{"id":"F2006B05234","name":"AD/CESSNA 206/3 Amdt 3 - Wing Rear Spar","slug":"ad-cessna-206-3-amdt-3-wing-rear-spar","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":45522,"registerId":"commonwealth-F2006B05234-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 206/3 Amdt 3 - Wing Rear Spar","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 206 Series Aeroplanes\n\nAD/CESSNA 206/3\n\nAmdt 3\n\n  \nWing Rear Spar 1/90\n\nApplicability: All models fitted with rear spar assembly P/N 1220050-1, \\-2, \\-23, \\-24, \\-25 or \\-26.\n\nNote: These part numbers are in aircraft serial numbers 206-0001 to 206-0275, U206-0276 to U206-1367, and P206-0001 to P206-0597; excepting of course those aircraft that have had rear spar assemblies replaced with later part numbers.\n\nRequirement: Visually inspect each main plane rear spar web for fatigue cracking at the root attachment area and the upper flange of the rear spar channel at the outer end of the attachment fittings. These cracks originate in the radius which is located beneath the attachment fittings. This inspection shall be carried out using a magnifying glass of at lease 4X magnification or alternatively, a device such as the “Syte Ade” may be employed. Since the trailing edge root end rib fits closely to the spar, it may be difficult to detect possible cracks, therefore, where doubt exists, the trailing edge root end rib shall be removed for more detailed inspection.\n\nNote: The affected area is illustrated in Rex Aviation Technical Memorandum No. 12 dated 10 May 1960.\n\nCompliance: Within 500 hours time in service after 25 January 1990, and thereafter at intervals not exceeding 500 hours time in service.\n\nBackground: There have been several reports of cracks in the rear spar near the attachment fitting, including at least one fatal accident, in another model that uses a similar design of spar assembly.\n\nThe problem seems to be confined to the early design rear spars. Later spars have a thicker web and additional doublers. Amendment 3 changes the applicability of this Directive to clarify that only the early part number rear spars need to be inspected.\n\nThe inspection interval has been extended to 500 hours based on service experience.","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"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 3 narrows the Directive’s scope by limiting applicability to early rear spar assemblies listed by part number (see 'Applicability' and 'Background') and raises the inspection interval to 500 hours (see 'Compliance' and 'Background'). Practically, fewer aircraft are subject to the inspections, while affected owners/operators must perform recurring inspections (and sometimes remove the trailing edge root end rib) at the stated intervals. The Civil Aviation Safety Authority issues the requirement; owners/operators pay the inspection and remediation costs (see 'Requirement' and 'Compliance')."},"complexity_factors":["Clear, narrow technical requirement (Requirement): visual inspection with specified minimum magnification (4X) or equivalent device.","Identification of affected hardware (Applicability): specific rear spar part numbers and serial-number ranges determine who is covered.","Compliance timing (Compliance): fixed service-hour deadlines — initial within 500 hours after 25 Jan 1990, then every 500 hours.","Access/detection difficulty (Requirement): potential need to remove the trailing edge root end rib where cracks are hard to see increases labour/time.","Safety-critical context (Background): presence of reported cracks and at least one fatal accident raises enforcement priority.","Amendment change (Background): alters applicability and interval, so operators must confirm spar part numbers before deciding inspection frequency."],"plain_english_summary":"Requires owners/operators of Cessna 206 aeroplanes fitted with the listed early rear-spar part numbers to visually inspect the wing rear-spar web for fatigue cracking at the root attachment and upper flange, using at least 4X magnification (or equivalent). Inspections must occur within 500 hours after 25 January 1990 and every 500 hours thereafter. Amendment 3 narrows applicability to those early part numbers and extends the inspection interval to 500 hours, citing reports of cracks including a fatal accident."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":true,"description":"Amendment 3 narrowed the scope from previous versions. Originally the directive likely applied more broadly to Cessna 206 aircraft; Amendment 3 specifically restricts it to only the early-design rear spars (part numbers 1220050-1, -2, -23, -24, -25, -26) and explicitly excludes aircraft with later, improved spar designs. The inspection interval was also extended based on operational experience, reducing regulatory burden on operators."},"complexity_factors":["Single, specific technical requirement with clear applicability criteria","Only 6 defined part numbers in applicability section","Simple compliance timeline: 500 hours initial, then recurring every 500 hours","No cross-references to other legislation or regulations beyond the enabling Civil Aviation Regulations 1998","One conditional element (removal of rib 'where doubt exists')","Straightforward amendment history explaining the change from previous versions"],"plain_english_summary":"This CASA safety rule requires owners/operators of early-model Cessna 206/U206/P206 aircraft with original rear wing spars to inspect the rear spar for fatigue cracks. It targets aircraft built in the 1960s–mid‑1970s that retain the early spar design.\n\nInspections use magnification (or a special tool) and may require removing the trailing edge root rib for access, are recurring (every 500 flight hours), and aim to prevent catastrophic wing failure after fatigue cracking and at least one fatal accident."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar","history":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar/history","analysis":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar/analysis","conflicts":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar/conflicts","importantCases":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar/important-cases","documents":"/api/acts/ad-cessna-206-3-amdt-3-wing-rear-spar/documents"}}