ECCN 9E003

• a."Technology" "required" for the "development" or "production" of any of the following gas turbine engine "parts," "components" or systems:
• 1. Gas turbine blades, vanes or "tip shrouds", made from Directionally Solidified (DS) or Single Crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress-rupture life exceeding 400 hours at 1,273 K (1,000 °C) at a stress of 200 MPa, based on the average property values;
• 2. Combustors having any of the following:
• 2.a. 'Thermally decoupled liners' designed to operate at 'combustor exit temperature' exceeding 1,883 K (1,610 °C);
• 2.b. Non-metallic liners;
• 2.c. Non-metallic shells; or
• 2.d. Liners designed to operate at 'combustor exit temperature' exceeding 1,883 K (1,610 °C) and having holes that meet the parameters specified by 9E003.c;
• 2.e. Utilizing 'pressure gain combustion';
• 3. "Parts" or "components," that are any of the following:
• 3.a. Manufactured from organic "composite" materials designed to operate above 588 K (315 °C);
• 3.b. Manufactured from any of the following:
• 3.b.1. Metal "matrix" "composites" reinforced by any of the following:
• 3.b.1.a. Materials controlled by 1C007;
• 3.b.1.b. "Fibrous or filamentary materials" specified by 1C010; or
• 3.b.1.c. Aluminides specified by 1C002.a; or
• 3.b.2. Ceramic "matrix" "composites" specified by 1C007; or
• 3.c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks or 'splitter ducts', that are all of the following:
• 3.c.1. Not specified in 9E003.a.3.a;
• 3.c.2. Designed for compressors or fans; and
• 3.c.3. Manufactured from material controlled by 1C010.e with resins controlled by 1C008;
• 4. Uncooled turbine blades, vanes or "tip shrouds" designed to operate at a 'gas path temperature' of 1,373 K (1,100 °C) or more;
• 5. Cooled turbine blades, vanes or "tip shrouds", other than those described in 9E003.a.1, designed to operate at a 'gas path temperature' of 1,693 K (1,420 °C) or more;
• 6. Airfoil-to-disk blade combinations using solid state joining;
• 8. 'Damage tolerant' gas turbine engine rotor "parts" or "components" using powder metallurgy materials controlled by 1C002.b; or
• 11. 'Fan blades' having all of the following:
• 11.a. 20% or more of the total volume being one or more closed cavities containing vacuum or gas only; and
• 11.b. One or more closed cavities having a volume of 5 cm3 or larger;
• b."Technology" "required" for the "development" or "production" of any of the following:
• 1. Wind tunnel aero-models equipped with non-intrusive sensors capable of transmitting data from the sensors to the data acquisition system; or
• 2. "Composite" propeller blades or prop-fans, capable of absorbing more than 2,000 kW at flight speeds exceeding Mach 0.55;
• c."Technology" "required" for manufacturing cooling holes in gas turbine engine "parts" or "components" incorporating any of the "technologies" specified by 9E003.a.1, 9E003.a.2, or 9E003.a.5, and having any of the following:
• 1. Having all of the following:
• 1.a. Minimum 'cross-sectional area' less than 0.45 mm2;
• 1.b. 'Hole shape ratio' greater than 4.52; and
• 1.c. 'Incidence angle' equal to or less than 25°; or
• 2. Having all of the following:
• 2.a. Minimum 'cross-sectional area' less than 0.12 mm2;
• 2.b. 'Hole shape ratio' greater than 5.65; and
• 2.c. 'Incidence angle' more than 25°;
• d."Technology" "required" for the "development" or "production" of helicopter power transfer systems or tilt rotor or tilt wing "aircraft" power transfer systems;
• e."Technology" for the "development" or "production" of reciprocating diesel engine ground vehicle propulsion systems having all of the following:
• 1. 'Box volume' of 1.2 m3 or less;
• 2. An overall power output of more than 750 kW based on 80/1269/EEC, ISO 2534 or national equivalents; and
• 3. Power density of more than 700 kW/m3 of 'box volume';
• a.The outside dimension from valve cover to valve cover;
• b.The dimensions of the outside edges of the cylinder heads; or
• c.The diameter of the flywheel housing;
• a.The dimension of the crankshaft center-line to the top plane of the valve cover (or cylinder head) plus twice the stroke; or
• b.The diameter of the flywheel housing.
