{"id":"F2006L03625","name":"AD/SA 315/6 - Tail Rotor Blade Skin","slug":"ad-sa-315-6-tail-rotor-blade-skin","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":137323,"registerId":"commonwealth-F2006L03625-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 315/6 | Tail Rotor Blade Skin | 12/2006 |\n| ----------- | --------------------- | ------- |\n\n| Applicability: | Model SA 315 B helicopters, equipped with tail rotor blade part numbers:3160S-34-10000, all dash numbers, and 3160S-34-11000, all dash numbers.                                                                                                                           |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Perform an inspection in accordance with paragraph 2.B. of Eurocopter Alert Service Bulletin No. 05.36, of the lower and upper surfaces of blade part numbers:3160S-34-10000-10, and subsequent,3160S-34-11000, all dash numbers.Note: DGAC AD 1998-288-042(A) R1 refers. |\n| Compliance:    | Within 10 flight hours after 23 November 2006, and thereafter at intervals not to exceed 10 flight hours.                                                                                                                                                                 |\n|                | This Airworthiness Directive becomes effective on 23 November 2006.                                                                                                                                                                                                       |\n| Background:    | A report was received of a crack in the skin of a tail rotor blade lower surface, near the attachment bolt on the blade cuff stem, on the leading edge side. Such cracking, unless detected, could result in failure of the blade.                                        |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n12 October 2006","sortOrder":0},{"sectionNumber":"AD/SA 315/6","sectionType":"part","heading":"AD/SA 315/6","content":"## AD/SA 315/6","sortOrder":1},{"sectionNumber":"Tail Rotor Blade Skin","sectionType":"part","heading":"Tail Rotor Blade Skin","content":"## Tail Rotor Blade Skin","sortOrder":2},{"sectionNumber":"12/2006","sectionType":"part","heading":"12/2006","content":"## 12/2006","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard, narrow Airworthiness Directive issued in response to a specific reported safety defect. It maintains the typical scope of ADs: targeted safety intervention for a specific aircraft component with defined applicability. No scope creep is evident."},"complexity_factors":["Very short document (approximately 200 words of substantive content)","Only 2 defined part number ranges in applicability section","Single operational requirement with clear reference to external technical document (Eurocopter Alert Service Bulletin)","Simple compliance timeline: initial 10 flight hours, then recurring every 10 flight hours","No nested exceptions, conditional logic, or cross-references to other legislation","Straightforward cause-and-effect: reported crack → inspection mandate → failure prevention"],"plain_english_summary":"This CASA Airworthiness Directive mandates owners/operators of Eurocopter SA 315 B “Lama” helicopters fitted with tail rotor blades P/N 3160S-34-10000 or 3160S-34-11000 series to inspect blade upper and lower surfaces per Eurocopter Alert Service Bulletin No. 05.36.  \n\nInspections must begin within 10 flight hours of 23 Nov 2006 and repeat every 10 flight hours to detect a skin crack found near the blade root — a defect that could lead to catastrophic blade failure and loss of the helicopter."},"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":4,"scope_assessment":{"changed":false,"description":"The directive applies specifically to Model SA 315 B helicopters fitted with the listed tail-rotor blade part numbers; it mandates a recurring inspection regime. The instrument references DGAC AD 1998-288-042(A) R1 but does not indicate an expansion or narrowing of the applicability beyond the listed models and part numbers."},"complexity_factors":["Narrow applicability to Model SA 315 B and two specific tail-rotor blade part number series (Applicability).","Inspection must follow an external document: Eurocopter Alert Service Bulletin No. 05.36, paragraph 2.B (Requirement) — adds dependency on a manufacturer bulletin for procedure.","Very short recurring interval: initial check within 10 flight hours of the effective date and thereafter every 10 flight hours (Compliance) — creates high operational and scheduling burden.","Inspections cover both lower and upper surfaces and target a specific location (near the attachment bolt on the cuff stem leading edge) which may require close visual or specialised inspection techniques (Requirement / Background).","Potential immediate operational impact if cracks are found (Background) — may require repair or grounding, imposing direct costs on owners/operators.","Identification of 'subsequent dash numbers' may complicate parts tracking and compliance verification (Applicability).","Effective date and short compliance window increase administrative pressure on operators to log and prove compliance promptly (Compliance)."],"plain_english_summary":"Requires repeated inspections of the upper and lower surfaces of specified tail-rotor blade skins on Eurocopter SA 315 B helicopters, carried out in accordance with paragraph 2.B of Eurocopter Alert Service Bulletin No. 05.36. Owners/operators of helicopters fitted with part numbers 3160S-34-10000 (and subsequent dash numbers) or 3160S-34-11000 must inspect within 10 flight hours after 23 November 2006 and then every 10 flight hours to detect skin cracking near the cuff stem attachment that could lead to blade failure."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin","history":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin/history","analysis":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin/analysis","conflicts":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin/conflicts","importantCases":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin/important-cases","documents":"/api/acts/ad-sa-315-6-tail-rotor-blade-skin/documents"}}