Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p240
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 684751–687587

engine type.
2. 'Dry weight' is the weight of the engine without fluids (fuel, hydraulic fluid, oil, etc.) and does not include the nacelle (housing).
3. 'First‑stage rotor diameter' is the diameter of the first rotating stage of the engine, whether a fan or compressor, measured at the leading edge of the blade tips.
9. A. 102. 'Turboprop engine systems' specially designed for "unmanned aerial vehicles" capable of a range exceeding 300 km, and specially designed components therefor, having a 'maximum power' greater than 10 kW.
Note: 9A102 does not apply to civil certified engines.
Technical Notes:
1. For the purposes of 9A102 a 'turboprop engine system' incorporates all of the following:
a. Turboshaft engine; and
b. Power transmission system to transfer the power to a propeller.
2. For the purposes of 9A102 the 'maximum power' is achieved uninstalled at sea level static conditions using the ICAO standard atmosphere.
9. A. 104. Sounding rockets, capable of a range of at least 300 km.
N.B.: SEE ALSO 9A004.
Note: Certain items specified in 9A104 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.
9. A. 105. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid or gel propellant rocket system, as follows:
N.B.: SEE ALSO 9A119.
a. Engines or motors usable in "missiles", other than those specified by 9A005, having a total impulse capacity equal to or greater than 1.1 MNs;
b. Engines or motors, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified by 9A005 or 9A105.a., having a total impulse capacity equal to or greater than 0.841 MNs.
Note: Certain items specified in 9A105 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.

9. A. 106. Systems or components, other than those specified by 9A006 as follows, specially designed for liquid or gel propellant propulsion systems:
a. Combustion chambers, usable in "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
b. Rocket nozzles, usable in "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
c. Thrust vector control sub‑systems, usable in "missiles";
Technical Note:
Examples of methods of achieving thrust vector control specified by 9A106.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.
d. 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