{"id":"F2009L00889","name":"AD/EC 225/4 Amdt 1 - Main Rotor Hub Dome Fairing Attachment Screws","slug":"ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":78195,"registerId":"commonwealth-F2009L00889-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eurocopter EC 225 Series Helicopters","sectionType":"division","heading":"Eurocopter EC 225 Series Helicopters","content":"### Eurocopter EC 225 Series Helicopters\n\n| AD/EC 225/4 Amdt 1 | Main Rotor Hub Dome FairingAttachment Screws | 4/2009 |\n| ------------------ | -------------------------------------------- | ------ |\n\n| Applicability: | Model EC 225 LP helicopters, all serial numbers, except those that have been modified during production with MOD 0743718 or in-service with Eurocopter EC225 Service Bulletin (SB) No. 62-007 original issue, or later EASA approved revision.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Check that there is no crack in the dome fairing support and readjust the tightening torque of the screws which secure the dome fairing support to the dome fairing, in accordance with instructions specified in paragraph 2.B.2 of EUROCOPTER EC 225 Alert Service Bulletin (ASB) No. 05A005 Revision 1, or later EASA approved revision.2. Readjust the tightening torque of the dome fairing support attachment screws on the dome fairing, in accordance with the instructions specified in paragraph 2.B.3 of ASB No. 05A005 Revision 1, or later EASA approved revision.Checks and corrective actions accomplished before the effective date of this Directive in accordance with ASB No.05A005 at original issue are acceptable compliance with the initial requirements of Requirements 1 and 2 of this Directive. After the effective date of this Directive, repetitive checks and corrective actions as required by Requirement 2 of this Directive must be accomplished in accordance with ASBNo. 05A005 at Revision 1.If, during any check required by this Directive, a crack is found in the dome fairing support at the dome fairing attachment points, before further flight, remove and replace the dome fairing support and the associated coning stop support assembly in accordance with the instructions of SB No. 62-007 original issue, or later EASA approved revision.Replacement of parts in accordance with the instructions of SB No. 62-007 original issue, or later EASA approved revision, constitutes terminating action for the repetitive checks required by Requirement 2 of this Directive.Note: EASA AD 2009-0023 refers. |\n| Compliance:    | 1. Unless the initial check is already accomplished, before further flight after9 April 2009.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n\n|             | 2. At intervals not to exceed 165 flight hours; until compliance with SB No. 62-007 original issue, or later EASA approved revision.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| ----------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Amendment becomes effective on 9 April 2009.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               |\n| Background: | This Emergency Airworthiness Directive was issued following the discovery of two cracks in the dome fairing attachment on the dome fairing support. These fatigue cracks were due to the loss of tightening torque of the screws which secure this assembly. These cracks, in time, can lead to the loss of the dome fairing in flight.Amendment 1 is issued in response to a new EASA AD, which introduces the latest revision of the Requirement document, and modification 0743718 (and associated SB No. 62-007) which constitutes terminating action for the repetitive checks required by this Directive. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n25 February 2009","sortOrder":0},{"sectionNumber":"AD/EC 225/4 Amdt 1","sectionType":"part","heading":"AD/EC 225/4 Amdt 1","content":"## AD/EC 225/4 Amdt 1","sortOrder":1},{"sectionNumber":"Main Rotor Hub Dome FairingAttachment Sc","sectionType":"part","heading":"Main Rotor Hub Dome FairingAttachment Screws","content":"## Main Rotor Hub Dome Fairing  \nAttachment Screws","sortOrder":2},{"sectionNumber":"4/2009","sectionType":"part","heading":"4/2009","content":"## 4/2009","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"This amendment updates the required reference material (directing compliance with ASB No. 05A005 Revision 1 or later) and recognises modification MOD 0743718 / SB No. 62-007 as the specified terminating action for repetitive inspections. Compared with the original Directive, the amendment therefore alters scope by (a) incorporating a newer ASB revision as the operative instruction set for inspections and torque readjustment, and (b) explicitly adding the production/in-service modification (MOD 0743718 / SB 62-007) as an accepted terminating action that removes the recurring inspection requirement. The core safety purpose (detect and correct fatigue cracks caused by loss of screw torque) remains the same, but the instrument changes the compliance path and documents that define acceptable work."},"complexity_factors":["Single-aircraft type and limited applicability (EC 225 LP only) with explicit exclusions (MOD 0743718 or SB 62-007 installed)","References to three external technical documents (ASB No. 05A005 Revision 1, SB No. 62-007, and EASA AD) rather than full procedures in the Directive","One recurring obligation (checks every 165 flight hours) and a single clear terminating action (replacement via SB 62-007)","A simple conditional: if crack found → remove and replace before further flight","Limited number of operational deadlines (initial check before next flight unless already done; 165 flight hour repeat interval)","Some minor conditional acceptance of prior compliance (work done to original ASB issue is acceptable for initial actions)"],"plain_english_summary":"**What this directive does (in simple terms)**\n\n- **Which aircraft are affected:** Model EC 225 LP helicopters (all serial numbers), except helicopters already modified during production with MOD 0743718 or those that have had the in-service modification described in Eurocopter Service Bulletin (SB) No. 62-007 (original issue) or a later EASA-approved revision. (See \"Applicability\".)