{"id":"F2006B05819","name":"AD/PA-32/25 Amdt 2 - Stabilator Hinge Attaching Bolts","slug":"ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":135780,"registerId":"commonwealth-F2006B05819-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/PA-32/25 Amdt 2 - Stabilator Hinge Attaching Bolts","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-32 (Cherokee Six) Series Aeroplanes\n\nAD/PA-32/25\n\nAmdt 2\n\n  \nStabilator Hinge Attaching Bolts 10/92\n\nApplicability: Models PA-32-260 and \\-300 with serial numbers listed in Piper SL 614.\n\nRequirement: 1. Remove tail cone fairing and closeout panel from the aft fuselage bulkhead to gain access to the twelve fitting attachment nuts. There are six bolts and nuts per fitting.\n\n    2. Inspect around bolt holes in bulkhead and fitting for cracks, deformation, or other damage.\n\n    3. Torque nuts to a value of 35-40 inch pounds and reinstall closeout panel and tail cone fairing.\n\nNote: FAA AD 72-14-07 refers.\n\nCompliance: Unless already accomplished; within 100 hours time in service after 17 September 1992. The compliance of the previous issue of this Directive was: Within 100 hours time in service after 31 August 1972. This Amendment is effective from 17 September 1992.\n\nBackground: This Directive was issued to ensure that the bolts on the attachment fittings were of a specified uniform torque value. Amendment 2 is issued to align the applicability with the relevant Country of Origin Directive.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":true,"description":"Amendment 2 updates the applicability to align with the Country of Origin Directive by specifying serial numbers per Piper SL 614 and sets the effective compliance date of 17 September 1992. The substantive maintenance requirements (inspection and torquing to 35–40 in‑lb) remain the same. (Background; Applicability; Compliance.)"},"complexity_factors":["Narrow technical scope limited to particular PA‑32 models/serials (Applicability referencing Piper SL 614).","Specific mechanical instruction: removal of fairing/closeout panel, visual inspection for cracks/deformation, and torquing to a precise value (Requirement).","Short, fixed compliance deadline tied to flight hours and an effective date (Compliance).","Cross‑reference to FAA AD 72‑14‑07 and Piper SL 614 creates reliance on external documents for full scope (Requirement; Background).","Low legal discretion: prescriptive maintenance actions rather than delegations or discretionary powers (Requirement)."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of specified Piper PA‑32‑260 and PA‑32‑300 aeroplanes (serial numbers listed in Piper SL 614) to remove the tail cone fairing and closeout panel, inspect the stabilator hinge bolt holes and fittings for cracks or deformation, torque the twelve attaching nuts to 35–40 inch‑pounds, and reinstall the panels (Requirement; Applicability). Compliance is mandatory within 100 hours time‑in‑service after 17 September 1992; aircraft owners/operators and maintenance providers pay for and carry out or contract the work, and CASA enforces compliance (Compliance; Background)."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is Amendment 2 to an existing directive. The amendment simply updates the applicability to align with the US (Country of Origin) directive and extends the compliance deadline. The core safety purpose — ensuring proper torque on stabilator hinge bolts — remains unchanged from the original 1972 directive."},"complexity_factors":["Very short document (approximately 200 words)","Only 2 defined applicability criteria (model numbers and serial numbers)","Simple 3-step procedural requirement with no conditional logic","Single cross-reference to FAA AD 72-14-07 (informational only)","No nested exceptions or complex compliance calculations","Clear, unambiguous mechanical instructions"],"plain_english_summary":"This AD requires owners/operators and maintenance personnel of specified Piper PA-32-260 and PA-32-300 serial-numbered aeroplanes to inspect and torque the bolts securing the stabilator. \n\nDone within 100 hours after 17 September 1992, the action prevents loose or damaged stabilator fittings that could cause control problems or structural failure in flight."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts","history":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts/history","analysis":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts/analysis","conflicts":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts/conflicts","importantCases":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts/important-cases","documents":"/api/acts/ad-pa-32-25-amdt-2-stabilator-hinge-attaching-bolts/documents"}}