CATEGORY 9 – AEROSPACE AND PROPULSION
9 A - Equipment, assemblies and components
NB: |
For propulsion systems designed or intended to resist neutron radiation or transient ionizing radiation, see the list of war materials. |
9A001 - Aeronautical gas turbine engines having any of the following:
a. | incorporating any of the “technologies” specified in 9E003.a., 9E003.h. or paragraph 9E003.i.; Or
Note 1: |
Paragraph 9A001.a. does not control aeronautical gas turbine engines that have all of the following characteristics:
a. | certified by the civil aviation authorities of one or more EU Member States or States participating in the Wassenaar Arrangement; And |
b. | intended for the propulsion of an “aircraft” with non-military crew, for which one of the following documents has been issued by the civil aviation authorities of one or more EU Member States or States participating in the Wassenaar arrangement for the "aircraft", with this specific engine type:
1. | civil type certificate; Or |
2. | equivalent document recognized by the International Civil Aviation Organization (ICAO). |
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Note 2: |
Paragraph 9A001.a. does not control aeronautical gas turbine engines designed for auxiliary power units (APGs) approved by the civil aviation authorities of one or more EU Member States or States participating in the Wassenaar Arrangement . |
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b. | designed for the propulsion of an “aircraft” designed to cruise at or above Mach 1 for more than 30 minutes. |
9A002 - 'Marine gas turbine engines' having an ISO continuous power equal to or greater than 24,245 kW and a specific fuel consumption less than 0.219 kg/kWh in the power range of 35 to 100%, and their assemblies and components specially designed.
Note: |
The term 'marine gas turbine engine' includes industrial or aeronautically derived gas turbine engines which are adapted for the generation of electrical power or the propulsion of a vessel. |
9A003 - Specially designed assemblies or components incorporating any of the "technologies" specified in 9E003.a., 9E003.h. or 9E003i., for any of the following aeronautical gas turbine engines:
a. | specified in paragraph 9A001; Or |
b. | the design or production of which either originates in a non-EU member state or non-participating state in the Wassenaar arrangement , or of a provenance unknown to the manufacturer. |
9A004 - Space launchers, “space vehicles”, “space vehicle service modules”, “space vehicle payloads”, “space vehicle” onboard systems or equipment and ground equipment, as follows:
c. | “space vehicle service modules”; |
d. | “space vehicle payloads” including the property specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.c., 5A002. e., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e ., 6A008.k., 6A008.l. or 9A010.c.; |
e. | on-board systems or equipment specially designed for 'space vehicles' and having any of the following functions:
1. | 'control and telemetry data processing';
Note: |
For purposes of 9A004.e.1., 'control and telemetry data processing' includes the management, storage and processing of service module data. |
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2. | 'payload data processing'; Or
Note: |
For purposes of 9A004.e.2., 'payload data processing' includes the management, storage and processing of payload data. |
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3. | 'attitude and orbit control';
Note: |
For the purposes of 9A004.e.3., 'attitude and orbit control' includes sensing and actuation to determine and control the position and orientation of a "space vehicle" . |
NB: |
For equipment specially designed for military use, see the list of war materials. |
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f. | ground equipment specially designed for “space vehicles”, as follows:
1. | telemetry and remote control equipment; |
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9A005 - Liquid propellant rocket propulsion systems containing any of the systems or components specified in 9A006.
NB: |
SEE ALSO 9A105 AND 9A119. |
9A006 - Systems and components, specially designed for liquid propellant rocket propulsion systems, as follows:
NB: |
SEE ALSO 9A106, 9A108 AND 9A120. |
a. | cryogenic refrigerants, on-board dewars, cryogenic heat pipes or cryogenic systems specially designed for use in space vehicles and capable of limiting cryogenic fluid losses to less than 30% per year; |
b. | cryogenic tanks or closed-cycle refrigeration systems capable of ensuring temperatures equal to or less than 100 K (–173 °C) for “aircraft” capable of sustained flight at speeds above Mach 3, launch vehicles or “space vehicles”; |
c. | pasty hydrogen transfer or storage systems; |
d. | high pressure (greater than 17.5 MPa) turbopumps or pump components or their related gas generation or expansion cycle turbine drive systems; |
e. | high pressure thrust chambers (greater than 10.6 MPa) and their associated nozzles; |
f. | propellant storage devices operating on the principle of capillary retention or positive expulsion (i.e. with collapsible bladders); |
g. | liquid propellant injectors, the individual orifices of which have a diameter equal to or less than 0.381 mm (an area equal to or less than 1.14 × 10 – 3 cm 2 for non-circular orifices) specially designed for liquid propellant engines; |
h. | one-piece carbon-carbon thrust chambers or one-piece carbon-carbon ejection cones having a density greater than 1.4 g/cm 3 and a tensile strength greater than 48 MPa. |
9 A007 - Solid propellant rocket propulsion systems having any of the following characteristics:
NB: |
SEE ALSO 9A107 AND 9A119. |
a. | total pulse capacity greater than 1.1 MNs; |
b. | specific impulse equal to or greater than 2.4 kNs/kg when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa; |
c. | mass fractions per stage greater than 88% and total solid propellant loading greater than 86%; |
d. | components specified in 9A008; Or |
e. | propellant bonding and insulation systems using the principle of direct bonding to the envelope to provide a 'strong mechanical bond' or provide a barrier to chemical migration between the solid propellant and the envelope insulation material . Technical note: By 'strong mechanical bond' is meant a bonding force equal to or greater than the mechanical strength of the propellant. |
