EASA AD No.: 2014-0159

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.: 2014-0159

Date: 07 July 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].



### Design Approval Holder’s Name:

AIRBUS HELICOPTERS Type/Model designation(s):

SA 365, AS 365 and SA 366 helicopters

TCDS Number: EASA.R.105

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA Emergency AD 2 010-0064-E dated 06 April 2010.



### ATA 53 Fuselage – 9° Frame – Inspection

Manufacturer(s): Airbus Helicopters (formerly Euroc opter, Eurocopter France, Aerospatiale).

Applicability: SA 365 N, SA 365 N1, AS 365 N2 and A S 365 N3 helicopters, all serial numbers, and SA 366 G1 helicopters, all serial numb ers.

Reason: Airbus Helicopters was informed that, durin g a Major Inspection of an AS 365 N2 helicopter, a crack was detected on the 9 ° frame. The affected helicopter had accumulated 10 786 flight hours (FH) at the time of the inspection. The crack was located 230 mm above the cabin floor and had grown over a large section of the 9° frame on the R ight Hand (RH) side.

This condition, if not detected and corrected, coul d lead to a structural failure of the 9° frame and reduced structural integrity of th e helicopter.

To address this potential unsafe condition, and pen ding the results of analysis, EASA issued Emergency AD 2009-0125-E to require rep etitive detailed visual inspections on the RH and Left Hand (LH) side of th e 9° frame to detect any crack and, depending on findings, accomplishment of applicable corrective action(s).

After EASA AD 2009-0125-E was issued, the results o f analyses demonstrated that the flight time leading to crack initiation in the affected area varied significantly depending on the weight and balance d ata of the affected helicopter models.

Consequently, EASA issued EASA Emergency AD 2010-00 64-E, retaining the requirements of EASA AD 2009-0125-E, which was supe rseded, but modifying compliance times, depending on helicopter model.EASA AD No.: 2014-0159

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. Since EASA Emergency AD 2010-0064-E was issued, fur ther analysis led to an amendment of the inspection thresholds defined in E mergency AD 2010-0064-E and enlargement of the area to be in spected up to the junction with the upper part of the 9° frame. Consequently, Airbus Helicopters issued AS365 Alert Service Bulletin (ASB) No. 05.00.57 Rev ision 2, and SA366 ASB No. 05.39 Revision 2 to provide the revised inspect ion instructions.

For the reasons described above, this AD retains th e requirements of EASA AD 2010-0064-E, which is superseded, modifies the comp liance times depending on helicopter model, and requires the inspections t o be accomplished in
accordance with modified instructions.

Effective Date: 21 July 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

(1) For helicopters which, on the effective date of this AD, accumulated less flight hours (FH) and flight cycles (FC), than the threshold as defined in Table 1 of this AD, as applicable to helicopter mod el:

Within 110 FH after exceeding the threshold as defi ned in Table 1 of this AD, whichever occurs first, and as applicable, and thereafter at interval not to exceed 110 FH, inspect the 9° frame on the RH an d LH sides, in accordance with the instructions of paragraph 2 of Airbus Helicopters ASB AS365 05.00.57 Revision 2, or SA366 05.39 Revision 2, as applicable to helicopter model.

Table 1 – Threshold to Determine Initial Inspection

Model Service Life Accumulated Since First Flight (FH or FC, whichever occurs first)

SA 365 N 22 980 FC or 11 490 FH

SA 365 N1 20 980 FC or 10 490 FH

AS 365 N2 18 280 FC or 9 140 FH

AS 365 N3 17 480 FC or 8 740 FH

SA 366 G1 16 780 FC or 8 390 FH

(2) For helicopters which, on the effective date of this AD, accumulated FH or FC equal to or more than the threshold as defined i n Table 1 of this AD, as applicable to helicopter model:

Before exceeding 110 flying FH after the last inspe ction of 9° frame on the RH and LH sides accomplished in accordance with par agraph 2.B.2 of Airbus Helicopters ASB AS365 05.00.57 Revision 1, o r SA366 05.39 Revision 1, as applicable to helicopter model, or w ithin 110 FH after the effective date of this AD, whichever occurs first, and thereafter at interval no to exceed 110 FH, inspect the 9° frame on the RH and LH sides in accordance with the instructions of paragraph 2 of Airbus Helicopters ASB AS365 05.00.57 Revision 2, or SA366 05.39 Revision 2, as applicable to helicopter model.

(3) If, during any inspection as required by paragr aph (1) or (2) of this AD, as applicable, any crack is detected having a length l ess than 33 mm, contact Airbus Helicopters for approved repair instructions and accomplish actions specified in paragraphs (3.1) and (3.2) of this AD:

(3.1) Within 10 FH after detection of the crack and , thereafter, at intervals not to exceed 10 FH, inspect the area of the 9° frame in accordance with the instructions of paragraph 2 of Airbus Helicopters ASB AS365 05.00.57 Revision 2, or SA366 05.39EASA AD No.: 2014-0159

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. Revision 2, as applicable to helicopter model.

(3.2) Within 660 FH or 12 months, whichever occurs first after detection of the crack, accomplish the repair in accordance w ith Airbus Helicopter repair instructions. Accomplishment of t he repair constitutes terminating action for repetitive inspe ction at reduced interval as required by paragraph (3.1) of this AD.

(4) If, during any inspection as required by paragr aph (1) or (2) of this AD, as applicable, any crack is detected having a length e qual to, or more than, 33 mm, before next flight, contact Airbus Helicopte rs for approved repair instructions and accomplish those instructions acco rdingly.

(5) If, during any inspection accomplished within t he reduced interval, as required by paragraph (3.1) of this AD, any new cra ck is identified, before next flight, contact Airbus Helicopters for approve d instructions and accomplish those instructions accordingly.

(6) Accomplishment of a repair on a helicopter, as required by paragraph (3.2) or paragraph (4) of this AD, or instructions as req uired by paragraph (5) of this AD, does not constitute terminating action for the repetitive inspections as required by paragraph (1) or (2) of this AD for that helicopter.

Ref. Publications: Airbus Helicopters AS365 ASB 05. 00.57 Revision 1 dated 31 March 2010 and Revision 2 dated 07 April 2014,

Airbus Helicopters SA366 ASB 05.39 Revision 1 dated 31 March 2010 and Revision 2 dated 07 April 2014.

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 substantiated, EA SA 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: Airbus Helicopters (STDI) – Aéroport de Marseille Provence 13725 Marignane Cede x, France; Telephone +33 (4) 42 85 97 97;fax +33 (4) 42 85 99 66;

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



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