2510 Prepreg System Data Sheet PRODUCT NOTES The 2510 prepreg system is specifically formulated for out-of-autoclave (OOA) processing of aerospace primary structures. This prepreg system has excellent all-around structural properties with a high wet and dry Tg while offering low-energy curing (250-270°F, 121-132°C). Industry Material Specification Product can be purchased to Aerospace Material Specifications 3960, 3914, and 3915. Industry Database FAA approved design allowable values (AGATE methodology), results in a low cost one-batch equivalency. Easy Layup Product allows complex part layup with minimal cuts or ridge lines. It maintains a comparable class A finish through post-cure, minimizing sanding and finishing times. Flexible Cure Methods Curing methods include autoclave or oven cure. Product can be cured with or without using a dwell. Readily Available Product is in stock and ready to ship. High Heat Tolerance High Tg is suitable for structures exposed to elevated service temperatures. AVAILABLE PRODUCT FORMATS PART NUMBER FIBER FORMAT FIBER TYPE/STYLE ROLL WIDTH Plain Weave Glass Fabric NEAT RESIN PHYSICAL PROPERTIES RESIN VISCOSITY CURVE STORAGE LIFE Out Life* Freezer Life *Tack and drape is optimum at 72F and 65% RH

LAMINA/LAMINATE MECHANICAL PROPERTIES: P707AG-15 (OVEN CURE) PROPERTY In-Plane Shear Strength @ 5% or Ultimate In-Plane Shear Modulus Short Beam Shear Strength Poisson’s Ratio Open Hole Tension Strength (25/50/25) Open Hole Compression Strength (25/50/25) Compression After Impact (25/50/25) Laminate Density Fiber Volume Fraction LAMINA/LAMINATE MECHANICAL PROPERTIES: F6273C-07M (OVEN CURE) PROPERTY In-Plane Shear Strength @ 5% or Ultimate In-Plane Shear Modulus Short Beam Shear Strength Poisson’s Ratio Open Hole Tension Strength (25/50/25) Open Hole Compression Strength (25/50/25) Compression...

LAMINA/LAMINATE MECHANICAL PROPERTIES: FGF7781-07I PROPERTY In-Plane Shear Strength @ 5% or Ultimate In-Plane Shear Modulus Short Beam Shear Strength Poisson’s Ratio Open Hole Tension Strength (25/50/25) Open Hole Compression Strength (25/50/25) Laminate Density Fiber Volume Fraction Notes: CTA: -65°F (-54°C), Ambient RTA: 72°F (22°C), Ambient ETW: 180°F (82°C), conditioned at 160°F/85% RH until equilibrium Tension and compression values are normalized to the indicated CPT values BAGGING PROCEDURE Notes: 1. Debulk every four plies, or as needed, when laying up material 2. It is recommended that...

RECOMMENDED OVEN CURE CYCLE 1. Apply full vacuum* to the part. Higher vacuum levels will yield better results. 2. Maintaining vacuum for at least three hours prior to beginning cure cycle is recommended for optimal part quality. This promotes the extraction of trapped air and gases, producing a lower void content. 3. Ramp to 270 ± 10°F at 1-5°F/min (132 ± 5°C at 0.6-2.8°C/min) and hold for 120 minutes. 4. Cool temperature down to 130°F at max rate of 5°F/min (54°C at 2.8°C/min). TIME (MINUTES) ALTERNATIVE OVEN CURE CYCLE Recommended for thick laminates, to reduce the risk of interlaminar voids...