Commission Delegated Regulation (EU) 2022/1 of 20 October 2021 amending Regulation (EU) 2021/821 of the European Parliament and of the Council as regards the list of dual-use items

• — Gas turbine engine (turbojet, turboprop and turbofan);

• — Ramjet or scramjet;

• — Rocket motor or engine (liquid/gel/solid-propellant and hybrid).

9A012

"Unmanned aerial vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:

• N.B.1. SEE ALSO 9A112.

• N.B.2. For "UAVs" that are "sub-orbital craft", see 9A004.h.

• a. "UAVs" or unmanned "airships", designed to have controlled flight out of the direct ‘natural vision’ of the ‘operator’ and having any of the following:

• 1. Having all of the following:

• a. A maximum ‘endurance’ greater than or equal to 30 minutes but less than 1 hour; and

• b. Designed to take-off and have stable controlled flight in wind gusts equal to or exceeding 46,3 km/h (25 knots); or

• 1. A maximum ‘endurance’ of 1 hour or greater;

Technical Notes:

• 1. For the purposes of 9A012.a., ‘operator’ is a person who initiates or commands the "UAV" or unmanned "airship" flight.

• 2. For the purposes of 9A012.a., ‘endurance’ is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind.

• 3. For the purposes of 9A012.a., ‘natural vision’ means unaided human sight, with or without corrective lenses.

• b. Related equipment and components, as follows:

• 1. Not used;

• 1. Not used;

• 1. Equipment or components, specially designed to convert a manned "aircraft" or manned "airship", to a "UAV" or unmanned "airship", specified in 9A012.a.;

• 1. Air breathing reciprocating or rotary internal combustion type engines, specially designed or modified to propel "UAVs" or unmanned "airships", at altitudes above 15 240 metres (50 000 feet).

9A101 Turbojet and turbofan engines, other than those specified in 9A001, as follows;

• a. Engines having all of the following characteristics:

• 1. ‘Maximum thrust value’ greater than 400 N excluding civil certified engines with a ‘maximum thrust value’ greater than 8 890 N;

- 2. Specific fuel consumption of 0,15 kg N^–1 h^–1 or less;

• 1. ‘Dry weight’ less than 750 kg; and

• 1. ‘First-stage rotor diameter’ less than 1 m;

Technical Notes:

• 1. For the purpose of 9A101.a.1., ‘maximum thrust value’ is the manufacturer’s demonstrated maximum thrust for the engine type un-installed at sea level static conditions using the ICAO standard atmosphere. The civil type certified thrust value will be equal to or less than the manufacturer’s demonstrated maximum thrust for the engine type un-installed.

• 2. Specific fuel consumption is determined at maximum continuous thrust for engine type un-installed at sea level static conditions using the ICAO standard atmosphere.

• 3. ‘Dry weight’ is the weight of the engine without fluids (fuel, hydraulic fluid, oil, etc.) and does not include the nacelle (housing).

• 4. ‘First-stage rotor diameter’ is the diameter of the first rotating stage of the engine, whether a fan or compressor, measured at the leading edge of the blade tips.

• b. Engines designed or modified for use in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a.

9A102

‘Turboprop engine systems’ specially designed for unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor, having a ‘maximum power’ greater than 10 kW.

• Note: 9A102 does not control civil certified engines.

Technical Notes:

• 1. For the purposes of 9A102, a ‘turboprop engine system’ incorporates all of the following:

• a. Turboshaft engine; and

• b. Power transmission system to transfer the power to a propeller.

• 2. For the purposes of 9A102, the ‘maximum power’ is achieved un-installed at sea level static conditions using ICAO standard atmosphere.

9A104 Sounding rockets, capable of a range of at least 300 km.

• N.B. SEE ALSO 9A004.

9A105 Liquid propellant rocket engines or gel propellant rocket motors, as follows:

• N.B. SEE ALSO 9A119.

• a. Liquid propellant rocket engines or gel propellant rocket motors, usable in "missiles", other than those specified in 9A005, integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 MNs;

• b. Liquid propellant rocket engines or gel propellant rocket motors, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005 or 9A105.a., integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs.

9A106 Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion or gel propellant rocket systems:

• a. Not used;

• b. Not used;

• c. Thrust vector control sub-systems, usable in "missiles";

Technical Note:

Examples of methods of achieving thrust vector control specified in 9A106.c. are:

• 1. Flexible nozzle;

• 2. Fluid or secondary gas injection;

• 3. Movable engine or nozzle;

• 4. Deflection of exhaust gas stream (jet vanes or probes); or

• 5. Thrust tabs.

• d. Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in "missiles", designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz;

• Note: The only servo valves, pumps and gas turbines specified in 9A106.d., are the following:

• a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms;

• b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 r.p.m. at a maximum operating mode or with discharge pressures equal to or greater than 7 MPa;

• c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 r.p.m. at the maximum operating mode.

• e. Combustion chambers and nozzles for liquid propellant rocket engines or gel propellant rocket motors specified in 9A005 or 9A105.

9A107 Solid propellant rocket motors, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A007, having total impulse capacity equal to or greater than 0,841 MNs.

• N.B. SEE ALSO 9A119.

9A108 Components, other than those specified in 9A008, as follows, specially designed for solid and hybrid rocket propulsion systems:

• a. Rocket motor cases and "insulation" components therefor, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;

• b. Rocket nozzles, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;

• c. Thrust vector control sub-systems, usable in "missiles".

Technical Note:

Examples of methods of achieving thrust vector control specified in 9A108.c. are:

• 1. Flexible nozzle;

• 2. Fluid or secondary gas injection;

• 3. Movable engine or nozzle;

• 4. Deflection of exhaust gas stream (jet vanes or probes); or

• 5. Thrust tabs.

