{"id":"F2006B03803","name":"AD/BEECH 33/36 Amdt 2 - Rudder Forward Spar","slug":"ad-beech-33-36-amdt-2-rudder-forward-spar","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":43399,"registerId":"commonwealth-F2006B03803-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BEECH 33/36 Amdt 2 - Rudder Forward Spar","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)  \nBeechcraft 33 and 35-33 (Debonair/Bonanza) Series Aeroplanes\n\nAD/BEECH 33/36\n\nAmdt 2\n\n  \nRudder Forward Spar 5/98\n\nApplicability: Models Serial Numbers\n\n35-33, 35-A33, 35-B33, 35-C33, E33, F33, G33 CD-1 through CD1304\n\n    35- C33A, E33A, F33A CE-1 through CE-1425\n\nE33C, F33C CJ-1 through CJ-179\n\nRequirement: 1. Inspect the rudder forward spar in accordance with Beech Service Bulletin SB 2333 Revision 1 dated Nov 1991.\n\nNote: FAA AD 93-24-03 Amendment 39-8752 refers.\n\nCompliance: 1. Before exceeding 1000 hrs component TIS or 100 hrs TIS after 1 Nov 1990, whichever occurs later and thereafter at intervals not to exceed 500 hrs TIS.\n\nThe following are terminating actions for this Directive:\n\n    Installation of repair kit 33-6001-1S in accordance with the Beech SB 2333 Revision 1;\n\n    b. Replacement of the rudder assembly with the applicable part number in accordance with Beech SB2333 Revision 1;\n\n    c. Installation of rudder spar reinforcements in accordance with FAA STC SA4899NM; and,\n\n    d. Installation of rudder spar reinforcements in accordance with FAA STC SA00044LA.\n\nThis amendment becomes effective on 23 April 1998.\n\nBackground: This AD was raised as a result of eight reports of cracks at the hinge bracket attachments in the rudder forward spar. The cause is fatigue initiating at holes drilled to install nut plates. Failure to correct this condition may result in loss of aircraft control. This amendment calls up the latest FAA AD information and highlights the presence of other terminating action.\n\nAmendment 1 of this airworthiness directive became effective in January 1993. The original issue of this airworthiness directive became effective in August 1990.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment updates the AD by calling up the latest FAA AD information and explicitly highlights additional acceptable terminating actions, but it does not broaden the range of aircraft affected or change the safety objective. The instrument remains focused on detecting and correcting fatigue cracking at the rudder forward spar; changes are limited to acceptable remedies and cross-references to external documents rather than an expansion of purpose or scope."},"complexity_factors":["Short directive (single component, limited scope)","Multiple serial-number ranges listed for applicability (several sub-models and ranges)","Cross-reference to external technical documents: Beech SB 2333 Revision 1","Cross-reference to FAA AD 93-24-03 (informational)","Four alternative terminating actions, including two FAA STCs (SA4899NM, SA00044LA)","Conditional initial compliance deadline phrased as “whichever occurs later” (slightly increases reading complexity)","Repeating inspection interval (every 500 hrs TIS)"],"plain_english_summary":"**What this instrument requires**\n\n- It orders owners/operators of certain Beechcraft Debonair/Bonanza (models 33/35-33 family) aeroplanes, identified by specific serial-number ranges, to inspect the rudder forward spar for cracking in accordance with Beech Service Bulletin SB 2333 Revision 1 (Nov 1991). (See the “Requirement” and “Compliance” sections.)\n\n- The first inspection must be done before the rudder forward spar exceeds 1,000 hours time-in-service (TIS), or within 100 hours TIS if the AD applies to the aircraft after 1 November 1990 — whichever of those two deadlines is later. After that, inspections must be repeated at intervals not greater than 500 hours TIS. (See the “Compliance” section.)\n\n- The AD lists four alternative \"terminating actions\" (ways to stop the repetitive inspections):\n  - install Beech repair kit 33-6001-1S per SB 2333 Rev 1;\n  - replace the rudder assembly with the specified part number per SB 2333 Rev 1;\n  - install rudder spar reinforcements under FAA STC SA4899NM; or\n  - install rudder spar reinforcements under FAA STC SA00044LA.\n\n**Who is affected**\n\n- Registered owners and operators of Beechcraft 35-33/35-A33/35-B33/35-C33/E33/F33/G33 and related sub-models whose serial numbers fall in the ranges listed in the AD. Maintenance organisations that perform the inspections, repairs or installations are also directly affected.