{"id":"F2006L03628","name":"AD/SA 315/10 - Main Rotor Blade Attachment Fittings","slug":"ad-sa-315-10-main-rotor-blade-attachment-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":137330,"registerId":"commonwealth-F2006L03628-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 315/10 | Main Rotor Blade Attachment Fittings | 12/2006 |\n| ------------ | ------------------------------------ | ------- |\n\n| Applicability: | Model SA 315 B helicopters.                                                                                                                                                                                                                                                                                   |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Perform a crack detection inspection on the attachment fitting in the area of the main rotor blade attachment bolts, in accordance with the procedure specified in Chapter 5 of the DGAC approved Maintenance Manual, Revision dated 03-96, or later approved revision.Note: DGAC AD 96-081-036(B) R1 refers. |\n| Compliance:    | At intervals not to exceed 400 flight hours.                                                                                                                                                                                                                                                                  |\n|                | This Airworthiness Directive becomes effective on 23 November 2006.                                                                                                                                                                                                                                           |\n| Background:    | The DGAC requires certain inspections in response to fatigue tests conducted on the main rotor blade spar/fitting.                                                                                                                                                                                            |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n13 October 2006","sortOrder":0},{"sectionNumber":"AD/SA 315/10","sectionType":"part","heading":"AD/SA 315/10","content":"## AD/SA 315/10","sortOrder":1},{"sectionNumber":"Main Rotor Blade Attachment Fittings","sectionType":"part","heading":"Main Rotor Blade Attachment Fittings","content":"## Main Rotor Blade Attachment Fittings","sortOrder":2},{"sectionNumber":"12/2006","sectionType":"part","heading":"12/2006","content":"## 12/2006","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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, narrow Airworthiness Directive targeting a specific safety issue on a specific helicopter model. It has not expanded beyond its original purpose of mandating crack inspections following fatigue test findings."},"complexity_factors":["Single, specific mechanical component targeted (main rotor blade attachment fittings)","Only one compliance interval specified (400 flight hours)","Single reference to external technical document (DGAC maintenance manual Chapter 5)","No defined terms section, no conditional logic, no exceptions or exemptions","Extremely short document (approximately 150 words of substantive content)","Clear, unambiguous applicability (Model SA 315 B only)"],"plain_english_summary":"Owners and operators of Eurocopter SA 315 B (Lama) helicopters in Australia must perform inspections of the main rotor blade attachment fittings for cracks — focusing on the bolt/attachment area — following the DGAC‑approved maintenance procedure (Chapter 5, Mar 1996 or later). Inspections are required at intervals not exceeding 400 flight hours due to fatigue‑test findings that indicate risk of crack growth; noncompliance breaches aviation law and risks catastrophic rotor failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The instrument applies narrowly to Model SA 315 B and implements the DGAC‑required inspections described in the Background. The AD does not expand beyond mandating the inspection procedure and a 400‑flight‑hour interval (Applicability; Requirement; Compliance); no text indicates a broader or narrower scope than the stated DGAC response."},"complexity_factors":["Narrow applicability: applies only to Model SA 315 B helicopters (Applicability) — reduces regulatory breadth but concentrates impact on specific operators.","Prescribed procedure referenced externally: inspection must follow Chapter 5 of the DGAC‑approved Maintenance Manual, Revision 03‑96 or later (Requirement) — requires access to and reliance on an external, agency‑approved document.","Recurring interval obligation: inspections every 400 flight hours (Compliance) — creates ongoing scheduling and cost commitments for operators.","Technical inspection requirement: crack‑detection in the bolt‑area of blade attachment fittings (Requirement) — may require specialised inspection methods, training or equipment.","Cross‑jurisdictional reference: references DGAC AD 96‑081‑036(B) R1 and DGAC procedures (Requirement; Background) — introduces dependence on a foreign authority's standards and future revisions.","Compliance timeline: effective date specified as 23 November 2006 (Compliance) — imposes a fixed date by which operators must be compliant.","Limited regulatory discretion in text: AD prescribes the inspection procedure and interval, leaving little operational discretion but requiring maintenance organisations to interpret and apply the referenced manual (Requirement).","Administrative burden: recordkeeping, maintenance scheduling and potential grounding time during inspections implied by recurring inspections (Compliance)."],"plain_english_summary":"It mandates recurring crack-detection inspections of the main rotor blade attachment fittings on Eurocopter SA 315 B helicopters, using the DGAC‑approved Maintenance Manual procedure, at intervals not exceeding 400 flight hours (Requirement; Compliance). It affects operators and maintenance organisations who must schedule and pay for inspections; the AD says it responds to fatigue-test findings (Background)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings","history":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings/history","analysis":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings/analysis","conflicts":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings/conflicts","importantCases":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings/important-cases","documents":"/api/acts/ad-sa-315-10-main-rotor-blade-attachment-fittings/documents"}}