{"id":"F2006B04848","name":"AD/CAP 10/6 - Lower Torque Link Attachment Weld","slug":"ad-cap-10-6-lower-torque-link-attachment-weld","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":44655,"registerId":"commonwealth-F2006B04848-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# AIRWORTHINESS DIRECTIVE\n\n![](image.001.png)\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\nAvions Mudry Cap Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/CAP 10/6 Lower Torque Link Attachment","sectionType":"part","heading":"AD/CAP 10/6 Lower Torque Link Attachment Weld 9/2004","content":"# AD/CAP 10/6 Lower Torque Link Attachment Weld 9/2004\n\nApplicability: CAP 10B aircraft, serial number 300 and subsequent, or modified in accordance with MOD 000302 “CAP 10C wing”; and where a main landing gear has a separation zone between the chrome plated area of the moving strut and the torque link attachment of less than 1 mm (0.040-inch), as specified in Requirement document.\n\nRequirement: Inspect in accordance with Apex Aircraft Service Bulletin No. 040506, dated 7 June 2004.\n\nNote: DGAC AD F-2004-108 refers.\n\nCompliance: Within 50 hours time in service after 2 September 2004. Thereafter at intervals not to exceed 100 hours time in service. These periods may be increased by up to10% to align the inspection with a scheduled maintenance check.\n\nThis Airworthiness Directive becomes effective on 2 September 2004.\n\nBackground: The main landing gear torque link attachment to the moving strut may have been welded onto the chrome plated surface, which could embrittle the weld and lead to cracks.\n\n![](image.002.png)  \n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 13 July 2004\n\n![](image.001.png)","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"No change from the instrument's stated intent in the source text: the AD targets CAP 10 aircraft that meet the gap specification and requires inspections per Apex SB No.040506. The AD expressly refers to DGAC AD F-2004-108 and sets the same corrective inspection requirement and intervals."},"complexity_factors":["Narrow applicability tied to aircraft model, serial numbers (CAP 10B serial no. 300 onward) and modification status (MOD 000302).","Technical measurement trigger: separation zone less than 1 mm between chrome‑plated strut and torque‑link attachment.","Reliance on an external maintenance procedure: Apex Aircraft Service Bulletin No. 040506 (7 June 2004) prescribes inspection steps.","Recurring compliance timetable with initial and repeat intervals (initial 50 hours after effective date; thereafter 100‑hour intervals) and a 10% allowance to align with scheduled maintenance.","Safety mechanism identified: potential weld embrittlement leading to cracks (Background).","Legal basis: issued under CASR 1998 subregulation 39.1(1) by the CASA delegate."],"plain_english_summary":"This AD mandates recurring inspections, using Apex Aircraft Service Bulletin No. 040506, of the main landing‑gear torque‑link weld on specified Avions Mudry CAP 10 aircraft where the gap to the chrome‑plated moving strut is under 1 mm, to detect possible weld embrittlement and cracking. Operators bear the cost of inspections per the service bulletin at the specified intervals. The AD is issued under CASR 39.1(1), which authorizes the CASA delegate to issue directives requiring corrective action for unsafe conditions."},"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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a targeted safety directive addressing a specific manufacturing defect identified in 2004. It has not expanded beyond its original purpose of inspecting and monitoring the torque link attachment weld condition on affected CAP 10B aircraft."},"complexity_factors":["Single, specific mechanical issue (welding defect on one component)","Narrow applicability: only CAP 10B aircraft, serial 300+, with specific dimensional condition (<1mm separation zone)","Simple compliance structure: one-time initial inspection + recurring interval","Only one external reference (Apex Aircraft Service Bulletin)","No defined terms section, no cross-references to other legislation","Straightforward conditional logic: IF aircraft type AND serial number AND modification status AND dimensional condition THEN inspect","Single exception/allowance: 10% extension to align with scheduled maintenance"],"plain_english_summary":"This safety order requires owners/operators of French-built CAP 10B aeroplanes (serials ≥300 and those modified to CAP 10C wing standard) to inspect main landing gear torque links where welds may have fused to chrome-plated surfaces, risking cracks and potential gear failure.  \n\nInitial inspection must occur within 50 flying hours after 2 September 2004, with repeats every 100 hours (allowing a 10% extension to match maintenance), carried out per Manufacturer Service Bulletin No. 040506."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld","history":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld/history","analysis":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld/analysis","conflicts":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld/conflicts","importantCases":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld/important-cases","documents":"/api/acts/ad-cap-10-6-lower-torque-link-attachment-weld/documents"}}