{"id":"F2006L01097","name":"AD/CONVAIR/10 - Main Landing Gear Cylinders","slug":"ad-convair-10-main-landing-gear-cylinders","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":58443,"registerId":"commonwealth-F2006L01097-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Kelowna Flightcraft (General Dynamics/Co","sectionType":"division","heading":"Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes","content":"### Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes\n\n| AD/CONVAIR/10 | Main Landing Gear Cylinders | 5/2006 |\n| ------------- | --------------------------- | ------ |\n\n| Applicability: | Model 340 and 440 aircraft, and all such model aircraft converted to turbopropeller power.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Inspect the entire outer surface of the main landing gear cylinders part numbers 528002 or 528402, including the fulcrum arms, for cracks using magnetic particle or dye penetrant methods, or approved equivalent method.If cracks are detected, before further flight, either rework the cylinder in a manner approved by the FAA, or replace the cylinder with a cylinder which has been inspected in accordance with Requirement 1, and is found to be free of cracks.2. If cylinders are reworked, accomplish the following:a. Identify and record the cylinders and areas reworked.b. Limit the use of reworked cylinders to those aircraft operating below or at a maximum of 55,000 lbs. take-off gross weight. If any reworked cylinder is installed in any aircraft converted to turbopropeller power in accordance with STC SA4-1100 (known as Model 580), install a placard in only those aircraft previously approved for operating weights above 55,000 lbs., and in full view of the pilots, which reads as follows: “Maximum Take-off Gross Weight 55,000 lbs.”3. Repeat the Requirement 1 inspection.4. If no cracks are detected during any Requirement 1 inspection, and it is determined that a cylinder has less than 14,000 hours time in service, repeat the Requirement 1 inspection.5. If no cracks are detected during any Requirement 1 or 4 inspection, and a cylinder is determined to have more than 14,000 hours time in service, repeat the Requirement 1 inspection.Note: FAA AD 71-02-03 Amdt 39-1145 refers. |\n\n| Compliance: | 1. Unless the initial inspection is already accomplished, within 50 hours time in service after 11 May 2006.2. Before further flight.3. At intervals not to exceed 1,000 hours time in service from the last inspection.4. Before the accumulation of 15,000 hours time in service.5. At intervals not to exceed 1,000 hours time in service from the last inspection. |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Airworthiness Directive becomes effective on 11 May 2006.                                                                                                                                                                                                                                                                                                         |\n| Background: | The FAA requires inspections to detect cracking in the main landing gear cylinders. Undetected cracks could result in failure of a main landing gear.                                                                                                                                                                                                                  |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 March 2006","sortOrder":0},{"sectionNumber":"AD/CONVAIR/10","sectionType":"part","heading":"AD/CONVAIR/10","content":"## AD/CONVAIR/10","sortOrder":1},{"sectionNumber":"Main Landing Gear Cylinders","sectionType":"part","heading":"Main Landing Gear Cylinders","content":"## Main Landing Gear Cylinders","sortOrder":2},{"sectionNumber":"5/2006","sectionType":"part","heading":"5/2006","content":"## 5/2006","sortOrder":3}],"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":false,"description":"The directive targets inspections and remedial action for specific main landing‑gear cylinders (P/N 528002, 528402) on Convair Model 340/440 and their turboprop conversions (Applicability). It implements inspection intervals, repair/replace requirements, recordkeeping and weight/placard limits (Requirements, Compliance) to detect cracking; it does not broaden applicability beyond those parts/models or add unrelated obligations."},"complexity_factors":["Specific applicability to Model 340/440 and turboprop conversions and to two part numbers (Applicability) — narrows who must comply but requires operators to verify parts.","Multiple inspection triggers and branching intervals (Requirement 1, 4, 5; Compliance) — initial within 50 hours unless already done, repeat every 1,000 hours, and different checks tied to 14,000/15,000 hours thresholds.","Requirement that rework be approved by the FAA or cylinders be replaced before further flight (Requirement 1 & 2) — adds regulatory approval step and potential downtime/cost for operators.","Recordkeeping/identification duty for reworked cylinders (Requirement 2a) — administrative compliance burden on operators.","Operational limitation on reworked cylinders to aircraft ≤55,000 lb MTOW and a placard requirement for certain STC‑converted aircraft (Requirement 2b) — changes permissible usage and requires cockpit placarding for some operators.","Inspection method allows 'approved equivalent' (Requirement 1) — introduces regulator discretion over acceptable methods.","Effective and compliance timing specified (Compliance) — short lead time for initial inspections creates scheduling pressure."],"plain_english_summary":"This Airworthiness Directive requires operators of Convair Model 340 and 440 aeroplanes (including those converted to turboprop power) to inspect main landing‑gear cylinders (P/N 528002 or 528402) using magnetic particle, dye penetrant or an approved equivalent, and to repair (FAA‑approved) or replace any cracked cylinder before further flight. It sets short initial and 1,000‑hour recurring inspection intervals, limits reworked cylinders to aircraft with MTOW ≤55,000 lb, and requires placards/records where applicable; the stated purpose is to detect cracks that could cause landing‑gear failure."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with focused scope on specific landing gear components for specific aircraft models. The scope remains tightly constrained to safety-critical inspection requirements for the identified part numbers, with no evidence of scope creep beyond the original safety purpose."},"complexity_factors":["Multiple nested conditional requirements (Requirements 1-5 with cross-references between them)","Specific part number limitations (528002 or 528402) requiring technical documentation cross-checking","Dual-path compliance depending on inspection results (crack detected vs. no crack detected)","Weight restriction and placard requirement triggered only for specific aircraft configurations (Model 580 conversions previously approved for >55,000 lbs)","Variable inspection intervals based on accumulated flight hours (14,000/15,000 hour thresholds)","Reference to external FAA AD (71-02-03 Amdt 39-1145) for additional context","Multiple compliance deadlines (initial 50-hour window, before further flight, recurring 1,000-hour intervals, and 15,000-hour cap)"],"plain_english_summary":"This AD mandates recurring non‑destructive inspections (magnetic particle or dye‑penetrant) of specified main landing‑gear cylinders on Convair 340/440/580 aircraft to detect fatigue cracks and require repair or replacement of cracked parts.  \n\nIf repaired, operators face a reduced takeoff‑weight limit and a cockpit placard for some turboprop conversions. The rule protects against landing‑gear collapse by catching cracks before they cause catastrophic failure and applies to all owners/operators of the affected vintage Convair models."}},"importantCases":[],"_links":{"self":"/api/acts/ad-convair-10-main-landing-gear-cylinders","history":"/api/acts/ad-convair-10-main-landing-gear-cylinders/history","analysis":"/api/acts/ad-convair-10-main-landing-gear-cylinders/analysis","conflicts":"/api/acts/ad-convair-10-main-landing-gear-cylinders/conflicts","importantCases":"/api/acts/ad-convair-10-main-landing-gear-cylinders/important-cases","documents":"/api/acts/ad-convair-10-main-landing-gear-cylinders/documents"}}