Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p223
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 637569–640727

Measurement Units (IMUs);
d. Inertial Navigation Systems (INSs);
e. Inertial Reference Systems (IRSs);
f. Inertial Reference Units (IRUs).
Note 2: 7A103.a does not specify equipment containing accelerometers specified by 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down‑hole well services operations.
Technical Note:
'Inertial measurement equipment or systems' specified by 7A103.a. incorporate accelerometers or gyros to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned.
7. A. 103. b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in 'missiles';
7. A. 103. c. 'Integrated navigation systems', designed or modified for 'missiles' and capable of providing a navigational accuracy of 200 m "Circular Error Probable" ("CEP") or less;
Technical Note:
An 'integrated navigation system' typically incorporates the following components:
1. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system);
2. One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and
3. Integration hardware and software;
7. A. 103. d. Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, having all the following characteristics, and specially designed components therefor;
1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes;
2. Capable of providing azimuthal accuracy better (less) than 0.5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field.
Note: Flight control and navigation systems in 7A103.d. include gyrostabilisers, automatic pilots and inertial navigation systems.
Technical Note:
In 7A103 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
7. A. 104. Gyro‑astro compasses and other devices, other than those specified by 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.
7. A. 105. Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, Galileo or BeiDou), having any of the following characteristics, and specially designed components therefor:
a. Designed or modified for use in space launch vehicles specified by 9A004, unmanned aerial vehicles specified by 9A012 or 9A112.a or sounding rockets specified by 9A104; or
b. Designed or modified for airborne applications and having any of the following:
1. Capable of providing navigation information at speeds in excess of 600 m/s;
2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secured signal/data; or
3. Being specially designed to employ anti‑jam features