{"id":"F2007L02448","name":"AD/BELL 222/24 Amdt 1 - Main Rotor Hydraulic Actuator Support","slug":"ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":67916,"registerId":"commonwealth-F2007L02448-current","compilationNumber":null,"startDate":"2026-04-02","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 222/24 Amdt 1 | Main Rotor Hydraulic Actuator Support | 9/2007 |\n| --------------------- | ------------------------------------- | ------ |\n\n| Applicability: | Model 222, 222B, 222U, and 230 helicopters, with a main rotor hydraulic actuator support part number 222-040-125-001 installed.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. a. Visually inspect the main rotor hydraulic actuator support for the presence of all dowel pins and for sealant between the support and the transmission. If any pin is missing, or if no sealant is visible, before further flight, remove the support and further inspect the support, transmission case, studs, and dowel pins in accordance with the Accomplishment Instructions paragraphs 5 through 7 of BHTC Alert Service Bulletin (ASB) 222-00-86, 222U-00-57 or 230-00-18, as applicable. Repair or replace any unserviceable support, transmission case, stud, or dowel pin before further flight.b. Verify the torque of the support attaching nuts. Upper nuts must not rotate at a torque less than 40 inch-pounds. Lower nuts must not rotate at a torque less than 90 inch-pounds(i) If two or more upper nuts rotate at a torque less than 40 inch-pounds or two or more lower nuts rotate at a torque less than 90 inch-pounds, before further flight, remove the support and further inspect the support, transmission case, studs, and dowel pins in accordance with the Accomplishment Instructions paragraph 5 through 7 of the applicable ASB. Repair or replace any unserviceable support, transmission case, stud, or dowel pin before further flight.(ii) If less than two upper nuts rotate at a torque less than 40 inch-pounds or less than two lower nuts rotate at a torque of less than 90 inch pounds, before further flight, re-torque the upper nut to 50 to 70 inch-pounds plus tare and the lower nut to 100 to 140 inch-pounds plus tare.2. After re-installing a support for any reason, verify the torque of the nuts in accordance with Requirement 1.Note: Transport Canada ADCF-2000-29 and FAA AD 2001-01-51 refer. |\n\n| Compliance: | 1. Unless the initial inspection is already accomplished, within 25 hours time in service after 30 August 2007. Thereafter at intervals not to exceed 600 hours time in service or 12 months, whichever occurs first.2. At not less than 20 hours time in service, nor more than 30 hours time in service.The compliance time for Requirement 2 remains unchanged by this issue of the Directive. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Amendment becomes effective on 30 August 2007.                                                                                                                                                                                                                                                                                                                                               |\n| Background: | The FAA received a report of the failure of a main rotor hydraulic actuator support, resulting in an accident of a Model 222U helicopter.Amendment 1 is issued to include the Model 230 helicopter in applicability.                                                                                                                                                                              |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n11 July 2007","sortOrder":0},{"sectionNumber":"AD/BELL 222/24 Amdt 1","sectionType":"part","heading":"AD/BELL 222/24 Amdt 1","content":"## AD/BELL 222/24 Amdt 1","sortOrder":1},{"sectionNumber":"Main Rotor Hydraulic Actuator Support","sectionType":"part","heading":"Main Rotor Hydraulic Actuator Support","content":"## Main Rotor Hydraulic Actuator Support","sortOrder":2},{"sectionNumber":"9/2007","sectionType":"part","heading":"9/2007","content":"## 9/2007","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"This Amendment 1 expands the original directive's scope by adding the Model 230 helicopter to the applicability. The original AD (implied by the amendment note) only covered the 222 series models (222, 222B, 222U). The amendment maintains the same technical requirements and safety intent but broadens the fleet coverage to include an additional helicopter model that shares the same potentially defective part."},"complexity_factors":["Multiple conditional branches in Requirement 1 (visual inspection outcomes, torque test outcomes with thresholds for 'two or more' vs 'less than two' nuts)","Cross-references to three different Bell Alert Service Bulletins (ASB 222-00-86, 222U-00-57, 230-00-18) depending on helicopter model","Specific torque measurements with ranges and 'plus tare' adjustments (technical aviation terminology)","Dual compliance timelines (initial 25 hours, recurring 600 hours/12 months, and post-reinstallation 20-30 hours)","Reference to foreign regulatory instruments (Transport Canada ADCF-2000-29 and FAA AD 2001-01-51)","Nested applicability criteria (specific helicopter models AND specific part number)"],"plain_english_summary":"This AD requires owners/operators of Bell 222/222B/222U and newly included Model 230 helicopters fitted with main rotor hydraulic actuator support P/N 222-040-125-001 to perform mandated inspections, torque checks, and corrective maintenance of that support before flight. It responds to a support failure that led to loss of helicopter control; Amendment 1 simply adds Model 230 to the affected fleet."