| Publication(s) and related information |
ATR SB ATR42-55-0020 original issue dated 02 March 2023, or Revision 01 dated 24 July 2023, or
Revision 02 dated 03 September 2024, or Revision 03 dated 31 January 2025, or Revision 04 dated
06 June 2025.
ATR SB ATR72-55-1013 original issue dated 02 March 2023, or Revision 01 dated 24 July 2023, or
Revision 02 dated 03 September 2024, or Revision 03 dated 31 January 2025, or Revision 04 dated
06 June 2025.
ATR SB ATR42-55-0025 original issue dated 03 February 2025, or Revision 01 dated 06 June 2025.
ATR SB ATR72-55-1018 original issue dated 03 February 2025, or Revision 01 dated 06 June 2025.
The use of later approved revisions of the above-mentioned documents is acceptable for
compliance with the requirements of this AD. |
| Remarks |
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.
All interested persons may send their comments, referencing the AD Number, to the E-mail
address specified in below Remark 3, prior to 10 December 2026. Only if any comment is
received during the consultation period, a Comment Response Document will be published in
the EASA Safety Publications Tool, in a compressed (zipped) file, attached to the record for this
AD.
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.
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