{"id":"F2006L01099","name":"AD/CONVAIR/8 - NLG Drag Strut Upper Left Hand Segments","slug":"ad-convair-8-nlg-drag-strut-upper-left-hand-segments","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":58447,"registerId":"commonwealth-F2006L01099-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Kelowna Flightcraft (General Dynamics/Co","sectionType":"division","heading":"Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes","content":"### Kelowna Flightcraft (General Dynamics/Convair) Series Aeroplanes\n\n| AD/CONVAIR/8 | NLG Drag Strut Upper Left Hand Segments | 5/2006 |\n| ------------ | --------------------------------------- | ------ |\n\n| Applicability: | Model 340 and 440 aircraft, and any such model aircraft converted to turbopropeller power.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Perform an external visual inspection of all part number (P/N) 340-5210103, 5215103, or 340-7310231 nose landing gear drag strut upper left hand segments for cracking in the area depicted by Figure 1, view A-A, General Dynamics Service Bulletin (SB) 640 (340D) No. 32-7, dated 20 June 1973, by dye penetrant, eddy current, or ultrasonic methods, in accordance with the Accomplishment Instructions of SB 32-7 (disassembly of strut is not required).2. If a crack is detected during any inspection, replace the drag strut with a new P/N 340-7310231-1 or serviceable parts (items 1 through 4, Convair Service Engineering Report No. 340-44A/440-44A, dated 16 June 1961.3. If cracks are not detected during any inspection, repetitively inspect in accordance with Requirement 1.If a new P/N 340-7310231-1 part is used as a replacement, the inspection requirements of this Directive are terminated.4. If a reworked part (re. Convair Service Engineering Report No. 340-44A/440-44A) is used as a replacement, inspect in accordance with Requirement 1.Note: FAA AD 73-18-01 Amdt 39-1705 refers. |\n| Compliance:    | 1. Unless the initial inspection is already accomplished, within 10 landings after11 May 2006. Reinspect within 600 landings of initial inspection, unless already accomplished.2. Before further flight.3. At intervals not to exceed 2,400 landings.4. Reinspect within 600 landings after installation. Inspect thereafter at intervals not to exceed 2,400 landings.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n|                | This Airworthiness Directive becomes effective on 11 May 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n\n| Background: | The FAA requires certain inspections to prevent possible collapse of the nose landing gear due to fatigue cracking of the drag strut upper left hand segments. |\n| ----------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 March 2006","sortOrder":0},{"sectionNumber":"AD/CONVAIR/8","sectionType":"part","heading":"AD/CONVAIR/8","content":"## AD/CONVAIR/8","sortOrder":1},{"sectionNumber":"NLG Drag Strut Upper Left Hand Segments","sectionType":"part","heading":"NLG Drag Strut Upper Left Hand Segments","content":"## NLG Drag Strut Upper Left Hand Segments","sortOrder":2},{"sectionNumber":"5/2006","sectionType":"part","heading":"5/2006","content":"## 5/2006","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The Directive applies to the same Convair 340/440 airframes (including turboprop conversions) and targets the specified NLG drag-strut segments as described in referenced service documents. It does not broaden part types or aircraft beyond those listed; it primarily formalises inspection and replacement requirements already identified in the referenced FAA AD and service bulletins."},"complexity_factors":["Multiple specific part numbers to inspect and replace (P/N 340-5210103, 5215103, 340-7310231; replacement P/N 340-7310231-1) (Requirement 1–3)","Several accepted non-destructive inspection methods (dye penetrant, eddy current, ultrasonic) and a non-disassembly rule (Requirement 1)","Different outcomes change ongoing obligations: installing a new P/N terminates inspections, installing a reworked part requires continued inspections (Requirement 2–4)","Compliance timing tied to landings with multiple intervals (within 10 landings, reinspect within 600 landings, repeat at ≤2,400 landings) creating operational scheduling constraints (Compliance)","Applicability covers original and turboprop-converted airframes, widening the affected fleet (Applicability)","Cross-references to historical service documents and FAA ADs increase interpretation needs (SB 32-7, Convair Service Engineering Report, FAA AD 73-18-01) (Requirement note; Background)","Clear effective date imposes near-term mandatory action (Effective 11 May 2006)"],"plain_english_summary":"This Airworthiness Directive requires owners/operators of Convair Model 340 and 440 (including turboprop conversions) to inspect specific nose-landing-gear drag strut upper left-hand segments for cracks, using dye-penetrant, eddy-current or ultrasonic methods, and to replace cracked parts. It sets inspection intervals tied to landings, gives replacement-part options that stop or continue inspections, and fixes short compliance deadlines. It matters because it aims to prevent nose-gear collapse from fatigue cracking and prescribes who must inspect and when."},"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":3,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive implementing a specific safety inspection requirement. The scope remains tightly focused on the original safety concern (fatigue cracking in nose landing gear drag struts) and has not expanded beyond this specific mechanical defect."},"complexity_factors":["Multiple part numbers referenced (P/N 340-5210103, 5215103, 340-7310231, 340-7310231-1) with subtle distinctions between them","Four separate compliance deadlines with conditional logic (Requirements 1-4 mapped to Compliance 1-4)","Cross-reference to external technical documents: General Dynamics Service Bulletin 32-7, Convair Service Engineering Report 340-44A/440-44A, and FAA AD 73-18-01","Technical inspection methods specified (dye penetrant, eddy current, ultrasonic) requiring specialist aviation maintenance knowledge","Termination condition for inspection requirements (new P/N 340-7310231-1) vs. continuing obligations (reworked parts)"],"plain_english_summary":"This AD requires Australian owners/operators of Convair Model 340/440 (including turboprop conversions) to inspect the nose landing gear drag strut upper left-hand segment for fatigue cracking using dye‑penetrant, eddy‑current, or ultrasonic methods, replace any cracked part before further flight, and continue periodic inspections unless replaced with the specified new part number. It mirrors an FAA action to prevent nose‑gear collapse; the first inspection was mandated within 10 landings of 11 May 2006."}},"importantCases":[],"_links":{"self":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments","history":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments/history","analysis":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments/analysis","conflicts":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments/conflicts","importantCases":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments/important-cases","documents":"/api/acts/ad-convair-8-nlg-drag-strut-upper-left-hand-segments/documents"}}