Document ID: chunk:federal_register_of_legislation:F2009L01484:body:0
Version: federal_register_of_legislation:F2009L01484
Segment Type: other
Provision Reference: 
Character Range: 0–2124

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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 328/72  Elevator, Rudder and Aileron  5/2009
              Trim Tab Assemblies

Applicability:  Model 328-100 aircraft, all serial numbers; and,

                Model 328-300 aircraft, all serial numbers.
Requirement:    Action in accordance with the requirements of EASA AD 2009-0044.

                Note:  328 Support Services GmbH Service Bulletins SB-328-27-483 original issue, and SB-328J-27-233 original issue, or later EASA approved revisions, refer.
Compliance:     As specified in the Requirement document, with a revised effective date of
                7 May 2009.
                This Airworthiness Directive becomes effective on 7 May 2009.
Background:     During a recent Aileron Dual Load Path and Linkage Inspection, which is a certification maintenance requirement (CMR) task, the installed control rods were found to be corroded.  An investigation revealed that the Tab Side Fitting was cracked.  Subsequently, similar cracks were found in a supporting lever of the Control Rod attachment fitting of the Trim Tab on another aircraft, during the applicable CMR inspection.  This condition, if not corrected, could lead to structural failure of the dual path attachment arrangement of the affected trim and spring tabs, possibly resulting in a flutter problem that could lead to loss of control of the aircraft.

David Villiers
Delegate of the Civil Aviation Safety Authority

11 March 2009