{"id":"F2006B01962","name":"AD/A320/73 - Frame 60 and 62 Cargo Door Frame","slug":"ad-a320-73-frame-60-and-62-cargo-door-frame","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41184,"registerId":"commonwealth-F2006B01962-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/73 - Frame 60 and 62 Cargo Door Frame","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)  \nAirbus Industrie A319, A320 and A321 Series Aeroplanes\n\nAD/A320/73 Frame 60 and 62 Cargo Door Frame 2/97\n\nApplicability: All Airbus A320 with bulk Cargo Door installed (Airbus Industrie Modification 20029), and without Airbus Industrie Modification 21277 or Airbus Industrie Service Bulletin A320-53-1021 incorporated.\n\nRequirement: Carry out an Eddy Current Inspection of the upper frame flanges at frames 60 and 62 between stringers 40 and 42 in accordance with Airbus Industrie Service Bulletin A320-53-1022 Revision 1.\n\nIf a crack is detected, repair as per Airbus Industrie Service Bulletin A320-53-1021 revision 1.\n\nNote: French DGAC AD 96-238-091(B) refers.\n\nCompliance: Within 20,000 flights and within every 1,200 flights thereafter.\n\nNote: Incorporation of Airbus Industrie Service Bulletin A320-53-1021 Revision 1 constitutes terminating action for this Directive.\n\nThis Amendment is effective from 30 January 1997.\n\nBackground: During fatigue testing, cracking was found in the flanges of the affected frames. This directive requires inspecting for these cracks.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive sticks to its original safety focus: detect and repair fatigue cracking in frames 60 and 62 on A320‑family aeroplanes with the bulk cargo door. It applies only to aircraft without the later modifications or service bulletin incorporated; incorporating the service bulletin removes the continuing inspection obligation. There is no expansion beyond the original technical problem identified in fatigue testing."},"complexity_factors":["Targeted technical requirement: eddy‑current non‑destructive inspection of specific frame flanges (requires trained personnel and equipment).","Applicability conditioned on aircraft configuration and incorporation of particular Airbus modifications/service bulletins (filters which aircraft/operators are affected).","Prescriptive repair path: detected cracks must be repaired per a specified Airbus Service Bulletin (dependency on manufacturer documentation).","Maintenance scheduling and fleet planning: fixed flight‑based compliance intervals (20,000 flights initial; 1,200 flights repeat) affect operator planning and aircraft availability.","Terminating action mechanic: incorporation of the Service Bulletin removes ongoing inspection burden (affects operator cost/benefit timing).","Cross‑reference to foreign AD (DGAC) and manufacturer documents increases regulatory and documentary coordination needs."],"plain_english_summary":"Requires operators of Airbus A319/A320/A321 aeroplanes fitted with the bulk cargo door (unless specific later modifications are already installed) to perform eddy‑current inspections of the upper cargo‑door frame flanges at frames 60 and 62 between stringers 40 and 42. Any crack found must be repaired following the referenced Airbus Service Bulletin. Inspections are due within 20,000 flights and then every 1,200 flights; incorporating the Service Bulletin is a terminating action. Operators pay for inspections and repairs."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original narrow scope: addressing a specific structural fatigue issue discovered during testing of Airbus A320 family aircraft cargo door frames. The document has not expanded beyond its original safety purpose."},"complexity_factors":["Single, specific technical requirement with clear applicability criteria","Only 3 defined technical references (Modification 20029, Modification 21277, Service Bulletin A320-53-1021)","Simple conditional logic: inspect → if crack found → repair","Clear compliance timeline (20,000 flights initial, 1,200 flights recurring)","No nested exceptions or cross-references to other legislation","Short document (approximately 150 words) with single purpose"],"plain_english_summary":"This safety inspection order requires operators of Airbus A320-family aircraft fitted with the large bulk cargo door (and not already modified by Airbus SB A320‑53‑1021/Mod 21277) to perform regular eddy‑current inspections of cargo door frame flanges for fatigue cracks, repair any findings per manufacturer methods, and repeat inspections periodically. It prevents structural failure revealed in fatigue testing; installing Airbus’s service bulletin is the terminating action that removes the inspection requirement."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame","history":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame/history","analysis":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame/analysis","conflicts":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame/conflicts","importantCases":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame/important-cases","documents":"/api/acts/ad-a320-73-frame-60-and-62-cargo-door-frame/documents"}}