{"id":"F2006B05502","name":"AD/PA-23/75 Amdt 1 - Rudder Upper and Lower Hinge Attachments - Inspection","slug":"ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":46348,"registerId":"commonwealth-F2006B05502-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PA-23/75 Amdt 1 - Rudder Upper and Lower Hinge Attachments - 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)  \nPiper PA-23 (Apache and Aztec) Series Aeroplanes\n\nAD/PA-23/75\n\nAmdt 1\n\n  \n\nRudder Upper and Lower Hinge Attachments - Inspection\n\n  \n9/80\n\nApplicability: All models PA-23 and PA-23-160 with S/Nos. 23-1 and subsequent.\n\nRequirement: 1. Remove the rudder upper hinge P/N 17063-03 and inspect the rudder upper hinge reinforcement bracket P/N 17067-18 or equivalent for cracks using a dye penetrant technique.\n\n    2. Inspect the rudder lower hinge bracket assembly P/N 17289-00 in the bearing area for cracks using a dye penetrant technique.\n\n    3. If cracks are found in the reinforcing bracket during the inspection of para. 1, remove the bracket and inspect the exposed spar web for cracks using a dye penetrant technique.\n\nNote 1: A 10X glass may be used in lieu of a dye penetrant technique for recurring inspections.\n\nNote 2: FAA AD 78-08-03 Amdt. 39-3339 refers to this inspection.\n\nCompliance: 1 & 2 \\- Unless already accomplished, initially inspect within 100 hours time in service after 30 September 1980 and thereafter at intervals not exceeding 1000 hours time in service or 3 years whichever occurs first.\n\nBackground: This amendment reflects the current FAA inspection requirements as referenced in FAA AD 78-08-03 Amdt. 39-3339.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a narrow, technical maintenance directive focused on a specific airframe component. It has not expanded beyond its original purpose of ensuring rudder hinge integrity on specific Piper aircraft models."},"complexity_factors":["Single, specific aircraft type and serial number range","Only 3 numbered requirements plus 2 notes","No defined terms section","No cross-references to other legislation (only reference to FAA AD is informational)","Simple conditional logic (only one 'if-then' in requirement 3)","Clear, sequential compliance timeline","Total length: approximately 200 words"],"plain_english_summary":"This CASA Airworthiness Directive mandates regular inspections of the rudder hinge attachments on Piper PA‑23/PA‑23‑160 aircraft (serials 23‑1 onward). Operators must use dye‑penetrant (or 10× magnification follow‑ups) to check upper and lower hinge brackets and the rudder spar where cracks are suspected. Inspections start within 100 flight hours from 30‑Sep‑1980 and repeat every 1,000 hours or 3 years. It prevents in‑flight rudder failure and aligns with the FAA."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Background states this amendment 'reflects the current FAA inspection requirements' (FAA AD 78‑08‑03). Mechanically, the amendment aligns inspection procedures and compliance timing with that FAA AD, affecting inspection methods and intervals applicable to PA‑23 series aircraft S/N 23‑1 onward."},"complexity_factors":["Technical inspection method requirement (dye‑penetrant or 10× glass) imposes equipment/skill needs.","Removal of the upper hinge bracket and inspection of the exposed spar web if cracks are found increases labour and downtime.","Specific part-number and serial-number applicability requires record checks to determine affected aircraft.","Two-tier compliance timing (initial 100 hours after a specified date, then 1000 hours or 3 years) requires ongoing tracking.","Cross-reference to FAA AD 78‑08‑03 means operators must monitor an external standard for related changes."],"plain_english_summary":"Requires owners/operators of all Piper PA‑23 (Apache and Aztec) aircraft, serial 23‑1 onward, to inspect the rudder upper and lower hinge attachments for cracks. Inspections must use a dye‑penetrant technique (a 10× glass is allowed for recurring checks); if the reinforcing bracket is cracked it must be removed and the spar web inspected. Compliance is initial inspection within 100 hours TIS after 30 Sept 1980, then every 1000 hours or 3 years, whichever is sooner. The operator bears inspection labour, downtime and any repair costs."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection","history":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection/history","analysis":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection/analysis","conflicts":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection/conflicts","importantCases":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection/important-cases","documents":"/api/acts/ad-pa-23-75-amdt-1-rudder-upper-and-lower-hinge-attachments-inspection/documents"}}