{"id":"F2006B07509","name":"AD/TSA-600/45 Amdt 1 - Wing 55% Upper Spar Cap","slug":"ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":50001,"registerId":"commonwealth-F2006B07509-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/TSA-600/45 Amdt 1 - Wing 55% Upper Spar Cap","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)  \nAerostar (Piper/Ted Smith) 600 and 700 Series Aeroplanes\n\nAD/TSA-600/45\n\nAmdt 1\n\n  \nWing 55% Upper Spar Cap 2/99\n\nApplicability: All serial numbers of the following aircraft models:\n\nPA-60-600 (Aerostar 600) PA-60-601 (Aerostar 601)\n\nPA-60-601P (Aerostar 601P) PA-60-602P (Aerostar 602P) PA-60-700P (Aerostar 700P)\n\nRequirement: 1. Inspect the forward face of each wing’s 55-percent upper spar cap for cracks above the main landing gear fitting in the top of the wheel well. Accomplish this inspection in accordance with the Instructions section of Aerostar Service Bulletin SB600-132. The initial inspection must be accomplished using dye penetrant methods, except that for aircraft repaired as a result of the inspection required by the original issue of this Directive, the initial inspection may be visual. All subsequent inspections must be dye penetrant or visual inspections.\n\n    2. If any cracks are found during the Requirement 1 inspection, accomplish either paragraph a. or b. below:\n\n    Replace the upper spar cap in accordance with the applicable maintenance manual, and continue to inspect in accordance with Requirement 1; or,\n\n    b. Obtain a repair scheme from the manufacturer or a person authorised by CASA, incorporate this scheme, and continue to inspect in accordance with Requirement 1.\n\nNote: FAA AD 98-24-29 Amdt 39-10916 refers.\n\nCompliance: 1. Initially, within 100 hours time in service after 25 February 1999, thereafter at intervals not to exceed 100 hours time in service.\n\n2. Repair before further flight and re-inspect at intervals not to exceed 100 hours time in service.\n\nThis Amendment becomes effective on 25 February 1999.\n\nBackground: A significant crack, running in a spanwise direction, was found in the wing upper spar cap in the area above the main landing gear attachment. As a precautionary measure the area was inspected on all aircraft which may be similarly affected.\n\nAmendment 1 is issued in response to the recent issue of an FAA AD which introduces initial and repetitive inspections to aircraft previously cleared of having cracks, and to aircraft that were repaired after cracks were found.\n\nThe original issue of this Airworthiness Directive became effective on 2 January 1997.\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES","sortOrder":0}],"analysis":{"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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":true,"description":"The original directive (effective January 1997) appears to have been a one-time or limited inspection following the discovery of a crack. Amendment 1 significantly expands the scope by: (1) introducing recurring inspections every 100 flight hours rather than a single check, (2) applying to aircraft previously cleared as unaffected, and (3) applying to aircraft that had already been repaired. This transforms a targeted precautionary inspection into an ongoing airworthiness monitoring regime."},"complexity_factors":["Single, clearly defined applicability (5 specific aircraft models)","Two main requirements with straightforward conditional logic (if cracks found → repair)","Only one defined technical reference (Aerostar Service Bulletin SB600-132)","Simple compliance timeline (100 hours recurring)","Minimal cross-referencing (one note referencing related FAA directive)","Short document length (approximately 300 words of substantive content)"],"plain_english_summary":"This safety inspection order requires owners/operators and maintenance organisations of Piper Aerostar 600/700-series aircraft to perform recurring inspections of the wing’s upper spar cap (around the 55% station) to detect cracks. It mandates dye‑penetrant testing (with limited visual exceptions), grounding any aircraft with detected cracks until the spar is replaced or an approved repair is fitted, preventing potential catastrophic wing failure by ensuring early detection and continued monitoring."},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":true,"description":"Amendment 1 expands the original AD's inspection obligations by introducing initial and repetitive inspections for aircraft that had been previously cleared of cracks and for aircraft repaired after cracks were found, aligning the Directive with FAA AD 98-24-29 (Background). The original AD took effect 2 January 1997; this Amendment (effective 25 February 1999) adds those inspection and recurrence requirements."},"complexity_factors":["Applicability: affects all serial numbers of PA-60-600, PA-60-601, PA-60-601P, PA-60-602P and PA-60-700P aircraft (Applicability).","Inspection location and standard: inspect forward face of each wing’s 55%-upper spar cap above the main landing gear in the top of the wheel well per Aerostar Service Bulletin SB600-132 (Requirement 1).","Inspection methods: initial inspection must use dye‑penetrant methods, except aircraft repaired as a result of the original AD may have an initial visual inspection; all subsequent inspections may be dye‑penetrant or visual (Requirement 1).","Timing and recurrence: initial inspection within 100 hours time in service after 25 February 1999, then at intervals not to exceed 100 hours (Compliance 1).","Mandatory corrective action: if cracks found, either replace the upper spar cap per the maintenance manual or incorporate a repair scheme from the manufacturer or a person authorised by CASA (Requirement 2 a/b).","Flight prohibition and follow-up: repairs must be done before further flight and re‑inspection continues at intervals not to exceed 100 hours (Compliance 2).","Regulatory cross‑reference and policy alignment: references FAA AD 98-24-29; Amendment 1 was issued to introduce inspections for aircraft previously cleared or repaired (Note; Background).","Compliance burden and costs: recurring inspections every 100 hours, potential parts and labour for replacement, or administrative/technical cost to obtain and implement an approved repair scheme from manufacturer or CASA‑authorised person (Requirement 1; Requirement 2).","Operational/implementation points: dye‑penetrant capability or outsourcing needed; accessibility of inspection area (wheel well) may increase man‑hours and downtime; authority to approve repairs rests with manufacturer or CASA‑authorised person (Requirement 1; Requirement 2)."],"plain_english_summary":"Owners and operators of Aerostar (Piper/Ted Smith) PA-60-600/601/601P/602P/700P aeroplanes must inspect the forward face of each wing’s 55% upper spar cap above the main landing gear for cracks, initially using dye‑penetrant (visual allowed in certain previously repaired aircraft) and then at recurring 100‑hour intervals. If cracks are found the spar cap must be replaced per the maintenance manual or repaired under a manufacturer- or CASA‑authorised scheme before further flight. The measure responds to a spanwise crack discovered above the landing gear attachment."}},"importantCases":[],"_links":{"self":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap","history":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap/history","analysis":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap/analysis","conflicts":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap/conflicts","importantCases":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap/important-cases","documents":"/api/acts/ad-tsa-600-45-amdt-1-wing-55-upper-spar-cap/documents"}}