Complete subsystems usable in the systems specified in 1.A., as follows: a. Individual rocket stages usable in the systems specified in 1.A.; b. Re-entry vehicles, and equipment designed or modified therefor, usable in the systems specified in 1.A., as follows, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads: 1. Heat shields, and components therefor, fabricated of ceramic or ablative materials; 2. Heat sinks and components therefor , fabricated of light-weight, high heat capacity materials; 3. Electronic equipment specially designed for re-entry vehicles; c. Solid propellant rocket motors, hybrid rocket motors or liquid propellant rocket engines, usable in the systems specified in 1.A., having a total impulse capacity equal to or greater than 1.1 x 10 6 Ns; d. ‘Guidance sets’, usable in the systems specified in 1.A., capable of achieving system accuracy of 3.33% or less of the “range” (e.g. a ‘CEP’ of 10 km or less at a “range” of 300 km), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft; e. Thrust vector control sub-systems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “range”/”payload” capability of systems specified in 1.A.; f. Weapon or warhead safing, arming, fuzing, and firing mechanisms, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for systems other than those specified in 1.A.