EASA AD No.: 2011-0164 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0164 

Date: 31 August 2011 

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) : 

AS 350 and AS 355 helicopters 

TCDS Number : EASA.R.008, EASA.R.146 

Foreign AD : Not applicable 

Supersedure : None 

ATA 67 Rotors Flight Control – Tail Rotor Control Stop Screws – 

Inspection 

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

Applicability: AS 350 B, AS 350 BA, AS 350 BB, AS 350 B1, AS 350 B2, AS 350 B3 and 

AS 350 D helicopters, all serial numbers (s/n), if equipped with an Autopilot 

(AP), and AS350 B3 helicopters, all s/n, without an AP installed, but 

embodying modification 073252. 

AS 355 E, AS 355 F, AS 355 F1, AS 355 F2, AS 355 N and AS 355 NP 

helicopters, all s/n, if equipped with an AP, and AS 355 N and AS 355 NP 

helicopters, all s/n, without an AP installed, but embodying modification 

071908. 

Reason: During take-off with a sling load, the pilot of an AS350 B3 helicopter noticed 

that he reached one of the yaw stops before its usual position. The 

subsequent inspection revealed that a nut of the tail rotor control stop was 

loose and that the corresponding tail rotor control stop screw was out of 

adjustment. 

This condition, if not detected and corrected, can lead to the loss of 

adjustment of the affected stop and consequently limit yaw authority, 

possibly resulting in loss of control of the helicopter. 

For the reasons described above, this AD requires repetitive inspections of 

the tail rotor control stop screws and, depending on findings, adjustment. 

This AD is considered an interim action, pending the development of a 

modification, and further AD action may follow.

Effective Date: 14 September 2011 
EASA AD No.: 2011-0164 

EASA Form 110 Page 2/2 

Required Action(s) and 

Compliance Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 110 flight hours (FH) after the effective date of this AD, inspect 

the tail rotor control stop screws in accordance with the instructions of 

paragraph 3.B.2 of Eurocopter Alert Service Bulletin (ASB) No. AS350-

05.00.64, or of ASB No. AS355-05.00.59, as applicable to helicopter 

model. 

(2) If, during the inspection as required by paragraph (1) of this AD, 

discrepancies are detected, before next flight, adjust the stops and, 

irrespective of findings, mark a line of paint on the screw/nut assembly, 

in accordance with the instructions of paragraph 3.B.2 of Eurocopter 

ASB No. AS350-05.00.64, or of ASB No. AS355-05.00.59, as 

applicable to helicopter model. 

(3) Thereafter, at intervals not to exceed 110 FH, inspect the red paint lines 

on the screw and nut for alignment, in accordance with the instructions 

of paragraph 3.B.3 of Eurocopter ASB No. AS350-05.00.64, or of ASB 

No. AS355-05.00.59, as applicable to helicopter model. 

(4) If, during any inspection as required by paragraph (3) of this AD, 

discrepancies are detected, before next flight, remove the red paint 

marks, adjust the stops and mark a new line of paint on the screw/nut 

assembly, in accordance with the instructions of paragraph 3.B.2 of 

Eurocopter ASB No. AS350-05.00.64, or of ASB No. AS355-05.00.59, 

as applicable to helicopter model. 

(5) Corrective action as required by paragraph (4) of this AD does not 

constitute terminating action for the repetitive inspections as required 

by paragraph (3) of this AD. 

Ref. Publications: Eurocopter ASB No. AS350-05.00.64 dated 30 August 2011 

Eurocopter ASB No. AS355-05.00.59 dated 30 August 2011 

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 Safety 

Information Section, Executive 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 - Customer Service Technical Support Department, 

Aéroport de Marseille, Provence 13725 Marignane Cedex – France 

Telephone: + 33 (0)4 42 85 99 51, Fax: + 33 (0)4 42 85 99 66. 

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