EASA AD No.: 2009-0019

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009–0019

Date: 03 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 participat e 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 a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) :
AS350 helicopters

TCDS Number : EASA.R.008

Foreign AD : Not applicable

Supersedure : This AD super sedes and cancels EASA AD 2008-0205-E dated 02 December 2008



### ATA 67 Rotors Flight Control - Collective Pitch Lever Locking Stud – Inspection / Repair

Manufacturer(s): EUROCOPTER (formerl y EUROCOPTER FRANCE, AEROSPATIALE).

Applicability: All AS350 B, BA, BB, B1, B2, B3, D helicopters,

• Delivered before embodiment of modification 073175; or

• Helicopters on which the locking studs or the collective pitch levers or the locking strips have been reworked or modified in service; or

• Helicopters having accomplished Revision 0 or Revision 1 of EUROCOPTER SB No. 67.00.37, corresponding to modification 073237;
or

• Helicopters with a serial number equal to: 3972, 3973, 3982, 3987, 4003, 4023, 4046, 4050, 4086, 4120, 4122, 4132, 4143, 4152, 4172, 4194, 4259, 4314, 4324, 4378, 4392, 4447, 4452, 4477, 4489, 4490, 4501, 4523, 4546, 4560, 4589, 4594, 4599, 4632, 4659, 4666, 4671. NOTE Refer to the Aircraft Individual Inspection Record (RIC), the Log Cards (FM) or the aircraft logbook to identify the ac tual configuration of the helicopter.
Reason: EUROCOPTER has developed the modification 073237 which prevents wear of the locking stud and thus prec ludes the risk of untimely unlocking of the collective pitch lever during the engine starting phase. This modification has introduced a new locking stud which is longer than the previous one. As a result, the clearance between the locking stud and the locking strip isEASA AD No.: 2009-0019

EASA Form 110 Page 2/3 reduced and in some cases it proves to be insufficient when the collective pitch lever is positioned on the "low pitch" stop. In fact, on a helicopter during an autorotat ion test in flight, it was found that the collective pitch lever rubbed against t he locking strip in the "low pitch" position (low position). This rubbing is due to insufficient clearance and could result in untimely locking of the collect ive pitch lever and consequent loss of control of the helicopter. To preclude the risk of untimely locking, EASA AD 2008-0 205-E required an inspection to verify the presence of the required minimum clearance between the end of the locking stud and the locking strip and provided a repair solution in case the clearance is insufficient. This was extended as a precautionary measure also to helicopters with locking system configuration prior to modification 073237. This AD, superseding EASA AD 2008-0205- E taking over its requirements, mandates also to repeat the clearanc e measurements under the conditions and at the intervals defined in paragraph 3. of the Required Action and Compliance Time section of this AD.
Effective Date: 17 February 2009

Required Action(s) and Compliance Time(s): Required as indicated, in accordance with the instructions of EUROCOPTER Emergency Alert Service Bulletin No. 05.00.58: 1. Helicopters having embodied modification 073237:

1.1. After the last flight of the day following the effective date of this AD measure the clearance between the end of the locking stud and the locking strip in accordance with paragraph 2.B.2.a. 1.2. If the clearance is equal to or more than 3 mm return the helicopter to flight configuration. 1.3. If the clearance is less than 3 mm and the helicopter has not embodied modification 073175, accomplish the instructions of paragraph 2.B.2.b. 1.4. If the clearance is less than 3 mm and the helicopter has already embodied modification 073175, accomplish the instructions of paragraph 2.B.2.c. 2. Helicopters not having embodied modification 073237:

2.1 After the last flight of the day fo llowing the effective date of this AD measure the clearance between the end of the locking stud and the locking strip in accordance with paragraph 2.B.3.a. 2.2 If the clearance is equal to or more than 3 mm return the helicopter to flight configuration. 2.3 If the clearance is less than 3 mm and the helicopter has not embodied modification 073175, accomplish the instructions of paragraph 2.B.3.b. 2.4 If the clearance is less than 3 mm and the helicopter has already embodied modification 073175, suspend flights, contact EUROCOPTER for instructions and follow their corrective actions.
3. The clearance measurement defined in paragraph 1. or 2. of this AD, depending on the helicopter configuration, has to be repeated:

• each time the collective pitch lever, the locking stud or the locking pitch are replaced;

• each time the locking strip setting is readjusted;

• at intervals not exceeding 660 flight hours or 2 years, whichever occurs first.EASA AD No.: 2009-0019

EASA Form 110 Page 3/3 4. If a flight is necessary to ferry the helicopter to a repair station or a place where the maintenance can be performed in order to comply with paragraphs 1.or 2. of this AD, the f light is permitted with no passenger on board.
Ref. Publications: EUROCOPTER Emergency Al ert Service Bulletin No. 05.00.58 Rev. 0 dated 01 December 2008. The use of later approved revisions of this document 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 contac t: EUROCOPTER (STDI) – Aéroport de Marseille Provence 13725 Marignane Cedex – France. Tel: +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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