EASA AD No.: 2010-0064-E 

EASA Form 111 Page 1/3 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0064-E

Date: 01 April 2010

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 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) :

SA 365, AS 365 and SA 366 helicopters

TCDS Number: France No.159 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA Emergency AD 2009-0125-E dated 12 June 2009 and 

the correction dated 15 June 2009. 

ATA 53 Fuselage – Frame No. 9 – Inspection / Repair

Manufacturer(s): Eurocopter (formerly Eurocopter France, Aérospatiale) 

Applicability: 

SA 365 N, SA 365 N1, AS 365 N2 and AS 365 N3 helicopters, all serial 

numbers, and 

SA 366 G1 helicopters, all serial numbers. 

Reason: 

Eurocopter was informed of a crack which was discovered in the No.9 frame of 

an AS 365 N2 helicopter which had logged a total of 10 786 Flight Hours (FH). 

The crack, which was located 230 mm above the cabin floor and which had 

grown over a large section of the No.9 frame on the Right Hand (RH) side, was 

discovered during the Major Inspection of the helicopter. 

This condition, if not corrected, could lead to the failure of the No.9 frame which 

would adversely affect the structural integrity of the helicopter. 

Pending the results of the analyses that were being conducted to establish the 

cause of the crack, EASA Emergency AD 2009-0125-E was published to require 

detailed visual inspections on the RH and Left Hand (LH) side of the No.9 frame 

to detect any crack and, in case a crack was found, to accomplish the 

associated corrective actions. 

The results of the analyses show that the time required for initiation of a crack in 

this area varies a lot according to the weight and balance data of the different 

aircraft versions. 

For the reasons described above, this AD retains the requirements of EASA 

Emergency AD 2009-0125-E, which is superseded, and modifies the action 

compliance times according to helicopter types. 
EASA AD No.: 2010-0064-E 

EASA Form 111 Page 2/3 

Effective Date: 06 April 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Prior to reaching the FH threshold as defined in Table 1 of this AD, as 

applicable, or within 10 FH after the effective date of this AD, whichever 

occurs later, inspect the inner angles and flanges of the No.9 frame on the 

RH and LH sides, in accordance with the instructions of paragraph 2 of 

Eurocopter Alert Service Bulletin (ASB) AS365 ASB 05.00.57 Revision 1, or 

SA366 ASB 05.39 Revision 1, as applicable to helicopter model. 

Table 1 

Helicopter model: Threshold:

AS 365 N3 2 090 FH 

AS 365 N2 3 190 FH 

SA 365 N 8 990 FH 

SA 365 N1, SA 366 G1 9 990 FH 

(2) Thereafter, at intervals not exceeding 110 FH, repeat the inspection in 

accordance with the instructions of paragraph 2 of Eurocopter Alert Service 

Bulletin (ASB) AS365 ASB 05.00.57 Revision 1, or SA366 ASB 05.39 

Revision 1, as applicable to helicopter model. 

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, a 

crack is found, contact Eurocopter for approved repair instructions and 

accomplish those instructions within the compliance time, as applicable to 

crack length detected, as indicated in Table 2 of this AD. 

Table 2 

Detected Crack Location and 

Length 

Required Action(s): 

- Inner Flange, less than 33 mm

or 

- Inner Angle, less than 33 mm 

Reduce the interval of the inspection 

as required by paragraph (2) of this 

AD to not exceed 10 FH; accomplish 

the approved repair within 660 FH or 

12 months, whichever occurs first 

after detection of the crack. 

- Inner Flange, 33 mm or longer

or 

- Inner Angle, 33 mm or longer 

accomplish the approved repair 

before next flight 

Inner Angle and Inner Flange, 

irrespective of length 

accomplish the approved repair 

before next flight 

(4) Repair of a helicopter as required by paragraph (3) of this AD does not 

constitute terminating action for the repetitive inspection requirements of 

paragraph (2) of this AD. 

Ref. Publications: 

Eurocopter AS365 ASB 05.00.57 Revision 1, and 

Eurocopter SA366 ASB 05.39 Revision 1, both dated 31 March 2010. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 
EASA AD No.: 2010-0064-E 

EASA Form 111 Page 3/3 

Remarks :

1. If requested and appropriately substantiated, EASA can approve Alternative 

Methods of Compliance 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 referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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

4. For any question 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 10; fax: +33 (0) 4 42 85 99 66;

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