Document ID: chunk:federal_register_of_legislation:F2017L00081:reg:25:p3
Version: federal_register_of_legislation:F2017L00081
Segment Type: reg
Provision Reference: reg 25 (pt 3/15)
Character Range: 164485–167393

aircraft (see Category XII(d));
 (e) thrust vector control sub‑systems, except as provided in Note (1) below for those designed for rocket systems that do not exceed the range/payload capability of Item 1 (see Category IV);
 (f) warhead safing, arming, fuzing, and firing mechanisms, except as provided in Note (1) below for those designed for systems other than those in Item 1 (see Category IV(h)).
Note 1: The exceptions in subitems (b), (d), (e), and (f) above may be treated as Category II if the subsystem is exported subject to end use statements and quantity limits appropriate for the excepted end use stated above.
Note 2: CEP (circle of equal probability) is a measure of accuracy, and defined as the radius of the circle centered at the target, at a specific range, in which 50 percent of the payloads impact.
Note 3: A "guidance set" integrates the process of measuring and computing a vehicle's position and velocity (that is, navigation) with that of computing and sending commands to the vehicle's flight control systems to correct the trajectory.
Note 4: Examples of methods of achieving thrust vector control which are covered by subitem (e) include:
(a) flexible nozzle;
(b) fluid or secondary gas injection;
(c) movable engine or nozzle; Deflection of exhaust gas stream (jet vanes or probes); or
(d) use of thrust tabs.

Item 3—Category II
  Propulsion components and equipment usable in the systems in Item 1, as follows:
 (a) lightweight turbojet and turbofan engines (including) turbocompound engines) that are small and fuel efficient (see Category IV(h) and Category VIII(b));
 (b) ramjet/Scramjet/pulse jet/combined cycle engines, including devices to regulate combustion, and specially designed components therefor (see Category IV(h) and Category VIII(b));
 (c) rocket motor cases, "interior lining", "insulation" and nozzles therefor (see § Category IV(h) and Category V(c));
 (d) staging mechanisms, separation mechanisms, and interstages therefor (see Category IV(c) and (h));
 (e) liquid and slurry propellant (including oxidizers) control systems, and specially designed components therefor, designed or modified to operate in vibration environments of more than 100 g RMS between 20 Hz and 2,000 Hz (see Category IV(c) and (h));
 (f) hybrid rocket motors and specially designed components therefor (see Category IV(h)).
Note 1: Subitem 3(a) engines may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for manned aircraft.
Note 2: In subitem 3(c), "interior lining" suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials, for example, carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior (see Category V(c)).
Note 3: In subitem 3(c), "insulation" intended