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 participate 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 operate 

an aircraft to which an AD applies, except in accordance with 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]. 

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 supersedes 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 Starflex 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EASA AD 2006-0245 superseded DGAC France AD F-2005-167, only to 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 Emergency 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 absence 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 includes 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 2008
EASA 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) after 01 September 2006 [the effective date 

of EASA AD 2006-0245] and thereafter at intervals not exceeding 

10 FH, visually check that the bonding 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 delamination 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, thereby reaching or exceeding one or 

more of the removal criteria specified 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 accordance 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, corresponding to the helicopter version. 

Ref. Publications: 

Eurocopter AS 365 N Alert Service 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 & Research Section, Certification 

Directorate, EASA; E-mail ADs@easa.europa.eu 

4. For any questions concerning the technical content of the requirements 

in this AD, please contact: 

Eurocopter (STDI) - Aéroport 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