{"id":"F2008L04429","name":"AD/PA-38/22 Amdt 1 - Aft Vertical Fin Spar - Inspection","slug":"ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76422,"registerId":"commonwealth-F2008L04429-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-38/22 Amdt 1 | Aft Vertical Fin Spar - Inspection | 13/2008 |\n| ------------------ | ---------------------------------- | ------- |\n\n| Applicability: | All model PA-38-112 with S/Nos. 38-78A0001 to 38-80A0198 which do not incorporate aft vertical fin spar assembly P/N 77601-16, upper rudder hinge shimP/N 85606-02, and fuselage bulkhead assembly P/N 85615-02.                                                                                                                                                                                        |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Inspect the aft vertical fin spar P/N 77601-02 for cracks in accordance with PiperSB No. 745 Part IV using a dye penetrant method or equivalent.Note: USA AD 82-27-08 (a)(3) refers.                                                                                                                                                                                                                    |\n| Compliance:    | At intervals not exceeding 200 hours time in service.Compliance with the original issue of this Directive constitutes compliance with Amendment 1.                                                                                                                                                                                                                                                      |\n|                | This Amendment becomes effective on 18 December 2008.                                                                                                                                                                                                                                                                                                                                                   |\n| Background:    | Testing by the aircraft manufacturer has revealed that cracks may develop in the aft vertical fin spar and bulkhead.Amendment 1 aligns the AD with USA AD 82-27-08 (a)(3) to clarify that this periodic inspection is not applicable to aircraft which have been modified by incorporation of the new design of aft vertical fin spar assembly, upper rudder hinge shim and fuselage bulkhead assembly. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 October 2008","sortOrder":0},{"sectionNumber":"AD/PA-38/22 Amdt 1","sectionType":"part","heading":"AD/PA-38/22 Amdt 1","content":"## AD/PA-38/22 Amdt 1","sortOrder":1},{"sectionNumber":"Aft Vertical Fin Spar - Inspection","sectionType":"part","heading":"Aft Vertical Fin Spar - Inspection","content":"## Aft Vertical Fin Spar - Inspection","sortOrder":2},{"sectionNumber":"13/2008","sectionType":"part","heading":"13/2008","content":"## 13/2008","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment narrows rather than expands scope. The original directive applied more broadly; Amendment 1 specifically excludes aircraft that have been modified with improved parts. This is a precision adjustment to avoid redundant inspections, not scope creep."},"complexity_factors":["Very short document (approximately 250 words)","Only 3 defined part numbers in the applicability section","Single operational requirement with one compliance method","No nested exceptions or conditional logic beyond the applicability carve-out","One cross-reference to a US AD and one to a manufacturer service bulletin","Straightforward temporal compliance (every 200 hours)"],"plain_english_summary":"CASA requires owners/operators of Piper PA-38‑112 Tomahawks (S/N 38‑78A0001 to 38‑80A0198) to inspect the aft vertical fin spar (P/N 77601‑02) for cracks using dye‑penetrant or approved methods every 200 flight hours, unless the aircraft has been modified with the redesigned spar, an upper rudder hinge shim, and a fuselage bulkhead assembly.\n\nThis amendment clarifies that upgraded aircraft are exempt, aligns with US AD 82‑27‑08, and leaves prior compliance unchanged."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Amendment 1 clarifies and aligns the Directive with USA AD 82-27-08 (a)(3) by explicitly excluding aircraft already modified with the redesigned aft vertical fin spar, upper rudder hinge shim and bulkhead (Background / Applicability). It does not broaden applicability, add new inspection types, or change the 200-hour recurring interval; compliance with the original issue still constitutes compliance (Compliance)."},"complexity_factors":["Narrow technical applicability tied to specific serial-number range and part numbers (Applicability).","Mandatory inspection method referenced (dye penetrant) and a service bulletin: Piper SB No. 745 Part IV (Requirement).","Recurring compliance obligation with a fixed interval: every 200 hours TIS (Compliance).","Explicit exemption for aircraft with redesigned assemblies (P/Ns 77601-16, 85606-02, 85615-02) requiring parts-level checks (Applicability / Background).","Cross-reference to USA AD 82-27-08 (a)(3) introduces an external regulatory linkage (Background / Requirement).","Operational burden concentrated on owners/operators who must schedule, perform and fund inspections (Compliance / Requirement).","Limited regulator discretion — the directive prescribes method and interval, but allows an 'equivalent' inspection method (Requirement).","Compliance transition: original-issue compliance counts as compliance with Amendment 1, reducing retroactive enforcement complexity (Compliance)."],"plain_english_summary":"Requires owners/operators of specified `Piper PA-38-112` aircraft (S/Ns 38-78A0001 to 38-80A0198) that have not had the redesigned assemblies to inspect the aft vertical fin spar (P/N 77601-02) for cracks using dye-penetrant per Piper SB No. 745 Part IV, at intervals not exceeding 200 hours. Aircraft fitted with the redesigned spar, upper rudder hinge shim (`P/N 85606-02`) and bulkhead (`P/N 85615-02`) are exempt. The stated purpose is to detect cracking; inspection costs and scheduling are borne by operators."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection","history":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection/history","analysis":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection/analysis","conflicts":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection/conflicts","importantCases":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection/important-cases","documents":"/api/acts/ad-pa-38-22-amdt-1-aft-vertical-fin-spar-inspection/documents"}}