{"id":"F2006B11190","name":"AD/LUSCOMBE/2 Amdt 1 - Wing Spar Corrosion","slug":"ad-luscombe-2-amdt-1-wing-spar-corrosion","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":56896,"registerId":"commonwealth-F2006B11190-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"carefully.","sectionType":"part","heading":"carefully.","content":"# carefully.\n\nNote: In the location under the forward spars, support the wing half at normal height by any stable means, such as a ladder and padded lashed block. This will support the wing as the wing strut is removed. Avoid excess vertical deflection of the wing as this may stress the wing root attach point.\n\n    6. Using suitable light and the access gained by the wing strut hole, visually inspect the front of the rear spar and the rear of the front spar for abnormal bulges or erupted spar surfaces.\n\n    7. Remove the wing tip fairing by drilling out the rivets (using a #30 drill or smaller), and inspect the spars for abnormal bulges or erupted spar surfaces in the “U channel attach area\" of each spar, and the outer lengths to the splices of the sheet metal spar extrusions.\n\nNote: Inspection of the front of the front spar may be performed by using the existing inspection holes and a “light trolley\" on the upper aileron cable ( the illumination from the light trolley must be sufficient to provide for adequate inspection). Attach the light trolley to the upper aileron cable with a tie wrap, connect a wire or rope of suitable length to the tie wrap and use this as a means to move the light along the face of the spar.","sortOrder":0},{"sectionNumber":"8. Replace rivets through the skin and f","sectionType":"part","heading":"8. Replace rivets through the skin and front / rear spars with AN426 flush rivets to secure former, spar and skin. Install at least 6 rivnuts (3 on top / 3 on bottom) through the skin and former. Reattach wing tip fairings with #8/32 rivnuts or #8/32 x ½ machine screws, through the fairing, skin, and formers.","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\nAppendix to AD/LUSCOMBE/2 Amdt 1\n\nINSPECTION PROCEDURES FOR LUSCOMBE MODEL 8, 8A, 8B, 8C, 8D, 8E, 8F, T-8F AIRCRAFT THAT HAVE NOT ACCOMPLISHED THE INSPECTION IN ACCORDANCE WITH THE PROCEDURES IN THE DON LUSCOMBE AVIATION HISTORY FOUNDATION RECOMMENDATION #2, DATED DECEMBER 15, 1993; REVISED NOVEMBER 21, 1995.\n\n    Remove all existing wing root fairings, wing inspection hole covers, and wing strut cover plates on both the right and left wing.\n\n    2. Loosen the rear wing spar root attach bolts on both the right and left wings (one each wing) to permit a small wing deflection.\n\n    3. Perform a visual inspection of the extruded rear spar aft face of the left and right wing.\n\n    4. Inspect the face of the aft rear spar from the root to the spliced sheet metal tip spar at the wing root fairing location.\n\n    5. To permit removal of the wing strut, unbolt the wing strut and remove the strut\n\n# carefully.\n\nNote: In the location under the forward spars, support the wing half at normal height by any stable means, such as a ladder and padded lashed block. This will support the wing as the wing strut is removed. Avoid excess vertical deflection of the wing as this may stress the wing root attach point.\n\n    6. Using suitable light and the access gained by the wing strut hole, visually inspect the front of the rear spar and the rear of the front spar for abnormal bulges or erupted spar surfaces.\n\n    7. Remove the wing tip fairing by drilling out the rivets (using a #30 drill or smaller), and inspect the spars for abnormal bulges or erupted spar surfaces in the “U channel attach area\" of each spar, and the outer lengths to the splices of the sheet metal spar extrusions.\n\nNote: Inspection of the front of the front spar may be performed by using the existing inspection holes and a “light trolley\" on the upper aileron cable ( the illumination from the light trolley must be sufficient to provide for adequate inspection). Attach the light trolley to the upper aileron cable with a tie wrap, connect a wire or rope of suitable length to the tie wrap and use this as a means to move the light along the face of the spar.\n\n# 8. Replace rivets through the skin and front / rear spars with AN426 flush rivets to secure former, spar and skin. Install at least 6 rivnuts (3 on top / 3 on bottom) through the skin and former. Reattach wing tip fairings with #8/32 rivnuts or #8/32 x ½ machine screws, through the fairing, skin, and formers.","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"The amendment explicitly targets Luscombe Model 8, 8A–8F and T-8F aircraft that have NOT previously completed the inspection in accordance with the cited Don Luscombe Recommendation #2. That narrows compliance to that subset and prescribes specific inspection and rectification steps (inspection of spars, removal/reattachment of fairings and strut, and prescribed rivet/rivnut installations)."