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The method of sealing and bonding faying surfaces of laminated graphite reinforced epoxy plates, including the steps of mixing an uncured epoxy resin with a filler of carbon microspheres, impregnating a layer of spaced glass fibers or cloth with the mixture, positioning the impregnated fibers betwee

The method of sealing and bonding faying surfaces of laminated graphite reinforced epoxy plates, including the steps of mixing an uncured epoxy resin with a filler of carbon microspheres, impregnating a layer of spaced glass fibers or cloth with the mixture, positioning the impregnated fibers between the faying surfaces of overlapping plates, fastening the plates together, and curing the resin. When it is necessary to repair the seal, the fasteners are removed and the plates are separated with a wedge at the seal bondline without damaging the plate laminations.

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1. A method of securing composite overlapping, laminated reinforced epoxy plates at their faying surfaces and of sealing and bonding the faying surfaces for use in an aircraft, said method comprising: mixing an uncured resin with carbon microspheres; impregnating a layer of spaced fibers with sa

1. A method of securing composite overlapping, laminated reinforced epoxy plates at their faying surfaces and of sealing and bonding the faying surfaces for use in an aircraft, said method comprising: mixing an uncured resin with carbon microspheres; impregnating a layer of spaced fibers with said mixture; positioning the impregnated fibers between faying surfaces of overlapping laminated plates to form a thin bonding and sealing joint and to form a continuous electrically conductive contact path with the microspheres through the joint; said plates being adapted to form aircraft wall structures and being formed having layers impregnated with epoxy to form a lamination along each layer; securing the plates together at the faying surfaces with fastening means; and curing the uncured resin to bond and seal the faying surfaces together to form a thin sealing bondline in the joint, the microspheres being in sufficient quantity to weaken the seal so as to permit the laminated plates to be wedged apart at the bondline when the fastening means are removed and so that damage from the wedging is limited to the bondline within the joint. 2. The method according to claim 1 including: mixing and positioning the uncured resin, microspheres, and fibers between the faying surfaces to form the contact path substantially in the form of a thin discontinuous, approximate layer; the microspheres being irregularly spaced by resin adjacent the continuous contact path. 3. The method according to claim 1 in which: the fastening means extend through the plates and the overlapping surfaces; the fastening means being dielectric. 4. The method according to claim 3 in which: the epoxy plates are reinforced with graphite fibers. 5. The method according to claim 1 in which: the carbon microspheres having diameters in the range of 5 to 150 microns; said microspheres being generally hollow. 6. The method according to claim 5 in which: the bonding and sealing joint has a thickness of about 0.013". 7. The method according to claim 6 in which: the weight percent of the carbon with respect to the resin in the seal is in the range of between 20 to 35, and the density of the carbon microspheres is substantially less than that of the resin in the seal. 8. The method according to claim 7 in which: the carbon microspheres appear to be carbon dust to the naked eye, being irregularly spaced by resin so as not to form a continuous solid layer. 9. A method of sealing and bonding the faying surfaces of composite overlapping, laminated, graphite reinforced epoxy plates and of separating the sealed and bonded plates at the faying surfaces without damaging the laminated plates, said method comprising: mixing an uncured resin with carbon microspheres; impregnating a layer of spaced fibers with said mixture; positioning the impregnated fibers between faying surfaces of overlapping plates to form a thin bonding and sealing joint and to form a continuous electrically conductive contact path with the microspheres through the joint; said plates being adapted to form aircraft wall structures and being formed having layers impregnated with epoxy to form a lamination along each layer; securing the plates together at the faying surfaces with dielectric fasteners; curing the uncured resin to bond and seal the faying surfaces together to form a thin sealing bondline in the joint between the secured plates, the microspheres being in sufficient quantity to weaken the seal so as to permit the plates to be separated without damage thereto; removing the fasteners when the plates are to be separated; and separating the plates at the bondline to break the seal and bond at the joint to separate the plates without damaging the plate laminations. 10. The method according to claim 9 in which: the carbon microspheres appear to be carbon dust to the naked eye and are substantially in the form of a thin discontinuous, approximate layer; the microspheres being irregularly spaced by resin adjacent the continuous conductive contact path. 11. The method according to claim 10 in which: the microspheres are generally hollow and have diameters in the range of 5 to 150 microns. 12. The method according to claim 11 in which: the seal has a thickness of about 0.013". 13. The method according to claim 12 in which: the weight percent of the carbon with respect to the resin in the seal is in the range of between 20 to 35, and the density of the carbon microspheres is substantially less than that of the resin in the bonding means. 14. A method of securing composite overlapping, laminated graphite reinforced epoxy plates at their faying surfaces and of sealing and bonding the faying surfaces for use in an aircraft, said method comprising: mixing an uncured epoxy resin with carbon microspheres; impregnating a layer of spaced fibers with said mixture; positioning the impregnated fibers between faying surfaces of overlapping plates to form a thin bonding and sealing joint; said plates being adapted to form aircraft wall structures and being formed having a series of successive layers impregnated with epoxy to form a lamination along each successive layer; securing the plates together at the faying surfaces with dielectric fasteners; and curing the uncured resin to bond and seal faying surfaces together to form a thin sealing bondline in the joint; the carbon microspheres forming a continuous electrically conductive contact path within the seal and being substantially in the form of a thin discontinuous, approximate layer; the microspheres being irregularly spaced by resin adjacent the continuous conductive path; a sufficient amount of microspheres being present in the seal to weaken the seal so the plates can be forcibly separated at the joint with a separating wedge without damaging the plates when the fasteners have been removed. 15. The method according to claim 14 in which: the microspheres are generally hollow, having diameters in the range of 5 to 150 microns. 16. The method according to claim 15 in which: the bonding and sealing joint has a thickness of about 0.013". 17. The method according to claim 16 in which: the weight percent of carbon with respect to the resin in the seal is in the range of between 20 to 35, and the density of the carbon microspheres is substantially less than that of the resin in the seal.