{"id":12550,"date":"2026-03-16T03:36:54","date_gmt":"2026-03-16T03:36:54","guid":{"rendered":"https:\/\/hlh-js.com\/?p=12550"},"modified":"2026-03-16T03:49:52","modified_gmt":"2026-03-16T03:49:52","slug":"ceramic-media-for-aerospace","status":"publish","type":"post","link":"https:\/\/hlh-js.com\/ru\/resource\/\u0431\u043b\u043e\u0433\/ceramic-media-for-aerospace\/","title":{"rendered":"Ceramic Media for Aerospace"},"content":{"rendered":"<!-- ============================================================\n     CERAMIC MEDIA FOR AEROSPACE \u2013 CLUSTER PAGE #12\n     Company: Jiangsu Henglihong Technology Co., Ltd.\n     Target: WordPress Gutenberg \u2192 Custom HTML block\n     SEO Target Keyword: Ceramic Media for Aerospace\n     Secondary KWs: aerospace deburring media, vibratory finishing aerospace,\n                    ceramic media titanium finishing, edge radiusing aerospace parts\n     Pillar Page: https:\/\/hlh-js.com\/resource\/blog\/ceramic-media\/\n     Word Count: ~3,200 words\n     Last updated: 2026-03\n     ============================================================ -->\n\n<style>\n\/* \u2500\u2500 Reset & Base \u2500\u2500 *\/\n.hlh-pillar *,\n.hlh-pillar *::before,\n.hlh-pillar *::after { box-sizing: border-box; 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color: #1a3a5c; text-decoration: underline; text-underline-offset: 3px; }\n.hlh-inline-link:hover { color: #e8610a; }\n\n\/* \u2500\u2500 FAQ \u2500\u2500 *\/\n.hlh-faq { margin: 24px 0; }\n.hlh-faq-item { border: 1px solid #d8e4f0; border-radius: 8px; margin-bottom: 12px; overflow: hidden; }\n.hlh-faq-q { background: #f4f7fb; padding: 15px 20px; font-family: 'Arial', sans-serif; font-size: 16px; font-weight: 700; color: #0d1f3c; border-left: 4px solid #e8610a; }\n.hlh-faq-a { padding: 15px 20px; font-size: 15px; line-height: 1.7; color: #2c2c2c; }\n.hlh-faq-a p { margin: 0 0 10px; }\n.hlh-faq-a p:last-child { margin-bottom: 0; }\n\n\/* \u2500\u2500 CTA \u2500\u2500 *\/\n.hlh-cta {\n  background: linear-gradient(135deg, #e8610a 0%, #c24d06 100%);\n  border-radius: 12px; padding: 44px 40px; margin: 52px 0 28px;\n  text-align: center; position: relative; overflow: hidden;\n}\n.hlh-cta::before { content: ''; position: absolute; top: -50px; right: -50px; width: 200px; height: 200px; border-radius: 50%; background: rgba(255,255,255,0.07); }\n.hlh-cta h2 { font-family: 'Arial Black', sans-serif; font-size: clamp(20px, 3vw, 26px); color: #ffffff; border: none; margin: 0 0 12px; padding: 0; }\n.hlh-cta p { font-family: 'Arial', sans-serif; font-size: 16px; color: rgba(255,255,255,0.88); max-width: 500px; margin: 0 auto 24px; }\n.hlh-cta-btn {\n  display: inline-block; background: #ffffff; color: #c24d06 !important;\n  font-family: 'Arial Black', sans-serif; font-size: 15px; font-weight: 900;\n  text-decoration: none !important; padding: 14px 34px; border-radius: 6px;\n  letter-spacing: 0.03em; transition: transform 0.15s, box-shadow 0.15s;\n  box-shadow: 0 4px 16px rgba(0,0,0,0.2);\n}\n.hlh-cta-btn:hover { transform: translateY(-2px); box-shadow: 0 8px 24px rgba(0,0,0,0.25); }\n\n\/* \u2500\u2500 Anchor \u2500\u2500 *\/\n.hlh-anchor { scroll-margin-top: 80px; }\n\n\/* \u2500\u2500 Responsive \u2500\u2500 *\/\n@media (max-width: 600px) {\n  .hlh-hero { padding: 36px 24px; }\n  .hlh-toc  { padding: 20px 20px; }\n  .hlh-cta  { padding: 32px 22px; }\n  .hlh-compliance-box { padding: 22px 20px; }\n  .hlh-fatigue-label { width: 130px; font-size: 12px; }\n}\n<\/style>\n\n<div class=\"hlh-pillar\" itemscope itemtype=\"https:\/\/schema.org\/Article\">\n\n  \n  <!-- Hero -->\n  <div class=\"hlh-hero\">\n    <h1 itemprop=\"headline\">Ceramic Media for Aerospace: Deburring, Edge Radiusing &amp; Fatigue Life Improvement for Titanium, Nickel Superalloy, and Aluminum Flight-Critical Components<\/h1>\n    <p class=\"hlh-hero-sub\">How ceramic mass finishing media is used in aerospace manufacturing to meet the edge condition, surface roughness, and fatigue life requirements of flight-critical structural and engine components \u2014 with AS9100-compatible process documentation guidance and material-specific specifications.<\/p>\n    <div class=\"hlh-hero-meta\">\n      <span>&#128197; <strong>Updated March 2026<\/strong><\/span>\n      <span>&#9201; <strong>15 min<\/strong> read<\/span>\n      <span>&#127981; By <strong>Jiangsu Henglihong Technology<\/strong><\/span>\n    <\/div>\n  <\/div>\n\n  <!