{"id":"F2007L01557","name":"AD/BEECH 90/75 Amdt 5 - Nose Landing Gear Lower Shock Absorber Assembly","slug":"ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66051,"registerId":"commonwealth-F2007L01557-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 90 and 65-90 (King Air) Serie","sectionType":"division","heading":"Beechcraft 90 and 65-90 (King Air) Series Aeroplanes","content":"### Beechcraft 90 and 65-90 (King Air) Series Aeroplanes\n\n| AD/BEECH 90/75 Amdt 5 | Nose Landing Gear LowerShock Absorber Assembly | 7/2007 |\n| --------------------- | ---------------------------------------------- | ------ |\n\n| Applicability: | Model 65-90, 65-A90, B90, C90, and C90A, serial numbers LJ-1 through LJ-1190.Model E90, serial numbers LW-1 through LW-347.Model F90, serial numbers LA-2 through LA-236.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\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.                                                                                                                                                                                                                                                                                                     |\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 Requirements 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 90/75 Amdt 5","sectionType":"part","heading":"AD/BEECH 90/75 Amdt 5","content":"## AD/BEECH 90/75 Amdt 5","sortOrder":1},{"sectionNumber":"Nose Landing Gear LowerShock Absorber As","sectionType":"part","heading":"Nose Landing Gear LowerShock Absorber Assembly","content":"## Nose Landing Gear Lower  \nShock Absorber Assembly","sortOrder":2},{"sectionNumber":"7/2007","sectionType":"part","heading":"7/2007","content":"## 7/2007","sortOrder":3}],"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"Amendment 5 corrects a referencing error—Requirement 3 should cite Part II of the Raytheon MSB rather than Part III—without expanding or narrowing applicability, inspection methods, or the kit‑installation requirement. The Directive’s operative scope and terminating action remain as before (Background)."},"complexity_factors":["External procedural cross‑reference: Mandatory inspection and repair steps are defined by Raytheon MSB SB 32‑2102 Revision 7 rather than set out in full in the Directive, requiring operators to obtain and follow that document (Requirement).","Specified NDT techniques: The Directive mandates particular non‑destructive test methods (fluorescent liquid penetrant or magnetic particle), which impose technical skill and tooling requirements on maintenance providers (Requirement).","Model/serial specificity: Applicability is limited to multiple model variants and specific serial number ranges, requiring operators to verify applicability precisely for each airframe (Applicability).","Terminating action via named kits: The Directive requires installation of specific kit part numbers (101‑8030‑1S or 114‑8015‑1S) when cracks are found; fitting a kit terminates the repetitive inspection obligation (Requirement; Note 1).","Staggered compliance windows: Initial inspection timing depends on whether the aircraft was covered by a prior issue of the Directive, creating two separate start‑dates and record‑checking obligations (Compliance 1.a/1.b).","Repetitive inspection burden: If no cracks are found, inspections must be repeated at intervals not exceeding 200 hours TIS, imposing recurring cost and aircraft downtime until terminating action is taken (Compliance 3).","Drafting correction risk: This amendment corrects a reference (Part III → Part II) in Requirement 3; such corrections can cause temporary uncertainty for compliance officers and maintenance providers (Background).","Cross‑jurisdictional reference: The Directive notes an FAA corrected AD (2004‑23‑02) as related material, so operators may need to consult foreign AD material for full context (Requirement Note 2).","Who pays and who decides: Aircraft owners/operators bear inspection and repair costs and must decide whether to continue recurring inspections or install the kit; maintenance providers execute the required NDT and kit installation (Requirement; Compliance)."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of specified Beechcraft 65-90/90 series aeroplanes (serial ranges listed in Applicability) to inspect the nose landing gear lower shock absorber fork for cracks using fluorescent liquid‑penetrant or magnetic‑particle methods and, if cracks are found, fit a specified repair kit. Installing the kit ends the repetitive 200‑hour inspections; the amendment corrects a drafting error in the referenced service bulletin part. (Requirement; Compliance; Background.)"},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"Originally focused on inspecting for slippage at tube/fork intersection and dye checking welds. Amendment 3 added modification kit option. Amendment 4 expanded applicability to additional aircraft serial numbers and mandated kit installation when cracks found (rather than just repair). Amendment 5 is purely corrective (fixing a citation error), but the directive has grown significantly from its original inspection-only purpose to now mandating specific hardware modifications and covering a broader fleet."},"complexity_factors":["Multiple amendment history (Amendment 5) requiring cross-referencing with previous versions to understand full compliance obligations","Dual-path compliance structure depending on whether aircraft was covered by previous directive (1.a vs 1.b)","Conditional logic: different actions required based on inspection results (crack found vs no crack found)","Specific technical references to manufacturer service bulletins (MSB SB 32-2102 Revision 7) and kit numbers (101-8030-1 S, 114-8015-1 S)","Cross-reference to foreign aviation authority documentation (FAA AD 2004-23-02)","Time-based compliance measured in 'hours time in service' rather than calendar dates (except for effective date)","Terminating action provision that modifies ongoing obligations"],"plain_english_summary":"This CASA Airworthiness Directive mandates repeated non‑destructive inspection of the nose landing‑gear fork on specific Beechcraft 90‑series aircraft (about 1,500 units) and requires replacement with an approved modification kit if cracks are found. If no cracks are detected, inspections recur every 200 flight hours; installing the kit eliminates the recurring inspections.\n\nThe AD addresses a safety risk of landing‑gear failure from fatigue cracks and corrects a paperwork error in the FAA bulletin referenced in the prior version."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly","history":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly/history","analysis":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly/analysis","conflicts":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly/conflicts","importantCases":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly/important-cases","documents":"/api/acts/ad-beech-90-75-amdt-5-nose-landing-gear-lower-shock-absorber-assembly/documents"}}