{"id":"F2007L01560","name":"AD/BEECH 1900/2 Amdt 2 - Nose Gear Lower Shock Absorber Assembly","slug":"ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66059,"registerId":"commonwealth-F2007L01560-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 1900 Series Aeroplanes","sectionType":"division","heading":"Beechcraft 1900 Series Aeroplanes","content":"### Beechcraft 1900 Series Aeroplanes\n\n| AD/BEECH 1900/2 Amdt 2 | Nose Gear Lower ShockAbsorber Assembly | 7/2007 |\n| ---------------------- | -------------------------------------- | ------ |\n\n| Applicability: | Model 1900, serial numbers UA-1 through UA-3.Model 1900C, serial numbers UB-1 through UB-74, and UC-1 through UC-78.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\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 2003.2. 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; as specified in MSBSB 32-2102 Revision 7, Revised: July 2003.3. 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.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 Corrected 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 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 time in service after 5 July 2007.2. Before further flight.3. At intervals not to exceed 200 hours time in service. If cracks are found during any inspection, incorporate Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable.The compliance times for Requirements 2 and 3 remain unchanged by this issue of the Directive.                                                                                                                                                                                                       |\n\n|             | This Airworthiness Directive becomes effective on 5 July 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\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 1 required the same inspection requirements by a different inspection method, but required incorporation of an improved nose landing gear fork kit anytime a crack is found; and added additional aircraft to applicability.Amendment 2 is issued to correct 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. |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n9 May 2007","sortOrder":0},{"sectionNumber":"AD/BEECH 1900/2 Amdt 2","sectionType":"part","heading":"AD/BEECH 1900/2 Amdt 2","content":"## AD/BEECH 1900/2 Amdt 2","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":"7/2007","sectionType":"part","heading":"7/2007","content":"## 7/2007","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"Amendment 2 corrects an incorrect cross‑reference in the referenced service bulletin (Part III should be Part II) as stated in the Background. The substantive requirements (inspection method, 200‑hour intervals, kit installation as terminating action, and applicability) and compliance times remain unchanged."},"complexity_factors":["Technical inspection methods required (fluorescent liquid penetrant or magnetic particle) — requires specialised maintenance capability (Requirement 1).","Dependence on an external service bulletin (Raytheon MSB SB 32-2102 Revision 7) for inspection procedures and repetition intervals.","Multiple serial‑number applicability ranges across Model 1900/1900C variants, requiring operators to check applicability precisely.","Staggered compliance timing depending on whether the operator was affected by the previous issue (Compliance 1.a vs 1.b).","Immediate action on detection: incorporation of specified kits before further flight (Compliance 2 & Requirement 2), creating potential operational downtime.","Kit incorporation is a terminating action for inspections (Note 1) — creates a clear but binary compliance pathway (inspect repeatedly or fit kit).","Historical cross‑reference error corrected by this amendment (Background) — risk of operator confusion if relying on earlier texts.","Reference to related FAA AD (Note 2) adds an external regulatory cross‑check requirement for some operators."],"plain_english_summary":"This Airworthiness Directive requires operators of specified Beechcraft 1900 series aircraft (listed serial ranges) to inspect the nose landing‑gear lower shock‑absorber fork for cracks using fluorescent liquid penetrant or magnetic‑particle methods, repeat inspections every 200 flight hours, and install Kit No. 101-8030-1S or 114-8015-1S if cracks are found; kit installation terminates the inspection requirement.\n\nThe directive places inspection, repair and downtime costs on aircraft owners/operators and requires maintenance providers with non‑destructive testing capability; Amendment 2 corrects a service‑bulletin cross‑reference (Part III → Part II) without changing compliance times."},"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":false,"description":"This Amendment 2 is purely corrective — it fixes a typographical error in Requirement 3 (changing 'Part III' to 'Part II' of the referenced service bulletin). The substantive safety requirements and aircraft applicability remain identical to Amendment 1. The scope has not expanded beyond the original safety purpose of preventing nose gear fork failures."},"complexity_factors":["Multiple serial number ranges defining applicability (3 distinct groups across 2 models)","Conditional compliance paths based on whether aircraft were affected by previous directive version","Cross-reference to external technical document (Raytheon MSB SB 32-2102 Revision 7)","Nested conditional logic: different actions required depending on inspection results (cracks found vs. not found)","Terminating action provision that ends recurring inspection requirement","Amendment structure requiring understanding of previous versions (Amendment 1 and original) to fully comprehend current requirements","Specific technical terminology (fluorescent liquid penetrant, magnetic particle method, time in service)"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of specified Beechcraft 1900/1900C serials to inspect the nose landing‑gear fork for cracks using fluorescent penetrant or magnetic particle testing per the manufacturer’s service bulletin. If cracks are found the fork must be replaced with an improved kit before flight; if not, inspections repeat every 200 flight hours until the kit is fitted. This Amendment 2 corrects a paperwork reference in the service bulletin."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly","history":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly/history","analysis":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly/analysis","conflicts":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly/conflicts","importantCases":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly/important-cases","documents":"/api/acts/ad-beech-1900-2-amdt-2-nose-gear-lower-shock-absorber-assembly/documents"}}