Commonwealth legislation

AD/FU24/63 - Main Spar Web

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Commonwealth

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legislative instrument

Plain English Summary

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Mechanically, this Airworthiness Directive requires owners/operators of Airparts (NZ) FU24 aircraft with turbine engines to remove underwing panels and fairings, visually inspect the main spar web for buckling, cracking or fastener distress, repair any damage before further flight, and report results to the manufacturer (for onward transmission to the NZ CAA). Compliance must occur within 100 flight hours after 24 Nov 2004 or by 31 Dec 2004, whichever comes first. It affects aircraft operators, maintenance providers and the manufacturer.

This matters because it forces timely inspection, repair and reporting of a primary wing structure component.

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Current sections

Direct links to the current provisions in AD/FU24/63 - Main Spar Web.

AIRWORTHINESS DIRECTIVE

View image in the official source

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 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.

View image in the official source

Airparts (NZ) Ltd. FU 24 Series Aeroplanes

AD/FU24/63 Main Spar Web 1/2005 DM

Applicability: All Model FU24 aircraft equipped with turbine engines.

Requirement: 1. Remove underwing access panels, wing to fuselage fairings, and leading edge intertank fairings to gain access to the main spar web.

2. Visually inspect the main spar web between outer wing attachment and as far inboard of the fuselage attach as possible via the underwing access points, for signs of damage as follows:

Buckling or creasing of the web panels.

b. Cracking of the web, caps, or stiffeners. Cracking may particularly occur in the bend radii of stiffeners near the upper and lower ends of the stiffeners (both integral and riveted web stiffeners).

c. Fastener distress. Inspect web to cap and web to stiffener rivets and fasteners for distortion, missing heads, looseness, or other signs of distress.

3. If damage is found during the inspection, repair before further flight.

4. Report findings (including nil damage) to the manufacturer for on-forwarding to the NZ CAA.

Note: NZ CAA AD DCA/FU24/175 refers.

Compliance: Within 100 hours time in service after 24 November 2004 or by 31 December 2004, whichever occurs first.

This Airworthiness Directive becomes effective on 24 November 2004.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

Airparts (NZ) Ltd. FU 24 Series Aeroplanes