{"id":"F2021L01010","name":"AD/BEECH 200/45 Amdt 5 Nose Gear Lower Shock Absorber Assembly","slug":"ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":101980,"registerId":"commonwealth-F2021L01010-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 200 (Super King Air) Series A","sectionType":"part","heading":"Beechcraft 200 (Super King Air) Series Aeroplanes","content":"# Beechcraft 200 (Super King Air) Series Aeroplanes\n\n| AD/BEECH 200/45 Amdt 5 | Nose Gear Lower ShockAbsorber Assembly | 15/2021 |\n| ---------------------- | -------------------------------------- | ------- |\n\n| Applicability: | Beechcraft Model 200 and B200, serial numbers BB-2, and BB-6 through BB-1314.Beechcraft Model 200C and B200C, serial numbers BL-1 through BL-72, and BL-124 through BL-131.Beechcraft Model 200CT and B200CT, serial numbers BN-1 through BN-4.Beechcraft Model 200T and B200T, serial numbers BT-1 through BT-33.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Inspect, using fluorescent liquid penetrant or magnetic particle method, the nose landing gear fork assembly for cracks, in accordance with Part II of Raytheon Aircraft Company Mandatory Service Bulletin (MSB) SB 32-2102 Revision 7, Revised: July 2003, as in force at the commencement of this AD.2. If cracks are found during the Requirement 1 inspection, incorporate Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable; in accordance with Part III of MSB SB 32-2102 Revision 7, Revised: July 2003 as in force at the commencement of this AD.3. If no cracks are found during the Requirement 1 inspection, repeat the inspection in accordance with Part II of MSB SB 32-2102 Revision 7, Revised: July 2003 as in force at the commencement of this AD.Note 1: Incorporation of Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable, is terminating action for the inspection requirements of this Directive.Note 2: FAA AD 2004-23-02 Amdt 39-13857 refers. |\n| Compliance:    | 1.a. For aircraft affected by the previous issue of this Directive, initially inspect within 200 hours time in service (TIS) after the last inspection required by the previous issue of this Directive.1.b. For aircraft not affected by the previous issue of this Directive, initially inspect within 200 hours TIS after the commencement of this Directive.2. Before further flight.3. At intervals not to exceed 200 hours TIS. If cracks are found during any inspection, incorporate Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable.                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n\n|             | Note 3: If the aircraft is on the manufacturer’s maintenance schedule then a planning tolerance of ± 10% can be applied to the 200 hour TIS periods detailed in Requirements 1 and 3 of this AD as provided in the manufacturer’s phase inspection schedules.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This AD commences on 17 August 2021.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| Background: | The manufacturer required a mandatory inspection of the nose gear lower shock absorber for evidence of slippage at the intersection of the tube and fork assembly, and a dye check of the weld area on the fork assembly.Amendment 2 introduced a modification kit which, if fitted, removes the repetitive inspection requirement.Amendment 3 required the same inspection requirements by a different inspection method but required incorporation of an improved nose landing gear fork kit anytime crack is found; and added additional aircraft to applicability.Amendment 4 was issued on 26 October 2006 and corrected an error in Requirement 3, where Part III of the referenced Beech MSB should have been Part II. This error flowed from related FAA AD 2004-23-02.Amendment 5 introduces a planning tolerance to align the inspections required with the aircraft phase inspection schedule detailed in the aircraft maintenance manual. |\n\n![Text\nDescription automatically generated](image.001.jpeg)\n\nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n16 July 2021","sortOrder":0},{"sectionNumber":"AD/BEECH 200/45 Amdt 5","sectionType":"part","heading":"AD/BEECH 200/45 Amdt 5","content":"## AD/BEECH 200/45 Amdt 5","sortOrder":1},{"sectionNumber":"Nose Gear Lower ShockAbsorber Assembly","sectionType":"part","heading":"Nose Gear Lower ShockAbsorber Assembly","content":"## Nose Gear Lower Shock  \nAbsorber Assembly","sortOrder":2},{"sectionNumber":"15/2021","sectionType":"part","heading":"15/2021","content":"## 15/2021","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"Originally intended as a straightforward safety inspection for nose gear cracks, the directive has expanded through five amendments. Amendment 2 added modification kits as terminating action, Amendment 3 changed inspection methods and expanded applicability to more aircraft, Amendment 4 corrected technical errors, and Amendment 5 (current) introduced planning tolerances to integrate with maintenance schedules. The scope has shifted from a rigid inspection mandate to a more flexible maintenance-schedule-aligned system, though the core safety purpose remains unchanged."