EASA AD No.: 2010-0006 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0006 

Date: 07 January 2010 

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 05 Time Limits / Maintenance Checks – Tail Rotor (TR) Pitch-Change 

Links – Inspection 

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

Applicability: 

Models 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, if equipped with TR pitch-change 

links having Part Number (P/N) 350A33-2100-00, 350A33-2100-01, 350A33-

2100-02, 350A33-2100-03, 350A33-2100-04, 350A33-2121-00, 350A33-2121-

01, 350A33-2121-02, 350A33-2143-00, 350A33-2145-00 or 350A33-2145-01. 

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

helicopters, all serial numbers, if equipped with TR pitch-change links having 

P/N 350A33-2121-00, 350A33-2121-01, 350A33-2121-02, 350A33-2143-00, 

350A33-2145-00 or 350A33-2145-01. 

Reason: 

A case has been reported where the pilot of an AS 350 helicopter felt slight 

vibrations in the pedal unit in flight. A few minutes later, the vibration level 

increased and the pilot carried out a precautionary autorotation landing. 

After landing, it was discovered that one TR pitch-change link was damaged, 

that the tail-boom cone was missing and there was an impact mark on the tailboom. Further investigation of the affected TR pitch-change link has shown 

extensive wear on the ball-joint and failure of the web of the ball-joint due to 

fatigue. The wear of affected TR pitch-change link could have been discovered 

during a regular check for no play in the links, which is scheduled at intervals not 

exceeding 30 flight hours (FH) and to be accomplished during checks after the 

last flight of the day (ALF). 

This condition, if not detected and corrected, could lead to loss of the anti-torque 
EASA AD No.: 2010-0006 

EASA Form 110 Page 2/2 

function, possibly resulting in loss of control of the helicopter. 

For the reasons described above, this AD requires repetitive inspections for no 

play in the TR pitch-change links and corrective actions, depending on findings. 

Effective Date: 21 January 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 30 FH after the effective date of this AD, inspect the TR 

pitch-change links in accordance with paragraph 2.B.1 of Eurocopter AS350 

Alert Service Bulletin (ASB) 05.00.60 or AS355 ASB No. 05.00.56, as 

applicable to helicopter model. 

(2) Thereafter, at interval not to exceed 30 FH, inspect the TR pitch-change 

links in accordance with paragraph 2.B.2 of Eurocopter AS350 ASB No. 

05.00.60 or AS355 ASB No. 05.00.56, as applicable to helicopter model. 

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

play is detected, before next flight, inspect the ball-joints of the TR pitchchange links in accordance with paragraph 2.B.3 of Eurocopter AS350 ASB 

No. 05.00.60 or AS355 ASB No. 05.00.56, as applicable to helicopter 

model, and, depending on findings, accomplish the necessary corrective 

actions. 

(4) The accomplishment of corrective actions as required by paragraph (3) of 

this AD does not constitute terminating action for the repetitive inspections 

as required by paragraph (2) of this AD. 

Ref. Publications: 

Eurocopter AS350 ASB No. 05.00.60 dated 08 December 2009, and 

Eurocopter AS355 ASB No. 05.00.56 dated 08 December 2009. 

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.