},"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":5,"scope_assessment":{"changed":true,"description":"This Amendment (Amdt 1) expanded the directive’s applicability to include the Model 230 helicopter in addition to Models 222, 222B and 222U. The core requirements (inspections, torque checks, removal/repair procedures and compliance intervals) remain the same; the scope change increases the population of affected aircraft and therefore increases the number of operators and maintenance organisations subject to the directive."},"complexity_factors":["Multiple conditional branches in Requirement 1 (1a, 1b, including counts of nuts that fail torque thresholds)","References to external manufacturer documents (ASB paragraphs 5–7) for detailed inspection and repair steps","Numeric torque thresholds with two-tiered responses (lower threshold triggers removal if count>=2; intermediate threshold requires re‑torque to a higher range)","Recurring compliance schedule and a separate short follow‑up window after re‑installation (initial within 25 hours, then 600 hours/12 months; re‑verification 20–30 hours)","Technical term requiring operational knowledge (\"plus tare\") and need for calibrated torque tools and trained staff","Cross‑references to other authorities’ ADs (Transport Canada, FAA) — operators must reconcile multiple documents","Specific part‑number applicability limits the directive to a subset of fleet"],"plain_english_summary":"**What this directive does (mechanics)**\n\n- It requires operators of Bell 222, 222B, 222U and 230 helicopters that have main rotor hydraulic actuator support part number 222-040-125-001 installed to carry out specific visual and torque inspections, and to take corrective action where deficiencies are found. (Applicability)\n\n- Requirement 1a: Visually inspect the support for the presence of all dowel pins and for sealant between the support and the transmission. If any dowel pin is missing, or if no sealant is visible, the support must be removed and a more detailed inspection carried out of the support, transmission case, studs and dowel pins following the manufacturer’s Accomplishment Instructions (ASB paragraphs 5–7). Any unserviceable parts must be repaired or replaced before further flight. (Requirement 1a)\n\n- Requirement 1b: Check the torque of the support attaching nuts. Upper nuts must not turn at a torque less than 40 inch‑pounds; lower nuts must not turn at a torque less than 90 inch‑pounds. There are three possible outcomes:\n  - If two or more upper nuts turn at <40 in‑lb, or two or more lower nuts turn at <90 in‑lb, remove the support and carry out the detailed inspection and repairs described above before further flight. (Requirement 1b(i))\n  - If fewer than two upper nuts turn at <40 in‑lb or fewer than two lower nuts turn at <90 in‑lb, re‑torque the nuts to the higher specified ranges before further flight: upper nuts 50–70 in‑lb plus tare, lower nuts 100–140 in‑lb plus tare. (Requirement 1b(ii))\n  - After any re‑installation of the support for any reason, verify the torques again as per Requirement 1. (Requirement 2)\n\n- The detailed inspection and repair steps referenced above are those in Bell Helicopter Textron Canada Alert Service Bulletins (ASB 222‑00‑86, 222U‑00‑57, or 230‑00‑18 as applicable). The Directive also cross‑references related Transport Canada and FAA airworthiness directives. (Note)\n\n**When inspections must be done (compliance times)**\n\n- Initial inspection: within 25 hours time‑in‑service after 30 August 2007 unless already done. Thereafter repeat inspections at intervals not exceeding 600 hours time‑in‑service or 12 months, whichever occurs first. (Compliance 1)\n\n- The re‑installation verification (Requirement 2) must be done between 20 and 30 hours time‑in‑service after re‑installation. The compliance time for Requirement 2 is unchanged by this amendment. (Compliance 2)\n\n**Why this was issued (stated reason)**\n\n- The FAA reported a failure of a main rotor hydraulic actuator support that resulted in an accident to a Model 222U helicopter. The directive’s stated purpose is to detect missing dowel pins, missing sealant, loose attaching nuts, or other deterioration that could lead to support failure and loss of main rotor hydraulic actuation. The published background for this amendment notes that Model 230 was added to the applicability. (Background)\n\n**Who it affects and who pays**\n\n- Affected parties: owners/operators of Bell 222/222B/222U/230 helicopters fitted with support part number 222‑040‑125‑001, aircraft maintenance organisations and licensed maintenance personnel who perform the inspections and repairs. (Applicability, Requirements)\n\n- Who pays: the operator pays for labor (inspection and torque checks), any removal/repair/replacement parts, and aircraft downtime while work is done. Maintenance organisations may invoice for labour and parts. There may be additional indirect costs if the aircraft is out of service for an extended period awaiting parts or repair.