{"id":"F2006B08180","name":"AD/CESSNA 310/53 - Wing Front Spar Lower Attachment Fittings","slug":"ad-cessna-310-53-wing-front-spar-lower-attachment-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115383,"registerId":"commonwealth-F2006B08180-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CESSNA 310/53 - Wing Front Spar Lower 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)  \nCessna 310 Series Aeroplanes\n\nAD/CESSNA 310/53 Wing Front Spar Lower Attachment Fittings 6/89\n\nApplicability: All models.\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    2. Visually inspect the upper and lower edges of the lug of each wing fitting, looking for cracks as shown in the figure below.\n\n    3. From inside the wheel well, visually inspect each visible wing fitting for cracks and surface pitting in the area shown in the figure.\n\nNote: It is not necessary to remove the primer for any of the above inspections.\n\n![](image.002.png)  \n\nWing Fitting Showing Typical Cracking\n\nNote: Fitting Shown removed from aircraft for clarity\n\nCompliance: Before exceeding 5000 hours component time in service or before the issue of the next Maintenance Release after 15 June 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.\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\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.","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 Airworthiness Directive maintains its original narrow scope — addressing a specific safety defect in a specific aircraft part. It has not expanded beyond its original purpose of mandating repetitive visual inspections for fatigue cracking in Cessna 310 wing attachment fittings."},"complexity_factors":["Very short document (approximately 250 words)","Only 3 defined procedural steps","Single applicability criterion (all Cessna 310 models)","Simple compliance timeline (5000 hours or specific date, whichever is later)","No cross-references to other legislation or regulations beyond the enabling authority (Civil Aviation Regulations 1998, Part 39)","Clear, diagram-supported instructions with minimal technical jargon","Single exception/note (primer need not be removed)"],"plain_english_summary":"This safety inspection order requires owners/operators of Cessna 310 series and related twin‑engine Cessna aircraft to inspect the wing front spar lower attachment fittings (P/N 0822550) for fatigue cracks and corrosion that could cause wing separation.  \n\nA visual inspection—after removing the wing‑to‑fuselage fairing but without stripping primer—must be done before 5,000 flight hours (or the next Maintenance Release after 15 June 1989) and thereafter at every Maintenance Release."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive applies fleet‑wide to all Cessna 310 models and introduces repetitive visual inspections of the specified wing fitting; this aligns with the stated purpose in the Background to detect fatigue/stress‑corrosion cracking and does not expand beyond that original remedial intent."},"complexity_factors":["Applicability to all models increases fleet coverage and inspection demand (Requirement: \"Applicability: All models\").","Physical access needed: removal of the fairing between wing and carry‑thru to gain access (Requirement: step 1).","Inspection method relies on visual detection of cracks and pitting, creating judgment calls for maintenance personnel (Requirement: steps 2–3).","Timing and record trigger linked to component hours and issue of a Maintenance Release, requiring tracking of component time and maintenance records (Compliance).","Recurring inspections at each scheduled Maintenance Release create an ongoing compliance burden for operators (Compliance: \"Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release\").","Note that primer removal is not required, which reduces one potential complexity in inspection procedure (Note).","Background uncertainty (fatigue/stress corrosion found in similar fittings) underpins fleet‑wide inspection despite limited incidents (Background)."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of Cessna 310-series aeroplanes to remove the fairing, visually inspect the wing front spar lower attachment fittings (P/N 0822550) for cracks and surface pitting, and repeat inspections at each scheduled Maintenance Release. Compliance is due before a fitting reaches 5,000 hours component time or before the next Maintenance Release after 15 June 1989, whichever is later. Aircraft owners/operators pay for the inspections and any repairs; the Civil Aviation Safety Authority sets the compliance timing and reinspection schedule."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings","history":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings/history","analysis":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings/analysis","conflicts":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings/conflicts","importantCases":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings/important-cases","documents":"/api/acts/ad-cessna-310-53-wing-front-spar-lower-attachment-fittings/documents"}}