9A109 Hybrid rocket motors and specially designed components as follows:

• a. Hybrid rocket motors usable in complete rocket systems or unmanned aerial vehicles, capable of 300 km, other than those specified in 9A009, having a total impulse capacity equal to or greater than 0,841 MNs, and specially designed components therefor;

• b. Specially designed components for hybrid rocket motors specified in 9A009 that are usable in "missiles".

• N.B. SEE ALSO 9A009 AND 9A119.

9A110 Composite structures, laminates and manufactures thereof, other than those specified in 9A010, specially designed for use in ‘missiles’ or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

• N.B. SEE ALSO 1A002.

Technical Note:

In 9A110 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9A111 Pulse jet or detonation engines, usable in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.

• N.B. SEE ALSO 9A011 AND 9A118.

Technical Note:

In 9A111 detonation engines utilise detonation to produce a rise in effective pressure across the combustion chamber. Examples of detonation engines include pulse detonation engines, rotating detonation engines or continuous wave detonation engines.

9A112

"Unmanned aerial vehicles" ("UAVs"), other than those specified in 9A012, as follows:

• a. "Unmanned aerial vehicles" ("UAVs") capable of a range of 300 km;

• b. "Unmanned aerial vehicles" ("UAVs") having all of the following:

• 1. Having any of the following:

- a. An autonomous flight control and navigation capability; or

• b. Capability of controlled flight out of the direct vision range involving a human operator; and

• 1. Having any of the following:

• a. Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or

• b. Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.

Technical Notes:

• 1. An aerosol consists of particulate or liquids other than fuel components, by products or additives, as part of the payload to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding.

• 2. An aerosol dispensing system/mechanism contains all those devices (mechanical, electrical, hydraulic, etc.), which are necessary for storage and dispersion of an aerosol into the atmosphere. This includes the possibility of aerosol injection into the combustion exhaust vapour and into the propeller slip stream.

9A115 Launch support equipment as follows:

• a. Apparatus and devices for handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or ‘missiles’;

Technical Note:

In 9A115.a. ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

• b. Vehicles for transport, handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles".

9A116 Reentry vehicles, usable in "missiles", and equipment designed or modified therefor, as follows:

• a. Reentry vehicles;

• b. Heat shields and components therefor, fabricated of ceramic or ablative materials;

• c. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;

• d. Electronic equipment specially designed for reentry vehicles.

9A117 Staging mechanisms, separation mechanisms, and interstages, usable in "missiles".

• N.B. SEE ALSO 9A121.

9A118 Devices to regulate combustion usable in engines, which are usable in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a., specified in 9A011 or 9A111.

9A119 Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109.

9A120 Liquid or gel propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or ‘other liquid or gel propellants’ used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.

• Note: In 9A120 ‘other liquid or gel propellants’ includes, but is not limited to, propellants specified in THE MILITARY GOODS CONTROLS.

9A121 Umbilical and interstage electrical connectors specially designed for "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

Technical Note:

Interstage connectors referred to in 9A121 also include electrical connectors installed between the "missile", space launch vehicle or sounding rocket and their payload.

9A350 Spraying or fogging systems, specially designed or modified for fitting to aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles, and specially designed components therefor, as follows:

• a. Complete spraying or fogging systems capable of delivering, from a liquid suspension, an initial droplet ‘VMD’ of less than 50 μm at a flow rate of greater than two litres per minute;

• b. Spray booms or arrays of aerosol generating units capable of delivering, from a liquid suspension, an initial droplet ‘VMD’ of less than 50 μm at a flow rate of greater than two litres per minute;

• c. Aerosol generating units specially designed for fitting to systems specified in 9A350.a. and .b.

• Note: Aerosol generating units are devices specially designed or modified for fitting to aircraft such as nozzles, rotary drum atomisers and similar devices.

• Note: 9A350 does not control spraying or fogging systems and components that are demonstrated not to be capable of delivering biological agents in the form of infectious aerosols.

Technical Notes:

• 1. Droplet size for spray equipment or nozzles specially designed for use on aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles should be measured using either of the following:

- a. Doppler laser method;

• b. Forward laser diffraction method.

• 2. In 9A350 ‘VMD’ means Volume Median Diameter and for water-based systems this equates to Mass Median Diameter (MMD).

9B Test, Inspection and Production Equipment

9B001 Manufacturing equipment, tooling or fixtures, as follows:

• N.B. SEE ALSO 2B226

• a. Directional solidification or single crystal casting equipment designed for "superalloys";

• b. Casting tooling, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds", manufactured from refractory metals or ceramics, as follows:

• 1. Cores;

• 1. Shells (moulds);

• 1. Combined core and shell (mould) units;

• c. Directional-solidification or single-crystal additive-manufacturing equipment, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds".

9B002 On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, having all of the following:

• a. Specially designed for the "development" of gas turbine engines, assemblies or components; and

• b. Incorporating any of the "technologies" specified in 9E003.h. or 9E003.i.

9B003 Equipment specially designed for the "production" or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s and temperatures in excess of 773 K (500 °C), and specially designed components or accessories therefor.

9B004 Tools, dies or fixtures, for the solid state joining of "superalloy", titanium or intermetallic airfoil-to-disk combinations described in 9E003.a.3. or 9E003.a.6. for gas turbines.

9B005 On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following:

• N.B. SEE ALSO 9B105.

• a. Wind tunnels designed for speeds of Mach 1,2 or more;

• Note: 9B005.a. does not control wind tunnels specially designed for educational purposes and having a ‘test section size’ (measured laterally) of less than 250 mm.

