{"id":"F2007L01585","name":"AD/BELL 430/10 - Tail Rotor Pitch Change Mechanism","slug":"ad-bell-430-10-tail-rotor-pitch-change-mechanism","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66126,"registerId":"commonwealth-F2007L01585-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Bell Helicopter Textron Canada (BHTC) 43","sectionType":"division","heading":"Bell Helicopter Textron Canada (BHTC) 430 Series Helicopters","content":"### Bell Helicopter Textron Canada (BHTC) 430 Series Helicopters\n\n| AD/BELL 430/10 | Tail Rotor Pitch Change Mechanism | 7/2007 |\n| -------------- | --------------------------------- | ------ |\n\n| Applicability: | Bell Helicopter Textron Canada (BHTC) Model 430 helicopters serial numbers 49001 through 49122.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | 1. Verify the existing rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions detailed in Alert Service Bulletin (ASB) 430-07-39 dated 9 January 2007 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.2. Determine whether the tail rotor yoke is to be replaced in accordance with ASB 430-07-39, item 3 of Accomplishment Instructions. If required, replace the yoke with an airworthy part.3. Perform a new rigging procedure as per Accomplishment Instructions provided in ASB 430-07-39.Note: Transport Canada AD CF-2007-04 dated 5 April 2007 refers. |\n| Compliance:    | At the next 150 hour or annual inspection but no later than 31 December 2007, unless already accomplished.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n|                | This Airworthiness Directive becomes effective on 5 July 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| Background:    | It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.This AD mandates verification of the tail rotor pitch change mechanism, and new rigging procedures.                                                                                                                                                                                                                                                                                                                                                                            |\n\n![](image.001.png)  \nCharles Lenarcic  \nDelegate of the Civil Aviation Safety Authority\n\n14 May 2007","sortOrder":0},{"sectionNumber":"AD/BELL 430/10","sectionType":"part","heading":"AD/BELL 430/10","content":"## AD/BELL 430/10","sortOrder":1},{"sectionNumber":"Tail Rotor Pitch Change Mechanism","sectionType":"part","heading":"Tail Rotor Pitch Change Mechanism","content":"## Tail Rotor Pitch Change Mechanism","sortOrder":2},{"sectionNumber":"7/2007","sectionType":"part","heading":"7/2007","content":"## 7/2007","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, targeted airworthiness directive addressing a specific safety-of-flight issue with a defined helicopter model. The scope remains precisely limited to the tail rotor pitch change mechanism rigging issue identified in the background, with no expansion beyond the original safety purpose."},"complexity_factors":["Single, clearly defined applicability (specific helicopter model and serial number range)","Three straightforward sequential requirements with explicit reference to external technical document (ASB 430-07-39)","Simple compliance deadline (next inspection or fixed date, whichever comes first)","No defined terms section, no cross-references to other legislation, no conditional exceptions","Background explanation is concise and directly supports the requirement","Total length is extremely short (approximately 200 words of substantive content)"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of Bell 430 helicopters (S/N 49001–49122) to inspect and correct the tail rotor pitch change mechanism per Bell Alert Service Bulletin 430-07-39. Where necessary the tail rotor yoke must be replaced and the mechanism re-rigged by the next 150‑hour or annual inspection, and no later than 31 December 2007. The AD addresses interference risks that could cause tail rotor failure and loss of control."},"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"Scope remains limited to Model 430 helicopters serial numbers 49001–49122 and mandates a one‑time verification, conditional part replacement, and re‑rigging per ASB 430‑07‑39. The instrument corrects rigging procedures because of possible parts interference (Background) but does not expand applicability or create ongoing recurring obligations beyond the specified compliance timeline (Applicability; Requirement; Compliance)."},"complexity_factors":["Technical procedure complexity: requires detailed rigging verification and a new rigging procedure (Requirement; ASB 430-07-39).","Parts decision and replacement: carrier must determine if tail rotor yoke replacement is required and fit an airworthy part if so (Requirement, item 2).","Time-limited compliance window: must be completed at next 150‑hour or annual inspection or by a fixed date (Compliance).","Applicability narrow but specific: affects only Model 430 helicopters serial numbers 49001–49122 (Applicability).","Regulatory dependency: work must follow Alert Service Bulletin or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada (Requirement).","Operator cost and logistics: owners/operators pay for inspection, possible parts procurement and labour; potential scheduling impact to meet the deadline (Requirement; Compliance).","Certification/discretion point: acceptance of later ASB revisions requires approval by the Chief, Continuing Airworthiness, Transport Canada (Requirement).","Reference to related foreign AD: notes Transport Canada AD CF-2007-04 (Note), creating potential cross-jurisdictional coordination."],"plain_english_summary":"This directive requires operators of Bell Helicopter Textron Canada Model 430 helicopters (serial numbers 49001–49122) to verify the tail rotor pitch change mechanism, replace the tail rotor yoke if required, and perform a new rigging procedure per ASB 430‑07‑39. Operators (owners) bear the cost of inspection, any part replacement and labour; work must be done at the next 150‑hour or annual inspection or by 31 December 2007 (Requirement; Compliance)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism","history":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism/history","analysis":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism/analysis","conflicts":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism/conflicts","importantCases":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism/important-cases","documents":"/api/acts/ad-bell-430-10-tail-rotor-pitch-change-mechanism/documents"}}