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- Point in Time (07/03/2003)
- Original (As adopted by EU)
Council Regulation (EC) No 1334/2000 of 22 June 2000 setting up a Community regime for the control of exports of dual-use items and technology (repealed)
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Version Superseded: 30/09/2004
Point in time view as at 07/03/2003.
There are currently no known outstanding effects for the Council Regulation (EC) No 1334/2000 (repealed), PART I.
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NB: SEE ALSO 1C101 U.K.
NB: SEE ALSO 6B108 U.K.
NB: SEE ALSO MILITARY GOODS CONTROLS U.K.
NB: SEE ALSO MILITARY GOODS CONTROLS U.K.
A transmitting frequency below 5 kHz ;
Designed to withstand …;
Incorporating hydrophones … or
Incorporating multiplexed hydrophone group signal modules …;
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;
Note: 7B001 does not control test, calibration or alignment equipment for Maintenance Level I or Maintenance Level II. U.K.
N.B.: SEE ALSO 9A104. U.K.
Note 1: 9A004 does not control payloads. U.K.
N.B.: SEE ALSO 9A105 and 9A119. U.K.
N.B.: SEE ALSO 9A119. U.K.
Total impulse capacity exceeding 1,1 MNs.
N.B.: SEE ALSO 9A108.c. U.K.
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°/s2 or more.
N.B.: SEE ALSO 9A004. U.K.
N.B.: SEE ALSO 9A119. U.K.
Liquid propellant rocket engines usable in "missiles", other than those specified in 9A005, having a total impulse capacity of 1,1 MNs or greater; 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.
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.
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.
Reentry vehicles;
Heat shields and components therefor fabricated of ceramic or ablative materials;
Heat sinks and components therefor fabricated of light-weight, high heat capacity materials;
Electronic equipment specially designed for reentry vehicles.
Note: For "technology" for the repair of controlled structures, laminates or materials, see 1E002.f. U.K.
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.
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