUS Phone : +33 (0) 5 67 19 18 42 Fax : +33 (0) 5 67 19 12 05 Email: philippe.kerangueven@airbus.com

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AOT ref: A32L004 - 14 Page 5 of 5 Date: 28 - JUL - 2014

IRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Best Regards,

Jean - Luc MOUYSSET VICE PRESIDENT ENGINEERING SUPPORT CUSTOMER SERVICES Philippe GOURDON VICE PRESIDENT A330/A340 PROGRAMME CUSTOMER SERVICES