{"id":"F2006B01961","name":"AD/A320/72 - Frame 56 Connecting Angle","slug":"ad-a320-72-frame-56-connecting-angle","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41183,"registerId":"commonwealth-F2006B01961-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/72 - Frame 56 Connecting Angle","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/A320/72 Frame 56 Connecting Angle 2/97\n\nApplicability: All Airbus A320 without Airbus Industrie Modification 20941 or Airbus Industrie Service Bulletin A320-53-1011 incorporated.\n\nRequirement: Inspect the connecting angle between frame 56 and the frame support at stringer 38 in accordance with Airbus Industrie Service Bulletin A320-53-1084 Revision 1.\n\nNote: French DGAC AD 96-237-090(B) refers.\n\nCompliance: Inspect before 20,000 flights and if no cracks are detected, at intervals not exceeding 12,000 flights. If cracks are detected, reinspect at the intervals defined in Airbus Industrie Service Bulletin A320-53-1084 Revision 1.\n\nNote: Airbus Industrie Service Bulletin A320-53-1011 is terminating action for this Directive.\n\nThis Airworthiness Directive becomes effective on 30 January 1997.\n\nBackground: During fatigue testing, cracking of the connecting angle was discovered. This Directive inspects this connecting angle, and allows a tighter inspection regime if cracks are found.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The Directive implements targeted inspection requirements to detect fatigue cracking identified in testing and applies only to A319/A320/A321 aircraft lacking the specified modification or service bulletin. It does not broaden applicability beyond that identified safety concern; instead it enforces a manufacturer-defined inspection regime (see Applicability; Requirement; Compliance)."},"complexity_factors":["Narrow applicability: only A319/A320/A321 aircraft without Mod 20941 or SB A320‑53‑1011 are affected (Applicability).","Dependence on external technical documents: inspection procedure and reinspection intervals are defined by Airbus Service Bulletin A320‑53‑1084 Revision 1 (Requirement; Compliance).","Numeric timing and branching: fixed initial deadline (before 20,000 flights), repeating interval (≤12,000 flights), plus alternate intervals if cracks found (Compliance).","Terminating action referenced: incorporation of Service Bulletin A320‑53‑1011 is stated as terminating action for the Directive (Note).","Technical specificity: inspection targets a precise structural location (connecting angle between frame 56 and frame support at stringer 38), requiring specialised maintenance skills.","Regulatory formality: issued as an Airworthiness Directive with an effective date (becomes effective on 30 January 1997), creating a mandatory compliance obligation.","Cross-reference to foreign authority: notes alignment with French DGAC AD 96-237-090(B), indicating coordinated international oversight (Note)."],"plain_english_summary":"Requires inspections of the connecting angle between frame 56 and the frame support at stringer 38 on Airbus A319/A320/A321 aeroplanes that have not incorporated Airbus Modification 20941 or Service Bulletin A320‑53‑1011. Inspections must be completed before 20,000 flights and then at intervals not exceeding 12,000 flights; if cracks are found, reinspection intervals follow those in Airbus Service Bulletin A320‑53‑1084 Revision 1.\n\nThis measure responds to fatigue cracking found during testing; the inspection and any corrective work are obligations for aircraft operators and their maintenance organisations and will incur their costs."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive addressing a specific structural fatigue issue discovered during testing. The scope remains precisely limited to inspection of the frame 56 connecting angle on unmodified A320 aircraft, with no evidence of scope creep or expansion beyond the original safety purpose."},"complexity_factors":["Single, specific mechanical component addressed (frame 56 connecting angle)","Clear applicability test (two specific modification numbers)","Straightforward compliance timeline (20,000 flights initial, 12,000 flights recurring)","Only one cross-reference to an external technical document (Airbus Service Bulletin A320-53-1084 Revision 1)","Binary condition (cracks detected vs. not detected) with clear branching outcomes","No defined terms section, no nested exceptions, no conditional logic beyond the crack/no-crack scenario"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections of a specific connecting-angle bracket on Airbus A320s that have not received Modification 20941 or Service Bulletin A320‑53‑1011. Owners/operators must inspect before 20,000 flights and, if no cracking is found, repeat every 12,000 flights; detected cracks trigger a tighter Airbus-specified inspection regimen. The measure addresses fatigue-found cracking that could threaten structural integrity and is terminated for aircraft that install SB A320‑53‑1011."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-72-frame-56-connecting-angle","history":"/api/acts/ad-a320-72-frame-56-connecting-angle/history","analysis":"/api/acts/ad-a320-72-frame-56-connecting-angle/analysis","conflicts":"/api/acts/ad-a320-72-frame-56-connecting-angle/conflicts","importantCases":"/api/acts/ad-a320-72-frame-56-connecting-angle/important-cases","documents":"/api/acts/ad-a320-72-frame-56-connecting-angle/documents"}}