{"id":"F2006B01940","name":"AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window Frame","slug":"ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41162,"registerId":"commonwealth-F2006B01940-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window 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/A320/50 Fuselage \\- Lower Forward Corner of\n\nCockpit Sliding Window Frame\n\n  \n5/95\n\nApplicability: Airbus Industrie A320 aircraft serial number 002 to 008, 010 to 014, 016 to 078 and 080 to 098 inclusive. This AD is applicable to aircraft serial number 003 and 004 on the left hand window frame only and for serial number 023 applicable to the right hand window frame only.\n\nRequirement: Inspect, using high frequency eddy current, the lower forward corner of the sliding window frame at fuselage frame 4. Inspect, in accordance with Airbus Industrie Service Bulletin A320-53-1082, around the five fasteners specified in Fig 1.\n\nNote: DGAC AD 94-166-056(B) refers.\n\nCompliance: Initially inspect before 15000 flights.\n\nRe-inspect frames without cracks at 15000 flight intervals.\n\nRe-inspect frames with cracks in accordance with the schedule specified in paragraph B(2)(b) of Airbus Industrie Service Bulletin A320-53-1082.\n\nNote: Modification in accordance with Airbus Industrie Service Bulletin A320-53- 1044 cancels the inspection requirements of this AD.\n\nThis AD is effective from 27 April 1995.\n\nBackground: Cracks were found on the lower forward corner of the sliding window frame at frame 4 during the full scale fatigue test.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Scope remains focused on the lower forward corner of the cockpit sliding window frame at fuselage frame 4 for the listed serial-numbered aircraft to detect fatigue cracks. The AD continues to allow termination of inspections by a specified modification; there is no indication in the text that the scope was broadened or narrowed from its stated safety purpose."},"complexity_factors":["Applicability limited to specific aircraft serial numbers and, for a few serials, to one window frame only (adds tracking complexity).","Mandates a specific non‑destructive test method (high‑frequency eddy current) with inspection locations defined by Airbus Service Bulletin A320‑53‑1082.","Different follow-up regimes: fixed 15,000‑flight intervals for unaffected frames and a separate schedule for cracked frames (service‑bulletin referenced).","Provides a terminating action (modification per Service Bulletin A320‑53‑1044) that cancels recurring inspections, requiring operators to choose between recurring inspections or a one‑time modification.","Requires operators to monitor flight counts and maintain compliance records across affected airframes.","Cross‑references a foreign authority AD (DGAC), increasing reliance on external technical material."],"plain_english_summary":"This Airworthiness Directive requires operators of specified Airbus A319/A320/A321 serial-numbered aircraft to inspect the lower forward corner of the cockpit sliding-window frame at fuselage frame 4 using high-frequency eddy-current testing. Initial inspection is required before 15,000 flights and then at 15,000-flight intervals; frames with cracks follow a service‑bulletin reinspection schedule.\n\nOperators must follow Airbus Service Bulletin A320‑53‑1082, bear inspection costs, and may remove the inspection obligation by completing the modification in Service Bulletin A320‑53‑1044. The AD responds to cracks found in a fatigue test."},"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":3,"scope_assessment":{"changed":false,"description":"This is a single-issue airworthiness directive focused on a specific structural defect discovered during fatigue testing. It maintains narrow scope targeting only the identified vulnerable aircraft serial numbers and the specific window frame location where cracks were found."},"complexity_factors":["Multiple applicability exceptions requiring careful serial number matching (003/004 left side only, 023 right side only)","Cross-reference to external technical document (Airbus Service Bulletin A320-53-1082) for inspection procedures and crack-found scheduling","Conditional compliance paths: initial inspection, re-inspection with/without cracks, and modification cancellation clause","Technical aviation terminology requiring domain knowledge (eddy current, fuselage frame 4, service bulletins)"],"plain_english_summary":"This directive orders operators of certain serial-numbered Airbus A319/A320/A321 aircraft to inspect the lower forward corner of the cockpit sliding window frame for cracks using high-frequency eddy current testing, initially before 15,000 flights and then every 15,000 flights if no defects are found. Some airframes require side-specific checks; if cracks are discovered a different inspection cadence applies. It responds to cracks found in fatigue testing and can be ended for modified aircraft per a specified service bulletin."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame","history":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame/history","analysis":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame/analysis","conflicts":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame/conflicts","importantCases":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame/important-cases","documents":"/api/acts/ad-a320-50-fuselage-lower-forward-corner-of-cockpit-sliding-window-frame/documents"}}