{"id":"F2007L01569","name":"AD/SMA/3 - Engine Primary Exhaust Assembly","slug":"ad-sma-3-engine-primary-exhaust-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66083,"registerId":"commonwealth-F2007L01569-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"SMA Piston Engines","sectionType":"division","heading":"SMA Piston Engines","content":"### SMA Piston Engines\n\n| AD/SMA/3 | Engine Primary Exhaust Assembly | 7/2007 |\n| -------- | ------------------------------- | ------ |\n\n| Applicability: | Société de Motorisations Aéronautiques (SMA) SR305-230 or SR305-230-1 engines fitted with an exhaust collector assembly having a part number (P/N) SF01080014-0.Note 1: These engines are known to be installed on, but not limited to, Cessna 182 series and Reims F182 series aeroplanes.                                                                                                                                                                                                      |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | 1. a. Perform a visual inspection in the area of the TIT probe mount weld for cracks as detailed in SMA Service Bulletin No. SB-01-78-001 revision 3 dated 27 March 2007 or later NAA approved revisions.b. If cracks in the exhaust collector assembly are found, replace the exhaust collector assembly.2. Repeat the actions in Requirement 1 of this AD.3 Replace the exhaust collector assembly P/N SF01080014-0 with a serviceable part.Note 2: EASA AD 2007-0127 dated 7 May 2007 refers. |\n| Compliance:    | 1. a. At 30 +/- 2 exhaust collector assembly flight hours since new.b. Before further flight after the effective date of this AD.2. At 40 +/- 2 exhaust collector assembly flight hours since new.3. At or before 50 exhaust collector assembly flight hours since new.                                                                                                                                                                                                                          |\n|                | This Airworthiness Directive becomes effective on 5 July 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n\n| Background: | Several occurrences of cracks on the exhaust collector assembly have been reported in service. Failure of the engine primary exhaust can lead to a loss of engine manifold pressure and may result in a loss of engine power. In some recent occurrences, cracking has appeared near the weld of the Turbine Inlet Temperature (TIT) probe support. This eventually led to an open hole in the exhaust collector assembly. The resulting loss of engine power resulted in an emergency landing. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n24 May 2007","sortOrder":0},{"sectionNumber":"AD/SMA/3","sectionType":"part","heading":"AD/SMA/3","content":"## AD/SMA/3","sortOrder":1},{"sectionNumber":"Engine Primary Exhaust Assembly","sectionType":"part","heading":"Engine Primary Exhaust Assembly","content":"## Engine Primary Exhaust Assembly","sortOrder":2},{"sectionNumber":"7/2007","sectionType":"part","heading":"7/2007","content":"## 7/2007","sortOrder":3}],"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":2,"scope_assessment":{"changed":false,"description":"This is a standard, targeted airworthiness directive addressing a specific safety defect in a specific engine component. The scope remains precisely limited to the exhaust collector assembly cracking issue identified in the background, with no evidence of scope creep or expansion beyond the original safety purpose."},"complexity_factors":["Single, narrow technical scope focused on one specific engine part (P/N SF01080014-0)","Only 3 defined compliance actions with clear time intervals","Minimal cross-referencing (only one external reference to EASA AD 2007-0127 and one SMA Service Bulletin)","No nested exceptions or conditional logic — requirements apply uniformly to all affected engines","Short document length with straightforward tabular format","Single applicability criterion based on engine model and part number"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections and replacement of exhaust collector assembly SF01080014-0 on SMA SR305-230 and SR305-230-1 engines (commonly installed on Cessna 182s) after reported cracking that has led to engine power loss and emergency landings. Operators must inspect within 30 flight hours (or immediately if already fitted), re-inspect every 40 hours, and replace the part before 50 flight hours to prevent sudden engine failure."},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"The directive addresses a narrowly defined mechanical safety issue (cracking of a specific exhaust collector assembly P/N) and stays within that original safety purpose. It does not broaden applicability beyond the engines fitted with the specified part number, nor does it add unrelated requirements. The instrument prescribes inspections and replacement directly tied to the reported failure mode and therefore has not expanded in scope beyond its original technical intent."