{"id":"F2006B05210","name":"AD/CESSNA 205/5 Amdt 1 - Rear Spar","slug":"ad-cessna-205-5-amdt-1-rear-spar","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":45443,"registerId":"commonwealth-F2006B05210-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 205/5 Amdt 1 - 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 205 (210-5) Series Aeroplanes\n\nAD/CESSNA 205/5\n\nAmdt 1\n\n  \nRear Spar 1/75\n\nApplicability: All models except those with rear spar P/Nos. 0523400-90 LH and \\-91 RH. 0523400- 111 LH and -112 RH.\n\nRequirement: 1\\. Visually inspect the main plane rear spar web at the root attachment area and upper flange of the rear spar channel at the outer end of the attachment fittings 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 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 100 hours time in service after 30 November 1967 and thereafter at intervals not exceeding 100 hours time in service.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a narrow, targeted safety directive focused on a specific structural defect in a specific aircraft model. It has not expanded beyond its original purpose of mandating repetitive inspections for rear spar fatigue cracks in Cessna 205 series aircraft."},"complexity_factors":["Single, specific aircraft type (Cessna 205/210-5 series)","Clear applicability exclusion (4 specific part numbers listed)","Straightforward two-part inspection requirement with one alternative method (magnifying glass vs. Syte Ade device)","Single compliance deadline with simple recurring interval (100 hours time in service)","One conditional instruction (removal of trailing edge root end rib only 'where doubt exists')","No cross-references to other legislation or complex defined terms","Short document (approximately 200 words)","Single note referencing external technical document for illustration purposes only"],"plain_english_summary":"This CASA Airworthiness Directive mandates repetitive inspections of the rear spar on Cessna 205 (210‑5) series aeroplanes (excluding aircraft with specified alternative rear spar part numbers) to detect fatigue cracks in the root attachment area and upper flange radii.  \n\nInspections require at least 4× magnification, removal of the trailing edge root end rib if it obstructs the view, and must be done within 100 hours of the effective date and every 100 hours thereafter to prevent potential catastrophic structural failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The provided text sets inspection requirements, exclusions, methods, and intervals but contains no comparative material showing a change in applicability or obligations from an earlier instrument; the title shows 'Amdt 1' but no prior-versus-current differences are provided."},"complexity_factors":["Applicability carve-outs: four specific rear-spar part numbers are excluded from the requirement, so operators must check part numbers before applying the AD.","Localized inspection area: inspection targets the rear spar web at the root attachment and the upper flange at the outer end of attachment fittings (identifying the precise area may require the Rex Aviation Technical Memorandum No. 12 for illustration).","Crack origin detail: directive states cracks originate in the radius beneath attachment fittings, which narrows where inspectors must concentrate their search.","Prescribed inspection technique: requires a magnifying glass of at least 4X or an equivalent device (e.g. 'Syte Ade'), creating a minimum tooling/skill standard.","Removal discretion: where visual access is impeded, the trailing-edge root end rib must be removed for a detailed inspection, imposing additional labour and potential downtime decisions on operators.","Fixed periodicity and retroactive hook: compliance is tied to a historical start date (within 100 hours after 30 Nov 1967) and fixed 100-hour intervals, creating a recurring operational burden."],"plain_english_summary":"This Airworthiness Directive requires operators of Cessna 205/210-5 series aeroplanes (except those fitted with four specified rear-spar part numbers) to visually inspect the rear spar web and the upper flange at the attachment fittings for fatigue cracks, using at least 4X magnification or an equivalent device and removing the trailing-edge root rib if doubt exists. The Civil Aviation Safety Authority requires the first inspection within 100 hours time in service after 30 November 1967 and then every 100 hours thereafter; owners/operators pay for and carry out the inspections."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar","history":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar/history","analysis":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar/analysis","conflicts":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar/conflicts","importantCases":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar/important-cases","documents":"/api/acts/ad-cessna-205-5-amdt-1-rear-spar/documents"}}