Airworthiness Directive · Amendment 39-18362 · Landing gear
Airbus Airplanes
This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342, and A330-343 airplanes; all manufacturer serial numbers; except those on which Airbus Modification 58896 has been embodied in production or embodied through Airbus Service Bulletin A330-32-3237.
(2) Model A340-211, A340-212, A340-213, A340-311, A340-312, and A340-313 airplanes; all manufacturer serial numbers; except those on which Airbus Modification 58896 has been embodied in production or embodied through Airbus Service Bulletin A340-32-4279.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by reports that the inner bore of some main landing gear (MLG) unit bogie beams were insufficiently re-protected against corrosion after inspection or maintenance actions were accomplished. This AD requires for certain MLG units, determining which revision of the component maintenance manual (CMM) was used to accomplish the most recent MLG unit overhaul; a detailed inspection for missing or damaged paint, and if necessary, a detailed inspection of the cadmium plating for discrepancies, measurement of the depth of the cadmium plating, a general visual inspection of the base metal for corrosion or damage, a detailed inspection of repaired areas for cracking or corrosion; and corrective actions if necessary. We are issuing this AD to detect and correct corrosion in the bore of each MLG unit bogie beam, which could result in collapse of a MLG unit, and subsequent damage to the airplane and injury to occupants.
Within 12 months after the effective date of this AD: For MLG units having a 201252 series or 201490 series part number, determine the revision of the Messier-Dowty component maintenance manual (CMM) used to do the most recent MLG unit overhaul. If it is determined that the Messier-Dowty CMM revision specified in paragraph (g)(1) or (g)(2) of this AD was used to accomplish the most recent MLG unit overhaul: Within 12 months after the effective date of this AD, clean the area between the bogie pivot pin and the bogie beam bore of each MLG unit and do a detailed inspection for missing or damaged paint, in accordance with Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do not have a date.
(1) For MLG units having a part number in the 201252 series: Messier-Dowty CMM 32-11-74, Revision 25 or earlier.
(2) For MLG units having a part number in the 201490 series: Messier-Dowty CMM 32-12-05, Revision 20 or earlier.
If, during the inspection required by paragraph (g) of this AD, any missing or damaged paint is found: Before further flight, do a detailed inspection of the cadmium plating for discrepancies, measure the depth of the plating as applicable, and do a general visual inspection of the base metal for corrosion or damage, in accordance with Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do not have a date. If any discrepancy, damage, or corrosion is found, before further flight, do all applicable corrective actions, and do a detailed inspection of repaired areas for cracking or corrosion, in accordance with Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 4, which do not have a date, except where Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014, including Appendixes 1, 2, 3, and 4, specifies to contact Messier-Dowty if cracking or corrosion is found in a repaired area, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, report the findings of the inspection required by paragraph (g) of this AD to Airbus, Customer Services Engineering—SEEL1, Attn: Philippe Kerangueven, Product Leader A330/A340, ATA-32, Landing Gear Systems, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; phone +33 (0) 5 67 19 18 42; fax +33 0 5 67 19 12 05; email philippe.kerangueven@airbus.com. The report must include the information specified in Appendix 2 of Airbus Alert Operators Transmission A32L004-14, dated July 28, 2014.
(1) If the inspection was done on or after the effective date of this AD: Within 90 days after that inspection.
(2) If the inspection was done before the effective date of this AD: Within 90 days after the effective date of this AD.
Accomplishment of the boroscope inspection of the internal diameter of the bogie beam for corrosion or damage to the protective treatments, measurement of the depth of the protective treatments as applicable, and accomplishment of all applicable corrective actions, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated November 16, 2007, including Appendixes A, B, C, and D, dated November 16, 2007; or Revision 1, dated September 22, 2008, including Appendixes A, B, C, and D, dated September 22, 2008; are acceptable for the corresponding actions required by paragraphs (g) and (h) of this AD for that MLG unit; however, after accomplishment of the actions in the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34-32-272, dated November 16, 2007, including Appendixes A, B, C, and D, dated November 16, 2007; or Service Bulletin A33/34-32-272, Revision 1, dated September 22, 2008, including Appendixes A, B, C, and D, dated September 22, 2008; the actions specified in the Messier-Dowty service information identified in paragraphs (j)(1) through (j)(5) of this AD must not be accomplished on that same MLG unit. Where Messier-Dowty Service Bulletin A33/34-32-272, dated November 16, 2007, including Appendixes A, B, C, and D, dated November 16, 2007; or Revision 1, dated September 22, 2008, including Appendixes A, B, C, and D, dated September 22, 2008; specify to contact Messier-Dowty for repair information, the repair must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(1) Messier-Dowty Service Bulletin A33/34 32-285, dated July 9, 2010.
(2) Messier-Dowty Service Bulletin A33/34 32-285, Revision 1, dated October 4, 2011.
(3) Messier-Dowty Service Bulletin A33/34 32-285, Revision 2, dated October 4, 2012.
(4) Messier-Dowty Service Bulletin A33/34 32-285, Revision 3, dated September 11, 2013.
(5) Messier-Dowty Service Bulletin A33/34 32-285, Revision 4, dated January 23, 2014.
Note 1 to paragraph (j) of this AD: Inspections done using the instructions in Messier-Dowty Service Bulletin A33/34-32-285, Revision 5, dated August 14, 2014, do not affect the optional method of compliance provided by this paragraph.
As of the effective date of this AD, any overhauled MLG unit having a 201252 series or 201490 series part number may be installed on an airplane, provided the most recent MLG overhaul was done using a Messier-Dowty CMM that is not specified in paragraph (g)(1) or (g)(2) of this AD, or, prior to installation, the MLG unit passes the inspection required by paragraph (g) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
