EASA AD No.: 2013-0081R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0081R1

Date: 20 June 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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 2 6 March 2013.



### ATA 67 Rotor Flight Controls – Tail Rotor Control Turnbuck le – Inspection

/ Replacement

Manufacturer(s): Eurocopter

Applicability: SA 330 J, AS 332 C, AS 332 C1, AS 33 2 L, AS 332 L1, AS 332 L2 and EC 225 LP helicopters, all serial numbers, equipped wi th tail rotor control turnbuckles Part Number 330A27-5031-20.

Reason: During flight controls rigging after helico pter maintenance, a failure due to corrosion was reportedly found on one of the two tu rnbuckles installed on the yaw flight control cables of the tail rotor.
The subsequent investigation revealed a lack of Mas tinox sealant coating between both sides of the turnbuckle internal tappi ngs and the interface screws of the end-fitting components of the yaw fli ght control cables, which is likely the cause for development of a galvanic corr osion. This kind of corrosion could affect either the inside of the turnbuckle (t apping threads and/or middle hole of the part) or its external surface.
This condition, if not detected and corrected, coul d lead to failure of a tail rotor control turnbuckle, possibly resulting in loss of c ontrol of the tail rotor and then of the helicopter. To address this potential unsafe condition, EASA is sued AD 2013-0081 to require repetitive inspections of the two tail rot or 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 S ervice Bulletin (ASB) No SA330-05.98 Revision 1(R1), ASB No. AS332-05.00.95R 1 and ASB No. EC225-05A031R1 to provide instructions to detect an d correct any corrosion on the affected turnbuckles and specify that turnbu ckles found externallyEASA AD No.: 2013-0081R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. corroded less than or equal to 0,3 mm must be repla ced 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 previous ly:
(1) Within the compliance time as defined in Table 1 of this AD, or before next flight after the installation of any used turn buckle on a helicopter, as applicable, and thereafter at intervals not to exce ed 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. EC22 5-05A031, 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 paragr aph (1) of this AD, corrosion or crack is found on the tappings or midd le hole of the internal surface of any turnbuckle, before next flight, repl ace the affected turnbuckle with a serviceable part in accordance wi th 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 paragr aph (1) of this AD, any crack or corrosion of more than 0,3 mm depth is fou nd on the external surface of any turnbuckle, before next flight, repl ace the affected turnbuckle with a serviceable part in accordance wi th 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 paragr aph (1) of this AD, corrosion equal to 0,3 mm depth or less is identifi ed on the external surface of any turnbuckle, accomplish the following actions: (4.1) Before next flight, accomplish an anti- corro sion treatment of the affected turnbuckle in accordance with the instruct ions 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 applicab le to helicopter model; and
(4.2) Within 6 months after the anti-corrosion trea tment application as required by paragraph (4.1) of this AD, replace the anti-corrosion retreated turnbuckle with a serviceable part in acc ordance 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. EC225-05A0 31, as applicable to helicopter model.EASA AD No.: 2013-0081R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Ref. Publications: Eurocopter SA330 ASB No. SA330-0 5.98, 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 docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substant iated, 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 Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical conten t 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

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