{"id":"F2006B03926","name":"AD/BEECH 400/23 - Engine Mount","slug":"ad-beech-400-23-engine-mount","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":43535,"registerId":"commonwealth-F2006B03926-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# ![](image.001.png)  \nAIRWORTHINESS DIRECTIVE\n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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\nBeechcraft 400 Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/BEECH 400/23 Engine Mount 4/2002 DM","sectionType":"part","heading":"AD/BEECH 400/23 Engine Mount 4/2002 DM","content":"# AD/BEECH 400/23 Engine Mount 4/2002 DM\n\nApplicability: Model 400 series aircraft, serial numbers RJ-1 through RJ-65.\n\nModel 400A series aircraft, serial numbers RK-1 and subsequent. Model 400T series aircraft, serial numbers TT-1 through TT-180. Model 400T-1 series aircraft, serial numbers TX-1 through TX-11.\n\nRequirement: Perform a fluorescent penetrant inspection to detect cracking in the radius of the cutout of the aft flange of the left engine forward carry-through mount bracket, in accordance with Raytheon Safety Communique No. 189, Revision 1, dated January 2002.\n\nIf any cracking is detected, before further flight, replace the cracked part with a new bracket and fitting in accordance with Raytheon Maintenance Manual, Chapter 54-40-\n\n00. The replacement parts are identified in the Requirement document.\n\nNote: FAA AD 2002-01-23 Amdt 39-12617 refers.\n\nCompliance: At the later of the following times:\n\nBefore the accumulation of 1,500 total flight hours, or;\n\nWithin 25 flight hours or 14 days after 27 February 2002, whichever occurs first. Repeat thereafter at intervals not to exceed 200 flight hours.\n\nThis Airworthiness Directive becomes effective on 27 February 2002.","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument, as drafted, prescribes inspection and replacement for enumerated serial numbers with specific compliance timings and repeat intervals. There is no text in this document that amends, broadens or narrows those applicability or compliance requirements beyond what is stated."},"complexity_factors":["Technical non‑destructive testing specified (fluorescent penetrant inspection) — requires trained personnel and materials.","Applicability limited by multiple serial‑number ranges across four model variants, requiring record checks.","Dual initial compliance trigger (1,500 total flight hours OR within 25 flight hours/14 days of 27 Feb 2002) adds scheduling complexity for operators.","Recurring inspection interval (every 200 flight hours) imposes ongoing monitoring and logging.","Mandatory replacement before further flight if cracking detected — immediate parts availability and downtime implications.","Dependence on external manufacturer documents (Raytheon Safety Communique No.189 Rev 1 and Raytheon Maintenance Manual Chapter 54‑40‑00) for inspection and replacement procedures.","Cross‑reference to FAA AD 2002‑01‑23 for related authority and technical context."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of specified Beechcraft 400, 400A, 400T and 400T‑1 aeroplanes (particular serial‑number ranges) to inspect the aft flange cutout of the left engine forward carry‑through mount bracket for cracking using fluorescent penetrant, and to replace any cracked bracket before further flight. It sets an initial compliance window (before 1,500 total flight hours or within 25 flight hours/14 days of 27 Feb 2002, whichever is later) and recurring inspections every 200 flight hours. Operators pay for inspections, replacements, downtime and must follow the Raytheon documents cited."},"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":2,"scope_assessment":{"changed":false,"description":"This is a standard, targeted airworthiness directive addressing a specific unsafe condition in a defined aircraft population. The scope remains precisely limited to the engine mount bracket inspection and replacement requirement as originally intended."},"complexity_factors":["Single, specific mechanical component targeted (one bracket on one engine mount)","Clear applicability section with explicit serial number ranges","Straightforward binary requirement: inspect, and if cracked, replace","Simple compliance timeline with two alternative triggers (flight hours or calendar date) plus a recurring interval","Only one external document reference (Raytheon Safety Communique No. 189)","No nested exceptions, conditional logic, or defined terms section","Short document (approximately 250 words)"],"plain_english_summary":"This safety order requires owners and operators of specific Beechcraft 400-series jets to inspect the left engine forward carry‑through mount bracket for fatigue cracks using fluorescent penetrant inspection. If cracks are found the aircraft must be grounded and the bracket replaced before further flight, with inspections repeated every 200 flight hours.\n\nIt affects aircraft owners, operators and maintenance organisations and is urgent because a failed engine mount risks in‑flight engine separation."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-400-23-engine-mount","history":"/api/acts/ad-beech-400-23-engine-mount/history","analysis":"/api/acts/ad-beech-400-23-engine-mount/analysis","conflicts":"/api/acts/ad-beech-400-23-engine-mount/conflicts","importantCases":"/api/acts/ad-beech-400-23-engine-mount/important-cases","documents":"/api/acts/ad-beech-400-23-engine-mount/documents"}}