9A008 - Components specially designed for solid propellant rocket propulsion systems, as follows:
a. | propellant bonding and insulation systems using the principle of direct bonding to the envelope to provide a 'strong mechanical bond' or provide a barrier to chemical migration between the solid propellant and the envelope insulation material ; Technical note: By 'strong mechanical bond' is meant a bonding force equal to or greater than the mechanical strength of the propellant. |
b. | motor casings of wound “composite” fibers having a diameter greater than 0.61 m or 'structural efficiency ratios (PV/W)' greater than 25 km; Technical note: The 'structural efficiency ratio (PV/W)' is the product of the burst pressure (P) by the volume (V) of the envelope, divided by the total weight (W) of this envelope. |
c. | nozzles having thrust levels exceeding 45 kN or neck erosion rates less than 0.075 mm/s; |
d. | mobile nozzles or thrust vector control systems by secondary fluid injection capable of performing one of the following operations:
1. | omni-axial movement greater than ±5°; |
2. | angular vector rotations of 20°/s or more; Or |
3. | angular vector accelerations of 40°/s 2 or more. |
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9A009 - Solid propellant rocket propulsion systems having any of the following:
NB: |
SEE ALSO 9A109 AND 9A119. |
a. | total pulse capacity greater than 1.1 MNs; Or |
b. | thrust levels greater than 220 kN at external vacuum conditions. |
9A010 - Components, systems and structures, specially designed for launch vehicles, launch vehicle propulsion systems or “space vehicles”, as follows:
NB: |
SEE ALSO 1A002 AND 9A110. |
a. | components and structures, each exceeding 10 kg, and specially designed for launchers, made from any of the following materials:
1. | “composite” materials composed of “fibrous or filamentary materials” specified in 1C0010.e. and resins specified in 1C008 or 1C009.b.; |
2. | Metal “matrix” “composites” reinforced using:
a. | materials specified in 1C007; |
b. | “fibrous or filamentary materials” specified in paragraph 1C010; Or |
c. | aluminides specified in 1C002.a.; Or |
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3. | ceramic “matrix” “composite” materials specified in 1C007; |
Note: |
The above weight limitation is not applicable to front cones. |
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b. | components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009, made from any of the following materials:
1. | “fibrous or filamentary materials” specified in 1C0010.e. and resins specified in 1C008 or 1C009.b.; |
2. | Metal “matrix” “composites” reinforced using:
a. | materials specified in 1C007; |
b. | “fibrous or filamentary materials” specified in paragraph 1C010; Or |
c. | aluminides specified in 1C002.a.; Or |
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3. | ceramic “matrix” “composite” materials specified in 1C007; |
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c. | structural components and insulation systems, specially designed to actively control the dynamic response or distortion of “space vehicle” structures; |
d. | Liquid propellant pulse engines having a thrust-to-weight ratio equal to or greater than 1 kN/kg and a response time (time required to reach 90% of total rated thrust from start-up) less than 30 ms. |
9A011 - Ramjet engines, supersonic combustion or combined ramjet engines, and specially designed components therefor.
NB: |
SEE ALSO 9A111 AND 9A118. |
9A012 – “Unmanned aerial vehicles” (“UAVs”), unmanned “airships”, related equipment and components, as follows:
a. | Unmanned 'UAVs' and 'airships' designed to have controlled flight outside the direct 'natural' field of vision of the 'operator' and having any of the following characteristics:
1. | having all of the following characteristics:
a. | a maximum 'autonomy' greater than or equal to 30 minutes but less than 1 hour; And |
b. | designed to take off and have stable controlled flight with wind gusts equal to or greater than 46.3 km/h (25 knots); Or |
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2. | a maximum 'autonomy' equal to or greater than 1 hour; Technical notes:
1. |
For purposes of 9A012.a., an 'operator' is the person who initiates or directs the flight of the unmanned "UAV" or "airship". |
2. |
For the purposes of 9A012.a., 'range' is calculated in standard atmosphere (ISO 2533:1975), at sea level and in zero wind. |
3. |
For the purposes of 9A012.a., 'natural vision' means the vision of the human eye, with or without corrective lenses. |
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b. | related equipment and components, as follows:
3. | equipment or components specially designed to convert a crewed “aircraft” or crewed “airship” into an uncrewed “UAV” or “airship” specified in 9A012.a.; |
4. | reciprocating or rotary aerobic engines of the internal combustion type, specially designed or modified to propel unmanned “UAVs” or “airships” to altitudes above 15,240 meters (50,000 feet). |
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9A101 - Turbojets and turboprops other than those specified in 9A001, as follows:
a. | motors having the following two characteristics:
1. | 'maximum thrust' greater than 400 N (motor not installed) with the exception of motors certified for civil applications and whose thrust exceeds 8,890 N (motor not installed); And |
2. | specific consumption of 0.15 kg/N/h or less (measured at maximum continuous power under static conditions, at sea level, in ICAO standard atmosphere); |
Technical note: For the purposes of 9A101.a.1., 'maximum thrust' is the maximum thrust demonstrated by the manufacturer for the engine type not installed. The certified thrust value for civil applications will be equal to or less than the maximum thrust demonstrated by the manufacturer for the engine type. |
b. | engines designed or modified for use in “missiles” or unmanned aerial vehicles specified in 9A012 or 9A112.a. |
9A102 - 'Turboprop systems' specially designed for unmanned aerial vehicles specified in 9A012 or 9A112.a, and specially designed components therefor, providing 'maximum power' greater than 10 kW.
