AD/FU24/62 - Forward Fin Structure

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B10008 Not in force Legislative Instrument

Legislation content

 


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 39.1 (1) of CAR 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.

 

Airparts (NZ) Ltd. FU 24 Series Aeroplanes

 

AD/FU24/62 Forward Fin Structure  6/2002 DM

 

Applicability: All Model FU24, FU24A, -950, -950M, and -954.

 

Requirement: Referring to Figure 1, perform a detailed visual inspection of the forward area at the base of the fin for cracks. Pay particular attention to the skin in the area of the rivets that join the fin skin to bulkhead part number 242305, and aft to the first vertical lap joint. Inspect from the bottom of the fin up to the first external strap. To accomplish this inspection, any rubber abrasion protection that is fitted in this area, including any sealant, must be removed. The fin leading edge fairing, part number 242321, must also be removed.

 

If any structure is found cracked, repair before further flight.


 

Figure 1

 

Note: NZ CAA Emergency AD DCA/FU24/173 refers.

 

Compliance: Before 8 May 2002.

 

This Airworthiness Directive becomes effective on 1 May 2002.

 

Airparts (NZ) Ltd. FU 24 Series Aeroplanes

 

AD/FU24/62 (continued)

 

Background: The NZ CAA raised an airworthiness directive in response to a recent fatal accident where the aircraft’s fin separated in flight. Initial investigation revealed that the forward fin structure failed from fatigue cracks that were concealed beneath the rubber abrasion protection fitted to the fin. This Directive is considered interim action, pending completion of the investigation.


 

Steven John Swift

Delegate of the Civil Aviation Safety Authority 24 April 2002

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 1 May 2002..

Interactions

Authorises

All Versions

Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.