{"id":"F2006B04244","name":"AD/BEECH 90/56 Amdt 3 - Fuselage Structural Fatigue","slug":"ad-beech-90-56-amdt-3-fuselage-structural-fatigue","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":44025,"registerId":"commonwealth-F2006B04244-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BEECH 90/56 Amdt 3 - Fuselage Structural Fatigue","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \n![](image.002.png)  \nBeechcraft 90 and 65-90 (King Air) Series Aeroplanes\n\nAIRWORTHINESS DIRECTIVE\n\n![](image.002.png)\n\n![](image.002.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 90/56 Amdt 2 and issues the following AD under subregulation 39.1 (1) of CAR 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\nAD/BEECH 90/56\n\nAmdt 3\n\n  \nFuselage Structural Fatigue 12/2000\n\nApplicability: Models 65-90, 65-A90, B90, C90, C90A and E90.\n\nRequirement: Inspect the fuselage structure, and retire the fuselage life-limited components, in accordance with Section 5-11-00, Fuselage and Associated Structure, in the Beech King Air 90 Maintenance Manual P/N 90-590012-13B7 as Revised July 30 1999.\n\nCompliance: Not later than the times shown in the Beech King Air 90 Maintenance Manual.\n\nNote: Compliance with previous issues of this Directive, satisfies the initial inspection requirements of this issue.\n\nThis Amendment becomes effective on 30 November 2000.\n\nBackground: The original issue of this AD promulgated a fatigue life limitation for the fuselage. It became effective on 31 March 1981.\n\nAmendment 1 became effective on 7 October 1999 and allowed continued operation beyond the previous life limitation, based on an inspection program developed by the manufacturer and published in the maintenance Manual.\n\nAmendment 2 was issued on 2 December 1999 to correct administrative problems which occurred during processing of Amendment 1.\n\nAmendment 3 corrects a minor error and reflects the current amendment status of the Maintenance Manual.\n\n![](image.003.png)  \n\nDavid Alan Villiers\n\nDelegate of the Civil Aviation Safety Authority 17 October 2000\n\n![](image.002.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 1 November 2000.","sortOrder":0}],"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":3,"scope_assessment":{"changed":true,"description":"Yes. The original AD (1981) imposed a fixed fuselage fatigue life limitation. A later amendment replaced that fixed life-limit approach with an inspection-based regime developed by the manufacturer, allowing continued operation beyond the prior life limit subject to inspection (see Background and Requirement). Amendment 3 itself is a minor correction and alignment to the current Maintenance Manual, but the substantive scope change occurred when the AD moved from a strict life-limit to an inspection programme (Background; Requirement)."},"complexity_factors":["Short text (single-page AD) with limited clauses","Direct applicability list (6 model variants)","Primary regulatory content defers to an external document: Section 5-11-00 of the Beech King Air 90 Maintenance Manual (requires access to that manual)","Compliance timing and detail are contained in the external manual rather than the AD itself","Simple exception: previous compliance with earlier AD issues satisfies the initial inspection requirement (one nested conditional)","Amendment history and the need to reference the correct manual revision add administrative tracking complexity"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- Requires owners/operators of certain Beechcraft 90/65-90 (King Air) aeroplanes to inspect the fuselage structure and to retire (remove from service) fuselage components that have a life limit, following the procedures in the manufacturer’s maintenance manual. (Requirement)\n- Specifies which models are covered: Models 65-90, 65-A90, B90, C90, C90A and E90. (Applicability)\n- Tells operators to follow the timing and intervals shown in the Beech King Air 90 Maintenance Manual (Section 5-11-00). (Compliance)\n- Notes that if an operator complied with previous issues of this same Airworthiness Directive, that satisfies the initial inspection obligation under this amendment. (Note)\n\n**Who this affects**\n\n- Aircraft owners and operators of the listed Beechcraft 90/65-90 (King Air) models. (Applicability)\n- Maintenance organisations and licensed engineers who perform fuselage inspections and carry out component retirement and replacement per the manufacturer’s manual. (Requirement; Compliance)\n- Potentially parts suppliers who supply life-limited fuselage components when retired parts must be replaced.