Note: |
Paragraph 9A102 does not control engines certified for civil applications. |
1. | For the purposes of 9A102, a 'turboprop system' includes all of the following:
b. | power transmission system for transmitting power to a propeller. |
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2. | For the purposes of 9A102, 'maximum power' is obtained with the engine uninstalled, under static conditions at sea level, in an ICAO standard atmosphere. |
9A104 - Sounding rockets, with a range of at least 300 km.
9A105 - Liquid propellant rocket engines or gel propellant rocket engines, as follows :
a. | liquid propellant rocket engines or gel propellant rocket engines usable in “missiles”, other than those specified in 9A005, integrated into, or designed or modified to be integrated into, a liquid propellant or gel propellant propulsion system having a total pulse equal to or greater than 1.1 MNs; |
b. | liquid propellant rocket engines or gel propellant rocket engines usable in complete rocket systems or unmanned aerial vehicles, with a range of at least 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 having a total impulse equal to or greater than 0.841 MNs. |
9A106 - Systems or components, other than those specified in 9A006, as follows, specially designed for liquid propellant rocket propulsion systems:
b. | rocket nozzles and combustion chambers, usable in “missiles”, in space launch vehicles specified in 9A004 or in sounding rockets specified in 9A104; |
c. | thrust vector control subsystems, usable in “missiles”; Technical note: Means for controlling the thrust vector referred to in paragraph 9A106.c. are, for example:
2. | secondary fluid or gas injection; |
3. | moving engine or nozzle; |
4. | deflection of the exhaust gas jet (jet deflection vanes or probes); Or |
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d. | liquid, suspended and gel propellant control systems (including oxidants), and specially designed components therefor, usable in "missiles", designed or modified to operate in a vibrational environment of more than 10 g effective between 20 Hz and 2kHz.
Note: |
Paragraph 9A106.d applies only to the following servovalves, pumps and gas turbines:
a. | servovalves designed for flow rates equal to or greater than 24 l/min, under an absolute pressure equal to or greater than 7 MPa, having an actuator response time less than 100 ms; |
b. | pumps, for liquid propellants, whose shaft rotates at a speed equal to or greater than 8,000 rpm in maximum operating mode or whose outlet pressure is equal to or greater than 7 MPa; |
c. | gas turbines, for liquid propellant turbopumps, the shaft of which rotates at a speed equal to or greater than 8,000 rpm in maximum operating mode; |
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e. | combustion chambers and nozzles, usable in "missiles", in space launch vehicles specified in 9A004 or in sounding rockets specified in 9A104. |
9A107 - Solid propellant rocket engines, usable in complete rocket systems or unmanned aerial vehicles, with a range of at least 300 km, other than those specified in 9A007, having a total impulse capacity equal to or greater than 0.841 MNs.
9A108 - Components, other than those specified in 9A008, as follows, specially designed for solid propellant rocket propulsion systems:
a. | rocket motor casings and their “insulation” components, usable in “missiles”, in space launchers specified in paragraph 9A004 or sounding rockets specified in paragraph 9A104; |
b. | rocket nozzles, usable in “missiles”, in space launch vehicles specified in 9A004 or in sounding rockets specified in 9A104; |
c. | thrust vector control subsystems, usable in “missiles”. Technical note: Means for controlling the thrust vector referred to in paragraph 9A108.c. are, for example:
2. | secondary fluid or gas injection; |
3. | moving engine or nozzle; |
4. | deflection of the exhaust gas jet (jet deflection vanes or probes); Or |
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9A109 - Hybrid rocket engines and their specially designed components as follows:
a. | hybrid rocket engines, usable in complete rocket systems or unmanned aerial vehicles, with a range of at least 300 km, other than those specified in 9A009, having a total impulse capacity equal to or greater than 0.841 MNs , and their specially designed components; |
b. | components specially designed for hybrid rocket motors specified in 9A009 and usable in “missiles”. |
NB: |
SEE ALSO 9A009 AND 9A119. |
9A110 - Composite structures, laminated products, and products made therefrom, other than those specified in 9A010, specially designed for use in 'missiles' or in subsystems specified in 9A005, 9A007, paragraph 9A105, paragraph 9A106.c., paragraph 9A107, paragraph 9A108.c., paragraph 9A116 or paragraph 9A119.
Technical note: In paragraph 9A110, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems, with a range of at least 300 km.
9A111 - Pulse reactors usable in "missiles" and unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.
