{"id":"F2008L02517","name":"AD/EMB-145/14 - Main Landing Gear Trailing Arm","slug":"ad-emb-145-14-main-landing-gear-trailing-arm","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74483,"registerId":"commonwealth-F2008L02517-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Embraer EMB-135 and EMB-145 Series Aerop","sectionType":"division","heading":"Embraer EMB-135 and EMB-145 Series Aeroplanes","content":"### Embraer EMB-135 and EMB-145 Series Aeroplanes\n\n| AD/EMB-145/14 | Main Landing Gear Trailing Arm | 8/2008 |\n| ------------- | ------------------------------ | ------ |\n\n| Applicability: | Models EMB-145 and EMB-135 aircraft, equipped with main landing gear part number 2309-2002-001, -002, -003, -004, -005, -006, -009, -010, -501, -502, -503,-504, -505, -506, -507, -508, -509, -510, -511, or -512; or part number2309-3002-501, -502, -503, -504, -505, -506, -507, -508, -509, or -510, with a cardan assembly part number 2309-2041-003 installed. |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Perform a detailed visual inspection of the main landing gear trailing arm for integrity of the sealant and damage at the trailing arm surface, in accordance with EMBRAER Service Bulletin (SB) No. 145-32-0091 original issue, or SB No. 145-32-0091 Revision 1, or later CTA/ANAC approved revision.If any sign of sealant failure or damage at the trailing arm surface is found, before further flight, replace the cardan assembly part number 2309-2041-003 with a part number 2309-2041-401 cardan assembly, and perform a detailed visual inspection of the internal surface of the pivot axle of the trailing arm for corrosion, and repair any damage of the trailing arm, as necessary, in accordance with the Component Maintenance Manual. If corrosion is found, replace pin part number 2309-2050-003 with a new part number 2309-2050-003 pin and apply corrosion protection to the pin, before further flight.2. If no sign of sealant failure or damage at the trailing arm surface is found, repeat the Requirement 1 detailed visual inspection of the main landing gear trailing arm until replacement of the cardan assembly part number 2309-2041-003 with a part number 2309-2041-401 cardan assembly, and accomplishment of the detailed visual inspection of the internal surface of the pivot axle of the trailing arm for corrosion.Note: Brazil CTA AD 2004-08-02 Amdt 39-1039 refers. |\n| Compliance: | 1. Unless already accomplished, before 31 August 2008.2. At intervals not to exceed 5,500 flight hours or 24 months, whichever occurs first. |\n| | This Airworthiness Directive becomes effective on 31 July 2008. |\n\n| Background: | A report was received of a fracture of the main landing gear trailing arm axle due to internal corrosion of the axle. This condition, unless detected and corrected, could result in a take-off or landing accident due to a disconnection between the shock absorber and the trailing arm. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n18 June 2008","sortOrder":0},{"sectionNumber":"AD/EMB-145/14","sectionType":"part","heading":"AD/EMB-145/14","content":"## AD/EMB-145/14","sortOrder":1},{"sectionNumber":"Main Landing Gear Trailing Arm","sectionType":"part","heading":"Main Landing Gear Trailing Arm","content":"## Main Landing Gear Trailing Arm","sortOrder":2},{"sectionNumber":"8/2008","sectionType":"part","heading":"8/2008","content":"## 8/2008","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with a focused, single-purpose scope: addressing a specific safety defect in specific aircraft models. The scope remains tightly constrained to the identified landing gear corrosion risk and has not expanded beyond this original safety purpose."},"complexity_factors":["Specific part number references (over 20 different part numbers listed in applicability)","Conditional logic: different actions required depending on inspection findings (damage found vs. no damage found)","Cross-reference to Brazilian aviation authority directive (CTA AD 2004-08-02)","Reference to external technical documents (Embraer Service Bulletin 145-32-0091 and Component Maintenance Manual)","Dual compliance timeline (one-time deadline plus recurring interval)","Technical aviation terminology requiring domain knowledge (cardan assembly, trailing arm, sealant integrity)"],"plain_english_summary":"This AD mandates inspection of the main landing‑gear trailing arm on certain Embraer EMB‑135/145 aircraft for sealant damage and hidden internal corrosion, and requires replacement of the cardan assembly and further corrosion checks if defects are found. \n\nIt affects owners, operators and maintenance organisations of those aircraft with the listed part numbers — intended to prevent in‑flight landing‑gear failure that could cause a serious accident."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The instrument's scope focuses on specified trailing-arm, cardan and pin part numbers on EMB-135/145 aircraft and prescribes inspections, conditional replacements and recurring intervals to address internal axle corrosion. The text gives no indication the Australian scope departs from that safety objective; it also references a related Brazilian AD but does not expand or narrow the set of affected parts or actions described in this directive."},"complexity_factors":["Wide list of affected part numbers and two aircraft models increases tracking and inventory matching (Applicability).","Conditional, staged requirements: immediate replacement and further internal inspections if sealant failure/damage is found; otherwise repeat inspections until replacement occurs (Requirement).","Recurring compliance intervals — every 5,500 flight hours or 24 months — require ongoing maintenance planning and record-keeping (Compliance).","Mandated use of specified Embraer Service Bulletin revisions or later CTA/ANAC–approved revisions creates an administrative dependency on external approvals (Requirement).","Technical repairs must follow the Component Maintenance Manual; corrosion protection and specific pin replacement add supply-chain and technical workload (Requirement).","A fixed initial compliance deadline (before 31 August 2008) imposes immediate action where not already done (Compliance).","Underlying safety driver is internal axle corrosion that can cause structural fracture and disconnection between shock absorber and trailing arm (Background), increasing the operational urgency and potential for aircraft downtime."],"plain_english_summary":"This Airworthiness Directive requires operators of Embraer EMB-135 and EMB-145 aeroplanes fitted with certain main landing-gear and cardan parts to inspect the trailing-arm sealant and surface for damage, repeat those inspections at set intervals, and replace the cardan assembly or pin and repair/coat parts if corrosion or sealant failure is found. It was issued to prevent axle fracture that could cause a take-off or landing accident. Operators pay for inspections, parts and repairs and must schedule recurring maintenance to comply."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm","history":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm/history","analysis":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm/analysis","conflicts":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm/conflicts","importantCases":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm/important-cases","documents":"/api/acts/ad-emb-145-14-main-landing-gear-trailing-arm/documents"}}