},"complexity_factors":["Short document with a single, focused safety problem (cracking at the TIT probe weld)","Clear applicability: only SMA SR305-230 / SR305-230-1 engines fitted with exhaust collector P/N SF01080014-0","Three-step Requirement (inspect, repeat inspect, replace) with simple conditional (if cracks found -> replace)","Specific, short compliance windows with tolerances (30 ± 2 h, 40 ± 2 h, replace by 50 h)","Reference to one Service Bulletin (SB-01-78-001 Rev 3) and one external AD (EASA AD 2007-0127) rather than many cross-references","Few defined terms and no nested exceptions or multi‑layered conditions","Notes clarifying known aircraft types but not expanding applicability"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- It requires operators of certain SMA piston engines to inspect and, if necessary, replace the primary exhaust (exhaust collector assembly) that has part number SF01080014-0.\n- Specifically, a visual inspection of the weld area where the Turbine Inlet Temperature (TIT) probe is mounted must be carried out in accordance with SMA Service Bulletin SB-01-78-001 (Rev 3 or later NAA‑approved revision). If cracking is found, the exhaust collector assembly must be replaced. After initial inspection(s), the exhaust collector assembly P/N SF01080014-0 must be replaced with a serviceable part by 50 flight hours since new. (See the Requirement and Compliance sections.)\n\n**Who is affected**\n\n- Owners and operators of Société de Motorisations Aéronautiques (SMA) SR305-230 or SR305-230-1 engines that are fitted with an exhaust collector assembly P/N SF01080014-0. The AD notes these engines are known to be installed on, but not limited to, Cessna 182 and Reims F182 aeroplanes.\n- Maintenance organisations and mechanics who perform the inspections and any required replacements.\n\n**Why it matters (the stated safety problem)**\n\n- The directive responds to service reports of cracks in the exhaust collector assembly near the TIT probe support weld. If the exhaust collector fails, it can cause a loss of engine manifold pressure and reduced engine power; some occurrences led to emergency landings. The AD’s stated purpose (as reflected in the Background and the cross-reference to EASA AD 2007-0127) is to detect and remove cracked assemblies before they fail.\n\n**How it works in practice (timing and actions)**\n\n- Initial inspection: perform a visual inspection of the TIT probe mount weld area as specified in the referenced SMA Service Bulletin. The Compliance table requires this at 30 ± 2 flight hours since the exhaust collector assembly was new, and also explicitly before further flight after the AD’s effective date.\n- Repeat inspection: perform the inspection again at 40 ± 2 flight hours since new.\n- Mandatory replacement: replace the exhaust collector assembly P/N SF01080014-0 with a serviceable part at or before 50 flight hours since new.\n\n**Practical consequences, costs and implementation issues**\n\n- Who pays: aircraft owners/operators pay for the inspections, labour, and any replacement part and associated installation costs. Maintenance workshops receive the inspection and repair revenue.\n- Operational impact: the inspection and replacement schedule is compressed (three actions all within 50 flight hours). That can require prioritising affected aircraft for maintenance, potential short-term grounding if parts are not available, and scheduled downtime. The AD does not specify who supplies a \"serviceable part\" or whether a redesigned/strengthened part is required—operators must follow the service bulletin and any local approvals.\n- Inspectability and detection risk: the directive mandates a visual inspection of the weld area. The effectiveness of that inspection depends on accessibility of the weld, lighting, inspector skill, and whether any cracking is readily visible. If the weld area is hard to access, further disassembly or non‑destructive testing may be needed in practice (the Service Bulletin will provide the method). This introduces implementation risk and variability in outcomes.\n- Supply and market effects: replacement demand is concentrated on owners of affected engines; manufacturers and maintenance providers may gain concentrated revenue from parts and repairs. If supply of replacement assemblies is limited, operators face higher downtime or costs.\n- Behavioural responses: operators may accelerate replacement, restrict flights until a serviceable part is fitted, or prioritise inspections for aircraft used for commercial or higher‑risk operations.\n\n**References and instructions to follow**\n\n- The AD explicitly requires following SMA Service Bulletin SB-01-78-001 (Revision 3 or later NAA-approved revision) for the inspection details (Requirement). It also refers to EASA AD 2007-0127 for related material.\n\n**Net effect (summary sentence)**\n\n- The AD forces a quick inspection-and-replace cycle on a specific exhaust collector assembly (P/N SF01080014-0) fitted to specified SMA SR305 engines to mitigate reported cracks that can cause loss of engine power. It shifts inspection, replacement and downtime costs onto aircraft owners/operators and places the practical burden of detection and part supply on maintenance providers and manufacturers."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly","history":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly/history","analysis":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly/analysis","conflicts":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly/conflicts","importantCases":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly/important-cases","documents":"/api/acts/ad-sma-3-engine-primary-exhaust-assembly/documents"}}