NB: |
SEE ALSO 9A011 AND 9A118. |
9A112 - “Unmanned aerial vehicles” (“UAVs”), other than those specified in 9A012, as follows:
a. | “unmanned aerial vehicles” (“UAVs”) with a range of 300 km; |
b. | “unmanned aerial vehicles” (“UAVs”) having all of the following characteristics:
1. | having one of the following characteristics:
a. | autonomy of control and navigation; Or |
b. | possibility of controlled flight outside the direct field of vision of a human operator; And |
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2. | having one of the following characteristics:
a. | integration of an aerosol spraying system/device with a capacity greater than 20 liters; Or |
b. | designed or modified to incorporate an aerosol spray system/device having a capacity greater than 20 liters. |
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Technical notes:
1. |
An aerosol is particulate matter or liquid other than fuel, byproducts or additives, which forms the "payload" that will be dispersed into the atmosphere. Pesticides sprayed on crops and chemical powders used to seed clouds are examples of aerosols. |
2. |
An aerosol spray system contains all the devices (mechanical, electrical, hydraulic, etc.) necessary for the storage and dispersion of the aerosol into the atmosphere. This includes the possibility of aerosol injection into combustion exhaust gases and propeller wash. |
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9A115 – Launch support equipment, as follows:
a. | apparatus and devices for handling, controlling, operating and launching, designed or modified for use in space launch vehicles specified in 9A004, in sounding rockets specified in 9A104 or in unmanned aerial vehicles specified in 9A104 paragraph 9A012 or paragraph 9A112.a.; |
b. | vehicles for transport, handling, control, operation and launch, designed or modified for use in space launch vehicles specified in 9A004 or in sounding rockets specified in 9A104. |
9A116 - Re-entry vehicles, usable in "missiles", and their specially designed or modified equipment, as follows:
b. | heat shields and their components made of ceramic or ablative materials; |
c. | heat sinks and their components made of lightweight materials with high thermal capacity; |
d. | electronic equipment specially designed for re-entry vehicles. |
9A117 - Stage separation, separation and interstage separation devices, usable in “missiles”.
9A118 - Combustion control devices for use in engines specified in 9A011 or 9A111 that may be used in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a.
9A119 - Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, with a range of at least 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109 .
9A120 - Liquid propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or "other liquid propellants", used in rocket systems capable of carrying a payload of at least 500 kg up to a range of at least 300 km.
Note: |
In paragraph 9A120, 'other liquid propellants' includes, but is not limited to, propellants specified in the War Material List. |
9A121 - Specially designed umbilical and interstage electrical connectors for "missiles", space launch vehicles specified in 9A004, or sounding rockets specified in 9A104.
Technical note: Interstage connectors specified in 9A121 also include electrical connectors installed between the "missile", space launch vehicle or sounding rocket and their payload.
9A350 - Spray or fogging systems, specially designed or modified to equip aircraft, “lighter-than-air vehicles” or unmanned aerial vehicles, and specially designed components therefor, as follows:
a. | complete spray or nebulization systems capable of dispersing, from a liquid suspension, an initial droplet of less than 50 μm “VMD” at a flow rate greater than two liters per minute; |
b. | booms or spray networks of aerosol generation units capable of dispersing, from a liquid suspension, an initial droplet of less than 50 μm “VMD” at a flow rate greater than two liters per minute; |
c. | aerosol generation units specially designed to equip systems specified in 9A350.a. and B.
Note: |
Aerosol generating units are devices specially designed or modified to equip aircraft, for example nozzles, rotary atomizers and similar devices. |
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Note: |
Paragraph 9A350 does not control spray or nebulizer systems and components that are proven not to be capable of dispersing biological agents in the form of infectious aerosols. |
1. | The droplet size for spray equipment or nozzles specially designed for use on aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles must be measured using one of the following two methods:
b. | direct laser diffraction method. |
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2. | In 9A350, “VMD” means volume median diameter and, for aqueous systems, this is equivalent to mass median diameter (MMD). |
9 B - Testing, inspection and production equipment
9B001 - Equipment, tooling or fixtures, specially designed for the manufacture of moving blades, fixed blades or cast end shrouds of gas turbine engines, as follows:
a. | directed solidification or single-crystal molding equipment; |
b. | molding tools, made of refractory metals or ceramics, as follows;
3. | combinations of cores and casings (molds); |
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c. | additive manufacturing equipment for monocrystalline or directed solidification structures. |
9B002 - Online (real-time) control systems, instruments (including sensors) or automated data acquisition and processing equipment, having all of the following characteristics:
a. | specially designed for the “development” of gas turbine engines, their assemblies or components; And |
b. | incorporating “technologies” specified in 9E003.h or 9E003.i. |
9B003 - Equipment specially designed for the "production" or testing of gas turbine brush seals designed to operate at seal tip velocities greater than 335 m/s and temperatures greater than 773 K (500 °C), and their specially designed parts or accessories.
9B004 - Tools, dies or fixtures for solid-state assembly of “superalloy”, titanium or intermetallic blade-disc connections specified in 9E003.a.3. or 9E003.a.6., for gas turbines.