\n\n**Why it matters (stated purpose, and how the rule achieves it)**\n\n- The stated purpose is to address fuselage structural fatigue by either limiting life or managing continued operation through inspections. The AD implements that purpose by requiring inspections and retirement of life-limited parts according to the manufacturer’s program in the maintenance manual. (Background; Requirement)\n\n**Costs, incentives and trade-offs (practical effects)**\n\n- Who pays: aircraft owners/operators pay for inspections, any required maintenance downtime, and replacement of retired components. (Requirement; Compliance)\n- Who decides: the Civil Aviation Safety Authority (CASA) delegate issues the AD; the manufacturer defines the inspection program and timing in the Maintenance Manual that the AD requires operators to follow. The operator must follow the manual’s instructions. (Requirement; Compliance)\n- Behavioural change required: operators must implement an inspection programme for the fuselage and must remove life-limited items when required; some operators who previously relied on a fixed life limit may instead rely on ongoing inspections to extend service life. (Background; Requirement)\n- Costs vs. benefits: inspections increase maintenance cost and aircraft downtime but can allow continued operation beyond a prior fixed life limit if inspections show the structure remains airworthy. The AD shifts the control of the ongoing safety regime to an inspection-based approach specified by the manufacturer. (Background; Requirement)\n\n**Implementation risks and practical notes**\n\n- The AD cross-references the manufacturer’s Maintenance Manual (Section 5-11-00). Practical compliance therefore requires access to the correct revision of that manual and the ability to perform or contract the specified inspections. (Requirement; Compliance)\n- The AD does not reproduce inspection intervals or procedures itself; it defers to the manual for timing and detail. That creates dependence on the manual’s accuracy and on keeping up with its revisions. (Requirement; Compliance)\n- The AD clarifies that earlier compliance with prior versions satisfies the initial inspection requirement, reducing duplicate work for operators who already complied. (Note)\n\n**History and scope change (brief)**\n\n- The original AD (1981) imposed a fuselage fatigue life limitation. A later amendment (1999) replaced the strict life limit with an inspection programme published by the manufacturer, allowing continued operation beyond the former limit subject to inspection. This amendment (Amdt 3) corrects a minor error and aligns the AD with the current Maintenance Manual revision. (Background)\n\n**Concrete mechanics to follow immediately**\n\n- Locate Section 5-11-00, Fuselage and Associated Structure, in the Beech King Air 90 Maintenance Manual (P/N 90-590012-13B7, Rev. as of July 30, 1999 or later revision specified by the operator’s approved procedures).\n- Complete the inspections and retire life-limited components according to the procedures and intervals in that section, by the times specified in the manual. (Requirement; Compliance)\n\n(References in text: Applicability; Requirement; Compliance; Note; Background)"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment remains tightly focused on its original purpose: managing fuselage fatigue life limitations for specific Beechcraft King Air 90 models. Amendment 3 makes only administrative corrections (fixing a minor error and updating the maintenance manual reference) without expanding the aircraft types covered, the safety actions required, or the operational circumstances. The scope has remained consistent since the original 1981 issue."},"complexity_factors":["Short, single-purpose directive (approximately 400 words)","Only 6 specific aircraft models listed in applicability section","Single requirement with clear cross-reference to manufacturer maintenance manual","No nested exceptions or conditional logic — compliance is mandatory with straightforward deadlines","Minimal defined terms (only standard aviation acronyms like AD, CASA, P/N)","Background section provides clear amendment history but does not create additional legal obligations"],"plain_english_summary":"This Airworthiness Directive requires Australian owners, operators and maintainers of certain Beechcraft King Air 90 series aircraft to follow the King Air 90 Maintenance Manual’s inspection rules for fuselage structural fatigue and to permanently retire parts that have reached their safe service limits. It’s intended to prevent catastrophic airframe failure. Amendment 3 (effective 30 November 2000) corrects a minor error and updates the manual reference."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue","history":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue/history","analysis":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue/analysis","conflicts":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue/conflicts","importantCases":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue/important-cases","documents":"/api/acts/ad-beech-90-56-amdt-3-fuselage-structural-fatigue/documents"}}