{"id":"F2006B08098","name":"AD/CESSNA 210/5 Amdt 2 - Rear Spar - Inspection","slug":"ad-cessna-210-5-amdt-2-rear-spar-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115208,"registerId":"commonwealth-F2006B08098-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 210/5 Amdt 2 - Rear Spar - Inspection","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 210 Series Aeroplanes\n\nAD/CESSNA 210/5\n\nAmdt 2\n\n  \nRear Spar \\- Inspection 5/68\n\nApplicability: All except cantilever wing models. (All models prior to model 210G).\n\nRequirement: 1. Visually inspect the main plane rear spar web at the root attach area and the upper flange of the rear spar channel, at the outer end of the attachment fitting, for fatigue cracks.\n\n    2. These cracks originate in the radius which is located beneath the attachment fittings.\n\n    3. This inspection shall be carried out using a magnifying glass of at least 4X magnification or alternatively, a device such as the “Syte Ade” may be employed.\n\n    4. 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 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: At intervals not exceeding 100 hours time in service after 1 September 1971.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, narrow Airworthiness Directive focused on a specific safety-critical inspection for a defined aircraft type. It has not expanded beyond its original purpose of mandating rear spar inspections for fatigue cracks in early Cessna 210 models."},"complexity_factors":["Single, specific technical requirement with clear procedural steps","Only 4 defined applicability criteria (aircraft model, wing type, date threshold)","No cross-references to other legislation or regulations beyond the parent Civil Aviation Regulations 1998","Simple compliance timeline (fixed interval of 100 hours)","Single exception noted (cantilever wing models excluded)","Total length: approximately 200 words","No conditional logic or nested exceptions"],"plain_english_summary":"This CASA Airworthiness Directive mandates regular inspections of the rear wing spar for fatigue cracks on Cessna 210 models made before the cantilever‑wing 210G, affecting owners, operators and maintenance organisations. \n\nInspections must be performed using magnification (or approved alternative) at recurring 100‑hour intervals to detect cracks early and prevent potential wing structural failure."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The text is an amended airworthiness directive but the extract does not identify any changes to applicability or core inspection requirements from prior versions. It states current applicability, inspection method, and a 100‑hour repeat interval without showing how those elements differ from the original instrument."},"complexity_factors":["Narrow applicability: applies only to Cessna 210 models prior to 210G, excluding cantilever wing models (Applicability).","Specific, localized inspection area: fatigue cracks originate in a radius beneath attachment fittings and must be checked at the root attach area and upper flange (Requirement 1–2).","Detection difficulty: close fit of the trailing edge root end can obscure cracks, creating an operational decision to remove that part for a detailed inspection (Requirement 4).","Minimum equipment standard: requires at least 4× magnification or an alternate device such as a 'Syte Ade' (Requirement 3).","Recurring compliance interval: inspections mandated at intervals not exceeding 100 hours time in service, creating ongoing operational and scheduling burden (Compliance).","Limited procedural detail in directive: inspection technique and criteria for acceptable findings are not specified in this extract, leaving room for judgment by operators/maintenance providers (Requirement generally)."],"plain_english_summary":"Requires operators of Cessna 210 models prior to 210G (excluding cantilever‑wing types) to visually inspect the rear spar web and upper flange at the wing root attachment for fatigue cracks, using at least 4× magnification or an equivalent device and removing the trailing edge root end if doubt exists. Inspections must be repeated at intervals not exceeding 100 hours time‑in‑service. Owners/operators pay for and decide when to remove parts for closer inspection; this is a recurring maintenance requirement (Applicability; Requirement; Compliance)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection","history":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection/history","analysis":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection/analysis","conflicts":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection/conflicts","importantCases":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection/important-cases","documents":"/api/acts/ad-cessna-210-5-amdt-2-rear-spar-inspection/documents"}}