Safety Publications Tool
2021-0171 : Tail Rotor – Pitch Control Rod Bearing – Inspection / Replacement
EASA approval number
EASA VTOL Department
/ Type Designation
SA/AS 365 / EC 155
AS 365 N2
AS 365 N3
EC 155 B
EC 155 B1
SA 365 N1
This AD supersedes EASA AD 2017-0125 dated 21 July 2017.
Publication(s) and related information
Eurocopter AS365 SB 65.00.17 Revision 1 dated 23 February 2011. Eurocopter EC155 SB 65-006 Revision 1 dated 23 February 2011. Airbus Helicopters ASB AS365-01.00.67 original issue dated 04 May 2016, or Revision 1 dated 03 June 2016, or Revision 2 dated 28 October 2016, or Revision 3 dated 20 July 2017, or Revision 4 dated 11 December 2019, or Revision 5 dated 25 March 2020, or Revision 6 dated 14 June 2021. Airbus Helicopters ASB EC155-04A014 original issue dated 04 May 2016, or Revision 1 dated 03 June 2016, or Revision 2 dated 28 October 2016, or Revision 3 dated 20 July 2017, or Revision 4 dated 11 December 2019, or Revision 5 dated 25 March 2020, or Revision 6 dated 14 June 2021. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments, postponing the public consultation process until after publication. 3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, 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 AD 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_AD_2021_0171.pdf (225 kb)
For help on using this tool, please refer to
the help section
For any inquiry regarding ADs, please contact
the EASA AD team
To report any bug, broken link or problem with this application, please contact the
Disclaimer & copyright notice
- 2021 ©