-- TOC -->\n  <nav class=\"hlh-toc\" aria-label=\"Table of Contents\">\n    <div class=\"hlh-toc-title\">&#9776; Table of Contents<\/div>\n    <ol>\n      <li><a href=\"#why-aerospace\">Why Edge Condition Is a Flight-Safety Issue<\/a><\/li>\n      <li><a href=\"#materials\">Aerospace Material Challenges: Ti, Inconel, Aluminum, Steel<\/a><\/li>\n      <li><a href=\"#fatigue\">Edge Radiusing and Fatigue Life Improvement<\/a><\/li>\n      <li><a href=\"#component-applications\">Ceramic Media by Aerospace Component<\/a>\n        <ol>\n          <li><a href=\"#turbine-blades\">Turbine Blades &amp; Vanes<\/a><\/li>\n          <li><a href=\"#structural-fasteners\">Structural Fasteners<\/a><\/li>\n          <li><a href=\"#landing-gear\">Landing Gear Components<\/a><\/li>\n          <li><a href=\"#airframe-structures\">Airframe Structural Components<\/a><\/li>\n          <li><a href=\"#engine-discs\">Engine Discs &amp; Shafts<\/a><\/li>\n        <\/ol>\n      <\/li>\n      <li><a href=\"#process-specs\">Aerospace Process Specifications<\/a><\/li>\n      <li><a href=\"#as9100\">AS9100 Compliance and Process Validation<\/a><\/li>\n      <li><a href=\"#faq\">\u0427\u0430\u0441\u0442\u043e \u0437\u0430\u0434\u0430\u0432\u0430\u0435\u043c\u044b\u0435 \u0432\u043e\u043f\u0440\u043e\u0441\u044b<\/a><\/li>\n    <\/ol>\n  <\/nav>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 1 \u2014 WHY AEROSPACE\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"why-aerospace\" class=\"hlh-anchor\">1. Why Edge Condition Is a Flight-Safety Issue<\/h2>\n\n  <p>\n    In most industries, deburring is a quality and assembly concern \u2014 a burr causes a fit problem, a cleanliness issue, or a minor injury risk. In aerospace structural and propulsion components, the stakes are categorically higher: a sharp edge or residual burr on a flight-critical component is a <strong>fatigue crack initiation site<\/strong>. Under the cyclic stresses of flight \u2014 repeated pressurization cycles, vibration, thermal cycling \u2014 a crack that initiates at a sharp notch will propagate under fatigue loading at a rate orders of magnitude faster than it would from a radiused edge of the same geometry.\n  <\/p>\n\n  <p>\n    The relationship between edge condition and fatigue life in high-strength aerospace alloys is well-established in aerospace fracture mechanics. A sharp edge with a root radius of 0.01 mm has a stress concentration factor (Kt) of 5\u201310 or higher depending on geometry \u2014 meaning the local stress at the notch tip is 5\u201310 times the nominal applied stress. For titanium alloy components operating at 60\u201370% of their ultimate tensile strength, this amplification brings the local stress into the crack initiation range within a small number of fatigue cycles. A controlled edge radius of 0.05\u20130.2 mm, produced by ceramic mass finishing, reduces Kt to 1.5\u20133.0 \u2014 dramatically extending crack initiation life.\n  <\/p>\n\n  <div class=\"hlh-callout hlh-callout-warn\">\n    <div class=\"hlh-callout-icon\">&#9992;&#65039;<\/div>\n    <p><strong>Regulatory context:<\/strong> FAA Advisory Circular AC 43.13-1B and EASA guidance material both reference edge condition and surface preparation requirements for fatigue-critical repairs and manufacturing operations. Boeing and Airbus process specifications (BPS and AIMS series respectively) include explicit edge radius requirements and surface finish specifications that ceramic mass finishing processes must meet and document. Failure to demonstrate process control to these specifications disqualifies a supplier from providing parts for certified aircraft programs.<\/p>\n  <\/div>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 2 \u2014 MATERIALS\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"materials\" class=\"hlh-anchor\">2. Aerospace Material Challenges: Ti, Inconel, Aluminum, Steel<\/h2>\n\n  <p>\n    Aerospace manufacturing uses a narrower but more demanding range of materials than any other industry. Each principal aerospace alloy family presents specific challenges for ceramic mass finishing that require tailored media specifications.\n  <\/p>\n\n  <div class=\"hlh-mat-challenge\">\n    <div class=\"hlh-mat-challenge-title\">&#128301; Aerospace Material Properties &amp; Ceramic Media Requirements<\/div>\n    <div class=\"hlh-mat-challenge-grid\">\n\n      <div class=\"hlh-mat-cell\">\n        <div class=\"hlh-mat-cell-name\">Titanium (Ti-6Al-4V, Ti-6Al-2Sn-4Zr-2Mo)<\/div>\n        <div class=\"hlh-mat-cell-props\">UTS: 900\u20131,200 MPa. Low thermal conductivity (7 W\/m\u00b7K). Work-hardens moderately. Chemically reactive with oxygen at &gt;300\u00b0C.<\/div>\n        <div class=\"hlh-mat-cell-media\">&#8594; CBF required; neutral high-lubricity compound; no heat tinting permitted; hard-bond alumina<\/div>\n      <\/div>\n\n      <div class=\"hlh-mat-cell\">\n        <div class=\"hlh-mat-cell-name\">Nickel Superalloy (Inconel 718, Ren\u00e9 88, Waspaloy)<\/div>\n        <div class=\"hlh-mat-cell-props\">UTS: 1,200\u20131,500 MPa. Very high work-hardening rate. Abrasive to tooling. Excellent oxidation resistance to 700\u00b0C+.<\/div>\n        <div class=\"hlh-mat-cell-media\">&#8594; CBF with coarse-medium alumina; hard bond; low compound lubricity (for grain engagement); short cycles<\/div>\n      <\/div>\n\n      <div class=\"hlh-mat-cell\">\n        <div class=\"hlh-mat-cell-name\">Aluminum (7075-T6, 2024-T3, 6061-T6)<\/div>\n        <div class=\"hlh-mat-cell-props\">UTS: 480\u2013580 MPa (7075). Soft \u2014 susceptible to imprinting. Iron contamination causes galvanic staining. Anodize-sensitive surface.