{"id":"F2006B06618","name":"AD/ROBIN/20 - Main Gear Torque Link Attachment","slug":"ad-robin-20-main-gear-torque-link-attachment","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":48476,"registerId":"commonwealth-F2006B06618-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/ROBIN/20 - Main Gear Torque Link Attachment","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)  Robin Aviation Series Aeroplanes\n\n \n\nAD/ROBIN/20 Main Gear Torque Link Attachment 13/94\n\nApplicability: Model HR100/250TR and HR100/285TR.\n\n \n\nRequirement: Action in accordance with Avions Pierre Robin Service Bulletin 134.\n\n \n\nNote: DGAC AD 94-129(A) refers.\n\n \n\nCompliance: Unless already accomplished, within 25 hours time in service after 8 December 1994, and thereafter at intervals as specified in the Requirement Document.\n\n \n\nBackground: The DGAC requires an inspection in response to field reports of cracks on the strut torque link welded attachment points.\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":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive addressing a specific mechanical defect in specific aircraft models. It has not expanded beyond its original purpose of mandating inspections for cracked torque link attachments."},"complexity_factors":["Single, specific aircraft model applicability (2 models only)","No defined terms section - uses plain language","Single compliance action (follow the service bulletin)","No cross-references to other legislation beyond a note about the French AD","Clear, unconditional requirement with simple time-based trigger","Total length: approximately 150 words"],"plain_english_summary":"This is an **Airworthiness Directive** (a mandatory safety order) issued by Australia's Civil Aviation Safety Authority for specific Robin Aviation aeroplanes.\n\n**What it does:**\n- Requires owners/operators of **HR100/250TR and HR100/285TR model aircraft** to inspect the main landing gear torque link attachment points for cracks\n- The inspection must follow **Service Bulletin 134** from the manufacturer (Avions Pierre Robin)\n\n**Who it affects:**\n- Owners and operators of these specific Robin aircraft models\n- Maintenance organisations servicing these aircraft\n\n**Why it matters:**\n- **Safety-critical:** Cracks in the torque link attachment could lead to landing gear failure\n- The French aviation authority (DGAC) mandated this after receiving field reports of actual cracks appearing in service\n- Non-compliance means the aircraft cannot legally fly\n\n**Key deadlines:**\n- First inspection required within **25 flight hours** after 8 December 1994\n- Ongoing inspections required at intervals set by the manufacturer's service bulletin"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive is narrowly targeted: it applies only to two Robin aircraft models and requires inspections and corrective actions as set out in Avions Pierre Robin Service Bulletin 134. The stated purpose (addressing reported cracks at torque‑link welded attachment points) matches the actions required (an inspection regime and follow-up) and the AD does not expand the technical scope beyond those aircraft and that structural area. (Applicability; Requirement; Background)"},"complexity_factors":["Narrow applicability to two specific aircraft models (Applicability)","Dependence on an external document (Avions Pierre Robin Service Bulletin 134) for technical detail and recurring intervals (Requirement)","Short initial compliance window (25 hours time in service after 8 December 1994) requiring rapid scheduling (Compliance)","Technical nature of the inspection (welded attachment points on main‑gear torque link) requiring qualified maintenance personnel (Background; Requirement)","Lack of specified recurring intervals within the AD itself (Compliance) — intervals are in the Requirement Document, creating reliance on an external source"],"plain_english_summary":"This AD requires owners/operators of Robin HR100/250TR and HR100/285TR aeroplanes to carry out the inspection and any corrective work specified in Avions Pierre Robin Service Bulletin 134 (initially within 25 hours TIS after 8 December 1994, then at the recurring intervals the Service Bulletin sets) because of reported cracks at the main‑gear strut torque‑link welded attachments.\n\nIt affects those owners/operators, who must schedule the inspections/repairs and bear the associated downtime, labour and parts costs."}},"importantCases":[],"_links":{"self":"/api/acts/ad-robin-20-main-gear-torque-link-attachment","history":"/api/acts/ad-robin-20-main-gear-torque-link-attachment/history","analysis":"/api/acts/ad-robin-20-main-gear-torque-link-attachment/analysis","conflicts":"/api/acts/ad-robin-20-main-gear-torque-link-attachment/conflicts","importantCases":"/api/acts/ad-robin-20-main-gear-torque-link-attachment/important-cases","documents":"/api/acts/ad-robin-20-main-gear-torque-link-attachment/documents"}}