{"id":"F2007L04513","name":"AD/BEECH 55/96 - Structural Life Limit for Airframe","slug":"ad-beech-55-96-structural-life-limit-for-airframe","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":70970,"registerId":"commonwealth-F2007L04513-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 55, 58 and 95-55 (Baron) Seri","sectionType":"division","heading":"Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes","content":"### Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes\n\n| AD/BEECH 55/96 | Structural Life Limit for Airframe | 13/2007 |\n| -------------- | ---------------------------------- | ------- |\n\n| Applicability: | Model 58P and 58TC aircraft, with the following serial numbers: TJ-177, TJ-178,TJ-180, TJ-211, TJ-213, TJ-247, TJ-284, TJ-285, TJ-289, TJ-290, TJ-314, TJ-322, TJ-367, TJ-368, TJ-370, TJ-371, TJ-425, TJ-426, TJ-433, TJ-442 and TK-33, that are certified in any category. These aircraft were used as lead aircraft by the United States Forest Service for fire fighting missions.                                                                                                                                                                       |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | 1. Insert Raytheon Model 58P/58PA and Model 58TC/58TCA POH/AFM Supplement, part number 102-590000-67, issued January 2005, into the limitations section of the pilots operating handbook/AFM (P/N 102-590000-41 or 106-590000-5). The POH/AFM Supplement limits the structural fatigue life of the airframe (wing, fuselage, empennage and associated structure) to 4,500 hours TIS.2. Do not operate any Model 58P and 58TC aircraft (with any serial number as listed in the applicability of this AD).Note: FAA AD 2007-21-02, Amendment 39-15220 refers. |\n| Compliance:    | 1. Before further flight after 20 December 2007, unless already accomplished.2. As of the effective date of this AD, upon accumulation of 4,500 hours TIS on the airframe (wing, fuselage, empennage and associated structure) or before further flight, whichever occurs later.                                                                                                                                                                                                                                                                             |\n|                | This Airworthiness Directive becomes effective on 20 December 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          |\n| Background:    | This AD is a result of the FAA’s analysis and determination that the operational history and usage of the affected aircraft requires a reduction in the structural life limit to 4,500 hours TIS. The actions specified in this AD are intended to prevent structural failure of the airframe.                                                                                                                                                                                                                                                               |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n9 November 2007","sortOrder":0},{"sectionNumber":"AD/BEECH 55/96","sectionType":"part","heading":"AD/BEECH 55/96","content":"## AD/BEECH 55/96","sortOrder":1},{"sectionNumber":"Structural Life Limit for Airframe","sectionType":"part","heading":"Structural Life Limit for Airframe","content":"## Structural Life Limit for Airframe","sortOrder":2},{"sectionNumber":"13/2007","sectionType":"part","heading":"13/2007","content":"## 13/2007","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Scope remains focused on the listed Model 58P/58TC serial numbers and reduces the certified structural life to 4,500 hours TIS for the airframe (Background; Requirement). The AD does not broaden applicability beyond those serial numbers or add additional structural areas beyond wing, fuselage, empennage and associated structure."},"complexity_factors":["Narrow applicability: only specified serial numbers of Model 58P/58TC/58TCA (Applicability).","Single, discrete compliance action: insert POH/AFM supplement specifying 4,500 hours TIS structural life (Requirement, part 1).","Clear operational prohibition when limit reached: do not operate the listed models beyond 4,500 hours TIS (Requirement, part 2; Compliance).","Firm effective/compliance deadlines: before further flight after 20 December 2007 and upon accumulation of 4,500 hours TIS (Compliance).","Administrative and operational burden on owners/operators: updating POH/AFM, tracking TIS, and retiring/grounding aircraft at limit (Requirement; Compliance).","Cross-reference to FAA AD 2007-21-02 for underlying analysis (Requirement note).","Regulatory enforcement by CASA via issued AD (signature/Delegate; Background)."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of certain Beechcraft 58P/58TC serial-numbered aircraft to insert a Raytheon POH/AFM supplement that limits the airframe (wing, fuselage, empennage and associated structure) fatigue life to 4,500 hours time-in-service (TIS) and prohibits operation beyond that limit. It takes effect 20 December 2007. The AD targets the listed serial numbers (used as lead aircraft by the US Forest Service) and shifts the compliance burden and operational decision (retire/ground aircraft) to owners/operators."},"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 AD maintains its original narrow scope. It targets a specific safety issue (structural fatigue in firefighting aircraft) and applies only to 21 identified aircraft. There is no evidence of scope creep; the directive remains tightly focused on the original safety concern identified by the FAA regarding US Forest Service operational history."},"complexity_factors":["Single, clearly defined applicability section listing specific aircraft by serial number (21 aircraft total)","Two straightforward compliance requirements with clear deadlines","Minimal defined terms (only 'TIS' — Time In Service — requires industry knowledge)","No nested exceptions or conditional logic; requirements apply uniformly to all listed aircraft","Short document (approximately 300 words) with simple tabular format","Single cross-reference to FAA AD 2007-21-02 for background context only"],"plain_english_summary":"This CASA Airworthiness Directive forces 21 specific pressurised Beechcraft Baron aircraft (former US Forest Service fire‑bombers) to be retired at 4,500 total flight hours and requires owners to update flight manuals accordingly. CASA acted because these airframes, exposed to high‑stress firefighting ops, risk structural failure if allowed to continue beyond that life limit."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe","history":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe/history","analysis":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe/analysis","conflicts":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe/conflicts","importantCases":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe/important-cases","documents":"/api/acts/ad-beech-55-96-structural-life-limit-for-airframe/documents"}}