{"id":"F2007L01559","name":"AD/BEECH 300/20 - Nose Gear Lower Shock Absorber Assembly","slug":"ad-beech-300-20-nose-gear-lower-shock-absorber-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":66057,"registerId":"commonwealth-F2007L01559-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 300 Series Aeroplanes","sectionType":"division","heading":"Beechcraft 300 Series Aeroplanes","content":"### Beechcraft 300 Series Aeroplanes\n\n| AD/BEECH 300/20 | Nose Gear Lower ShockAbsorber Assembly | 7/2007 |\n| --------------- | -------------------------------------- | ------ |\n\n| Applicability: | Model 300 aircraft, serial numbers FA-1 through FA-168 and FF-1 through FF-19.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           |\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. Unless the initial inspection is already accomplished, 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|                | This Airworthiness Directive becomes effective on 5 July 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           |\n\n| Background: | The FAA received reports of cracks in the nose landing gear fork on several Raytheon aircraft. The actions required by this Directive are intended to detect and correct cracks in the nose landing gear fork, which could result in reduced structural integrity and inability of the nose landing gear fork to carry design limit and ultimate loads. The reduced residual strength may cause separation failure of the nose landing gear fork, which could result in loss of control of the aircraft during takeoff, landing, and taxi operations. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n9 May 2007","sortOrder":0},{"sectionNumber":"AD/BEECH 300/20","sectionType":"part","heading":"AD/BEECH 300/20","content":"## AD/BEECH 300/20","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":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive maintaining its original purpose: addressing a specific safety defect in specific aircraft. The scope remains tightly focused on the nose landing gear fork assembly issue as originally identified."},"complexity_factors":["Short, single-purpose document focused on one mechanical issue","Clear three-step requirement structure (inspect, repair if needed, repeat if clear)","Specific technical references to manufacturer bulletins (MSB SB 32-2102 Revision 7) and kit numbers","Simple conditional logic (if cracks found → repair; if no cracks → re-inspect)","Limited applicability (specific aircraft models and serial numbers only)","No nested definitions or extensive cross-referencing to other legislation","Contains only 2 terminating notes and 1 external reference (FAA AD)"],"plain_english_summary":"This AD requires owners/operators of specified Beechcraft 300 serials to inspect the nose landing gear fork for cracks using approved non‑destructive methods, initially within 200 flight hours after 5 July 2007 and then every 200 hours if no crack is found. Any cracked fork must be replaced with the approved repair kit before flight; installing the kit ends the repetitive inspections. It’s issued to prevent nose‑gear collapse and loss of control."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This directive stays focused on the original safety objective: detect and correct cracks in the nose landing gear fork on specified Beechcraft Model 300 serial numbers. Mechanically it requires inspections and, if necessary, installation of specified kits; installation is explicitly a terminating action. The directive does not expand applicability beyond the listed serial numbers, introduce new unrelated requirements, or add broader regulatory powers. It therefore does not materially change the scope beyond the original airworthiness concern described in the background and as reflected in the referenced FAA action and the Raytheon service bulletin."},"complexity_factors":["Single narrow subject (nose landing gear fork) and limited aircraft population (specific serial ranges).","Three explicit substantive requirements (inspect; install kit if cracks found; repeat inspection if no cracks).","Two accepted inspection methods (fluorescent liquid penetrant and magnetic particle) requiring qualified technicians.","Cross‑reference to an external document: Raytheon MSB SB 32‑2102 Revision 7 (Part II) — procedural detail delegated outside the directive.","Two terminating kit options (Kit No. 101‑8030‑1S and Kit No. 114‑8015‑1S) and a terminating action clause (stops recurring inspections).","Simple compliance timing rules (inspect within 200 hours after effective date; repeat every 200 hours; repair before further flight if crack found).","Cross‑reference to a related FAA Corrected AD (administrative cross‑jurisdictional reference)."],"plain_english_summary":"**What this directive requires (mechanical change):**\n\n- Applies to Beechcraft Model 300 aeroplanes, serial numbers FA‑1 through FA‑168 and FF‑1 through FF‑19.