{"id":"F2006B01804","name":"AD/A109/2 Amdt 3 - Tail Rotor Blade Root Fitting","slug":"ad-a109-2-amdt-3-tail-rotor-blade-root-fitting","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41002,"registerId":"commonwealth-F2006B01804-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A109/2 Amdt 3 - Tail Rotor Blade Root Fitting","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nAgusta A109 Series Helicopters\n\nAD/A109/2\n\nAmdt 3\n\n  \n\nTail Rotor Blade Root Fitting 6/93 DM\n\nApplicability: All models fitted with tail rotor blades P/Nos 109-0132-02, \\-11 and \\-15. Requirement: Action in accordance with Agusta BT No. 109-51 Rev. B.\n\nNote: The previous issue of this Directive referred to RAI AD 86-6/A109-34 Rev 1.\n\nCompliance: Unless already accomplished, prior to further flight after 14 April 1993, thereafter: Part II: at each daily inspection,\n\nPart III: every 25 hours’ time in service.\n\nThis Directive must be entered onto the Maintenance Release as maintenance required. Part II of the Requirement document may be performed by the pilot in command in which case a certification is to be made by entering AD/A109/2 Amdt 3 against the Daily Inspection certification on the Maintenance Release. A copy of this Directive and the Requirement document must be carried in the aircraft.\n\nBackground: This Directive was initially raised as the result of longitudinal cracking of the blade root fitting due to stress corrosion. Amendment 1, refined the requirements and Amendment 2 provided for terminating action through fitment of -121 blades.\n\nAmendment 3 requires further work, and includes into the inspection the area diametrically opposed the original area.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The Directive began as an inspection for longitudinal cracking from stress corrosion in a specific blade‑root area. Amendment 1 refined requirements; Amendment 2 introduced a terminating action (fitment of -121 blades); Amendment 3 expands inspections to include the area diametrically opposed the original area and requires further work, thereby broadening the inspection scope (Background)."},"complexity_factors":["Specific applicability limited to three blade part‑numbers reduces scope of affected fleet","Mixed inspection schedule (immediate, daily Part II, and every 25 hours Part III) adds recurring compliance events","Pilot-authorised performance of Part II reduces need for licensed maintenance but creates a procedural certification step on the Maintenance Release","Availability of a terminating action (fitment of -121 blades mentioned in prior amendment) creates an alternative compliance path and potential replacement cost","Amendment history and inclusion of an additional inspection area (diametrically opposed) slightly increases technical detail operators must follow"],"plain_english_summary":"Mandates inspections and corrective work on Agusta A109 tail rotor blade root fittings (P/N 109-0132-02, -11, -15) in accordance with Agusta BT No. 109-51 Rev. B. Initial inspection is required before the next flight after 14 April 1993; thereafter Part II at each daily inspection and Part III every 25 flight hours. \n\nThis applies to aircraft operators and pilots: a copy must be carried aboard, compliance entered on the Maintenance Release (pilots may perform Part II and must certify it), and operators bear the cost and time of recurring inspections or blade modification/replacement."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"The directive has expanded beyond its original scope. Initially focused on a specific cracking area in the blade root fitting, Amendment 3 now requires inspection of an additional area 'diametrically opposed' to the original. This represents a broadening of the safety mandate based on operational experience or new failure data, rather than a simple clarification or procedural refinement."},"complexity_factors":["Short, single-purpose directive (approximately 250 words)","Only 3 defined part numbers for applicability","Simple conditional structure: initial compliance + two recurring intervals (daily/25-hour)","Cross-reference to external manufacturer document (Agusta BT No. 109-51 Rev. B) without reproducing its contents","One nested exception: pilot may perform Part II inspections with specific certification requirements","Minimal legislative cross-referencing (only mentions Civil Aviation Regulations 1998, Part 39)"],"plain_english_summary":"This Airworthiness Directive mandates inspection of tail‑rotor blade root fittings on Agusta A109 helicopters (blades P/N 109‑0132‑02, ‑11, ‑15) for stress‑corrosion cracks, with Amendment 3 expanding the inspected area.  \n\nIt requires immediate and recurring inspections, maintenance‑release recording, and retention of the directive aboard the aircraft to prevent catastrophic tail‑rotor failure and loss of directional control."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting","history":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting/history","analysis":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting/analysis","conflicts":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting/conflicts","importantCases":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting/important-cases","documents":"/api/acts/ad-a109-2-amdt-3-tail-rotor-blade-root-fitting/documents"}}