| Number |
2021-0005 |
| Issued by |
 Europe |
| Issue date |
2021-01-14 |
| Effective date |
2021-01-21 |
| 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 |
This AD has been republished to correct a typographical error in the Reason section.
|
| Supersedure |
This AD supersedes EASA AD 2016-0083 dated 28 April 2016.
|
| 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 40 dated 30 November 2020.
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 24 dated 30 November 2020.
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 02 dated 30 November 2020.
The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD. |
| PAD number |
20-191 |
| Remarks |
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 02 December 2020 as PAD 20-191 for consultation until 30 December 2020. The Comment Response Documents can be found in the EASA Safety Publications Tool, in the 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.
|
