EASA AD No.: 2011-0189-E 

EASA Form 111 Page 1/3

EASA EMERGENCY AIRWORTHINESS 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 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]. 

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 supersedes 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 equipped 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 separation of the angle section of the IGB 

fairing which is riveted to the IGB fairing (the IGB fairing gutter), resulting in 

interference with the tail rotor (TR) inclined drive shaft. This condition, if not 

corrected, can lead to failure of the drive shaft, causing loss of the TR drive 

and consequent reduced control of the helicopter. 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 issued 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 was issued, a total separation of the gutter with 

interference contact with the TR inclined drive shaft occurred again, revealing 

a more extensive problem concerning the riveting of the gutter. 

Therefore, EASA published Emergency 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, cracks were reportedly found on the gutter 

of some helicopters, some of which had optional gutter reinforcement 
EASA AD No.: 2011-0189-E 

EASA Form 111 Page 2/3

modification installed. Consequently, 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. The AD was then superseded by EASA 

Emergency AD 2011-0129-E, retaining the repetitive inspections for cracks 

and interferences, and subsequently requiring 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 operators, of the gutter removal modification. 

For the reasons described above, this new EASA Emergency AD, retains the 

repetitive inspection requirements of EASA AD 2011-0129-E, which is 

superseded, requires additionally the inspection 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 thereafter 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 Eurocopter 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), within15 flight hours (FH) after the 

effective date of this AD, and thereafter 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 Bulletin (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 Revision 4, dated 27 September 2011 

Eurocopter EC225 ASB 53A001 Revision 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 immediate 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 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.