Paragraph 9B Equipment, Assemblies and Components
Test, Inspection and Production Equipment
Specially designed equipment, tooling or fixtures, as follows, for manufacturing or measuring gas turbine blades, vanes or tip shroud castings:
Automated equipment using non-mechanical methods for measuring airfoil wall thickness;
Tooling, fixtures or measuring equipment for the laser, water jet or ECM/EDM hole drilling processes specified in head c. of entry 9E003;
Directional solidification or single crystal casting equipment;
Ceramic cores or shells;
Ceramic core manufacturing equipment or tools;
Ceramic core leaching equipment;
Ceramic shell wax pattern preparation equipment;
Ceramic shell burn out or firing equipment.
On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for the development of gas turbine engines, assemblies or components incorporating technologies specified in head a. of entry 9E003.
Equipment specially designed for the production or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s, and specially designed parts or accessories therefor.
Tools, dies or fixtures for the solid state joining of gas turbine superalloy or titanium components.
On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with the following wind tunnels or devicesf1:
Wind tunnels designed for speeds of Mach 1.2 or more;
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except:
those specially designed for educational purposes and having a test section size (measured laterally) of less than 250 mm;
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In this head, “Test section size” means the diameter of the circle, or the side of a square, or the longest side of a rectangle, at the largest test section location.
Devices for simulating flow-environments at speeds exceeding Mach 5, including hot-shot tunnels, plasma arc tunnels, shock tubes, shock tunnels, gas tunnels and light gas guns;
Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 × 106.
Specially designed acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 micropascals) with a rated output of 4 kW or more at a test cell temperature exceeding 1,273 K (1,000°C), and specially designed transducers, strain gauges, accelerometers, thermocouples or quartz heaters therefor.
Equipment specially designed for inspecting the integrity of rocket motors using non-destructive test (NDT) techniques other than planar X-ray or basic physical or chemical analysisf2.
Transducers specially designed for the direct measurement of the wall skin friction of the test flow with a stagnation temperature exceeding 833 K (560°C).
Tooling specially designed for producing turbine engine powder metallurgy rotor components capable of operating at stress levels of 60% of ultimate tensile strength (UTS) or more and metal temperatures of 873 K (600°C) or more.
Wind tunnels for speeds of Mach 0.9 or more, usable for missiles and their subsystems.
Environmental chambers and anechoic chambers, as follows:
Environmental chambers capable of simulating the following flight conditions:
Vibration environments of 10 g rms or greater between 20 Hz and 2,000 Hz and imparting forces of 5 kN or greater; and
Altitudes of 15,000 m or greater; or
Temperature of at least 223 K (-50°C) to 398 K (+ 125°C);
Anechoic chambers capable of simulating the following flight conditions:
Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 20 micropascals) or with a rated power output of 4 kW or greater; and
Altitudes of 15,000 m or greater; or
Temperature of at least 223 K (-50°C) to 398 K (+ 125°C).
Specially designed production equipment for the systems, sub-systems and components specified in entries 9A005 to 9A009, 9A011, 9A101, 9A105 to 9A109, 9A111, 9A116 to 9A119.
Specially designed production facilities for the systems, sub-systems, and components specified in entries 9A004 to 9A009, 9A011, 9A101, 9A104 to 9A109, 9A111, 9A116 to 9A119.
Test benches and test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:
The capacity to handle more than 90 kN of thrust; or
Capable of simultaneously measuring the three axial thrust components.
Annotations
Footnotes
- f1
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See also 9B105
- f2
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For Radiographic equipment, see sub-head e.5. of entry 3A001.