Technical Note:

‘Test section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, at the largest test section location.

• b. Devices for simulating flow-environments at speeds exceeding Mach 5, including hot-shot tunnels, plasma arc tunnels, shock tubes, shock tunnels, gas tunnels and light gas guns; or

• c. Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 × 10⁶.

9B006 Acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 μPa) with a rated output of 4 kW or more at a test cell temperature exceeding 1 273 K (1 000 °C), and specially designed quartz heaters therefor.

• N.B. SEE ALSO 9B106.

9B007 Equipment specially designed for inspecting the integrity of rocket motors and using Non-Destructive Test (NDT) techniques other than planar x-ray or basic physical or chemical analysis.

9B008 Direct measurement wall skin friction transducers specially designed to operate at a test flow total (stagnation) temperature exceeding 833 K (560 °C).

9B009 Tooling specially designed for producing gas turbine engine powder metallurgy rotor components having all of the following:

• a. Designed to operate at stress levels of 60 % of Ultimate Tensile Strength (UTS) or more measured at a temperature of 873 K (600 °C); and

• b. Designed to operate at 873 K (600 °C) or more.

• Note: 9B009 does not control tooling for the production of powder.

9B010 Equipment specially designed for the production of items specified in 9A012.

9B105

‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for ‘missiles’ and their subsystems.

• N.B. SEE ALSO 9B005.

• Note: 9B105 does not control wind-tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

• 1. In 9B105 ‘aerodynamic test facilities’ includes wind tunnels and shock tunnels for the study of airflow over objects.

• 2. In Note to 9B105, ‘test cross section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, or the major axis of the ellipse at the largest ‘test cross section’ location. ‘Test cross section’ is the section perpendicular to the flow direction.

• 3. In 9B105 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B106 Environmental chambers and anechoic chambers, as follows:

• a. Environmental chambers having all of the following:

• 1. Capable of simulating any of the following flight conditions:

• a. Altitude equal to or greater than 15 km; or

• b. Temperature range from below 223 K (–50 °C) to above 398 K (125 °C); and

• 1. Incorporating, or ‘designed or modified’ to incorporate, a shaker unit or other vibration test equipment to produce vibration environments equal to or greater than 10 g rms, measured ‘bare table’, between 20 Hz and 2 kHz while imparting forces equal to or greater than 5 kN;

Technical Notes:

• 1. 9B106.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g., a sine wave) and systems capable of generating a broad band random vibration (i.e., power spectrum).

• 2. In 9B106.a.2., ‘designed or modified’ means the environmental chamber provides appropriate interfaces (e.g., sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in 2B116.

• 3. In 9B106.a.2., ‘bare table’ means a flat table, or surface, with no fixture or fittings.

• b. Environmental chambers capable of simulating the following flight conditions:

• 1. Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 20 μPa) or with a total rated acoustic power output of 4 kW or greater; and

• 1. Altitude equal to or greater than 15 km; or

• 1. Temperature range from below 223 K (– 50 °C) to above 398 K (125 °C).

9B107

‘Aerothermodynamic test facilities’, usable for ‘missiles’, ‘missile’ rocket propulsion systems, and reentry vehicles and equipment specified in 9A116, having any of the following characteristics:

• a. An electrical power supply equal to or greater than 5 MW; or

• b. A gas supply total pressure equal to or greater than 3 MPa.

Technical Notes:

• 1. ‘Aerothermodynamic test facilities’ include plasma arc jet facilities and plasma wind tunnels for the study of thermal and mechanical effects of airflow on objects.

• 2. In 9B107 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B115 Specially designed "production equipment" for the systems, sub-systems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A105 to 9A109, 9A111, 9A116 to 9A120.

9B116 Specially designed "production facilities" for the space launch vehicles specified in 9A004, or systems, sub-systems, and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A104 to 9A109, 9A111, 9A116 to 9A120 or ‘missiles’.

Technical Note:

In 9B116 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B117 Test benches or test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:

• a. The capacity to handle more than 68 kN of thrust; or

• b. Capable of simultaneously measuring the three axial thrust components.

9C Materials

9C108

"Insulation" material in bulk form and "interior lining", other than those specified in 9A008, for rocket motor cases usable in "missiles" or specially designed for solid propellant rocket engines specified in 9A007 or 9A107.

9C110 Resin impregnated fibre prepregs and metal coated fibre preforms therefor, for composite structures, laminates and manufactures specified in 9A110, made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a "specific tensile strength" greater than 7,62 × 10⁴ m and a "specific modulus" greater than 3,18 × 10⁶ m.

• N.B. SEE ALSO 1C010 AND 1C210.

• Note: The only resin impregnated fibre prepregs specified in entry 9C110 are those using resins with a glass transition temperature (Tg), after cure, exceeding 418 K (145 °C) as determined by ASTM D4065 or equivalent.

9D Software

9D001

"Software", not specified in 9D003 or 9D004, specially designed or modified for the "development" of equipment or "technology", specified in 9A001 to 9A119, 9B or 9E003.

9D002

"Software", not specified in 9D003 or 9D004, specially designed or modified for the "production" of equipment specified in 9A001 to 9A119 or 9B.

9D003

"Software" incorporating "technology" specified in 9E003.h. and used in "FADEC Systems" for systems specified in 9A or equipment specified in 9B.

