An aircraft power distribution architecture (10; 100; 200; 300; 400) for an aircraft including a plurality of aircraft systems (70, 80; 172, 174, 176, 180, 182; 272, 276, 280, 282, 284; 372, 376, 380, 382, 384; 474, 476, 478, 480, 482, 486) comprising: an engine (90; 190; 290; 390; 490) having a low spool compressor and a high spool compressor; an electric power distributor (30; 130; 230; 330; 430); an Auxiliary Power Unit (20; 120; 220; 320; 420) coupled to said electric power distributor (30; 130; 230; 330; 430), and operable to provide power to said electric power distributor (30; 130; 230; 330; 430); a low pressure bleed (60; 160; 260; 360; 460) connected to said APU (20; 120; 220; 320; 420), said low pressure bleed (60; 160; 260; 360; 460) being operable to bleed air from said APU (20; 120; 220; 320; 420) or from the aircraft engine (90; 190; 290; 390; 490), and operable to provide bleed air to a plurality of pneumatic aircraft systems (70; 172, 174, 176; 272, 276; 372, 376; 474, 476, 478); and an electric generator system (50; 150; 250; 350; 450) coupled to said electric power distributor (30; 130; 230; 330; 430) and operable to provide electric power to said electric power distributor (30; 130; 230; 330; 430), wherein said electric power distributor (30; 130; 230; 330; 430) is further coupled to a plurality of aircraft systems (80; 180, 182; 280, 282, 284; 380, 382, 384; 480, 482, 486) that use electric power; characterized in that said engine (90; 190; 290; 390; 490) comprises a low spool compressor and a high spool compressor interface, in that said low pressure bleed (60; 160; 260; 360; 460) is suitable to be connected to both said low spool compressor and high spool compressor interface, and in that said low pressure bleed (60; 160; 260; 360; 460) is operable to bleed air pressure from said low spool compressor and said high spool compressor interface. an engine (90; 190; 290; 390; 490) having a low spool compressor and a high spool compressor; an electric power distributor (30; 130; 230; 330; 430); an Auxiliary Power Unit (20; 120; 220; 320; 420) coupled to said electric power distributor (30; 130; 230; 330; 430), and operable to provide power to said electric power distributor (30; 130; 230; 330; 430); a low pressure bleed (60; 160; 260; 360; 460) connected to said APU (20; 120; 220; 320; 420), said low pressure bleed (60; 160; 260; 360; 460) being operable to bleed air from said APU (20; 120; 220; 320; 420) or from the aircraft engine (90; 190; 290; 390; 490), and operable to provide bleed air to a plurality of pneumatic aircraft systems (70; 172, 174, 176; 272, 276; 372, 376; 474, 476, 478); and an electric generator system (50; 150; 250; 350; 450) coupled to said electric power distributor (30; 130; 230; 330; 430) and operable to provide electric power to said electric power distributor (30; 130; 230; 330; 430), wherein said electric power distributor (30; 130; 230; 330; 430) is further coupled to a plurality of aircraft systems (80; 180, 182; 280, 282, 284; 380, 382, 384; 480, 482, 486) that use electric power; characterized in that said engine (90; 190; 290; 390; 490) comprises a low spool compressor and a high spool compressor interface, in that said low pressure bleed (60; 160; 260; 360; 460) is suitable to be connected to both said low spool compressor and high spool compressor interface, and in that said low pressure bleed (60; 160; 260; 360; 460) is operable to bleed air pressure from said low spool compressor and said high spool compressor interface.