{"id":"F2006B05464","name":"AD/PA-23/36 Amdt 1 - Engine Mount - Inspection","slug":"ad-pa-23-36-amdt-1-engine-mount-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":46237,"registerId":"commonwealth-F2006B05464-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PA-23/36 Amdt 1 - Engine Mount - Inspection","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-23 (Apache and Aztec) Series Aeroplanes\n\nAD/PA-23/36\n\nAmdt 1\n\n  \nEngine Mount \\- Inspection 5/72\n\nApplicability: PA-23-250 series with S/Nos. 2505 and subsequent with engine mount P/No.\n\n31215.\n\nRequirement: 1. For aircraft with engine mounts date-stamped prior to 26 May 1965, visually inspect the mounts for cracks in the following areas:\n\n    (a) The lower forward lateral tube.\n\n    (b) The three-tube horizontal diagonal truss in and around the three welded junctures with the lower forward lateral fore and aft tube; and\n\n    (c) The lower left horizontal fore and aft tube.\n\n    2. For aircraft with engine mount date-stamped 26 May 1965 or later and having 1000 hours or more total time in service, visually inspect the engine mount tubes forward of the firewall for cracks.\n\n    3. If cracks are found accomplish either of the following:\n\n    (a) Replace the engine mount prior to further flight with a new mount P/N 31215. After installation of a new mount continue repetitive inspection of this mount after 1000 hours total time in service as detailed in para. 2; or\n\n    (b) Repair the engine mount prior to further flight in accordance with a scheme acceptable to the Secretary, and inspect the entire engine mount for cracks prior to installation using a magnetic particle method. Thereafter continue visual inspections of the mount at intervals not to exceed 100 hours time in service.\n\nNote 1: On engine mounts date-stamped prior to 26 May 1965, a pictorial description of the affected areas can be found in Piper SL No. 462.\n\nNote 2: FAA AD 68-7-4 Amdt. 39-576 as amended by amendments 39-1324 and\n\n39-1426 also refers.\n\nNote 3: The engine mount is date-stamped on either of the two diamond-shaped gusset plates located near the upper firewall attachment points.\n\nCompliance: Within 50 hours time in service after 31 May 1972 unless already inspected within the last 50 hours time in service, and thereafter at intervals not exceeding 100 hours time in service.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument targets a defined subset of PA‑23‑250 aircraft (serials 2505 onward with engine mount P/N 31215) and prescribes inspection and rectification procedures. It does not expand applicability beyond those serial numbers or part numbers, but clarifies inspection locations, intervals, and acceptable repair/replace options."},"complexity_factors":["Conditional applicability based on airframe serial numbers and a specific engine mount part number (S/Ns 2505+ with P/N 31215).","Different inspection requirements depending on the mount date‑stamp (before or on/after 26 May 1965) and total hours in service.","Multiple inspection intervals and compliance deadlines (initial within 50 hours, then every 100 hours; repaired mounts inspected every 100 hours or every 100 hours after replacement).","Two compliance routes if cracks found: mandatory replacement with a specified P/N or repair under a scheme acceptable to the Secretary, creating administrative discretion.","Technical inspection methods specified for repaired mounts (magnetic particle inspection before installation) and reliance on referenced manufacturer service literature and FAA ADs.","Operational and cost implications for operators (inspection time, potential frequent re‑inspections, repair vs replacement decisions)."],"plain_english_summary":"**This airworthiness directive requires visual inspections of engine mounts on Piper PA‑23‑250 aeroplanes (serials 2505 onward) fitted with engine mount P/N 31215.** It sets which tubes and welded junctures to inspect, initial and recurring intervals, and requires either replacement with a new mount or a Secretary‑approved repair if cracks are found, with differing post‑repair inspection frequencies."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is Amendment 1 to an existing Airworthiness Directive (AD/PA-23/36). The scope remains tightly focused on engine mount inspections for the specified Piper aircraft series. The amendment appears to update or clarify the original 1972 directive without expanding beyond the original safety purpose of preventing engine mount failures."},"complexity_factors":["Multiple conditional inspection paths based on manufacturing date (pre/post 26 May 1965) and flight hours (1,000+ hours threshold)","Two distinct remediation pathways (replacement vs. repair) with different ongoing inspection intervals","Cross-reference to external documents (Piper Service Letter No. 462, FAA AD 68-7-4 and amendments)","Specific technical terminology requiring aviation engineering knowledge (magnetic particle method, part numbers, serial number ranges)","Date-stamping location described in Note 3 (diamond-shaped gusset plates) adds operational detail"],"plain_english_summary":"This CASA Airworthiness Directive applies to Piper Apache/Aztec PA‑23‑250 aircraft (S/N 2505 onward) using engine mount P/N 31215 and mandates inspections for cracks in the engine mount, with intervals and scope depending on mount manufacture date and hours. \n\nIf cracks are found the mount must be replaced or repaired to the Secretary’s approval (with magnetic particle testing and follow‑up inspections). The rule starts within 50 flight hours and repeats every 100 hours to prevent catastrophic engine separation."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection","history":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection/history","analysis":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection/analysis","conflicts":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection/conflicts","importantCases":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection/important-cases","documents":"/api/acts/ad-pa-23-36-amdt-1-engine-mount-inspection/documents"}}