{"id":"F2006L03622","name":"AD/SA 315/3 - Main Rotor Blade Root Skin and Reinforcement Strip Bonding","slug":"ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":137316,"registerId":"commonwealth-F2006L03622-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 315/3 | Main Rotor Blade Root Skin andReinforcement Strip Bonding | 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 skin and the blade root reinforcement strip area for bonding separation, cracks, and corrosion in accordance with paragraph 2 of Eurocopter Service Bulletin No. 05.34 R1.If bonding separation, cracking, or corrosion is detected during any inspection, and is within the criteria defined in paragraph 2 of the Requirement document, before further flight, remove the blade from service.Inspect blades held as spares before entry into service.Note: DGAC AD 98-277-040(A) R1 refers. |\n| Compliance:    | Unless the initial inspection is already accomplished, within 25 flight hours or 30 days after 23 November 2006, whichever occurs first.Inspect thereafter at intervals not to exceed 100 flight hours or 6 months, whichever occurs first; except when bonding separation is detected in the non-hatched area of the reinforcement strip, in which case the inspection interval is reduced to 25 flight hours.                                                                                                                 |\n|                | This Airworthiness Directive becomes effective on 23 November 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n| Background:    | The DGAC received a report of main rotor blade failure on a SE 3130 helicopter.                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n12 October 2006","sortOrder":0},{"sectionNumber":"AD/SA 315/3","sectionType":"part","heading":"AD/SA 315/3","content":"## AD/SA 315/3","sortOrder":1},{"sectionNumber":"Main Rotor Blade Root Skin andReinforcem","sectionType":"part","heading":"Main Rotor Blade Root Skin andReinforcement Strip Bonding","content":"## Main Rotor Blade Root Skin and  \nReinforcement Strip Bonding","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"},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"The instrument applies to a defined set of SA 315B helicopters with specified blade part numbers and imposes inspection and removal requirements. The text shows no expansion or narrowing beyond that applicability; it implements targeted inspections to address reported rotor-blade failures and does not indicate a change from that original corrective intent (Applicability; Requirement; Compliance)."},"complexity_factors":["Cross-reference to an external document (Eurocopter Service Bulletin No. 05.34 R1) for inspection procedures and defect criteria (Requirement).","Multiple, conditional inspection intervals: initial 25 flight hours/30 days, recurring 100 flight hours/6 months, and reduced 25 flight hours if separation in non‑hatched reinforcement area (Compliance).","Detailed applicability limited to SA 315B helicopters fitted with numerous specific blade part numbers — narrow population but many P/N variants (Applicability).","Mandatory removal-from-service action where defects meet the bulletin’s criteria; immediate operational consequence for operators (Requirement).","Obligation to inspect spares before entry into service introduces pre‑use compliance steps (Requirement).","Reference to a foreign authority directive (DGAC AD 98-277-040(A) R1) adds an additional cross-check and potential interpretive complexity (Note).","Effective date and short compliance windows create implementation and logistical pressure on operators and maintenance providers (Compliance/Effective date).","Potential ambiguity where the AD defers to 'paragraph 2 of the Requirement document' for limits/criteria — requires reading and interpreting another document."],"plain_english_summary":"This Airworthiness Directive requires operators of Eurocopter SA 315B helicopters fitted with the listed main-rotor blade part numbers to carry out periodic inspections of the blade root skin and reinforcement strip for bonding separation, cracking and corrosion, following Eurocopter Service Bulletin No. 05.34 R1 (Requirement; Applicability). Defective blades that meet the bulletin’s removal criteria must be taken out of service before further flight. Initial and recurring inspection intervals, and a shorter interval when separation appears in a specified area, are set out in the Compliance section."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard single-issue Airworthiness Directive addressing a specific safety defect in a specific aircraft type. The scope remains tightly focused on the original safety concern (main rotor blade bonding failures) without expansion into unrelated operational or maintenance areas."},"complexity_factors":["Single technical requirement with clear conditional logic (if-then structure for defect detection)","Multiple part numbers listed in applicability (7 dash number ranges)","Two-tier compliance schedule with exception clause (standard 100hr/6mo interval vs reduced 25hr interval for specific defect location)","References external technical document (Eurocopter Service Bulletin No. 05.34 R1) without reproducing its content","Cross-reference to French aviation authority directive (DGAC AD 98-277-040(A) R1)","No defined terms section; uses standard aviation terminology","Short document (approximately 250 words of substantive content)"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspections of main rotor blades on Eurocopter SA 315B \"Lama\" helicopters because the bond between the blade skin and its internal reinforcement can fail. Owners, operators and anyone fitting spare blades must inspect blades and remove any with bonding damage from service immediately.\n\nTriggered by a DGAC-reported blade failure, the AD forces recurring inspections to eliminate a failure mode that could lead to catastrophic rotor loss and crash."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding","history":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding/history","analysis":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding/analysis","conflicts":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding/conflicts","importantCases":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding/important-cases","documents":"/api/acts/ad-sa-315-3-main-rotor-blade-root-skin-and-reinforcement-strip-bonding/documents"}}