An aircraft electrical system comprising: a generator coupled with a gas turbine engine ; and a controller operable to distribute power of the generator , the controller including, a first control module positioned at a first location remote from the generator , the first control module being configured to verify at least one output of the generator , detect a fault condition of the generator , and control operation of at least one power bus in communication with the first control module , a second control module positioned at a second location proximate the generator and configured to regulate the at least one output of the generator , wherein the at least one output includes a voltage; and wherein the the second control module is configured to report measured parameters to the first control module , and wherein the first control module is configured to compare the reported measured parameters with parameters measured by the first control module; and wherein the fault condition that is detected is based upon the comparison of the reported measured parameters with the parameters measured by the first control module; and the first control module is located in a fuselage of an aircraft and the second control module is located in a generator region of the aircraft; and a generator line control in communication with the first control module and the second control module , wherein the generator line control receives power from the generator , and the generator line control is configured to be changed to an OFF state by either of the first control module and the second control module in response to the fault condition such that distribution of power from the generator ceases. a generator coupled with a gas turbine engine ; and a controller operable to distribute power of the generator , the controller including, a first control module positioned at a first location remote from the generator , the first control module being configured to verify at least one output of the generator , detect a fault condition of the generator , and control operation of at least one power bus in communication with the first control module , a second control module positioned at a second location proximate the generator and configured to regulate the at least one output of the generator , wherein the at least one output includes a voltage; and wherein the the second control module is configured to report measured parameters to the first control module , and wherein the first control module is configured to compare the reported measured parameters with parameters measured by the first control module; and wherein the fault condition that is detected is based upon the comparison of the reported measured parameters with the parameters measured by the first control module; and the first control module is located in a fuselage of an aircraft and the second control module is located in a generator region of the aircraft; and a generator line control in communication with the first control module and the second control module , wherein the generator line control receives power from the generator , and the generator line control is configured to be changed to an OFF state by either of the first control module and the second control module in response to the fault condition such that distribution of power from the generator ceases. <EOS>