{"id":"F2006B06371","name":"AD/PT6A/8 - Compressor Rear Hub Hardness","slug":"ad-pt6a-8-compressor-rear-hub-hardness","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"repealed","isInForce":false,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":47630,"registerId":"commonwealth-F2006B06371-current","compilationNumber":null,"startDate":"2026-04-02","status":"Repealed","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PT6A/8 - Compressor Rear Hub Hardness","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 - 106 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Pratt and Whitney Canada Turbine Engines - PT6A Series\n\n \n\nAD/PT6A/8 Compressor Rear Hub Hardness 10/85\n\nApplicability: PT6A-6, -6A, -6B, -20 and PT6B-9 which do not include the intent of SB No. 1079 (old No. 119, Rev. 2) or SB No. 1094 (old No. 140, Rev. 3).\n\n \n\nDocument: 1. UACL SB No. 62, Rev. 3;\n\n \n\n2.    UACL SB No. 1035, or\n\n \n\n3.    AD/UAC-T/2B.\n\n \n\nCompliance: Before installation in an aircraft following next reconditioning completed after 21 November 1969.\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":1602},"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This 1985 directive maintains its original narrow technical scope concerning compressor rear hub hardness requirements for specific PT6A engine variants. No evidence of scope expansion beyond the original safety mandate."},"complexity_factors":["Extensive whitespace and formatting artifacts from document conversion","Reference to external technical documents (Service Bulletins) without reproducing their content","Conditional applicability clause excluding engines with prior modifications (SB No. 1079 or 1094)","Specific date-based compliance trigger (post-21 November 1969 reconditioning)"],"plain_english_summary":"This AD requires operators and maintenance organisations of specified Pratt & Whitney Canada PT6A/PT6B turboprop engines to verify the compressor rear hub meets required hardness before the engine can be installed after reconditioning, unless already modified per Service Bulletins 1079 or 1094. \n\nCompliance must follow one of the approved technical documents (UACL Service Bulletin No. 62 Rev 3, No. 1035, or AD/UAC-T/2B). This prevents hub failure and preserves flight safety."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness","history":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness/history","analysis":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness/analysis","conflicts":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness/conflicts","importantCases":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness/important-cases","documents":"/api/acts/ad-pt6a-8-compressor-rear-hub-hardness/documents"}}