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2021-0214 : SUPERSEDED BY EASA AD 2022-0103

Number 2021-0214
Issued by Europe  Europe
Issue date 2021-09-17
Effective date 2021-10-01
EASA approval number
ATA Chapter 05
Approval Holder
/ Type Designation
  • PILATUS AIRCRAFT LTD
    • PC-12
      • PC-12
      • PC-12/45
      • PC-12/47
      • PC-12/47E
Revision Not applicable
Correction Not applicable
Supersedure This AD supersedes EASA AD 2021-0005 dated 07 January 2021, including its Correction dated 14 January 2021.
Publication(s) and related information Pilatus PC-12, PC-12/45 and PC-12/47 AMM Chapter 04-00-00 (DMC-12-A-04-00-00-00A-000A-A issue 15), Document Number 02049 Issue 01 Revision 41 dated 05 July 2021. Pilatus PC-12/47E AMM Chapter 04-00-00 (DMC-12-B-04-00-00-00A-000A-A issue 17), Document Number 02300 Issue 01 Revision 25 dated 08 July 2021. Pilatus PC-12/47E AMM Chapter 04-00-00 (DMC-12-C-04-00-00-00A-000A-A issue 2), Document Number 02436 Issue 01 Revision 03 dated 08 July 2021. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
PAD number 21-125
Remarks 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 19 August 2021 as PAD 21-125 for consultation until 16 September 2021. No comments were received during the consultation period. 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.