{"id":"F2006L02608","name":"AD/A119/8 - Tail Rotor Pitch Control Link Assembly","slug":"ad-a119-8-tail-rotor-pitch-control-link-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":59891,"registerId":"commonwealth-F2006L02608-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Agusta A119 Series Helicopters","sectionType":"division","heading":"Agusta A119 Series Helicopters","content":"### Agusta A119 Series Helicopters\n\n| AD/A119/8 | Tail Rotor Pitch Control Link Assembly | 10/2006 TX |\n| --------- | -------------------------------------- | ---------- |\n\n| Applicability: | Agusta A119 helicopters fitted with tail rotor pitch control link assembly part number (P/N) 109-0130-05-117 with serial (S/N) from MO001 up to S/N MO773 (included).The AD does not apply to tail rotor pitch control link assembly P/N 109-0130-05-117 with S/N MOxxx and identified with the letter T” after the S/N. |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | Action in accordance with Agusta Alert SB 119-15 or later EASA approved revisions.Note: EASA Emergency AD 2006-0228-E dated 27 July 2006 refers.                                                                                                                                                                         |\n| Compliance:    | Before further flight after the effective date of this AD.For links held as spares: Before installation on a helicopter after the effective date of this AD.                                                                                                                                                             |\n|                | This Airworthiness Directive becomes effective on 7 August 2006.                                                                                                                                                                                                                                                         |\n| Background:    | An A109E experienced a failure of the tail rotor pitch control link assembly P/N109-0130-05-117 with 10 FH. Preliminary investigation made by the TCH Agusta has revealed that the failure has been caused by a production defect.                                                                                       |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n3 August 2006","sortOrder":0},{"sectionNumber":"AD/A119/8","sectionType":"part","heading":"AD/A119/8","content":"## AD/A119/8","sortOrder":1},{"sectionNumber":"Tail Rotor Pitch Control Link Assembly","sectionType":"part","heading":"Tail Rotor Pitch Control Link Assembly","content":"## Tail Rotor Pitch Control Link Assembly","sortOrder":2},{"sectionNumber":"10/2006 TX","sectionType":"part","heading":"10/2006 TX","content":"## 10/2006 TX","sortOrder":3}],"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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a targeted emergency safety directive addressing a specific known defect in a specific aircraft part. The scope remains precisely limited to the identified production defect in the tail rotor pitch control link assembly. No scope creep is evident."},"complexity_factors":["Very short document (under 300 words)","Only 2 defined part/serial number ranges to identify affected aircraft","Single compliance action (follow the Service Bulletin)","Simple conditional exemption (parts marked with 'T' are excluded)","No cross-references to other legislation beyond a single referenced Service Bulletin and EASA Emergency AD","Clear, unambiguous compliance deadline (before further flight after effective date)"],"plain_english_summary":"This AD mandates immediate inspection or replacement of the tail rotor pitch control link assembly (part 109-0130-05-117, S/N MO001–MO773) on affected Agusta A119 helicopters, following Agusta Alert Service Bulletin 119-15. Parts marked with a trailing “T” are exempt.\n\nIt must be done before the helicopter next flies after 7 August 2006 (or before installing a spare). The directive responds to a production defect that can cause loss of control; non‑compliance is illegal and hazardous."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The supplied text contains no indication that the AD's scope has been amended since issuance. It sets explicit applicability by part and serial numbers, notes an exclusion (‘‘T’’-identified units), prescribes compliance via a specified service bulletin and an effective date of 7 August 2006."},"complexity_factors":["Serial-number-limited applicability (Applicability): tracking affected units MO001–MO773, and excluding those identified with a trailing 'T', increases parts-tracing administrative work.","Dependence on external documents (Requirement): mandates compliance 'in accordance with Agusta Alert SB 119-15 or later EASA approved revisions', creating reliance on service bulletin content and any future approved revisions.","Urgent compliance timeframe (Compliance): 'Before further flight' forces immediate operational decisions and potential aircraft grounding.","Spare-parts control (Compliance): requires action on spares 'before installation', imposing inventory checks and installation prohibitions.","Cross-authority reference (Requirement/Note): cites EASA Emergency AD 2006-0228-E, requiring coordination with an overseas regulator's directive.","Preliminary technical cause (Background): identifies a production defect as the cause, which may prompt follow-up inspections, corrective production actions, or replacement campaigns."],"plain_english_summary":"This Airworthiness Directive requires operators to inspect or take the corrective action specified in Agusta Alert SB 119-15 (or later EASA-approved revisions) for tail rotor pitch control link assembly P/N 109-0130-05-117 with serial numbers MO001–MO773 on Agusta A119 helicopters, and forbids installing affected spare links, effective before the next flight. The AD follows a reported failure traced to a production defect and therefore affects A119 owners/operators and maintenance organisations, who must bear immediate inspection, grounding or replacement costs."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly","history":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly/history","analysis":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly/analysis","conflicts":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly/conflicts","importantCases":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly/important-cases","documents":"/api/acts/ad-a119-8-tail-rotor-pitch-control-link-assembly/documents"}}