\n\n**Why it matters (the safety problem and mechanical cause)**\n\n- The AD was issued because operators reported eight instances of cracks at the hinge-bracket attachments in the rudder forward spar. The cracks were caused by fatigue starting at holes drilled to install nut plates. If unchecked, this cracking can lead to loss of aircraft control. (See the “Background” section.)\n\n**How it works in practice (mechanics, costs and choices)**\n\n- Owners must (a) keep track of the rudder forward spar’s hours TIS, (b) perform inspections using the procedures in Beech SB 2333 Rev 1 at the required initial and repeat intervals, and (c) take corrective action if cracks are found.\n\n- Recurrent cost options: operators can continue with recurring inspections (labour and downtime every ~500 hours TIS), or choose an upfront modification (repair kit, full rudder replacement, or STC-installed reinforcements). The listed modifications are accepted by this AD as terminating actions: once installed in accordance with the referenced documents, the repetitive-inspection requirement no longer applies.\n\n- Who bears the cost: aircraft owners/operators pay for inspections, parts, labour and downtime; maintenance providers perform the work and bill accordingly. Choosing a terminating action shifts costs from repeated inspection labour to an upfront parts-and-installation bill, and reduces future inspection burden.\n\n**Regulatory and implementation notes**\n\n- The AD does not itself contain detailed inspection or repair steps; it requires use of Beech Service Bulletin SB 2333 Rev 1 (external technical document) for procedures. It also accepts specific FAA Supplemental Type Certificates (STCs) as terminating actions. That creates dependence on external documents and on availability of repair kits, parts and STC-approved modification data.\n\n- Practical risks and trade-offs: availability of repair kits or STC-approved reinforcements, scheduling downtime at an approved maintenance facility, and the immediate cash cost of a terminating modification versus the recurring cost and operational disruption of repeated inspections. The AD centralises the decision: comply by inspection or by performing an approved modification.\n\n**Source claim vs. mechanical effect**\n\n- The AD’s stated purpose is safety (to prevent spar fatigue cracking and potential loss of control). Mechanically, it achieves that by mandating inspection intervals and by permitting four specific modifications that remove the need for further inspections. The consequence for operators is clear: either budget for recurrent inspections and potential repairs, or install one of the approved fixes to stop the inspection cycle.\n\n(References in the AD: “Requirement”, “Compliance”, “Terminating actions” and “Background”.)"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment remains focused on its original purpose: addressing rudder forward spar fatigue cracks in specific Beechcraft models. Amendment 2 simply updates the reference to the latest FAA AD information and clarifies available terminating actions — it does not expand beyond the original safety issue."},"complexity_factors":["Single, clearly defined applicability (specific aircraft models and serial numbers)","One primary requirement with four alternative terminating actions","Simple compliance timeline with two conditions and a recurring interval","Minimal cross-referencing (one FAA AD and one manufacturer service bulletin)","No nested definitions or conditional exceptions","Total length under 300 words"],"plain_english_summary":"This safety notice requires owners/operators of specified Beechcraft Debonair and Bonanza (33 and 35-33 series) to inspect the rudder forward spar for fatigue cracks per the manufacturer’s service bulletin, with an initial deadline tied to hours-in-service and recurring inspections every 500 hours. Approved repair kits, rudder replacement, or FAA‑approved STCs can eliminate repetitive inspections. It addresses drilled‑hole fatigue that could cause spar failure and loss of aircraft control."},"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-33-36-amdt-2-rudder-forward-spar","history":"/api/acts/ad-beech-33-36-amdt-2-rudder-forward-spar/history","analysis":"/api/acts/ad-beech-33-36-amdt-2-rudder-forward-spar/analysis","conflicts":"/api/acts/ad-beech-33-36-amdt-2-rudder-forward-spar/conflicts","importantCases":"/api/acts/ad-beech-33-36-amdt-2-rudder-forward-spar/important-cases","documents":"/api/acts/ad-beech-33-36-amdt-2-rudder-forward-spar/documents"}}