{"id":"F2006B02733","name":"AD/B727/32 - Nose Landing Gear Actuating Bracket - Inspection","slug":"ad-b727-32-nose-landing-gear-actuating-bracket-inspection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42075,"registerId":"commonwealth-F2006B02733-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B727/32 - Nose Landing Gear Actuating Bracket - Inspection","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\nCOMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n \n\n![](image.001.png)  Boeing 727 Series Aeroplanes\n\n \n\nAD/B727/32 Nose Landing Gear Actuating Bracket - Inspection 6/66\n\nApplicability: All models with nose landing gear actuator brackets, P/N 65-16370-1, which have accumulated 1000 hours total time in service.\n\n \n\nRequirement: Remove Bracket P/N 65-16370-1 and inspect for cracks initiating at all bolt holes using a fluorescent dye penetrant or eddy current technique.\n\n \n\nCompliance: At intervals not exceeding 600 hours time in service.\n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n\n \n","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"The directive imposes a new or clarified inspection obligation for a specific part once it reaches 1000 hours TIS and at 600-hour intervals thereafter. The provided text does not indicate any change from an earlier rule or modification to prior scope; it sets a standalone applicability threshold, inspection method, and interval."},"complexity_factors":["Single, clearly-identified part number (P/N 65-16370-1) limits scope.","Simple, specified inspection techniques (fluorescent dye penetrant or eddy current) reduce procedural ambiguity.","Fixed applicability threshold (1000 hours TIS) and fixed recurring interval (600 hours) simplify scheduling.","Requirement to remove the bracket increases practical complexity (physical removal, not in-situ inspection).","No repair/clearance criteria stated in the text, leaving follow-up actions to existing maintenance rules and judgement."],"plain_english_summary":"What this directive does (mechanical effect)\n\n- The Commonwealth (Civil Aviation Safety Authority) requires that the nose landing gear actuating bracket, part number 65-16370-1, be removed from service and inspected for cracks that start at any of the bolt holes. The inspection must use either a fluorescent dye penetrant or an eddy current technique. (See: \"Requirement\".)\n\nWho is covered and when it starts\n\n- The rule applies to every Boeing 727 with that specific bracket (P/N 65-16370-1) once that bracket has reached 1,000 hours total time in service. Operators must apply the inspection requirement to those brackets. (See: \"Applicability\".)\n\nHow often it must be done\n\n- After the bracket has reached the 1,000-hour applicability threshold, it must be inspected repeatedly at intervals not exceeding 600 hours time in service. In other words, inspections occur every 600 hours TIS or sooner. (See: \"Compliance\".)\n\nPractical implications, incentives and costs (mechanical and economic mechanisms)\n\n- Who pays: aircraft owners/operators pay for removal, inspection (fluorescent dye penetrant or eddy current), and any follow-up repair or replacement if cracks are found. (See: \"Requirement\".)\n- Who decides: the regulator (Civil Aviation Safety Authority, via this airworthiness directive) determines the inspection obligation and methods. Operators must follow the directive's instructions. (See header and schedule title.)\n- Behaviour changes required: operators must remove the bracket from the aircraft to perform the specified non-destructive inspection methods; they must schedule repeated downtime to meet the 600-hour inspection interval; and they must track each affected bracket’s total time in service to know when the 1,000-hour applicability threshold is reached. (See: \"Applicability\", \"Requirement\", \"Compliance\".)\n- Compliance burden: the directive requires physical removal of the part and use of one of two technical inspection methods, which implies labour time, specialised inspection equipment or service, and aircraft out-of-service time while removal/inspection occur. (See: \"Requirement\".)\n- Implementation risk and discretion: the directive prescribes the inspection methods but does not set repair or replacement criteria or allowance for alternative methods; any judgement about whether detected cracking requires repair or replacement is not specified in the text provided. That leaves implementers to follow existing maintenance and repair standards to address findings. (See: \"Requirement\".)\n\nTrade-offs and potential operational effects\n\n- The directive increases routine maintenance actions for affected brackets and thereby raises maintenance costs and aircraft downtime for operators of affected aeroplanes. The inspection interval (600 hours) sets a recurring scheduling obligation. (See: \"Compliance\".)\n- Benefits claimed by the directive (explicitly in the text): the inspections target cracks initiating at bolt holes on the specified bracket. The mechanical effect is detection of such cracks before they progress; the directive itself does not state follow-up repairs, so subsequent actions will follow existing maintenance rules and operator procedures. (See: \"Requirement\".)\n\nSource citations\n\n- Applicability: \"All models with nose landing gear actuator brackets, P/N 65-16370-1, which have accumulated 1000 hours total time in service.\" (Applicability)\n- Requirement: \"Remove Bracket P/N 65-16370-1 and inspect for cracks initiating at all bolt holes using a fluorescent dye penetrant or eddy current technique.\" (Requirement)\n- Compliance: \"At intervals not exceeding 600 hours time in service.\" (Compliance)"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, standalone airworthiness directive with a single, specific safety purpose. It has not expanded beyond its original intent — to mandate inspection of a known failure-prone component on a specific aircraft type."},"complexity_factors":["Extremely short document (under 200 words)","Only 1 defined term implicitly referenced (P/N = Part Number)","No cross-references to other legislation or regulations","Simple conditional logic: single applicability criterion (1000 hours time in service)","Single compliance action with clear interval (600 hours)","No exceptions, exemptions, or nested conditions","Straightforward technical requirement with two alternative inspection methods"],"plain_english_summary":"**What this is:** This is an Airworthiness Directive (AD) — essentially a mandatory safety notice issued by Australia's Civil Aviation Safety Authority (CASA). Think of it like a compulsory recall notice, but for aircraft parts rather than cars.\n\n**What it does:** It orders owners and operators of Boeing 727 aeroplanes to inspect a specific part — the \"nose landing gear actuating bracket\" (part number 65-16370-1) — for cracks. This bracket helps control the front landing gear that steers the plane on the ground.\n\n**Who must comply:** Anyone operating a Boeing 727 that has this specific bracket installed AND has flown more than 1,000 hours total.\n\n**What must be done:**\n- **Remove** the bracket from the aircraft\n- **Inspect it** for cracks starting at any bolt holes using either:\n  - Fluorescent dye penetrant (a special liquid that seeps into cracks and glows under UV light), or\n  - Eddy current testing (using electromagnetic fields to detect surface cracks)\n\n**How often:** This inspection must be repeated every 600 flight hours.\n\n**Why it matters:** Cracks in landing gear components can lead to catastrophic failure during takeoff or landing. This AD prevents accidents by catching fatigue damage before it becomes dangerous."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection","history":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection/history","analysis":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection/analysis","conflicts":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection/conflicts","importantCases":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection/important-cases","documents":"/api/acts/ad-b727-32-nose-landing-gear-actuating-bracket-inspection/documents"}}