9D004 Other "software" as follows:

• a. 2D or 3D viscous "software", validated with wind tunnel or flight test data required for detailed engine flow modelling;

• b. "Software" for testing aero gas turbine engines, assemblies or components, having all of the following:

• 1. Specially designed for testing any of the following:

• a. Aero gas turbine engines, assemblies or components, incorporating "technology" specified in 9E003.a., 9E003.h. or 9E003.i.; or

• b. Multi-stage compressors providing either bypass or core flow, specially designed for aero gas turbine engines incorporating "technology" specified in 9E003.a. or 9E003.h.; and

• 1. Specially designed for all of the following:

• a. Acquisition and processing of data, in real time; and

• b. Feedback control of the test article or test conditions (e.g. temperature, pressure, flow rate) while the test is in progress;

• Note: 9D004.b. does not control software for operation of the test facility or operator safety (e.g. overspeed shutdown, fire detection and suppression), or production, repair or maintenance acceptance-testing limited to determining if the item has been properly assembled or repaired.

• c. "Software" specially designed to control directional solidification or single crystal material growth in equipment specified in 9B001.a. or 9B001.c.;

• d. Not used;

• e. "Software" specially designed or modified for the operation of items specified in 9A012;

• f. "Software" specially designed to design the internal cooling passages of aero gas turbine blades, vans and "tip shrouds";

• g. "Software" having all of the following:

• 1. Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

• 1. Theoretical modelling predictions of the aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.

9D005

"Software" specially designed or modified for the operation of items specified in 9A004.e. or 9A004.f.

• N.B. For "software" for items listed in 9A004.d. that are incorporated into "spacecrafts payloads", see the appropriate Categories.

9D101

"Software" specially designed or modified for the "use" of goods specified in 9B105, 9B106, 9B116 or 9B117.

9D103

"Software" specially designed for modelling, simulation or design integration of the space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles", or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

• Note: "Software" specified in 9D103 remains controlled when combined with specially designed hardware specified in 4A102.

9D104

"Software" as follows:

• a. "Software" specially designed or modified for the "use" of goods specified in 9A001, 9A005, 9A006.d., 9A006.g., 9A007.a., 9A009.a., 9A010.d., 9A011, 9A101, 9A102, 9A105, 9A106.d., 9A107, 9A109, 9A111, 9A115.a., 9A117 or 9A118.

• b. "Software" specially designed or modified for the operation or maintenance of subsystems or equipment specified in 9A008.d., 9A106.c., 9A108.c. or 9A116.d.

9D105

"Software" specially designed or modified to coordinate the function of more than one subsystem, other than that specified in 9D004.e., in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104 or ‘missiles’

• Note: 9D105 includes "software" specially designed for a manned "aircraft" converted to operate as "unmanned aerial vehicle", as follows:

• a. "Software" specially designed or modified to integrate the conversion equipment with the "aircraft" system functions; and

• b. "Software" specially designed or modified to operate the "aircraft" as an "unmanned aerial vehicle".

Technical Note:

In 9D105 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9E Technology

• Note: "Development" or "production" "technology" specified in 9E001 to 9E003 for gas turbine engines remains controlled when used for repair or overhaul. Excluded from control are: technical data, drawings or documentation for maintenance activities directly associated with calibration, removal or replacement of damaged or unserviceable line replaceable units, including replacement of whole engines or engine modules.

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.

• N.B. For "technology" for the repair of controlled structures, laminates or materials, see 1E002.f.

9E003

Other "technology" as follows:

• a. "Technology""required" for the "development" or "production" of any of the following gas turbine engine 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;

Technical Note:

For the purposes of 9E003.a.1., stress-rupture life testing is typically conducted on a test specimen.

- 2. Combustors having any of the following:

- a. ‘Thermally decoupled liners’ designed to operate at ‘combustor exit temperature’ exceeding 1 883K (1 610 °C);

• b. Non-metallic liners;

- c. Non-metallic shells; or

• d. 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.;

- Note: *The "required"

"technology" for holes in 9E003.a.2. is limited to the derivation of the geometry and location of the holes.*

Technical Notes:

- 1. ‘Thermally decoupled liners’ are liners that feature at least a support structure designed to carry mechanical loads and a combustion facing structure designed to protect the support structure from the heat of combustion. The combustion facing structure and support structure have independent thermal displacement (mechanical displacement due to thermal load) with respect to one another, i.e. they are thermally decoupled.

• 2. ‘Combustor exit temperature’ is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a "steady state mode" of operation at the certificated maximum continuous operating temperature.

- N.B. *See 9E003.c. for "technology"

"required" for manufacturing cooling holes.*

• 1. Components that are any of the following:

• a. Manufactured from organic "composite" materials designed to operate above 588 K (315 °C);

• b. Manufactured from any of the following:

• 1. Metal "matrix""composites" reinforced by any of the following:

• a. Materials specified in 1C007;

- b. "Fibrous or filamentary materials" specified in 1C010; or

- c. Aluminides specified in 1C002.a.; or

- 2. Ceramic "matrix""composites" specified in 1C007.; or

• c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or ‘splitter ducts’, that are all of the following:

- 1. Not specified in 9E003.a.3.a.;

• 1. Designed for compressors or fans; and

• 1. Manufactured from material specified in 1C010.e. with resins specified in 1C008;

Technical Note:

A ‘splitter duct’ performs the initial separation of the air-mass flow between the bypass and core sections of the engine.

• 1. Uncooled turbine blades, vanes or "tip-shrouds", designed to operate at a ‘gas path temperature’ of 1 373 K (1 100 °C) or more;

• 1. 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;

Technical Note:

‘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.

• 1. Airfoil-to-disk blade combinations using solid state joining;

• 1. Not used;

• 1. ‘Damage tolerant’ gas turbine engine rotor components using powder metallurgy materials specified in 1C002.b.; or

Technical Note:

‘Damage tolerant’ components are designed using methodology and substantiation to predict and limit crack growth.

