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 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) : 

EC 225 LP helicopters 

TCDS Number : EASA.R.002 

Foreign AD : Not applicable 

Supersedure : This AD supersedes 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 issued 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 repetitive checks required by this AD.

Effective Date: 06 March 2009 
EASA 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) after 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 torque 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 exceeding 165 FH, readjust the tightening 

torque of the dome fairing support attachment 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 Eurocopter EC225 ASB No. 05A005 at original 

issue are acceptable to comply with the initial requirements of paragraphs 

(1) and (2) of this AD. After the effective date of this AD, repetitive checks 

and corrective actions as required by paragraph (2) of this AD must be 

accomplished in accordance 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 attachment points, before further flight, 

remove and replace the dome fairing support and the associated coning 

stop support assembly in accordance with 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 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 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 97, Fax +33 (0)4 42 85 99 66 

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