{"id":"F2006L03585","name":"AD/ECUREUIL/112 Amdt 1 - Cabin Vibration Damper Assembly","slug":"ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":61132,"registerId":"commonwealth-F2006L03585-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eurocopter AS 350 (Ecureuil) Series Heli","sectionType":"division","heading":"Eurocopter AS 350 (Ecureuil) Series Helicopters","content":"### Eurocopter AS 350 (Ecureuil) Series Helicopters\n\n| AD/ECUREUIL/112 Amdt 1 | Cabin Vibration Damper Assembly | 12/2006 |\n| ---------------------- | ------------------------------- | ------- |\n\n| Applicability: | 1. Eurocopter AS 350 B, BA, BB, B1, B2, B3 and D helicopters fitted with:a. a cabin vibration damper assembly installed on the right hand (RH) side of the helicopter; andb. an automatic flight control system;and2. Eurocopter EC 130 B4 helicopters fitted with cabin vibration damper blades and which have never been modified per modification 073565.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Visually check the visible areas of the blade of the vibration damper assembly, installed on the RH side of the helicopter, for cracks, in accordance with paragraph 2.B.1 of Eurocopter AS 350 Alert Service Bulletin (ASB)No. 05.00.48 dated 24 May 2006, or Eurocopter EC130 ASB 05A002 dated28 June 2006, or any subsequent EASA approved revisions, as is applicable.2. If a crack is found, remove the RH vibration damper assembly, replace the cracked blade and re-install the vibration damper assembly fitted with a new blade, and adjust the vibration damper in accordance with Eurocopter ASBNo. 05.00.48, or Eurocopter EC130 ASB 05A002, or any subsequent EASA approved revisions, as is applicable.3. For AS350 helicopters modified per MODs 072262, 071543 and OP1055 install a vibration damper/casing assembly on the RH side of the helicopter, in accordance with paragraph 2 of Eurocopter ASB No. 53.00.34 or any subsequent EASA approved revisions, as is applicable.4. For EC 130B4 helicopters not modified per MOD 073521 (SB No. 53-006) and MOD 073525 (SB No. 53-007), install a vibration damper/casing assembly on the RH and LH side of the helicopter, in accordance with paragraphs 2.B.1, 2.B.2. and 2.B.5. of Eurocopter ASB No. 53A008 or any subsequent EASA approved revisions, as is applicable. |\n\n|             | 5. For EC 130B4 helicopters modified per MOD 073521 (SB No. 53-006) or MOD 073525 (SB No. 53-007), install a vibration damper / casing assembly on the RH and LH side of the helicopter, in compliance with the instructions specified in paragraphs 2.B.1, 2.B.3. and 2.B.5. of Eurocopter ASB No. 53A008 or any subsequent EASA approved revisions, as is applicable.Terminating Action.Compliance with Requirements 3 or 4 or 5 as is applicable provides terminating action to the repetitive inspections detailed in Requirement 1 of this AD.Note: EASA AD 2006-0273 dated 4 September 2006 and AD 2006-0278 dated7 September 2006 refers. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Compliance: | 1. Repetitively before the first flight of the day after the effective date of this AD.2. Before further flight.3. No later than 30 June 2007.4. No later than 31 May 2007.5. No later than 31 May 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n|             | This Amendment becomes effective on 23 November 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background: | In the event of a failure of the blade of the RH cabin vibration damper assembly, for helicopters fitted with an automatic flight control system, the failed part that remains trapped in the bottom structure lower fairing can interfere with the trim actuator rod which is installed nearby. Such interference could jam the flight controls.This amendment introduces a mandatory modification to the vibration damper assembly which terminate the repetitive inspection called up in this AD.The original issue of this AD became effective 20 June 2005.                                                                                 |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n13 October 2006","sortOrder":0},{"sectionNumber":"AD/ECUREUIL/112 Amdt 1","sectionType":"part","heading":"AD/ECUREUIL/112 Amdt 1","content":"## AD/ECUREUIL/112 Amdt 1","sortOrder":1},{"sectionNumber":"Cabin Vibration Damper Assembly","sectionType":"part","heading":"Cabin Vibration Damper Assembly","content":"## Cabin Vibration Damper Assembly","sortOrder":2},{"sectionNumber":"12/2006","sectionType":"part","heading":"12/2006","content":"## 12/2006","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":true,"description":"This amendment expands and alters the original AD by adding mandatory installation requirements for vibration damper/casing assemblies (providing a terminating action to the prior repetitive inspections), by specifying applicability to additional EC130 B4 configurations, and by setting discrete installation deadlines. The original AD (effective 20 June 2005) required repetitive inspections; this amendment prescribes hardware modification as an alternative to ongoing inspections."},"complexity_factors":["Multiple aircraft models and variants listed (AS350 B/BA/BB/B1/B2/B3/D and EC130 B4), increasing applicability permutations.","Conditional applicability tied to specific installed equipment and modification status (e.g. presence of cabin damper assembly, automatic flight control system, and particular MOD numbers).","Procedural requirements reference external manufacturer Alert Service Bulletins and any subsequent EASA‑approved revisions, creating dependency on outside documents for compliance steps.","Mix of repetitive operational inspections (pre‑flight daily) and hardware modification/installation actions with separate compliance deadlines.","Terminating action: installing the specified vibration damper/casing assemblies cancels the repetitive inspection requirement, making compliance outcomes dependent on upgrade uptake.","Safety‑critical replacement and adjustment steps require technical work (remove, replace blade, adjust damper) rather than simple administrative compliance.","Multiple compliance deadlines and a ‘before further flight’ immediate action for found cracks increase planning and operational burden."],"plain_english_summary":"This amendment requires operators of specified Eurocopter AS350 and EC130 helicopters to inspect the right-hand cabin vibration damper blade before flight, replace any cracked blade, and install updated damper/casing assemblies by set deadlines; completing the mandated installation stops the need for daily inspections. It applies to helicopters fitted with the listed damper assemblies and, for AS350, an automatic flight control system. The measure responds to risk that a failed damper blade can jam the trim actuator rod and impede flight controls."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive amendment. The original AD (effective June 2005) mandated repetitive inspections. This Amendment 1 adds permanent modification options that terminate those inspections. The scope remains focused on the original safety issue (vibration damper blade failure) and has not expanded beyond this specific airworthiness concern."},"complexity_factors":["Multiple applicability categories with overlapping conditions (AS 350 vs EC 130, modified vs unmodified aircraft)","Five distinct requirements with different compliance deadlines and conditions","Heavy reliance on external technical documents (Eurocopter Alert Service Bulletins) rather than self-contained instructions","Cross-references to specific modification numbers (MODs) and Service Bulletin numbers that operators must locate and interpret","Conditional logic: Requirements 3, 4, and 5 are mutually exclusive alternatives depending on aircraft modification status","Terminating action concept — compliance with one requirement ends obligations under another"],"plain_english_summary":"This AD requires operators of certain Eurocopter AS350 (B/BA/BB/B1/B2/B3/D) with a right‑hand cabin vibration damper and automatic flight control system, and EC130 B4s with unmodified damper blades, to perform daily pre‑flight visual checks and replace any cracked damper blades. Cracked blades can break and jam the flight controls. A mandated permanent modification (introduced by Amendment 1) must be installed by the deadlines to end the repetitive inspections."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly","history":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly/history","analysis":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly/analysis","conflicts":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly/conflicts","importantCases":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly/important-cases","documents":"/api/acts/ad-ecureuil-112-amdt-1-cabin-vibration-damper-assembly/documents"}}