{"id":"F2006B06772","name":"AD/SA-TP/23 Amdt 1 - Structural Components Fatigue Lives","slug":"ad-sa-tp-23-amdt-1-structural-components-fatigue-lives","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"repealed","isInForce":false,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":114610,"registerId":"commonwealth-F2006B06772-current","compilationNumber":null,"startDate":"2026-04-03","status":"Repealed","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/SA-TP/23 Amdt 1 - Structural Components Fatigue Lives","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  British Aerospace (Scottish Aviation) Twin Pioneer Series Aeroplanes\n\n \n\n# AD/SA-TP/23\n\nAmdt 1\n\nApplicability: All models.\n\n# Structural Components Fatigue Lives NK\n\n \n\nDocument: Scottish Aviation TNS No. 33, Issue 2.\n\n \n\nCompliance: As detailed in Appendix N of the requirement document.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"kimi_summary":{"_metrics":{"model":"kimi-k2.5","source":"moonshot-batch","completionTokens":2101},"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"As Amendment 1, this instrument appears to maintain the original scope of regulating fatigue life limits for Twin Pioneer structural components. The amendment likely updates the referenced technical document issue number or compliance dates rather than expanding coverage to new aircraft types or unrelated safety systems."},"complexity_factors":["Extremely short instrument (approximately 100 words) with no internal definitions","Single, unambiguous compliance obligation referencing external technical standard","Narrow applicability (only one specific aircraft type)","No conditional logic, exceptions, or cross-references to other legislation"],"plain_english_summary":"**What this is:** A mandatory safety rule (called an Airworthiness Directive) for anyone who owns, operates, or maintains **British Aerospace (Scottish Aviation) Twin Pioneer** aircraft—a type of vintage twin-engine utility plane.\n\n**What it requires:** Operators must follow a specific technical manual (**Scottish Aviation TNS No. 33, Issue 2, Appendix N**) that sets **fatigue life limits** for structural components. **Fatigue life** refers to how many flights or hours a metal part can safely endure before stress cracks become likely. Once a part reaches its limit, it must be replaced or overhauled to prevent structural failure.\n\n**Who must comply:** All operators of any Twin Pioneer model.\n\n**Why it matters:** Metal fatigue is a leading cause of catastrophic airframe failures. This rule prevents accidents by forcing operators to retire or inspect aging structural parts before they break."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives","history":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives/history","analysis":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives/analysis","conflicts":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives/conflicts","importantCases":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives/important-cases","documents":"/api/acts/ad-sa-tp-23-amdt-1-structural-components-fatigue-lives/documents"}}