EASA AD No.: 2013-0081R1 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2013-0081R1 

Date: 20 June 2013 

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 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): 

SA 330, AS 332 and EC 225 helicopters

TCDS Number: EASA.R.002 

Foreign AD: Not applicable 

Revision: This AD revises EASA AD 2013-0081 dated 26 March 2013. 

ATA 67 Rotor Flight Controls – Tail Rotor Control Turnbuckle – Inspection 

/ Replacement 

Manufacturer(s): Eurocopter 

Applicability: SA 330 J, AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2 and EC 

225 LP helicopters, all serial numbers, equipped with tail rotor control 

turnbuckles Part Number 330A27-5031-20. 

Reason: During flight controls rigging after helicopter maintenance, a failure due to 

corrosion was reportedly found on one of the two turnbuckles installed on the 

yaw flight control cables of the tail rotor. 

The subsequent investigation revealed a lack of Mastinox sealant coating 

between both sides of the turnbuckle internal tappings and the interface 

screws of the end-fitting components of the yaw flight control cables, which is 

likely the cause for development of a galvanic corrosion. This kind of corrosion 

could affect either the inside of the turnbuckle (tapping threads and/or middle 

hole of the part) or its external surface. 

This condition, if not detected and corrected, could lead to failure of a tail rotor 

control turnbuckle, possibly resulting in loss of control of the tail rotor and then 

of the helicopter. 

To address this potential unsafe condition, EASA issued AD 2013-0081 to 

require repetitive inspections of the two tail rotor control turnbuckles and, 

depending on findings, accomplishment of applicable corrective actions, 

possibly including replacement of the parts. 

Since that AD was issued, Eurocopter issued Alert Service Bulletin (ASB) No 

SA330-05.98 Revision 1(R1), ASB No. AS332-05.00.95R1 and ASB No. 

EC225-05A031R1 to provide instructions to detect and correct any corrosion 

on the affected turnbuckles and specify that turnbuckles found externally 
EASA AD No.: 2013-0081R1 

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corroded less than or equal to 0,3 mm must be replaced after an anticorrosion treatment application. 

For the reasons described above, this AD is revised to amend the compliance 

time for turnbuckle replacement (paragraph 4.2) to be counted from the anticorrosion treatment. 

Effective Date: Revision 1: 27 June 2013 

Original issue: 02 April 2013 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the compliance time as defined in Table 1 of this AD, or before 

next flight after the installation of any used turnbuckle on a helicopter, as 

applicable, and thereafter at intervals not to exceed 12 months, inspect 

the two tail rotor control turnbuckles for absence of corrosion and crack 

in accordance with the instructions of paragraph 3 of Eurocopter ASB No 

SA330-05.98, ASB No. AS332-05.00.95 or ASB No. EC225-05A031, as 

applicable to helicopter model. 

Table 1 

Helicopter model and delivery 

date 

Compliance time after 

02 April 2013 

[the effective date of the original 

issue of this AD]

SA 330 helicopters, and 

AS 332 and EC 225 helicopters 

delivered before 01 March 2013 

Within 110 flight hours or 3 

months, whichever occurs first 

AS 332 and EC 225 helicopters 

delivered on or after 01 March 2013 Within 12 months 

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

corrosion or crack is found on the tappings or middle hole of the internal 

surface of any turnbuckle, before next flight, replace the affected 

turnbuckle with a serviceable part in accordance with the instructions of 

paragraph 3.B.2.d of Eurocopter ASB No SA330-05.98, ASB No. AS332-

05.00.95 or ASB No. EC225-05A031, as applicable to helicopter model. 

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

crack or corrosion of more than 0,3 mm depth is found on the external 

surface of any turnbuckle, before next flight, replace the affected 

turnbuckle with a serviceable part in accordance with the instructions of 

paragraph 3.B.2.d of Eurocopter ASB No SA330-05.98, ASB No. AS332-

05.00.95 or ASB No. EC225-05A031, as applicable to helicopter model. 

(4) If, during any inspection as required by paragraph (1) of this AD, 

corrosion equal to 0,3 mm depth or less is identified on the external 

surface of any turnbuckle, accomplish the following actions: 

(4.1) Before next flight, accomplish an anti- corrosion treatment of the 

affected turnbuckle in accordance with the instructions of 

paragraph 3.B.2.c of Eurocopter ASB No SA330-05.98, ASB No. 

AS332-05.00.95 or ASB No. EC225-05A031, as applicable to 

helicopter model; and 

(4.2) Within 6 months after the anti-corrosion treatment application as 

required by paragraph (4.1) of this AD, replace the anti-corrosion 

retreated turnbuckle with a serviceable part in accordance with the 

instructions of paragraph 3.B.2.d of Eurocopter ASB No SA330-

05.98, ASB No. AS332-05.00.95 or ASB No. EC225-05A031, as 

applicable to helicopter model. 
EASA AD No.: 2013-0081R1 

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Ref. Publications: Eurocopter SA330 ASB No. SA330-05.98, Revision 0, dated 14 March 2013 

or Revision 1, dated 05June 2013, 

Eurocopter AS332 ASB No. AS332-05.00.95, Revision 0, dated 14 March 

2013 or Revision 1, dated 05 June 2013, 

Eurocopter EC225 ASB No. EC225-05A031, Revision 0, dated 14 March 2013 

or Revision 1, dated 05 June 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until 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 (STDI) – Aéroport de Marseille Provence 13725 

Marignane Cedex, France; 

telephone +33 (4) 42 85 97 97; facsimile +33 (4) 42 85 99 66; 

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