EASA AD No.: 2014

- 0076

- 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

- 0076

- E

Date: 25 March 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 1

. 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 wi th 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):

AS 350 and AS 355 helicopters

TCDS Number: EASA.R. 008 and EASA.R.146

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– Rear Structure Junction Frame Reinforcement Angles

– Inspection

Manufacturer(s): Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)

Applicability: AS 350 B, BA, BB, B1, B2, B3 and D helicopters, and AS 355 E, F, F1, F2 , N and N P helicopters, all serial numbers

,

- i f incorporating modification ( MOD ) 07 3215

, or

- if equipped with at least one reinforcement angle

, Part Number ( P/N ) 350A08.2493 .21 or P / N 350A08.2493 .23, following the repair carried out in accordance with MRM Work Card 53.10.22.772 or AMM Task 53

- 31

- 00, 8

- 5

.

Reason: During the inspection of several AS 355 helicopters

, cracks were found in the reinforcement angles of the rear structure / tail boom junction frame

. Subsequent investigation revealed that cracks were i nitiated on the non

- visible surface of the angle (surface in contact with the frame)

. Th is condition, if not detected and corrected, could lead to further crack propagation and subsequent loss of the tail boom , resulting in loss of the helicopter

. F or the reason described above, this AD requires repetitive inspections of the affected area and , depending on findings, replacement of affected parts

. Terminating corrective action is currently under investigation by Airbus Helicopters

. This AD is considered as a temporary measure and further AD action may follow.

Effective Date: 27 March 2014EASA AD No.: 2014

- 0076

- 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) W ithin the compliance time as defined in Table 1 of this AD

, and, t hereafter

, at intervals not t o exceed 10 flight hours ( FH )

, inspect the rei nforcement angles in accordance with the instructions of paragraph 3.B.1 of A irbus H elicopters E mergency A lert S ervice B ulletin (ASB) AS350 05.00.70 or ASB AS355 05.00.62 , as applicable to helicopter type

.

Table 1

– Inspection Threshold

FH accumulated (on the effective date of this AD) since installation of MOD 07 3215 , or since installation of a reinforcement angle Compliance Time

Less than 640 FH Before exceeding 650 FH

, but not before accumulating 640 FH

640 FH or more Within 10 FH after the effective date of this AD

( 2 ) W ithin 165 FH after the initial inspection as required by paragraph (1) of this AD, and

, thereafte r , at intervals not to exceed 165 FH, inspect the rei nforcement angles in accordance with the instructions of paragraph 3.B.2 of Airbus Helicopters ASB AS350 05.00.70 or ASB AS355 05.00.62, as applicable to helicopter type

. ( 3 ) Accomplishment of the first inspection as required by paragraph ( 2 ) of this AD constitutes terminating action for the repetitive inspections required by paragraph (1) of this AD

. ( 4 ) If

, during any inspection a s required by paragraph (1) or (2) of this AD, crack s are detected, before next flight

, contact Airbus Helicopters for approved instructions for corrective action ( s ) and accomplish those instructions accordingly.

Ref. Publications: A irbus H elicopters Emergency ASB AS350 05.00.70 dated 24 March 2014

. Airbus Helicopters Emergency ASB AS355 05.00.62 dated 24 March 2014

. The use of later approved revisions of the s e document s 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: Airbus Helicopters

– Aéroport de Marseille Provence, 13725 Marignane Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 85 99 66; E

- mail: Directive.technical

- support@eurocopter.com

.