{"id":"F2006B08376","name":"AD/CESSNA 400/92 Amdt 1 - Wing Front Spar Lower Attachment Fittings","slug":"ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115799,"registerId":"commonwealth-F2006B08376-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 400/92 Amdt 1 - Wing Front Spar Lower Attachment Fittings","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Cessna 400 Series Aeroplanes\n\n \n\nAD/CESSNA 400/92\n\nAmdt 1\n\n\nWing Front Spar Lower Attachment Fittings 3/89\n\n \n\nApplicability: All 400 series aircraft, except for models 404 and 441.\n\n \n\nRequirement: 1. Remove the fairing between the wing and carry-thru and gain access to the wing front spar lower attachment fittings P/N 0822550.\n\n \n\n2.    Visually inspect the upper and lower edges of the lug of each wing fitting, looking for fatigue cracks as shown in the figure.\n\n \n\n3.    From inside the wheel well, visually inspect each visible wing fitting for stress corrosion cracks and associated surface pitting in the area shown in figure A.\n\n \n\nNote: It is not necessary to remove the primer for any of the above inspections.\n\n \n\nCompliance: Prior to exceeding 5000 hours component time in service, or prior to the issue of the next Maintenance Release after 22 March 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.\n\n \n\n \n\n![](image.002.png)  \n\n\n \n\n# Wing Fitting Showing Typical Cracking\n\n \n\nNote: Fitting Shown removed from aircraft for clarity\n\n \n\n# Figure A\n\n \n\nBackground: Fatigue cracking has been discovered in the wing fitting from an Australian-registered Cessna 310R with 6500 hours time in service. No abnormality could be found in the fitting or the aircraft’s history. Since then, stress corrosion cracking has been found in a similar wing fitting in a Cessna 402C with 6400 hours time in service.\n\n \n\nThere is insufficient evidence to regard either of these as isolated occurrences: either or both may be expected to occur at a later time elsewhere in the fleet of Cessna twins which use the same generic wing fitting. A simple repetitive visual inspection has therefore been introduced.\n\n \n\n \n\n \n\n \n","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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is Amendment 1 to an existing Airworthiness Directive. The scope remains tightly focused on the original safety issue: inspection of wing front spar lower attachment fittings for fatigue and stress corrosion cracking in Cessna 400 series aircraft. The amendment appears to maintain the same applicability and core requirements as the original AD/CESSNA 400/92, with no evidence of scope creep into unrelated systems or aircraft types."},"complexity_factors":["Single, clearly defined applicability (all 400 series except two models)","Only 3 specific inspection steps required","Simple compliance timeline with two alternative triggers (hours OR date, whichever is later)","Minimal defined terms — only standard aviation terminology (P/N, Maintenance Release, time in service)","No cross-references to other legislation or regulations","Single background scenario with clear safety rationale","Visual aids referenced but not complex technical diagrams requiring expert interpretation"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of most Cessna 400‑series twins (not 404/441) to inspect the wing front spar lower attachment fittings for fatigue and corrosion cracks. Inspections remove a fairing to visually check fitting lugs and the wheel‑well side; primer need not be stripped.\n\nIt must be done before the fitting reaches 5,000 hours (or by the next Maintenance Release after 22 Mar 1989) and repeated at each subsequent Maintenance Release — to prevent wing separation after cracked fittings were found."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument applies to all 400 series aircraft except models 404 and 441 and mandates repetitive visual inspections of a specific fitting (P/N 0822550) with a defined compliance trigger and ongoing reinspections. The text gives no indication that the scope has been expanded or narrowed from an earlier intent; it targets the fittings and inspection cadence to address detected fatigue and stress‑corrosion cracking."},"complexity_factors":["Limited and specific applicability: only Cessna 400 series, excluding models 404 and 441.","Few, concrete tasks: fairing removal and visual inspections (upper/lower lug edges; wheel‑well view).","Single identified part: P/N 0822550 simplifies targeting and inventory checks.","Access requirement: removal of fairing and internal wheel‑well inspection may require time, tools or jacks.","Conditional compliance timing: 'prior to exceeding 5000 hours or next Maintenance Release after 22 Mar 1989, whichever is later' introduces a logical condition for scheduling.","Ongoing compliance: reinspections at each scheduled Maintenance Release create recurring operational burden.","No requirement to remove primer reduces inspection effort but relies on visual detection limits.","Illustrative figures referenced to define inspected areas (visual comparators rather than measurement thresholds)."],"plain_english_summary":"This airworthiness directive requires operators of Cessna 400‑series aeroplanes (except models 404 and 441) to remove the wing-to-carry‑through fairing and carry out repetitive visual inspections of the wing front spar lower attachment fittings (P/N 0822550) for fatigue and stress‑corrosion cracking, including inspections from inside the wheel well. No primer removal is required.\n\nCompliance must occur before the fitting exceeds 5,000 hours component time or before the next Maintenance Release after 22 March 1989 (whichever is later), and then at each scheduled Maintenance Release. Operators pay for and must act on any repairs found."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings","history":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings/history","analysis":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings/analysis","conflicts":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings/conflicts","importantCases":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings/important-cases","documents":"/api/acts/ad-cessna-400-92-amdt-1-wing-front-spar-lower-attachment-fittings/documents"}}