<\/div>\n        <div class=\"hlh-mat-cell-media\">&#8594; Non-ferrous-safe ceramic; mildly acidic compound; moderate amplitude; strict dimensional control<\/div>\n      <\/div>\n\n      <div class=\"hlh-mat-cell\">\n        <div class=\"hlh-mat-cell-name\">High-Strength Steel (300M, 4340, 15-5 PH, 17-4 PH)<\/div>\n        <div class=\"hlh-mat-cell-props\">UTS: 1,400\u20132,000 MPa. Hydrogen embrittlement risk (avoid acidic compounds). Hard chrome plating often follows \u2014 strict Ra requirement.<\/div>\n        <div class=\"hlh-mat-cell-media\">&#8594; Alkaline compound only; medium alumina; controlled Ra for plating adhesion; verify Kt at critical features<\/div>\n      <\/div>\n\n    <\/div>\n  <\/div>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 3 \u2014 FATIGUE LIFE\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"fatigue\" class=\"hlh-anchor\">3. Edge Radiusing and Fatigue Life Improvement<\/h2>\n\n  <p>\n    The fatigue life improvement from ceramic mass finishing in aerospace applications is not merely a quality specification checkbox \u2014 it is a quantifiable, engineering-substantiated benefit that has been measured and documented in published fatigue test programs for both structural alloys and superalloys. Understanding the magnitude of this improvement, and the process conditions that reliably produce it, is essential for aerospace manufacturing engineers specifying ceramic finishing processes.\n  <\/p>\n\n  <h3>Relative Fatigue Life by Edge Condition (Normalized to Baseline)<\/h3>\n  <div class=\"hlh-fatigue-wrap\">\n    <div class=\"hlh-fatigue-row\">\n      <div class=\"hlh-fatigue-label\">As-machined (sharp edge)<\/div>\n      <div class=\"hlh-fatigue-track\">\n        <div class=\"hlh-fatigue-fill hlh-fatigue-fill-base\" style=\"width:30%\">1.0\u00d7 (baseline)<\/div>\n      <\/div>\n    <\/div>\n    <div class=\"hlh-fatigue-row\">\n      <div class=\"hlh-fatigue-label\">Deburred, no edge radius<\/div>\n      <div class=\"hlh-fatigue-track\">\n        <div class=\"hlh-fatigue-fill hlh-fatigue-fill-deburred\" style=\"width:50%\">1.5 \u2013 2.0\u00d7<\/div>\n      <\/div>\n    <\/div>\n    <div class=\"hlh-fatigue-row\">\n      <div class=\"hlh-fatigue-label\">Ceramic edge radius 0.05\u20130.15 mm<\/div>\n      <div class=\"hlh-fatigue-track\">\n        <div class=\"hlh-fatigue-fill hlh-fatigue-fill-radius\" style=\"width:70%\">2.5 \u2013 4.0\u00d7<\/div>\n      <\/div>\n    <\/div>\n    <div class=\"hlh-fatigue-row\">\n      <div class=\"hlh-fatigue-label\">Ceramic radius + porcelain polish<\/div>\n      <div class=\"hlh-fatigue-track\">\n        <div class=\"hlh-fatigue-fill hlh-fatigue-fill-radius\" style=\"width:85%\">3.5 \u2013 5.5\u00d7<\/div>\n      <\/div>\n    <\/div>\n    <div class=\"hlh-fatigue-row\">\n      <div class=\"hlh-fatigue-label\">Ceramic radius + shot peen (combined)<\/div>\n      <div class=\"hlh-fatigue-track\">\n        <div class=\"hlh-fatigue-fill hlh-fatigue-fill-radius\" style=\"width:100%\">5.0 \u2013 8.0\u00d7<\/div>\n      <\/div>\n    <\/div>\n  <\/div>\n  <p style=\"font-family:'Arial',sans-serif; font-size:13px; color:#6a7a8a; margin-top:-12px; margin-bottom:24px;\">\n    &#9432; Fatigue life multipliers are indicative ranges compiled from published aerospace fatigue test literature for titanium and nickel superalloy specimens. Actual values vary by alloy, geometry, and stress ratio. Validate for your specific application.\n  <\/p>\n\n  <p>\n    The most important insight from the fatigue data is the <strong>non-linear benefit of combining edge radiusing with controlled surface roughness reduction<\/strong>. Ceramic deburring alone (removing the burr but leaving a sharp edge) provides a 1.5\u20132\u00d7 fatigue life improvement by eliminating the stress concentration of the burr. Controlled edge radiusing adds another 1.5\u20132\u00d7 improvement by reducing the notch stress concentration at the edge itself. A final porcelain polishing stage reduces Ra and eliminates micro-notch features from the abrasive ceramic stage, adding another incremental improvement. The combined three-stage process can deliver 3.5\u20135.5\u00d7 the fatigue life of an as-machined part at very modest total cycle time cost.\n  <\/p>\n\n  <p>\n    When ceramic mass finishing is combined with downstream shot peening \u2014 the aerospace industry&#8217;s primary fatigue enhancement treatment \u2014 the interaction is synergistic: ceramic finishing establishes the clean, radiused surface condition that maximizes the effectiveness of shot peening by ensuring the compressive stress field introduced by peening extends from a well-defined, reproducible surface geometry rather than from a random burr profile.