AD/EC 225/9 Amdt 1 Fuselage Intermediate Gearbox Fairing Gutter (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/EC 225/9 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Eurocopter EC 225 Series Helicopters

AD/EC 225/9 Amdt 1 Fuselage - Intermediate Gearbox Fairing Gutter 2/2009 TX

Applicability:

Model EC 225 LP helicopters, all serial numbers, except those that have been modified during production with MOD 0726599 or in-service with Eurocopter EC225 Service Bulletin 53-007.

Requirement:

Action in accordance with the instructions given in paragraph 2.B of EC225 Alert Service Bulletin No. 53A001 Revision 1.

If discrepancies are found during any check, before further flight, perform corrective actions in accordance with the instructions given in paragraph 2.B of EC225 Alert Service Bulletin No. 53A001 Revision 1.

Note 1:  After modification of a helicopter in accordance with Eurocopter EC225 Service Bulletin 53-007, the repetitive check requirements are no longer required.

Note 2:  EASA Emergency AD 2008-0219-E refers.

Compliance:

Within 15 flight hours after the last check required by the previous issue of this Directive, or after the effective date of this Directive, whichever occurs first; and thereafter at intervals not to exceed 165 flight hours.

This Amendment becomes effective on 15 December 2008.

Background:

This Directive was issued following a report of separation of the gutter, producing interference with the inclined drive shaft.  The wear resulting from this interference can, in time, lead to the failure of the drive shaft and the loss of the tail rotor drive.

Amendment 1 retains the requirements of EASA AD 2007-0090-E and requires more extensive repetitive checks of the IGB fairing gutter and, in the case of discrepancies, replacement of damaged parts.

David Punshon
Delegate of the Civil Aviation Safety Authority

15 December 2008