{"id":"F2006B05540","name":"AD/PA-24/41 Amdt 2 - Wing Inspection for Fatigue Cracking","slug":"ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":46459,"registerId":"commonwealth-F2006B05540-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PA-24/41 Amdt 2 - Wing Inspection for Fatigue Cracking","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)  \nPiper PA-24 (Comanche) Series Aeroplanes\n\nAD/PA-24/41\n\nAmdt 2\n\n  \nWing Inspection for Fatigue Cracking 12/91\n\nApplicability: All model PA-24 Model PA-24-250 S/N 24-1 and subsequent Model PA-24-260 S/N 24-3642, 24-4000 and subsequent Model PA-24-400 S/N 26-1 and subsequent.\n\nRequirement: Modify the wing skin and visually inspect the left and right wing lower main spar caps and upper main spar attachment plate, in accordance with the Technical Requirements of FAA Emergency Airworthiness Directive 82-19-01 Piper dated 3 September 1982.\n\nNote: The FAA rescinded AD 82-19-01 on 27 April 1988 and no longer supplies copies . A copy of this document is available, free of charge from Manager, Airworthiness and Operations Branch, Civil Aviation Authority, GPO Box 367,CANBERRA ACT 2601.\n\nCompliance: At intervals not exceeding 100 hours time in service. This Directive was originally issued in June 1984. This amendment, which is issued for clarification only and does not affect compliance times, is effective from 12 December 1991.\n\nBackground: This requirement is based upon a FAA Directive issued to prevent the possibility of catastrophic wing failure associated with fatigue damage. Amendment 1 to this Directive clarified that the inspection is repetitive. Amendment 2 clarifies that the inspections must be continued for Australian registered aircraft (even though AD 82- 19-01 has been withdrawn by the FAA), because the possibility of fatigue cracking still exists.","sortOrder":0}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive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":"The legislation maintains its original narrow scope. Amendment 2 explicitly confirms the directive continues to apply to Australian-registered aircraft despite the FAA withdrawing its equivalent rule. This is a clarification of ongoing applicability, not an expansion into new aircraft types, new inspection methods, or extended operational contexts."},"complexity_factors":["Short, single-purpose directive with one primary requirement","Only 3 defined model/serial number groupings in applicability section","Single cross-reference to external FAA document (AD 82-19-01)","Simple compliance trigger: fixed 100-hour interval","No nested exceptions or conditional logic — applies to all listed aircraft uniformly","Amendment history is narrative background only, not operative text"],"plain_english_summary":"This Airworthiness Directive requires Australian operators of certain Piper PA‑24 Comanche serial ranges to modify the wing skin and perform repeated (every 100 flight hours) visual inspections of main spar attachments per the original 1982 FAA service instruction. It targets fatigue cracking that can cause catastrophic wing failure and remains an indefinite, ongoing safety mandate in Australia despite the FAA’s later withdrawal."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 2 clarifies that inspections must continue for Australian-registered aircraft despite the FAA having rescinded its AD, thereby extending the directive's operational duration in Australia without changing the 100‑hour compliance interval (Background; Compliance)."},"complexity_factors":["Clear, single technical requirement: modify wing skin and visually inspect specified spar areas (Requirement).","Repetitive inspection interval imposed (every 100 hours TIS) creating ongoing operational and maintenance burden (Compliance).","Applicability limited to specific PA-24 models and serial-number ranges, requiring owners to check serials (Applicability).","References external FAA Emergency AD for technical procedure even though that FAA AD was later rescinded, raising document-access and authority-clarity issues (Requirement; Note; Background).","No detailed enforcement, remediation, or repair standards in the text — relies on the FAA document for technical requirements (Requirement)."],"plain_english_summary":"Requires owners/operators of specified Piper PA-24 (Comanche) aeroplanes (listed by model and serial number) to modify the wing skin and carry out recurring visual inspections of the left and right lower main spar caps and the upper main spar attachment plate every 100 hours time-in-service (Applicability; Requirement; Compliance). The directive is retained by the Australian authority to prevent possible catastrophic wing failure and continues even though the original FAA AD was later rescinded (Requirement; Background; Note)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking","history":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking/history","analysis":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking/analysis","conflicts":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking/conflicts","importantCases":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking/important-cases","documents":"/api/acts/ad-pa-24-41-amdt-2-wing-inspection-for-fatigue-cracking/documents"}}