{"id":"F2006B02025","name":"AD/AA-1/14 - Rudder Control Bars - Inspection","slug":"ad-aa-1-14-rudder-control-bars-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41247,"registerId":"commonwealth-F2006B02025-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/AA-1/14 - Rudder Control Bars - Inspection","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)  \nGulfstream (Grumman American/ American Aviation) AA-1 Series Aeroplanes\n\nAD/AA-1/14 Rudder Control Bars \\- Inspection 2/75\n\nApplicability: All models.\n\nRequirement: To confirm that rudder control bars P/N 601031-501 are correctly welded inspect visually as follows:\n\n    View both rudder control bars located inside the lower forward fuselage.\n\n    2. Inspect weld joints at junction of rudder cable attach arm and rudder control bar. Each joint must have a weld bead at four locations i.e. fore and aft bottom and fore and aft top.\n\n    3. Inspect weld joints at junction of rudder pedal tees and rudder control bar. Each joint must have a weld bead at four locations i.e. fore and aft bottom and fore and aft top.\n\n    4. If inspection reveals missing welds, replacement or repairs to an approved scheme must be incorporated before further flight.\n\nCompliance: Before further flight after 21 February 1975.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"No change of scope is indicated within the supplied text. The directive applies to all AA-1 series models and is limited to inspection (and replacement/repair if necessary) of rudder control bars P/N 601031-501, with compliance required before further flight after 21 February 1975 (Applicability; Requirement; Compliance)."},"complexity_factors":["Narrow technical focus limited to a single part number (P/N 601031-501) and specified weld locations (Requirement).","Simple, visual inspection procedure with step-by-step instructions reduces procedural complexity (Requirement steps 1–3).","Mandatory repair or replacement to an “approved scheme” introduces some procedural ambiguity and potential administrative delay because the approver/approval process is not specified (Requirement step 4).","Immediate compliance deadline (Before further flight after 21 February 1975) creates operational urgency and scheduling complexity for affected operators (Compliance).","Access requirement: viewing parts located inside the lower forward fuselage may require disassembly or special access, adding practical maintenance effort (Requirement step 1)."],"plain_english_summary":"What this directive does (mechanics)\n\n- Requires operators of Gulfstream (Grumman American/American Aviation) AA-1 series aeroplanes to visually inspect the rudder control bars with part number 601031-501 to confirm certain welds are present. The inspection points are: (a) weld joints at the junction of the rudder cable attach arm and the rudder control bar (each joint must have a weld bead at four locations: fore and aft bottom and fore and aft top); and (b) weld joints at the junction of the rudder pedal tees and the rudder control bar (each joint must have a weld bead at four locations: fore and aft bottom and fore and aft top). If any required welds are missing, the control bar must be replaced or repaired to an approved scheme before the aeroplane is flown again. (Requirement; Compliance.)\n\nWho this affects and who pays\n\n- Affected parties: owners and operators of AA-1 series aeroplanes fitted with rudder control bars P/N 601031-501 (Applicability; Requirement).\n- Who pays: the aircraft owner/operator bears the cost of performing the visual inspection and, if necessary, paying for replacement parts or repairs carried out to an approved scheme (Requirement).\n\nWhy it matters (stated purpose and practical test)\n\n- The directive’s stated aim is to confirm that the rudder control bars are correctly welded (Requirement). Mechanically, the rule forces verification of specific welds and stops aircraft from flying if those welds are missing until replacement or approved repairs are done (Requirement; Compliance).\n\nTrade-offs, incentives and implementation notes\n\n- Compliance timing: the work had to be done before further flight after 21 February 1975; that deadline imposes immediate downtime and scheduling costs on operators who had affected aircraft in service at that date (Compliance).\n- Detection method and implementation risk: the required check is a visual inspection of the lower forward fuselage area where the control bars are located. Visual inspection is straightforward to carry out but may not detect subsurface defects; the directive does not require non‑destructive testing methods (Requirement).\n- Repair approval and bureaucratic discretion: the directive requires repairs or replacement to follow an “approved scheme.” The text does not specify the approver or approval process, so obtaining an acceptable repair scheme can be a source of administrative delay or cost (Requirement).\n- Operational effect: an aircraft found with missing welds must be grounded until the replacement/repair is completed to the approved scheme, producing immediate loss of availability and potential scheduling or revenue effects for operators (Requirement; Compliance).\n- Specificity of obligation: the directive identifies the exact part number (P/N 601031-501) and precise weld locations to inspect, which narrows compliance to a defined component and reduces ambiguity about scope of inspection (Applicability; Requirement).\n\nConcrete behavioural changes required\n\n- Maintenance personnel must view both rudder control bars inside the lower forward fuselage and inspect the specified weld locations (Requirement).\n- If welds are missing, maintenance organisations must either replace the part or perform repairs according to an approved scheme before the aircraft is next flown (Requirement; Compliance).\n\nSource citations\n\n- Applicability: “All models.”\n- Part number: “rudder control bars P/N 601031-501” (Requirement).\n- Inspection steps and weld locations: Requirement, numbered steps 1–3.\n- Action on defects: Requirement step 4; Compliance: “Before further flight after 21 February 1975.”"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, time-bound safety directive issued in 1975 (as indicated by '2/75' in the reference). It has not expanded beyond its original narrow purpose of inspecting specific weld joints on specific aircraft. Airworthiness Directives are typically standalone instruments that remain in force until complied with or superseded, and do not grow in scope over time."},"complexity_factors":["Single, specific mechanical part targeted (P/N 601031-501)","Straightforward visual inspection procedure with only 3 inspection points described","Binary compliance outcome: pass inspection or ground aircraft for repair","No defined terms section, no cross-references to other legislation","Single compliance date with no conditional exceptions or alternative methods","Total length: approximately 150 words"],"plain_english_summary":"This is an **Airworthiness Directive** — a mandatory safety order issued by Australia's Civil Aviation Safety Authority (CASA) that requires owners and operators of specific aircraft to take action.\n\n**What it does:**\nOrders immediate visual inspections of rudder control bars on **Gulfstream AA-1 series aeroplanes** (also known as Grumman American or American Aviation AA-1s). These are small, single-engine aircraft.\n\n**The specific problem:**\nThe directive targets a particular part number (P/N 601031-501) — the rudder control bars. Inspectors must check that welding joints are complete at eight specific locations where the rudder cables and pedal connections attach to the control bars. There should be weld beads at four points on each joint (front, back, top, and bottom).\n\n**What happens if problems are found:**\nIf any welds are missing, the aircraft **cannot fly** until repairs are made using an approved repair scheme.\n\n**Who it affects:**\n- Owners and operators of all Gulfstream/Grumman American/ American Aviation AA-1 series aircraft\n- Licensed aircraft maintenance engineers performing inspections\n- Flying schools or clubs operating these aircraft types\n\n**Why it matters:**\nRudder control bars are critical flight controls. Missing welds could lead to structural failure of the rudder system, potentially causing loss of directional control during flight. This directive was issued as an emergency safety measure with immediate effect — aircraft had to be inspected before their next flight after 21 February 1975."}},"importantCases":[],"_links":{"self":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection","history":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection/history","analysis":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection/analysis","conflicts":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection/conflicts","importantCases":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection/important-cases","documents":"/api/acts/ad-aa-1-14-rudder-control-bars-inspection/documents"}}