{"id":"F2006L03623","name":"AD/SA 315/4 - Main Rotor Blade Cuff to Spar Assembly","slug":"ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":137318,"registerId":"commonwealth-F2006L03623-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eurocopter SA 315 (Lama) Series Helicopt","sectionType":"division","heading":"Eurocopter SA 315 (Lama) Series Helicopters","content":"### Eurocopter SA 315 (Lama) Series Helicopters\n\n| AD/SA 315/4 | Main Rotor Blade Cuff to Spar Assembly | 12/2006 |\n| ----------- | -------------------------------------- | ------- |\n\n| Applicability: | Model SA 315 B helicopters, equipped with main rotor blade part number:3160S11-10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-45000 all dash numbers, 3160S11-50000 all dash numbers, and 3160S11-55000 all dash numbers.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | Inspect the main rotor blade spar areas for cracks in accordance with paragraph 2.B. of Eurocopter Service Bulletin No. 05.39.Note: DGAC AD 1998-171-039(A) R2 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n| Compliance:    | 1. For blades which have accumulated less than 400 flight hours:Upon accumulating 400 flight hours.2. For blades which have accumulated more than 400 flight hours:And which have been previously checked in accordance with Eurocopter Service Telex No. 01-20 or 01-30, within 25 flight hours after the last check, unless already accomplished.3. For blades which have accumulated more than 400 flight hours:And which have not been previously checked in accordance with Eurocopter Service Telex No. 01-20 or 01-30, before further flight.4. Repeat inspection at intervals not to exceed 100 flight hours or 600 flight cycles, whichever occurs first.5. Accomplish inspection before further flight after a sudden occurrence of vibrations at 1 omega.6. Accomplish inspection on blades held as spares before installation on the helicopter. |\n|                | This Airworthiness Directive becomes effective on 23 November 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          |\n\n| Background: | The DGAC received a report of the failure of a main rotor blade on a SA 315 B helicopter. |\n| ----------- | ----------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n12 October 2006","sortOrder":0},{"sectionNumber":"AD/SA 315/4","sectionType":"part","heading":"AD/SA 315/4","content":"## AD/SA 315/4","sortOrder":1},{"sectionNumber":"Main Rotor Blade Cuff to Spar Assembly","sectionType":"part","heading":"Main Rotor Blade Cuff to Spar Assembly","content":"## Main Rotor Blade Cuff to Spar Assembly","sortOrder":2},{"sectionNumber":"12/2006","sectionType":"part","heading":"12/2006","content":"## 12/2006","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive applies specifically to SA 315B helicopters with the listed blade part numbers and imposes inspection requirements to address a reported blade failure. The instrument does not expand or narrow applicability beyond that stated purpose in the text provided."},"complexity_factors":["Multiple blade part numbers listed — increases tracking and recordkeeping for operators.","Different initial compliance paths depending on accumulated flight hours and whether prior checks were done (Compliance paragraphs 1–3).","Recurring inspection interval tied to either flight hours or flight cycles (Compliance paragraph 4) — requires dual tracking.","Additional mandatory triggers: inspection after sudden 1‑omega vibrations and before installing spares (Compliance paragraphs 5–6).","Dependence on external technical documents: Eurocopter Service Bulletin para 2.B and referenced DGAC AD (Requirement) — requires access to and reliance on manufacturer/foreign authority guidance for inspection method and criteria."],"plain_english_summary":"Requires mandatory inspections of the main rotor blade cuff-to-spar area on SA 315B helicopters fitted with the listed blade part numbers. Operators and maintenance organisations must carry out initial checks depending on accumulated flight hours and prior checks, repeat inspections every 100 flight hours or 600 cycles, and immediate checks after sudden 1‑omega vibrations or before installing spares. The stated purpose is to detect cracks after a reported blade failure; operators pay inspection costs and bear downtime risk (see 'Requirement' & 'Compliance')."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive addressing a specific mechanical failure mode in a specific helicopter type. It has not expanded beyond its original purpose of preventing main rotor blade failures through mandated inspections."},"complexity_factors":["Multiple conditional compliance pathways based on flight hours accumulated (3 distinct categories)","Cross-reference to external technical documents (Eurocopter Service Bulletin No. 05.39, DGAC AD 1998-171-039(A) R2, Eurocopter Service Telex No. 01-20 and 01-30)","Dual recurring inspection intervals (flight hours OR flight cycles — whichever occurs first)","Technical aviation terminology requiring domain knowledge ('1 omega' vibration, 'cuff to spar assembly', 'dash numbers')","Specific part number enumeration with 'all dash numbers' wildcard notation"],"plain_english_summary":"This AD requires owners, operators and maintenance organisations of Eurocopter SA 315 B “Lama” helicopters (specific 3160S11-series main rotor blades, including spares) to inspect the cuff-to-spar assembly for fatigue cracks and to take immediate action if 1‑rpm vibration is detected. \n\nIssued after a reported blade failure, it enforces time- and usage-based inspection deadlines (and grounding until inspected where applicable) to catch cracks before catastrophic blade separation and prevent crashes."},"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-sa-315-4-main-rotor-blade-cuff-to-spar-assembly","history":"/api/acts/ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly/history","analysis":"/api/acts/ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly/analysis","conflicts":"/api/acts/ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly/conflicts","importantCases":"/api/acts/ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly/important-cases","documents":"/api/acts/ad-sa-315-4-main-rotor-blade-cuff-to-spar-assembly/documents"}}