Safety Publications Tool
21-126R1 : Time Limits / Maintenance Checks – Main Gearbox Suspension Bar Pins / Fittings – Re-calculation of Life Limits / Replacement / Modification
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ADs [at] easa.europa [dot] eu
EASA approval number
EASA VTOL Department
/ Type Designation
SA 330 / AS 332 / EC 225
AS 332 L2
EC 225 LP
This AD supersedes EASA AD 2017-0189 dated 22 September 2017.
Publication(s) and related information
AH AS332 Emergency ASB 01.00.86 original issue dated 27 July 2017, or Revision 1 dated 25 August 2017, or Revision 2 dated 02 March 2020, or Revision 3 dated 19 August 2021, or Revision 4 dated 06 January 2022. AH EC225 Emergency ASB 04A013 original issue dated 27 July 2017, or Revision 1 dated 25 August 2017, or Revision 2 dated 02 March 2020, or Revision 3 dated 19 August 2021, or Revision 4 dated 06 January 2022. AH SB AS332-53.02.03 original issue dated 19 August 2021, or AH ASB AS332-53.02.03 Revision 1 dated 06 January 2022. AH SB EC225-53-065 original issue dated 19 August 2021, or AH ASB EC225-53065 Revision 1 dated 06 January 2022. AH AS332 L2 ALS Revision 009 dated 02 June 2021. AH EC 225 LP ALS Revision 013 dated 08 March 2021. 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 31 January 2022. 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_126_R1.pdf (227 kb)
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