A brake system for an aircraft, comprising: a left pedal assembly comprising a left pedal, a first left sensor associated with the left pedal and configured to generate a first left signal in response to translation of the left pedal; a second left sensor associated with the left pedal and configured to generate a second left signal in response to translation of the left pedal; a right pedal assembly comprising a right pedal, a first right sensor associated with the right pedal and configured to generate a first right signal in response to translation of the right pedal; a second right sensor associated with the right pedal and configured to generate a second right signal in response to translation of the right pedal; a normal brake control logic configured to control the brake system in response to a normal condition being set, wherein the normal brake control logic commands a first left force to a left brake located on a left side of the aircraft based on the first left signal and the second left signal, wherein the normal brake control logic commands a first right force to a right brake located on a right side of the aircraft based on the first right signal and the second right signal, corresponding to a greatest amount of pedal deflection; an emergency brake control logic configured to control the brake system in response to an emergency condition being set, wherein the emergency brake control logic is configured to command a same force to the left brake and the right brake based on a one of the first left signal, the second left signal, the first right signal or the second right signal, corresponding to a greatest amount of pedal deflection; and a switch operable to set the emergency condition. a left pedal assembly comprising a left pedal, a first left sensor associated with the left pedal and configured to generate a first left signal in response to translation of the left pedal; a second left sensor associated with the left pedal and configured to generate a second left signal in response to translation of the left pedal; a right pedal assembly comprising a right pedal, a first right sensor associated with the right pedal and configured to generate a first right signal in response to translation of the right pedal; a second right sensor associated with the right pedal and configured to generate a second right signal in response to translation of the right pedal; a normal brake control logic configured to control the brake system in response to a normal condition being set, wherein the normal brake control logic commands a first left force to a left brake located on a left side of the aircraft based on the first left signal and the second left signal, wherein the normal brake control logic commands a first right force to a right brake located on a right side of the aircraft based on the first right signal and the second right signal, corresponding to a greatest amount of pedal deflection; an emergency brake control logic configured to control the brake system in response to an emergency condition being set, wherein the emergency brake control logic is configured to command a same force to the left brake and the right brake based on a one of the first left signal, the second left signal, the first right signal or the second right signal, corresponding to a greatest amount of pedal deflection; and a switch operable to set the emergency condition.