\n\n**What behaviour changes**\n\n- Operators must add the specified visual and torque checks to their maintenance schedule at the stated initial and recurrent intervals. If problems are found they must remove the support and follow the ASB repair/inspection steps (paragraphs 5–7). If only limited nut looseness is found they must re‑torque to higher specified values (50–70 in‑lb upper; 100–140 in‑lb lower, plus tare). After any re‑installation the torque verification must be repeated within 20–30 hours TIS.\n\n**Analytical overview of trade‑offs, costs and implementation risks**\n\n- Safety rationale vs cost: The directive’s stated safety aim (preventing structural failure of the hydraulic actuator support) is implemented through inspections and thresholded corrective action. The direct costs are maintenance labour, torque‑measuring equipment use, potential replacement parts (support, studs, dowel pins, or transmission case repairs), and aircraft downtime. These are borne by operators. (Requirements; Compliance)\n\n- Compliance burden and predictability: The inspection schedule (initial within 25 hours, then every 600 hours or 12 months) is straightforward to budget into maintenance cycles. The re‑installation verification window (20–30 hours) imposes a short‑term follow up obligation after any support work.\n\n- Operational disruption risk: If the inspection detects missing pins or sealant, or multiple loose nuts, the support must be removed and further inspected/ repaired before further flight. That can ground an aircraft until parts or repairs are completed, creating concentrated costs for the affected operator.\n\n- Technical implementation risks: Accurate assessment depends on correct visual inspection (sealant may be hard to assess) and torque checks (requires calibrated torque tools and trained personnel). The instruction to re‑torque ‘plus tare’ requires staff to understand and apply torque sequencing and tare compensation correctly; mistakes could leave a nut under‑ or over‑torqued.\n\n- Reliance on external documents: The AD delegates detailed removal/inspection/repair technique to the Bell ASBs (paragraphs 5–7). Operators must have and follow those manufacturer procedures to comply; this transfers procedural detail to the manufacturer documents and means compliance requires access to and correct application of those ASBs. (Requirement references)\n\n- Market effects: The directive imposes a routine maintenance cost on affected operators and increases demand for qualified maintenance work and replacement parts for the specific support part number. It does not restrict ownership, sale, or operation beyond the maintenance requirements; independent maintenance organisations can perform the work provided they meet regulatory and licensing requirements.\n\n- Incentives and behaviour: Operators have a clear incentive to comply to avoid forced grounding and to reduce safety risk. There is also an incentive to ensure correct initial installation and sealant application (to avoid repeated inspections/repairs). Maintenance organisations have an incentive to ensure torque equipment calibration and staff competence to avoid costly rework.\n\n**Concrete implementation points for operators**\n\n- Confirm whether your helicopter has part number 222‑040‑125‑001 installed; if not, the AD does not apply. (Applicability)\n\n- If it does, schedule the initial inspection within 25 hours TIS from the effective date if not already done, and then at 600‑hour or 12‑month intervals. Keep records of the torque measurements and any removal/repairs done per the ASB instructions.\n\n- If you remove or reinstall the support for any reason, plan the 20–30 hour TIS torque re‑verification. (Requirement 2)\n\n**Official claim vs practical costs**\n\n- The official claim is that these steps will detect and prevent support failure (Background; Requirements). Practically, this will reduce but not eliminate risk — effectiveness depends on quality of inspection/repair, availability of parts, and proper torque application. The main trade‑off is maintenance cost and potential aircraft downtime versus reduced likelihood of a support failure that could lead to an accident."}},"importantCases":[],"_links":{"self":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support","history":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support/history","analysis":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support/analysis","conflicts":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support/conflicts","importantCases":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support/important-cases","documents":"/api/acts/ad-bell-222-24-amdt-1-main-rotor-hydraulic-actuator-support/documents"}}