{"id":"F2006B10009","name":"AD/FU24/63 - Main Spar Web","slug":"ad-fu24-63-main-spar-web","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":55368,"registerId":"commonwealth-F2006B10009-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# ![](image.001.png)  \nAIRWORTHINESS DIRECTIVE\n\nFor 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.\n\n![](image.001.png)  \n\nAirparts (NZ) Ltd. FU 24 Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/FU24/63 Main Spar Web 1/2005 DM","sectionType":"part","heading":"AD/FU24/63 Main Spar Web 1/2005 DM","content":"# AD/FU24/63 Main Spar Web 1/2005 DM\n\nApplicability: All Model FU24 aircraft equipped with turbine engines.\n\nRequirement: 1. Remove underwing access panels, wing to fuselage fairings, and leading edge intertank fairings to gain access to the main spar web.\n\n    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:\n\n    Buckling or creasing of the web panels.\n\n    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).\n\n    c. Fastener distress. Inspect web to cap and web to stiffener rivets and fasteners for distortion, missing heads, looseness, or other signs of distress.\n\n    3. If damage is found during the inspection, repair before further flight.\n\n    4. Report findings (including nil damage) to the manufacturer for on-forwarding to the NZ CAA.\n\nNote: NZ CAA AD DCA/FU24/175 refers.\n\nCompliance: Within 100 hours time in service after 24 November 2004 or by 31 December 2004, whichever occurs first.\n\nThis Airworthiness Directive becomes effective on 24 November 2004.","sortOrder":1}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, single-issue airworthiness directive focused specifically on main spar web inspections for one aircraft model. It has not expanded beyond its original safety purpose."},"complexity_factors":["Single, discrete safety action with clear mechanical steps","Only 4 defined procedural requirements plus a reporting obligation","No nested exceptions or conditional logic — inspection required for all applicable aircraft regardless of other factors","Single cross-reference to related NZ authority directive (informational only)","Clear, unambiguous compliance deadline with simple 'whichever occurs first' formulation","No interpretive provisions, definitions section, or delegated legislative mechanisms"],"plain_english_summary":"This AD mandates owners/operators of Fletcher FU24 aircraft with turbine engines to inspect the wing’s main spar web for cracking, buckling, or damaged rivets, and repair any defects before further flight. The inspection had to be completed within 100 flight hours after 24 Nov 2004 (or by 31 Dec 2004), with results reported to the manufacturer for forwarding to New Zealand’s regulator. It prevents catastrophic wing failure."},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"Based solely on the AD text provided, the scope is limited to Model FU24 aircraft with turbine engines and mandates inspection, repair and reporting. The instrument does not on its face expand or narrow that applicability beyond stating the affected models and the required corrective actions and timeframe."},"complexity_factors":["Technical inspection of a primary structure (main spar web) requires removal of underwing access panels and fairings, increasing maintenance effort and downtime (Requirement).","Inspection criteria are visual and cover multiple damage modes: buckling/creasing, cracking (including stiffener bend radii), and fastener distress — demands experienced inspection judgment (Requirement).","Mandatory repair before further flight creates an immediate operational constraint if damage is found (Requirement).","Reporting obligation to the manufacturer and onward to NZ CAA adds administrative compliance steps and recordkeeping (Requirement).","Short compliance window (within 100 hours or by 31 Dec 2004) increases scheduling pressure for operators (Compliance).","Applicability limited to FU24 models fitted with turbine engines narrows affected population but concentrates work among those operators (Applicability)."],"plain_english_summary":"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.\n\nThis matters because it forces timely inspection, repair and reporting of a primary wing structure component."}},"importantCases":[],"_links":{"self":"/api/acts/ad-fu24-63-main-spar-web","history":"/api/acts/ad-fu24-63-main-spar-web/history","analysis":"/api/acts/ad-fu24-63-main-spar-web/analysis","conflicts":"/api/acts/ad-fu24-63-main-spar-web/conflicts","importantCases":"/api/acts/ad-fu24-63-main-spar-web/important-cases","documents":"/api/acts/ad-fu24-63-main-spar-web/documents"}}