EASA AD No.: 2011-0189-E

EASA Form 111 Page 1/3 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2011-0189-E

Date: 29 September 2011

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 participat e 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 opera te an aircraft to which an AD applies, except in accordance with t he requirements of that AD, unless otherwise specified by the Ag ency [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) exemptio n]. 

### Type Approval Holder’s Name :

EUROCOPTER Type/Model designation(s) :
AS 332 and EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: This AD super sedes EASA Emergency AD 2011-0129-E dated 08 July 2011.



### ATA 53 Fuselage – Intermediate Gear Box (IGB) Fairing – Inspection / Replacement

Manufacturer(s): EUROCOPTER. (formerly EUROCOPTER France).

Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2 and EC 225 LP helicopters, all serial numbers, if equipp ed with IGB fairing Part Number (P/N) 332A24-0303-05XX or P/N 332A24-0303-06XX or P/N 332A081391.00 or P/N 332A081391.01.

Reason: In 2005, a helicopter experienced separa tion of the angle section of the IGB fairing which is riveted to the IGB fair ing (the IGB fairing gutter), resulting in interference with the tail rotor (TR) in clined drive shaft. This condition, if not corrected, can lead to failure of the dr ive shaft, causing loss of the TR drive and consequent reduced control of the he licopter. To address this situation, DGAC France issued AD F-2005-116 that required a one-time inspection and after another report of gutter separation, EASA iss ued Emergency AD 2007- 0090-E, superseding DGAC France AD F-2005-116R1, to require repetitive inspections of the gutter riveting condition on the IGB fairing.
After EASA AD 2007-0090-E wa s issued, a total separat ion of the gutter with interference contact with the TR incli ned drive shaft occurred again, revealing a more extensive problem concerning the riveting of the gutter. Therefore, EASA published Emergenc y AD 2008-0219-E, superseding EASA AD 2007-0090-E, to require more extensive repetitive inspections of the IGB fairing gutter and to allow, as an optional terminating action, the reinforcement of the gutter riveting on the IGB fairing. After AD 2008-0219-E was issued, crac ks were reportedly found on the gutter of some helicopters, some of wh ich had optional gutter reinforcementEASA AD No.: 2011-0189-E

EASA Form 111 Page 2/3 modification installed. Consequent ly, EASA published Emergency AD 2009- 0275-E, superseding EASA AD 2008-0219-E, to re-establish the repetitive inspections of the IGB fairing gutter for all helicopters, irrespective of modification status, and to reduce the inspection interval. Further gutter cracks occurrences were reported while the inspections of AD 2009-0275-E were effective. T he AD was then superseded by EASA Emergency AD 2011-0129-E, retaining the repetitive inspections for cracks and interferences, and subsequently requi ring removal of the gutter from the IGB fairing mandatory, pending the development of a new IGB fairing by Eurocopter. Since AD 2011-0129-E was issued, Eurocopter received several more reports of finding cracks in the IGB fairing, and also now in the associated attachment supports. These cracks developed on helicopters shortly after the accomplishment, by the affected operator s, of the gutter removal modification. For the reasons described above, this new EASA Emergency AD, retains the repetitive inspection requirement s of EASA AD 2011-0129-E, which is superseded, requires additionally the ins pection of the IGB fairing and of its attachment supports and deletes the requirement to remove the gutter.

Effective Date: 03 October 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For helicopters equipped with an IGB fairing with gutter (P/N 332A24- 0303-05XX or 332A24-0303-06XX), within15 flight hours (FH) after the effective date of this AD, and thereafte r at intervals not to exceed 15 FH, inspect the gutter for cracks and inspect the condition of the IGB fairing and its attachment supports in accordance with the instructions of paragraphs 2.B.1 and 2.B.4 of Euroc opter AS332 Alert Service Bulletin (ASB) 53.01.47 Revision 4 or EC225 ASB 53A001 Revision 4, as applicable to helicopter version. (2) For helicopters equipped with an IGB fairing without gutter (P/N 332A08-1391-00 or 332A08-1391-01), with in15 flight hours (FH) after the effective date of this AD, and thereafte r at intervals not to exceed 15 FH, inspect the condition of the IGB fairing and its attachment supports in accordance with the instructions of paragraphs 2.B.4 of Eurocopter AS332 Alert Service Bulletin (ASB) 53.01.47 Revision 4 or EC225 ASB 53A001 Revision 4, as applicable to helicopter version. (3) If, during any inspection as required by paragraph (1) or (2) of this AD, any discrepancy (as defined in Eurocopter AS332 ASB 53.01.47 Revision 4, or EC225 ASB 53A001 Revision 4) is found, before next flight, accomplish the associated (depending on findings) corrective actions in accordance with the instructions of paragraphs 2.B.3 and 2.B.4 of Eurocopter AS332 Alert Service Bullet in (ASB) 53.01.47 Revision 4 or EC225 ASB 53A001 Revision 4, as applicable and to the helicopter version. (4) After the effective date of this AD, do not install on a helicopter an IGB fairing unless it has a Part Number (P/N) 332A24-0303-0601. (5) Replacement of an IGB fairing as required by paragraph (3) of this AD, does not constitute terminating action for the repetitive inspection requirements of this AD.

Ref. Publications: Eurocopter AS332 ASB 53.01.47 Revi sion 4, dated 27 September 2011 Eurocopter EC225 ASB 53A001 Revisi on 4, dated 27 September 2011. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.EASA AD No.: 2011-0189-E

EASA Form 111 Page 3/3 Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to implement the full consultation process and an immedi ate publication and notification. 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 tec hnical 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

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