{"id":"F2006B06072","name":"AD/PC-12/1 - Nose Landing Gear Forged Main Fitting","slug":"ad-pc-12-1-nose-landing-gear-forged-main-fitting","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":114470,"registerId":"commonwealth-F2006B06072-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PC-12/1 - Nose Landing Gear Forged Main Fitting","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)  \nPilatus PC-12 Series Aeroplanes\n\nAD/PC-12/1 Nose Landing Gear Forged Main Fitting 6/95\n\nApplicability: All PC-12 fitted with nose landing gear P/N 532.20.12.036\n\nRequirement: Locally strip paint and inspect the nose landing gear forged main fitting using the fluorescent penetrant inspection method in accordance with CAO 108.10. Inspect the areas defined in Pilatus Service Bulletin PC-12 32-001, figure 1. Re-protect bare metal with a single coat of primer.\n\nAlternatively a high frequency eddy current inspection method, approved by the Authority may be used, in which case it is not necessary to strip the paint.\n\nCompliance: Initially inspect before 50 hours time in service or before 25 hours time in service after 25 May 1995, whichever occurs later.\n\nRe-inspect at intervals not to exceed 200 hours time in service.\n\nBackground: An operator has reported finding cracks in the upper portion of the nose landing gear main forging. This directive requires removal of the paint and a fluorescent penetrant inspection since the cracks in the forging may be tight and difficult to detect visually. The use of fluorescent penetrant or eddy current increases the reliability of detection and consequently allows an increased inspection interval.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is an Airworthiness Directive (AD)—a standard safety instrument with narrow, specific scope from inception. It addresses exactly one identified safety issue (cracks in one specific aircraft part) and has not expanded beyond this original purpose."},"complexity_factors":["Single, specific technical requirement with clear alternative method","Only one defined term (time in service) used in standard aviation sense","No cross-references to other legislation beyond CAO 108.10 (a standard aviation maintenance reference)","Simple conditional logic: two alternative inspection methods with straightforward compliance deadlines","Short document (approximately 200 words) with single purpose"],"plain_english_summary":"Owners, operators and maintainers of Pilatus PC‑12 aeroplanes with nose landing gear forged main fitting P/N 532.20.12.036 must inspect that fitting for cracks using fluorescent penetrant inspection (after paint removal) or CASA‑approved eddy current inspection (no paint removal), and re‑prime if paint was stripped. Initial inspection is required by the earlier of 50 flight hours or within 25 flight hours after 25 May 1995, then every 200 flight hours. The directive addresses discovered fine cracks that could cause landing gear failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Scope remains focused on detecting cracks in the specified nose landing gear forging (Applicability, Background). The AD limits its reach to that P/N and prescribes inspection methods and intervals, without expanding to other parts or aircraft."},"complexity_factors":["Narrow applicability: only Pilatus PC‑12 with nose gear P/N 532.20.12.036 (Applicability)","Technical inspection methods: fluorescent penetrant per CAO 108.10 and Pilatus SB PC‑12 32‑001, versus high‑frequency eddy‑current (Requirement)","Operational burden: paint stripping, fluorescent inspection, and re‑priming create labour, downtime, and materials costs (Requirement)","Regulatory discretion: alternative inspection method requires Authority approval, creating an approval step and potential variability (Requirement)","Scheduling constraint: specified initial timing and 200‑hour recurring interval impose service scheduling and tracking (Compliance)","Cross‑reference reliance: effectiveness depends on procedures in CAO 108.10 and Pilatus Service Bulletin (Requirement / Background)"],"plain_english_summary":"This AD requires operators of Pilatus PC‑12 aeroplanes fitted with nose landing gear P/N 532.20.12.036 to strip paint and carry out a fluorescent‑penetrant inspection of the nose‑gear forged main fitting per CAO 108.10 and Pilatus Service Bulletin PC‑12 32‑001 (figure 1). An Authority‑approved high‑frequency eddy‑current inspection may be used instead without paint removal.\n\nInitial inspection is before 50 hours TIS (or before 25 hours after 25 May 1995, whichever is later), then re‑inspect every 200 hours. Operators pay for labour, downtime and re‑priming; the Civil Aviation Authority decides acceptable alternative methods."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting","history":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting/history","analysis":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting/analysis","conflicts":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting/conflicts","importantCases":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting/important-cases","documents":"/api/acts/ad-pc-12-1-nose-landing-gear-forged-main-fitting/documents"}}