Document ID: chunk:federal_register_of_legislation:F2008L02959:body:0
Version: federal_register_of_legislation:F2008L02959
Segment Type: other
Provision Reference: 
Character Range: 0–2323

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/DO 328/35 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.

Dornier 328 Series Aeroplanes
AD/DO 328/35 Amdt 1  Rudder Spring Tab Lever Assembly  9/2008

Applicability:  Model 328-100 aircraft, all serial numbers, with part number 001A272A4020-002 rudder spring tab lever assembly installed.
Requirement:    Action in accordance with the requirements of EASA AD 2008-0107.

                Note:  AvCraft Aerospace GmbH ASB-328-27-036 dated 12 February 2003 and
                ASB-328-27-036 Revision 1 dated 7 May 2004, and 328 Support Services GmbH ASB-328-27-036 Revision 2 dated 24 January 2008, or later EASA approved revisions, refer; and, AvCraft Aerospace GmbH SB-328-27-459 dated 3 May 2004 and 328 Support Services GmbH SB-328-27-459 Revision 1 dated 24 January 2008, or later EASA approved revisions, refer.
Compliance:     As specified in the Requirement document, with Compliance (1) effective date to be read as the date specified in the original issue of this Directive (19 January 2006).
                This Amendment becomes effective on 28 August 2008.
Background:     The manufacturer has determined that the possibility of failure exists in the rudder flight control system due to cracks in the spring tab lever assembly bearing lugs.

                Amendment 1 is issued in response to a new EASA AD, which expands applicability, reduces the inspection interval to 400 flight hours, and requires replacement of the rudder spring tab lever assembly with an improved unit as mandatory terminating action to the inspection requirement.

David Villiers
Delegate of the Civil Aviation Safety Authority

14 July 2008