CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

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

A330-200/300 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: if 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: PCS-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 Bugatti 

Dowty (Service Bulletin)

Ref. 10: PCS-2141, LHE Cadmium Brush Plating, Messier-Bugatti-Dowty
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Ref. 11: M-DLPS1004-4-1, Machining Requirements for Ultra High Tensile Steels 1760MPa (255 KSI) 

Tensile Strength and Above, Dowty Aerospace Gloucester Limited

Ref 12: M-DLNDT 17 Eddy Current Flaw Detection Method, Messier-Dowty

Ref 13: PCS-2302 Rotary Flap Peening 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), Introduction of a new Bogie 

and Dressings with a new two coat paint 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 protection 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-Service 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 the 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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- Embodiment of VSB A33/34-32-272 (SB 32-4268 or SB 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 MANPOWER

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 pin. 

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 

Appendix 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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- 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 boroscope 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 areas 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 attention 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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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