{"id":"F2006B05955","name":"AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement","slug":"ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":136114,"registerId":"commonwealth-F2006B05955-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement","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)  \nPiper PA-38 (Tomahawk) Series Aeroplanes\n\nAD/PA-38/17\n\nAmdt 2\n\n  \nRudder Upper Hinge \\- Inspection and Replacement 2/81\n\nApplicability: All models PA-38-112 with S/Nos. 38-78A0001 to 38-80A0099, 38-80A0113, 38- 80A0120 and 38-80A0123 to 38-80A0165.\n\nRequirement: To avoid possible flight hazards associated with a crack in the rudder upper hinge fitting accomplish the following:\n\n    Remove the rudder upper hinge pin and carefully displace the rudder from the fin aft to expose the surfaces of both rudder upper hinge brackets P/N 77610-02.\n\n    2. Visually inspect all the hinge surfaces in the area of the hinge pin hole to the forward edge of the hinge for cracks using at least a 10X lens, or an approved dye penetrant technique.\n\n    3. On re-installation of the upper hinge bolt, torque nut to 50-70 inch pounds (do not exceed maximum figure).\n\n    4. Replace the hinge brackets with steel brackets P/N 77610-03 in accordance with Piper SB No. 686.\n\n    5. Retire the steel hinge brackets P/N 77610-03 from service.\n\nNote: Installation of steel hinge brackets P/N 77610-03 obviates the need for inspection in accordance with paras. S1 and 2.\n\nCompliance: For Paras. 1, 2 & 3 \\- Initially inspect within 10 hours time in service after 6 June 1980 and thereafter at intervals not exceeding 50 hours time in service until modified in accordance with Piper SB No. 686.\n\nFor Para. 4 \\- Within 300 hours time in service after 4 July 1980.\n\nFor Para. 5 \\- Prior to the accumulation of 5000 hours component time in service.\n\nBackground: Reports have been received of cracks developing in the upper rudder hinge brackets. This Directive has been revised to reflect the content of the applicable FAA AD 80- 22-13 Amdt. 39-3960.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"The directive was revised to align with the applicable FAA AD (Background). The revision introduces a mandated replacement of aluminium hinge brackets with steel P/N 77610‑03 within 300 hours and requires retirement of those steel brackets at 5,000 component hours, while stating that installing the steel brackets removes the recurring inspection requirement (Requirements paras 4–5; Note; Compliance)."},"complexity_factors":["Narrow applicability by specific serial number ranges (Applicability) increases administrative checking for affected owners/operators.","Multiple action types required: physical displacement/removal, visual or dye‑penetrant inspection, torqueing, part replacement and component retirement (Requirements paras 1–5).","Several distinct compliance deadlines: initial 10 hours, recurring 50‑hour intervals, replacement within 300 hours, and retirement at 5,000 component hours (Compliance).","Technical specifications add precision: minimum 10× magnification or approved dye penetrant for inspection; torque nut to 50–70 inch‑pounds (Requirements paras 2–3).","Referenced service information dependency: replacement must follow Piper SB No. 686, creating dependence on external manufacturer documentation (Requirement para 4).","Operational ambiguity risk: the note that steel bracket installation 'obviates the need for inspection in accordance with paras. S1 and 2' uses inconsistent paragraph labeling, which could confuse compliance interpretation (Note).","Cross‑jurisdictional alignment: revised text explicitly reflects an FAA AD, so corrective scope and timing may mirror FAA provisions rather than original domestic wording (Background)."],"plain_english_summary":"Requires owners/operators of specified Piper PA-38‑112 serial numbers to inspect the rudder upper hinge brackets for cracks, re-torque the upper hinge nut to 50–70 in·lb on re‑installation, and to replace aluminium brackets with steel P/N 77610‑03 within set flight‑hour limits; the steel fittings must be retired at 5,000 component hours. The directive aims to prevent hinge failures and has been revised to align with the applicable FAA airworthiness directive.\n\nThese obligations impose inspection, torque and parts‑replacement costs on aircraft owners/operators and remove recurring inspections once steel brackets are fitted."},"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":3,"scope_assessment":{"changed":false,"description":"This is Amendment 2 of an existing Airworthiness Directive. The scope remains tightly focused on the original safety issue (rudder upper hinge cracks in specific Piper PA-38 aircraft). The amendment updates the directive to align with the corresponding FAA AD, but does not expand the applicability or introduce new unrelated requirements."},"complexity_factors":["Multiple compliance deadlines with different triggering events (hours in service from specific dates)","Cross-reference to external technical document (Piper Service Bulletin No. 686)","Specific part numbers and serial number ranges requiring careful identification","Technical measurement requirements (torque specifications in inch-pounds, magnification levels)","Conditional logic: inspection requirement is 'obviated' (cancelled) once modification is complete"],"plain_english_summary":"This CASA Airworthiness Directive orders owners/operators of certain Piper PA‑38‑112 Tomahawks (serials from about 1978–1980) to inspect the rudder upper hinge brackets for cracks and, ultimately, replace the original aluminium brackets with steel parts. \n\nIt’s mandatory because cracked hinge brackets can lead to rudder failure and loss of control; the AD sets inspection intervals, torque/reassembly requirements, and retirement limits for the replacement parts to ensure safety."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement","history":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement/history","analysis":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement/analysis","conflicts":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement/conflicts","importantCases":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement/important-cases","documents":"/api/acts/ad-pa-38-17-amdt-2-rudder-upper-hinge-inspection-and-replacement/documents"}}