- Y Diweddaraf sydd Ar Gael (Diwygiedig)
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Commission Delegated Regulation (EU) 2020/1749 of 7 October 2020 amending Council Regulation (EC) No 428/2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items
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[9E001] "Technology" according to the General Technology Note for the "development" of equipment or "software", specified in 9A001.b., 9A004 to 9A012, 9A350, 9B or 9D.
[9E002] "Technology" according to the General Technology Note for the "production" of equipment specified in 9A001.b., 9A004 to 9A011, 9A350 or 9B.
[9E003] Other "technology" as follows:
"Technology""required" for the "development" or "production" of any of the following gas turbine engine components or systems:
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;
For the purposes of 9E003.a.1., stress-rupture life testing is typically conducted on a test specimen.
Combustors having any of the following:
‘Thermally decoupled liners’ designed to operate at ‘combustor exit temperature’ exceeding 1 883K (1 610 °C);
Non-metallic liners;
Non-metallic shells; or
Liners designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610 °C) and having holes that meet the parameters specified in 9E003.c.;
Components that are any of the following:
Manufactured from organic "composite" materials designed to operate above 588 K (315 °C);
Manufactured from any of the following:
Metal "matrix""composites" reinforced by any of the following:
Materials specified in 1C007;
"Fibrous or filamentary materials" specified in 1C010; or
Aluminides specified in 1C002.a.; or
Ceramic "matrix""composites" specified in 1C007.; or
Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or ‘splitter ducts’, that are all of the following:
Not specified in 9E003.a.3.a.;
Designed for compressors or fans; and
Manufactured from material specified in 1C010.e. with resins specified in 1C008;
A ‘splitter duct’ performs the initial separation of the air-mass flow between the bypass and core sections of the engine.
Uncooled turbine blades, vanes or "tip-shrouds", designed to operate at a ‘gas path temperature’ of 1 373 K (1 100 °C) or more;
Cooled turbine blades, vanes, "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;
‘Gas path temperature’ is the bulk average gas path total (stagnation) temperature at the leading edge plane of the turbine component when the engine is running in a "steady state mode" of operation at the certificated or specified maximum continuous operating temperature.
Airfoil-to-disk blade combinations using solid state joining;
Not used;
‘Damage tolerant’ gas turbine engine rotor components using powder metallurgy materials specified in 1C002.b.; or
‘Damage tolerant’ components are designed using methodology and substantiation to predict and limit crack growth.
Not used;
Not used;
‘Fan blades’ having all of the following:
20 % or more of the total volume being one or more closed cavities containing vacuum or gas only; and
"Technology""required" for the "development" or "production" of any of the following:
Wind tunnel aero-models equipped with non-intrusive sensors capable of transmitting data from the sensors to the data acquisition system; or
"Composite" propeller blades or propfans, capable of absorbing more than 2 000 kW at flight speeds exceeding Mach 0,55;
"Technology""required" for manufacturing cooling holes, in gas turbine engine components incorporating any of the "technologies" specified in 9E003.a.1., 9E003.a.2. or 9E003.a.5., and having any of the following:
Having all of the following:
Minimum ‘cross-sectional area’ less than 0,45 mm2;
‘Hole shape ratio’ greater than 4,52; and
‘Incidence angle’ equal to or less than 25o; or
Having all of the following:
Minimum ‘cross-sectional area’ less than 0,12 mm2;
‘Hole shape ratio’ greater than 5,65; and
‘Incidence angle’ more than 25o;
"Technology""required" for the "development" or "production" of helicopter power transfer systems or tilt rotor or tilt wing "aircraft" power transfer systems;
"Technology" for the "development" or "production" of reciprocating diesel engine ground vehicle propulsion systems having all of the following:
‘Box volume’ of 1,2 m3 or less;
An overall power output of more than 750 kW based on 80/1269/EEC, ISO 2534 or national equivalents; and
Power density of more than 700 kW/m3 of ‘box volume’;
‘Box volume’ in 9E003.e. is the product of three perpendicular dimensions measured in the following way:
:
The length of the crankshaft from front flange to flywheel face;
:
The widest of any of the following:
The outside dimension from valve cover to valve cover;
The dimensions of the outside edges of the cylinder heads; or
The diameter of the flywheel housing;
:
The largest of any of the following:
The dimension of the crankshaft centre-line to the top plane of the valve cover (or cylinder head) plus twice the stroke; or
The diameter of the flywheel housing.
"Technology""required" for the "production" of specially designed components for high output diesel engines, as follows:
"Technology""required" for the "production" of engine systems having all of the following components employing ceramics materials specified in 1C007:
Cylinder liners;
Pistons;
Cylinder heads; and
One or more other components (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors);
"Technology""required" for the "production" of turbocharger systems with single-stage compressors and having all of the following:
Operating at pressure ratios of 4:1 or higher;
Mass flow in the range from 30 to 130 kg per minute; and
Variable flow area capability within the compressor or turbine sections;
"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:
Injection amount in excess of 230 mm3 per injection per cylinder; and
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;
"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;
‘High output diesel engines’ are diesel engines with a specified brake mean effective pressure of 1,8 MPa or more at a speed of 2 300 r.p.m., provided the rated speed is 2 300 r.p.m. or more.
"Technology" for gas turbine engine "FADEC systems" as follows:
"Development""technology" for deriving the functional requirements for the 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);
"Development" or "production""technology" for control and diagnostic components unique to the "FADEC system" and used to regulate engine thrust or shaft power;
"Development""technology" for the control law algorithms, including "source code", unique to the "FADEC system" and used to regulate engine thrust or shaft power;
"Technology" for adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:
"Development""technology" for deriving the functional requirements for the components that maintain engine stability;
"Development" or "production""technology" for components unique to the adjustable flow path system and that maintain engine stability;
"Development""technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability.
Inlet guide vanes;
Variable pitch fans or prop-fans;
Variable compressor vanes;
Compressor bleed valves; or
Adjustable flow path geometry for reverse thrust.
[9E101]
"Technology" according to the General Technology Note for the "development" of goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.
[9E102] "Technology" according to the General Technology Note for the "use" of space launch vehicles specified in 9A004, goods specified in 9A005 to 9A011, ‘UAV’s specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a., 9A115 to 9A121, 9B105, 9B106, 9B115, 9B116, 9B117, 9D101 or 9D103.
In 9E102 ‘UAV’ means unmanned aerial vehicle systems capable of a range exceeding 300 km.
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