Fiber-Metal Laminates (FMLs) were developed for aeronautical applications at the Technical University of Delft, Netherlands. The main characteristic of this family of composite materials is their very low fatigue crack propagation rates when compared to traditional aeronautical Al alloys. This behavior arises from the fiber-bridging mechanism, which restricts the crack opening in the loading part of the fatigue cycle, diminishing the crack growth rate under cyclic loading. Although these laminates were basically developed taking advantage of the bridging mechanism, they also present several benefits over monolithic alloys, i.e. higher specific strength and resistance to corrosion, impact, and flame penetration. Glass-Fiber-Reinforced Aluminum (GLARE) laminates are reinforced by continuous S2 glass fibers and were developed for primary applications (fuselages, bulkheads, etc.). Commercial GLARE laminates are reinforced by fibers oriented following the loading characteristics of the structure and can be manufactured as thin sheets of dimensions either similar to those of commercial Al alloys, or with larger dimensions, including low complexity shapes and double curvature panels. The most important application of GLARE laminates is as large parts of the upper fuselage of the Airbus A380. The structural application of GLARE laminates demands a deep knowledge of its mechanical properties. Traditionally, monotonic fracture tests are performed on large and expensive center cracked (M(T)) panels. A testing methodology to evaluate the fracture toughness of FMLs based on elastic-plastic fracture mechanics (J-Integral and CTOD ?₅) and using small C(T) and SE(B) specimens was proposed. The use of small tests specimens presents some advantages, which include lower material cost and the possibility of testing inside small environmental chambers. The objective of this work is to present the developed methodology and its application to unidirectional and bidirectional GLARE laminates, as well as compare results from traditional M(T) and small C(T) (compact tension) specimens at room and low temperature.