• 1. Not used;

• 1. Not used;

• 1. ‘Fan blades’ having all of the following:

• a. 20 % or more of the total volume being one or more closed cavities containing vacuum or gas only; and

• b. One or more closed cavities having a volume of 5 cm³ or larger;

Technical Note:

For the purposes of 9E003.a.11., a ‘fan blade’ is the aerofoil portion of the rotating stage or stages, which provide both compressor and bypass flow in a gas turbine engine.

• 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

• 1. "Composite" propeller blades or propfans, 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 components incorporating any of the "technologies" specified in 9E003.a.1., 9E003.a.2. or 9E003.a.5., and having any of the following:

• 1. Having all of the following:

• a. Minimum ‘cross-sectional area’ less than 0,45 mm²;

• b. ‘Hole shape ratio’ greater than 4,52; and

• c. ‘Incidence angle’ equal to or less than 25^o; or

• 1. Having all of the following:

• a. Minimum ‘cross-sectional area’ less than 0,12 mm²;

• b. ‘Hole shape ratio’ greater than 5,65; and

• c. ‘Incidence angle’ more than 25^o;

• Note: 9E003.c. does not control "technology" for manufacturing constant radius cylindrical holes that are straight through and enter and exit on the external surfaces of the component.

Technical Notes:

• 1. For the purposes of 9E003.c., the ‘cross-sectional area’ is the area of the hole in the plane perpendicular to the hole axis.

• 2. For the purposes of 9E003.c., ‘hole shape ratio’ is the nominal length of the axis of the hole divided by the square root of its minimum ‘cross-sectional area’.

• 3. For the purposes of 9E003.c., ‘incidence angle’ is the acute angle measured between the plane tangential to the aerofoil surface and the hole axis at the point where the hole axis enters the aerofoil surface.

• 4. Methods for manufacturing holes in 9E003.c. include "laser" beam machining, water jet machining, Electro-Chemical Machining (ECM) or Electrical Discharge Machining (EDM).

• 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;

• 1. An overall power output of more than 750 kW based on 80/1269/EEC, ISO 2534 or national equivalents; and

• 1. Power density of more than 700 kW/m³ of ‘box volume’;

Technical Note:

‘Box volume’ in 9E003.e. is the product of three perpendicular dimensions measured in the following way:

Length	:	The length of the crankshaft from front flange to flywheel face;
Width	:	The widest of any of the following: 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;
Height	:	The largest of any of the following: a. The dimension of the crankshaft centre-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 components for high output diesel engines, as follows:

• 1. "Technology""required" for the "production" of engine systems having all of the following components employing ceramics materials specified in 1C007:

• a. Cylinder liners;

• b. Pistons;

• c. Cylinder heads; and

• d. One or more other components (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors);

• 1. "Technology""required" for the "production" of turbocharger systems with single-stage compressors and having all of the following:

• a. Operating at pressure ratios of 4:1 or higher;

• b. Mass flow in the range from 30 to 130 kg per minute; and

• c. Variable flow area capability within the compressor or turbine sections;

• 1. "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:

• a. Injection amount in excess of 230 mm³ per injection per cylinder; and

• 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;

Technical Note:

‘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.

• h. "Technology" for gas turbine engine "FADEC systems" as follows:

• 1. "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);

• 1. "Development" or "production""technology" for control and diagnostic components unique to the "FADEC system" and used to regulate engine thrust or shaft power;

• 1. "Development""technology" for the control law algorithms, including "source code", unique to the "FADEC system" and used to regulate engine thrust or shaft power;

• Note: 9E003.h. does not control technical data related to engine-"aircraft" integration required by the civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States to be published for general airline use (e.g., installation manuals, operating instructions, instructions for continued airworthiness) or interface functions (e.g., input/output processing, airframe thrust or shaft power demand).

• 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 components that maintain engine stability;

• 1. "Development" or "production""technology" for components unique to the adjustable flow path system and that maintain engine stability;

• 1. "Development""technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability.

• Note: 9E003.i. does not control "technology" for any of the following:

• 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.

• N.B. For "technology" "required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" SEE ALSO MILITARY GOODS CONTROLS.

9E101

• a. "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.

• b. "Technology" according to the General Technology Note for the "production" of 'UAV's specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.

Technical Note:

In 9E101.b. ‘UAV’ means unmanned aerial vehicle systems capable of a range exceeding 300 km.

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.

Technical Note:

In 9E102 ‘UAV’ means unmanned aerial vehicle systems capable of a range exceeding 300 km. ’

ANNEX II

‘ANNEX IV

LIST OF DUAL-USE ITEMS REFERRED TO IN ARTICLE 11(1) OF THIS REGULATION

The entries do not always cover the complete description of the item and the related notes in Annex I ¹⁴. Only Annex I provides for the complete description of the items.

The mention of an item in this Annex does not affect the application of the provisions concerning mass-market products in Annex I.

The terms appearing in straight double quotes are defined terms in the global definitions list of Annex I.

