EASA AD No : 2011-0154

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0154

Date: 22 August 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD unless otherwis e 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, A rticle 14(4) exemption]. 

### Type Approval Holder’s Name :

EUROCOPTER Type/Model designation(s) :
AS 365, EC 155, SA 365 and SA 366 helicopters

TCDS Number: DGAC France No. 159

Foreign AD: Not Applicable
Supersedure: This AD supersedes DGAC France AD F-2 005-127 R1 dated 01 February 2006,

EASA approval number 2006-0019, .



### ATA 67 Rotor Flight Controls – Collective Pitch Lever Rest raining Tab –

Inspection / Adjustment

Manufacturer(s): Eurocopter (formerly Eurocopter Fr ance, Aerospatiale).

Applicability: EC 155 B, EC 155 B1, SA 365 N, SA 36 5 N1, AS 365 N2, AS 365 N3 and SA 366 G1 helicopters, all serial numbers except helicopte rs on which MOD 0767B65 has been embodied in-production or having embodied MOD 0767B65 in-service through accomplishment of Eurocopter AS365 Service Bulletin (SB) No. 67.00.12. or SA 366 SB No. 67.07 or EC 155 SB No. 67-009 Revi sion 1, as applicable to helicopter version.
Reason: The following two occurrences have been rep orted to Eurocopter:



### - An in-flight inopportune collective pitch lever loc king occurred when moving the collective pitch lever to the low-pitch position, and



### - An inopportune collective pitch lever unlocking dur ing engine starting. These inopportune pitch lever locking or unlocking conditions, if not detected and corrected, could result respectively in the loss of control of the helicopter during flight or to an uncontrolled takeoff of the helicop ter on ground. To address this unsafe condition, in 2005, Eurocopt er issued AS 365 Alert Telex No 67.00.10, SA 366 Alert Telex No. 67.05 and EC 15 5 Alert Telex No. 67A007. These Alert Telexes were mandated by DGAC France AD F-2005-127 and required an inspection of the collective pitch leve r for correct locking and unlocking conditions.
Revision 1 of DGAC France AD F-2005-127 covered the conversion of Eurocopter AS 365, SA 366 or EC 155 Alert Telexes i n corresponding AlertEASA AD No : 2011-0154

EASA Form 110 Page 2/3 Service Bulletins (ASB), keeping the same reference numbers (referenced above), and introducing additional information conc erning the instructions to be applied to prevent the risk of collective pitch lev er unlocking. Since issuance of DGAC France AD F-2005-127 R1, EC developed an optional modification, MOD 0767B65, which consists of replac ing the flexible collective lever locking blade by an assembly comprised of a b lade, a hinge and a return spring. The embodiment of this modification address es the inopportune pitch lever locking or unlocking unsafe conditions.
For the reasons described above, this new EASA AD s upersedes DGAC France AD F-2005-127 R1, retaining all its requirements an d excludes from the applicability helicopters which embody MOD 0767B65. MOD 0767B65 may be embodied in-service through accomplishment of Euroc opter AS365 Service Bulletin (SB) No. 67.00.12. or SA 366 SB No. 67.07 or EC 155 SB No. 67-009 Revision 1.
Effective Date: 05 September 2011

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 50 flight hours after 20 July 2005 (the effective date of DGAC France AD F-2007-127 at its original issue), inspec t the collective pitch lever for correct locking and unlocking and in case of discrepancy, accomplish the necessary corrective actions in comp liance with the instructions of Eurocopter ASB AS 365 No 67.00.10 R evision 1, SA 366 No. 67.05 Revision 1 or EC 155 No. 67A007 Revision 1, as applicable to helicopter version.
(2) An inspection, as required by paragraph (1) of this AD, performed before the effective date of this AD in accordance with Eu rocopter ASB AS 365 No 67.00.10, SA 366 No. 67.05 or EC 155 No. 67A007, all at original issue, as applicable to helicopter version, is acce ptable to comply with the requirements of this AD.

Ref. Publications: Eurocopter AS 365 Alert Service Bulletin No. 67.00.10 Revision 1 dated 25 February 2009. Eurocopter SA 366 Alert Service Bulletin No. 67.05 Revision 1 dated 25 February 2009. Eurocopter EC 155 Alert Service Bulletin No. 67A007 Revision 1 dated 25 February 2009. Eurocopter AS 365 Service Bulletin No. 67.00.12 dat ed 25 February 2009. Eurocopter SA 366 Service Bulletin SB No. 67.07 dat ed 25 February 2009. Eurocopter EC 155 Service Bulletin SB No. 67-009 Re vision 1 dated 19 July 2010.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA 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 t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

.EASA AD No : 2011-0154

EASA Form 110 Page 3/3 4. For any question concerning the technical conten t 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 8 5 99 66 E-mail: Directive.technical-support@eurocopter.com

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