{"id":"F2008L02967","name":"AD/OH-58/3 - Main Rotor Blade Pitch Link Tubes","slug":"ad-oh-58-3-main-rotor-blade-pitch-link-tubes","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74936,"registerId":"commonwealth-F2008L02967-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Bell OH-58A (206A-1) Series Helicopters","sectionType":"division","heading":"Bell OH-58A (206A-1) Series Helicopters","content":"### Bell OH-58A (206A-1) Series Helicopters\n\n| AD/OH-58/3 | Main Rotor Blade Pitch Link Tubes | 9/2008 |\n| ---------- | --------------------------------- | ------ |\n\n| Applicability: | Model OH-58A (Bell 206A-1) series helicopters, including all certificated versions; with main rotor blade pitch link assemblies part number 206-010-330 and206-010-342, as applicable, installed. |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | To detect and prevent possible corrosion and cracks in the main rotor blade pitch link tubes part number 206-010-330, all dash numbers, accomplish the following:Inspect the ends and outside diameter surface of each tube for corrosion and cracking, using a 3x or higher magnifying glass.Replace corroded or cracked tubes detected during any inspection before further flight.If tubes are replaced or adjusted, track the main rotor blades in accordance with the appropriate maintenance and overhaul information manual.Apply corrosion preventative compound MIL-C-16173 Grade 2, or equivalent, to the exposed threads of the upper and lower clevises, the ends of each tube, and the mating faces of the locks and nuts and the top surfaces of the nuts after the nuts are properly torqued on each pitch link assembly.Note 1: Bell Helicopter Service Bulletin 206-04-2-73-1 original issue, or later FAA approved revision, refers.Note 2: FAA AD 73-19-09 Amdt 39-1718 refers. |\n| Compliance: | Unless the initial inspection is already accomplished, within the next 25 hours time in service; and thereafter at intervals not to exceed 50 hours time in service. |\n| | This Airworthiness Directive becomes effective on 28 August 2008. |\n| Background: | Corrosion and cracking has been found in the main rotor blade pitch link tubes. |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n14 July 2008","sortOrder":0},{"sectionNumber":"AD/OH-58/3","sectionType":"part","heading":"AD/OH-58/3","content":"## AD/OH-58/3","sortOrder":1},{"sectionNumber":"Main Rotor Blade Pitch Link Tubes","sectionType":"part","heading":"Main Rotor Blade Pitch Link Tubes","content":"## Main Rotor Blade Pitch Link Tubes","sortOrder":2},{"sectionNumber":"9/2008","sectionType":"part","heading":"9/2008","content":"## 9/2008","sortOrder":3}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific safety defect in specific helicopter models. It has not expanded beyond its original purpose of preventing pitch link tube failures."},"complexity_factors":["Single, discrete safety issue addressed (corrosion in specific part)","Only 2 applicable part numbers specified","Straightforward compliance timeline (25 hours initial, 50 hours recurring)","Simple inspection method (visual with magnifying glass)","Clear pass/fail criteria (replace if corroded or cracked)","No nested exceptions, conditional clauses, or cross-references to other legislation","References only technical documents (service bulletin, FAA AD) for guidance, not for legal operation"],"plain_english_summary":"This mandatory CASA Airworthiness Directive requires owners/operators of Bell OH-58A (206A-1) helicopters with pitch link P/Ns 206-010-330 or 206-010-342 to inspect main rotor blade pitch link tubes for corrosion and cracks, replace any defective tubes before flight, and apply anti‑rust treatment after maintenance.\n\nIt matters because pitch link failure can cause loss of blade pitch control and catastrophic loss of aircraft control; the AD sets short, recurring inspection intervals to catch problems early."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD is narrowly focused on detecting and preventing corrosion/cracking in specified main rotor pitch link tubes for a defined set of helicopters and prescribes inspections, replacement when defects are found, corrosion prevention treatment, and blade tracking. This appears consistent with the stated purpose (addressing found corrosion and cracking) and does not broaden the regulation beyond that safety objective."