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EP137 - Preimpregnated materials for aircraft parts (v2)

EP137 - Preimpregnated materials for aircraft parts (v2)

EP137 - Preimpregnated materials for aircraft parts (v2)

Product catalog summary
Overview: The document details the specifications and properties of EP137-G228-40, a fiber-reinforced thermosetting prepreg material used in aircraft parts, particularly passenger floors. It highlights the material's composition, performance characteristics, and compliance with industry standards.
Material Composition: EP137-G228-40 is composed of S2-glass fabric Style 6522, impregnated with 40% epoxy resin EP137. The fabric is woven in an 8H satin style and weighs 115 g/m². The epoxy resin system is low-smoke, highly toughened, and self-extinguishing, with excellent adhesion to core materials.
Performance and Applications: The prepreg is suitable for high-performance lightweight composite structures, offering high interlaminar shear strength and adjustable tackiness. It is used to prevent electro-galvanic corrosion and improve impact behavior in aircraft interiors. The material can be used in both monolithic and sandwich structures, with curing possible through press, vacuum, and autoclave molding at temperatures between 120ºC and 155ºC.
Compliance and Standards: EP137-G228-40 meets AIRBUS material performance specifications ABS 5672-02 and AIMS 05-10-027. Cured laminates comply with FAR 25.853 Flame Test and ABD 0031 NBS Smoke Chamber standards.
Mechanical Properties: The document provides typical mechanical properties, including flexural strength, tensile strength, and compressive strength at room temperature and elevated temperatures. The material exhibits a glass transition temperature (Tg) of 125ºC.
Storage and Handling: The prepreg is delivered in rolls with a storage life of 15 days at room temperature and 6 months at -5ºC. Recommended curing processes include press, autoclave, and vacuum-bag methods.
Burning Behavior: The material's burning behavior is tested under AITM standards, showing specific values for flammability, smoke density, and heat release.
Disclaimer: The document includes a disclaimer emphasizing the need for users to conduct their own testing to ensure suitability for specific applications. It also notes that specifications and prices are subject to change without notice.
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Catalog excerpts

EP137 - Preimpregnated materials for aircraft parts (v2)-1

EP137-G228-40 Fiber reinforced thermosetting preimpregnated material for aircraft parts (e.g. passenger floor). Woven fabric of S2-glass filament yarn Style 6522, 115 g/m², 8H satin, preimpregnated with 40% epoxy resin EP137 (125ºC). Low-smoke, highly toughened and self-extinguishing epoxy resin system Very good FST behaviour Excellent adhesion to core materials Improved storage conditions at -5ºC Revision: 2011/02 Seite 1 von 4

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EP137 - Preimpregnated materials for aircraft parts (v2)-2

Description Such composite structures can be exposed easily to temperatures in the range of -55ºC up to +90ºC. EP137-G228-40 consists of a S2-glass fabric Style 6522, impregnated with the epoxy resin EP137. The highly-toughened This prepreg meets the following AIRBUS material performance specification: resin matrix is a 125ºC curing system with a high flame-retardancy and low smoke behaviour at fire and provides excellent properties such as high interlaminar shear strength, adjustable tackiness and ABS 5672-02 retarded flow during processing. AIMS 05-10-027 (certification) The prepreg is perfectly...

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EP137 - Preimpregnated materials for aircraft parts (v2)-3

Curing Conditions Standard Cycle 120/140/155ºC Temperature Cure Time 90/60/30 min 0.07 MPa Spec. Pressure Heat-up 3K/min from 60ºC (max) 4K/min to 60ºC Cool-down Remove material at at least 60ºC Press, Autoclave, Vacuum-bag Recommended curing process Mechanical Properties (Typical Values) Temp. [° C] Flexural Strength (warp) Flexural Modulus (warp) Tensile Strength (warp) Tensile Modulus (warp) RT 80 RT 80 RT 80 RT Standard ISO 178 ISO 178 ISO 527-4 ISO 527-4 Results 700 MPa 450 25 21 700 650 24 GPa MPa GPa Compressive Strength (warp) EN 2850 MPa Compressive Modulus (warp) EN 2850 GPa RT Interlaminar...

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EP137 - Preimpregnated materials for aircraft parts (v2)-4

Burning Behaviour Test method Max. mean values 120 burn length after flame time Flammability vertical, 60s flaming AITM 2.0002A mm 3 s 0 after flame time of drips s Flammability vertical, 12s flaming Max. specific optical smoke density within 4 min flaming mode AITM 2.0007A 100 Heat release AITIM 2.0006 45 Heat release rate AITIM 2.0006 50 Ds kW m² kW*min m² Disclaimer The materials, products and services of the Gurit Group sold by the respective legal entity (the “Company”) of the Gurit Group are subject to the Standard Conditions of Sale of the Company which are available on request or may...

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*Prices are pre-tax. They exclude delivery charges and customs duties and do not include additional charges for installation or activation options. Prices are indicative only and may vary by country, with changes to the cost of raw materials and exchange rates.