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 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) : 

AS350 helicopters 

TCDS Number : EASA.R.008 

Foreign AD : Not applicable 

Supersedure : This AD supersedes 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 (formerly 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 actual configuration of the helicopter. 

Reason: EUROCOPTER has developed the modification 073237 which prevents 

wear of the locking stud and thus precludes 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 is 
EASA 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 autorotation test in flight, it was found that 

the collective pitch lever rubbed against the locking strip in the "low pitch" 

position (low position). This rubbing is due to insufficient clearance and could 

result in untimely locking of the collective pitch lever and consequent loss of 

control of the helicopter. 

To preclude the risk of untimely locking, EASA AD 2008-0205-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 clearance 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 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.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 flight is permitted with no passenger on 

board. 

Ref. Publications: EUROCOPTER Emergency Alert 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 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. 

Tel: +33(0)4 42 85 97 97 – Fax: +33(0)4 42 85 99 66, 

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