EASA AD No.: 20 14

- 0170

TE. CAP.0011 0

- 00 3 © 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

. : 20 14

- 0170

Date: 17 July 2014

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 EU 748/2012, Part 21

. A.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 ope rate 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

F oreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013

- 0031 dated 18 February 2013

.



### 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 maintenance instructions and airworthiness limitations applicable to the Structure and Components of PC

- 12 aeroplanes are specified in the Aircraft Maintenance Manual (AMM) under Chapter 4 , Airworthiness Limitation Section (ALS).

The instructions contained in the ALS document have been identified as mandatory actions for continued airworthiness and f ailure to comply with these instructions and limitations could potentially lead to an unsafe condition

. Pilatus Aircraft Ltd. recently issued Pilatus PC

- 12 AMM report 02049 issue 28 for PC

- 12, PC

- 12/45 and PC

- 12/47 aeroplanes and PC

- 12 AMM report 02300 issue 11 for PC

- 12/47E aeroplanes to incorporate new repetitive inspection intervals of the inboard flap drive arms because of the detection of cracked parts.

For the reason d escribed above, this AD retains the requirements of EASA AD 2013

- 0031, which is superseded, and requires implementation of the new maintenance requirements and/or airworthiness limitations.

Effective Date: 31 July 2014EASA AD No.: 20 14

- 0170

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) From the effective date of this AD, accomplish the following actions, as detailed in Chapter 4 of the AMM report ( the ALS d ocument ) specified in Table 1 of this AD, as applicable to aeroplane model : (1.1) Replace each component before exceeding the applicable life limit,

and (1.2) Within the thresholds and intervals, accomplish all applicable maintenance tasks. The next inspection of the inboard flap drive arms must be accomplished within 150 flight hours or within three months, whichever occurs first after the effective date of this AD

. (2) In case of finding discrepancies (as defined in Chapter 4 of the AMM report specified in Table 1 of this AD, as applicable to aeroplane model ) during accomplishment of any task as required by paragraph (1) of this AD, within the applicable compliance time specified in Chapter 4 of the relevant AMM report, accomplish the app licable maintenance procedures for corrective actions in accordance with the approved maintenance documentation. If no compliance time is identified in Chapter 4 of the relevant AMM report, accomplish the applicable corrective actions before next flight. I f a detected discrepancy is not identified in Chapter 4 of the relevant AMM report, before next flight, contact Pilatus Aircraft Ltd. for approved instructions and accomplish those instructions accordingly.

Table 1

– Applicable A MM Report / ALS Document

Aeroplane Model AMM Report / ALS Document

PC

- 12, PC

- 12/45, PC

- 12/47 Chapter 4 of AMM report 02049, issue 28, dated 31 Ma y 2014

PC

- 12/47E Chapter 4 of AMM report 02300, issue 11, dated 31 Ma y 2014

(3) Compliance with the requirements of paragraphs (1) and (2) of this AD can be demonstrated by: (3.1) Revising as follows the approved Aircraft Maintenance Programme and standard practices on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane:
Incorporate all applicable maintenance instructions and associated airworthiness limitations specified in Chapter 4 of AMM report 02049 issue 28 or AMM report 02300 issue 11, dated 31 May 2014

, and (3.2) Complying with the approved Aircraft Maintenance P rogramme described in paragraph (3.1) of this AD.

Ref. Public ations: Pilatus PC

- 12 Structural, Component and Miscellaneous

– Airworthiness Limitations, Chapter 4 of AMM report 02049 issue 28 dated 31 May 2014, for PC

- 12, PC

- 12/45, PC

- 12/47 aeroplanes.

Pilatus PC

- 12 Structural, Component and Miscellaneous

– Airworthiness Limitations, Chapter 4 of AMM report 02300 issue 11 dated 31 Ma y 2014, for PC

- 12/47E aeroplanes.
The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.EASA AD No.: 20 14

- 0170

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Me thods of Compliance for this AD

. 2. This AD was posted on 23 June 2014 as PAD 14

- 102 for consultation until 07 July 2014. 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

.