| Publication(s) and related information |
Aerolite AG ASB 17-012 original issue dated 24 August 2017, Revision A dated 15 May 2023, Revision B dated 11 August 2023, or Note 1: The requirements of paragraph (1) of this AD are not applicable for aeroplanes not having an operational approval to conduct CAT II or CAT III approaches.
evision C dated 09 May 2024, or Revision D dated 18 November 2024.
Aerolite AG ASB 17-013 original issue dated 09 January 2018, Revision A dated 15 May 2023 or Revision B dated 11 August 2023, or Revision C dated 18 November 2024.
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 03 January 2025. 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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