AD/S-PUMA/60 Amdt 1 Fuselage Inclined 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/S-PUMA/60 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 AS 332 (Super Puma) Series Helicopters

AD/S-PUMA/60 Amdt 1 Fuselage Inclined Gearbox Fairing Gutter 9/2005 TX

Applicability:

All AS 332C, C1, L, L1 and AS 332 L2 equipped with modification MOD 0723356.

Note:  This modification may have been included on helicopters since new, or as a retrofit action, in compliance with Service Bulletin No. 53.01.10 R0 or R1 for all
AS 332 helicopter versions.

Requirement:

1.    Carry out a one-off visual check to ensure that the gutter does not produce interference with the inclined gear box (IGB) fairing and the inclined tail rotor drive shaft.

a.     If interference is found, remove and replace the inclined drive shaft.

2.    Carry out a one-off tactile check, in order to make sure that the gutter is correctly secured to the IGB fairing without any loose attaching rivets.

a.     If there is no interference and any rivets are found to be loose, replace any loose rivets.

These requirements are to be carried out in accordance with Paragraph 2.B. of EUROCOPTER AS 332 Alert Telex (AT) 53.01.47 or later DGAC approved revisions.

Note:  DGAC AD UF-2005-104, (EASA approval No. EASA.R.AD.01 001 dated
24 June 2005) refers.

Compliance:

1.    Unless previously accomplished, before further flight, after the effective date of this AD.

a.     before further flight, after inspection per requirement 1.

2.    Unless previously accomplished, before further flight, after the effective date of this AD.

a.     before further flight, after inspection per requirement 2.

This Amendment becomes effective on 30 June 2005.

Background:

A scheduled maintenance inspection discovered wear on the inclined tail rotor drive shaft caused by interference between the angle section of the IGB fairing and the drive shaft.

The resulting wear of this interference can lead to the failure of the drive shaft and the loss of the tail rotor drive and subsequent loss of control of the helicopter.  This AD addresses the unsafe condition.

The original issue of this AD becomes effective 30 June 2005.

This amendment specifies that a one-off inspection is required.

James Coyne
Delegate of the Civil Aviation Safety Authority

29 June 2005