{"id":"F2007L02564","name":"AD/HU 369/118 - Landing Gear Fairing Support Assembly","slug":"ad-hu-369-118-landing-gear-fairing-support-assembly","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":68251,"registerId":"commonwealth-F2007L02564-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"McDonnell Douglas (Hughes) and Kawasaki ","sectionType":"division","heading":"McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters","content":"### McDonnell Douglas (Hughes) and Kawasaki 369 Series Helicopters\n\n| AD/HU 369/118 | Landing Gear Fairing Support Assembly | 9/2007 |\n| ------------- | ------------------------------------- | ------ |\n\n| Applicability: | Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, and 500N helicopters, with any of the components in Assembly/Components Affected list of MD Helicopters Service Bulletin SB369H-244, SB369E-094, SB500N-022,SB369D-200, and SB369F-078, as applicable, installed; excluding any helicopter with Aerometals strut part number 369XH6001-41, -42, -51, or -52, installed in accordance with Supplemental Type Certificate No. SR00981LA. |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Remove all landing gear fairings (fairings) and inspect each landing gear fairing support assembly (support assembly) to determine the number and location of the rivets attaching the support assembly to the landing gear strut assembly (strut assembly), and if necessary, accomplish rework instructions; in accordance with the Accomplishment Instructions of MD Helicopters Service BulletinSB369H-244, SB369E-094, SB500N-022, SB369D-200, and SB369F-078, as applicable.If any strut assembly is found cracked, before further flight, replace the cracked strut assembly with a serviceable strut assembly.2. For any strut assembly that has a third rivet hole, remove the fairing inspection button plug and clean and inspect the area in and around the rivet hole for cracks using a bright light and a 10x or higher magnifying glass.If, during any inspection, a forward strut assembly or aft strut assembly is found cracked, before further flight, replace the cracked strut assembly with a serviceable strut assembly.Note 1: Installing a strut assembly that has only two rivet holes is terminating action for the requirements of this Directive.Note 2: FAA AD 2007-12-23 Amdt 39-15101 refers. |\n| Compliance: | 1. Unless already accomplished, within 4 months after 30 August 2007.2. At intervals not to exceed 100 hours time in service or during each annual inspection, whichever occurs first. |\n| | This Airworthiness Directive becomes effective on 30 August 2007. |\n\n| Background: | The FAA received five reports of landing gear strut failures. Undetected cracking could result in failure of a strut and subsequent loss of control of the helicopter during landing. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n17 July 2007","sortOrder":0},{"sectionNumber":"AD/HU 369/118","sectionType":"part","heading":"AD/HU 369/118","content":"## AD/HU 369/118","sortOrder":1},{"sectionNumber":"Landing Gear Fairing Support Assembly","sectionType":"part","heading":"Landing Gear Fairing Support Assembly","content":"## Landing Gear Fairing Support Assembly","sortOrder":2},{"sectionNumber":"9/2007","sectionType":"part","heading":"9/2007","content":"## 9/2007","sortOrder":3}],"analysis":{"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with a focused, narrow scope: addressing a specific mechanical defect in landing gear strut assemblies on specific helicopter models. The scope remains tightly constrained to the safety issue identified (five reported strut failures) and does not expand beyond the original safety purpose."},"complexity_factors":["Multiple model variants listed in applicability (11 different helicopter models)","Cross-references to five different service bulletins (SB369H-244, SB369E-094, SB500N-022, SB369D-200, SB369F-078)","Specific exclusion based on part numbers and Supplemental Type Certificate (SR00981LA)","Two-tier compliance structure (initial deadline + recurring intervals)","Conditional logic: 'if cracked, replace before further flight'","Reference to foreign aviation authority directive (FAA AD 2007-12-23)","Technical terminology requiring aviation engineering knowledge (strut assemblies, fairings, rivet holes, terminating action)"],"plain_english_summary":"Owners/operators of specific McDonnell Douglas (Hughes) and Kawasaki helicopters must remove landing‑gear fairings to inspect how fairing support brackets attach to struts, perform bright‑light/magnified inspections for cracks, and replace any cracked strut assemblies before flight. Initial inspection was required within 4 months of Aug 30, 2007, then every 100 flight hours or annually. \n\nIt affects Model 369 series and 500N helicopters (with certain Aerometals‑modified struts excluded) after reports of strut failures that could cause loss of control."},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":false,"description":"Scope aligns with the directive's original safety focus: inspect landing-gear fairing support assemblies on listed MD/Kawasaki 369 and 500N models, excluding helicopters fitted with specified Aerometals struts under STC SR00981LA (Applicability). The directive addresses five FAA-reported strut failures (Background) and prescribes inspection, rework or replacement measures and recurring checks (Requirement / Compliance). There is no expansion beyond those targeted aircraft, components and remedial steps."},"complexity_factors":["Multi-model applicability with cross-references to several MD Helicopters Service Bulletins (SB369H-244, SB369E-094, SB500N-022, SB369D-200, SB369F-078) (Applicability / Requirement)","Specific exclusion for helicopters with Aerometals struts installed under STC SR00981LA, requiring operators to check STC status (Applicability)","Two-step inspection regime: initial removal of fairings and rivet-count inspection, plus targeted inspection (remove inspection button plug, bright light and 10x magnifier) if a third rivet hole exists (Requirement)","Mandatory corrective actions: rework as per service bulletin or immediate replacement of any cracked strut before further flight (Requirement — replace before flight)","Mixed timelines: initial compliance deadline (within 4 months after 30 August 2007) plus recurrent inspections at intervals not to exceed 100 hours TIS or at each annual inspection (Compliance)","Terminating action available (installing a strut with only two rivet holes) which affects parts procurement and configuration decisions (Note 1)","Operational impact on serviceability: potential grounding until replacement if cracking found, and labour involved in fairing removal/inspection/rework","Reference to FAA AD 2007-12-23 creates cross-jurisdictional compliance linkage (Requirement / Note 2)"],"plain_english_summary":"Requires removal of landing-gear fairings and inspection of the fairing support assembly rivet configuration on specified MD/Kawasaki 369 and 500N series helicopters, with rework or strut replacement as needed; excludes helicopters fitted with certain Aerometals struts under STC SR00981LA. The AD responds to five FAA reports of strut failures and aims to detect cracking that could lead to strut failure; it imposes immediate and recurring inspection work and replacement-before-flight obligations that operators must carry out."}},"importantCases":[],"_links":{"self":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly","history":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly/history","analysis":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly/analysis","conflicts":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly/conflicts","importantCases":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly/important-cases","documents":"/api/acts/ad-hu-369-118-landing-gear-fairing-support-assembly/documents"}}