\n  <\/p>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 4 \u2014 COMPONENT APPLICATIONS\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"component-applications\" class=\"hlh-anchor\">4. Ceramic Media by Aerospace Component<\/h2>\n\n  <div class=\"hlh-aero-grid\">\n\n    <div class=\"hlh-aero-card critical\" id=\"turbine-blades\">\n      <span class=\"hlh-aero-icon\">&#128293;<\/span>\n      <div class=\"hlh-aero-name\">Turbine Blades &amp; Vanes<\/div>\n      <div class=\"hlh-aero-material\">Nickel Superalloy (Inconel 718, Ren\u00e9 88)<\/div>\n      <div class=\"hlh-aero-body\">\n        Complex fir-tree root form requires diagonal cylinder or cone to access slot flanks. Blade tip and leading\/trailing edges need precise radius control \u2014 typically 0.05\u20130.12 mm. Cooling holes (0.5\u20131.5 mm diameter) require media stops or oversized media to prevent entry. Three-stage process: heavy CBF deburr \u2192 fine CBF edge radius \u2192 porcelain polish.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: Diag. cylinder 6\u20138 mm (root) + fine sphere 5 mm (LE\/TE) | Machine: CBF | No heat tinting permitted | Post-process: FPI for crack inspection<\/div>\n    <\/div>\n\n    <div class=\"hlh-aero-card\" id=\"structural-fasteners\">\n      <span class=\"hlh-aero-icon\">&#128295;<\/span>\n      <div class=\"hlh-aero-name\">Structural Fasteners (Bolts, Pins, Studs)<\/div>\n      <div class=\"hlh-aero-material\">Ti-6Al-4V \/ A286 \/ 300M Steel<\/div>\n      <div class=\"hlh-aero-body\">\n        Thread root radius and under-head radius are the two highest-fatigue-risk features. Cone media sized to enter thread helix without lodging achieves controlled root radius. CBF preferred for consistent root radius uniformity across 100% of parts. Steel satellite burnishing of shank provides compressive stress for tension-tension fatigue.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: Cone \u2192 steel satellite | Machine: CBF + vibratory burnish | Verify: Thread gauge 100% after each stage<\/div>\n    <\/div>\n\n    <div class=\"hlh-aero-card critical\" id=\"landing-gear\">\n      <span class=\"hlh-aero-icon\">&#128587;&#65039;<\/span>\n      <div class=\"hlh-aero-name\">Landing Gear Main Fittings &amp; Actuators<\/div>\n      <div class=\"hlh-aero-material\">300M, 4340, 15-5 PH Steel<\/div>\n      <div class=\"hlh-aero-body\">\n        Highest-stressed structural components in the airframe. Lug bores, pin holes, and fillet radii at section transitions are primary fatigue initiation sites. <strong>Alkaline compound mandatory<\/strong> \u2014 acidic compounds cause hydrogen embrittlement in ultra-high-strength steel. Edge radius specification is tight: 0.05\u20130.20 mm with documented CMM verification. Shot peening follows as a mandatory next step.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: Triangle\/cylinder, 15\u201320 mm \u2192 fine cylinder \u2192 porcelain | Compound: pH 8.5\u201310 strictly | Post: Shot peen + hard chrome<\/div>\n    <\/div>\n\n    <div class=\"hlh-aero-card\" id=\"airframe-structures\">\n      <span class=\"hlh-aero-icon\">&#9992;&#65039;<\/span>\n      <div class=\"hlh-aero-name\">Airframe Structural Components (Ribs, Spars, Frames)<\/div>\n      <div class=\"hlh-aero-material\">7075-T6, 2024-T3 Aluminum<\/div>\n      <div class=\"hlh-aero-body\">\n        Large-format machined aluminum structures with hundreds of hole edges, cutout perimeters, and pocket floors requiring simultaneous deburring. Non-ferrous-safe ceramic prevents galvanic staining before anodizing. Tub vibratory machines handle long, flat structural components. Critical: confirm media cannot enter rivet holes or interference-fit bushing holes.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: NF-safe triangle\/cylinder, 12\u201320 mm | Compound: pH 5.5\u20136.5 | Machine: Tub vibratory | Pre-anodize surface prep<\/div>\n    <\/div>\n\n    <div class=\"hlh-aero-card critical\" id=\"engine-discs\">\n      <span class=\"hlh-aero-icon\">&#9898;<\/span>\n      <div class=\"hlh-aero-name\">Compressor &amp; Turbine Discs<\/div>\n      <div class=\"hlh-aero-material\">Titanium \/ Nickel Superalloy<\/div>\n      <div class=\"hlh-aero-body\">\n        Disc bore, rabbet fits, and blade attachment slots (dovetail or fir-tree) are life-limiting features. Edge radius control at slot flanks directly determines the disc&#8217;s low-cycle fatigue (LCF) life \u2014 a documented factor in several historic engine disc failure events. Three-stage process with written first-article approval required before production. All process records retained for part life.