{"id":"F2006B08552","name":"AD/CHA/25 Amdt 1 - Wing Front Strut Fittings","slug":"ad-cha-25-amdt-1-wing-front-strut-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":51350,"registerId":"commonwealth-F2006B08552-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/CHA/25 Amdt 1 - Wing Front Strut Fittings","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  American Champion (Aeronca, Bellanca) Series Aeroplanes\n\n \n\n# AD/CHA/25\n\nAmdt 1\n\nApplicability: Models:\n\n# Wing Front Strut Fittings 12/96 DM\n\n \n\n8KCAB S/N 643-90 to 768-96, and all other S/N. equipped with metal spar wings assembly P/N 7-1521;\n\n \n\n8GCBC S/N 361-91 to 377-96, and all other S/N equipped with metal spar wings assembly P/N 7-1542;\n\n \n\n7GCBC S/N 1200-94 to 1215-96, and all other S/N equipped with metal spar wings assembly P/N 7-1541;\n\n \n\n7ECA S/N 1355-95 to 1358-96, and all other S/N equipped with metal spar wings assembly P/N 7-1567.\n\n7GCAA and 7KCAB, all S/N equipped with metal spar wings assembly P/N 7-1567. Requirement:              1. Install inspection holes and removable covers in accordance with the appropriate\n\nAmerican Champion Service Letter (SL) as follows:\n\n \n\n1. Model 8KCAB in compliance with SL408 - SL410, or\n\n\n \n\nb.    Model 8KCAB not in compliance with SL408 - SL 411, or\n\n \n\nc.    Model 7ECA, 7GCAA, 7GCBC, and 8GCBC in compliance with SL409 Rev A\n\n- SL412, or\n\n \n\nd.   Model 7ECA, 7GCAA, 7GCBC, and 8GCBC not compliance with SL409 Rev A. - SL413.\n\n \n\n2.    Replace the wing front strut attach fitting in accordance with American Champion SL 414 Rev. A, or 415 Rev. A, as appropriate.\n\n \n\nNote: FAA AD 96-18-02 refers, and supersedes AD 96-03-11.\n\n \n\nCompliance: Unless already accomplished, within 20 hours time in service after 02 October 1996.\n\n \n\nWhere replacement wing front strut fittings may not be immediately available from the aircraft manufacturer, continued inspection in accordance with the requirements of SL 408 or SL 409, as appropriate, is authorised at intervals not exceeding 20 hours time in service until:\n\n \n\n1. cracking, scratches or surface deformities are found on an attach fitting, or\n\n\n \n\nb.    parts become available from American Champion, or\n\n \n\nc.    five repetitive inspections have been carried out (120 hours time in service)\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\nBackground:  This Directive follows a fatal accident overseas, where the investigation found fatigue cracking of the wing front strut fittings. Subsequent inspections of other aircraft of the type found other instances of cracking.\n\n \n\nAmendment 1 increases the model and serial number range, introduces inspection access and removable inspection covers, and requires the installation of reliable airworthy replacement fittings.\n\n \n\nThe initial issue of this Airworthiness Directive became effective on 27 March 1996.\n","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"Amendment 1 broadened and clarified scope compared with the initial AD: it increased the model and serial-number ranges covered, introduced a new requirement to install inspection access holes and removable covers, and made mandatory the installation of the specified replacement wing front strut fittings. The original AD (effective 27 March 1996) has been expanded to require both improved inspection access and fitted replacement parts rather than inspection-only remedies."},"complexity_factors":["Multiple affected models and several serial-number ranges to check for applicability","References to multiple American Champion Service Letters (SL408–SL415, including revisions and alternatives) creating branching compliance paths","Two distinct mandated actions (install inspection access covers; replace attach fitting) with conditional allowance for repeated inspections if parts unavailable","Short compliance deadline (20 hours TIS) plus an alternative five-inspection limit (120 hours TIS) — timing adds operational complexity","Cross-reference to FAA AD (96-18-02) and supersession note increases cross-jurisdictional citation load"],"plain_english_summary":"**What this directive does (mechanical effect)\n\n- Applies to certain American Champion (Aeronca, Bellanca) light aeroplane models and specific serial-number ranges that have the listed metal-spar wing assemblies. (See the Applicability list in the AD.)\n- Requires two things:  \n  1. Install inspection access holes and removable inspection covers in the wing front strut attach area, following the American Champion Service Letters (SL) specified for each model (SL408–SL413 as appropriate). (Requirement 1)  \n  2. Replace the wing front strut attach fitting with the approved replacement fitting, following American Champion SL414 Rev A or SL415 Rev A as appropriate. (Requirement 2)\n- Sets the compliance timing: unless already done, the work must be done within 20 hours time-in-service (TIS) after 2 October 1996. (Compliance)\n- Provides a temporary alternative if replacement fittings are not immediately available from the manufacturer: continue inspections per the relevant Service Letter at intervals not exceeding 20 hours TIS until one of three things happens — cracking/deformity is found, parts become available, or five inspections (total 120 hours TIS) have been completed. (Conditional continuation clause)\n- Cross-references the relevant FAA airworthiness directive (FAA AD 96-18-02). (Note)\n\n**Who this affects\n\n- Aircraft owners/operators of the listed American Champion models and serial numbers.  \n- Maintenance organisations and licensed mechanics who must carry out the inspections, install access covers, and fit the replacement attach fittings.  \n- Parts suppliers (notably American Champion) who supply the replacement fittings and inspection hardware.  \n- Regulators/inspectorates who monitor compliance.\n\n**Why the rule exists (official rationale)\n\n- The AD follows a fatal overseas accident where investigators found fatigue cracking in the wing front strut fittings. Inspections of additional aircraft found other instances of cracking. The AD’s stated purpose is to prevent failure of the wing front strut fitting by (a) making the area inspectable (access holes/removable covers) and (b) installing a reliable replacement fitting. (Background and Amendment notes)\n\n**Practical effects, costs and trade-offs\n\n- Who pays: aircraft owners/operators pay for parts, labour, and downtime. Maintenance providers charge for labour and may need to source parts from American Champion (or authorised suppliers).  \n- Who decides: the regulator (Civil Aviation Safety Authority via the AD) mandates compliance; operators decide which compliance path to take (immediate replacement where possible, or temporary repetitive inspections if parts are unavailable).  \n- Behaviour changes required: owners must schedule and fund inspections or replacements within the tight 20 hours TIS window; maintenance shops must perform installation of access panels and replacement fittings to the Service Letter instructions.  \n- Compliance burden: short compliance window (20 hours TIS) imposes rapid action and potential operational disruption; repetitive inspections at 20-hour intervals are frequent and increase maintenance load if parts are unavailable.  \n- Implementation risk: replacement parts availability may be constrained (the AD explicitly contemplates this), creating reliance on repetitive inspections; installing inspection access and replacement fittings requires correct workmanship to be effective.  \n- Effects on markets and choice: raises short-term demand for specified replacement fittings and maintenance services, concentrating spending on the aircraft manufacturer or authorised suppliers; may increase operating costs for small operators and reduce available aircraft hours while work is done. Operators facing part shortages may defer replacement but must accept increased inspection frequency or ground the aircraft if defects are found.  \n\n**Trade-offs and opportunity costs\n\n- Immediate replacement imposes up-front cost and possible downtime but is intended to remove the need for repetitive short-interval inspections.  \n- Continued inspections (when parts are unavailable) lower immediate parts cost but increase ongoing maintenance time, monitoring burden and accident risk between inspections.  \n- The AD centralises technical conformity by mandating the manufacturer’s Service Letter procedures; this reduces operator discretion over the engineering solution but aims to ensure a uniform corrective action.\n\n**Implementation and compliance considerations (concrete mechanics)\n\n- Operators must identify whether their aeroplane serial number and wing spar part number are within the applicability list.  \n- If the aircraft is applicable and not already modified, operators must either: (a) install inspection access and replace the fitting per the stated SLs, or (b) where parts are unavailable, perform inspections per the SL at intervals not exceeding 20 hours TIS until a defect is found, parts arrive, or five inspections have been completed (120 hours TIS).  \n- If cracking, scratches or surface deformities are found during inspection, replacement is then required immediately. (Conditional clause)\n\n**Source citations inside the AD**\n- Requirement 1 (install inspection holes/removable covers): Requirement section referencing SL408–SL413.  \n- Requirement 2 (replace wing front strut attach fitting): Requirement section referencing SL414 Rev A or SL415 Rev A.  \n- Compliance timing: “within 20 hours time in service after 02 October 1996.” (Compliance section)  \n- Temporary inspection regime when parts unavailable: authorised at intervals not exceeding 20 hours TIS until cracking found, parts available, or five inspections (120 hours TIS). (Compliance section)  \n- Background: links the AD to a fatal overseas accident and subsequent findings of fatigue cracking. (Background/Amendment note)\n\n**Summary statement of incentives and who bears costs**\n- The AD forces a safety-improving action that shifts direct costs to individual aircraft owners/operators (parts, labour, downtime) and creates demand for manufacturer-supplied replacement fittings and maintenance services. The regulator prescribes the method and timetable; operators choose between immediate replacement or a short-term, inspection-based workaround when parts are unavailable."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original directive (March 1996) was narrower in scope. Amendment 1 significantly expanded coverage to additional serial numbers and models, added new requirements for inspection access holes and covers (not just replacement), and introduced the concept of repetitive inspections as an interim measure. What began as a targeted replacement order evolved into a comprehensive inspection and modification program with multiple compliance pathways."},"complexity_factors":["Multiple overlapping applicability criteria combining model numbers, serial number ranges, and parts numbers (P/N)","Nested conditional requirements with cross-references to manufacturer service letters (SL408-SL415) rather than spelling out the actual work required","Alternative compliance paths (inspection vs replacement) with cascading conditions","Complex compliance timeline with multiple triggering events (hours in service, parts availability, finding defects, or cap of 5 inspections)","Reference to foreign regulatory action (FAA AD 96-18-02) without fully incorporating its text","Inconsistent formatting and numbering (mix of '1.' and 'b.' in the same list)"],"plain_english_summary":"This CASA safety order requires owners/operators of certain American Champion light aeroplanes to modify wings to allow inspection for cracks in wing front strut fittings and to replace any faulty fittings with redesigned stronger parts. Prompt inspections (within 20 flying hours after Oct 1996) and repeated checks until replacement parts are fitted are mandated. Issued after a fatal overseas crash from metal-fatigue failure, the order widens coverage to more aircraft of the affected 1990s metal-wing types."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings","history":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings/history","analysis":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings/analysis","conflicts":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings/conflicts","importantCases":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings/important-cases","documents":"/api/acts/ad-cha-25-amdt-1-wing-front-strut-fittings/documents"}}