EASA AD No.: 2013

- 011 5

- E

TE. CAP.0011 1

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

. : 2013

- 011 5

- E

Date: 28 May 2013

Note: This Emergency 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 E U 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 w ith 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

- 6/B2

- H4 aeroplanes

TCDS Number: Switzerland No. F 56

- 10

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– Rivet ed Structural Part s
– Inspection / Repair

Manufacturer(s): Pilatus Aircraft Ltd.

Applicability: PC

- 6/B2

- H4 aeroplanes, Manufacturer Serial Number s (MSN) 735, 863, 909, 923, 948, 956, 958, 977, 978, 979, 980, 981, 982, 985 and 986.

Reason: Reports have been received that rivets with insufficient shear ( about 50% shear allowable ) were delivered from the supplier to Pilatus . Investigations revealed that the faulty rivets were already installed in various airframes and spare parts during the production process.

This condition, if not corrected, could result in a reduced strength of t he aeroplane structure.

For the reason s described above, this AD prohibits all flight operations for the affected aeroplanes

, except for a ferry flight under limited flight conditions to a repair station. In order to resume flights, this AD requires accomp lishment of an inspection and, depending on findings, a repair of all affected areas of the aeroplane.

Effective Date: 30 May 2013EASA AD No.: 2013

- 011 5

- E

TE. CAP.0011 1

- 00 3 © 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: (1) Before next flight after the effective date of this AD, for aeroplanes ident ified in the applicability paragraph, contact Pilatus for approved inspections instructions, inspect the affected areas and, depending on findings, contact Pilatus for approved repair ins tructions and accomplish those repair instructions accordingly

. (2 ) A single ferry flight is permitted to a repair station where the inspection and repair, as required by paragraph (1) of this AD, can be accomplished, provided that the aeroplane passes a pre

- flight inspection in accordance with the instructions of Section 2.2 of Pilatus PC

- 6 TM

- 06

- 000004. The applicable ferry flight conditions ar e detailed in Section 2.3 of Pilatus PC

- 6 TM

- 06

- 000004. (3) From the effective date of this AD, do not install on any aeroplane any parts having a manufacturing date between September 2010 and May 2013, and identified by P art N umber (P/N) and serial number (s/n) in Table 1 of this AD

, unless the part has been inspected and , depending on findings, repaired in accordance with Pilatus Approved Repair Design Data

. Table 1

– Affected Spare Parts

Part Name P/N s/n

Rudder 113.40.06.018 590, K001, K002 and K003
Tail Cone, Short 620.10.08.504 (not serialized parts)

Ref. Public ations: PILATUS PC

- 6 Technical Memo TM

- 06

- 000004, dated 16 May 2013. 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. The results of the safety assessment have indicated the need for immediate publication and notification, without the full public consultation process

. 3. Enquiries regarding this A D 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 Liaison Manager, CH

- 6371 STANS, Switzerland. Tel.: +41 (0)41 619 65 80 Fax: +41 (0)41 619 65 76 E

- mail: fodermatt@pilatus

- a ircraft.com

.