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EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

EAD No.: 2006-0321-E

Date: 18 October 2006 

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.

Type Approval Holder’s Name : 

EUROCOPTER 

Type/Model designation(s) : 

SA 365 N, AS 365 N, SA 366 and SA 365C 

Helicopters 

TCDS Number: France DGAC 159 

Foreign AD: Not applicable. 

Supersedes: EASA AD No. 2006-0245 

ATA 05, 62, 

65 for SA 365 C Rotor(s) – Starflex Star Arm Ends – Check/Replacement 

Manufacturer(s): EUROCOPTER (formerly EUROCOPTER FRANCE – AEROSPATIALE).

Applicability: All 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: This Airworthiness Directive (AD) is issued 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. 

This AD covers Revision 1 of the EUROCOPTER Alert Service Bulletins (ASB) 

referenced below, corresponding to the helicopter version. 

This AD supersedes EASA AD No. 2006-0245 and introduces a check for absence 

of delamination on the star arm end, on the horizontal center plane, flush with the 

bush.

Effective Date: 18 October 2006

Compliance: The following measures are mandatory as from September 01, 2006, the effective 

date of EASA AD No. 2006-0245: 

1. No later than within 10 flying hours, then at intervals not exceeding 10 flying 

hours, visually check that the bonding of the bushes has not failed and that the 

arm ends are not distorted, in compliance with paragraph 2.B.1.a. of the 

referenced EUROCOPTER ASB, corresponding to the helicopter version.

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The following measures are rendered mandatory from the effective date of this AD:

2. No later than within 10 flying hours, then at intervals not exceeding 10 flying 

hours, 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 center plane, flush with the bush, in compliance with 

the instructions specified in paragraph 2.B.1.b. of the referenced 

EUROCOPTER ASB, corresponding to the helicopter version. 

3. Interpretation of the results: 

 If the bonding of a bush has failed and/or if a star arm end is distorted and/or if 

there is delamination on the star arm end, remove and replace the Starflex star 

before resuming flights. 

Ref. Publications: EUROCOPTER AS 365 N ASB No. 05.00.51 Revision 1, SA 366 ASB No. 05.35 

Revision 1 or SA 365 C ASB No. 05.28 Revision 1, as applicable, or any 

subsequent approved revisions. 

Remarks: 1. If requested and appropriately substantiated the responsible EASA manager for 

the related product has the authority to accept Alternative Methods of 

Compliance (AMOCs) for this AD. 

2. The safety assessment has requested not to implement the full consultation 

process and an immediate publication and notification. 

3. Enquiries regarding this AD should be addressed to the AD Focal Point, 

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. 

Tel.: +33 (0) 4 42 85 97 97 - Fax: +33 (0) 4 42 85 99 66. 

E-mail: Directive.technical-support@eurocopter.com

 

SUPERSEDED