{"id":"F2005L01761","name":"AD/BELL 222/29 - Drive Hub Studs","slug":"ad-bell-222-29-drive-hub-studs","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":35859,"registerId":"commonwealth-F2005L01761-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Bell Helicopter Textron Canada (BHTC) 22","sectionType":"division","heading":"Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters","content":"### Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters\n\n| AD/BELL 222/29 | Drive Hub Studs | 8/2005 |\n| -------------- | --------------- | ------ |\n\n| Applicability: | All Bell Helicopter Textron Canada (BHTC) (previously manufactured by Bell Helicopter Textron, Inc. (BHTI)) Model 222 helicopters, with drive hub assembly, part number (P/N) 222-010-417-009, installed.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. (a) Remove nuts and washers from the studs which attach spline plate, P/N222-310-418-105/-107, to the drive hub assembly, P/N 222-010-417-009.(b) Visually inspect washers, P/N AN960-416, and mating surface on the spline plate, P/N 222-310-418-105/-107, for any signs of fretting, cracking, or wear.(c) If any fretting or wear is found, replace spline plate, P/N222-310-418-105/-107, and drive hub assembly, P/N 222-010-417-009.(d) If no fretting or wear is found, install new nuts, P/N MS21042L4, and washers, P/N AN960-416, and torque nuts to 100 inch pounds plus friction (tare) torque.2. (a) apply 50 inch-pounds of torque to the spline plate P/N222-310-418-105/-107 retaining nuts.(b) If the nuts do not move, the nut torque is sufficient.(c) If, while performing step (a), one or more of the spline plate P/N222-310-418-105/-107 retaining nuts move prior to reaching 50 inch-pounds, replace spline plate, P/N 222-310-418-105/-107, and drive hub assembly, P/N 222-010-417-009.Note: FAA AD 87-09-02 R2 Amendment 39-6399, refers. |\n| Compliance:    | 1. Unless already accomplished, within 7 days of effective date of this AD.2. After completing the requirements of paragraphs 1 (a) and 1 (b) and then repetitively at intervals not to exceed 50 hours time in service.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n|                | This Airworthiness Directive becomes effective on 4 August 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           |\n\n| Background: | To prevent possible failure of the drive hub studs which could result in loss of flight control and subsequent loss of the helicopter. |\n| ----------- | -------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n18 June 2005","sortOrder":0},{"sectionNumber":"AD/BELL 222/29","sectionType":"part","heading":"AD/BELL 222/29","content":"## AD/BELL 222/29","sortOrder":1},{"sectionNumber":"Drive Hub Studs","sectionType":"part","heading":"Drive Hub Studs","content":"## Drive Hub Studs","sortOrder":2},{"sectionNumber":"8/2005","sectionType":"part","heading":"8/2005","content":"## 8/2005","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"Scope remains narrowly focused on Bell 222 helicopters fitted with drive hub assembly P/N 222‑010‑417‑009 and the spline plate P/N 222‑310‑418‑105/-107. The AD prescribes inspections, torque checks and replacement where wear or movement is detected; it does not expand to other models or unrelated components. The AD references FAA AD 87‑09‑02 R2 but does not, in the text supplied, broaden applicability beyond the listed parts and aircraft."},"complexity_factors":["Technical torque specifications and functional check: requires torquing nuts to 100 inch‑pounds plus friction (tare) torque and a separate 50 inch‑pound movement check (Requirement 1(d); Requirement 2(a)-(c)).","Detailed, part‑numbered actions: multiple specific parts named (drive hub assembly P/N 222‑010‑417‑009; spline plate P/N 222‑310‑418‑105/-107; washers AN960‑416; replacement nuts MS21042L4) increasing inventory and procurement complexity (Applicability; Requirement 1(a), 1(d)).","Short mandatory initial compliance window: actions must be completed within 7 days of the AD's effective date, concentrating scheduling and supply pressure (Compliance 1).","Repetitive inspection interval: mandatory recurring checks at intervals not to exceed 50 flight hours create ongoing maintenance burden (Compliance 2).","Failure triggers replacement of major parts: finding fretting/wear or nut movement requires replacement of both the spline plate and the drive hub assembly, increasing parts and labour costs (Requirement 1(c); Requirement 2(c)).","Operational impact: procedure requires removal and reinstallation of nuts and washers and functional torque testing, causing aircraft downtime and technician labour (Requirement 1(a)-(d); Requirement 2).","Cross‑reference to FAA AD 87‑09‑02 R2: regulatory alignment may require interpretive attention for compliance history and prior corrective actions (Requirement note).","Clear, narrow applicability reduces breadth but raises concentration of cost for affected operators: applies only to Model 222 helicopters with the specified drive hub assembly P/N (Applicability).","Effective date and administrative entry: AD becomes effective 4 August 2005, imposing an immediate legal deadline for compliance planning (Compliance; effective date line)."],"plain_english_summary":"This Airworthiness Directive requires operators of Bell 222 helicopters fitted with drive hub assembly P/N 222-010-417-009 to inspect and secure the spline‑plate studs, replace parts if fretting or movement is found, and perform a torque check. Initial work must be done within seven days and, if clear, repeat checks are required every 50 flight hours. The stated objective is to prevent drive‑hub stud failure and potential loss of control; compliance imposes maintenance, parts and downtime costs on operators."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with a narrow, specific safety purpose — preventing drive hub stud failure in a particular helicopter model. The scope remains tightly focused on the original safety issue without expansion into broader operational or regulatory matters."},"complexity_factors":["Short, single-purpose directive with only 2 main requirements","Specific part numbers referenced (6 distinct P/Ns) but no defined terms section","Simple conditional logic: 'if damage found, replace; if not, reinstall'","Clear compliance timeline (7 days initial, then every 50 hours)","No cross-references to other legislation beyond a note about the related FAA directive","Straightforward mechanical inspection procedure with pass/fail criteria"],"plain_english_summary":"Owners and operators of Bell 222 helicopters fitted with drive hub assembly P/N 222-010-417-009 must inspect and, if needed, replace studs, nuts, washers and the spline plate in the rotor drive hub. This AD requires an initial check within 7 days, a 50 in‑lb torque test, and repeat inspections every 50 flight hours.\n\nIt’s mandatory because failing drive hub studs can lead to catastrophic loss of flight control; noncompliance risks a fatal crash."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-bell-222-29-drive-hub-studs","history":"/api/acts/ad-bell-222-29-drive-hub-studs/history","analysis":"/api/acts/ad-bell-222-29-drive-hub-studs/analysis","conflicts":"/api/acts/ad-bell-222-29-drive-hub-studs/conflicts","importantCases":"/api/acts/ad-bell-222-29-drive-hub-studs/important-cases","documents":"/api/acts/ad-bell-222-29-drive-hub-studs/documents"}}