{"id":"F2006L01067","name":"AD/CONVAIR/15 - Nose Landing Gear Aluminium Uplock Quadrant Lug","slug":"ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":58378,"registerId":"commonwealth-F2006L01067-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/15 | Nose Landing Gear AluminiumUplock Quadrant Lug | 5/2006 |\n| ------------- | ---------------------------------------------- | ------ |\n\n| Applicability: | Model 240, 340, and 440 aircraft, and all such aircraft converted to turbopropellor power.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Accomplish the following requirements:a. Remove the AN3-21 bolt attaching the nose landing gear uplock release cable clevis and the emergency release cylinder to the uplock assembly.b. Inspect the part number (P/N) 240-5250109-6 nose landing gear uplock quadrant for cracks in the AN3 bolt attach lug using a 2x or stronger magnifying glass, or dye penetrant method.c. If cracks are detected, before further flight, replace the quadrant with either a new aluminium quadrant P/N 240-5250109-6, or a steel quadrant P/N240-5250109-9. If a new aluminium quadrant is installed, accomplish Requirements 1.a. through 1.d. at the intervals specified in Compliance 1.c.d. Reinstall the AN3 bolt attaching release cable and emergency release cylinder and check rigging of the nose landing gear uplock installation in accordance with the applicable maintenance manual.2. Retire P/N 240-5250109-6 aluminium quadrants at specified interval.Note 1: Installation of steel quadrant P/N 240-5250109-9 constitutes terminating action for the requirements of this Directive.Note 2: FAA AD 77-10-11 Amdt 39-2905 refers. |\n| Compliance:    | 1. Within 60 hours time in service after 11 May 2006, and thereafter at intervals not to exceed 60 hours time in service; until a P/N 240-5250109-9 steel quadrant is installed.1.c. Accomplish Requirements 1.a. through 1.d. at intervals not to exceed 600 hours time in service.2. Before accumulating 1,200 hours time in service.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n\n|             | This Airworthiness Directive becomes effective on 11 May 2006.                                                                      |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------- |\n| Background: | The FAA requires certain actions to detect stress corrosion cracking in the aluminium uplock quadrant lug on the nose landing gear. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n31 March 2006","sortOrder":0},{"sectionNumber":"AD/CONVAIR/15","sectionType":"part","heading":"AD/CONVAIR/15","content":"## AD/CONVAIR/15","sortOrder":1},{"sectionNumber":"Nose Landing Gear AluminiumUplock Quadra","sectionType":"part","heading":"Nose Landing Gear AluminiumUplock Quadrant Lug","content":"## Nose Landing Gear Aluminium  \nUplock Quadrant Lug","sortOrder":2},{"sectionNumber":"5/2006","sectionType":"part","heading":"5/2006","content":"## 5/2006","sortOrder":3}],"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":false,"description":"This AD maintains its original narrow scope. It addresses a specific safety defect identified by the FAA in a particular aircraft component. The directive has not expanded beyond its original purpose of ensuring the airworthiness of Convair nose landing gear uplock quadrants."},"complexity_factors":["Single, specific mechanical issue addressed (one part on one aircraft type)","Only 2 part numbers referenced throughout","Clear sequential requirements (inspect → replace if cracked → retire at hour limit)","Simple compliance timeline (60 hours initial, then 600 hour intervals, or 1,200 hour retirement)","Minimal cross-referencing (only one FAA AD mentioned in background)","No nested exceptions or conditional logic — straightforward if/then structure","Short document (approximately 300 words of substantive content)"],"plain_english_summary":"This AD requires owners/operators of Convair 240/340/440 (including turboprop conversions) to inspect the aluminium nose-gear uplock quadrant lug for stress corrosion cracking and replace any cracked parts before further flight. Aluminium lugs must be retired after 1,200 flight hours, or operators may fit the steel replacement part (P/N 240-5250109-9) to eliminate the inspection requirement. It targets vintage Convair operators and became effective 11 May 2006."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"This directive implements inspection, replacement and retirement requirements specifically to detect and mitigate stress‑corrosion cracking of the aluminium uplock quadrant lug, consistent with the FAA AD it references. It remains focused on that single safety issue and on the same aircraft/part cohort; it does not broaden the subject matter or expand regulatory reach beyond addressing the identified fatigue/corrosion risk."},"complexity_factors":["Limited applicability to three aircraft models (Model 240, 340, 440) including turboprop conversions","Multiple specific part numbers referenced (P/N 240-5250109-6 aluminium, P/N 240-5250109-9 steel, AN3-21 bolt)","Three different interval thresholds to track (60 hours, 600 hours, 1,200 hours) with conditional continuation depending on which part is installed","Two accepted inspection methods with different sensitivity and resourcing implications (2× magnifier or dye penetrant)","Terminating action condition (installation of steel quadrant) that changes ongoing obligations","Cross-reference to an external FAA AD (FAA AD 77-10-11), creating reliance on non-local regulatory material","Procedural steps include temporary removal of a bolt and subsequent rigging checks per the maintenance manual"],"plain_english_summary":"**What this instrument does (mechanical changes first)**\n\n- Requires operators of Convair/General Dynamics/Kelowna Flightcraft Model 240, 340 and 440 aeroplanes (including those converted to turboprop power) to inspect and, if necessary, replace the aluminium nose-landing-gear uplock quadrant lug (part number P/N 240-5250109-6). (Applicability)\n\n- Specifically, the directive requires: (Requirement 1)\n  - Remove the AN3-21 bolt that attaches the uplock release cable clevis and the emergency release cylinder to the uplock assembly (Req 1.a).  \n  - Inspect the uplock quadrant lug (P/N 240-5250109-6) for cracks using either a 2× (or stronger) magnifying glass or a dye-penetrant inspection method (Req 1.b).  \n  - If any cracks are found, replace the aluminium quadrant before further flight with either a replacement aluminium quadrant (same P/N) or a steel quadrant (P/N 240-5250109-9). If a new aluminium quadrant is fitted, continue the inspection and bolt-removal/reinstall cycle at the intervals set out in the Compliance section (Req 1.c–1.d).  \n  - Reinstall the AN3 bolt and check the rigging of the nose landing gear uplock in accordance with the applicable maintenance manual (Req 1.d).\n\n- Retirement and terminating action: Retire (remove from service) the aluminium quadrant (P/N 240-5250109-6) before it accumulates 1,200 hours time in service (Compliance 2). Installing the steel quadrant (P/N 240-5250109-9) is stated as a terminating action for the directive (Note 1).\n\n- Inspection/interval schedule (Compliance):  \n  - All affected aircraft must begin the required actions within 60 hours time in service after 11 May 2006 and then repeat them at intervals not exceeding 60 hours until a steel quadrant is installed (Compliance 1).  \n  - If an aluminium quadrant is replaced with a new aluminium quadrant, the required bolt removal/inspection/rigging sequence must be done at intervals not to exceed 600 hours time in service (Compliance 1.c).  \n  - Aluminium quadrants must be retired before 1,200 hours time in service (Compliance 2).\n\n**Why it exists (stated purpose)**\n\n- The directive implements actions mirroring an FAA airworthiness directive (FAA AD 77-10-11 Amdt 39-2905) to detect and address stress-corrosion cracking in the aluminium uplock quadrant lug on the nose landing gear. (Background)\n\n**Who this affects and who decides**\n\n- Who pays: aircraft owners/operators and maintenance organisations bear the costs — labour for recurrent inspections, possible dye-penetrant inspection services, replacement parts (either new aluminium quadrants or the steel quadrant), and aircraft downtime. (Requirements; Compliance)\n\n- Who decides: certified maintenance organisations or authorised personnel perform the inspections, fittings and rigging per the aircraft maintenance manual, and operators must comply with the directive under CASA oversight. Installing the steel quadrant ends the directive’s recurring inspection requirement (Note 1).\n\n**Costs, incentives and trade-offs**\n\n- Direct costs: recurrent inspections every 60 hours (until a steel quadrant is fitted) create ongoing maintenance hours and associated downtime. Dye-penetrant inspection may require specialised materials/facilities and slightly higher labour time than a visual inspection with magnifier. (Req 1.b; Compliance)\n\n- One-off cost vs ongoing cost: operators can choose to fit the steel quadrant (P/N 240-5250109-9). That upgrade is a one-off cost but constitutes terminating action for the AD, removing the need for the frequent 60‑hour inspections. If operators keep using aluminium replacement quadrants, they face longer 600‑hour inspection intervals but must still retire aluminium parts by 1,200 hours. (Req 1.c; Compliance; Note 1)\n\n- Risk and detection limits: the inspection options offered (2× magnifier or dye penetrant) differ in sensitivity. Dye penetrant is more likely to detect fine surface cracks but requires suitable facilities and trained personnel. Relying on a low-magnification visual inspection increases the risk of missing small cracks. (Req 1.b)\n\n- Behavioural effects: the directive creates an economic incentive to invest in the steel quadrant to remove recurring inspection burden. Operators with low utilisation may defer the upgrade but incur repeated inspection costs; high-utilisation operators face faster accumulation toward the 1,200‑hour retirement requirement.\n\n**Implementation and compliance risks**\n\n- Compliance depends on correct removal/reinstallation and rigging per the applicable maintenance manual — errors in rigging could introduce other safety issues. (Req 1.d)\n\n- Record-keeping and tracking hours-in-service for each quadrant are necessary to ensure retirement before 1,200 hours; poor records risk non‑compliance. (Compliance 2)\n\n**Official rationale and testing it against costs**\n\n- The stated purpose is to detect and mitigate stress-corrosion cracking in the aluminium uplock quadrant lug (Background; FAA AD reference). Mechanically, the directive reduces the single-point failure risk by requiring inspection and replacement or permanent modification (steel quadrant). The trade-off is maintenance effort and replacement cost paid by operators against reduced risk and, if steel is installed, lower long‑term inspection burden.\n\n(References: Requirement paragraphs 1.a–1.d, Compliance paragraphs 1 and 2, Notes 1–2, Background.)"}},"importantCases":[],"_links":{"self":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug","history":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug/history","analysis":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug/analysis","conflicts":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug/conflicts","importantCases":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug/important-cases","documents":"/api/acts/ad-convair-15-nose-landing-gear-aluminium-uplock-quadrant-lug/documents"}}