A case for a gas turbine engine comprising: a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers, a forward shell section and an aft shell section adjacent to said containment section, said forward and aft shell sections (64, 68) also comprising a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said forward shell section and said aft shell section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said forward shell section and said aft shell section, and a flange section axially forward of said forward shell section; said flange section being formed of a second plurality of non-crimp fabric layers; characterised in that: the case comprises a ballistic liner secondarily bonded to said containment section; and by further comprising: a fiberglass layer as an outermost layer and any innermost layer to encapsulate said plurality of unidirectional roving fiber layers and said plurality of non-crimp fabric layers, wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said containment section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said containment section; an abradable layer radially inboard of the inner ballistic liner; and aerodynamic liners (82, 84) located axially forward and axially aft of the abradable liner. a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers, a forward shell section and an aft shell section adjacent to said containment section, said forward and aft shell sections (64, 68) also comprising a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said forward shell section and said aft shell section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said forward shell section and said aft shell section, and a flange section axially forward of said forward shell section; said flange section being formed of a second plurality of non-crimp fabric layers; characterised in that: the case comprises a ballistic liner secondarily bonded to said containment section; and by further comprising: a fiberglass layer as an outermost layer and any innermost layer to encapsulate said plurality of unidirectional roving fiber layers and said plurality of non-crimp fabric layers, wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said containment section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said containment section; an abradable layer radially inboard of the inner ballistic liner; and aerodynamic liners (82, 84) located axially forward and axially aft of the abradable liner. a fiberglass layer as an outermost layer and any innermost layer to encapsulate said plurality of unidirectional roving fiber layers and said plurality of non-crimp fabric layers, wherein said plurality of unidirectional roving fiber layers define approximately 25% of a thickness of said containment section and said plurality of non-crimp fabric layers define approximately 75% of said thickness of said containment section; an abradable layer radially inboard of the inner ballistic liner; and aerodynamic liners (82, 84) located axially forward and axially aft of the abradable liner.