9B005 - Online (real-time) control systems, instruments (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following devices:
a. | wind tunnels designed for speeds equal to or greater than Mach 1.2;
Note: |
Paragraph 9B005.a. does not apply to wind tunnels specially designed for teaching purposes and having a 'test vein dimension' (measured laterally) less than 250 mm. Technical note: The 'test vein size' is either the diameter of the circle, the side of the square, or the length of the rectangle, measured at the largest part of the vein. |
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b. | devices for simulating flow environments at speeds greater than Mach 5, including heated gas shock tubes, plasma arc wind tunnels, shock wave tubes, shock wave wind tunnels, gas blowers and light gas cannons; Or |
c. | wind tunnels or devices, other than two-dimensional ones, capable of simulating flow at a Reynolds number greater than 25 × 10 6 . |
9B006 - Specially designed acoustic vibration testing equipment capable of producing sound pressure at levels equal to or greater than 160 dB (referred to 20 μΡa), with a rated output power equal to or greater than 4 kW, at a temperature of the test cell above 1273 K (1000 °C), and their specially designed quartz heaters.
9B007 - Equipment specially designed for testing the integrity of rocket engines using non-destructive testing techniques other than planar x-ray analysis or basic physical or chemical analysis.
9B008 - Direct wall coating friction measurement transducers specially designed to operate at a total (stagnation) temperature of the test flow greater than 833 K (560 °C).
9B009 - Tooling specially designed for the production of powder metallurgical turbine engine rotor components capable of operating at stress levels equal to or greater than 60% of the ultimate breaking strength (UTS) and at temperatures metal equal to or greater than 873 K (600 °C).
9B010 - Equipment specially designed for the production of goods specified in paragraph 9A012.
9B105 - 'Aerodynamic test facilities' designed for speeds equal to or greater than Mach 0.9, usable for 'missiles' and their subsystems.
Note: |
Paragraph 9B105 does not control wind tunnels designed for speeds equal to or less than Mach 3 with a 'test crossing vein dimension' equal to or less than 250 mm. |
1. | In paragraph 9B105, 'aerodynamic test facilities' include wind tunnels and shock wave wind tunnels intended for the study of air flow over objects. |
2. | In the note to paragraph 9B105, the 'dimension of the test crossing vein' is either the diameter of the circle, or the side of the square, or the length of the rectangle, or the principal axis of the ellipse measured at the largest part of the vein. The 'test crossing vein' is the part perpendicular to the direction of flow. |
3. | In paragraph 9B105, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km. |
9B106 – Environmental chambers and anechoic chambers, as follows:
a. | environmental chambers having all of the following characteristics:
1. | capable of simulating any of the following flight conditions:
a. | altitude equal to or greater than 15 km; Or |
b. | thermal amplitude ranging from less than 223 K (– 50 °C) to more than 398 K (+ 125 °C); And |
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2. | incorporating, or 'designed or modified' to incorporate, a vibrating unit or other vibration testing equipment to produce vibration environments equal to or greater than 10 g RMS, measured bare table, between 20 Hz and 2 kHz while communicating forces equal to or greater than 5 kN; |
Technical notes:
1. |
Paragraph 9B106.a.2. describes systems capable of creating a vibrational environment with a simple wave (e.g. a sine wave) and systems capable of creating a broadband random vibration (i.e. a power spectrum). |
2. |
In 9B106.a.2., the term 'designed or modified' means that the environmental chamber provides suitable interfaces (e.g., closure devices) to accommodate a vibrating unit or other environmental protection equipment. vibration test, as specified in paragraph 2B116. |
3. |
In paragraph 9B106.a.2., the term 'bare table' means a flat table or surface without fixtures or equipment. |
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b. | environmental chambers capable of simulating the following flight conditions:
1. | acoustic environments at a total noise pressure level of 140 dB (compared to 20 μΡa) or more or with a total sound power output level of 4 kW or more; And |
2. | altitude equal to or greater than 15 km; Or |
3. | thermal amplitude ranging from less than 223 K (– 50 °C) to more than 398 K (+ 125 °C). |
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9B115 - “Production equipment” specially designed for systems, subsystems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A105 to 9A109, 9A111 and 9A116 to 9A120.
9B116 - “Production support equipment” specially designed for space launch vehicles specified in 9A004, for systems, subsystems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A104 to 9A109, 9A111 and 9A116 to 9A120, or for 'missiles'.
Technical note: In paragraph 9B116, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km.
9B117 - Test stands and brake test stands for solid or liquid propellant rockets and rocket engines, having any of the following characteristics:
a. | capable of supporting a thrust greater than 68 kN; Or |
b. | capable of simultaneously measuring the three components of thrust. |
9C - Materials
9C108 - Bulk “insulation” material and “liners”, other than those specified in 9A008, for use in rocket motor casings for use in “missiles” or specially designed for solid propellant rocket motors specified in 9A007 or 9A107.
Technical note: In 9C108, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems with a range of at least 300 km.
9C110 - Resin prepreg fibers and metal-coated fibrous preforms for composite structures, laminates and manufactured products specified in 9A110, made with an organic or metallic matrix using fibrous or filamentary reinforcements having a "specific tensile strength" greater than 7.62 × 10 4 m and a “specific module” greater than 3.18 × 10 6 m.