\n\n- **The immediate requirement:** Before the next flight (unless already done), the operator must inspect the main rotor **dome fairing support** where it attaches to the dome fairing and make sure there are no cracks. The operator must also **readjust the tightening torque** of the screws that secure the dome fairing support to the dome fairing. The work must follow the steps set out in EUROCOPTER EC 225 Alert Service Bulletin (ASB) No. 05A005 Revision 1 (or a later EASA-approved revision). (See \"Requirement\" and \"Compliance\".)\n\n- **Ongoing requirement:** Repeat the torque checks and corrective actions at intervals not exceeding **165 flight hours** until the helicopter is modified in accordance with SB No. 62-007 (original issue) or a later EASA-approved revision. (See \"Requirement\" and \"Compliance\".)\n\n- **If a crack is found:** Do not fly the helicopter. Before the next flight, remove and replace the dome fairing support and the associated coning stop support assembly in accordance with SB No. 62-007 (original issue) or a later EASA-approved revision. Replacing those parts per the SB is a **terminating action** for the repetitive 165‑hour checks (i.e. once replaced per the SB, you no longer need the repeating inspections). (See \"Requirement\".)\n\n- **Acceptable prior compliance:** If the initial checks and corrective actions were done before this Directive came into force in accordance with ASB No. 05A005 at its original issue, that satisfies the initial inspection obligations here. (See \"Requirement\".)\n\n- **Why this matters:** The Directive was issued after two fatigue cracks were discovered where the dome fairing support attaches to the dome fairing. Investigators traced the cracks to loss of screw tightening torque. If left unaddressed, such cracks could progress and potentially lead to loss of the dome fairing in flight (safety risk). The Directive mandates inspections, torque re‑adjustment and, if necessary, part replacement to address that risk. (See \"Background\".)\n\nWho pays, who decides, and what changes in practice\n\n- **Who pays:** Helicopter operators bear the direct costs: technician labour for inspections and torque checks, any consumables, parts and replacement costs where cracks are found, and aircraft downtime while work is performed.\n\n- **Who decides/authorises the work:** The Civil Aviation Safety Authority (through this Directive) sets the mandatory actions; the technical work must follow Eurocopter ASB No. 05A005 Revision 1 and SB No. 62-007 (or later EASA‑approved revisions). An EASA-approved revision of those documents governs acceptable methods and parts.\n\n- **Behavioral change required of operators:** Perform an immediate (pre-flight) inspection and torque re‑adjustment if not already done; then implement recurring torque checks every 165 flight hours until the SB modification is installed. If a crack is found, remove and replace the affected assemblies before further flight.\n\nImplementation notes, trade-offs and risks\n\n- **Operational cost vs. frequency:** The recurring 165‑flight‑hour inspections impose ongoing maintenance burden and aircraft downtime; installing the SB modification (MOD 0743718 or in-service SB 62-007) removes that recurring obligation but requires one‑off parts and modification costs.\n\n- **Compliance and detection risks:** Detecting fatigue cracks depends on access and inspection method specified in the ASB; inadequate inspection technique or improper torque measurement could miss developing cracks. Torque re‑adjustment requires calibrated tools and correct procedures.\n\n- **Supply and timing risk:** If a crack is found, replacement parts and qualified maintenance capacity are required; lead times and scheduling affect aircraft availability.\n\n- **Economic incentives:** Operators face a choice: pay ongoing inspection costs or pay for the terminating modification. Service bulletins and required parts create a market for maintenance and replacement parts; operators will weigh recurring inspection cost and downtime against the one‑off modification expense.\n\nRelevant references in the Directive: Applicability (who is covered), Requirement (what to do, when, and follow ASB/SB), Compliance (deadlines and interval), Background (why it was issued)."},"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 is an amendment to an existing Emergency AD, but it maintains the original scope (addressing the dome fairing attachment screw issue). The amendment simply updates the reference documents to incorporate a new revision of the Alert Service Bulletin and adds the permanent fix (MOD 0743718/SB 62-007) as terminating action. The core safety purpose remains unchanged."},"complexity_factors":["Short, single-purpose document focused on one specific mechanical defect","Only 4 defined document references (ASB No. 05A005, SB No. 62-007, MOD 0743718, EASA AD 2009-0023)","Clear sequential requirements with simple conditional logic (if crack found → replace parts)","Single exception clause for pre-existing compliance","No nested definitions or extensive cross-referencing to other legislation","Straightforward compliance timeline (immediate + recurring every 165 hours)"],"plain_english_summary":"This emergency Airworthiness Directive orders owners and operators of Eurocopter EC225 LP helicopters (unless already modified by MOD 0743718 or SB No. 62‑007) to urgently inspect and secure screws on the main rotor hub dome fairing, and to repeat inspections every 165 flight hours until the SB replacement is installed. \n\nIt addresses fatigue cracks from loose screws that could allow the dome fairing to detach in flight, preventing a serious safety hazard by mandating immediate checks, torque correction, and a terminating repair."}},"importantCases":[],"_links":{"self":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws","history":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws/history","analysis":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws/analysis","conflicts":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws/conflicts","importantCases":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws/important-cases","documents":"/api/acts/ad-ec-225-4-amdt-1-main-rotor-hub-dome-fairing-attachment-screws/documents"}}