EASA AD No.: 2013-0095-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2013-0095-E

Date: 16 April 2013

Note: This Emergency 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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

EUROCOPTER

Type/Model designation(s):

AS 350 and AS 355 helicopters

TCDS Number: EASA.R.008

Foreign AD: Not Applicable

Supersedure: None

ATA 67

Rotor Flight Controls – Main/Tail Rotor Servo-Control Bearings –

Inspection / Replacement

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

helicopters, all serial numbers, equipped with single hydraulic main and tail 

servo-controls manufactured by “SAMM”, “TRW”, “GOODRICH”, or “UTAS”.

Reason: Excessive axial play was detected on bearings Part Number (P/N) 801462 

installed on the input lever of the main and tail rotor servo-controls. The 

defective bearings could also have been fitted on servo-controls repaired at the 

"UTC AEROSPACE SYSTEMS" premises in the "Monroe, N/C, USA" repair 

station. This defect could initiate an excessive lever/distributor off-centring of 

the slide valve, causing the distributor slide valve to jam in its sleeve.

For helicopters with single hydraulic main and tail servo-controls, this condition, 

if not detected and corrected, could lead to a hard-point (friction point) in the 

flight controls and increase pilot work load, which would make it necessary to 

cut-off of the hydraulic power and to follow the procedures specified in the 

applicable Section 3 of the Rotorcraft Flight Manual (RFM).

For the reasons described above, this AD requires identification of the affected 

servo-control units and, when an affected servo-control is found installed,

repetitive pre-flight checks and replacement of the affected main and/or tail 

servo-controls.

Effective Date: 18 April 2013
EASA AD No.: 2013-0095-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 10 flight hours (FH) or 7 days, whichever occurs first after the 

effective date of this AD, verify if any affected bearing is fitted in the single 

hydraulic main and/or tail servo-controls in accordance with the instructions 

of paragraph 1.E.2 of Eurocopter AS350 Emergency Alert Service Bulletin 

(ASB) No. 67.00.60, or AS355 ASB No. 67.00.41, as applicable to 

helicopter type.

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

that any servo-control installed on the in-service rotorcraft is equipped with 

a non-compliant bearing, before next flight, and, thereafter, during each 

pre-flight check (RFM, Section 4), check each affected servo-control for

free-travel.

(3) If, during any pre-flight check of the free-travel of the servo-controls as 

required by paragraph (2) of this AD, a “friction point” is detected, before 

next flight, replace the servo-control with a serviceable one in accordance 

with the instructions of Section 3 of Eurocopter AS350 ASB No. 67.00.60, 

or AS355 ASB No. 67.00.41, as applicable to helicopter type.

(4) Unless already accomplished as required by paragraph (3) of this AD, 

within 50 FH or 120 days, whichever occurs first after the effective date of 

this AD, replace each affected servo-control with a serviceable one in 

accordance with the instructions of Section 3 of Eurocopter AS350 ASB 

No. 67.00.60, or AS355 ASB No. 67.00.41, as applicable to helicopter 

type.

(5) From the effective date of this AD, do not install on any helicopter any 

servo-control, unless it has passed the inspection in accordance with the 

instructions of paragraph 1E.1.a or 1.E.1.b of Eurocopter AS350 ASB No. 

67.00.60, or AS355 ASB No. 67.00.41, as applicable to helicopter type.

Ref. Publications: Eurocopter AS350 ASB No. 67.00.60 dated 15 April 2013.

Eurocopter AS355 ASB No. 67.00.41 dated 15 April 2013.

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 results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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.