PART I

(possibility of National General Authorisation for intra-Union trade)

Items of stealth technology

1C001	Materials specially designed for absorbing electromagnetic radiations, or intrinsically conductive polymers. N.B. SEE ALSO 1C101
1C101	Materials and devices for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures, other than those specified in 1C001, usable in ‘missiles’, “missile” subsystems or unmanned aerial vehicles specified in 9A012. Note: 1C101 does not control materials if such goods are formulated solely for civil applications. Technical Note: In 1C101 ‘missiles’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
1D103	“Software” specially designed for analysis of reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures.
1E101	“Technology” according to the GTN for the “use” of goods specified in 1C101 or 1D103.
1E102	“Technology” according to the GTN for the “development” of “software” specified in 1D103.
6B008	Pulse radar cross-section measurement systems having transmit pulse widths of 100 ns or less and specially designed components therefor. N.B. SEE ALSO 6B108
6B108	Systems specially designed for radar cross section measurement usable for ‘missiles’ and their subsystems. Technical Note: In 6B108 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

Items of the Community strategic control

1A007	Equipment and devices, specially designed to initiate charges and devices containing “energetic materials”, by electrical means, as follows: N.B. SEE ALSO MILITARY GOODS CONTROLS, 3A229 AND 3A232. a. Explosive detonator firing sets designed to drive multiple controlled detonators specified in 1A007.b. below; b. Electrically driven explosive detonators as follows: 1. Exploding bridge (EB); 2. Exploding bridge wire (EBW); 3. Slapper; 4. Exploding foil initiators (EFI). Note: 1A007.b. does not control detonators using only primary explosives, such as lead azide.
1C239	High explosives, other than those specified in the Military Goods Controls, or substances or mixtures containing more than 2 % by weight thereof, with a crystal density greater than 1,8 g/cm3 and having a detonation velocity greater than 8 000  m/s.
1E201	“Technology” according to the General Technology Note for the “use” of goods specified in 1C239.
3A229	High-current pulse generators, as follows … N.B. SEE ALSO MILITARY GOODS CONTROLS
3A232	Multipoint initiation systems, other than those specified in 1A007 above, as follows… N.B. SEE ALSO MILITARY GOODS CONTROLS
3E201	“Technology” according to the General Technology Note for the “use” of equipment specified in 3A229 or 3A232.
6A001	Acoustics, limited to the following:
6A001.a.1.b.	Object detection or location systems, having any of the following: 1. A transmitting frequency below 5 kHz; 6. Designed to withstand …;
6A001.a.2.a.2.	Hydrophones … Incorporating …
6A001.a.2.a.3.	Hydrophones … Having any …
6A001.a.2.a.6.	Hydrophones … Designed for …
6A001.a.2.b.	Towed acoustic hydrophone arrays …
6A001.a.2.c.	Processing equipment, specially designed for real time application with towed acoustic hydrophone arrays, having “user-accessible programmability” and time or frequency domain processing and correlation, including spectral analysis, digital filtering and beamforming using Fast Fourier or other transforms or processes;
6A001.a.2.e.	Bottom or bay-cable hydrophone arrays, having any of the following: 1. Incorporating hydrophones …, or 2. Incorporating multiplexed hydrophone group signal modules …;
6A001.a.2.f.	Processing equipment, specially designed for real time application with bottom or bay cable systems, having “user-accessible programmability” and time or frequency domain processing and correlation, including spectral analysis, digital filtering and beamforming using Fast Fourier or other transforms or processes;
6D003.a.	“Software” for the “real-time processing” of acoustic data;
8A002.o.3.	Noise reduction systems designed for use on vessels of 1 000 tonnes displacement or more, as follows: b. ‘Active noise reduction or cancellation systems’, or magnetic bearings, specially designed for power transmission systems, and incorporating electronic control systems capable of actively reducing equipment vibration by the generation of anti-noise or anti-vibration signals directly to the source; Technical Note: ‘Active noise reduction or cancellation systems’ incorporate electronic control systems capable of actively reducing equipment vibration by the generation of anti-noise or anti-vibration signals directly to the source.
8E002.a.	“Technology” for the “development”, “production”, repair, overhaul or refurbishing (re-machining) of propellers specially designed for underwater noise reduction.

Items of the Community strategic control — Cryptanalysis — Category 5 Part 2

5A004.a.	Equipment designed or modified to perform ‘cryptanalytic functions’. Note: 5A004.a. includes systems or equipment, designed or modified to perform ‘cryptanalytic functions’ by means of reverse engineering. Technical Note: ‘Cryptanalytic functions’ are functions designed to defeat cryptographic mechanisms in order to derive confidential variables or sensitive data, including clear text, passwords or cryptographic keys.
5D002.a.	“Software” specially designed or modified for the “development”, “production” or “use” of any of the following: 3. Equipment as follows: a. Equipment specified in 5A004.a.;
5D002.c.	“Software” having the characteristics of, or performing or simulating the functions of, any of the following: 3. Equipment as follows: a. Equipment specified in 5A004.a.;
5E002.a.	Only “technology” for the “development”, “production” or “use” of the goods specified in 5A004.a, 5D002.a.3. or 5D002.c.3. above.