NB: |
SEE ALSO 1C010 AND 1C210. |
Note: |
Paragraph 9C110 applies only to resin prepreg fibers using a resin whose glass transition temperature (Tg), determined according to ASTM D4065 or an equivalent standard, is greater than 418 K (145 °C) after polymerization. |
9D - Software
9D001 - “Software” specially designed or modified for the “development” of equipment or “technology”, specified in 9A001 to 9A119, subcategory 9B or 9E003.
9D002 - “Software” specially designed or modified for the “production” of equipment specified in paragraphs 9A001 to 9A119 or in subcategory 9B.
9D003 - “Software” incorporating “technologies” specified in 9E003.h. and used in “FADEC systems” for systems covered in subcategory 9A or equipment covered in subcategory 9B.
9D004 – Other “software”, as follows:
a. | 2D or 3D viscous flow “software”, validated with test data obtained in wind tunnels or in flight, necessary for detailed modeling of flow in engines; |
b. | “software” for testing aeronautical gas turbine engines or their assemblies or components, specially designed for real-time data acquisition, compression and analysis, and capable of feedback control, including adjustments dynamics to be applied to the equipment undergoing the test or to the test conditions(s), during the test; |
c. | “Software” specially designed to control the directed solidification or growth of single-crystal materials in equipment specified in 9B001.a. or 9B001.c.; |
e. | “software” specially designed or modified for the operation of goods specified in 9A012; |
f. | “software” specially designed for the design of internal cooling channels of moving blades, fixed blades and “end shrouds” of aeronautical gas turbines; |
g. | “software” having all of the following characteristics:
1. | specially designed to predict aerothermal, aeromechanical and combustion conditions in aeronautical gas turbine engines; And |
2. | whose theoretical model predictions of aerothermal, aeromechanical and combustion conditions have been validated on the basis of real performance data from aeronautical gas turbine engines (experimental or series). |
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9D005 - “Software” specially designed or modified for the operation of goods specified in 9A004.e. or 9A004.f.
9D101 - “Software” specially designed or modified for the “use” of property specified in 9B105, 9B106, 9B116 or 9B117.
9D103 - "Software" specially designed for modeling, simulation or integration of space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles", or subsystems specified in 9A005, paragraph 9A007, paragraph 9A105, paragraph 9A106.c., paragraph 9A107, paragraph 9A108.c., paragraph 9A116 or paragraph 9A119.
Note: |
“Software” specified in 9D103 remains subject to control 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. , paragraph 9A009.a., paragraph 9A010.d., paragraph 9A011, paragraph 9A101, paragraph 9A102, paragraph 9A105, paragraph 9A106.d., paragraph 9A107, paragraph 9A109, paragraph 9A111, paragraph 9A115.a., paragraph 9A117 or paragraph 9A118; |
b. | “software” specially designed or modified for the operation or maintenance of subsystems or equipment specified in 9A008.d., 9A106.c., 9A108.c. and 9A116.d. |
9D105 - “Software” specially designed or modified to coordinate the operation of more than one subsystem, other than those specified in 9D004.e., in space launch vehicles specified in 9A004, sounding rockets specified in 9A104, or the 'missiles'.
Technical note: In paragraph 9D105, the term 'missile' means complete rocket systems and unmanned aerial vehicle systems, with a range of at least 300 km.
9E - Technology
Note: |
The “development” or “production” “technology” referred to in paragraphs 9E001 to 9E003 for gas turbine engines remains subject to control when used for repair or overhaul. Excluded from inspection: technical data, drawings or documentation intended for maintenance activities directly related to the calibration, removal or replacement of damaged or unusable inline interchangeable units, including the replacement of entire motors or of engine modules. |
9E001 - “Technology”, as defined in the General Technology Note, for the “development” of equipment or “software” specified in 9A001.b., 9A004 to 9A012, 9A350 or subcategories 9B or 9D.
9E002 - “Technology”, as defined in the General Technology Note, for the “production” of equipment specified in 9A001.b., 9A004 to 9A011, 9A350 or subcategory 9B.
NB: |
For “technology” for repairing structures, rolled products or controlled materials, materials, see 1E002.f. |
9E003 - Other “technologies”, as follows:
a. | “technology” “necessary” for the “development” or “production” of any of the following gas turbine engine components or systems:
1. | moving blades, fixed blades or gas turbine “end shrouds” obtained by directed solidification (SD) or single crystals of alloys and having (in the 001 orientation of the Miller index) a service life exceeding 400 hours at 1273 K (1000 °C) under a stress of 200 MPa, based on average values of this property; |
2. | combustion chambers having any of the following characteristics:
a. | thermally decoupled liners designed to operate at a 'combustion chamber outlet temperature' above 1883 K (1610°C); |
c. | non-metallic casings; Or |
d. | liners designed to operate at a 'combustion chamber outlet temperature' greater than 1883 K (1610°C) and having orifices conforming to the parameters specified in 9E003.c.; |
Note: |
The “required” “technology” for ports specified in 9E003.a.2. is limited to the derivation of the geometry and location of the orifices. |
Technical note: The 'combustion chamber outlet temperature' corresponds to the volume average of the total temperature of the gas flow (stagnation) between the exit plane of the combustion chamber and the leading edge of the guide vanes of the turbine (c i.e. measured at engine station T40 as defined by SAE ARP 755A) when the engine is operating in 'stationary mode' at the certified maximum continuous operating temperature.
