Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p238
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 679195–682382

45 kN or nozzle throat erosion rates of less than 0.075 mm/s;
d. Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following:
1. Omni‑axial movement exceeding ± 5°;
2. Angular vector rotations of 20°/s or more; or
3. Angular vector accelerations of 40°/s2 or more.
9. A. 009. Hybrid rocket propulsion systems having any of the following:
a. Total impulse capacity exceeding 1.1 MNs; or
b. Thrust levels exceeding 220 kN in vacuum exit conditions.
9. A. 010. Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or "spacecraft", as follows:
N.B.: SEE ALSO 1A002 AND 9A110.
          a. Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:
              1. "Composite" materials consisting of "fibrous or filamentary materials" specified by 1C010.e. and resins specified by 1C008. or 1C009.b.;
              2. Metal "matrix" "composites" reinforced by any of the following:
                   a. Materials specified by 1C007.;
                   b. "Fibrous or filamentary materials" specified by 1C010.; or
                   c. Aluminides specified by 1C002.a.; or
              3. Ceramic "matrix" "composite" materials specified by 1C007.;
Note: The weight cut‑off is not relevant for nose cones.
9. A. 010. b. Components and structures, specially designed for launch vehicle propulsion systems specified by 9A005 to 9A009 manufactured using any of the following:
              1. "Fibrous or filamentary materials" specified by 1C010.e. and resins specified by 1C008. or 1C009.b.;
              2. Metal "matrix" "composite" materials reinforced by any of the following:
                   a. Materials specified by 1C007;
                   b. "Fibrous or filamentary materials" specified by 1C010; or
                   c. Aluminides specified by 1C002.a.; or
              3. Ceramic "matrix" "composite" materials specified by 1C007;
9. A. 010. c. Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of "spacecraft" structures;
9. A. 010. d. Pulsed liquid rocket engines with thrust‑to‑weight ratios equal to or more than 1 kN/kg and a 'response time' of less than 30 ms.
Technical Note:
For the purposes of 9A010.d., 'response time' is the time required to achieve 90% of total rated thrust from start‑up.
9. A. 011. Ramjet, scramjet or 'combined cycle engines', and specially designed components therefor.
Technical Note:
For the purposes of 9A011, 'combined cycle engines' combine two or more of the following types of engines:
        ‑ Gas turbine engine (turbojet, turboprop and turbofan);
        ‑ Ramjet or scramjet;
        ‑ Rocket motor or engine (liquid/gel/solid‑propellant and hybrid).
N.B.: SEE ALSO 9A111 AND 9A118.
9. A. 012. "Unmanned aerial vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:
N.B.: For "UAVs" that are "sub‑orbital craft", see 9A004.h.
9. A. 012. a. "UAVs" or unmanned "airships", designed to have controlled flight out of the direct 'natural vision' of the