},"complexity_factors":["Single affected helicopter model family (OH-58A / Bell 206A-1) and limited part numbers (206-010-330 and 206-010-342) — reduces scope complexity","One primary inspection method (visual with 3x magnifying glass) and clear pass/fail action (replace if corroded/cracked)","Simple compliance timeline (initial within 25 hours TIS, then every 50 hours TIS)","Cross-references to external documents: Bell Service Bulletin 206-04-2-73-1 and FAA AD 73-19-09, and to the maintenance/overhaul manual — introduces dependency on external procedural detail","A small number of discrete required actions (inspect, replace if defective, apply corrosion preventive, track blades after adjustment) — low procedural branching","No extensive definitions, nested exceptions, or conditional legal tests beyond the visual inspection outcome"],"plain_english_summary":"**What this instrument does**\n\n- This Airworthiness Directive (AD) requires owners/operators of certain Bell OH-58A (Bell 206A-1) series helicopters to inspect the main rotor blade pitch link tubes (part number 206-010-330, all dash numbers) for corrosion and cracking, and to take corrective action if defects are found. (Requirement; Applicability)\n\n**Who it affects**\n\n- Owners, operators and maintenance organisations responsible for Bell OH-58A (206A-1) series helicopters that have main rotor blade pitch link assemblies with part numbers 206-010-330 or 206-010-342 installed. If your helicopter does not have those parts installed, this AD does not apply. (Applicability)\n\n**What you must do (mechanics of the rule)**\n\n- Inspect the ends and the outside diameter of each pitch link tube using at least a 3x magnifying glass. (Requirement)\n- If any tube is found to be corroded or cracked, it must be replaced before the helicopter flies again. (Requirement)\n- If tubes are replaced or adjusted, you must re-track the main rotor blades following the procedures in the helicopter maintenance/overhaul information manual. (Requirement)\n- After any replacement or whenever exposed threads/faces are present, apply a corrosion preventative compound (MIL-C-16173 Grade 2 or equivalent) to specified areas: exposed threads of upper and lower clevises, the ends of each tube, mating faces of the locks and nuts, and the top surfaces of the nuts after proper torquing. (Requirement)\n\n**When you must do it**\n\n- If you have not already done the initial inspection, do it within the next 25 hours time-in-service. After that, inspect at intervals not exceeding 50 hours time-in-service. (Compliance)\n\n**Cross-references and technical detail**\n\n- The AD refers to Bell Helicopter Service Bulletin 206-04-2-73-1 (original issue or later FAA-approved revision) and to FAA AD 73-19-09 Amdt 39-1718 for related guidance or procedures. It also directs the use of the appropriate maintenance/overhaul manual for blade tracking procedures. (Requirement, Notes)\n\n**Why it matters**\n\n- Corrosion and cracking have been found in these pitch link tubes. Pitch links connect rotor blades to the control structure; failure could affect rotor control. The AD is a mandatory safety action to detect and remove degraded components before they cause in-flight failure. (Background)\n\n**Who pays and what changes in behaviour**\n\n- Operators bear the direct costs: labour to perform inspections at the specified intervals, materials (corrosion preventative compound), and the cost of replacement tubes where defects are found. Operators also incur aircraft downtime while inspections and replacements are performed. Maintenance teams will need to schedule recurring inspections every 50 flight hours and follow the torque/track procedures required after replacement or adjustment. (Requirement; Compliance)\n\n**Implementation risks and practical trade-offs**\n\n- The inspection method specified is a visual inspection with a 3x magnifying glass; this is simple and quick but may not detect subsurface or very fine cracks that require higher-resolution non-destructive testing (NDT). The AD relies on replacement when visible corrosion/cracking is detected rather than requiring blanket replacement of parts. (Requirement)\n- The AD cross-references a service bulletin and the maintenance/overhaul manual for procedural detail; the quality and clarity of those documents will affect compliance ease and consistency. (Notes)\n- Potential operational impacts include recurring inspection labour and possible parts lead times if multiple replacements are required; these translate into direct costs and aircraft availability effects. (Compliance; Requirement)\n\n**Source claims vs mechanics**\n\n- The AD states its purpose is to \"detect and prevent possible corrosion and cracks\" in the specified pitch link tubes (Background; Requirement). Mechanically, it imposes recurring visual inspections, mandatory replacement for detected defects, corrosion-preventative treatment, and blade tracking after any replacement/adjustment. Those are the concrete measures that produce the safety outcome the AD claims. (Background; Requirement)\n\n**Key documentary facts**\n\n- Effective date stated: 28 August 2008. The AD was issued because corrosion and cracking had been found in the subject parts. (Compliance; Background)"}},"importantCases":[],"_links":{"self":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes","history":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes/history","analysis":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes/analysis","conflicts":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes/conflicts","importantCases":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes/important-cases","documents":"/api/acts/ad-oh-58-3-main-rotor-blade-pitch-link-tubes/documents"}}