Safety Publications Tool
21-169 : Landing Gear – Main and Centre Landing Gear Bogie Pivot Pins – Inspection / Replacement
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EASA approval number
EASA Large Aeroplanes Department
/ Type Designation
This AD supersedes EASA AD 2012-0053R1 dated 27 November 2018.
Publication(s) and related information
Airbus SB A330-32-3240 original issue dated 08 December 2010, or Revision 01 dated 02 May 2011, or Revision 02 dated 02 December 2011, or Revision 03 dated 13 December 2012, or Revision 04 dated 16 April 2014, or Revision 05 dated 03 November 2014, or Revision 06 dated 22 December 2015, or Revision 07 dated 18 April 2016, or Revision 08 dated 04 April 2017, or Revision 09 dated 22 July 2019, or Revision 10 dated 25 March 2021. Airbus SB A340-32-4281 original issue dated 08 December 2010, or Revision 01 dated 02 December 2011, or Revision 02 dated 03 November 2014. Airbus SB A340-32-5096 original issue dated 08 December 2010, or Revision 01 dated 02 December 2011, or Revision 02 dated 03 November 2014. Airbus SB A330-32-3290 original issue dated 26 December 2017. Airbus SB A330-32-3291 original issue dated 28 September 2018. Airbus SB A340-32-4315 original issue dated 26 December 2017. Airbus SB A340-32-4316 original issue dated 28 September 2018. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
1. This Proposed AD will be closed for consultation on 10 December 2021. 2. Enquiries regarding this PAD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 3. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this PAD, and which may occur, or have occurred on a product, part or appliance not affected by this PAD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this PAD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification.
EASA_PAD_21_169.pdf (214 kb)
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