{"id":"F2008L04390","name":"AD/BEECH 55/62 Amdt 6 - Wing Main Spar Centre Section","slug":"ad-beech-55-62-amdt-6-wing-main-spar-centre-section","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76347,"registerId":"commonwealth-F2008L04390-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 55, 58 and 95-55 (Baron) Seri","sectionType":"division","heading":"Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes","content":"### Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes\n\n| AD/BEECH 55/62 Amdt 6 | Wing Main Spar Centre Section | 13/2008 |\n| --------------------- | ----------------------------- | ------- |\n\n| Applicability: | As detailed in the requirements document.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Inspect the wing forward spar carry through structure forward and aft frames, in accordance with Beechcraft Service Bulletin No 2269 Rev 1, dated March 1990 or later FAA approved revision.Note: FAA AD 90-08-14 Amendment 39-6563 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n| Compliance:    | Within 100 hours time in service after 30 November 1989, or prior to the accumulation of 1500 hours total time in service, whichever occurs later. Where no cracks are found, repeat the inspections at intervals not to exceed 500 hours time in service. Where cracks are found, repeat the inspections at intervals as detailed in the Requirement Document. Crack limits must not be exceeded.Specific locations repaired or reinforced by the installation of the applicable Beech P/N 58-4008 kit or other approved scheme, need not be inspected before 1500 hours time in service after installation of the repair, however affected areas adjacent to repair doublers remain subject to the above compliance. Aircraft inspected in accordance with the previous issue of this Directive, shall be considered to have been inspected in accordance with this amendment. |\n|                | This Amendment becomes effective on 18 December 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            |\n| Background:    | There have been numerous reports of cracking at various locations in the wing carry through structure. This problem was first found in Australia in 1981. The cracking is caused by fatigue in the corners of the fuselage frame webs around and between huckbolts and in area where stringers are attached. To date there have been no reports of cracks having progressed to failure, but uncorrected this condition could lead to eventual catastrophic failure.Amendment 5 was issued to allow the use of later FAA approved revisions to Beechcraft Service Bulletin No. 2269.                                                                                                                                                                                                                                                                                              |\n\n|     | Amendment 6 has been issued to amend reference to the FAA AD. |\n| --- | ------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 October 2008","sortOrder":0},{"sectionNumber":"AD/BEECH 55/62 Amdt 6","sectionType":"part","heading":"AD/BEECH 55/62 Amdt 6","content":"## AD/BEECH 55/62 Amdt 6","sortOrder":1},{"sectionNumber":"Wing Main Spar Centre Section","sectionType":"part","heading":"Wing Main Spar Centre Section","content":"## Wing Main Spar Centre Section","sortOrder":2},{"sectionNumber":"13/2008","sectionType":"part","heading":"13/2008","content":"## 13/2008","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original scope. Amendment 6 is a technical update that only revises the reference to the corresponding FAA Airworthiness Directive number. The substantive safety requirement — inspecting the wing main spar centre section for fatigue cracking — remains unchanged from the original 1989 directive and subsequent amendments. The document has not expanded beyond its original purpose of ensuring structural integrity of the wing carry-through structure on affected Beechcraft Baron aircraft."},"complexity_factors":["Short, single-purpose document (approximately 300 words of substantive content)","Only 2 defined technical references (Beechcraft Service Bulletin No 2269 Rev 1, FAA AD 90-08-14 Amendment 39-6563)","Clear conditional logic with explicit time-based triggers (100 hours/1500 hours TIS)","Single exception clause for repaired aircraft with specific part number reference (Beech P/N 58-4008)","No cross-references to other legislation or regulations beyond the cited service bulletin and FAA AD","Straightforward compliance structure: inspect → if cracks found, repair and re-inspect; if no cracks, re-inspect periodically"],"plain_english_summary":"This AD mandates owners/operators of Beechcraft Baron 55, 58 and 95-55 series in Australia to inspect the wing forward spar carry‑through structure for fatigue cracking per Beech Service Bulletin (FAA‑approved). It requires initial and repeat inspections, with limited deferral if approved repairs are installed.\n\nIt matters because carry‑through cracks can lead to catastrophic wing‑attachment failure; this amendment merely updates the corresponding FAA directive reference and preserves prior compliance."},"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":5,"scope_assessment":{"changed":false,"description":"Amendment 6 alters only the reference to the FAA airworthiness directive; it does not modify the inspection requirements, compliance timeframes, applicability framework, or repair/exemption mechanics set out in the requirement document. (See: “Amendment 6 has been issued to amend reference to the FAA AD.”)"},"complexity_factors":["Technical subject matter: inspections target fatigue cracking in wing carry‑through and frame web corners requiring specialised skills and interpretation.","Cross‑references to external documents: requires conformity with Beechcraft Service Bulletin No.2269 Rev 1 or later FAA‑approved revisions and cites FAA AD 90‑08‑14.","Multiple compliance timing rules: initial inspection windows (100 hours after 30 Nov 1989 or before 1500 total hours, whichever later) and repeat intervals (500 hours if no cracks; variable if cracks found).","Conditional exemptions and variance: repaired or reinforced locations using Beech P/N 58‑4008 change inspection timing, while adjacent areas remain subject to inspection.","Ambiguous applicability language: “As detailed in the requirements document” shifts substantive scope to another document, requiring cross‑checking.","Enforcement and administrative detail: effective date, CASA delegate signature and amendment numbering introduce procedural steps for regulators and operators.","Operational costs and incentives: recurring inspection costs, potential repair costs, and choices between monitoring vs permanent repair affect operator behaviour.","Recordkeeping and follow‑up discretion: repeat intervals “as detailed in the Requirement Document” grant administrative discretion and need for operator compliance tracking."],"plain_english_summary":"This amendment enforces inspections of the Beechcraft 55/58/95‑55 wing forward spar carry‑through structure per Beechcraft Service Bulletin No.2269 Rev 1 (or later FAA‑approved revision). Owners/operators must inspect within specified flight‑hour windows, repeat at set intervals, and repair or monitor any cracks; areas repaired with Beech kit P/N 58‑4008 have modified inspection timing. The Civil Aviation Safety Authority (delegate) issues and enforces the directive; aircraft owners bear inspection and repair costs. Amendment 6 only updates the FAA AD reference."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section","history":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section/history","analysis":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section/analysis","conflicts":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section/conflicts","importantCases":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section/important-cases","documents":"/api/acts/ad-beech-55-62-amdt-6-wing-main-spar-centre-section/documents"}}