{"id":"F2006B10619","name":"AD/HU 269/57 Amdt 4 - Centre Frame Aft Cluster Fitting","slug":"ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":116501,"registerId":"commonwealth-F2006B10619-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/HU 269/57 Amdt 4 - Centre Frame Aft Cluster Fitting","content":"![](image.001.png)\n\nAIRWORTHINESS DIRECTIVE\n\n![](image.001.png)  \n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/HU 269/57 Amdt 3 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\n![](image.001.png)  \n\nSchweizer (Hughes) 269 Series Helicopters\n\nAD/HU 269/57\n\nAmdt 4\n\n  \nCentre Frame Aft Cluster Fitting 6/2004\n\nApplicability: Model 269A, 269A-1, 269B, 269C, and 269C-1 helicopters, with a centre frame aft cluster fitting, part number 269A2234, 269A2234-3, 269A2235, or 269A2235-3, installed.\n\nRequirement: 1. Accomplish the following:\n\n    Chemically remove paint from the clevis lugs on each centre frame aft cluster fitting. Wash with water and dry.\n\n    b. Dye-penetrant inspect the clevis lugs on each aft cluster fitting.\n\n    c. If a crack is found, before further flight, replace the cracked aft cluster fitting with a serviceable part number 269A2234-3 or 269A2235-3 aft cluster fitting, as applicable.\n\n    d. If no cracking is found, clean the aft cluster fitting and repaint.\n\n2. Replace each aft cluster part number 269A2234 and part number 269A2235 not modified in accordance with Kit part number SA-269K-106-1 with part number 269A2234 and 269A2235 aft cluster fittings modified in accordance with Kit part number SA-269K-106-1; or with aft cluster fittings part number 269A2234-3 and 269A2235-3.\n\nNote 1: Installation of Aft Cluster Fitting Modification Kit, part number SA-269K- 0106-1, constitutes terminating action for the repetitive inspection requirements of this Directive.\n\n![](image.002.png)\n\nNote 2: FAA AD 2003-13-15 Amdt 39-13217 refers.\n\nCompliance: For Requirement 1:\n\nAll helicopters with part number 269A2234 or 269A2235 fittings installed:\n\nWithin 50 hours time in service after 15 May 2003, and thereafter at intervals not to exceed 50 hours time in service; until installation of Aft Cluster Fitting Modification Kit, part number SA-269K-0106-1.\n\nAll helicopters with part number 269A2234-3 or 269A2235-3 fittings installed:\n\nWithin 200 hours time in service after 15 May 2003, and thereafter at intervals not to exceed 200 hours time in service; until installation of Aft Cluster Fitting Modification Kit, part number SA-269K-0106-1.\n\nFor Requirement 2: Within 150 hours time in service or 6 months after 10 June 2004, whichever occurs first.\n\nThe compliance times for Requirement 1 remain unchanged by this issue. This Amendment becomes effective on 10 June 2004.\n\nBackground: A fatal accident report indicated that the cause was fatigue failure of a centre frame aft cluster fitting.\n\nAmendment 2 clarified that all aft cluster fittings have to be dye-penetrant inspected.\n\nAmendment 3 aligned this Directive with the requirements of the related FAA AD for part number 269A2234 and 269A2235 aft cluster fittings, and introduced optional terminating action for the repetitive inspection requirements of this Directive.\n\nAmendment 4 is issued in response to the related FAA AD, which requires unmodified basic part number aft cluster fittings to be removed from service.\n\nAmendment 2 of this Airworthiness Directive became effective on 3 March 1995.\n\n![Signature of David Villiers Delegate of the Civil Aviation Safety Authority](image.003.png)  \n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 29 April 2004\n\n![](image.001.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 19 May 2004.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 4 extends prior inspection-focused requirements by requiring unmodified basic part number aft cluster fittings (269A2234 and 269A2235) to be removed or modified/ replaced within a fixed time (150 hours or 6 months), aligning the AD with the related FAA AD. This changes scope from periodic inspection alone to mandatory replacement/modification unless the terminating kit is installed (Requirement 2; Background)."},"complexity_factors":["Multiple affected models and several specific part numbers in Applicability (269A2234, 269A2234-3, 269A2235, 269A2235-3).","Two-tier inspection intervals tied to part number status: 50 hours for basic parts, 200 hours for -3 parts (Compliance for Requirement 1).","Repetitive inspection requirement that continues until installation of a terminating modification kit (Note 1; Requirement 2).","Mandatory removal/replacement of unmodified basic part numbers within a hard time limit (150 hours or 6 months) (Requirement 2; Compliance).","Immediate safety action required if a crack is found—replace before further flight (Requirement 1(c)).","Dependence on a specific approved modification kit or on supply of -3 parts creates procurement and implementation steps for operators (Requirement 2; Note 1).","Cross-reference to FAA AD introduces a regulatory alignment element and potential for differing foreign directives to affect compliance (Note 2; Background)."],"plain_english_summary":"This Airworthiness Directive requires operators of Schweizer (Hughes) 269-series helicopters with certain centre frame aft cluster fittings to remove paint, perform dye‑penetrant inspections, replace any cracked fittings before further flight, and install modified or -3 series replacement fittings within set time limits. CASA (the delegate) issued the AD citing a fatal fatigue failure. Operators pay for inspections, repainting, replacements or modification kits; inspections recur (50 or 200‑hour intervals) until the terminating modification kit is fitted (Requirement 1–2; Compliance)."},"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 Amendment 4 remains tightly focused on the original safety issue (fatigue failure of centre frame aft cluster fittings). While it adds a new requirement (Requirement 2) mandating permanent replacement of unmodified parts, this is a logical progression from the inspection regime rather than scope creep. The directive maintains its original purpose of preventing structural failure in the specific helicopter models and components identified in the original AD."},"complexity_factors":["Multiple part numbers with similar but distinct requirements (269A2234 vs 269A2234-3)","Two-tier compliance schedule (50 hours vs 200 hours depending on part suffix)","Cross-reference to related FAA AD (2003-13-15)","Conditional logic: different actions required depending on inspection results (crack found vs no crack)","Terminating action concept requires understanding of modification kit installation","Amendment history references (Amendments 2, 3, and 4) create contextual overhead"],"plain_english_summary":"This CASA Airworthiness Directive mandates repetitive crack inspections and eventual replacement of certain centre-frame aft cluster fittings on Schweizer (Hughes) 269A/B/C series helicopters after a fatal fatigue failure. It requires dye-penetrant inspection and repair/replace if cracks are found, with unmodified fittings needing permanent replacement by modified/-3 parts within 150 flight hours or six months. The AD aims to prevent catastrophic structural failure and affects owners/operators of the specified helicopters."}},"importantCases":[],"_links":{"self":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting","history":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting/history","analysis":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting/analysis","conflicts":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting/conflicts","importantCases":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting/important-cases","documents":"/api/acts/ad-hu-269-57-amdt-4-centre-frame-aft-cluster-fitting/documents"}}