EASA AD No.: 2009-0023

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0023

Date: 20 February 2009

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 opera te an aircraft to which an AD applies, except in accordance with t he 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) :

EC 225 LP helicopters

TCDS Number : EASA.R.002

Foreign AD : Not applicable

Supersedure : This AD super sedes EASA Emergency AD 2006-0169-E dated 14 June 2006.



### ATA 62 Main Rotor System – Main Rotor Hub Dome Fairing Support Attachments to Dome Fairing – Check / Readjustment / Modification

Manufacturer(s): EUROCOPTER

Applicability: EC 225 LP helicopters, all serial numbers, except those that have been modified during production with MOD 0743718 or in-service with Eurocopter EC225 Service Bulletin (SB) No. 62-007.

Reason: EASA Emergency AD 2006-0169-E was issu ed following the discovery of two cracks in the dome fairing attachment on the dome fairing support. These fatigue cracks were due to the loss of the tightening torque of the screws which secure this assembly. This condition, if not corrected, could lead to the loss of the dome fairing in flight, possibly causing damage to the helicopter and injury to people on the ground. Since then, EUROCOPTER developed modification 0743718 (and associated EC225 SB No. 62-007) which consists of the installation of redesigned parts in this main rotor hub area and allows installation of improved definition of the dome fairing support. Installation of this dome fairing support requires that a brand new coning stop support assembly is also installed as appropriate interface. For the reason described above, this AD retains the requirements of the EASA Emergency AD 2006-0169-E, which is superseded, and adds the requirement, in case of crack findings, to install the new main rotor hub dome fairing support and associated coning stop support. Relevant replacement of parts in accordance with the instructions of Eurocopter EC225 SB No. 62-007 constitutes terminating action for the re petitive checks requi red by this AD.

Effective Date: 06 March 2009EASA AD No.: 2009-0023

EASA Form 110 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 15 flight hours (FH) afte r 14 June 2006 [the effective date of EASA EAD 2006-0169-E], check that there is no crack in the dome fairing support and readjust the tightening torq ue of the screws which secure the dome fairing support to the dome fairing, in accordance with the instructions of paragraph 2.B.2 of Eurocopter EC225 Alert Service Bulletin (ASB) No. 05A005 Revision 1. (2) Thereafter, at intervals not exce eding 165 FH, readjust the tightening torque of the dome fairing support atta chment screws on the dome fairing, in accordance with the instructions of paragraph 2.B.3 of Eurocopter EC225 ASB No. 05A005 Revision 1. (3) Checks and corrective actions accomplished prior to the effective date of this AD in accordance with Euroc opter EC225 ASB No. 05A005 at original issue are acceptable to comply with t he initial requirements of paragraphs (1) and (2) of this AD. After the effect ive date of this AD, repetitive checks and corrective actions as required by paragraph (2) of this AD must be accomplished in accord ance with Eurocopter EC225 ASB No. 05A005 at Revision 1. (4) If, during any check as required by this AD, a crack is found in the dome fairing support at the dome fairing atta chment points, before further flight, remove and replace the dome fairing support and the associated coning stop support assembly in accordance wi th the instructions of Eurocopter EC225 SB No. 62-007. (5) Replacement of parts in accordance with the instructions of Eurocopter EC225 SB No. 62-007 constitutes terminating action for the repetitive checks required by paragraph (2) of this AD.

Ref. Publications: EUROCOPTER EC 225 Alert Service Bulletin No. 05A005 Revision 1

EUROCOPTER EC 225 Service Bulletin No. 62-007 The use of later approved revisions of these documents 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 a llowance 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 question concerning the tec hnical 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

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