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: Diagonal cylinder \u2192 fine cone \u2192 porcelain | Machine: CBF (Ti\/Ni) | Full dimensional CMM + FPI after each stage<\/div>\n    <\/div>\n\n    <div class=\"hlh-aero-card\">\n      <span class=\"hlh-aero-icon\">&#9881;&#65039;<\/span>\n      <div class=\"hlh-aero-name\">Gearbox Components (Accessory Drive)<\/div>\n      <div class=\"hlh-aero-material\">Case-hardened Steel \/ M50 Bearing Steel<\/div>\n      <div class=\"hlh-aero-body\">\n        Aircraft accessory drive gearboxes operate at high speed with minimal lubrication margin \u2014 NVH performance and surface quality directly affect gearbox efficiency and oil temperature. Two-stage ceramic + steel burnishing process improves gear tooth surface quality and introduces compressive stress. Cleanliness specification similar to automotive valve body standard.\n      <\/div>\n      <div class=\"hlh-aero-spec\">Media: Cone \u2192 steel satellite | Machine: CBF + vibratory | Cleanliness: per OEM spec after process<\/div>\n    <\/div>\n\n  <\/div>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 5 \u2014 PROCESS SPECS\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"process-specs\" class=\"hlh-anchor\">5. Aerospace Process Specifications<\/h2>\n\n  <p>\n    The following process parameters represent validated starting points for the principal aerospace component categories. All aerospace finishing processes must be validated by a formal first-article trial with dimensional and surface inspection before production release, and process records must be maintained for the full service life of the component.\n  <\/p>\n\n  <div class=\"hlh-table-wrap\">\n    <table class=\"hlh-table\" role=\"table\" aria-label=\"Aerospace ceramic media process specifications\">\n      <thead>\n        <tr>\n          <th>Component \/ Material<\/th>\n          <th>Stage 1 Media<\/th>\n          <th>Stage 2 Media<\/th>\n          <th>Stage 3 Media<\/th>\n          <th>Machine<\/th>\n          <th>Compound pH<\/th>\n          <th>Critical Check<\/th>\n        <\/tr>\n      <\/thead>\n      <tbody>\n        <tr>\n          <td>Turbine blade \/ Inconel<\/td>\n          <td>Diag. cylinder 6\u20138 mm, coarse-med<\/td>\n          <td>Fine cone\/sphere 5 mm<\/td>\n          <td>Porcelain sphere 5 mm<\/td>\n          <td>CBF all stages<\/td>\n          <td>7.0 \u2013 8.5<\/td>\n          <td>No heat tinting; cooling hole media stop; FPI<\/td>\n        <\/tr>\n        <tr>\n          <td>Ti-6Al-4V structural fastener<\/td>\n          <td>Cone 8\u201310 mm, med-hard bond<\/td>\n          <td>Steel satellite<\/td>\n          <td>\u2014<\/td>\n          <td>CBF + vibratory<\/td>\n          <td>6.8 \u2013 7.5<\/td>\n          <td>Thread go\/no-go; surface: no heat tint<\/td>\n        <\/tr>\n        <tr>\n          <td>Landing gear \/ 300M steel<\/td>\n          <td>Triangle 15\u201320 mm, medium<\/td>\n          <td>Fine cylinder 10\u201312 mm<\/td>\n          <td>Porcelain sphere<\/td>\n          <td>Tub vibratory<\/td>\n          <td>8.5 \u2013 10.0 (strict)<\/td>\n          <td>No acidic compound (H embrittlement)<\/td>\n        <\/tr>\n        <tr>\n          <td>7075 aluminum airframe<\/td>\n          <td>NF-safe triangle 12\u201315 mm, med<\/td>\n          <td>Fine NF-safe cylinder<\/td>\n          <td>\u2014<\/td>\n          <td>Tub vibratory<\/td>\n          <td>5.5 \u2013 6.5<\/td>\n          <td>No Fe contamination; pre-anodize verify<\/td>\n        <\/tr>\n        <tr>\n          <td>Compressor disc \/ Ti alloy<\/td>\n          <td>Diag. cylinder 8 mm, hard bond<\/td>\n          <td>Fine cone 6 mm<\/td>\n          <td>Porcelain sphere 5 mm<\/td>\n          <td>CBF all stages<\/td>\n          <td>6.8 \u2013 7.5<\/td>\n          <td>CMM at each stage; FPI final; records retained full life<\/td>\n        <\/tr>\n        <tr>\n          <td>Nickel superalloy disc slots<\/td>\n          <td>Diag. cylinder 6 mm, coarse<\/td>\n          <td>Cone 5 mm, med-hard<\/td>\n          <td>Porcelain<\/td>\n          <td>CBF<\/td>\n          <td>7.0 \u2013 9.0<\/td>\n          <td>Slot width dimension after each stage; no surface smearing<\/td>\n        <\/tr>\n        <tr>\n          <td>300M landing gear actuator<\/td>\n          <td>Cylinder 12 mm, medium<\/td>\n          <td>Fine cylinder \u2192 porcelain<\/td>\n          <td>\u2014<\/td>\n          <td>Round bowl vibratory<\/td>\n          <td>8.5 \u2013 10.0<\/td>\n          <td>Ra \u2264 0.4 \u00b5m for hard chrome; no acidic exposure<\/td>\n        <\/tr>\n        <tr>\n          <td>Aircraft structural fastener (Al)<\/td>\n          <td>NF-safe cone 8 mm, fine<\/td>\n          <td>Steel satellite (shank burnish)<\/td>\n          <td>\u2014<\/td>\n          <td>CBF<\/td>\n          <td>6.0 \u2013 7.0<\/td>\n          <td>Thread gauge; no Fe staining before anodize<\/td>\n        <\/tr>\n      <\/tbody>\n    <\/table>\n  <\/div>\n\n  <!