EASA AD No.: 2012-0099

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0099

Date: 08 June 2012

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].



### Design Approval Holder’s Name :

Pilatus Aircraft Ltd. Type/Model designation(s) :

PC-12 aeroplanes

TCDS Number: EASA.A.089

Foreign AD: Not applicable

Supersedure: None



### ATA 05 Time Limits / Maintenance Checks – Airworthiness Limitation Section – Amendment / Implementation

Manufacturer(s): Pilatus Aircraft Ltd.

Applicability: PC-12, PC-12/45, PC-12/47, and PC-12/47E aeroplanes, all manufacturer serial numbers.

Reason: The mandatory instructions and airworthiness limitations applicable to the Structure and Components of the PC-12 are specified in the Aircraft Maintenance Manual (AMM) under Chapter 4. Prompted by a crack found on one wing of the aeroplane fleet leader, a more restrictive airworthiness limitation was introduced, in that manual, for the inspection of the main spar rib 6 strap fastener.

These documents include the maintenance instructions and/or airworthiness limitations developed by Pilatus Aircraft Ltd. and approved by EASA. Failure to comply with these instructions and limitations could potentially lead to unsafe condition. For the reasons described above, this AD requires the implementation of more restrictive maintenance instructions and/or airworthiness limitations.

Effective Date: 22 June 2012EASA AD No.: 2012-0099

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Required Action(s) and Compliance Time(s): Required as indicated unless previously accomplished: (1) After the effective date of this AD, accomplish the following actions, as detailed in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable: (1.1) Replace each component before or upon reaching the applicable life limit, and (1.2) Within the thresholds and intervals, accomplish all applicable maintenance tasks. (2) In case of finding discrepancies (as defined in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable) during accomplishment of any task as required by paragraph (§) (1) of this AD, within the applicable compliance time specified in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable, accomplish the applicable maintenance procedures for corrective actions in accordance with the approved maintenance documentation. If no compliance time is identified in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable, accomplish the applicable corrective actions before next flight. If a detected discrepancy is not identified in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable, before next flight, contact Pilatus Aircraft Ltd for approved instructions and accomplish those instructions accordingly.

Table 1

Aeroplane Model AMM reference

PC-12, PC-12/45, PC-12/47 Chapter 4 of AMM report 02049, issue 25, dated 25 January 2012

PC-12/47E Chapter 4 of AMM report 02300, issue 8, dated 25 January 2012

(3) Compliance with the requirements of § (1) of this AD can be demonstrated by: (3.1) Revising as follows, unless accomplished previously, the approved Aircraft Maintenance Programme from which the operator or the owner ensures the continuing airworthiness of each operated aeroplane:
Incorporate applicable maintenance requirements and associated airworthiness limitations specified in § (1) of this AD,

and (3.2) Complying with the approved Aircraft Maintenance Programme described in § (3.1) of this AD.

Ref. Publications: 1. Pilatus PC-12 Structural, Component and Miscellaneous – Airworthiness Limitations, Chapter 4 of AMM report 02049 issue 25 dated 5 January 2012, for PC-12, PC-12/45, PC-47. 2. Pilatus PC-12 Structural, Component and Miscellaneous – Airworthiness Limitations, Chapter 4 of AMM report 02300 issue 8 dated 25 January 2012, for PC-12/47E.
The use of later approved revision of these 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.EASA AD No.: 2012-0099

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 2. This AD was posted on 19 April 2012 as PAD 12-031 for consultation until 17 May 2012. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 4. For any question concerning the technical content of the requirements in this AD, please contact: PILATUS AIRCRAFT LTD., Customer Support Manager, CH-6371 STANS, Switzerland. Tel.: +41 (0)41 619 33 33 Fax: +41 (0)41 619 73 11. E-mail: SupportPC12@pilatus-aircraft.com

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