Source: https://www.law.cornell.edu/cfr/text/22/121.16
Timestamp: 2019-04-26 14:01:20+00:00

Document:
Section 121.16. Missile Technology Control Regime Annex.
22 CFR § 121.16 - Missile Technology Control Regime Annex.
Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets (see § 121.1, Cat. IV(a) and (b))) and unmanned air vehicle systems (including cruise missile systems, see § 121.1, Cat. VIII (a), target drones and reconnaissance drones (see § 121.1, Cat. VIII (a))) capable of delivering at least a 500 kg payload to a range of at least 300 km.
(c) Solid or liquid propellant rocket engines, having a total impulse capacity of 1.1 × 10 N-sec (2.5 × 10 lb-sec) or greater (see § 121.1, Cat. IV, (h)).
(f) Warhead safing, arming, fuzing, and firing mechanisms, except as provided in Note (1) below for those designed for systems other than those in Item 1 (see § 121.1, Cat. IV(h)).
(1) The exceptions in (b), (d), (e), and (f) above may be treated as Category II if the subsystem is exported subject to end use statements and quantity limits appropriate for the excepted end use stated above.
(2) CEP (circle of equal probability) is a measure of accuracy, and defined as the radius of the circle centered at the target, at a specific range, in which 50 percent of the payloads impact.
(3) A “guidance set” integrates the process of measuring and computing a vehicle's position and velocity (i.e., navigation) with that of computing and sending commands to the vehicle's flight control systems to correct the trajectory.
(v) Use of thrust tabs.
(f) Hybrid rocket motors and specially designed components therefor (see § 121.1, Cat. IV(h)).
(1) Item 3(a) engines may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for manned aircraft.
(2) In Item 3(C), “interior lining” suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials, e.g., carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior (see § 121.1, Cat. V(c)).
(3) In Item 3(c), “insulation” intended to be applied to the components of a rocket motor, i.e., the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.
(ii) 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 (1,000 psi).
(5) Item 3(e) systems and components may be exports as part of a satellite.
(iii) Compounds composed of fluorine and one or more of other halogens, oxygen or nitrogen.
(c) Other high energy density propellants such a Boron Slurry having an energy density of 40 × 10 joules/kg or greater.
(v) Polyfunctional aziridene amides with isophthalic, trimesic, isocyanuric, or trimethyladipic backbone also having a 2methyl or 2ethyl aziridine group (HX752, HX872 and HX877).
(1) Items (a) through (f) may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
(i) Drift rate is defined as the time rate of output deviation from the desired output. It consists of random and systematic components and is expressed as an equivalent angular displacement per unit time with respect to inertial space.
(ii) Stability is defined as standard deviation (1 sigma) of the variation of a particular parameter from its calibrated value measured under stable temperature conditions. This can be expressed as a function of time.
Flight control systems and “technology” as follows; designed or modified for the systems in Item 1.
(d) Design technology for integration of the flight control, guidance, and propulsion data into a flight management system for optimization of rocket system trajectory, (see § 121.1, Category IV (i)).
Items (a) and (b) may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
(2) Designed or modified for use with unmanned air vehicles covered by Item 1 (see § 121.1, Category XV(d)(4)).
(d) Electronic assemblies and components specifically designed for military use and operation at temperatures in excess of 125 degrees C, (see § 121.1, Category XI(a)(7)).
(e) Design technology for protection of avionics and electrical subsystems against electromagnetic pulse (EMP) and electromagnetic interference (EMI) hazards from external sources, as follows, (see § 121.1, Category XI (b)).
(3) Determination of hardening criteria for the above.
(1) Item 11 equipment may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
(3) In subitem (a), laser radar systems embody specialized transmission, scanning, receiving and signal processing techniques for utilization of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.
(iii) velocity resolution better than 3 meters per second.
(3) Software which processes post-flight, recorded data, enabling determination of vehicle position throughout its flight path (see § 121.1, Category IV(i)).
(b) Designed as ruggedized or “radiation hardened”.
Item 13 equipment may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
(iii) Incorporated “microcircuits” listed in (1), above.
Specially designed software, or specially designed software with related specially designed hybrid (combined analog/digital) computers, for modeling, simulation, or design integration of the systems in Item 1 and Item 2 (see § 121.1, Category IV(i) and Category XI(a)(6)).
The modelling includes in particular the aerodynamic and thermodynamic analysis of the system.
(b) Coatings, including paints, specially designed for reduced or tailored reflectivity or emissivity in the microwave, infrared or ultraviolet spectra, except when specially used for thermal control of satellites.
(c) Specially designed software or databases for analysis of signature reduction.
(d) Specially designed radar cross section measurement systems (see § 121.1, Category XI(a)(3)).
(a) “Radiation Hardened” “microcircuits” and detectors (see § 121.1, Category XI(c)(3) Note: This commodity has been formally proposed for movement to category XV(e)(2) in the near future).
(b) Radomes designed to withstand a combined thermal shock greater than 1000 cal/sq cm accompanied by a peak over pressure of greater than 50 kPa (7 pounds per square inch) (see § 121.1, Category IV(h)).
A detector is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. The following pages were removed from the final ITAR for replacement by DDTC's updated version § 6(l) of the Export Administration Act of 1979 (50 U.S.C. App. 2405(l)), as amended. In accordance with this provision, the list of MTCR Annex items shall constitute all items on the U.S. Munitions List in § 121.16.

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