{"id":"F2018L01159","name":"AD/STINSON 108/2 Stabilizer Leading Edge Attachment - Inspection","slug":"ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":97845,"registerId":"commonwealth-F2018L01159-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Univair Aircraft (Stinson) 108 Series Ae","sectionType":"part","heading":"Univair Aircraft (Stinson) 108 Series Aeroplanes","content":"# Univair Aircraft (Stinson) 108 Series Aeroplanes\n\n| AD/STINSON 108/2 | Stabilizer Leading EdgeAttachment - Inspection | 17/2018 |\n| ---------------- | ---------------------------------------------- | ------- |\n\n| Applicability: | Univair Aircraft Corporation Stinson 108 series aircraft, serial numbers 1 through 3500.                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Inspect stabilizer leading edge attachment in accordance with the instructions in Stinson Service Bulletin 254 dated 5 September 1947, as in force at the commencement of this AD.2. If during the Requirement 1 inspection, fatigue cracks of the stabilizer leading edge attachment are found, reinforcements to the stabilizer fitting must be added in accordance with the instructions in Stinson Service Bulletin 254 dated 5 September 1947, as in force at the commencement of this AD.Note: FAA AD 47-50-12 refers. |\n| Compliance:    | 1. Within 30 days after the commencement date of this AD, unless previously accomplished, and thereafter at intervals not to exceed 100 hours’ time in service.2. Before further flight.                                                                                                                                                                                                                                                                                                                                        |\n|                | This AD commences on 31 August 2018.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background:    | A review of the Australian Aircraft Register found that this aircraft type has been registered in Australia since 1987. There are currently 12 aircraft of this type on the register with the majority having been registered in 1994/95.This AD is issued detect and correct fatigue cracking of the stabilizer leading edge attachment.                                                                                                                                                                                       |\n\n![](image.001.jpeg)\n\nPieter van Dijk  \nDelegate of the Civil Aviation Safety Authority\n\n21 August 2018","sortOrder":0},{"sectionNumber":"AD/STINSON 108/2","sectionType":"part","heading":"AD/STINSON 108/2","content":"## AD/STINSON 108/2","sortOrder":1},{"sectionNumber":"Stabilizer Leading EdgeAttachment - Insp","sectionType":"part","heading":"Stabilizer Leading EdgeAttachment - Inspection","content":"## Stabilizer Leading Edge  \nAttachment - Inspection","sortOrder":2},{"sectionNumber":"17/2018","sectionType":"part","heading":"17/2018","content":"## 17/2018","sortOrder":3}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"No — the AD's scope aligns with its stated purpose in the text: to detect and correct fatigue cracking of the stabilizer leading edge attachment on Univair Stinson 108 series aircraft (serial numbers 1–3500). It implements inspections and conditional reinforcements as set out by Service Bulletin 254 and references FAA AD 47-50-12, with explicit timing and a commencement date (31 August 2018)."},"complexity_factors":["Narrow applicability to a fixed serial-number range (Applicability).","Mandatory inspection plus conditional repair: inspection required, reinforcement mandatory if cracks found (Requirement).","Prescribed timing: initial inspection within 30 days and recurrent intervals not to exceed 100 hours; immediate compliance before further flight if cracks found (Compliance).","Reliance on an external historical document for technical steps — Stinson Service Bulletin 254 dated 5 September 1947 (Requirement).","Cross-reference to an earlier FAA AD (FAA AD 47-50-12) which may affect interpretation (Requirement).","Small registered fleet in Australia (12 aircraft) but broad serial applicability may affect other operators (Background).","Commencement date specified (31 August 2018), creating a clear enforcement start (Compliance).","Compliance imposes direct costs on owners/operators for inspections and any reinforcements (implicit in Requirement/Compliance)."],"plain_english_summary":"This airworthiness directive requires owners/operators of Univair Stinson 108 series aeroplanes (serials 1–3500) to inspect the stabilizer leading‑edge attachment following Stinson Service Bulletin 254 and to install reinforcements if fatigue cracks are found. Inspections must begin within 30 days and recur at intervals not exceeding 100 hours; any required reinforcements must be fitted before further flight. Owners pay inspection and repair costs; the Civil Aviation Safety Authority (Delegate) enforces the AD (commencement 31 August 2018)."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific structural fatigue issue in a single vintage aircraft type. The scope has not expanded beyond the original safety concern."},"complexity_factors":["Single, specific aircraft type and serial number range (narrow applicability)","Only two main requirements: inspect, and repair if cracked","Clear compliance deadlines (30 days, 100-hour intervals, before flight)","References only one external document (Stinson Service Bulletin 254)","No nested exceptions, conditional logic, or extensive defined terms","Short document (approximately 300 words of substantive content)"],"plain_english_summary":"This AD mandates inspections of the stabilizer leading-edge attachment on Univair (Stinson) 108 series aeroplanes (S/N 1–3500) to detect fatigue cracks that could cause tail failure. Owners/operators must inspect per the referenced 1947 service bulletin—initially within 30 days of 31 Aug 2018 and then every 100 flight hours—and fit reinforcements before further flight if cracks are found.\n\nIt affects 12 vintage aircraft on the Australian register and aims to prevent catastrophic tail assembly failure."}},"importantCases":[],"_links":{"self":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection","history":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection/history","analysis":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection/analysis","conflicts":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection/conflicts","importantCases":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection/important-cases","documents":"/api/acts/ad-stinson-108-2-stabilizer-leading-edge-attachment-inspection/documents"}}