{"id":"F2006B08210","name":"AD/CESSNA 320/30 Amdt 1 - Wing Front Spar Lower Attachment Fittings","slug":"ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115436,"registerId":"commonwealth-F2006B08210-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 320/30 Amdt 1 - Wing Front Spar Lower Attachment Fittings","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Cessna 320 Series Aeroplanes\n\n \n\n# AD/CESSNA 320/30\n\nAmdt 1\n\nApplicability: All models.\n\n# Wing Front Spar Lower Attachment Fittings 6/89\n\n \n\nRequirement: 1. Remove the fairing between the wing and carry-thru and gain access to the wing front spar lower attachment fittings P/N 0822550.\n\n \n\n2.    Visually inspect the upper and lower edges of the lug of each wing fitting, looking for cracks as shown in the figure below.\n\n \n\n3.    From inside the wheel well, visually inspect each visible wing fitting for cracks and surface pitting in the area shown in the figure.\n\nNote: It is not necessary to remove the primer for any of the above inspections.\n\n \n\n \n\n![](image.002.png)  \n\n\n \n\n \n\nWing Fitting Showing Typical Cracking\n\nNote: Fitting Shown removed from aircraft for clarity\n\nCompliance: Before exceeding 5000 hours component time in service or before the issue of the next Maintenance Release after 15 June 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.\n\n \n\nBackground:  Fatigue cracking has been discovered in the wing fitting from an Australian-registered Cessna 310R with 6500 hours time in service. No abnormality could be found in the fitting or the aircraft’s history. Since then stress corrosion cracking has been found in a similar wing fitting in a Cessna 402C with 6400 hours time in service.\n\n \n\nThere is insufficient evidence to regard either of these as isolated occurrences: either or both may be expected to occur at a later time elsewhere in the fleet of Cessna twins which use the same generic wing fitting. A simple repetitive visual inspection has therefore been introduced.\n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"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 Amendment 1 to an existing Airworthiness Directive. The scope remains tightly focused on the original safety concern — inspection of wing front spar lower attachment fittings on Cessna 320 series aircraft. The amendment appears to be a routine update (possibly clarifying inspection procedures or compliance dates) without expanding the directive to additional aircraft types or structural components."},"complexity_factors":["Single, clearly defined applicability (All models of Cessna 320 series)","Only 3 specific inspection steps required","One defined part number (P/N 0822550)","Simple compliance timeline with clear alternative triggers (hours OR date)","No cross-references to other legislation or regulations","No nested exceptions or conditional logic","Background section provides clear rationale without adding legal complexity","Visual diagram referenced but not legally operative text"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections of the wing front spar lower attachment fittings on Cessna 320 series and other Cessna twins using the same fitting, to detect fatigue cracks and corrosion that could cause wing failure. \n\nOwners/operators must remove the fairing and perform required visual checks (no primer stripping) before the specified service threshold and thereafter at each Maintenance Release to prevent catastrophic structural failure."},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"The issued text applies to 'All models' and mandates inspections of P/N 0822550; the instrument is presented as an amendment but contains no information within the provided text that indicates a change in scope from an earlier version or the original intent."},"complexity_factors":["Applicability: specified as 'All models' — broad fleet coverage increases operational reach but keeps technical content uniform (Applicability).","Part- and task-specific actions: removal of fairing to gain access to a named part number (P/N 0822550) introduces a discrete access task (Requirement 1).","Inspection methods: repetitive visual inspections of specific lug edges and wheel-well views, with a no-primer-removal note limiting invasive work (Requirements 2–3; Note).","Compliance timing: a hard threshold (before 5,000 hours component time or next Maintenance Release after 15 June 1989) then continuing reinspections at each scheduled Maintenance Release — creates recurring compliance scheduling (Compliance).","Corrective-works implied: discovery of cracks will require repair/replacement actions and associated labour/parts costs (implied by inspection requirement and background).","Technical cause and uncertainty: background cites fatigue and stress-corrosion cracking in similar fittings, which motivates recurring inspections but leaves uncertainty about rate/location of future failures (Background)."],"plain_english_summary":"This airworthiness directive requires operators of all Cessna 320 series aeroplanes to remove the wing-to-carry‑through fairing and visually inspect the wing front spar lower attachment fittings (P/N 0822550) for cracks and surface pitting, including inspections from inside the wheel well; primer need not be removed. Operators must comply before the fitting exceeds 5,000 hours component time or by the next Maintenance Release after 15 June 1989, and then at each scheduled inspection. Operators bear inspection and any corrective costs; CASA enforces compliance."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings","history":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings/history","analysis":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings/analysis","conflicts":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings/conflicts","importantCases":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings/important-cases","documents":"/api/acts/ad-cessna-320-30-amdt-1-wing-front-spar-lower-attachment-fittings/documents"}}