{"id":"F2006B11397","name":"AD/MU-2/67 - Fuselage Frame","slug":"ad-mu-2-67-fuselage-frame","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":57298,"registerId":"commonwealth-F2006B11397-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/MU-2/67 - Fuselage Frame","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)  Mitsubishi MU-2 Series Aeroplanes\n\n \n\nAD/MU-2/67 Fuselage Frame 8/99\n\nApplicability: Model MU-2B-30, -35, and -36 aircraft, with serial numbers 501 through 696; except 652 and 661.\n\n \n\nRequirement: Inspect the fuselage frame in accordance with Mitsubishi Heavy Industries Service Bulletin 209B.\n\n \n\nNote: JCAB AD TCD-5030-99 refers.\n\n \n\nCompliance: Within 200 hours time in service after 12 August 1999; thereafter at intervals not to exceed 2,000 hours time in service.\n\n \n\nThis Airworthiness Directive becomes effective on 12 August 1999.\n\n \n\nBackground: The manufacturer received field reports of cracking around the splice screw holes of the fuselage frame at STA 4610. This Directive requires an inspection of the fuselage frames at STA 4610, 4850, and 5605.\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":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive confines inspections to the specific MU-2 models and serial numbers identified and to frames at STA 4610, 4850 and 5605, matching the manufacturer’s field reports of cracking. It prescribes inspection timing and method by reference to Service Bulletin 209B and does not expand the set of affected parts or aircraft beyond those reports."},"complexity_factors":["Narrow applicability by model and specific serial-number range with two serials excluded (precision in applicability increases administrative checks).","Mandatory action references an external document (Mitsubishi Heavy Industries Service Bulletin 209B) for inspection procedure (dependency on another instrument for technical detail).","Inspections required at three specific fuselage stations (STA 4610, 4850, 5605), requiring maintenance access and potential disassembly.","Time-based compliance: initial short-term window (200 hours after 12 Aug 1999) then recurring 2,000‑hour intervals (scheduling and recordkeeping burden).","Cross-reference to a foreign authority advisory (JCAB AD TCD-5030-99) adds context but may require checking multiple sources.","Operational impact: inspections create aircraft downtime and direct maintenance costs for owners/operators."],"plain_english_summary":"This Airworthiness Directive requires operators of Mitsubishi MU-2B-30, -35 and -36 aeroplanes (serial numbers 501–696, except 652 and 661) to inspect fuselage frames at STA 4610, 4850 and 5605 in accordance with Mitsubishi Heavy Industries Service Bulletin 209B. It responds to field reports of cracking around splice screw holes. Owners/operators must carry out the first inspection within 200 hours time in service after 12 August 1999 and then at intervals not exceeding 2,000 hours; they bear the inspection cost and arrange maintenance to comply."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, narrowly-targeted airworthiness directive addressing a specific structural defect in specific aircraft models. The scope remains precisely limited to the identified safety issue without expansion into broader operational or regulatory matters."},"complexity_factors":["Very short document (approximately 200 words)","Only 4 defined elements: specific aircraft models (MU-2B-30, -35, -36), serial number range (501-696), two excluded serial numbers (652, 661), and three structural station references (STA 4610, 4850, 5605)","Single straightforward requirement with clear compliance timeline","No cross-references to other legislation or complex conditional logic","One external reference to manufacturer service bulletin (incorporated by reference)","Simple exception structure (serial number range minus two specific exclusions)"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections of the fuselage frame for cracking around screw holes on Mitsubishi MU-2B-30/‑35/‑36 aeroplanes (serials 501–696, excluding 652 and 661) after reports of structural cracking that could threaten airworthiness.\n\nInspections must follow Mitsubishi Heavy Industries Service Bulletin 209B: first within 200 flight hours after 12 August 1999, then every 2,000 flight hours thereafter."}},"importantCases":[],"_links":{"self":"/api/acts/ad-mu-2-67-fuselage-frame","history":"/api/acts/ad-mu-2-67-fuselage-frame/history","analysis":"/api/acts/ad-mu-2-67-fuselage-frame/analysis","conflicts":"/api/acts/ad-mu-2-67-fuselage-frame/conflicts","importantCases":"/api/acts/ad-mu-2-67-fuselage-frame/important-cases","documents":"/api/acts/ad-mu-2-67-fuselage-frame/documents"}}