{"id":"F2008L02286","name":"AD/EMB-145/16 - Ailerons Power Control Actuator and Damper","slug":"ad-emb-145-16-ailerons-power-control-actuator-and-damper","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74201,"registerId":"commonwealth-F2008L02286-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-145/16 | Ailerons Power Control Actuator and Damper | 9/2008 DM |\n| ------------- | ------------------------------------------ | --------- |\n\n| Applicability: | Embraer EMB-145( ) aircraft. |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. For aircraft fitted with Power Control Actuator (PCA) P/N 394900-1003, 394900-1005 or 394900-1007:(a) Perform a repetitive visual inspection of all rod ends and fittings in each PCA (RH and LH) at the aileron and wing structure connection points, using a mirror and flashlight, in accordance with Embraer Service Bulletin No. 145-27-0054 Rev. 2, or later revisions approved by the CTA.(b) If any rod end is found cracked or failed, the PCA must be replaced by PCA P/N 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, in accordance with Embraer Service Bulletin No.145-27-0062, original issue, or later revisions approved by the CTA.(c) If any PCA fitting in the wing or aileron side is found cracked or failed, replace by new reinforced wing or aileron side PCA fittings in accordance with Embraer Service Bulletins Nos. 145-57-0019 Rev. 1 or 145-27-0061 Rev. 1, as applicable, or later revisions approved by the CTA.2. Aircraft with PCA P/N 394900-1003, 394900-1005, 394900-1007, 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007:Install new fittings and reinforcements in accordance with Embraer Service Bulletin Nos. 145-57-0019 Rev. 1 and 145-27-0061 Rev. 1, or later revisions approved by the CTA.3. Aircraft equipped with new ailerons PCA P/N 418800-1001, 418800-1003, 418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, in conjunction with the new PCA fittings and reinforcement provisions as detailed in Requirement 2:Perform the visual inspections in accordance with AMM TASK 27-12-01-212-002-A00, \"Aileron PCA Rod Ends/Fitting, Lugs for Integrity and General Condition\". |\n\n| | Terminating ActionAircraft equipped with new aileron PCA P/N 418800-1001, 418800-1003,418800-9003, 418800-1005, 418800-9005, 418800-1007 or 418800-9007, PCA and damper fittings and reinforcements, and aileron damper P/N 41012130-103 or 41012130-104, installed in production line or by incorporation of the Embraer Service Bulletins Nos. 145-27-0063, original issue (damper installation), 145-27-0061 Rev. 1 (aileron damper fitting and reinforcement installation), 145-57-0019 Rev. 1 (wing damper fitting installation) and 145-27-0062, original issue (PCA installation), or later revisions approved by the CTA, are no longer subject to the provisions of this AD provided the visual inspection of the PCA and damper terminals and fittings at the wing and aileron sides, for structural integrity, established in the EMB-145 MRB document for every 1000 flight hours, are implemented.Note: DAC AD 1999-02-01R6 refers. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Compliance: | For Requirement 1(a).For aircraft equipped with PCA P/N 394900-1003 or 394900-1005, at intervals not exceeding 25 flight hours or 3 operating days, whichever occurs later.For aircraft equipped with PCA P/N 394900-1007, at intervals not exceeding 100 flight hours or 14 operating days, whichever occurs later.For Requirements 1(b) and 1(c).Before later flight.For Requirement 2.Before the aircraft completes 6000 operating cycles.For Requirement 3.At intervals not to exceed 500 flight hours. |\n| | This Airworthiness Directive becomes effective on 29 June 2008. |\n\n| Background: | There have been occurrences of broken rod ends of the aileron PCA in different aircraft, either at the aileron or at the wing structure connection points. Several failures have also occurred in the aileron PCA fittings at the wing side. |\n| ----------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n24 June 2008","sortOrder":0},{"sectionNumber":"AD/EMB-145/16","sectionType":"part","heading":"AD/EMB-145/16","content":"## AD/EMB-145/16","sortOrder":1},{"sectionNumber":"Ailerons Power Control Actuator and Damp","sectionType":"part","heading":"Ailerons Power Control Actuator and Damper","content":"## Ailerons Power Control Actuator and Damper","sortOrder":2},{"sectionNumber":"9/2008 DM","sectionType":"part","heading":"9/2008 DM","content":"## 9/2008 DM","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":false,"description":"The directive, as provided, sets applicability, inspection and replacement requirements, and a conditional terminating action. The text contains no amendment history or indication that the instrument's scope has been altered from an earlier version; therefore a scope change cannot be identified from the supplied document."