{"id":"F2006B01935","name":"AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint","slug":"ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41157,"registerId":"commonwealth-F2006B01935-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-description: CASA Airworthiness Directive\nmeta-generator: Aspose.Words for .NET 22.10.0\nmeta-keywords: Issue 5/1995,Aircraft above 5700 kg,Airbus Industrie A319, A320 and A321 Series Aeroplanes,Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint,45\ntitle: Airworthiness Directive - AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint\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)  Airbus Industrie A319, A320 and A321 Series Aeroplanes\n\n \n\n# AD/A320/45 Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint\n\nApplicability: A320 series aircraft MSN 005 to 030 inclusive.\n\n# 5/95\n\n \n\nRequirement: Perform an external detailed visual inspection for missing or broken rivet heads at fuselage frames 13 and 14 on the left and right hand sides between stringers 1 and 7. Inspect in accordance with Airbus Industrie SB A320-53-1036.\n\n \n\nNote: DGAC AD 92-199-028(B) refers.\n\n \n\nCompliance: Inspect before 10000 flights or before 27 May 1995, whichever is the later. Repeat inspections at intervals not exceeding 6000 flights.\n\n \n\nModification in accordance with Airbus Industrie SB A320-53-1010 cancels the requirement of this AD.\n\n \n\nBackground: A number of damaged or missing rivet heads were found on the fatigue test article.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, single-issue airworthiness directive focused on a specific structural inspection. It has not expanded beyond its original purpose of addressing rivet integrity at frames 13-14 on early A320 aircraft. The document represents the complete regulatory instrument as issued."},"complexity_factors":["Very short document (approximately 150 words of substantive content)","Only 1 defined applicability criterion (aircraft serial numbers 005-030)","Single inspection requirement with clear alternative compliance path","No nested conditional logic or cross-references to other legislation","Simple temporal compliance structure (flight hours/calendar date, whichever is later)","Only one external reference (French DGAC AD 92-199-028(B)) mentioned in passing as a note"],"plain_english_summary":"This Airworthiness Directive requires operators of early-production Airbus A320s (serial numbers 005–030) to inspect the fuselage at frames 13–14 for missing or broken rivet heads after a fatigue-test discovery that could weaken structure in service. Inspections must occur by 10,000 flights (or by 27 May 1995) and repeat every 6,000 flights, unless the Airbus Service Bulletin modification is installed, which permanently terminates the inspection requirement."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive sets targeted inspection requirements for a defined MSN subset and specifies repeat intervals and a cancelling modification. The text does not indicate any expansion or narrowing beyond those stated applicability and compliance terms."},"complexity_factors":["Narrow applicability: specific to \"A320 series aircraft MSN 005 to 030 inclusive\" (source: Applicability).","Technical procedure delegated to an Airbus service bulletin: inspection in accordance with \"Airbus Industrie SB A320-53-1036\" (source: Requirement).","Fixed temporal compliance and repeat interval obligations: \"before 10000 flights or before 27 May 1995, whichever is the later\" and \"repeat inspections at intervals not exceeding 6000 flights\" (source: Compliance).","Termination condition via modification: \"Modification in accordance with Airbus Industrie SB A320-53-1010 cancels the requirement of this AD\" (source: Compliance).","Safety-triggered origin: based on findings on a fatigue test article, which limits scope to a identified structural area (source: Background).","Operator burden limited but nontrivial: requires scheduling inspections, technician time and record-keeping across affected MSN range (implied by Requirement and Compliance).","Reference to foreign AD: \"DGAC AD 92-199-028(B) refers\" adds cross-jurisdictional compliance context (source: Note)."],"plain_english_summary":"Requires an external detailed visual inspection for missing or broken rivet heads at fuselage frames 13 and 14 (left and right sides, between stringers 1–7) on Airbus A320 series aircraft MSN 005–030, carried out per Airbus Industrie SB A320‑53‑1036. Inspections must occur by 10,000 flights or 27 May 1995 (whichever is later) and repeat every 6,000 flights. Completion of Airbus SB A320‑53‑1010 cancels the inspection. The directive follows discovery of damaged or missing rivet heads on a fatigue test article."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint","history":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint/history","analysis":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint/analysis","conflicts":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint/conflicts","importantCases":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint/important-cases","documents":"/api/acts/ad-a320-45-fuselage-fasteners-at-skin-panel-to-frame-13-and-14-joint/documents"}}