This specification covers the requirements for nonperforated nylon paper base plastic honeycomb core material for aircraft structural applications, including exterior parts such as radio and radar antenna housings.
This recommended practice describes the materials, related equipment, and particular processing techniques utilized in process science curing of composite hardware where pressure is imparted specifically to the resin of curing composites. Included as Appendix "A" to this ARP is a discussion of the particular techniques developed for a processing science philosophy which has consistently produced void and porosity-free, large area, thick composite structures.
This recommended practice describes the materials and procedures for cleaning aluminum alloy detail parts and low-alloy steel parts (other than corrosion resistant steel) prior to structural adhesive bonding operations.
This SAE Aerospace Recommended Practice describes the aluminum weldbonding process for fabrication of secondary aircraft structural assemblies possessing excellent strength, fatigue life, and environmental durability.
This specification establishes the acceptance criteria and inspection requirements for adhesive-bonded sandwich structures including the metal-to-metal bonding found in these structures, but usage is not limited to such applications and each application should be considered individually.
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated carbon fiber plain weave fabric product. The prepreg is a plain weave fabric with 12K tows, a nominal fiber areal weight of 193 gsm, and nominal resin content of 42%.
This specification establishes the requirements for a nominal 250 °F cure epoxy preimpregnated 7781 glass fabric. The prepreg has a nominal fiber areal weight of 294 gsm, and nominal resin content of 38%.