{"id":"F2006L01095","name":"AD/CONVAIR/12 - Main Landing Gear Piston/Axle Assemblies","slug":"ad-convair-12-main-landing-gear-piston-axle-assemblies","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":58439,"registerId":"commonwealth-F2006L01095-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/12 | Main Landing Gear Piston/Axle Assemblies | 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 main landing gear Piston/Axle Assemblies part number 528039 with 10,000 or more hours time in service for crack indications in the fillet radius area between the axle and the outboard face of both brake attachment flanges, by dye penetrant inspection procedures; in accordance with Part I of General Dynamics 640 (340D) Service Bulletin (SB) No.32-3, dated 31 October 1969, or by magnetic particle inspection procedure.2. If no cracks are detected, repeat the Requirement 1 inspection.The Requirement 2. 1,000 hour inspection interval may be terminated when the inspection area identified above has been reworked in accordance with paragraphs C, D, and E of Part II of SB 32-3.Subsequent to the accumulation of 2,000 hours time in service after the rework, and before 2,500 hours time in service after rework, perform a Requirement 1 inspection for cracks. If no cracks are detected during this inspection, further inspections are not required by this Directive.3. If cracks are detected during any inspection, accomplish the following:a. Rework the cracked area in accordance with all the provisions of Part II of SB 32-3, provided the axle wall thickness remaining after rework is a minimum of 0.30-inches. After rework, repeat the Requirement 1 inspection.b. If cracks are detected which require removal of material that would leave a minimum axle wall thickness of less than 0.30-inches, replace the axle.Note: FAA AD 70-12-07 Amdt 39-1004 refers. |\n| Compliance: | 1. Unless the initial inspection is already accomplished, within 150 hours time in service after 11 May 2006, unless already accomplished within the last 850 hours time in service.2. At intervals not to exceed 1,000 hours time in service. |\n\n| | 3. Before further flight.3.a. At intervals not to exceed 2,500 hours time in service. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------- |\n| | This Airworthiness Directive becomes effective on 11 May 2006. |\n| Background: | The FAA requires inspection of the main landing gear axles to detect cracks. Undetected cracking could result in failure of the axle. |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n29 March 2006","sortOrder":0},{"sectionNumber":"AD/CONVAIR/12","sectionType":"part","heading":"AD/CONVAIR/12","content":"## AD/CONVAIR/12","sortOrder":1},{"sectionNumber":"Main Landing Gear Piston/Axle Assemblies","sectionType":"part","heading":"Main Landing Gear Piston/Axle Assemblies","content":"## Main Landing Gear Piston/Axle Assemblies","sortOrder":2},{"sectionNumber":"5/2006","sectionType":"part","heading":"5/2006","content":"## 5/2006","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard, targeted Airworthiness Directive addressing a specific safety-of-flight issue with a defined aircraft fleet. The scope remains tightly focused on the identified landing gear defect in Convair 340/440 series aircraft, consistent with the original purpose of preventing axle failure."},"complexity_factors":["Multiple conditional pathways: initial inspection, recurring inspection, repair-with-continuation, repair-with-termination, and replacement scenarios","Cross-reference to external technical document (General Dynamics Service Bulletin 32-3) which contains the actual inspection and repair procedures — the AD doesn't stand alone","Precise engineering thresholds (0.30-inch minimum wall thickness, 10,000 hours time-in-service trigger, specific part number 528039)","Layered compliance deadlines: initial 150-hour window, then 1,000-hour intervals, then 2,000-2,500 hour window post-rework","Reference to corresponding FAA AD (70-12-07) indicating harmonised but separate regulatory requirements","Nested exceptions: the 1,000-hour recurring inspection can be terminated under specific rework conditions, creating a conditional exit from the compliance loop"],"plain_english_summary":"This CASA Airworthiness Directive requires operators of Convair 340/440 (including turboprop conversions) in Australia to inspect main landing‑gear axle/piston assemblies for cracking and to repair or replace defects to maintain safe wall thickness. \n\nIt matters because axle crack failure can cause catastrophic landing collapse; the AD enforces timed inspections and corrective action to prevent accidents (effective 11 May 2006)."},"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":6,"scope_assessment":{"changed":false,"description":"Applicability is confined to Model 340 and 440 aeroplanes (including turboprop conversions) and to piston/axle assemblies part number 528039. The directive imposes inspection, rework and replacement obligations but does not expand the class of affected aircraft or parts beyond the stated applicability; it implements inspection and corrective‑action rules consistent with Service Bulletin 32‑3 and the referenced FAA AD."},"complexity_factors":["Multiple conditional inspection intervals (initial within 150 hours unless done in last 850 hours; repeat every 1,000 hours; termination and special checks tied to rework and 2,000–2,500 hour marks) — (Compliance; Requirement 2).","Technical inspection methods mandated (dye penetrant or magnetic particle) and specific inspection area (fillet radius between axle and outboard face of brake flanges) — (Requirement 1).","Dependency on an external maintenance document for acceptable rework procedures (Part II of Service Bulletin 32‑3) and on Part I for inspection procedures — (Requirement 1; Requirement 3a).","Clear material‑removal acceptance criterion (minimum axle wall thickness 0.30 inches) that determines whether rework or axle replacement is required — (Requirement 3a–b).","Immediate 'before further flight' obligation if cracks are found, creating an operational grounding/compliance decision point — (Requirement 3).","Limited applicability to specific models and part number (`528039`), requiring operators to track affected serials and conversions — (Applicability).","Cross‑reference to FAA AD 70‑12‑07 and dated Service Bulletin creates traceability and potential need to reconcile differing documents — (Note; Requirement references).","Formatting and sequencing in the instrument (numbering and timing conditions) add interpretive complexity for maintenance planners and regulators."],"plain_english_summary":"Requires regular inspections and, where needed, rework or replacement of main landing gear piston/axle assemblies (part `528039`) on Convair/General Dynamics Model 340 and 440 aeroplanes, including turboprop conversions, to detect and fix cracks in the axle fillet radius. Owners/operators must use dye‑penetrant or magnetic particle inspections, follow Service Bulletin 32‑3 for rework, and replace axles if wall thickness would fall below 0.30 inches. The instrument sets short‑term and recurring inspection intervals and immediate action if cracks are found."}},"importantCases":[],"_links":{"self":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies","history":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies/history","analysis":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies/analysis","conflicts":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies/conflicts","importantCases":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies/important-cases","documents":"/api/acts/ad-convair-12-main-landing-gear-piston-axle-assemblies/documents"}}