},"complexity_factors":["Multiple PCA part numbers with different mandated actions and inspection intervals (Requirements 1–3; Compliance).","Different mandatory outcomes: immediate replacement if cracked, retrofit by cycle threshold, or continued periodic inspections (Requirements 1(b),(c); Compliance).","Numerous referenced documents: several Embraer Service Bulletins, AMM task, and CTA approval for later revisions (Requirements; Terminating Action).","Terminating action conditional on combined installation of specific PCA P/Ns, reinforced fittings, and damper, plus MRB inspection implementation (Terminating Action).","Very short inspection intervals for some parts (every 25 flight hours or 3 operating days) creating potential operational disruption and increased maintenance burden (Compliance).","Regulatory discretion over later revisions approved by the CTA creates ongoing dependence on authority approvals and document versions (Requirements; Terminating Action).","Multiple alternate replacement part numbers increase logistical complexity for spare acquisition and maintenance planning (Requirement 1(b); Requirement 2).","Inspections require specific techniques (mirror and flashlight) and AMM task reference, imposing procedural and training requirements (Requirement 1(a); Requirement 3)."],"plain_english_summary":"This directive requires operators of Embraer EMB‑145 aircraft with specified aileron power control actuators to carry out repetitive visual inspections of PCA rod ends and fittings and to replace cracked or failed parts or install reinforced fittings and a damper per Embraer service bulletins. Compliance schedules vary by part number (from 25–100 flight‑hour inspection intervals, replacement before next flight if failed, or retrofit before 6000 cycles). Operators pay for inspections, parts and downtime; CASA (via the Delegate/CTA) enforces and approves service‑bulletin revisions (Requirements; Compliance)."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive format. The scope remains tightly focused on the specific safety defect (aileron PCA rod end failures) and the affected aircraft type. The multiple requirements and part number variations reflect the technical complexity of addressing a hardware defect across different aircraft configurations, not scope creep."},"complexity_factors":["Multiple part number variations (12 different PCA part numbers referenced) with different compliance timelines","Nested conditional requirements: different actions required depending on which PCA part number is installed, whether cracks are found, and whether upgraded parts are already fitted","Cross-references to 6 different Embraer Service Bulletins plus an Aircraft Maintenance Manual task","Terminating action clause with 4 specific service bulletin references and a cross-reference to another AD (DAC AD 1999-02-01R6)","Multiple compliance timeframes: 25 flight hours/3 days, 100 flight hours/14 days, 6000 cycles, 500 flight hours, and 'before later flight'","Technical aviation terminology throughout (PCA, P/N, MRB, AMM TASK, operating cycles vs flight hours)"],"plain_english_summary":"This CASA Airworthiness Directive orders mandatory inspections and repairs for Embraer EMB-145 aileron power control actuators after rod ends and fittings were found cracking and failing. Operators must perform frequent visual checks, replace defective parts with reinforced fittings, and carry out ongoing inspections. It affects EMB-145 operators in Australia (and visiting aircraft) to prevent loss of roll control and ensure flight safety."},"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-145-16-ailerons-power-control-actuator-and-damper","history":"/api/acts/ad-emb-145-16-ailerons-power-control-actuator-and-damper/history","analysis":"/api/acts/ad-emb-145-16-ailerons-power-control-actuator-and-damper/analysis","conflicts":"/api/acts/ad-emb-145-16-ailerons-power-control-actuator-and-damper/conflicts","importantCases":"/api/acts/ad-emb-145-16-ailerons-power-control-actuator-and-damper/important-cases","documents":"/api/acts/ad-emb-145-16-ailerons-power-control-actuator-and-damper/documents"}}