Division 9B Test, Inspection and Production Equipment

Manufacturing equipment, tooling or fixtures, as follows:

N.B. SEE ALSO 2B226

1. a..

   Directional solidification or single crystal casting equipment designed for "superalloys";

2. b..

   Casting tooling, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds", manufactured from refractory metals or ceramics, as follows:

   1. 1..

      Cores;

   2. 2..

      Shells (moulds);

   3. 3..

      Combined core and shell (mould) units;

3. c..

   Directional-solidification or single-crystal additive-manufacturing equipment, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds".

On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, having all of the following:

1. a..

   Specially designed for the "development" of gas turbine engines, assemblies or components; and

2. b..

   Incorporating any of the "technologies" specified in 9E003.h. or 9E003.i.

Equipment specially designed for the "production" or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s and temperatures in excess of 773 K (500 °C), and specially designed components or accessories therefor.

Tools, dies or fixtures, for the solid state joining of "superalloy", titanium or intermetallic airfoil-to-disk combinations described in 9E003.a.3. or 9E003.a.6. for gas turbines.

On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following:

N.B. SEE ALSO 9B105.

1. a..

   Wind tunnels designed for speeds of Mach 1,2 or more;

   Note: 9B005.a. does not control wind tunnels specially designed for educational purposes and having a ‘test section size’ (measured laterally) of less than 250 mm.

   Technical Note:

   ‘Test section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, at the largest test section location.

2. b..

   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; or

3. c..

   Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 x 10⁶.

Acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 μPa) with a rated output of 4 kW or more at a test cell temperature exceeding 1 273 K (1 000 °C), and specially designed quartz heaters therefor.

N.B. SEE ALSO 9B106.

Equipment specially designed for inspecting the integrity of rocket motors and using Non-Destructive Test (NDT) techniques other than planar x-ray or basic physical or chemical analysis.

Direct measurement wall skin friction transducers specially designed to operate at a test flow total (stagnation) temperature exceeding 833 K (560 °C).

Tooling specially designed for producing gas turbine engine powder metallurgy rotor components having all of the following:

1. a..

   Designed to operate at stress levels of 60 % of Ultimate Tensile Strength (UTS) or more measured at a temperature of 873 K (600 °C); and

2. b..

   Designed to operate at 873 K (600 °C) or more.

Note: 9B009 does not control tooling for the production of powder.

Equipment specially designed for the production of items specified in 9A012.

‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for ‘missiles’ and their subsystems.

N.B. SEE ALSO 9B005.

Note: 9B105 does not control wind-tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

1.

2.

3.

Environmental chambers and anechoic chambers, as follows:

1. a..

   Environmental chambers having all of the following:

   1. 1..

      Capable of simulating any of the following flight conditions:

      1. a..

         Altitude equal to or greater than 15 km; or

      2. b..

         Temperature range from below 223 K (-50°C) to above 398 K (+125°C); and

   2. 2..

      Incorporating, or ‘designed or modified’ to incorporate, a shaker unit or other vibration test equipment to produce vibration environments equal to or greater than 10 g rms, measured ‘bare table’, between 20 Hz and 2 kHz while imparting forces equal to or greater than 5 kN;

   Technical Notes:

   1.

   9B106.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g., a sine wave) and systems capable of generating a broad band random vibration (i.e., power spectrum).

   2.

   In 9B106.a.2., ‘designed or modified’ means the environmental chamber provides appropriate interfaces (e.g., sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in 2B116.

   3.

   In 9B106.a.2. ‘bare table’ means a flat table, or surface, with no fixture or fittings.

2. b..

   Environmental chambers capable of simulating the following flight conditions:

   1. 1..

      Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 20 μPa) or with a total rated acoustic power output of 4 kW or greater; and

   2. 2..

      Altitude equal to or greater than 15 km; or

   3. 3..

      Temperature range from below 223 K (-50°C) to above 398 K (+125°C).

‘Aerothermodynamic test facilities’, usable for ‘missiles’, ‘missile’ rocket propulsion systems, and reentry vehicles and equipment specified in 9A116, having any of the following characteristics:

1. a..

   An electrical power supply equal to or greater than 5 MW; or

2. b..

   A gas supply total pressure equal to or greater than 3 MPa.

Technical Notes:

1.

2.

Specially designed "production equipment" for the systems, sub-systems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A105 to 9A109, 9A111, 9A116 to 9A120.

Specially designed "production facilities" for the space launch vehicles specified in 9A004, or systems, sub-systems, and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A104 to 9A109, 9A111, 9A116 to 9A120 or ‘missiles’.

Technical Note:

In 9B116 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

Test benches and test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:

1. a..

   The capacity to handle more than 68 kN of thrust; or

2. b..

   Capable of simultaneously measuring the three axial thrust components.