Safety Publications Tool
2020-0132R1 : Stabilizers – Horizontal Stabilizer Attachment Bolts – Inspection / Modification / Clearance Check; Rotorcraft Flight Manual – Amendment
EASA approval number
EASA VTOL Department
/ Type Designation
This AD revises EASA AD 2020-0132 dated 08 June 2020, which superseded EASA AD 2018-0113 dated 23 May 2018.
Publication(s) and related information
Airbus Helicopters EC175 ASB 05A014 original issue dated 07 December 2016, or Revision 1 dated 21 December 2016, or Revision 2 dated 20 July 2017, or Revision 3 dated 29 September 2017, or Revision 4 dated 27 March 2018. Airbus Helicopters EC175 ASB 05A020 original issue dated 27 March 2018, or Revision 1 dated 03 June 2019 and Revision 2 dated 25 July 2019. Airbus Helicopters SB EC175-55-005 original dated 27 September 2017. Airbus Helicopters ASB EC175-55A006 original dated 27 March 2018. Airbus Helicopters RFM TR No. 14A original issue dated 28 September 2017. Airbus Helicopters EC175 B ALS Revision 7 dated 27 January 2017. 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_2020_0132R1.pdf (261 kb)
EASA_AD_2020_0132.zip (1 mb)
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