EASA AD No.: 2008-0165

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2008-0165

Date: 28 August 2008

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 participat e in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A .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 opera te an aircraft to which an AD applies, except in accordance with th e requirements of that AD, unless otherwise specified by the Ag ency [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) exemptio n].


### Type Approval Holder’s Name :

EUROCOPTER Type/Model designation(s) :

365 series and SA 366 helicopters

TCDS Number : France No. 159

Foreign AD : Not applicable

Supersedure : This AD superse des EASA Emergency AD 2006-0321-E dated 18 October 2006.



### ATA 05, 62, 65 Rotor(s) – Starflex Star Arm Ends – Check / Replacement

Manufacturer(s): Eurocopter (formerly Eurocopter France, Aerospatiale).

Applicability: Model SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 366 G1, SA 365 C, SA 365 C1, SA 365 C2 and SA 365 C3 helicopters, all serial numbers, equipped with main rotor hub (MRH) Starflex stars (all part numbers).

Reason: DGAC France issued AD F-2005-167 (EASA approval 2005-6347) following three cases of deterioration of a Star flex star arm end. In two of these cases, the deterioration caused high amplitude vibrations in flight, compelling the pilot to carry out a precautionary landing. In the event of failure of the Starflex star arm end, high-amplitude vibrations could make it difficult to control the helicopter.
EASA AD 2006-0245 superseded DGAC Fr ance AD F-2005-167, only to cover the conversion of the Eurocopter Alert Telexes into Alert Service Bulletins (ASB) with the same reference number, introducing no additional requirements. Thereafter, EASA Emer gency AD 2006-0321 -E was issued, superseding EASA AD 2006-0245, to cover Revision 1 of the Eurocopter ASB and to introduce a check for absenc e of delamination on the star arm end, on the horizontal centre plane, flush with the bush.

This new AD is issued as a result of the issuance of Revision 3 of the referenced Eurocopter ASB, which incl udes a rewrite of the “Operational Procedure” in paragraph 2.B, making the paragraph references in AD 2006- 0321-E incorrect. The requirements of AD 2006-0321-E are retained and no technical requirements have been added.

Effective Date: 11 September 2008EASA AD No.: 2008-0165

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously:
(1) Within 10 flight hours (FH) afte r 01 September 2006 [the effective date of EASA AD 2006-0245] and thereafte r at intervals not exceeding 10 FH, visually check that the bon ding of the bushes has not failed and that the arm ends are not distorted, in accordance with the instructions specified in Eurocopter AS 365 N ASB 05.00.51, SA 366 ASB 05.35, or SA 365 C ASB 05.28 (single document, ‘the Eurocopter ASB’), corresponding to the helicopter version.
(2) Within 10 FH after 18 October 2006 [the effective date of EASA AD 2006-0321-E] and thereafter at intervals not exceeding 10 FH, on each Starflex star arm and on both sides (leading edge and trailing edge), visually check that there is no delam ination in the composite material, in the area of the horizontal centre plane, flush with the bush, in accordance with the instructions specified in the Eurocopter ASB, corresponding to the helicopter version.
(3) If, during any check as required by this AD, the bonding of a bush has failed and/or if a star arm end is distorted and/or if delamination is detected on the star arm end, ther eby reaching or exceeding one or more of the removal criteria spec ified in the Eurocopter ASB, before next flight, replace the Starflex star with a serviceable unit in accordance with the instructions of the Eurocopter ASB, corresponding to the helicopter version.
(4) Visual checks and replacement actions accomplished prior to the effective date of this AD, in accord ance with the referenced Eurocopter ASB at original issue or Revision 1 or Revision 2, are acceptable to comply with the initial requirements of paragraphs (1) and (2) of this AD. After the effective date of this AD, repetitive visual checks and replacement actions must be accomplished in accordance with the Eurocopter ASB at Revision 3, corr esponding to the helicopter version.

Ref. Publications: Eurocopter AS 365 N Alert Servic e Bulletin 05.00.51, SA 366 ASB 05.35, and SA 365 C ASB 05.28 (single document ), original dated 04 April 2006, Revision 1 dated 12 October 2006, Revision 2 dated 22 November 2007 or Revision 3 dated 18 August 2008.
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 required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication.
3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA; E-mail ADs@easa.europa.eu
4. For any questions concerning the te chnical content of the requirements in this AD, please contact: Eurocopter (STDI) - Aéro port de Marseille Provence, 13725 Marignane Cedex – France Telephone +33 (0) 4 42 85 97 97, Fax +33 (0) 4 42 85 99 66 E-mail: Directive.technical-support@eurocopter.com