(7) "Production facilities" means equipment and specially designed software therefor integrated into installations for "development" or for one or more phases of "production".

(8) "Production equipment" means tooling, templates, jigs, mandrels, moulds, dies, fixtures, alignment mechanisms, test equipment, other machinery and components therefor, limited to those specially designed or modified for "development" or for one or more phases of "production".

Part I

1.Complete ballistic missiles, space launch vehicles, sounding rockets, cruise missile and unmanned air vehicles that can be used to deliver at least a 500 kg payload to a range of at least 300 km as well as the specially designed production facilities therefor.

2.The following items usable in the systems in Item 1:

(1) Individual stages of a ballistic missile;

(2) Individual stages of a rocket;

(3) Reentry vehicles of missiles;

(4) Heat shields and components fabricated of ceramic materials used in Subitem (3);

(5) Heat shields and components fabricated of ablative materials used in Subitem (3);

(6) Heat sinks and components fabricated of light-weight, high heat capacity materials used in Subitem (3);

(7) Electronic equipment specially designed for Subitem (3);

(8) Storable liquid propellant rocket engines, having a thrust force of 90 kN or greater;

(9) Solid propellant rocket engines, having a total impulse capacity of 1100 kN•s or greater;

(10) Guidance sets capable of achieving system accuracy of 10 km or less (CEP) for ballistic missiles with a range of 300 km;

(11) Thrust vector control sub-systems;

(12) Warhead safing, arming, fuzing, and firing mechanisms;

(13) Production facilities and equipments designed for Subitems (1) to (12).

3.Interstage mechanisms for space launch vehicles and the specially designed production equipment therefor.

4.Rocket motor cases and the specially designed production equipment therefor.

5.Hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems specially designed or modified for the systems in Item 1 of Part I.

6.Attitude control equipment specially designed or modified for the systems in Item 1 of Part I.

7.Design technology for integration of air vehicle fuselage, propulsion system and lifting control surfaces to optimize aerodynamic performance throughout the flight regime of an unmanned air vehicle.

8.Design technology for integration of the guidance, flight control, and propulsion data into a flight management system for optimization of trajectory of ballistic missiles or space launch vehicles.

9.Passive interferometer equipment usable in the systems in Item 1.

10.Apparatus and devices designed or modified for the handling, control, activation and launching of the systems in Item 1.

11.Vehicles designed or modified for the transport, handling, control, activation and launching of the systems in Item 1.

12.Gravity meters, gravity gradiometers, and specially designed components therefor, for airborne or marine use, and having a static or operational accuracy of one milligal or better, with a time to steady-state registration of two minutes or less;

13.Precision tracking systems:

(1) Tracking systems which use a translator installed on the rocket system or unmanned air vehicle in conjunction with either surface or airborne references or navigation satellite systems to provide real-time measurements of in-flight position and velocity;

(2) Software which processes post-flight, recorded data, enabling determination of vehicle position throughout its flight path.

14.Structure specially designed for reduced radar reflectivity.

15.Structural material specially designed for reduced radar reflectivity.

16.Coatings specially designed for reduced radar reflectivity.

17.Coatings specially designed for reduced optical reflectivity or emissivity.

18.Production equipment, technology and specially designed software usable in Items 14 to 17 above.

19.Technology and specially designed software for reduced radar reflectivity, ultraviolet/infrared signatures or acoustic signatures.

Part II

1.Reentry Vehicle Components and Technology Thereof

(1) Design and manufacturing technology for ceramic heat shields;

(2) Design and manufacturing technology for ablative heat shields;

(3) Design and manufacturing technology for heat sinks and components thereof;

(4) Structure for protection against electromagnetic pulse (EMP) and X-rays and shock wave and combined blast and thermal effects:

(a) Radiation-hardened microcircuits and detectors;

(b) Hardened radome structure designed to withstand a combined thermal shock greater than 418 J/cm2 accompanied by a peak over pressure of greater than 50 kPa.

(5) Design technology for radiation hardenning;

(6) Design technology for hardened structure.

2.Propulsion Components and Technology Thereof

(1) Lightweight turbojet engines that are small and fuel efficient;

(2) Lightweight turbofan engines that are small and fuel efficient;

(3) Lightweight turbocompound engines that are small and fuel efficient;

(4) Ramjet engines;

(5) Scramjet engines;

(6) Pulse jet engines;

(7) Combined cycle engines;

(8) Devices to regulate combustion for the above Subitems (4) to (7);

(9) Liquid and slurry propellant control systems, and specially designed components thereof, designed or modified to operate in vibration environments of more than 10 g (RMS) between 20 Hz and 2,000 Hz:

(a) Servo valves designed for flow rates of 24 liters per minute or greater, at an absolute pressure of 7,000 kPa or greater, that have an actuator response time of less than 100 microseconds;

(b) Pumps, for liquid propellants, with shaft speeds equal to or greater than 8,000 RPM or with discharge pressures equal to or greater than 7,000 kPa.

(10) Production facilities specially designed for the above Subitems (1) to (9).

3.Liquid Propellants

(1) Hydrazine with a concentration of more than 70 percent;

(2) Unsymmetric dimethylhydrazine (UDMH);

(3) Monomethylhydrazine (MMH);

(4) Mixed amine;

(5) Dinitrogen tetroxide;

(6) Red Fuming Nitric Acid.