EASA AD No.: 2012-0108-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0108-E

Date: 15 June 2012

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 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].

Design Approval Holder’s Name:

EUROCOPTER

Type/Model designation(s):

SA 365, AS 365 helicopters

TCDS Number: France No. 159

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Frame No.9 – Inspection / Repair

Manufacturer(s): Eurocopter (formerly Eurocopter France, Aérospatiale)

Applicability: Applicability: SA 365 N, SA 365 N1, AS 365 N2 and AS 365 N3 helicopters, all 

serial numbers, if a frame No.9 is installed 

- on which doublers or repairs at the level of the latch support and/or stretcher 

support have been installed in service in accordance with Eurocopter Alert

Service Bulletin (ASB) 53.00.42, or ASB 53.00.43, or

- on which doublers or repairs have been installed in production in accordance 

with drawing 365A094158, or drawing 365A094159, or 

- in accordance with Mechanical Repair Manual Work Card 53.10.22.772 or 

Work Card 53.10.22.773.

This AD does not apply to helicopters that have been modified in production in 

accordance with Eurocopter MOD 53C17 or MOD 53D02

Reason: Eurocopter was informed of a crack, which was discovered during the T 

inspection of an AS365 helicopter, starting from a rivet hole of the doubler 

installed in the frame No.9 in accordance with the instructions of Eurocopter 

ASB No. 53.00.42.

Structural alteration of the frame No.9 by modifications or repairs can result in 

fatigue crack initiation under normal operational loads. This condition, if not 

detected and corrected, could lead to crack propagation and failure of the frame 

No.9 which would adversely affect the structural integrity of the helicopter.

For the reasons described above, this AD requires repetitive inspections of the 

frame No.9 in the area of the doublers or the repair performed in the area of the 
EASA AD No.: 2012-0108-E

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 2/2

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

latch support and stretcher support.

Effective Date: 19 June 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 10 Flight Hours (FH) after the effective date of this AD, and 

thereafter, at intervals not to exceed 110 FH, inspect frame No.9 Right 

Hand (RH) side and Left Hand (LH) side in accordance with instructions of 

paragraph 3 of Eurocopter ASB AS365 ASB 05.00.63.

(2)If, during an inspection required by paragraph (1) of this AD, a crack is 

found, before next flight, contact Eurocopter for approved repair instructions

and perform those repairs accordingly.

A ferry flight not exceeding 10 FH is allowed if the cumulated length of 

crack(s) does not exceed 80 mm.

(3) Repair of a helicopter as required by paragraph (2) of this AD does not 

constitute terminating action for the repetitive inspection requirements of 

paragraph (1) of this AD.

Ref. Publications: Eurocopter AS365 ASB 05.00.63 Original issue, dated 06 June 2012

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 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 (STDI) – Aéroport de Marseille Provence, 13725 

Marignane Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33 (4) 

85 99 66; E-mail: Directive.technical-support@eurocopter.com.