{"id":"F2008L04427","name":"AD/PA-38/21 Amdt 1 - Vertical Fin Forward Spar Attachment Plate Replacement Life Limits","slug":"ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76418,"registerId":"commonwealth-F2008L04427-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Piper PA-38 (Tomahawk) Series Aeroplanes","sectionType":"division","heading":"Piper PA-38 (Tomahawk) Series Aeroplanes","content":"### Piper PA-38 (Tomahawk) Series Aeroplanes\n\n| AD/PA-38/21 Amdt 1 | Vertical Fin Forward Spar AttachmentPlate Replacement Life Limits | 13/2008 |\n| ------------------ | ----------------------------------------------------------------- | ------- |\n\n| Applicability: | All model PA-38-112 with S/Nos. 38-81A0001 to 38-82A0122.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. On aircraft with S/No. 38-81A0001 to 38-82A0101 which do not have Piper Kit No. 764421 installed, upon achieving 3000 hours time in service, and at intervals not exceeding 3000 hours time in service, replace the vertical fin forward spar attachment plate, Piper P/N 77553-05.Note 1: USA AD 82-27-08 (b)(1) refers.2. On aircraft with S/No. 38-81A0001 to 38-82A0101 which have Piper Kit No. 764421 installed, upon achieving 5000 hours time in service, and at intervals not exceeding 5000 hours time in service, replace the vertical fin forward spar attachment plate, Piper P/N 77553-05.Note 2: USA AD 82-27-08 (b)(2) and Piper SB No. 710 refer.3. On aircraft with S/No. 38-82A0102 to 38-82A0122, upon achieving 5000 hours time in service, and at intervals not exceeding 5000 hours time in service, replace the vertical fin forward spar attachment plate, Piper P/N 77553-05.Note 3: USA AD 82-27-08 (c) refers.Note 4: For aircraft with S/No. 38-82A0123 and higher, the retirement time for P/N 77553-05 is specified in the FAA-approved Airplane Flight Manual. |\n| Compliance:    | Compliance with the original issue of this Directive constitutes compliance with Amendment 1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n|                | This Amendment becomes effective on 18 December 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n| Background:    | Fatigue testing of the empennage structure has established replacement life limits.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               |\n\n|     | Amendment 1 aligns the requirement for aircraft which do not have Piper Kit No. 764421 installed with the requirement in USA AD 82-27-08 (b)(1). Amendment 1 adds aircraft with S/Nos. 38-82A0102 to 38-82A0122, and adds Note 4 regarding aircraft with S/Nos. 38-82A0123 and higher. |\n| --- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 October 2008","sortOrder":0},{"sectionNumber":"AD/PA-38/21 Amdt 1","sectionType":"part","heading":"AD/PA-38/21 Amdt 1","content":"## AD/PA-38/21 Amdt 1","sortOrder":1},{"sectionNumber":"Vertical Fin Forward Spar AttachmentPlat","sectionType":"part","heading":"Vertical Fin Forward Spar AttachmentPlate Replacement Life Limits","content":"## Vertical Fin Forward Spar Attachment  \nPlate Replacement Life Limits","sortOrder":2},{"sectionNumber":"13/2008","sectionType":"part","heading":"13/2008","content":"## 13/2008","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"Amendment 1 expands and clarifies scope. It aligns the no-kit requirement with USA AD 82-27-08(b)(1), adds serial numbers 38-82A0102–38-82A0122 into the 5,000 h replacement regime, and adds Note 4 directing that retirement times for S/N 38-82A0123 and higher are specified in the FAA-approved Airplane Flight Manual. This increases the set of affected aircraft and shifts some retirement determinations to the AFM."},"complexity_factors":["Multiple conditional replacement intervals (3,000 h or 5,000 h) tied to both serial-number ranges and whether Piper Kit No. 764421 is installed (Requirement items 1–3).","Distinct serial-number bands: 38-81A0001–38-82A0101; 38-82A0102–38-82A0122; and a separate provision for 38-82A0123 and higher (Notes 3–4).","Cross-references to external authorities (USA AD 82-27-08 and Piper SB/AFM) require operators to consult other documents to determine exact obligations (Notes 1–4).","Operational compliance burden: tracking total time-in-service (TIS) for affected parts and scheduling replacements at specified intervals.","Parts management and maintenance planning: need to source P/N 77553-05 replacements and record their retirement/replacement history.","Administrative clarity vs. retrofit complexity: amendment aligns some requirements with the FAA AD but also adds aircraft into scope, increasing the population of affected operators.","Compliance statement: compliance with the original Directive satisfies the amendment, which affects audit/transition considerations.","Legal/operational deadline: amendment effective date creates a fixed compliance timeline for operators to apply the life limits."],"plain_english_summary":"Sets compulsory replacement intervals for the vertical fin forward spar attachment plate (Piper P/N 77553-05) on specified Piper PA-38-112 Tomahawk aircraft: 3,000 hours TIS for certain early serial numbers without Piper Kit No. 764421, and 5,000 hours TIS where the kit is fitted or for later serial ranges. It affects owners/operators who must track hours and replace the plate to meet fatigue-derived life limits established by testing."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":true,"description":"The amendment expanded the original directive's scope. It added coverage for aircraft with serial numbers 38-82A0102 to 38-82A0122 (which weren't in the original), added guidance for newer aircraft (38-82A0123+) by referring them to the flight manual, and aligned requirements with the US AD for aircraft without the modification kit. The original likely only covered the earliest serial numbers."},"complexity_factors":["Multiple conditional requirements based on aircraft serial number ranges (4 distinct categories)","Cross-reference to US aviation regulations (USA AD 82-27-08) and manufacturer service bulletins (Piper SB No. 710)","Technical aviation terminology requiring specialized knowledge (empennage, time in service, part numbers)","Nested applicability conditions (serial number ranges AND modification kit status)","Short document but dense with conditional logic and external references"],"plain_english_summary":"This AD mandates periodic replacement of the vertical fin forward spar attachment plate on Piper PA‑38‑112 Tomahawk aircraft to prevent metal‑fatigue cracks that could lead to vertical fin separation. It covers serial numbers 38‑81A0001 through 38‑82A0122, affecting owners/operators of those aircraft.\n\nThis Amendment 1 aligns CASA requirements with US standards and expands the AD’s coverage to additional serial numbers previously omitted."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits","history":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits/history","analysis":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits/analysis","conflicts":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits/conflicts","importantCases":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits/important-cases","documents":"/api/acts/ad-pa-38-21-amdt-1-vertical-fin-forward-spar-attachment-plate-replacement-life-limits/documents"}}