Textual Amendments
‘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 .
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.
Equipment specially designed for the ’production’ of equipment specified in 7A117 above .
‘Production facilities’ specially designed for equipment specified in 7A117 above .
‘Software’ specially designed for the ‘use’ of equipment specified in 7B003 or 7B103 above .
‘Technology’ according to the General Technology Note for the ’development’ of equipment or ‘software’ specified in 7A117, 7B003, 7B103 or 7D101 above .
‘Technology’ according to the General Technology Note for the ’production’ of equipment specified in 7A117, 7B003 and 7B103 above .
‘Technology’ to the General Technology Note for the ‘use’ of equipment specified in 7A117, 7B003, 7B103 and 7D101 above .
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. U.K.
Note 1: 9A004 does not control payloads. U.K.
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.
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.
Total impulse capacity exceeding 1,1 MNs;
Components, as follows, specially designed for solid rocket propulsion systems:
N.B.: SEE ALSO 9A108.c.
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:
Omni-axial movement exceeding ± 5 °;
Angular vector rotations of 20 °/s or more; or
Angular vector accelerations of 40 °/s 2 or more.
Sounding rockets, capable of delivering at least a 500 kg payload to a range of at least 300 km.
N.B.: SEE ALSO 9A004.
Liquid propellant rocket engines, as follows:
N.B.: SEE ALSO 9A119.
Liquid propellant rocket engines usable in ’missiles’, other than those specified in 9A005, 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 :
nozzle throat diameter of 20 mm or less; and
combustion chamber pressure of 15 bar or less.
Systems or components, other than those specified in 9A006, usable in ‘ missiles ’ , as follows, specially designed for liquid rocket propulsion systems:
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 .
Examples of methods of achieving thrust vector control specified in 9A106.c. are:
flexible nozzle;
fluid or secondary gas injection;
movable engine or nozzle;
deflection of exhaust gas stream (jet vanes or probes); or
thrust tabs.
Components, other than those specified in 9A008, usable in ‘ missiles ’ , as follows, specially designed for solid rocket propulsion systems:
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 .
Examples of methods of achieving thrust vector control specified in 9A108.c. are:
flexible nozzle;
fluid or secondary gas injection;
movable engine or nozzle;
deflection of exhaust gas stream (jet vanes or probes); or
thrust tabs.
Re-entry vehicles, usable in ’missiles’, and equipment designed or modified therefor, as follows, except for re-entry vehicles designed for non-weapon payloads :
re-entry vehicles;
heat shields and components therefor fabricated of ceramic or ablative materials;
heat sinks and components therefor fabricated of lightweight, high-heat capacity materials;
electronic equipment specially designed for re-entry vehicles.
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 .
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 .
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 .
‘Software’ specially designed for the ‘use’ of goods specified in 9B116 above .
‘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 .
‘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.
‘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 .
‘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 .
Annex IV does not control the following items of the MTCR technology:
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;
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;
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;
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.]