},"complexity_factors":["Multiple aircraft models and specific serial number ranges listed in applicability table","Three distinct requirements with conditional logic (if cracks found vs. if no cracks found)","Cross-reference to external technical document (Raytheon MSB SB 32-2102 Revision 7)","Different compliance timelines for aircraft previously affected vs. not previously affected","Specific technical terminology (TIS - Time in Service, fluorescent liquid penetrant, magnetic particle method)","Reference to terminating action (modification kit installation ends inspection obligation)","Amendment history references (Amendments 2-5) creating contextual dependency"],"plain_english_summary":"This AD mandates crack-detection inspections of the nose landing-gear fork on specified Beechcraft Super King Air 200-series aircraft and requires replacement with an approved kit if cracks are found. Inspections must start within 200 flight hours and repeat every 200 hours until modified; following the manufacturer’s maintenance schedule gives a ±10% planning tolerance. It prevents nose-gear failure during landing/taxi and Amendment 5 adds alignment flexibility with routine maintenance."},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"The AD's scope and mechanics have evolved from the original: earlier amendments added a modification kit as terminating action and expanded affected aircraft; a later amendment changed the inspection method and corrected a drafting error; the current Amendment 5 adds a ±10% planning tolerance to align AD inspection intervals with manufacturer phase inspections. These changes adjust who must inspect, how often, what fixes terminate inspections, and permissible scheduling flexibility (Background; Requirement; Compliance; Note 3)."},"complexity_factors":["Multiple model and serial‑number ranges in applicability, requiring operators to check serial lists carefully (Applicability).","Technical inspection methods specified (fluorescent liquid penetrant or magnetic particle), requiring trained personnel and equipment (Requirement 1).","Inspections must be repeated at fixed flight‑hour intervals (200 hours TIS) with an exception for a ±10% planning tolerance if on the manufacturer’s schedule (Compliance; Note 3).","Installation of specific modification kits (Kit No. 101‑8030‑1S or 114‑8015‑1S) is mandatory if cracks are found and serves as terminating action for inspections, creating a binary remedial cost decision for owners (Requirement 2; Note 1).","The AD cross‑references an external service bulletin (Raytheon/Part II & III of MSB SB 32‑2102 Revision 7) and an FAA AD, tying compliance to documents 'as in force at the commencement of this AD', which creates dependency on external publications and revision status (Requirement; Note 2).","Amendment history includes prior changes to inspection method, added applicability, correction of a drafting error, and the latest insertion of planning tolerance, increasing interpretive complexity for which version applied to specific aircraft over time (Background).","A 'before further flight' requirement for corrective action when cracks are found imposes potential immediate grounding and logistic burdens on operators and maintenance providers (Compliance 2)."],"plain_english_summary":"Mandates regular non‑destructive inspections of the nose landing‑gear lower shock‑absorber fork on specified Beechcraft 200‑series aeroplanes and, if cracks are found, requires fitting a specified modification kit that terminates the repetitive inspections. It applies to owners/operators of the listed serial‑numbered aircraft and affects maintenance planning and repair costs by imposing 200‑hour inspection intervals (with a ±10% planning tolerance) and compulsory kit installation when defects are detected."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly","history":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly/history","analysis":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly/analysis","conflicts":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly/conflicts","importantCases":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly/important-cases","documents":"/api/acts/ad-beech-200-45-amdt-5-nose-gear-lower-shock-absorber-assembly/documents"}}