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 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 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 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 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 located axially forward and axially aft of the abradable liner . <EOS>