-- \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\n       SECTION 6 \u2014 AS9100\n  \u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550\u2550 -->\n  <h2 id=\"as9100\" class=\"hlh-anchor\">6. AS9100 Compliance and Process Validation<\/h2>\n\n  <div class=\"hlh-compliance-box\">\n    <div class=\"hlh-compliance-title\">&#128737;&#65039; AS9100 Rev D \u2014 Special Process Requirements for Ceramic Finishing<\/div>\n    <p>\n      Under AS9100 Rev D (and its predecessor revisions), ceramic mass finishing is classified as a <strong>special process<\/strong> \u2014 a manufacturing process whose output quality cannot be fully verified by subsequent inspection alone, requiring that the process itself be controlled, validated, and monitored. This classification imposes specific requirements on aerospace suppliers that go beyond standard process documentation practices.\n    <\/p>\n    <p>\n      <strong>Process validation (first-article):<\/strong> Before a ceramic finishing process can be used in production on a flight-critical part, a formal First Article Inspection (FAI) must be completed. The FAI includes dimensional verification of all critical features (edge radius at specified locations, Ra on specified surfaces), surface integrity verification (dye penetrant inspection for titanium and nickel parts, visual inspection for heat tinting), and a documented comparison of all process parameters against the process specification.\n    <\/p>\n    <p>\n      <strong>Process specification (written procedure):<\/strong> A written process specification must define every parameter that controls the process output: media lot number and specification, machine amplitude and frequency settings, compound type and pH range, media-to-parts ratio, cycle time, and inspection method with accept\/reject criteria. Any change to a specified parameter requires a formal engineering change notice and re-validation before production resumes.\n    <\/p>\n    <p>\n      <strong>Record retention:<\/strong> For life-limited parts (rotating engine components, primary structural members), process records must be retained for the operational service life of the part \u2014 which may be 30\u201340 years for commercial aircraft primary structure. Media lot traceability, machine calibration records, and inspection data must all be maintained and retrievable for this duration.\n    <\/p>\n  <\/div>\n\n  <h3>Key Differences Between Aerospace and General Industry Ceramic Finishing<\/h3>\n\n  <div class=\"hlh-table-wrap\">\n    <table class=\"hlh-table\" role=\"table\" aria-label=\"Aerospace vs general industry ceramic finishing differences\">\n      <thead>\n        <tr>\n          <th>Aspect<\/th>\n          <th>General Industry Practice<\/th>\n          <th>Aerospace (AS9100) Requirement<\/th>\n        <\/tr>\n      <\/thead>\n      <tbody>\n        <tr>\n          <td>Process documentation<\/td>\n          <td>Internal work instruction; informal parameter recording<\/td>\n          <td>Formal approved process specification; change control; revision history<\/td>\n        <\/tr>\n        <tr>\n          <td>First-article validation<\/td>\n          <td>Trial run with visual or profilometer check<\/td>\n          <td>Formal FAI with dimensional report, surface inspection, and customer approval for flight-critical parts<\/td>\n        <\/tr>\n        <tr>\n          <td>Media traceability<\/td>\n          <td>Supplier and grade; informal lot tracking<\/td>\n          <td>Lot number recorded in production traveler for each batch; lot-specific COC retained<\/td>\n        <\/tr>\n        <tr>\n          <td>Surface integrity<\/td>\n          <td>Visual inspection; occasional profilometer check<\/td>\n          <td>Dye penetrant inspection (FPI\/LPI) after finishing for Ti and Ni parts; heat tinting inspection with documented acceptance criteria<\/td>\n        <\/tr>\n        <tr>\n          <td>Edge radius verification<\/td>\n          <td>Visual or tactile check; sporadic measurement<\/td>\n          <td>CMM or optical measurement at specified locations; documented results in FAI report; AQL sampling in production<\/td>\n        <\/tr>\n        <tr>\n          <td>Record retention<\/td>\n          <td>Typically 3\u20137 years<\/td>\n          <td>Part service life (may be 30\u201340 years for primary structure)<\/td>\n        <\/tr>\n        <tr>\n          <td>Compound control<\/td>\n          <td>pH check at bowl; informal frequency<\/td>\n          <td>pH measurement with calibrated instrument at specified frequency; results recorded; out-of-range triggers defined reaction plan<\/td>\n        <\/tr>\n      <\/tbody>\n    <\/table>\n  <\/div>\n\n  <a class=\"hlh-cluster-link\" href=\"https:\/\/hlh-js.com\/resource\/blog\/ceramic-tumbling-media-2\/\" target=\"_blank\" rel=\"noopener\">\n    &#128196; Related: Ceramic Tumbling Media \u2014 Complete Mass Finishing Guide\n    <span>Machine selection, media:parts ratios, and validated process setup including CBF parameters for titanium and superalloys<\/span>\n  <\/a>\n\n  <a class=\"hlh-cluster-link\" href=\"https:\/\/hlh-js.com\/resource\/blog\/ceramic-media-for-deburring\/\" target=\"_blank\" rel=\"noopener\">\n    &#128196; Related: Ceramic Media for Deburring \u2014 Material-Specific Case Studies\n    <span>Validated process specifications for CNC-machined titanium and stainless steel components<\/span>\n  <\/a>\n\n  <!