1.A.2."Composite" structures or laminates, as follows:

a. Made from any of the following:
1. An organic "matrix" and "fibrous or filamentary materials" specified in 1.C.10.c. or 1.C.10.d.; or
2. Prepregs or preforms specified in 1.C.10.e.;
b. Made from a metal or carbon "matrix", and any of the following:
1. Carbon "fibrous or filamentary materials" having all of the following:
a. A "specific modulus" exceeding 10.15 x 10⁶ m; and
b. A "specific tensile strength" exceeding 17.7 x 10⁴ m; or
2. Materials specified in 1.C.10.c.
Note 1 1.A.2. does not apply to "composite" structures or laminates, made from epoxy resin impregnated carbon "fibrous or filamentary materials", for the repair of "civil aircraft" structures or laminates, having all of the following:
a. An area not exceeding 1 m²;
b. A length not exceeding 2.5 m; and
c. A width exceeding 15 mm.
Note 2 1.A.2. does not apply to semi-finished items specially designed for purely civilian applications as follows:
a. Sporting goods;
b. Automotive industry;
c. Machine tool industry;
d. Medical applications.
Note 3 1.A.2.b.1. does not apply to semi-finished items containing a maximum of two dimensions of interwoven filaments and specially designed for applications as follows:
a. Metal heat-treatment furnaces for tempering metals;
b. Silicon boule production equipment.
Note 4 1.A.2. does not apply to finished items specially designed for a specific application.
Note 5 1.A.2.b.1. does not apply to mechanically chopped, milled, or cut carbon "fibrous or filamentary materials" 25.0 mm or less in length.