{"id":"F2007L03588","name":"AD/GBK 117/18 Amdt 1 - Tail Rotor System - Control Lever - Inspection/Replacement","slug":"ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":69900,"registerId":"commonwealth-F2007L03588-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eurocopter BK 117 Series Helicopters","sectionType":"division","heading":"Eurocopter BK 117 Series Helicopters","content":"### Eurocopter BK 117 Series Helicopters\n\n| AD/GBK 117/18 Amdt 1 | Tail Rotor System - Control Lever - Inspection/Replacement | 11/2007 DM |\n| -------------------- | ---------------------------------------------------------- | ---------- |\n\n| Applicability: | MBB-BK 117C-2 helicopters fitted with a Tail Rotor Control Lever Part Number (P/N) B642M1009103. |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Visually inspect the control lever, in accordance with section 3.A of the accomplishment instructions of EUROCOPTER DEUTSCHLAND Alert Service Bulletin (ASB) MBB BK117 C-2-64A-002 Revision 02 dated 6 August 2007 or subsequent EASA approved revision.2. Repeat the inspection as specified in Requirement 1 of this AD.3. If, during any of the inspections detailed in Requirement required by this AD, score marks, notching, scratching, cracks or similar damage is detected, replace the affected control lever with an airworthy part.4. Replace all P/N B642M1009103 Tail Rotor Control Levers and Weights P/N B642M1011202 with the improved P/N B642M1009104 Tail Rotor Control Levers including weights in accordance with section 3.B of the accomplishment instructions of EUROCOPTER Deutschland ASB MBB BK117 C-2-64A-002 Revision 02.After installation of a P/N B642M1009104 Tail Rotor Control Lever Assembly on any helicopter as detailed in Requirement 4 of this AD, the repetitive inspections detailed in Requirement 2 of this AD are no longer required.5. Do not install a P/N B642M1009103 Tail Rotor Control Lever on any helicopter.Note: EASA AD 2007-0237 dated 31 August 2007 refers. This AD supersedes EASA AD 2007-0189 E. |\n| Compliance: | 1. For helicopters that have not been inspected as required by the original issue of this AD, before further flight after the effective date of this AD, unless previously accomplished. |\n\n| | For helicopters that have been inspected as required by the original issue of this AD, within the next 8 Flight Hours (FH) or before accumulating 25 FH after the last inspection as required by this AD, whichever occurs first after the effective date of this AD.2. At intervals not to exceed 8 FH, until replacement of the parts as detailed in Requirement 4 of this AD is made.3. Before further flight after the effective date of this AD.4. Before 25 November 2007.5. From 25 November 2007. |\n| ----------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| | This Amendment becomes effective on 11 September 2007. |\n| Background: | EASA was informed by the manufacturer of an in-flight incident in which a dynamic weight broke off the control lever subsequently leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off. For this reason, the manufacturer issued ASB MBB BK117 C-2-64A-002 to introduce a corresponding visual inspection.EASA subsequently issued Emergency AD 2006-0379-E to require operators to accomplish the inspection. The aim of that EAD was to prevent separation of dynamic weights in flight, which can lead to severe vibration and reduced controllability of the helicopter.This amendment mandates the replacement of certain parts and provides terminating action to the repetitive inspections detailed in this AD.The original issue of this AD became effective on 30 August 2007. |\n\n![](image.001.png) \nCharles Lenarcic \nDelegate of the Civil Aviation Safety Authority\n\n6 September 2007","sortOrder":0},{"sectionNumber":"AD/GBK 117/18 Amdt 1","sectionType":"part","heading":"AD/GBK 117/18 Amdt 1","content":"## AD/GBK 117/18 Amdt 1","sortOrder":1},{"sectionNumber":"Tail Rotor System - Control Lever - Insp","sectionType":"part","heading":"Tail Rotor System - Control Lever - Inspection/Replacement","content":"## Tail Rotor System - Control Lever - Inspection/Replacement","sortOrder":2},{"sectionNumber":"11/2007 DM","sectionType":"part","heading":"11/2007 DM","content":"## 11/2007 DM","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The amendment expands the original inspection‑only scope by mandating full replacement of P/N B642M1009103 levers and weights with improved P/N B642M1009104 assemblies and by forbidding reinstalling the old part, while making that retrofit the terminating action for repetitive inspections (see Requirements 2–5 and Background)."},"complexity_factors":["Narrow technical scope limited to MBB‑BK 117C‑2 helicopters fitted with P/N B642M1009103 (Applicability).","Specific parts and part numbers drive compliance (Requirements 3–5).","Multiple, short compliance timelines depending on prior inspections (Compliance: before further flight; within 8 FH; before 25 Nov 2007).","Termination provision: repetitive inspections stop after mandated retrofit (Requirement 4).","Prohibition on installing the old part establishes ongoing parts control (Requirement 5).","Cross‑references to manufacturer Alert Service Bulletin and EASA AD create external-document dependency (Requirement 1; Note).","Operational cost and logistics concentrated on operators who must source improved assemblies and schedule downtime (Requirements 3–4)."],"plain_english_summary":"**What it does:** Requires operators of MBB‑BK 117C‑2 helicopters fitted with Tail Rotor Control Lever P/N B642M1009103 to perform frequent visual inspections and, if damage is found, replace the lever; mandates replacing all affected levers and weights with improved P/N B642M1009104 assemblies by 25 November 2007 and prohibits reinstalling the old part. **Who pays/decides:** Aircraft operators must perform inspections and pay for replacements. The directive responds to an in‑flight failure of a control‑lever weight and aims to remove the need for ongoing inspections once the retrofit is done."},"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 amendment remains tightly focused on its original purpose: addressing the specific safety defect in the BK 117C-2 tail rotor control lever. The amendment adds the replacement requirement (Requirement 4) and terminating action, but this is a natural progression of the safety response rather than scope creep. The original AD required inspections; this amendment completes the safety loop by mandating permanent corrective action."},"complexity_factors":["Single, specific mechanical part targeted (P/N B642M1009103)","Clear sequential requirements (inspect → repeat → replace → terminate)","Only 5 numbered requirements with straightforward conditional logic","Limited cross-referencing (only references one Eurocopter Service Bulletin and one superseded EASA AD)","Specific compliance deadlines (dates and flight hours) with simple 'whichever occurs first' logic","No nested definitions or interpretation sections","Terminating action clearly specified (Requirement 4 ends Requirement 2)"],"plain_english_summary":"This AD mandates inspections and eventual replacement of the Tail Rotor Control Lever (P/N B642M1009103) on MBB‑BK 117C‑2 helicopters after a weight on the lever detached in flight, causing severe vibration and control difficulty. Operators must carry out visual inspections before next flight and every 8 flight hours until the lever is replaced with the improved P/N B642M1009104 by 25 November 2007; the older part is prohibited thereafter. It affects any operator of the specified helicopters using that part."}},"importantCases":[],"_links":{"self":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement","history":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement/history","analysis":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement/analysis","conflicts":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement/conflicts","importantCases":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement/important-cases","documents":"/api/acts/ad-gbk-117-18-amdt-1-tail-rotor-system-control-lever-inspection-replacement/documents"}}