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EAD 2022-0242-E : Flight Controls – Horizontal Tail Elevator U-Bracket – Inspection

Number 2022-0242-E
Issued by Europe  Europe
Issue date 2022-12-07
Effective date 2022-12-09
EASA approval number
Contributor EASA General Aviation Department
ATA Chapter 27
Approval Holder
/ Type Designation
  • SCHEMPP HIRTH FLUGZEUGBAU
    • Arcus
      • Arcus
      • Arcus M
      • Arcus T
    • Duo Discus Sailplanes
      • Duo Discus
      • Duo Discus C
    • Duo Discus T
    • Nimbus-4 Powered Sailplanes
      • Nimbus-4DM
      • Nimbus-4DT
      • Nimbus-4M
      • Nimbus-4T
    • Nimbus-4 Sailplanes
      • Nimbus-4
      • Nimbus-4D
Revision Not applicable
Correction Not applicable
Supersedure None
Publication(s) and related information Schempp-Hirth TN 396-22 original issue dated 08 September 2022, or Revision 1 dated 13 October 2022. Schempp-Hirth TN 380-3 original issue dated 08 September 2022, or Revision 1 dated 13 October 2022. Schempp-Hirth TN 868-24 original issue dated 08 September 2022, or Revision 1 dated 13 October 2022. Schempp-Hirth TN 890-18 original issue dated 08 September 2022, or Revision 1 dated 13 October 2022. Schempp-Hirth TN A532-10 original issue dated 08 September 2022. 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. The results of the safety assessment have indicated the need for immediate publication and notification, without the full consultation process. 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.