NB: |
See 9E003.c. for the “technology” “required” for manufacturing the cooling ports |
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3. | following components:
a. | made from organic “composites” designed to perform above 588 K (315 °C); |
b. | made from one of the following materials:
1. | Metal “matrix” “composites” reinforced using:
a. | materials specified in 1C007; |
b. | “fibrous or filamentary materials” specified in paragraph 1C010; Or |
c. | aluminides specified in 1C002.a.; Or |
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2. | Ceramic “matrix” “composites” specified in 1C007; Or |
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c. | stators, fixed blades, movable blades, end fairings, one-piece bladed rings, one-piece bladed discs or 'separator ducts' having all of the following characteristics:
1. | not specified in 9E003.a.3.a.; |
2. | designed for compressors or blowers; And |
3. | manufactured from materials specified in 1C010.e. and with the resins specified in paragraph 1C008. |
Technical note: A 'splitter duct' provides the initial separation of airflow between the bypass and the central sections of the engine. |
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4. | uncooled moving blades, fixed blades or 'tip shrouds' designed to operate at a 'gas flow temperature' of 1 373 K (1 100 °C) or more; |
5. | cooled moving blades, fixed blades, "end shrouds", other than those specified in 9E003.a.1., designed to operate at a 'gas flow temperature' equal to or greater than 1693 K ( 1420°C); Technical notes:
1. |
'Gas flow temperature' is the volume average total gas flow temperature (stagnation) at the leading edge of the turbine components when the engine is operating in 'steady mode' at continuous operating temperature and maximum certified or indicated. |
2. |
The term 'steady mode' defines the operating conditions of the engine, when the engine parameters, such as thrust/power, revolutions and others, do not fluctuate appreciably, when the ambient air temperature and air pressure engine intake are constant. |
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6. | blade-disc connections using solid-state assembly; |
7. | gas turbine engine components using “diffusion welding” “technology” specified in 2E003.b.; |
8. | 'damage tolerant' gas turbine engine rotor components using powder metallurgical materials specified in 1C002.b.; Or Technical note: 'Damage tolerant' components are designed using methodology and rationales to predict and limit crack growth. |
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b. | “technology” “necessary” for the “development” or “production” of any of the following:
1. | wind tunnel models, equipped with sensors without intrusion and provided with a means of transmitting data from the sensors to the data capture system; Or |
2. | propeller blades or turboprops made of “composite” materials capable of absorbing more than 2,000 kW at flight speeds above Mach 0.55; |
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c. | “technology” “required” for the manufacture of cooling ports in gas turbine engine components incorporating any of the “technologies” specified in 9E003.a.1., 9E003.a.2. or 9E003.a.5., and having one of the following characteristics:
1. | having all of the following characteristics:
a. | 'minimum cross section of a surface' less than 0.45 mm 2 ; |
b. | 'orifice aspect ratio' greater than 4.52; And |
c. | 'angle of incidence' equal to or less than 25°; Or |
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2. | having all of the following characteristics:
a. | 'minimum cross section of a surface' less than 0.12 mm 2 ; |
b. | 'orifice aspect ratio' greater than 5.65; And |
c. | 'angle of incidence' greater than 25°; |
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Note: |
Paragraph 9E003.c. does not refer to the "technology" for the manufacture of cylindrical orifices with constant radius which pass through the assembly without interruption, and penetrate then exit through the external surfaces of the components. |
Technical notes:
1. | For the purposes of 9E003.c., 'minimum surface cross-section' means the area of the orifice on the plane perpendicular to the axis of the orifice. |
2. | For the purposes of 9E003.c., 'port aspect ratio' means the nominal length of the orifice axis, divided by the square root of its 'minimum surface cross-section' . |
3. | For the purposes of 9E003.c., 'angle of incidence' is the acute angle measured between the plane tangential to the airfoil and the axis of the port at the point where the axis of the port penetrates the bearing surface. |
4. | Orifice manufacturing techniques specified in 9E003.c. include “laser”, water jet, electrochemical machining (ECM) or electrical discharge machine methods. |
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d. | “technology” “necessary” for the “development” or “production” of power transmission systems of helicopters or tilt-wing or tilt-rotor aircraft; |
e. | “technology” for the “development” or “production” of propulsion systems for reciprocating diesel-powered land vehicles having all of the following characteristics:
1. | 'parallelepiped volume' equal to or less than 1.2 m 3 ; |
2. | aggregate output power above 750 kW, based on Directive 80/1269/EEC or ISO 2534 or their national equivalents; And |
3. | power density greater than 700 kW/m 3 of the 'parallelepiped volume'; |
Technical note: The 'parallelepiped volume' referred to in paragraph 9E003.e. is the product of three perpendicular dimensions measured as follows:
length | : | the length of the crankshaft from the front flange to the flap face; | width | : | the largest of the following dimensions:
a. | exterior dimension from valve cover to valve cover; |
b. | dimensions of the outer edges of the cylinder heads; Or |
c. | flywheel housing diameter; |
| height | : | the largest of the following dimensions:
a. | dimensions of the crankshaft axis to the surface of the valve cover (or cylinder head) plus twice the stroke; Or |
b. | diameter of the flywheel housing. |
