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PAD 21-066 : Flight Controls – Trimmable Horizontal Stabilizer Actuator / Electric Load Sensing Device – Modification

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Number 21-066
Issued by Europe  Europe
Issue date 2021-05-04
EASA approval number
Contributor EASA Large Aeroplanes Department
ATA Chapter 27
Approval Holder
/ Type Designation
  • AIRBUS
    • A330
      • A330-201
      • A330-202
      • A330-203
      • A330-223
      • A330-223F
      • A330-243
      • A330-243F
      • A330-301
      • A330-302
      • A330-303
      • A330-321
      • A330-322
      • A330-323
      • A330-341
      • A330-342
      • A330-343
      • A330-941
    • A340
      • A340-211
      • A340-212
      • A340-213
      • A340-311
      • A340-312
      • A340-313
Revision Not applicable
Correction Not applicable
Supersedure None
Publication(s) and related information Airbus SB A330-27-3234 original issue dated 05 March 2019 and Revision 01 dated 12 October 2020. Airbus SB A330-27-3237 original issue dated 12 October 2020. Airbus SB A340-27-4213 original issue dated 12 October 2020. Airbus SB A340-27-4214 original issue dated 12 October 2020. Airbus RDAF 80874366/013/2021#A dated 12 February 2021. Airbus RDAF 80874366/022/2021#A dated 19 April 2021. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
Remarks 1. This Proposed AD will be closed for consultation on 01 June 2021. 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.

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