{"id":"F2006B04204","name":"AD/BEECH 90/102 - Engine Controls Cross Shaft","slug":"ad-beech-90-102-engine-controls-cross-shaft","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":43960,"registerId":"commonwealth-F2006B04204-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# ![](image.001.png)  \nAIRWORTHINESS DIRECTIVE\n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\n![](image.001.png)\n\nBeechcraft 90 and 65-90 (King Air) Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/BEECH 90/102 Engine Controls Cross Sh","sectionType":"part","heading":"AD/BEECH 90/102 Engine Controls Cross Shaft 11/2004","content":"# AD/BEECH 90/102 Engine Controls Cross Shaft 11/2004\n\nApplicability: Raytheon (Formely Beech) 65-A90, B90, C90, C90A, E90 and F90 aeroplanes having serial numbers as detailed in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634, dated September 2003.\n\nRequirement: 1. Inspect the engine controls/cross shaft/pedestal for proper installation and carry out a torque check of the attach bolts, in accordance with Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634.\n\n    2. If any improper installation or wrong torque is found during any inspection required by Requirement 1 of this Directive, correct the installation or torque in accordance with Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634.\n\n    3. Unless previously accomplished modify the pedestal and replace the engine controls cross shaft hardware in accordance with Part II, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634.\n\nModification of the pedestal and replacement of the engine controls cross shaft hardware is the terminating action for the repetitive inspection and re-torque requirements specified in Requirement 1 of this Directive.\n\nNote 1: FAA AD 2004-17-02 Amdt 39-13774 refers.\n\nNote 2: The aeroplane maintenance manual also addresses the issues detailed in Requirements 1,2 and 3 of this Directive.\n\nCompliance: For Requirement 1: Initially inspect within the next 50 hours’ time-in-service (TIS) after the effective date of this Directive, unless already done within the last 50 hours TIS, and thereafter at intervals not to exceed 100 hours TIS until the modification in Requirement 3 of this Directive is done.\n\nFor Requirement 2: Before further flight.\n\nFor Requirement 3: At the next scheduled Maintenance/inspection interval or 12 calendar months after the effective date of this Directive, whichever occurs later.","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This AD stays within the original safety‑remedial scope: it addresses a specific unsafe condition related to the engine controls cross‑shaft/pedestal for the enumerated Beechcraft 90 series aeroplanes. It does not broaden applicability beyond the serial‑numbered aircraft listed in the Raytheon service bulletin, nor does it add unrelated mandates. The main structural effect is to require a short‑term repetitive inspection regime until a manufacturer‑specified modification (a one‑time action) is completed, which is consistent with a targeted corrective objective rather than an expansion of scope."},"complexity_factors":["Applicability limited to specific models and serial numbers as listed in an external Service Bulletin (SB 73‑3634).","Three discrete requirements: inspect/torque check (Req 1), correct before next flight if defects found (Req 2), and modify/replace hardware as terminating action (Req 3).","Repetitive inspection schedule with termination: initial inspection within 50 hours unless already done; repeat every 100 hours until modification completed.","Conditional compliance timing for terminating action: at next scheduled maintenance or within 12 calendar months, whichever is later.","Dependency on external documents: Raytheon Mandatory Service Bulletin Parts I and II and airplane maintenance manual for procedural detail.","Cross‑reference to FAA AD 2004‑17‑02 (Note 1), adding an external regulatory reference.","Operationally critical ‘before further flight’ corrective action requirement, which can cause immediate grounding and operational disruption."],"plain_english_summary":"**What this directive does (mechanics)\n\n- Applies to: Beechcraft (Raytheon) 65–A90, B90, C90, C90A, E90 and F90 aircraft with the serial numbers listed in Raytheon Mandatory Service Bulletin SB 73‑3634 (see Applicability).\n\n- Mandatory actions required: (Requirement section)\n  - Inspect the engine control cross‑shaft and its pedestal for correct installation and check the torque on the attach bolts (Requirement 1, Part I of the Service Bulletin).\n  - If anything is installed incorrectly or bolt torque is wrong, fix it before the aircraft flies again (Requirement 2, Part I of the Service Bulletin).\n  - Unless already done, modify the pedestal and replace the cross‑shaft hardware as described in Part II of the Service Bulletin. Completing that modification stops the need for the repeated inspections and torque checks (Requirement 3, Part II of the Service Bulletin).\n\n- Timing (Compliance section)\n  - Initial inspection: within the next 50 hours time‑in‑service (TIS) after the AD is effective (unless that inspection was already done in the previous 50 hours).