EASA AD No.: 20 15

- 0 111

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 15

- 0 111

Date: 1 6 June 2015

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 EU 1321/2014 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 [EU 1321/2014 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: None



### ATA 27 Flight Controls

– Aileron Control System / Universal Joints

– Replacement

Manufacturer(s): Pilatus Aircraft Ltd.

Applicability: PC

- 12, PC

- 12/45 and PC

- 12/47E aeroplanes, manufacturer serial numbers (MSN) 244, MSN 307, MSN 409, MSN 646, MSN 1447 through MSN 1450, MSN 1461, MSN 1462, MSN 1466 through MSN 1514, MSN 1516 through

MSN 1520 and MSN 1523.

Reason: A case of malfunction ing was reported of a universal joint installed between the control tube assembly and the control column on a PC

- 12 /47E aeroplane

. Investigation determined that the malfunction was caused by an incorrectly manufactured universal joint. Universal joints from the same manufacturing batch were provided to operators between 01 March 2014 and 28 February 2015, and are thus potentially affected.

This condition, if not corrected, could lead to other cases of malfunction ing of

a universal join t, possibly resulting in reduced control of the aeroplane.

To address this potential unsafe condition, Pilatus Aircraft Ltd. issued Service Bulletin ( SB ) No. 27

- 022 to provide instructions for replacement of the universal joints in the flight controls.

For the reason described above, this AD requires removal from service of the potentially incorrectly manufactured universal joints.

Effective Date: 3 0 June 2015EASA AD No.: 20 15

- 0 111

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 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:

Note 1: For the purpose of this AD, the affected parts are universal joint s Part Number (P/N) 944.61.73.012 and P/N 527.10.12.195

, purchased between 01 March 2014 and 28 February 2015. The affected parts may also have been installed in service through an inspe ction kit P/N 500.50.12.314 for the aileron control system, purchased between 01 March 2014 and 28 February 2015.

(1) Within the compliance time defined in Table 1 of this AD, as applicable,

r eplace each affected universa l joint P/N 944.61.73.012 or

P/N 527.10.12.195 with a new universal joint P/N 527.10.12.195 ( purchased after 01 March 2015 and marked with a placard “RT iO” ) in

accordance with the instructions of Pilatus Aircraft Ltd. SB No. 27

- 022

.

Table 1

– Replacement of Universal Joints

Flight cycles (FC) accumulated on

the effective date of this AD ( since first flight of the aeroplane or since installation of the affected universal joint or inspection kit , as applicable) Compliance time (after the effective date of this AD)

Less than 200 FC Within 10 FC or 3 months, whichever

occurs first

200 FC or more Within 12 months

(2) Do not install on any aeroplane a universal joint P/N 944.61.73.012 or P/N 527.10.12.195 195 (except one marked with a placard “RT iO” ) or an inspection kit P/N 500.50.12.314 purchased between 01 March 2014 and 28 February 2015, as specified in paragraph (2.1) or (2.2) of this AD, as applicable.

(2.1) For an aeroplane that has an affected part installed:

After modificatio n of the aeroplane as required by paragraph (1)

of this AD.

(2.2) For an aeroplane that does not have an affected part installed:

From the effective date of this AD.

Ref. Public ations : Pilatus Aircraft Ltd

. SB No. 27

- 02 2 original issue, dated 17 March 2015.

The use of later approved revisions of this document 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.

2. This AD was posted on 29 April 2015 as PAD 15

- 053 for consultation until

27 May 2015

. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification 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

.