-- FAQ -->\n  <h2 id=\"faq\" class=\"hlh-anchor\">7. Frequently Asked Questions<\/h2>\n\n  <div class=\"hlh-faq\" itemscope itemtype=\"https:\/\/schema.org\/FAQPage\">\n\n    <div class=\"hlh-faq-item\" itemscope itemprop=\"mainEntity\" itemtype=\"https:\/\/schema.org\/Question\">\n      <div class=\"hlh-faq-q\" itemprop=\"name\">Can ceramic vibratory finishing be used on titanium engine discs?<\/div>\n      <div class=\"hlh-faq-a\" itemscope itemprop=\"acceptedAnswer\" itemtype=\"https:\/\/schema.org\/Answer\">\n        <div itemprop=\"text\">\n          <p>Yes, but centrifugal barrel finishing (CBF) is strongly preferred over vibratory for titanium engine discs, for two reasons. First, CBF&#8217;s higher G-force (10\u201325 G vs. 1 G in vibratory) generates sufficient contact pressure to cut efficiently against Ti-6Al-4V&#8217;s high strength and work-hardening tendency, producing the required edge radius in a shorter cycle time. Second, the shorter CBF cycle time means less total frictional heat accumulation at the part surface \u2014 an important consideration because titanium&#8217;s low thermal conductivity (7 W\/m\u00b7K) causes heat to build up at the surface under prolonged vibratory contact, risking heat tinting (oxidation discoloration) that is cause for rejection on flight-critical Ti parts. A neutral, high-lubricity compound further reduces friction-generated heat.<\/p>\n        <\/div>\n      <\/div>\n    <\/div>\n\n    <div class=\"hlh-faq-item\" itemscope itemprop=\"mainEntity\" itemtype=\"https:\/\/schema.org\/Question\">\n      <div class=\"hlh-faq-q\" itemprop=\"name\">What edge radius is typically specified on aerospace structural fasteners?<\/div>\n      <div class=\"hlh-faq-a\" itemscope itemprop=\"acceptedAnswer\" itemtype=\"https:\/\/schema.org\/Answer\">\n        <div itemprop=\"text\">\n          <p>Edge radius specifications for aerospace structural fasteners vary by fastener class, material, and the OEM&#8217;s structural substantiation. Common ranges are 0.05\u20130.15 mm for the thread root radius and 0.10\u20130.25 mm for the under-head fillet radius on titanium and high-strength steel fasteners. These values are typically defined in the fastener manufacturer&#8217;s process specification (which references the OEM&#8217;s material specification) and must be verified by measurement \u2014 either with an optical comparator, a CMM equipped with a small-radius probe, or a calibrated scanning system. Visual estimation is not an acceptable verification method for flight-critical fastener edge radii.<\/p>\n        <\/div>\n      <\/div>\n    <\/div>\n\n    <div class=\"hlh-faq-item\" itemscope itemprop=\"mainEntity\" itemtype=\"https:\/\/schema.org\/Question\">\n      <div class=\"hlh-faq-q\" itemprop=\"name\">Why can&#8217;t acidic compounds be used when finishing high-strength steel aerospace components?<\/div>\n      <div class=\"hlh-faq-a\" itemscope itemprop=\"acceptedAnswer\" itemtype=\"https:\/\/schema.org\/Answer\">\n        <div itemprop=\"text\">\n          <p>Ultra-high-strength steels such as 300M (modified 4340, UTS ~1,900 MPa) and 4340 in the 50\u201355 HRC temper are susceptible to hydrogen embrittlement \u2014 a mechanism where atomic hydrogen, generated by corrosive or electrolytic reactions at the steel surface, diffuses into the metal and accumulates at grain boundaries and stress concentration sites. Under sustained tensile stress, this hydrogen causes delayed brittle fracture at stress levels far below the material&#8217;s normal yield strength, often hours or days after the hydrogen exposure event. Even brief exposure to acidic solutions (below pH 6) during finishing can introduce sufficient hydrogen to cause embrittlement in these steels. Aerospace specifications for landing gear and other ultra-high-strength steel components therefore universally require alkaline compounds (pH 8.5\u201311) for all wet surface treatment processes, including ceramic deburring.<\/p>\n        <\/div>\n      <\/div>\n    <\/div>\n\n    <div class=\"hlh-faq-item\" itemscope itemprop=\"mainEntity\" itemtype=\"https:\/\/schema.org\/Question\">\n      <div class=\"hlh-faq-q\" itemprop=\"name\">Does ceramic mass finishing affect the dimensional tolerances of precision aerospace features?<\/div>\n      <div class=\"hlh-faq-a\" itemscope itemprop=\"acceptedAnswer\" itemtype=\"https:\/\/schema.org\/Answer\">\n        <div itemprop=\"text\">\n          <p>A properly specified and controlled ceramic finishing process produces dimensional changes of typically 0.002\u20130.010 mm (2\u201310 \u00b5m) on flat surfaces \u2014 below the tolerance of most aerospace precision features. External corners are radiused to the specified edge radius value, which is typically accounted for in the part drawing. The critical risk is over-processing: if cycle time, media aggressiveness, or machine amplitude exceeds the validated process specification, progressive material removal can take a feature out of tolerance over multiple batches. This is why the validated trial protocol \u2014 establishing the minimum effective cycle time with 15\u201320% margin, not an arbitrary generous cycle \u2014 is the most important single step in aerospace ceramic finishing process development.