\n  - Repeat inspections: at intervals not greater than 100 hours TIS until the pedestal modification and hardware replacement are completed.\n  - Corrections for any defects found: must be done before further flight.\n  - The pedestal modification/hardware replacement (the terminating action) must be done at the next scheduled maintenance/inspection or within 12 calendar months of the AD’s effective date, whichever is later.\n\n- Documents and references\n  - The detailed procedures are in Raytheon Aircraft Company Mandatory Service Bulletin SB 73‑3634 (Parts I and II).\n  - The AD also refers to FAA AD 2004‑17‑02 and the airplane maintenance manual for related guidance.\n\nWho is affected and who pays\n\n- Directly affected: operators and owners of the specific Beechcraft 90 series aeroplanes identified by serial number in SB 73‑3634.\n- Who pays: owners/operators pay for the inspections, any corrective work, the pedestal modification and parts, and for the labour and downtime while the work is done. If the operator uses an approved maintenance organisation, that business performs the work and charges for it.\n\nWhy it matters (stated purpose and practical trade‑offs)\n\n- Stated purpose: the AD addresses an unsafe condition associated with the engine controls cross‑shaft/pedestal (background references the safety concern; see Note 1 and Requirement sections).\n- Practical trade‑offs and incentives:\n  - Costs are concentrated on the affected aircraft owners/operators (inspection labour and parts, possible aircraft downtime).\n  - Completing the pedestal modification and hardware replacement removes the need for repeated inspections, converting a recurring cost into a one‑time cost (Requirement 3).\n  - If an inspection finds incorrect installation or incorrect torque, the operator must correct it before the next flight (Requirement 2), which can cause immediate operational disruption.\n  - Maintenance organisations may see additional business from performing inspections and the terminating modification; operators may choose between in‑house maintenance or contracting it out.\n  - The AD depends on external documents (Raytheon SB and the maintenance manual). Compliance therefore requires access to those documents and to parts described by the manufacturer.\n\nImplementation and compliance risks\n\n- Implementation depends on operators scheduling inspections and the terminating modification within the prescribed windows (50/100 hours and within 12 months or next scheduled maintenance).\n- Failure to complete the required work risks continued operation with the unsafe condition; discovery of incorrect installation can lead to immediate grounding until corrected (Requirement 2).\n- The AD relies on the Service Bulletin (SB 73‑3634) for detailed instructions; any ambiguity or parts availability issues in that SB can increase compliance cost and delay.\n\nBottom line (behavioural effects, in plain terms)\n\n- Operators must inspect and torque‑check the engine controls cross‑shaft bolts repeatedly until they carry out a manufacturer‑specified pedestal modification and hardware replacement. Fixes for any defects found must be done before further flight. The pedestal modification eliminates the need for continued inspections, but it creates a one‑time cost and scheduling requirement for affected operators."},"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 Airworthiness Directive maintains its original narrow scope: addressing a specific unsafe condition in specific Beechcraft King Air models regarding engine control cross shaft installation. It has not expanded beyond this original safety purpose."},"complexity_factors":["Short, single-purpose instrument focused on one mechanical issue","Only 3 substantive requirements with clear sequential logic (inspect → fix if needed → permanent modification)","Cross-reference to one external technical document (Raytheon Service Bulletin SB 73-3634) for detailed instructions","Simple conditional structure: 'if improper installation found, then correct before flight'","Compliance deadlines use standard aviation terminology (hours time-in-service, calendar months) but are clearly specified","No nested definitions or interpretation sections — terms used are industry-standard aviation maintenance terms"],"plain_english_summary":"This safety order requires owners and operators of specified Raytheon/BC/King Air 65-A90, B90, C90 (and variants) listed in service bulletin SB 73-3634 to inspect and torque the engine control cross shaft bolts, remedy any improper installation or looseness before flight, and install a permanent hardware/mounting pedestal modification by the next overhaul or within 12 months.  \n\nIt prevents potential loss of engine power control in flight by stopping cross-shaft failures."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft","history":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft/history","analysis":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft/analysis","conflicts":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft/conflicts","importantCases":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft/important-cases","documents":"/api/acts/ad-beech-90-102-engine-controls-cross-shaft/documents"}}