{"id":"F2006B04611","name":"AD/BELL 222/20 - Main Rotor Grip and Flapping Bearing Assembly","slug":"ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":44363,"registerId":"commonwealth-F2006B04611-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BELL 222/20 - Main Rotor Grip and Flapping Bearing Assembly","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters\n\n \n\n# AD/BELL 222/20  Main Rotor Grip and Flapping Bearing Assembly\n\nApplicability: All BHTC Model 222, 222B, and 222U helicopters.\n\n# 11/98\n\nTX\n\n \n\nRequirement: 1. Visually inspect the main rotor hub for obvious signs of fretting between the pitch horn and grip tangs; and between the flapping bearing assemblies and the main rotor yoke assembly.\n\n \n\nNote 1: For mechanical and corrosion limits refer to Bell Component Repair and Overhaul Manual, Volume 2.\n\n \n\n2. Verify the torque of the retaining bolts on the main rotor grips and flapping bearing assemblies as instructed in Part I, Initial Inspection of Bell Alert Service Bulletin 222-98-81 or 222U-98-52, as applicable. If any bolt moves before the torque of 100 foot pounds (136 Nm) is reached, before further flight, remove the pitch horn or flapping bearing, as applicable, for further inspection and possible repair. Re-apply corrosion preventive compound (C-101) MIL-C-16173, Grade 1 to the exposed portions of the bolts and nuts.\n\n \n\nNote 2: Transport Canada AD CF-98-16 refers.\n\n \n\nCompliance: Unless already accomplished, within 10 hours time in service after 7 August 1998.\n\n \n\nThis airworthiness directive becomes effective on 7 August 1998.\n\n \n\nBackground: Fatigue cracks at the bolt holes of the main rotor pitch horn, part number 222-011- 104-101, were reported. Also, the same main rotor hub assembly had a fatigue crack in the flapping bearing assembly, part number 222-310-114-111. The cracks were found to have originated at fretting points due to loss of torque on the bolts.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive's scope matches the stated safety concern: it applies to all listed Bell 222 variants and mandates inspections and torque checks within 10 hours to address fatigue cracks originating at fretting due to loss of bolt torque (Applicability; Requirement 1–2; Compliance). There is no indication in the text that the scope departs from the incident-driven intent described in the Background."},"complexity_factors":["Multiple discrete tasks: visual fretting inspection and bolt torque verification with follow-up removal/repair if bolts move (Requirement 1–2).","References to external technical sources for limits and procedures: Bell Component Repair and Overhaul Manual, Volume 2 and Bell Alert Service Bulletin 222-98-81 / 222U-98-52 (Requirement 1 note; Requirement 2).","A precise mechanical threshold specified (100 foot pounds / 136 Nm) for bolt torque that governs corrective action (Requirement 2).","Mandatory re-application of a specified corrosion-preventive compound (C-101 MIL-C-16173, Grade 1) after work (Requirement 2).","Short compliance window (within 10 hours time in service after 7 August 1998) creating scheduling and operational disruption risk (Compliance).","Applicability to all BHTC Model 222, 222B and 222U helicopters increases the population affected (Applicability)."],"plain_english_summary":"This airworthiness directive requires operators of Bell 222, 222B and 222U helicopters to inspect the main rotor hub for fretting and to verify/torque the retaining bolts on rotor grips and flapping bearings, removing parts for repair if bolts move (Requirement 1–2). It must be completed within 10 flight hours. The directive responds to reported fatigue cracks traced to bolt loosening; it shifts inspection, repair and corrosion-prevention costs and operational downtime to aircraft operators."},"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":3,"scope_assessment":{"changed":false,"description":"This is a discrete, time-bound safety directive addressing a specific mechanical defect in a defined aircraft type. It has not expanded beyond its original purpose of mandating inspections for fatigue cracks in main rotor components."},"complexity_factors":["Short, single-purpose directive with only 2 main requirements","Minimal defined terms (relies on external technical manuals for limits)","Simple conditional logic: 'If bolt moves before torque reached → remove for inspection'","Single cross-reference to Canadian aviation authority (Transport Canada AD CF-98-16)","Clear compliance deadline (10 hours time in service after 7 August 1998)","No nested exceptions or layered conditions"],"plain_english_summary":"This CASA Airworthiness Directive requires operators and maintainers of Bell 222, 222B and 222U helicopters in Australia to inspect main rotor connections for fretting and loose bolts, verify bolt torque to prevent movement, and reapply specified corrosion protection.  \n\nIt responds to discovered fatigue and wear in the main rotor hub that could cause catastrophic rotor failure, so compliance is mandatory to keep affected aircraft airworthy and safe."}},"importantCases":[],"_links":{"self":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly","history":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly/history","analysis":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly/analysis","conflicts":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly/conflicts","importantCases":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly/important-cases","documents":"/api/acts/ad-bell-222-20-main-rotor-grip-and-flapping-bearing-assembly/documents"}}