Abstract: A decompression panel assembly for use in an aircraft includes a frame including a first surface and an opposing second surface, wherein the frame defines a grille opening and at least partially defines a flow path opening. The decompression panel assembly also includes a face panel having a first surface retained against the frame second surface such that the face panel at least partially covers the grille opening. A retention mechanism is coupled to the face panel and is configured to retain the face panel against the frame in a closed position.

Abstract: A heat shield having a honeycomb core. The honeycomb core has a plurality of intersecting wall portions forming a plurality of cells. A strain compliant material is applied to the wall portions of the honeycomb core prior to filling of the cells with an ablative material. An ablative material at least substantially fills the cells of the honeycomb core.