},"complexity_factors":["Technical aircraft-structure work: removal of fairings, unbolting wing struts, temporary wing support and avoidance of excess deflection (notes and steps 2,5,5 note).","Detailed inspection locations: front/rear spar faces, U-channel attach areas, splices and outer lengths (steps 3,4,6,7).","Specific hardware and tools mandated: #30 drill, AN426 flush rivets, rivnuts (3 top/3 bottom), #8/32 rivnuts or #8/32 x ½ machine screws (step 8).","Requires creative access techniques: use of a 'light trolley' on aileron cable for illumination (note after step 7).","Compliance burden concentrated on small owners/operators and maintenance providers who must source parts and perform hands‑on work.","Reference to an external document (Don Luscombe Recommendation #2, dated and revised) creates dependency on that prior procedure for applicability.","Duplicated and slightly garbled text (e.g. 'f 8. Replace rivets...' and repeated sections) increases interpretive ambiguity for technicians.","Safety/engineering judgement required where corrosion is found—text prescribes rivet/fastener replacement but not detailed repair thresholds or approval pathways."],"plain_english_summary":"This amendment requires owners/operators of Luscombe Model 8-series aircraft that have not done the referenced Don Luscombe Recommendation #2 inspection to perform hands-on visual inspections of front and rear wing spars, remove wing fairings and struts as needed, and replace specified rivets and fasteners. It matters because it creates a clear, work‑order level obligation: affected owners must fund and carry out access, inspection and fastening work to address potential spar corrosion and secure the wing structure."},"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":"rejected","complexity_score":4,"rejection_reason":"This appears to be a corrupted, fragmented, or poorly extracted version of an Airworthiness Directive. The text contains significant repetition, formatting errors, broken sentences (e.g., \"f 8. Replace\"), and scattered editorial marks (\"carefully. carefully.\"). While the substantive content relates to a genuine CASA Airworthiness Directive (AD/LUSCOMBE/2), this version appears to be an incomplete or corrupted extraction rather than authoritative legislative text suitable for analysis.","scope_assessment":{"changed":false,"description":"This appears to be a standard Airworthiness Directive maintaining its original scope — mandatory safety inspection for specific aircraft models. The scope remains tightly focused on wing spar corrosion inspection for the listed Luscombe models."},"complexity_factors":["Technical aviation terminology throughout (spar, extrusion, rivnut, AN426, aileron cable)","Precise mechanical specifications (drill bit #30, 6 rivnuts minimum, specific rivet types)","Multi-step procedural sequence with safety-critical warnings about wing support","Conditional applicability limited to specific aircraft models and those not previously inspected under alternative procedure","Nested references to external documents (Don Luscombe Aviation History Foundation Recommendation #2, 1993/1995)","Physical manipulation requirements requiring specialized tools and knowledge (light trolley, tie wraps, specific drill sizes)","Repetitive and fragmented text structure suggesting this is a corrupted or poorly formatted extraction rather than clean legislative text"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators and maintenance engineers of specified Luscombe Model 8 series aircraft to perform detailed inspections of wing spars for corrosion, bulges, or fatigue on aircraft not already inspected under earlier industry guidance. \n\nIt’s mandatory because undetected spar corrosion can cause catastrophic wing failure; the inspections use precise, prescribed procedures and hardware to access and assess hidden wing structure and ensure safe reassembly."}},"importantCases":[],"_links":{"self":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion","history":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion/history","analysis":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion/analysis","conflicts":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion/conflicts","importantCases":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion/important-cases","documents":"/api/acts/ad-luscombe-2-amdt-1-wing-spar-corrosion/documents"}}