{"id":"F2006L02607","name":"AD/A109/54 - Tail Rotor Pitch Control Link Assembly","slug":"ad-a109-54-tail-rotor-pitch-control-link-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":59890,"registerId":"commonwealth-F2006L02607-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Agusta A109 Series Helicopters","sectionType":"division","heading":"Agusta A109 Series Helicopters","content":"### Agusta A109 Series Helicopters\n\n| AD/A109/54 | Tail Rotor Pitch Control Link Assembly | 10/2006 TX |\n| ---------- | -------------------------------------- | ---------- |\n\n| Applicability: | Agusta A109A, AII, C, K2, E, S, and LUH 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 109-122, 109K-47, 109EP-70, 109S-5, 109L-001, or later EASA approved revisions, as is applicable.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/A109/54","sectionType":"part","heading":"AD/A109/54","content":"## AD/A109/54","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":"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":3,"scope_assessment":{"changed":false,"description":"The AD's scope matches its stated purpose: it targets specific Agusta A109 models fitted with P/N 109-0130-05-117 serials MO001–MO773 (excluding parts marked 'T') to address a production-defect failure (Applicability; Background). It does not broaden applicability beyond that serial range or introduce additional aircraft types."},"complexity_factors":["Narrow, serial-numbered applicability increases administrative tracking (Applicability).","Dependence on external Agusta Alert Service Bulletins and an EASA Emergency AD for technical procedures (Requirement).","Immediate compliance timing: 'before further flight' and 'before installation' for spares creates operational disruption risk (Compliance).","Exception for parts identified with a trailing 'T' requires visual/record verification (Applicability).","Directive cites a production-defect origin but contains no in-AD technical remedy — implements SBs rather than set procedures (Background & Requirement).","Issued and enforced by CASA delegate (signature/date), so regulatory decision-making is centralized (effective date/issuer)."],"plain_english_summary":"**What it does:** Requires operators of Agusta A109 helicopters to follow Agusta Alert Service Bulletins (and the referenced EASA Emergency AD) to inspect and fix tail‑rotor pitch control link assemblies P/N 109‑0130‑05‑117 with S/N MO001–MO773, except parts marked with a trailing “T”.\n\nWho pays/decides: operators must bear inspection, repair or replacement costs and comply before next flight or before installing affected spares; the Civil Aviation Safety Authority issued the directive after a reported production defect."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, targeted airworthiness directive addressing a specific manufacturing defect in a specific aircraft component. The scope remains precisely limited to the safety-critical defect identified in the background section."},"complexity_factors":["Single, specific mechanical part identified by part number and serial number range","Straightforward applicability test: check if your helicopter model and part serial number fall within listed ranges","Clear exemption: serial numbers marked with 'T' are excluded","Single compliance action: follow manufacturer's service bulletin","No nested conditions, no cross-references to other legislation, no defined terms section","Length: approximately 250 words of substantive content"],"plain_english_summary":"This AD grounds certain Agusta A109 helicopters with a specific tail rotor pitch control link (P/N 109-0130-05-117, SN MO001–MO773) until that link is inspected or replaced per Agusta’s emergency service bulletin. Parts marked with a trailing “T” are excluded. Prompt action is required before the next flight after a reported in-service failure that led to loss of tail-rotor control and a crash; the directive took effect 7 August 2006."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly","history":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly/history","analysis":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly/analysis","conflicts":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly/conflicts","importantCases":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly/important-cases","documents":"/api/acts/ad-a109-54-tail-rotor-pitch-control-link-assembly/documents"}}