{"id":"F2008L00717","name":"AD/TECNAM/6 - Vertical Fin Spar","slug":"ad-tecnam-6-vertical-fin-spar","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":72754,"registerId":"commonwealth-F2008L00717-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"TECNAM P92, P96, and P2002 Series Aeropl","sectionType":"division","heading":"TECNAM P92, P96, and P2002 Series Aeroplanes","content":"### TECNAM P92, P96, and P2002 Series Aeroplanes\n\n| AD/TECNAM/6 | Vertical Fin Spar | 4/2008 |\n| ----------- | ----------------- | ------ |\n\n| Applicability: | Model P92-JS aircraft, serial numbers 013 through 068.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Inspect the vertical fin rear spar in accordance with Costruzioni Aeronautiche TECNAM S.r.l Service Bulletin (SB) 006-CS original issue, or later EASA approved revision. Using a 10x magnifying glass and a light source, inspect the rear spar for loose or missing rivets, cracks and deformation.If cracks or other damage is detected, before further flight, contact the manufacturer for further instructions.If no damage is detected, within 5 days after the inspection, complete the SB inspection report and forward to the manufacturer.Note: EASA AD 2008-0028-E refers. |\n| Compliance:    | Within 25 flight hours or 30 days after 10 April 2008, whichever occurs first. Inspect thereafter at intervals not to exceed 100 flight hours.                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n|                | This Airworthiness Directive becomes effective on 10 April 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n| Background:    | Fatigue cracks have been detected on the rear spar of the vertical fin, and subsequently on the fin front spar. Such cracking, unless detected and corrected, could lead to failure of the vertical fin and loss of control of the aircraft.                                                                                                                                                                                                                                                                                                                                           |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n26 February 2008","sortOrder":0},{"sectionNumber":"AD/TECNAM/6","sectionType":"part","heading":"AD/TECNAM/6","content":"## AD/TECNAM/6","sortOrder":1},{"sectionNumber":"Vertical Fin Spar","sectionType":"part","heading":"Vertical Fin Spar","content":"## Vertical Fin Spar","sortOrder":2},{"sectionNumber":"4/2008","sectionType":"part","heading":"4/2008","content":"## 4/2008","sortOrder":3}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a targeted safety directive addressing a specific airworthiness concern (fatigue cracking in vertical fin spars). The scope remains precisely limited to the identified safety risk and affected aircraft population. No scope creep is evident."},"complexity_factors":["Single, clearly defined applicability (one model, specific serial number range)","Straightforward inspection procedure referencing an external service bulletin","Simple conditional logic: if damage found → stop flying and contact manufacturer; if no damage → submit report within 5 days","Clear compliance timeline with two alternative triggers (flight hours or calendar days)","No nested definitions, no cross-references to other legislation beyond a single note about the corresponding EASA directive","Total length is approximately 200 words of substantive content"],"plain_english_summary":"This AD requires owners/operators of Tecnam P92‑JS aircraft (serials 013–068) to inspect the vertical fin spar for cracks, loose rivets or deformation using a magnifier and light. It’s mandatory: aircraft with cracks must be grounded and the manufacturer notified; clean inspections must be reported. Fatigue cracks in the fin spar could cause in‑flight tail failure, so prompt compliance is legally required to preserve safety."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument applies specifically to P92‑JS aircraft serial numbers 013–068 and prescribes inspection, reporting and repair coordination steps (Applicability; Requirement; Compliance). There is no text indicating expansion beyond that listed applicability, so scope remains as stated in the AD."},"complexity_factors":["Narrow applicability: only Tecnam P92‑JS serial numbers 013–068 (Applicability) reduces scope complexity.","Prescriptive inspection technique: 10× magnifying glass and light specified (Requirement) simplifies implementation.","Short initial compliance window (25 flight hours or 30 days from 10 April 2008) creates scheduling pressure (Compliance).","Recurring inspection interval (every 100 flight hours) requires ongoing compliance and record‑keeping (Compliance).","Mandatory reporting within five days and requirement to contact manufacturer before further flight increase administrative burden and can cause grounding (Requirement; Compliance).","Cross-reference to EASA AD and manufacturer Service Bulletin introduces external-document reliance (Requirement; Note)."],"plain_english_summary":"Requires owners/operators of Tecnam P92‑JS aircraft (serial numbers 013–068) to inspect the vertical fin rear spar with a 10× magnifier and light for loose/missing rivets, cracks or deformation. Inspections are due within 25 flight hours or 30 days from 10 April 2008 and then every 100 flight hours; detected damage must be managed with the manufacturer before further flight and an inspection report forwarded within five days. Owners/operators bear inspection, reporting and repair costs; the AD responds to detected fatigue cracking (Background)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-tecnam-6-vertical-fin-spar","history":"/api/acts/ad-tecnam-6-vertical-fin-spar/history","analysis":"/api/acts/ad-tecnam-6-vertical-fin-spar/analysis","conflicts":"/api/acts/ad-tecnam-6-vertical-fin-spar/conflicts","importantCases":"/api/acts/ad-tecnam-6-vertical-fin-spar/important-cases","documents":"/api/acts/ad-tecnam-6-vertical-fin-spar/documents"}}