{"id":"F2010L03121","name":"AD/EMB-145/23 - Main Landing Gear Trailing Arm Pins","slug":"ad-emb-145-23-main-landing-gear-trailing-arm-pins","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":85262,"registerId":"commonwealth-F2010L03121-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-145/23 | Main Landing Gear Trailing Arm Pins | 24/2010 |\n| ------------- | ----------------------------------- | ------- |\n\n| Applicability: | Embraer model EMB-135BJ, EMB-135ER, EMB-135KE, EMB-135KL,EMB-135LR, EMB-145, EMB-145EP, EMB-145ER, EMB-145EU, EMB-145LR, EMB-145LU, EMB-145MK, EMB-145MP, EMB-145MR and EMB-145XR airplanes.                                                                                                                                                                                                                                                  |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Action in accordance with ANAC Airworthiness Directive 2009-02-01.Note: Embraer Service Bulletin Nos. 145-32-0122, and 145-52-0047, or145LEG-32-0033 and 145LEG-52-0014 refer.                                                                                                                                                                                                                                                                |\n| Compliance:    | As stated in the requirement document with a revised effective date of 13 December 2010 and a revised Compliance time of 2 months from the effective date, unless accomplished previously.                                                                                                                                                                                                                                                    |\n|                | This Airworthiness Directive becomes effective on 13 December 2010.                                                                                                                                                                                                                                                                                                                                                                           |\n| Background:    | It has been found occurrences of main landing gear (MLG) trailing arm pins broken due to a fatigue mechanism induced by an excessive torque applied during the assemblage of auxiliary door support attachment and consequent deformation of the MLG trailing arm axle. A broken pin can lead to loss of the MLG trailing arm axle, disconnecting the trailing arm from the main strut, which affects the airplane controllability on ground. |\n\n![](image.001.png)\n\nMike Higgins  \nDelegate of the Civil Aviation Safety Authority\n\n25 November 2010","sortOrder":0},{"sectionNumber":"AD/EMB-145/23","sectionType":"part","heading":"AD/EMB-145/23","content":"## AD/EMB\\-145/23","sortOrder":1},{"sectionNumber":"Main Landing Gear Trailing Arm Pins","sectionType":"part","heading":"Main Landing Gear Trailing Arm Pins","content":"## Main Landing Gear Trailing Arm Pins","sortOrder":2},{"sectionNumber":"24/2010","sectionType":"part","heading":"24/2010","content":"## 24/2010","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"This instrument does not expand the set of affected aeroplane models or alter the core corrective actions; it revises the implementation timeline compared with the referenced ANAC AD by setting a revised effective date of 13 December 2010 and a compliance period of two months from that date (see 'Requirement' and 'Compliance' entries)."},"complexity_factors":["Cross-reference to a foreign regulator's directive (ANAC Airworthiness Directive 2009-02-01) — requires operators to follow an external document rather than prescribing actions directly.","Multiple referenced Embraer Service Bulletins (145-32-0122, 145-52-0047, 145LEG-32-0033, 145LEG-52-0014) which may contain technical procedures and variants.","Applicability covers many EMB-135 and EMB-145 variants, requiring fleet-level compliance tracking.","Safety-critical mechanical failure (fatigue of MLG trailing-arm pins) driven by specific assembly torque errors — inspections/repairs require qualified maintenance resources.","Administrative change: revised effective date (13 Dec 2010) and a short compliance window (2 months) imposes scheduling and logistical constraints on operators."],"plain_english_summary":"This Airworthiness Directive requires operators of Embraer EMB‑135 and EMB‑145 series aeroplanes to carry out the inspections and corrective actions set out in ANAC Airworthiness Directive 2009‑02‑01 (using the referenced Embraer service bulletins), with a revised effective date of 13 December 2010 and a two‑month compliance window. It responds to fatigue cracking of main landing gear trailing‑arm pins caused by excessive assembly torque; a broken pin can disconnect the trailing arm and impair ground controllability."},"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 single-issue Airworthiness Directive addressing a specific mechanical defect. It has not expanded beyond its original purpose of mandating inspection/repair of main landing gear trailing arm pins on specified Embraer aircraft."},"complexity_factors":["Very short document (approximately 250 words of substantive content)","Only 1 defined term implicitly used (the aircraft model designations)","No nested conditional logic or exceptions","Single cross-reference to external document (ANAC Airworthiness Directive 2009-02-01)","Simple compliance structure: do X by Y date unless already done","No internal Part or Division structure","Background section provides clear causal explanation without legal sub-clauses"],"plain_english_summary":"This mandatory AD requires owners and operators of specified Embraer EMB‑135/145 family jets, and their maintenance organisations, to inspect and repair main landing gear trailing arm pins after fatigue failures traced to overtightening. \n\nCompliance must follow Brazil’s ANAC 2009‑02‑01 and Embraer service bulletins, with corrective action within two months of 13 December 2010. It prevents landing‑gear collapse on ground, takeoff or landing."}},"importantCases":[],"_links":{"self":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins","history":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins/history","analysis":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins/analysis","conflicts":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins/conflicts","importantCases":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins/important-cases","documents":"/api/acts/ad-emb-145-23-main-landing-gear-trailing-arm-pins/documents"}}