## EASA EASAAD No. : 2014-0181 

## AIRWORTHINESS DIRECTIVE AD No.: 2014-0181
Date: 31 July 2014 Note: This Proposed Airworthiness Directive (PAD) 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 . In accordance with the EASA Continuing Airworthiness Procedures, the Executive Director is proposing the issuance of an EASA Airworthiness Directive (AD) , applicable to the aeronautical product(s) identified below. All interested persons may send their comments, referencing the PAD Number above. to the e-mail address specified i n the 'Remarks' section , prior to the consultation closing date indicated . 

### Design Approval Holder's Name: Type/Model designation(s): PILATUS AIRCRAFT Ltd. PC-6 aeroplanes TCDS Number: Foreign AD: Supersedure: 

### ATA05 Manufacturer(s): Applicability: Reason:

Effective Date: Switzerland No . F 56-10 Not applicable This AD supersedes EASA AD 2012-0268 dated 19 December 2012 . 

### Time Limits 

### I Maintenance Checks - Airworthiness Limitations Section -Amendment/Implementation
Pilatus Aircraft ltd. and Fairchild Republic Company (formerly Fairchild Industries, Fairchild Heli Porter and Fairchild-H iller Corporation). PC-6 aeroplanes, all models, all manufacturer serial numbers. The maintenance instructions and airworthiness limitations applicable to the Structure and Components of PC-6 aeroplanes are specified in the Aircraft Maintenance Manual (AMM) under Chapter 4 or in the Airworthiness Limitations Document (ALS), depending on aeroplane model. The instructions contained in the ALS document have been identified as mandatory actions for continued airworthiness and failure to comply with these instructions and limitations could potentially lead to an unsafe condition. Pilatus Ai rcraft Ltd. (Pilatus) recently issued PC-6 AMM, Chapter 04-00-00, Document Number 01975 issue 19 for PC-6 82-H2 and PC-6 82-H4 aeroplanes and PC-6 ALS, Document Number 02334 issue 

### 4 for all other PC-6 aeroplane models to incorporate new life limits for the Fire Extinguisher. For the reason described above, th is AD reta ins the requirements of EASA AD 2012-0268, which is superseded , and requires implementation ofthe new maintenance requirements and/or airworthiness limitations. 

### 14 August 

### 2014

TE.CAP.OOll0-004 ©European Aviation Safety Agency. All rights reserved. 1/3 Propri etary document. Copies are not controlled. Confirm revision status through the EASA- Internet/lntranet.Required Action(s) and Compliance Time(s):

Ref. Publications: EASAAD No.: 2014-0181 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, or in the ALS document , as specified in Table 1 ofthis AD, as applicable to aeroplane model: (1.1) Replace each component before exceeding the applicable l ife limit, and (1.2) Within the thresholds and intervals, accomplish all applicable maintenance tasks. Table 1 - Applicable AMM Report 

### I ALS Document Aeroplane Models PC-6 B2-H2 and PC-6 B2-H4 All other PC-6 models AMM Report I ALS Document Chapter 04-00-00 of AMM Document Number 01975, issue 19 dated 31 May 2014 ALS Document Number 02334 , issue 4 dated 31 May 2014 (2) In case of finding discrepancies (as defined in Chapter 4 ofthe AMM report or in the ALS document specified in Table 1 of this AD) during accomplishment of any task as required by paragraph (1) of this AD , within the compliance time specified in Chapter 4 ofthe relevant AMM report or in the ALS document, accomplish the applicable maintenance procedures for corrective actions in accordance with the approved mainten ance documentation . If no compliance time is identified in Chapter 4 of the relevant AMM report or in the A LS document, accomplish the applicable corrective actions before next flight. If a detected discrepancy is not identified in Chapter 4 ofthe relevant AMM report or in the ALS document, before next flight, contact Pilatus for approved instructions and accomplish those instructions accordingly. (3) Compliance with the requirements of paragraphs (1) and (2) ofthis 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 04-00-00 of AMM Document Number 01975 issue 19 or in the ALS Document Number 02334 issue 4 , as applicable to aeroplane model, and (3.2) Complying with the approved Aircraft Maintenance Programme described in paragraph (3.1) ofthis AD. Pilatus PC-6 ALS Document Number 02334, issue 4 dated 31 May 2014. Pilatus PC-6 AMM, Chapter 04-00-00, Document Number 01975, issue 19 dated 31 May 2014 . The use of later approved revisions of these documents is acceptable for compliance with the requirements ofthis AD.
TE.CAP.OOll0-004 ©E uropean Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Confirm revi sion status through the EASA-lnternet/lntranet.EASA AD No. : 2014-0181
Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD . 2. Th is AD was posted on 01 July 2014 as PAD 1 4-108 for consultation until 29 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: PI LATUS AIRCRAFT 

### l TO ., Customer Liaison Manager, CH-6371 STANS, Switzerland. Tel.: +41 (0)41 619 65 80 Fax: +41 (0)41 619 65 76 . E-mail: foderm att@pilatus-aircraft.com.

TE.CAP.OOll0-004 ©European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status th rough the EASA-Internettl ntranet. 3/3