<\/p>\n        <\/div>\n      <\/div>\n    <\/div>\n\n    <div class=\"hlh-faq-item\" itemscope itemprop=\"mainEntity\" itemtype=\"https:\/\/schema.org\/Question\">\n      <div class=\"hlh-faq-q\" itemprop=\"name\">Does Jiangsu Henglihong supply ceramic media with AS9100-compatible documentation for aerospace suppliers?<\/div>\n      <div class=\"hlh-faq-a\" itemscope itemprop=\"acceptedAnswer\" itemtype=\"https:\/\/schema.org\/Answer\">\n        <div itemprop=\"text\">\n          <p>Yes. Jiangsu Henglihong Technology Co., Ltd. supplies ceramic finishing media to aerospace Tier 1 and Tier 2 manufacturers with lot-specific documentation packages that support AS9100 Rev D requirements, including: Certificate of Conformance per the applicable material specification, dimensional inspection report (chip size, shape verification), and for applications requiring contamination documentation, ICP-OES analysis of trace elements. We can also provide process engineering support for first-article validation trials, including suggested process parameters for specific alloy and machine combinations. Contact our technical team to discuss your AS9100 documentation requirements.<\/p>\n        <\/div>\n      <\/div>\n    <\/div>\n\n  <\/div>\n\n  <!-- CTA -->\n  <div class=\"hlh-cta\">\n    <h2>Aerospace Finishing Requirements? We Support the Full Documentation Chain.<\/h2>\n    <p>From turbine blade root deburring to landing gear edge radiusing, Jiangsu Henglihong Technology Co., Ltd. supplies ceramic finishing media with AS9100-compatible lot documentation and process engineering support for flight-critical applications.<\/p>\n    <a class=\"hlh-cta-btn\" href=\"https:\/\/hlh-js.com\/contact\/\" target=\"_blank\" rel=\"noopener\">Request Aerospace Media &amp; Documentation &#8594;<\/a>\n  <\/div>\n\n  <!--\n  <script type=\"application\/ld+json\">\n  {\n    \"@context\": \"https:\/\/schema.org\",\n    \"@type\": \"Article\",\n    \"headline\": \"Ceramic Media for Aerospace: Deburring, Edge Radiusing & Fatigue Life Improvement for Titanium, Nickel Superalloy, and Aluminum Flight-Critical Components\",\n    \"description\": \"How ceramic mass finishing media is used in aerospace manufacturing \u2014 covering turbine blades, structural fasteners, landing gear, airframe structures, and engine discs \u2014 with AS9100 compliance guidance and process specifications. By Jiangsu Henglihong Technology Co., Ltd.\",\n    \"author\": {\n      \"@type\": \"Organization\",\n      \"name\": \"Jiangsu Henglihong Technology Co., Ltd.\",\n      \"url\": \"https:\/\/hlh-js.com\"\n    },\n    \"publisher\": {\n      \"@type\": \"Organization\",\n      \"name\": \"Jiangsu Henglihong Technology Co., Ltd.\",\n      \"url\": \"https:\/\/hlh-js.com\"\n    },\n    \"dateModified\": \"2026-03-13\",\n    \"mainEntityOfPage\": {\n      \"@type\": \"WebPage\",\n      \"@id\": \"https:\/\/hlh-js.com\/resource\/blog\/ceramic-media-for-aerospace\/\"\n    },\n    \"isPartOf\": {\n      \"@type\": \"WebPage\",\n      \"@id\": \"https:\/\/hlh-js.com\/resource\/blog\/ceramic-media\/\"\n    }\n  }\n  <\/script>\n  -->\n\n<\/div>\n<!-- END .hlh-pillar -->","protected":false},"excerpt":{"rendered":"<p>Ceramic Media for Aerospace: Deburring, Edge Radiusing &amp; Fatigue Life  [&#8230;]<\/p>","protected":false},"author":1,"featured_media":12572,"comment_status":"closed","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[62,177,138],"tags":[],"class_list":["post-12550","post","type-post","status-publish","format-standard","has-post-thumbnail","hentry","category-blog","category-material","category-resource"],"_links":{"self":[{"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/posts\/12550","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/users\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/comments?post=12550"}],"version-history":[{"count":4,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/posts\/12550\/revisions"}],"predecessor-version":[{"id":12580,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/posts\/12550\/revisions\/12580"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/media\/12572"}],"wp:attachment":[{"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/media?parent=12550"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/categories?post=12550"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/hlh-js.com\/ru\/wp-json\/wp\/v2\/tags?post=12550"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}