\n- Requires inspections of the nose landing gear fork (the lower shock absorber assembly) for cracks using either fluorescent liquid penetrant or magnetic particle inspection, following Part II of Raytheon Mandatory Service Bulletin SB 32‑2102 Revision 7 (July 2003). (These are non‑destructive inspection methods used to reveal surface and near‑surface cracks.)\n- If cracks are found, the operator must install either Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S as specified in the service bulletin. Installing either kit stops (terminates) the need for the recurring inspections required by this directive.\n- If no cracks are found, the inspections must be repeated at intervals not exceeding 200 flight hours.\n\n**When it must be done (compliance timing):**\n\n- If the initial inspection has not yet been done, it must be carried out within 200 flight hours after 5 July 2007.\n- If an inspection reveals a crack, the repair/kit installation must be done before the next flight.\n- If an inspection does not reveal a crack, repeat inspections must occur every 200 flight hours until terminating action (kit installation) is completed.\n\n**Why the rule exists (stated purpose):**\n\n- The regulator and FAA received reports of cracks in the nose landing gear fork on several Raytheon aircraft. The directive’s stated purpose is to detect and correct these cracks because an undetected crack could weaken the fork, potentially leading to separation failure and loss of control during takeoff, landing or taxi.\n\n**Who pays and who decides:**\n\n- Aircraft owners/operators of the affected Model 300 serial numbers are responsible for arranging and paying for inspections, any necessary kit installation, parts and associated labour. A licensed maintenance organisation or suitably qualified maintenance personnel must perform the inspections and kit installations in accordance with the referenced service bulletin. The regulator (Civil Aviation Safety Authority, per the signature on the document) enforces compliance.\n\n**Costs, incentives and trade‑offs:**\n\n- Direct costs: inspection labour and consumables (for penetrant or magnetic particle inspection), and if cracks are found or the owner chooses the terminating option, the one‑off cost of Kit No. 101‑8030‑1S or Kit No. 114‑8015‑1S plus installation labour.\n- Recurring costs versus one‑off cost: operators can either accept recurring inspections (every 200 hours) or install a kit which eliminates future inspection requirements under this directive. Installing the kit is a concentrated upfront cost that terminates a diffuse, ongoing inspection burden.\n- Operational costs: aircraft downtime for inspection and possible kit installation; scheduling and potential disruption to flight operations.\n- Implementation risks: the inspection methods require skilled technicians; improper technique can give false negatives (missed cracks) or false positives (unnecessary repairs). Availability of kits and replacement parts could affect downtime.\n- Compliance and enforcement: compliance is time‑based (hours in service) and enforced by the regulator; documentation of inspections/repairs is necessary to show compliance.\n\n**Effects on markets and choices:**\n\n- Demand for qualified maintenance services and the specified kits will increase among owners of affected serial numbers.\n- Owners face a choice: continue periodic inspections (recurring cost and operational disruption) or pay for kit installation (one‑off cost and immediate downtime) to remove the inspection obligation.\n\n**Implementation notes and cross‑references:**\n\n- The directive explicitly requires following Part II of Raytheon MSB SB 32‑2102 Revision 7 (July 2003). Operators must have access to that service bulletin and comply with its detailed procedures.\n- The directive also refers to a related FAA Corrected AD (2004‑23‑02 Amdt 39‑13857), signalling coordination with the FAA on the airworthiness concern.\n\n(References in this summary: Requirement items 1–3 and Compliance items 1–3; Note 1 on terminating action; background paragraph.)"},"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-300-20-nose-gear-lower-shock-absorber-assembly","history":"/api/acts/ad-beech-300-20-nose-gear-lower-shock-absorber-assembly/history","analysis":"/api/acts/ad-beech-300-20-nose-gear-lower-shock-absorber-assembly/analysis","conflicts":"/api/acts/ad-beech-300-20-nose-gear-lower-shock-absorber-assembly/conflicts","importantCases":"/api/acts/ad-beech-300-20-nose-gear-lower-shock-absorber-assembly/important-cases","documents":"/api/acts/ad-beech-300-20-nose-gear-lower-shock-absorber-assembly/documents"}}