{"id":"F2006B04301","name":"AD/BEECH 95/29 - Wing Main Spar Centre Section","slug":"ad-beech-95-29-wing-main-spar-centre-section","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":44112,"registerId":"commonwealth-F2006B04301-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BEECH 95/29 - Wing Main Spar Centre Section","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nBeechcraft 95 (Travelair) Series Aeroplanes\n\nAD/BEECH 95/29 Wing Main Spar Centre Section 11/90\n\nApplicability: Model 95, B95, B95A, D95A and E95, serial numbers TD-1 to TD-721 inclusive.\n\nRequirement: Inspect the wing forward spar carry through structure forward and aft frames, in accordance with Beechcraft Service Bulletin No 2269 Rev 1, dated March 1990.\n\nNote: FAA AD 90-08-14, Amendment 39-6563 refers.\n\nCompliance: Within 100 hours’ time in service after 1 November 1990, or prior to the accumulation of 1500 hours total time in service, whichever occurs later. Where no cracks are found, repeat the inspections at intervals not to exceed 500 hours’ time in service.\n\nWhere cracks are found, repeat the inspections at intervals as detailed in the requirement document.\n\nCrack limits must not be exceeded.\n\nSpecific locations repaired or reinforced by the installation of the applicable Beech P/N 58-4008 kit, or other approved scheme, need not be inspected before 1500 hours’ time in service after installation of the repair, however affected areas adjacent to repair doublers remain subject to the above compliance.\n\nBackground: There have been numerous reports of cracking at various locations in the wing carry through structure. This problem was first found in Australia, on other models, in 1981. The cracking is caused by fatigue in the corners of the fuselage frame webs, around and between huckbolts and in areas where stringers are attached. To date, there have been no reports of cracks having progressed to failure, however uncorrected this condition will lead to eventual catastrophic failure.\n\nEngineering analysis has determined, however, that cracking within defined limits is not an immediate threat to safe flight if assessed and monitored in accordance with this directive.","sortOrder":0}],"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The directive's scope, as supplied, targets fatigue cracking in the wing carry‑through structure of listed Beechcraft 95 serials and prescribes inspection and repair timing per the service bulletin. The text contains no amendment history or language indicating a change from the original intent; it constrains application to specified models/serials and sets conditional inspection regimes consistent with the stated safety purpose."},"complexity_factors":["Limited applicability to specific models and serial numbers increases administrative checking (Applicability).","Mandates inspections 'in accordance with' an external document (Beechcraft Service Bulletin No.2269 Rev 1), creating reliance on another text for procedural detail (Requirement).","Two-part compliance trigger: within 100 hours after a calendar date or prior to 1500 total hours, whichever is later — operators must compute and track both counters (Compliance).","Repeat intervals conditional on findings: 500 hours if no cracks, otherwise intervals 'as detailed in the requirement document', adding conditional scheduling complexity (Compliance/Requirement).","Repair carve‑out: areas repaired with a specified kit are exempt from inspection until 1500 hours after installation, but adjacent areas remain subject to inspection — creates partial exemptions to manage (Compliance).","'Crack limits must not be exceeded' and the background acceptance that limited cracking can be monitored introduces engineering judgement and potential inspection interpretation disputes (Background/Requirement).","Reference to related FAA AD creates cross‑jurisdictional traceability requirements for some operators (Note/Background)."],"plain_english_summary":"This airworthiness directive requires owners/operators of specified Beechcraft 95 series aeroplanes (serials TD-1 to TD-721) to inspect the wing forward spar carry‑through structure using Beechcraft Service Bulletin No.2269 Rev 1, within set flight‑time limits and at recurring intervals. The rule targets fatigue cracking reports; detected cracks shorten inspection intervals and may require repair. Owners pay for inspections and repairs; the regulator mandates the work and operators must change maintenance scheduling and recordkeeping accordingly."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a discrete airworthiness directive addressing a specific safety issue (fatigue cracking in wing spar structure) for a defined aircraft population. It has not expanded beyond its original technical safety purpose."},"complexity_factors":["Single specific aircraft model series with defined serial number range","Multiple compliance deadlines with conditional logic (100 hours after date OR 1,500 hours total time, whichever is later)","Nested conditional requirements (different inspection intervals depending on whether cracks are found or not)","Exception for repaired areas with specific part number (Beech P/N 58-4008) but with carve-out for adjacent areas","Reference to external technical document (Beechcraft Service Bulletin No 2269 Rev 1) for detailed inspection procedures","Cross-reference to US FAA Airworthiness Directive (90-08-14) for context"],"plain_english_summary":"This safety order requires owners/operators of Beechcraft Model 95/Travelair aircraft (serials TD-1–TD-721) to inspect the wing main spar at the fuselage per Beechcraft service bulletin for fatigue cracks. Initial inspection is within 100 flying hours after 1 Nov 1990 or before 1,500 total hours (whichever is later); repeat every 500 hours if clear, with shorter intervals or repairs per the bulletin; approved repairs defer inspection 1,500 hours but adjacent areas still require checks.\n\nCracks from metal fatigue can lead to catastrophic wing failure, so these inspections prevent uncontrolled structural failure."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section","history":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section/history","analysis":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section/analysis","conflicts":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section/conflicts","importantCases":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section/important-cases","documents":"/api/acts/ad-beech-95-29-wing-main-spar-centre-section/documents"}}