{"id":"F2013L00820","name":"AD/BEECH 200/38 Amdt 6 - Wing Front Spars","slug":"ad-beech-200-38-amdt-6-wing-front-spars","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":90504,"registerId":"commonwealth-F2013L00820-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 200 (Super King Air) Series A","sectionType":"division","heading":"Beechcraft 200 (Super King Air) Series Aeroplanes","content":"### Beechcraft 200 (Super King Air) Series Aeroplanes\n\n| AD/BEECH 200/38 Amdt 6 | Wing Front Spars | 11/2013 |\n| ---------------------- | ---------------- | ------- |\n\n| Applicability: | All model 200 series aircraft including those modified in accordance with STC SA1602CE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. For aircraft which have not been modified in accordance with STC SA1602CE, inspect and retire the outer wing attach bolts and nuts, and inspect the attach fittings and the wing main spars in accordance with the Beechcraft Structural Inspection and Repair Manual (SIRM) P/N 98-39006C3 as revised Feb 2008 or later approved revision, Chapter 57-17-00, “GENERAL - MAINTENANCE PRACTICES (MODEL 200 SERIES)”.2. For aircraft which have been modified in accordance with STC SA1602CE, inspect and retire the outer wing attach bolts and nuts, and inspect the outer wing upper attach fittings, the wing main spar upper cap, that portion of the lower spar cap outboard of the strap installation, and the accessible portions of the lower attach fittings, in accordance with the Beechcraft Structural Inspection and Repair Manual P/N 98-39006C3 as revised Feb 2008 or later approved revision, Chapter 57-17-00, “GENERAL - MAINTENANCE PRACTICES (MODEL 200 SERIES).Additionally, carry out the “Instructions for continued Airworthiness” as detailed in the STC SA1602CE document EO-B-8001.                                                                                                                                                                                                                                                                                                                                             |\n| Compliance:    | Inspect at the initial inspection thresholds and recurring inspection intervals specified in the applicable Requirement documents. Retire attach bolts and nuts at the times detailed in the SIRM.Note 1: These requirements are mandatory in the country of origin, FAR 43.13 refers.Note 2: Aircraft BT-31 and subsequent, BL-73 and subsequent, BN-5 and subsequent, BB-1158, BB-1167, and BB-1193 and subsequent, were manufactured with a shear fitting at the lower forward spar attachment. Earlier aircraft utilised a tension bolt in this location, characterised by the “bathtub” type fitting. All aircraft utilise tension type fittings on the forward spar upper attachment and the upper and lower rear spar attachments.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n|                | This Amendment becomes effective on 24 May 2013.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n| Background:    | The original of this Directive was issued on 31 December 1981 because of service experience with corrosion and cracking of the wing spars, and outer wing attachment fittings and bolts. It specified inspection in accordance with Beechcraft Service Instruction 0514-035 Rev 2.Amendment 1 became effective on 5 October 1989, and included inspection requirements for aircraft with the spar strap STC modification.Amendment 2 became effective on 9 August 1990 and incorporated the inspection method of the Beechcraft Structural Inspection and Repair Manual, which superseded SI 0514-035 Rev 2.Amendment 3 became effective on 10 August 2000, and was raised to reflect the amendment status of the Structural Inspection and Repair Manual, and to clarify the source and identity of the STC inspection document for modified aircraft.Subsequently, during a review of airframe ADs for the Beech heavy twins, it was realised that inspection of the wing attach nuts and bolts, which is a requirement of this AD, was duplicated by AD/BEECH 200/39 Amdt 4. Amendment 4 consolidated the two ADs into one. No additional requirements were introduced.Amendment 5 became effective on 20 November 2008 and was raised to reflect the amendment status of the Beechcraft Structural Inspection and Repair Manual.Amendment 6 is raised to correct the date of the requirement document and to allow the use of future revisions of the SIRM. |\n\n![HIGGINS_M](image.001.png)  \nMike Higgins  \nDelegate of the Civil Aviation Safety Authority\n\n17 May 2013","sortOrder":0},{"sectionNumber":"AD/BEECH 200/38 Amdt 6","sectionType":"part","heading":"AD/BEECH 200/38 Amdt 6","content":"## AD/BEECH 200/38 Amdt 6","sortOrder":1},{"sectionNumber":"Wing Front Spars","sectionType":"part","heading":"Wing Front Spars","content":"## Wing Front Spars","sortOrder":2},{"sectionNumber":"11/2013","sectionType":"part","heading":"11/2013","content":"## 11/2013","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"Amendment 6 corrects the date of the requirement document and expressly permits use of future approved revisions of the Beechcraft SIRM, but does not expand or reduce the AD's applicability or core inspection/retirement obligations. The Background confirms prior amendments adjusted references and consolidated duplicate ADs, while Amendment 6 only adjusts documentary references and revision allowance."},"complexity_factors":["Cross-reference dependence on an external, amendable technical manual (Beechcraft SIRM) which sets inspection thresholds and retirement intervals","Different inspection scopes depending on presence of STC SA1602CE modification (two related but distinct requirement sets)","Operational compliance burden falling on owners/operators (scheduling inspections, retiring bolts/nuts, performing repairs)","Historical layering of amendments and consolidation with other ADs (background shows prior duplications and consolidations)","Technical nature of inspections (corrosion/cracking detection on spars and fittings) requires specialised maintenance capability"],"plain_english_summary":"This Airworthiness Directive requires owners/operators of all Beechcraft Model 200 (Super King Air) series — including aircraft modified under STC SA1602CE — to inspect and retire outer wing attach bolts and nuts and to inspect front wing attach fittings and main spars in accordance with the Beechcraft Structural Inspection and Repair Manual (SIRM) (Applicability; Requirement). Compliance intervals and retirement times follow the SIRM; costs for inspections, repairs and part replacement are borne by the aircraft owner/operator. CASA enforces the AD; the AD allows use of later approved SIRM revisions (Compliance)."},"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 amendment maintains the original scope established in 1981. Amendment 6 is purely administrative — it corrects a document date and permits use of future manual revisions. The substantive safety requirements (inspect wing spars, retire bolts) remain unchanged from previous versions. The scope has not expanded beyond the original intent of ensuring wing structural integrity for this aircraft type."},"complexity_factors":["Multiple amendment history (6 versions since 1981) creating layered context","Two distinct compliance paths based on STC (Supplemental Type Certificate) modification status","Cross-references to external technical documents (Beechcraft SIRM P/N 98-39006C3 and STC document EO-B-8001)","Specific aircraft serial number ranges mentioned in Note 2 with different manufacturing configurations (shear fitting vs tension bolt)","Nested applicability clause covering 'all model 200 series' plus specific STC-modified aircraft"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspection and replacement of the outer wing attach bolts, nuts, and fittings on Beechcraft 200 (Super King Air) aircraft to prevent wing spar failure. Standard airframes follow the Beechcraft Structural Inspection and Repair Manual; aircraft modified under STC SA1602CE follow that manual plus the STC’s continued airworthiness instructions. The 2013 amendment updates referenced manuals and dates, not inspection requirements."}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars","history":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars/history","analysis":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars/analysis","conflicts":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars/conflicts","importantCases":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars/important-cases","documents":"/api/acts/ad-beech-200-38-amdt-6-wing-front-spars/documents"}}