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f. | “technology” “required” for the “production” of components specially designed for high performance diesel engines, as follows:
1. | “technology” “necessary” for the “production” of engine systems comprising all of the following components, employing ceramic materials specified in 1C007:
d. | one or more other components (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors); |
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2. | “technology” “necessary” for the “production” of single-stage turbocharging systems, and having all of the following characteristics:
a. | operating at compression ratios of 4:1 or greater; |
b. | mass flow rate in the range of 30 to 130 kg per minute; And |
c. | variable flow area in compressor or turbine; |
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3. | “technology” “required” for the “production” of fuel injection systems having a specially designed multi-fuel capability (e.g. diesel or propellant) covering a viscosity range from that of diesel [2.5 cSt to 310, 8 K (37.8 °C)] to that of gasoline [0.5 cSt at 310.8 K (37.8 °C)], and having all of the following characteristics:
a. | quantity injected exceeding 230 mm 3 per injection per cylinder; And |
b. | means of electronic control of the characteristics of the switching regulator specially designed to automatically provide a constant torque, depending on the properties of the fuel, through appropriate sensors; |
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g. | 'technology' 'necessary' for the 'development' or 'production' of 'high performance diesel engines' for the lubrication of cylinder walls by solid, gaseous or liquid film (or combinations thereof) and enabling operation at temperatures above 723 K (450 °C) measured on the cylinder wall at the upper end of the piston's uppermost ring stroke. Technical note: The term 'high performance diesel engine' means a diesel engine having a specified average effective brake pressure of 1.8 MPa or more at a rotational speed of 2300 rpm, provided that the rated speed is 2300 rpm or more. |
h. | “technology” for “FADEC systems” of gas turbine engines, as follows:
1. | “development” “technology” aimed at establishing operational requirements for components necessary for the “FADEC system” to adjust engine thrust or power output (e.g. feedback sensor accuracies and time constants, rate fuel valve oscillation); |
2. | “development” or “production technology” for control and diagnostic components specific to the “FADEC system” and used to adjust engine thrust or power output; |
3. | “development technology” for control law algorithms, including “source codes” specific to the “FADEC system” and used to adjust engine thrust or power output; |
Note: |
Paragraph 9E003.h. does not cover technical data relating to the integration of motorized "aircraft" required by the civil aviation services of one or more EU Member States or States participating in the Wassenaar Arrangement with a view to their publication and general use by airlines (e.g. installation manuals, operating instructions, instructions for continued airworthiness) or interface functions (e.g. I/O processing, airframe thrust or output power demand). |
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i. | “technology” intended for flow control systems designed to maintain engine stability in the case of gas generation turbines, fan or work turbines or ejection nozzles, as follows:
1. | “development” “technology” aimed at establishing operational requirements for components that maintain engine stability; |
2. | “development” or “production” “technology” for components that are specific to the vein adjustment system and maintain engine stability; |
3. | “development technology” for the control law algorithms, including “source codes”, which are specific to the vein adjustment system and maintain the stability of the motor. |
Note: |
Paragraph 9E003.i. does not control the “technology” of “development” or “production” of any of the following:
b. | variable pitch blowers or turboprops; |
c. | variable compressor blades; |
d. | compressor discharge valves; Or |
e. | adjustable vein geometry for the diverter. |
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j. | “technology” “necessary” for the “development” of wing folding systems designed for fixed-wing “aircraft” equipped with gas turbine engines.
NB: |
For the “technology” “necessary” for the “development” of wing folding systems designed for fixed-wing “aircraft”, see also the list of war materiel. |
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9E101 -
a. | “Technology” as defined in the General Technology Note for the “development” of products specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or paragraphs 9A115 to 9A121. |
b. | “Technology”, as defined in the General Technology Note, for the “production” of “UAVs” specified in 9A012 or products specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or paragraphs 9A115 to 9A121. Technical note: In 9E101.b., the term 'UAV' means unmanned aerial vehicle systems with a range exceeding 300 km. |
9E102 - “Technology”, as defined in the General Technology Note, for the “use” of space launch vehicles specified in 9A004, products specified in 9A005 to 9A011, “UAVs” specified in 9A012 or products specified in paragraphs 9A101, 9A102, 9A104 to 9A111, 9A112.a. and paragraphs 9A115 to 9A121, 9B105, 9B106, 9B115, 9B116, 9B117, 9D101 or 9D103.
Technical note: In 9E102, the term 'UAV' means unmanned aerial vehicle systems with a range exceeding 300 km."
( 1 ) Manufacturers who calculate positioning accuracy in accordance with ISO 230-2:1997 or ISO 230-2:2006 must consult the competent authorities of the Member State in which they are established. ( 2 ) Manufacturers who calculate positioning accuracy in accordance with ISO 230-2:1997 or ISO 230-2:2006 must consult the competent authorities of the Member State in which they are established. ( *1 ) Numbers in parentheses refer to notes after the table. |
