{"id":"F2006B03635","name":"AD/BEECH 1900/17 - Stabilon Attachment Angle","slug":"ad-beech-1900-17-stabilon-attachment-angle","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":43225,"registerId":"commonwealth-F2006B03635-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BEECH 1900/17 - Stabilon Attachment Angle","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)  \nBeechcraft 1900 Series Aeroplanes\n\nAD/BEECH 1900/17 Stabilon Attachment Angle 9/97\n\nDM\n\nApplicability: Model 1900D aircraft with serial numbers UE-1 through UE-215.\n\nRequirement: 1. Inspect the left and right stabilon attachment angles for proper thickness, which is\n\n.090 inch thick, in accordance with the Accomplishment Instructions section of Beechcraft Mandatory Service Bulletin (MSB) 2651.\n\n    2. If the attachment angles are not the correct thickness and measure only .071 inch thick, accomplish the following in accordance with the Accomplishment Instructions section of Beechcraft MSB 2651:\n\n    Repetitively inspect the stabilon attachment angles for cracks.\n\n    b. If cracks are evident, replace the attachment angles with attachment angles of the correct thickness (.090 inch thick); and,\n\n    c. If no cracks are evident during any of the inspections required by this directive, replace the .071 inch thick attachment angles with .090 inch thick attachment angles.\n\nNote: FAA AD 97-10-14 Amdt 39-10026 refers.\n\nCompliance: 1. Unless already accomplished, within 50 hours time in service after 16 July 1997.\n\n2. a. At intervals not to exceed 50 hours time in service.\n\n2. b. Before further flight.\n\n2. c. Within 600 hours time in service after 16 July 1997.\n\nNote: Replacing the .071 inch thick stabilon attachment angles with .090 inch thick attachment angles, terminates the repetitive inspection requirements of this Directive.\n\nBackground: The FAA received reports of the affected aircraft having the incorrect size stabilon attachment angles fitted. The actions specified by this Directive are intended to prevent separation of the stabilon from the aircraft, which could cause loss of aircraft stability during flight.","sortOrder":0}],"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 targeted safety directive addressing a specific manufacturing defect in a specific aircraft model. It has not expanded beyond its original purpose of preventing stabilon separation."},"complexity_factors":["Single, specific mechanical issue addressed (stabilon bracket thickness)","Only 2 defined measurements (.071 inch vs .090 inch)","Clear conditional logic: IF wrong thickness THEN inspect/replace","No nested exceptions or cross-references to other legislation","Single applicability criterion (specific serial number range)","Straightforward compliance timeline (50 hours, 600 hours, or before flight)","Background explanation included for context"],"plain_english_summary":"CASA orders owners/operators of Beechcraft 1900D aeroplanes (serials UE-1–UE-215) to inspect the stabilon attachment angle after some were found at 0.071\" instead of the required 0.090\", a defect that could let the stabilon detach and cause loss of control. \n\nIf undersize, recurring 50‑flight‑hour crack inspections and replacement rules apply (immediate if cracked; replacement within 600 flight hours if not); compliant parts require no action. This directive is legally binding."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The directive confines its scope to specified Model 1900D serial numbers and implements inspection and replacement actions that align with the stated FAA-reported problem (incorrect attachment angles). It does not expand applicability or introduce new categories of requirements beyond the corrective actions described in the Background and Requirements; procedural detail is delegated to Beechcraft MSB 2651 and the referenced FAA AD."},"complexity_factors":["Technical measurement tolerance: requires distinguishing .090 inch correct parts from .071 inch incorrect parts (Requirement 1 and Requirement 2).","Conditional workflow: if incorrect parts are found, directive requires repetitive crack inspections and conditional replacement (Requirement 2.a–c).","Repetitive inspection cadence and deadlines: initial inspection within 50 flight hours, inspections at intervals not to exceed 50 hours, and mandatory replacement within 600 hours if uncracked (Compliance 1; Compliance 2.a and 2.c).","Safety-critical immediate action: any cracks require replacement before further flight (Requirement 2.b; Compliance 2.b), creating potential operational grounding.","Narrow applicability: applies only to Model 1900D serial numbers UE-1 through UE-215 (Applicability).","Procedural dependence on manufacturer guidance: Accomplishment Instructions in Beechcraft MSB 2651 provide the required inspection and replacement methods (Requirement and Note).","Operational and supply risks: parts availability and maintenance capacity affect ability to meet repetitive inspection and replacement schedule (implied by Replacement/termination note and Compliance timing)."],"plain_english_summary":"Requires operators of Beechcraft 1900D aeroplanes (serial numbers UE-1 to UE-215) to inspect stabilon attachment angles for correct thickness (.090 in) and to either perform repetitive crack inspections or replace undersized (.071 in) angles with .090 in parts. The aim, as stated, is to prevent stabilon separation. Owners/operators pay for inspections, repairs and downtime; the Civil Aviation Safety Authority mandates compliance and delegates procedural detail to Beechcraft Mandatory Service Bulletin 2651 and the referenced FAA AD."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle","history":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle/history","analysis":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle/analysis","conflicts":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle/conflicts","importantCases":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle/important-cases","documents":"/api/acts/ad-beech-1900-17-stabilon-attachment-angle/documents"}}