{"id":"F2008L02968","name":"AD/OH-58/4 - Tail Rotor Blade Skin Surface","slug":"ad-oh-58-4-tail-rotor-blade-skin-surface","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74938,"registerId":"commonwealth-F2008L02968-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-58/4 | Tail Rotor Blade Skin Surface | 9/2008 |\n| ---------- | ----------------------------- | ------ |\n\n| Applicability: | Model OH-58A (Bell 206A-1) series helicopters, including all certificated versions; with tail rotor blades part number 206-010-750-005 and -007, installed.                                                                                                                                                                                                                                                                                                                                                                                                                       |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Perform a visual inspection for chordwise cracks in the tail rotor blade skin surfaces in the area between Blade Station 7.1 and 11.1, using a 3x or higher magnifying glass (Blade Station 0 is the centre of the tail rotor yoke).If cracking is detected during any inspection, before further flight, replace affected blade(s).2. Tail rotor blades with 450 hours or more total time in service must be removed from service.3. Tail rotor blades with less than 450 hours total time in service must be removed from service.Note: FAA AD 80-17-05 Amdt 39-3875 refers. |\n| Compliance:    | 1. Before the first flight of each day; until blade replacement per Requirement2 or 3.2. Within the next 50 hours time in service, unless already accomplished.3. Upon the accumulation of 500 hours total time in service.                                                                                                                                                                                                                                                                                                                                                       |\n|                | This Airworthiness Directive becomes effective on 28 August 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n| Background:    | The FAA requires certain actions to prevent failure of the tail rotor blades due to fatigue cracking.                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n14 July 2008","sortOrder":0},{"sectionNumber":"AD/OH-58/4","sectionType":"part","heading":"AD/OH-58/4","content":"## AD/OH-58/4","sortOrder":1},{"sectionNumber":"Tail Rotor Blade Skin Surface","sectionType":"part","heading":"Tail Rotor Blade Skin Surface","content":"## Tail Rotor Blade Skin Surface","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 is a standard, narrow Airworthiness Directive addressing a specific safety defect in specific helicopter components. The scope remains tightly focused on tail rotor blade fatigue cracking in Bell OH-58A series helicopters, consistent with the original purpose of ADs to address identified unsafe conditions in particular aircraft types."},"complexity_factors":["Single, specific technical subject matter (tail rotor blade inspection)","Only 2 defined part numbers in applicability","Three straightforward compliance deadlines with clear triggers (daily, 50 hours, 500 hours)","Minimal cross-referencing (single reference to FAA AD 80-17-05)","No nested exceptions or conditional logic — requirements apply uniformly to affected aircraft","Short document length (approximately 200 words of substantive content)"],"plain_english_summary":"This AD requires owners/operators of Bell OH-58A (Bell 206A-1 series) helicopters fitted with tail rotor blades P/N 206-010-750-005 or -007 to perform daily 3x visual inspections for fatigue cracks and to replace any cracked blade before next flight.  \n\nBlades must be retired: within 50 flight hours if already ≥450 hours, or at 500 total hours if under 450. The rule prevents blade failure and potential loss of control."},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"Scope is limited to Bell OH-58A (206A-1) helicopters fitted with tail rotor blades P/N 206-010-750-005 and -007 and mandates inspections and retirement of those blades. The instrument does not, on its face, expand or narrow applicability beyond that statement. (See 'Applicability' and 'Requirement' entries.) Note: the text contains inconsistent hour thresholds which affect implementation clarity but do not clearly change the stated scope."},"complexity_factors":["Multiple distinct compliance timings: daily pre-flight inspection requirement plus additional removal or action deadlines (Compliance: 1–3).","Apparent drafting inconsistency on retirement hours (Requirements refer to removal at 450 hours and/or 500 hours; Compliance lists 50‑hour and 500‑hour triggers), increasing interpretive risk.","Narrow applicability tied to specific part numbers (Applicability), requiring operators to verify blade P/Ns before applying the AD.","Operational impact: mandatory replacement before further flight if cracks are found (Requirement 1), which can ground an aircraft immediately and impose replacement costs.","Technical inspection method specified (3x magnifying glass) creates a minimal equipment standard but requires personnel time and training (Requirement 1).","Cross-reference to FAA AD 80-17-05 creates an external dependency for background and potentially for interpretation.","Document formatting/repetition and partial ambiguity in numbered Requirements/Compliance sections make administrative compliance and enforcement less straightforward."],"plain_english_summary":"Mandates daily visual inspections of the tail-rotor blade skin between blade stations 7.1 and 11.1 on Bell OH-58A (206A-1) helicopters fitted with tail rotor blades P/N 206-010-750-005 or -007, and requires removal of blades at specified hours limits. The AD’s stated purpose is to prevent fatigue cracking and tail-rotor failure; operators must inspect with a 3x (or greater) magnifier, replace cracked blades before further flight, and retire blades when the directive’s hour thresholds are reached."}},"importantCases":[],"_links":{"self":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface","history":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface/history","analysis":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface/analysis","conflicts":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface/conflicts","importantCases":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface/important-cases","documents":"/api/acts/ad-oh-58-4-tail-rotor-blade-skin-surface/documents"}}