{"id":"F2006B08202","name":"AD/CESSNA 320/23 - Main Landing Gear Attachment - Inspection","slug":"ad-cessna-320-23-main-landing-gear-attachment-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115414,"registerId":"commonwealth-F2006B08202-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 320/23 - Main Landing Gear Attachment - Inspection","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 320/23  Main Landing Gear Attachment - Inspection\n\nApplicability: All models 320 to 320D inclusive. Requirement:  With aeroplane on jacks:\n\n1. Remove Main Landing Gear Attaching “U” Bolts and Shafts.\n\n\n# 8/75\n\n \n\n2.    Visually inspect the “U” Bolts, with the aid of a 10X glass, in the area of the thread root ends for cracks.\n\n \n\n3.    Visually inspect the Attaching Shafts, with the aid of a 10X glass, in the area of the roll pin hole for cracks.\n\n \n\nCompliance: 1. For MLG attachment shafts and “U” bolts which have achieved 2500 hours at 12 August 1975; within 100 hours time in service and thereafter at intervals not exceeding 200 hours time in service.\n\n \n\n2. All other MLG attachment shafts and “U” bolts; before achieving 2500 hours time in service and thereafter at intervals not exceeding 200 hours time in service.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive focused on a specific mechanical failure mode in a specific aircraft type. It has not expanded beyond its original purpose of mandating inspections for landing gear attachment cracks."},"complexity_factors":["Very short document (approximately 200 words)","Only 2 defined applicability criteria (aircraft models and part hours)","Simple conditional structure (two compliance pathways based on existing flight hours)","No cross-references to other legislation or regulations","Straightforward procedural requirements with minimal technical exceptions","Single subject matter (one specific inspection task)"],"plain_english_summary":"This CASA Airworthiness Directive requires operators of Cessna 320–320D aeroplanes to jack the aircraft, remove the main landing-gear “U” bolts and shafts, and inspect those parts with a 10× magnifier for cracks at the thread ends and roll-pin hole. Inspections must occur before/at 2,500 flight hours (or within 100 fh if already over by Aug 1975) and recur every 200 fh to prevent fatigue-related gear failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Scope remains focused on inspection of main landing‑gear attaching U‑bolts and shafts for Cessna 320–320D models. The directive sets initial inspection timing using a historical hours threshold (12 Aug 1975) and mandates recurring 200‑hour inspections; it does not expand applicability or add other component requirements."},"complexity_factors":["Clear, narrow technical requirement (visual inspection with 10× magnifier) reduces procedural complexity.","Time-based compliance thresholds tied to a historical date (≥2,500 hours as of 12 Aug 1975) create conditional initial inspections.","Recurring periodicity (every 200 hours) imposes ongoing operational planning and tracking.","Physical removal of parts and jacking the aircraft increases labour, tooling and downtime requirements.","No remedial action or replacement criteria specified in the text if cracks are found, creating implementation discretion for maintainers.","Applicability covers all models 320–320D, so fleet operators must apply the rule uniformly across variants."],"plain_english_summary":"Mandates that owners/operators of Cessna 320–320D aircraft jack the aeroplane, remove main landing‑gear “U” bolts and attaching shafts, and inspect (with a 10× glass) for cracks at the thread‑root ends and at the roll‑pin hole. Parts with ≥2,500 hours as of 12 Aug 1975 must be inspected within 100 hours and then every 200 hours; all others before 2,500 hours and thereafter every 200 hours. This creates recurring inspection work and maintenance costs for operators and requires certified maintenance personnel to perform removals and checks."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection","history":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection/history","analysis":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection/analysis","conflicts":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection/conflicts","importantCases":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection/important-cases","documents":"/api/acts/ad-cessna-320-23-main-landing-gear-attachment-inspection/documents"}}