Abstract: Plastic laminated window 40 for aircraft passenger cabin having a peripheral edge insert 50 for providing additional shear-bearing area with respect to the chamfered peripheral edge portion 46 of the outer ply 44 of window 40.

Abstract: An electrically heatable window pane suitable for use in an anti-icing capacity in an aircraft windshield includes a substantially transparent layer of an electroconductive material, preferably tin oxide, sandwiched between fused sheets of glass. The sheets of glass and the layer of electroconductive material are fused together to form a structurally unitary window pane which is heatable by applying an electric potential to the electroconductive layer. Such a heatable window pane may be laminated to a structural fail-safe glass ply in a conventional manner to form a preferred embodiment of an aircraft windshield. In an alternative embodiment, an airplane windshield is formed with two independent electroconductive layers adjacent the inner and outer surfaces of the windshield to provide anti-icing capability on the outside surface and defogging capability on the inside surface.