Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p237
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 676440–679437

AND 9A120.
a. Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, specially designed for use in space vehicles and capable of restricting cryogenic fluid losses to less than 30% per year;
b. Cryogenic containers or closed‑cycle refrigeration systems, capable of providing temperatures of 100 K (‑173°C) or less for "aircraft" capable of sustained flight at speeds exceeding Mach 3, launch vehicles or "spacecraft";
c. Slush hydrogen storage or transfer systems;
d. High pressure (exceeding 17.5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
e. High‑pressure (exceeding 10.6 MPa) thrust chambers and nozzles therefor;
f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
g. Liquid propellant injectors with individual orifices of 0.381 mm or smaller in diameter (an area of 1.14 x 10‑3 cm2 or smaller for non‑circular orifices) and specially designed for liquid rocket engines;
h. One‑piece carbon‑carbon thrust chambers or one‑piece carbon‑carbon exit cones, with densities exceeding 1.4 g/cm3 and tensile strengths exceeding 48 MPa.
9. A. 007. Solid rocket propulsion systems having any of the following:
N.B.: SEE ALSO 9A107 AND 9A119.
a. Total impulse capacity exceeding 1.1 MNs;
b. Specific impulse of 2.4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa;
c. Stage mass fractions exceeding 88% and propellant solid loadings exceeding 86%;
d. Components specified by 9A008; or
e. Insulation and propellant bonding systems, using direct‑bonded motor designs to provide a 'strong mechanical bond' or a barrier to chemical migration between the solid propellant and case insulation material.
Technical Note:
For the purposes of 9A007.e., a 'strong mechanical bond' means bond strength equal to or more than propellant strength.
9. A. 008. Components specially designed for solid rocket propulsion systems, as follows:
N.B.: SEE ALSO 9A108.
a. Insulation and propellant bonding systems, using liners to provide a 'strong mechanical bond' or a barrier to chemical migration between the solid propellant and case insulation material;
Technical Note:
'Strong mechanical bond' means bond strength equal to or more than propellant strength.
b. Filament‑wound "composite" motor cases exceeding 0.61 m in diameter or having 'structural efficiency ratios (PV/W)' exceeding 25 km;
Technical Note:
For the purposes of 9A008.b., 'structural efficiency ratio (PV/W)' is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).
c. Nozzles with thrust levels exceeding 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