{"id":"F2007L01558","name":"AD/BEECH 65/61 Amdt 5 - Nose Gear Lower Shock Absorber Assembly","slug":"ad-beech-65-61-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":66054,"registerId":"commonwealth-F2007L01558-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 65 and 70 (Queen Air) Series ","sectionType":"division","heading":"Beechcraft 65 and 70 (Queen Air) Series Aeroplanes","content":"### Beechcraft 65 and 70 (Queen Air) Series Aeroplanes\n\n| AD/BEECH 65/61 Amdt 5 | Nose Gear Lower ShockAbsorber Assembly | 7/2007 |\n| --------------------- | -------------------------------------- | ------ |\n\n| Applicability: | Model A65 and A65-8200, serial numbers LC-240 through LC-335.Model 70, serial numbers LB-1 through LB-35.Model 65-A80, 65-A80-8800, and 65-B80, serial numbers LD-151 through LD-511.Model 65-88, serial numbers LP-1 through LP-26, LP-28, and LP-30 through LP-47.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 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.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 MSB SB32-2102 Revision 7, Revised: July 2003.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.                                                                                                                                                                                                                                                                                            |\n\n|             | 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| 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 3 introduced a modification kit which, if fitted, removes the repetitive inspection requirement.Amendment 4 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 5 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\n16 May 2007","sortOrder":0},{"sectionNumber":"AD/BEECH 65/61 Amdt 5","sectionType":"part","heading":"AD/BEECH 65/61 Amdt 5","content":"## AD/BEECH 65/61 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":"7/2007","sectionType":"part","heading":"7/2007","content":"## 7/2007","sortOrder":3}],"analysis":{"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"Amendment 5 corrects an erroneous cross-reference in Requirement 3 (it should cite Part II of the Raytheon MSB, not Part III) but does not alter the substantive inspection requirements, kit terminating action, applicability or the stated compliance times. The Directive explicitly notes compliance times remain unchanged."},"complexity_factors":["Multiple specific model and serial-number applicability ranges (precision required to identify affected aircraft)","Dependence on an external document (Raytheon MSB SB 32-2102 Revision 7, Part II) for inspection procedures and intervals","Two accepted non-destructive inspection methods specified (fluorescent liquid penetrant or magnetic particle)","Mandatory terminating-action kits with precise kit numbers (Kit No. 101-8030-1S or 114-8015-1S)","Staggered initial compliance timing depending on whether aircraft were affected by prior Directive issue","Correction of an internal reference (Requirement 3 should refer to Part II, not Part III) creates interpretation risk if not noted","Cross-reference to a related FAA AD and historical amendments increases traceability effort for operators and maintainers"],"plain_english_summary":"This Airworthiness Directive requires operators of specified Beechcraft 65/70 (Queen Air) aeroplanes to inspect the nose landing gear lower shock absorber fork for cracks using fluorescent liquid penetrant or magnetic particle methods per Raytheon MSB SB 32-2102 Revision 7. If cracks are found, operators must fit Kit No. 101-8030-1S or 114-8015-1S; fitting the kit stops the repetitive inspections. Owners/operators pay for inspections and kit installation; the Civil Aviation Safety Authority enforces the timing and compliance."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"Originally this AD only required inspections for slippage and dye checks of weld areas. Through Amendments 3, 4, and 5, it has expanded to: (1) introduce modification kits as terminating action, (2) mandate kit installation whenever cracks are found rather than allowing repairs, (3) add additional aircraft serial numbers to applicability, (4) change inspection methods, and (5) correct technical referencing errors. The current version is substantially broader than the original inspection-only directive."},"complexity_factors":["Multiple serial number ranges across five different aircraft models in applicability table","Conditional compliance paths: different deadlines for aircraft previously affected vs. new aircraft","Three-tier requirement structure (initial inspection, immediate action if cracked, repetitive inspection if clear)","Cross-reference to external technical document (Raytheon MSB SB 32-2102 Revision 7) for detailed procedures","Reference to corresponding FAA directive (AD 2004-23-02) for context","Amendment history tracking (Amendments 3, 4, and 5) showing evolution of requirements"],"plain_english_summary":"This AD requires owners/operators of specified Beechcraft Queen Air models/serials to inspect the nose landing-gear fork for cracks using fluorescent liquid penetrant or magnetic particle testing. If cracks are found, the aeroplane is grounded until an approved repair kit is installed; if clear, inspections recur every 200 flight hours until the kit is fitted.\n\nIt matters because fork fatigue could cause nosewheel collapse during taxi or landing, so these checks prevent potential accidents."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly","history":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly/history","analysis":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly/analysis","conflicts":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly/conflicts","importantCases":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly/important-cases","documents":"/api/acts/ad-beech-65-61-amdt-5-nose-gear-lower-shock-absorber-assembly/documents"}}