EASA AD No.: 2014

- 0145

- 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

. : 2014

- 0145

- E

Date: 06 June 2014

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 2 1A.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 wit h 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:

AIRBUS HELICOPTERS Type/Model designation(s):

EC130 helicopters

TCDS Number: EASA.R.008

F oreign AD: N o t applicable

Supersedure: N one



### ATA 53 Fuselage

– Tail Boom / Fenestron Junction Frame

– Inspection

Manufacturer(s): Airbus Helicopters ( f ormer ly Eurocopter, Eurocopter France )

Applicability: EC 130 B4 and EC 130 T2 helicopters, all serial numbers

.

Reason: Two events of crack propagation through the junction frame of the tail boom / Fenestron were reported following non

- scheduled inspections of EC130 B4 helicopters. The investigation revealed that the cracks initiated in the lower right hand ( RH ) part of the frame between the web and the flange where the lower spar of the tail boo m is joined. Although the crack s were of significant length, no deterioration was visible from the outside of the helicopter.

This condition, if not detected and corrected, could lead to structural failure, possibly resulting in Fenestron detachment and consequent los s of control of the helicopter.

To address this unsafe condition, Airbus Helicopters issued Emergency Alert Service Bulletin ( ASB ) No. 05A017 to provide instructions for detailed visual check s on the inside of the tail boom.

For the reasons d escribed above, this AD requires repetitive inspections of the affected area and, depending on findings, accomplishment of applicable corrective actions.

Effective Date: 09 June 2014EASA AD No.: 2014

- 0145

- 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) Within the threshold as specified in Tab le 1 of this AD, as applicable, accomplish a detailed visual inspect ion of the frame web in the radius between the web and the flange on the tail cone side in accordance with the instructions of paragraph 3.B.1 of Airbus Helicopter s EC130 Emergency ASB No. 05A 017

. (2) Within 25 flight hours (FH) after the inspection as required by paragraph (1) of this AD, and, t hereafter, at intervals not to exceed 25 FH, accomplish the inspection

, in accordance with the instructions of paragraph 3.B.2 of Airbus Helicopters EC130 Emergency ASB No. 05A017.

Table 1

– Inspection Threshold

FH accumulated, on the effective date of this AD, since first flight Compliance Time

Less than 690 FH Before exceeding 70 0 FH

.
690 FH or more W ithin 10 FH or 7 days

, whichever occurs first after the effective date of this AD

(3 ) If, during any inspecti on as required by paragraph (1) or (2) o f this AD, a crack is detected

, before next flight, contact Airbus Helicopter s for approved repair instructions and accomplish those instructions accordingly.

(4 ) Repair of a helico pter as required by paragraph (3 ) of this AD does not constitute terminating action for the repetitive inspections as required by this AD.

Ref. Public ations: Airbus Helicopter EC130 Emergen cy ASB 05A017 Rev. 0 dated 06 June 2014

. The u se of later approved revisions of th is 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
proces s

. 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: Airbus Helicopters

, Customer Service s, Technical Support Department

, Telephone +33 (0)4.42.85.97.16, Fax + 33 (0)4.42.85.99.66, E

- mail: airframe.technical

- support@eurocopter.com

.