{"id":"F2006B06106","name":"AD/PC-12/44 - Main Landing Gear Actuator","slug":"ad-pc-12-44-main-landing-gear-actuator","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":46853,"registerId":"commonwealth-F2006B06106-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# AIRWORTHINESS DIRECTIVE\n\n![](image.001.png)\n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\n![](image.001.png)  \n\nPilatus PC-12 Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/PC-12/44 Main Landing Gear Actuator 1","sectionType":"part","heading":"AD/PC-12/44 Main Landing Gear Actuator 11/2004","content":"# AD/PC-12/44 Main Landing Gear Actuator 11/2004\n\nApplicability: All Model PC-12 and PC-12/45 aircraft, serial numbers MSN 101 through MSN 560, and equipped with main landing gear actuators part number 960.30.01.103 with serial numbers 830E through 881E.\n\nRequirement: Action in accordance with Pilatus Aircraft PC-12 Service Bulletin No. 32-017, dated 3 August 2004, or a later revision approved by the FOCA.\n\nNote: Switzerland FOCA AD HB-2004-330 refers.\n\nCompliance: Before the accumulation of 1,000 hours total time in service on affected main landing gear actuator(s), but not later than 12 months after 28 October 2004.\n\nThis Airworthiness Directive becomes effective on 28 October 2004.\n\nBackground: The manufacturer has determined that some components of certain main landing gear actuators have had incorrect heat treatment during manufacture. Components in this condition can decrease the specified fatigue life of the actuators.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.002.png)  \n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 16 September 2004\n\n![](image.001.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 6 October 2004.","sortOrder":1}],"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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive with a narrow, specific scope addressing a single identified manufacturing defect in a specific aircraft component. The scope matches the original intent of correcting an unsafe condition in affected aircraft."},"complexity_factors":["Single, clearly defined applicability section with specific part and serial numbers","Single requirement referencing an external technical document (Service Bulletin)","Simple compliance deadline (whichever comes first of two conditions)","No defined terms section, no cross-references to other legislation beyond the enabling regulation (CASR 1998 subregulation 39.1(1))","No conditional logic or exceptions within the directive itself","Total length is approximately 250 words"],"plain_english_summary":"This safety order requires owners/operators of Pilatus PC‑12 and PC‑12/45 aircraft (S/N 101–560) fitted with main landing gear actuators P/N 960.30.01.103 (S/N 830E–881E) to follow Pilatus Service Bulletin No. 32‑017 (or later approved revision). Certain actuators had incorrect heat treatment reducing fatigue life; inspections/repairs must be done before those actuators reach 1,000 flight hours or within 12 months of 28 Oct 2004, to prevent landing‑gear failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD's scope matches the manufacturer's identified affected batch: specified PC-12/PC-12/45 MSNs and actuator part/serial numbers. It mandates corrective action per the named service bulletin and sets a clear compliance window. The instrument does allow later FOCA‑approved revisions to the service bulletin, which could modify approved means of compliance, but the AD itself does not expand or narrow the originally identified affected population."},"complexity_factors":["Narrow, specific applicability limited to defined aircraft MSNs and actuator part/serial numbers (reduces scope complexity).","Single prescriptive remedy: follow Pilatus Service Bulletin No. 32‑017 or later FOCA‑approved revision (dependency on manufacturer instructions and foreign authority approval).","Dual compliance trigger: either a flight-hour threshold (1,000 hours on actuator) or a calendar deadline (12 months from 28 Oct 2004) — requires operator tracking of hours and dates.","Technical cause (incorrect heat treatment / reduced fatigue life) may require component-level inspection/repair or replacement, involving maintenance resources and parts availability.","Legal basis under CASR subregulation 39.1(1) — enforces mandatory corrective action by CASA delegate; Gazette notification establishes effective date.","Potential for later approved service bulletin revisions to alter procedures or tolerances — introduces limited regulatory discretion over acceptable methods."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of Pilatus PC-12 and PC-12/45 aeroplanes (MSN 101–560) fitted with main landing gear actuator P/N 960.30.01.103, S/N 830E–881E, to carry out the work set out in Pilatus Service Bulletin No. 32‑017 (or a later FOCA‑approved revision). Compliance is required before an affected actuator accumulates 1,000 hours in service or within 12 months of 28 October 2004. The AD responds to incorrect heat treatment in some actuator components that can reduce fatigue life, and places the inspection/repair cost and record-keeping burden on operators."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pc-12-44-main-landing-gear-actuator","history":"/api/acts/ad-pc-12-44-main-landing-gear-actuator/history","analysis":"/api/acts/ad-pc-12-44-main-landing-gear-actuator/analysis","conflicts":"/api/acts/ad-pc-12-44-main-landing-gear-actuator/conflicts","importantCases":"/api/acts/ad-pc-12-44-main-landing-gear-actuator/important-cases","documents":"/api/acts/ad-pc-12-44-main-landing-gear-actuator/documents"}}