{"id":"F2006B07293","name":"AD/TB10/25 Amdt 2 - Wing Rear Attachment Fittings","slug":"ad-tb10-25-amdt-2-wing-rear-attachment-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":49262,"registerId":"commonwealth-F2006B07293-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/TB10/25 Amdt 2 - Wing Rear Attachment Fittings","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)  \nAerospatiale (Socata) TB9 and TB10 (Tobago) Series Aeroplanes\n\nAD/TB10/25\n\nAmdt 2\n\n  \nWing Rear Attachment Fittings 10/96\n\nApplicability: Models TB10 and TB200 S/N 804, 807,808, 816 to 819, 823 to 1701, 1707 to 1733,\n\n1737 to 1761.\n\nRequirement: 1. Remove the cowling under hull Nr.218 to gain access to the wing rear attachment fitting. Visually inspect the bend radii of the wing to fuselage rear attachment fitting for cracks.\n\n2. Remove and prepare the wing to rear fuselage rear attachment fittings in accordance with Socata SB 10-82-57 Amdt.1 and inspect using a fluorescent dye penetrant per CAO 108.10.\n\nNote: DGAC AD 94-249(A)R1 refers in part.\n\nCompliance: 1. Initially inspect within 100 hours time in service after 22 June 1995, thereafter at intervals not exceeding 200 hours time in service.\n\n2. Unless already accomplished in accordance with the initial issue of Requirement 2 Socata document; before the accumulation of 3 000 flights, or 2 000 hours time in service, whichever occurs first; thereafter at intervals not exceeding 3000 flights or 2000 hours time in service, whichever occurs first.\n\nInstallation of kit OPT10 920300 terminates this Directive on the side to which the kit is fitted.\n\nThe compliance remains unchanged from the previous issue. This Amendment becomes effective on 12 September 1996.\n\nBackground: Inspection of the wing to fuselage attachment is necessary to ensure the continued integrity of the structure.\n\nAmendment 1 added an in-situ visual inspection of the fittings due to reports to the Authority of cracks developing within times significantly less than that required by the DGAC AD and the manufacturer.\n\nAmendment 2 provides terminating action.\n\nThe original issue of this Airworthiness Directive became effective on 2 March 1995\\. Amendment 1 of this Airworthiness Directive became effective on 22 June 1995.","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":3,"scope_assessment":{"changed":true,"description":"Amendment 2 introduces a terminating action (installation of kit OPT10 920300) that removes the need for further inspections on the side fitted, while leaving the stated inspection requirements and intervals otherwise unchanged. Earlier Amendment 1 had added an in‑situ visual check; this Amendment therefore changes available compliance options but not the recurrent inspection schedule (Compliance; Background)."},"complexity_factors":["Technical inspection methods required (visual inspection, removal of cowling, fluorescent dye‑penetrant) (Requirement 1–2)","Multiple, different compliance intervals (initial 100 hours then 200‑hour recurring; separate 3,000 flights/2,000 hours schedule for penetrant) (Compliance)","Applicability limited to specific serial numbers, requiring operators to check fleet lists (Applicability)","Reference to external documents and standards (Socata SB 10‑82‑57 Amdt.1; CAO 108.10; DGAC AD noted) increases procedural complexity (Requirement/Note)","Optional terminating action (installation of kit OPT10 920300) creates a compliance choice for operators (Compliance)"],"plain_english_summary":"This Airworthiness Directive requires owners/operators of specified Socata TB10/TB200 aeroplanes to inspect the wing rear attachment fittings for cracks, using an initial in‑situ check and a detailed fluorescent dye‑penetrant inspection following Socata and CAO procedures. Inspections must occur at the stated flight/hour intervals, and installing kit OPT10 920300 on a side cancels the AD for that side (Requirements; Compliance). It matters because the fittings are structural load paths and cracking risks affect continued airworthiness (Background)."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive has remained focused on its original purpose: ensuring the structural integrity of wing rear attachment fittings on specific Socata aircraft. Amendment 1 added an interim visual inspection based on new safety data (cracks appearing earlier than expected), and Amendment 2 added a terminating action (modification kit installation). These are natural evolutions of the same safety issue rather than scope creep."},"complexity_factors":["Short, single-purpose document (2 pages) focused on one specific mechanical issue","Limited defined terms — only standard aviation abbreviations (S/N for serial number, Nr. for number)","Clear, numbered requirements with specific compliance timeframes","Some conditional logic ('whichever occurs first', 'unless already accomplished') but straightforward","Cross-references to external documents (Socata SB 10-82-57 Amdt.1, CAO 108.10, DGAC AD 94-249(A)R1) but these are standard aviation references","Narrow applicability — specific aircraft models and serial number ranges only"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of specified Socata TB10/TB200 Tobago aeroplanes to inspect wing rear attachment fittings for cracks — initially and at recurring intervals — because undetected cracking can lead to structural failure and wing separation.\n\nInspections include scheduled visual checks and a detailed fluorescent dye-penetrant inspection after a set number of flights/hours; installing modification kit OPT10 920300 on a side is a terminating action that removes the need for further inspections on that side."}},"importantCases":[],"_links":{"self":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings","history":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings/history","analysis":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings/analysis","conflicts":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings/conflicts","importantCases":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings/important-cases","documents":"/api/acts/ad-tb10-25-amdt-2-wing-rear-attachment-fittings/documents"}}