Items of the MTCR technology

7A117	“Guidance sets”, usable in “missiles” capable of achieving system accuracy of 3,33 % or less of the range (e.g., a ‘CEP’ of 10 km or less at a range of 300 km), except “guidance sets” designed for missiles with a range under 300 km or manned aircraft. Technical Note: In 7A117 ‘CEP’ (Circular Error Probable or Circle of Equal Probability) is a measure of accuracy, defined as the radius of the circle centred at the target, at a specific range, in which 50 % of the payloads impact.
7B001	Test, calibration or alignment equipment specially designed for equipment specified in 7A117 above. Note: 7B001 does not control test, calibration or alignment equipment for ‘Maintenance Level I’ or ‘Maintenance Level II’.
7B003	Equipment specially designed for the “production” of equipment specified in 7A117 above.
7B103	“Production facilities” specially designed for equipment specified in 7A117 above.
7D101	“Software” specially designed for the “use” of equipment specified in 7B003 or 7B103 above.
7E001	“Technology” according to the General Technology Note for the “development” of equipment or “software” specified in 7A117, 7B003, 7B103 or 7D101 above.
7E002	“Technology” according to the General Technology Note for the “production” of equipment specified in 7A117, 7B003 and 7B103 above.
7E101	“Technology” according to the General Technology Note for the “use” of equipment specified in 7A117, 7B003, 7B103 and 7D101 above.
9A004	Space launch vehicles capable of delivering at least a 500 kg payload to a range of at least 300 km. N.B. SEE ALSO 9A104. Note 1: 9A004 does not control payloads.
9A005	Liquid rocket propulsion systems containing any of the systems or components specified in 9A006 usable for space launch vehicles specified in 9A004 above or sounding rockets specified in 9A104 below. N.B. SEE ALSO 9A105 and 9A119.
9A007.a.	Solid rocket propulsion systems, usable for space launch vehicles specified in 9A004 above or sounding rockets specified in 9A104 below, with any of the following: N.B. SEE ALSO 9A119. a. Total impulse capacity exceeding 1,1 MNs;
9A008.d.	Components, as follows, specially designed for solid rocket propulsion systems: N.B. SEE ALSO 9A108.c. d. Movable nozzle or secondary fluid injection thrust vector control systems, usable for space launch vehicles specified in 9A004 above or sounding rockets specified in 9A104 below, capable of any of the following: 1. Omni-axial movement exceeding ± 5°; 2. Angular vector rotations of 20°/s or more; or 3. Angular vector accelerations of 40°/s2 or more.
9A104	Sounding rockets, capable of delivering at least a 500 kg payload to a range of at least 300 km. N.B. SEE ALSO 9A004.
9A105.a.	Liquid propellant rocket engines, as follows: N.B. SEE ALSO 9A119. a. Liquid propellant rocket engines usable in ‘missiles’, other than those specified in 9A005, integrated, or designed or modified to be integrated, into a liquid propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 MNs having a total impulse capacity equal to or greater than 1,1 MNs; except liquid propellant apogee engines designed or modified for satellite applications and having all of the following: 1. nozzle throat diameter of 20 mm or less; and 2. combustion chamber pressure of 15 bar or less.
9A106.c.	Systems or components, other than those specified in 9A006, usable in “missiles”, as follows, specially designed for liquid rocket propulsion systems: c. Thrust vector control sub-systems, except those designed for rocket systems that are not capable of delivering at least a 500 kg payload to a range of at least 300 km. Technical Note: Examples of methods of achieving thrust vector control specified in 9A106.c. are: 1. Flexible nozzle; 2. Fluid or secondary gas injection; 3. Movable engine or nozzle; 4. Deflection of exhaust gas stream (jet vanes or probes); or 5. Thrust tabs.
9A108.c.	Components, other than those specified in 9A008, usable in ‘missiles’ as follows, specially designed for solid rocket propulsion systems: c. Thrust vector control sub-systems, except those designed for rocket systems that are not capable of delivering at least a 500 kg payload to a range of at least 300 km. Technical Note: Examples of methods of achieving thrust vector control specified in 9A108.c. are: 1. Flexible nozzle; 2. Fluid or secondary gas injection; 3. Movable engine or nozzle; 4. Deflection of exhaust gas stream (jet vanes or probes); or 5. Thrust tabs.
9A116	Reentry vehicles, usable in “missiles”, and equipment designed or modified therefor, as follows, except for reentry vehicles designed for non-weapon payloads: a. Reentry vehicles; b. Heat shields and components therefor fabricated of ceramic or ablative materials; c. Heat sinks and components therefor fabricated of light-weight, high heat capacity materials; d. Electronic equipment specially designed for reentry vehicles.
9A119	Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, capable of delivering at least a 500 kg payload to a range of 300 km, other than those specified in 9A005 or 9A007.a. above
9B115	Specially designed “production equipment” for the systems, sub-systems and components specified in 9A005, 9A007.a., 9A008.d., 9A105.a., 9A106.c., 9A108.c., 9A116 or 9A119 above.
9B116	Specially designed “production facilities” for the space launch vehicles specified in 9A004, or systems, sub-systems, and components specified in 9A005, 9A007.a., 9A008.d., 9A104, 9A105.a., 9A106.c., 9A108.c., 9A116 or 9A119 above.
9D101	“Software” specially designed for the “use” of goods specified in 9B116 above.
9E001	“Technology” according to the General Technology Note for the “development” of equipment or “software” specified in 9A004, 9A005, 9A007.a., 9A008.d., 9B115, 9B116 or 9D101 above.
9E002	“Technology” according to the General Technology Note for the “production” of equipment specified in 9A004, 9A005, 9A007.a., 9A008.d., 9B115 or 9B116 above. Note: For “technology” for the repair of controlled structures, laminates or materials, see 1E002.f.
9E101	“Technology” according to the General Technology Note for the “development” or “production” of goods specified in 9A104, 9A105.a., 9A106.c., 9A108.c., 9A116 or 9A119 above.
9E102	“Technology” according to the General Technology Note for the “use” of space launch vehicles specified in 9A004, 9A005, 9A007.a., 9A008.d., 9A104, 9A105.a., 9A106.c., 9A108.c., 9A116, 9A119, 9B115, 9B116 or 9D101 above.