• f."Technology" "required" for the "production" of specially designed "parts" or "components" for high output diesel engines, as follows:
• 1. "Technology" "required" for the "production" of engine systems having all of the following "parts" and "components" employing ceramics materials controlled by 1C007:
• f.1.a Cylinder liners;
• 1.b. Pistons;
• 1.c. Cylinder heads; and
• 1.d. One or more other "part" or "component" (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors);
• 2. "Technology" "required" for the "production" of turbocharger systems with single-stage compressors and having all of the following:
• 2.a. Operating at pressure ratios of 4:1 or higher;
• 2.b. Mass flow in the range from 30 to 130 kg per minute; and
• 2.c. Variable flow area capability within the compressor or turbine sections;
• 3. "Technology" "required" for the "production" of fuel injection systems with a specially designed multifuel (e.g., diesel or jet fuel) capability covering a viscosity range from diesel fuel (2.5 cSt at 310.8 K (37.8 °C)) down to gasoline fuel (0.5 cSt at 310.8 K (37.8 °C)) and having all of the following:
• 3.a. Injection amount in excess of 230 mm3 per injection per cylinder; and
• 3.b. Electronic control features specially designed for switching governor characteristics automatically depending on fuel property to provide the same torque characteristics by using the appropriate sensors;
• g."Technology" "required" for the "development" or "production" of 'high output diesel engines' for solid, gas phase or liquid film (or combinations thereof) cylinder wall lubrication and permitting operation to temperatures exceeding 723 K (450 °C), measured on the cylinder wall at the top limit of travel of the top ring of the piston;
• h."Technology" for gas turbine engine "FADEC systems" as follows:
• 1. "Development" "technology" for deriving the functional requirements for the "parts" or "components" necessary for the "FADEC system" to regulate engine thrust or shaft power (e.g., feedback sensor time constants and accuracies, fuel valve slew rate);
• 2. "Development" or "production" "technology" for control and diagnostic "parts" or "components" unique to the "FADEC system" and used to regulate engine thrust or shaft power;
• 3. "Development" "technology" for the control law algorithms, including "source code", unique to the "FADEC system" and used to regulate engine thrust or shaft power;
• i."Technology" for adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:
• 1. "Development" "technology" for deriving the functional requirements for the "parts" or "components" that maintain engine stability;
• 2. "Development" or "production" "technology" for "parts" or "components" unique to the adjustable flow path system and that maintain engine stability;
• 3. "Development" "technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability;
• a.Inlet guide vanes;
• b.Variable pitch fans or prop-fans;
• c.Variable compressor vanes;
• d.Compressor bleed valves; or
• e.Adjustable flow path geometry for reverse thrust.
• j."Technology" "required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" powered by gas turbine engines.
• k."Technology", not specified in 9E003.a, 9E003.h, or 9E003.i, "required" for the "development" of any of the following components or systems, specially designed for aero gas turbine engines to enable "aircraft" to cruise at Mach 1 or greater for more than 30 minutes:
• 1. Propulsion inlet systems;
• 2. Propulsion exhaust systems;
• 3. 'Reheat systems';
• 4. 'Active thermal management systems' to condition fluids used to lubricate or cool 'engine rotor supports';
• 5. Oil-free 'engine rotor supports'; or
• 6. Systems to remove heat from 'compression system' core gas path flow.
• l."Technology" not otherwise controlled in 9E003.a.1 through a.8, a.10, and .h and used in the "development", "production", or overhaul of hot section "parts" or "components" of civil derivatives of military engines controlled on the U.S. Munitions List.

3 items reserved by BIS (not shown)