{"id":"F2006B03280","name":"AD/B767/10 - Main Landing Gear Shock Strut","slug":"ad-b767-10-main-landing-gear-shock-strut","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"repealed","isInForce":false,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42717,"registerId":"commonwealth-F2006B03280-current","compilationNumber":null,"startDate":"2026-04-01","status":"Repealed","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B767/10 - Main Landing Gear Shock Strut","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)  Boeing 767 Series Aeroplanes\n\n \n\nAD/B767/10 Main Landing Gear Shock Strut 6/86\n\nApplicability: All models with line positions 2 to 64 inclusive. Requirement: Action in accordance with Boeing SB No. 767-32-0045. Compliance:              Before exceeding 18,000 landings.\n\nBackground: A fatigue fracture has occurred on the fatigue test. The crack started at a lubrication hole where the upper torsion link is attached to the outer cylinder. This AD requires an inspection of the critical area, and enlargement of the hole edge radius if required to reduce the susceptibility to cracking. It has been raised because SB 767-32-0045 has been identified by the 767 Maintenance Planning Document as having flight safety implications.\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":1728},"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This directive remains tightly scoped to its original purpose of addressing a specific fatigue crack risk identified in early-production Boeing 767 main landing gear assemblies. It does not expand regulatory reach beyond the identified safety defect or applicable aircraft serial range."},"complexity_factors":["Single mechanical component targeted (main landing gear shock strut)","Narrow applicability criteria limited to specific production line positions (2-64)","Single external technical reference (Boeing SB 767-32-0045)","Clear quantitative compliance threshold (18,000 landings)","Binary action path (inspect and remediate only if required)"],"plain_english_summary":"This Airworthiness Directive requires operators of Boeing 767s built at line positions 2–64 to inspect and, if needed, repair a fatigue-prone area on the main landing gear where the upper torsion link attaches to the outer cylinder. Testing showed cracks can form around a lubrication hole, risking landing gear failure.\n\nOperators must follow Boeing Service Bulletin 767-32-0045 to inspect and smooth/enlarge the hole radius; work is required before the airplane exceeds 18,000 total landings."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b767-10-main-landing-gear-shock-strut","history":"/api/acts/ad-b767-10-main-landing-gear-shock-strut/history","analysis":"/api/acts/ad-b767-10-main-landing-gear-shock-strut/analysis","conflicts":"/api/acts/ad-b767-10-main-landing-gear-shock-strut/conflicts","importantCases":"/api/acts/ad-b767-10-main-landing-gear-shock-strut/important-cases","documents":"/api/acts/ad-b767-10-main-landing-gear-shock-strut/documents"}}