Exemptions:

Annex IV does not control the following items of the MTCR technology:

• 1. that are transferred on the basis of orders pursuant to a contractual relationship placed by the European Space Agency (ESA) or that are transferred by ESA to accomplish its official tasks;

• 1. that are transferred on the basis of orders pursuant to a contractual relationship placed by a Member State's national space organisation or that are transferred by it to accomplish its official tasks;

• 1. that are transferred on the basis of orders pursuant to a contractual relationship placed in connection with a Community space launch development and production programme signed by two or more European governments;

• 1. that are transferred to a State-controlled space launching site in the territory of a Member State, unless that Member State controls such transfers within the terms of this Regulation.

PART II

(no National General Authorisation for intra-Union trade)

Items of the CWC (Chemical Weapons Convention)

1C351.d.4.	Ricin
1C351.d.5.	Saxitoxin

Items of the NSG technology

All Category 0 of Annex I is included in Annex IV, subject to the following:

• — 0C001: this item is not included in Annex IV;

• — 0C002: this item is not included in Annex IV, with the exception of “special fissile materials” as follows:

• (a) separated plutonium;

• (b) “uranium enriched in the isotopes 235 or 233” to more than 20 %.

• — 0C003 only if for use in a “nuclear reactor” (within 0A001.a.);

• — 0D001 (“software”) is included in Annex IV except insofar as it relates to 0C001 or to those items of 0C002 that are excluded from Annex IV;

• — 0E001 (“technology”) is included in Annex IV except insofar as these related to 0C001 or to those items of 0C002 that are excluded from Annex IV.

1B226	Electromagnetic isotope separators designed for, or equipped with, single or multiple ion sources capable of providing a total ion beam current of 50 mA or greater. Note: 1B226 includes separators: a. Capable of enriching stable isotopes; b. With the ion sources and collectors both in the magnetic field and those configurations in which they are external to the field.
1B231	Tritium facilities or plants, and equipment therefor, as follows: a. Facilities or plants for the production, recovery, extraction, concentration, or handling of tritium; b. Equipment for tritium facilities or plants, as follows: 1. Hydrogen or helium refrigeration units capable of cooling to 23 K (– 250 °C) or less, with heat removal capacity greater than 150 W; 2. Hydrogen isotope storage or hydrogen isotope purification systems using metal hydrides as the storage or purification medium.
1B233	Lithium isotope separation facilities or plants, and equipment therefor, as follows: a. Facilities or plants for the separation of lithium isotopes; b. Equipment for the separation of lithium isotopes, as follows: 1. Packed liquid-liquid exchange columns specially designed for lithium amalgams; 2. Mercury or lithium amalgam pumps; 3. Lithium amalgam electrolysis cells; 4. Evaporators for concentrated lithium hydroxide solution.
1C012	Materials as follows: Technical Note: These materials are typically used for nuclear heat sources. b. “Previously separated” neptunium-237 in any form. Note: 1C012.b. does not control shipments with a neptunium-237 content of 1 g or less.
1C233	Lithium enriched in the lithium-6 (6Li) isotope to greater than its natural isotopic abundance, and products or devices containing enriched lithium, as follows: elemental lithium, alloys, compounds, mixtures containing lithium, manufactures thereof, waste or scrap of any of the foregoing. Note: 1C233 does not control thermoluminescent dosimeters. Technical Note: The natural isotopic abundance of lithium-6 is approximately 6,5 weight per cent (7,5 atom per cent).
1C235	Tritium, tritium compounds, mixtures containing tritium in which the ratio of tritium to hydrogen atoms exceeds 1 part in 1 000 , and products or devices containing any of the foregoing. Note: 1C235 does not control a product or device containing less than 1,48 × 103 GBq (40 Ci) of tritium.
1E001	“Technology” according to the General Technology Note for the “development” or “production” of equipment or materials specified in 1C012.b.
1E201	“Technology” according to the General Technology Note for the “use” of goods specified in 1B226, 1B231, 1B233, 1C233 or 1C235.
3A228	Switching devices, as follows: a. Cold-cathode tubes, whether gas filled or not, operating similarly to a spark gap, having all of the following characteristics: 1. Containing three or more electrodes; 2. Anode peak voltage rating of 2,5 kV or more; 3. Anode peak current rating of 100 A or more; and 4. Anode delay time of 10 μs or less; Note: 3A228 includes gas krytron tubes and vacuum sprytron tubes. b. Triggered spark-gaps having both of the following characteristics: 1. An anode delay time of 15 μs or less; and 2. Rated for a peak current of 500 A or more;
3A231	Neutron generator systems, including tubes, having both of the following characteristics: a. Designed for operation without an external vacuum system; and b. Utilizing electrostatic acceleration to induce a tritium-deuterium nuclear reaction.
3E201	“Technology” according to the General Technology Note for the “use” of equipment specified in 3A228 or 3A231 above.
6A203	Cameras and components, other than those specified in 6A003, as follows: a. Mechanical rotating mirror streak cameras, as follows, and specially designed components therefor: 1. Streak cameras with writing speeds greater than 0,5 mm per microsecond; b. Mechanical rotating mirror framing cameras, as follows, and specially designed components therefor: 1. Framing cameras with recording rates greater than 225 000 frames per second; Note: In 6A203.a. components of such cameras include their synchronising electronics units and rotor assemblies consisting of turbines, mirrors and bearings.
6A225	Velocity interferometers for measuring velocities exceeding 1 km/s during time intervals of less than 10 microseconds. Note: 6A225 includes velocity interferometers such as VISARs (Velocity interferometer systems for any reflector) and DLIs (Doppler laser interferometers).
6A226	Pressure sensors, as follows: a. Shock pressure gauges capable of measuring pressures greater than 10 GPa, including gauges made with manganin, ytterbium, and polyvinylidene fluoride (PVDF)/polyvinyl difluoride (PVF2); b. Quartz pressure transducers for pressures greater than 10 GPa.’