{"id":"F2006B08197","name":"AD/CESSNA 320/19 Amdt 1 - Wing and Airframe","slug":"ad-cessna-320-19-amdt-1-wing-and-airframe","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115406,"registerId":"commonwealth-F2006B08197-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 320/19 Amdt 1 - Wing and Airframe","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nCessna 320 Series Aeroplanes\n\nAD/CESSNA 320/19\n\nAmdt 1\n\n  \nWing and Airframe 10/95\n\nApplicability: All Cessna Model 320 Series aircraft.\n\nRequirement: 1. Retire the wing main spar lower cap and wing upper and lower attachment fittings from service.\n\nNote: The centre section spar caps and attachment fittings are not affected by this Requirement.\n\n2. Retire the remainder of the airframe from service.\n\nCompliance: 1. Retire components, in accordance with Requirement 1, before exceeding 19 200 hours time in service or 29 500 flights, whichever occurs first.\n\n2. Retire airframe, in accordance with Requirement 2, before exceeding 38 400 hours time in service or before 59 000 flights, whichever occurs first.\n\nNote 1: For aircraft with an unknown number of flights an estimate shall be made by dividing the number of hours flown by an average flight time of 0.5 hours.\n\nNote 2: The available fatigue data covers wing main spars only. The durability of other parts of the airframe has not been evaluated, and is therefore unknown. Based on experience, the Authority is prepared to credit unevaluated structure with a retirement life equal to double the life for the wing spar (Requirement 2). An extension beyond this may be available, but any application must be supported by a fatigue substantiation covering all the remaining primary structure. This should include empennage, wing centre section, wing rear spar, control surfaces, fuselage, etc. The substantiation may take the form of a safe life assessment, or a sufficiently rigorous revised inspection schedule to ensure that any fatigue cracking which could occur in service will be detected before the aircraft is endangered.\n\nBackground: Results of full scale fatigue testing of the wing, flight load data analysis and fleet usage have been used to extend the model 320 wing and attachment fitting fatigue life. The remainder of the airframe is allowed two wing spar lives without further substantiation.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original narrow scope — setting fatigue life limits for a specific aircraft model (Cessna 320 series). The document has not expanded beyond its safety-critical purpose of mandating component and airframe retirement."},"complexity_factors":["Short, single-purpose document (2 pages)","Only 2 defined operational terms ('time in service' and 'flights' used with standard aviation meanings)","Clear sequential structure: Applicability → Requirement → Compliance → Background","Minimal cross-referencing (only internal references to Requirement 1 and 2)","Simple conditional logic (whichever occurs first comparisons)","Two explanatory notes providing calculation methodology and technical justification"],"plain_english_summary":"CASA requires mandatory retirement deadlines for Cessna Model 320 series: critical wing parts must be removed before 19,200 flight hours or 29,500 cycles, and the entire airframe retired before 38,400 hours or 59,000 cycles (whichever is first). This affects owners, operators and maintenance organisations to mitigate metal‑fatigue risk; flying beyond the limits needs extensive engineering approval. Noncompliance is illegal and unsafe."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"The instrument extends and fixes explicit retirement lives: it sets new life limits for wing spars and attachment fittings and allows the rest of the airframe a retirement life equal to two wing-spar lives absent further substantiation. The Background states this is based on fatigue testing that extended wing and fitting fatigue life; further extension requires a full fatigue substantiation covering primary structure (Background; Reqs 1–2; Note 2)."},"complexity_factors":["Technical fatigue data is explicitly available only for wing main spars, not other structures (Note 2, Background).","Dual retirement thresholds expressed in hours or flight counts create parallel compliance metrics (Compliance, Reqs 1–2).","Rule for estimating unknown flight counts (divide hours by 0.5) imposes an indirect calculation and recordkeeping requirement (Note 1).","Centre section spar caps are carved out and not affected, requiring careful part-level distinction (Requirement 1).","Extensions require a fatigue substantiation covering multiple primary structures or a revised, rigorous inspection schedule — a technically demanding approval path (Note 2).","Operational compliance depends on accurate logbooks and calculation of flight cycles; enforcement requires administrative verification (Compliance, Note 1).","Phrase \"remainder of the airframe\" and scope of \"primary structure\" leave practical delineation and inspection burden open to interpretation (Note 2)."],"plain_english_summary":"This airworthiness directive requires owners/operators of all Cessna Model 320 aircraft to retire the wing main spar lower cap and the wing upper and lower attachment fittings by 19,200 hours or 29,500 flights, and to retire the remainder of the airframe by 38,400 hours or 59,000 flights (Reqs 1–2). Operators must track hours and flights (if flights unknown, estimate = hours/0.5), bear retirement costs, and may seek life extensions only with a full fatigue substantiation covering primary structure (Notes 1–2, Background)."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe","history":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe/history","analysis":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe/analysis","conflicts":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe/conflicts","importantCases":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe/important-cases","documents":"/api/acts/ad-cessna-320-19-amdt-1-wing-and-airframe/documents"}}