Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p241
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 687323–690141

Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in "missiles", designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz.
Note: The only servo valves, pumps and gas turbines specified by 9A106.d., are the following:
a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms;
b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8,000 r.p.m. at the maximum operating mode or with discharge pressures equal to or greater than 7 MPa.
c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8,000 rpm at the maximum operating mode.
Note: Certain items specified in 9A106 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.
9. A. 107. Solid propellant rocket motors, usable in complete rocket systems or "unmanned aerial vehicles", capable of a range of 300 km, other than those specified by 9A007, having total impulse capacity equal to or greater than 0.841 MNs.
N.B.: SEE ALSO 9A119.
9. A. 108. Components, other than those specified by 9A008, as follows, specially designed for solid rocket propulsion systems:
a. Rocket motor cases and "insulation" components therefor, usable in rocket motors specified by 9A107;
9. A. 108. b. Rocket nozzles, usable in rocket engines or rocket motors specified by 9A107;
c. Thrust vector control sub‑systems, usable in "missiles".
Technical Note:
Examples of methods of achieving thrust vector control specified by 9A108.c. are:
1. Flexible nozzle;
2. Fluid or secondary gas injection;
3. Movable engine or nozzle;
4. Deflection of exhaust gas stream (jet vanes or probes); or
5. Thrust tabs.
9. A. 109. Hybrid rocket motors, other than those specified by 9A009, and specially designed components thereof, as follows:
a. Hybrid rocket motors usable in complete rocket systems or "unmanned aerial vehicles" capable of a range exceeding 300 km, having a total impulse capacity equal to or greater than 0.841 MNs, but less than 1.1 MNs;
b. Specially designed components for hybrid rocket motors specified by 9A109.a.
N.B.: SEE ALSO 9A009 AND 9A119.
9. A. 110. Composite structures, laminates and manufactures thereof, other than those specified by 9A010, specially designed for use in 'missiles' or the subsystems specified by 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.
N.B.: SEE ALSO 1A002.
Technical Note:
In 9A110 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
9. A. 111. Pulse jet or detonation engines usable in "missiles" or unmanned aerial