{"id":"F2006B06467","name":"AD/R44/17 - Tail Rotor Pitch Control Assembly","slug":"ad-r44-17-tail-rotor-pitch-control-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":47956,"registerId":"commonwealth-F2006B06467-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# AIRWORTHINESS DIRECTIVE\n\n![](image.001.png)\n\n![](image.001.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\nRobinson R44 Series Helicopters","sortOrder":0},{"sectionNumber":"AD/R44/17 Tail Rotor Pitch Control Assem","sectionType":"part","heading":"AD/R44/17 Tail Rotor Pitch Control Assembly 4/2003","content":"# AD/R44/17 Tail Rotor Pitch Control Assembly 4/2003\n\nDM\n\nApplicability: Model R44 helicopters, with serial numbers up to and including 1208, except serial numbers 1143, 1165, 1183, 1189, 1192, 1196, 1197, 1198, 1200, 1203, and 1204,\n\nwith tail rotor pitch control assembly, part number C031-1, Revision G or prior, installed.\n\nRequirement: Inspect the tail rotor pitch control assembly for roughness or binding of the pitch control bearings by hand-rotating the pitch control bearing housing in accordance with Robinson Helicopter Company Service Bulletin SB-43A Revision A, dated 10 June 2002.\n\nIf the housing does not rotate freely, before further flight, replace the unserviceable pitch control assembly with a serviceable assembly.\n\nNote: FAA AD 2003-04-05 Amdt 39-13053 refers.\n\nCompliance: Within 20 hours time in service after 26 March 2003 for the initial inspection, unless already accomplished. Inspect thereafter at intervals not to exceed 300 hours time in service or 12 months, whichever occurs first.\n\nThis Airworthiness Directive becomes effective on 5 March 2003.\n\nBackground: The FAA received reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on Model R22 helicopters. Although there have been no reported failures on the Model R44 helicopters, the design of the pitch control assembly makes it susceptible to the same failures as have occurred on the Model R22 helicopter. Undetected bearing corrosion could lead to bearing failure and subsequent loss of directional control of the helicopter.\n\n![Signature of David Alan Villiers Delegate of the Civil Aviation Safety Authority](image.002.jpeg)  \n\nDavid Alan Villiers\n\n![](image.001.png)Delegate of the Civil Aviation Safety Authority 27 February 2003","sortOrder":1}],"analysis":{"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The AD targets the tail-rotor pitch control assembly and specific serial numbers/part revisions to address reported bearing lubrication/corrosion risks noted by the FAA. It confines action to the specified parts and serials and does not broaden applicability beyond those limits or add new failure modes in the text."},"complexity_factors":["Applicability narrowed by model, serial-number range and explicit serial exceptions (Applicability) — requires checking serial against list.","Part/revision dependency: only assemblies P/N C031-1 Revision G or earlier are affected (Applicability).","Inspection procedure delegated to external manufacturer document Robinson SB-43A Rev A (Requirement) — operators must obtain and follow that SB.","Dual compliance metric: initial inspection deadline (20 hrs TIS after 26 Mar 2003) and recurring intervals by flight hours or calendar time (300 hours or 12 months) (Compliance).","Mandatory grounding risk: unserviceable assembly must be replaced before further flight (Requirement) — immediate operational impact and replacement cost to operator.","Cross-reference to FAA AD (Note) increases interpretive reliance on related foreign AD information.","Background links cause to prior R22 reports (Background) but extends preventive action to R44s despite no reported R44 failures — affects scope of preventive maintenance."],"plain_english_summary":"This AD requires owners/operators of Robinson R44 helicopters (serials up to 1208, with some exceptions) with tail-rotor pitch control assembly P/N C031-1 Rev G or earlier to hand‑inspect the pitch control bearing housing per Robinson SB‑43A Rev A and replace any assembly that does not rotate freely. Initial inspection within 20 hours TIS after 26 March 2003; repeat every 300 hours or 12 months.\n\nCASA says this detects bearing corrosion/lubrication faults that could cause loss of directional control; operators bear inspection and replacement costs and must ground affected helicopters until fixed."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original narrow scope — addressing a specific safety defect in a specific helicopter model's component. There is no evidence of scope creep; it targets exactly the mechanical issue identified in the background (bearing lubrication failure risk) and applies only to the affected serial numbers."},"complexity_factors":["Single, specific mechanical component addressed (tail rotor pitch control assembly)","Clear applicability criteria (specific serial number range with explicit exceptions)","Straightforward two-step requirement: inspect, then replace if faulty","Simple compliance timeline (initial 20 hours, then 300 hours/12 months recurring)","Only one cross-reference (to FAA AD and manufacturer service bulletin)","No nested definitions, conditional logic, or interpretive provisions","Total length under 400 words"],"plain_english_summary":"This mandatory safety order affects certain early Robinson R44 helicopters (serials up to 1208, excluding a specified list) and requires owners/operators to hand‑rotate and inspect the tail‑rotor pitch‑control assembly bearings for roughness or stiffness. \n\nInspections are required within 20 flight hours after 26 March 2003 and then every 300 flight hours or 12 months, with replacement required before flight if faults are found. It aims to prevent bearing failure and loss of directional control."}},"importantCases":[],"_links":{"self":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly","history":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly/history","analysis":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly/analysis","conflicts":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly/conflicts","importantCases":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly/important-cases","documents":"/api/acts/ad-r44-17-tail-rotor-pitch-control-assembly/documents"}}