EASA AD No.: 2012-0268

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0268

Date: 19 December 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, 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, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption].


### Design Approval Holder’s Name :

PILATUS AIRCRAFT Ltd. Type/Model designation(s) :

PC-6 aeroplanes

TCDS Number: Switzerland No. F 56-10

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2010-0176 dated 20 August 2010.



### ATA 05 Time Limits / Maintenance Checks – Airworthiness Li mitations

Section – Amendment / Implementation

Manufacturer(s): Pilatus Aircraft Ltd. and Fairchil d Republic Company (formerly known as Fairchild Industries, Fairchild Heli Porter and Fai rchild-Hiller Corporation).

Applicability: PC-6 series aeroplanes, all models, all manufacturer serial numbers.

Reason: The mandatory instructions and airworthines s limitations applicable to the Structure and Components of the PC-6 are specified in the Aircraft Maintenance Manual (AMM) under Chapter 4 or in the Airworthines s Limitations Document (ALS), depending on the aeroplane model.

These documents include the maintenance instruction s and/or airworthiness limitations developed by Pilatus Aircraft Ltd. and approved by EASA. Failure to comply with these instructions and limitations coul d potentially lead to an unsafe condition. To address this potentially unsafe condi tion EASA issued AD 2010- 0176 to require implementation of maintenance instr uctions and/or airworthiness limitations in accordance with Pilatus PC- 6 ALS is sue 1, dated 14 May 2010 and Pilatus PC-6 AMM Chapter 4, issue 12, dated 14 May 2010.
Since that AD was issued, Pilatus Aircraft Ltd publ ished Pilatus PC-6 AMM (Number 01975) Chapter 4, issue 16 and PC- 6 ALS (N umber 02334) issue 3 to introduce a threshold for replacement of previously not listed Flap Actuator.
For the reason described above, this AD retains the requirement of AD 2010- 0176, which is superseded, and requires the impleme ntation of more restrictive maintenance requirements and/or airworthiness limit ation as specified in issue 16 of Chapter 4 of AMM and issue 3 of ALS. This AD also requires replacement of any Flap Actuator which, on the effective date o f this AD, has accumulated or exceeded 7 years since new or since last overhaul.EASA AD No.: 2012-0268

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 02 January 2013

Required Action(s) and Compliance Time(s): Required as indicated unless previously accomplishe d:
(1) After the effective date of this AD, accomplish the following actions, as detailed in Chapter 4 of the AMM report or the ALS Document specified in Table 1 of this AD, as applicable:
(1.1) Replace each component before or upon reachin g the applicable life limit, and
(1.2) Within the thresholds and intervals, accompli sh all applicable maintenance tasks.
(2) In case of finding discrepancies (as defined in Chapter 4 of the AMM report or the ALS document 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 or the ALS document specified in Table 1 of this AD, as applicable, accomplish the applicable maintenance procedures fo r corrective actions in accordance with the approved maintenance documentat ion. If no compliance time is identified in Chapter 4 of the A MM report or the ALS document specified in Table 1 of this AD, as applic able, accomplish the applicable corrective actions before next flight. I f a detected discrepancy is not identified in Chapter 4 of the AMM report or th e ALS document specified in Table 1 of this AD, as applicable, before next f light, contact Pilatus Aircraft Ltd. for approved instructions and accompl ish those instructions accordingly.

Table 1

Aeroplane Model(s) AMM / ALS reference

PC-6 B2-H2 and PC-6 B2-H4 Chapter 04-00-00 of AMM Document Number 01975, issue 16 dated 31 July 2012

All other PC-6 models ALS, Document Number 02334, issue 3 dated 31 July 2012

(3) Compliance with the requirements of § (1) of th is AD can be demonstrated by:
(3.1) Revising as follows, unless accomplished prev iously, the approved Aircraft Maintenance Programme from which the opera tor or the owner ensures the continuing airworthiness of each operated aeroplane:
Incorporate applicable maintenance requirements an d associated airworthiness limitations specified in § (1) of thi s AD,

and
(3.2) Complying with the approved Aircraft Maintena nce Programme described in § (3.1) of this AD.
(4) For aeroplanes which have a Flap Actuator insta lled, except part numbers 978.73.14.101 and 978.73.14.103, which, on the effe ctive date of this AD, has already accumulated or exceeded 3500 flight hou rs or 7 years since new or since last overhaul, within 6 month or 350 f light hours, whichever occurs first after the effective date of this AD, b ut not later than 8,5 years since new or since last overhaul, replace the Flap Actuator with a serviceable part in accordance with approved mainte nance instructions.EASA AD No.: 2012-0268

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Ref. Publications: Pilatus PC-6 ALS, Document Numbe r 02334, issue 3 dated 31 July 2012.
Pilatus PC-6 AMM, Chapter 04-00-00, Document Number 01975, issue 16 dated 31 July 2012.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 09 November 2012 as PAD 12 -141 for consultation until 07 December 2012. The Comment Response Docume nt can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical conten t of the requirements in this AD, please contact: PILATUS AIRCRAFT LTD., Customer Liaison Manager, CH-6371 STANS, Switzerland. Tel.: +41 (0)41 619 65 80 Fax: +41 (0)41 619 65 76 E-mail: fodermatt@pilatus-aircraft.com

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