A power drive unit associated with a plurality of components for use in an aircraft comprising: at least one motor; a gear ratio mechanism having an input shaft and an output shaft, the at least one motor being operably coupled to the input shaft, the output shaft being operably coupled to the plurality of components, wherein the gear ratio mechanism is capable of driving the output shaft using a plurality of gear ratios, and one of the plurality of gear ratios is selected based on a corresponding component of the plurality of components; wherein the gear mechanism further comprises: a first planetary gear set, which includes a first sun gear; a second planetary gear set, which includes a second sun gear; wherein the second planetary gear set is positioned downstream from the sun gear relative to the input shaft; a gear ratio mechanism of a power drive unit for controlling a plurality of aerodynamic surfaces of an aircraft; a carrier link associated with an output shaft, the carrier link connecting the first planetary gear set and the second planetary gear set; and wherein the first planetary gear set is operably coupled to a first aerodynamic surface of the aircraft and the second planetary gear set is operably coupled to a second aerodynamic surface of the aircraft; wherein the first and second aerodynamic surfaces include flap control surfaces and slat control surfaces and the actuation of the first and second aerodynamic surfaces are associated with the input shaft rotation direction; wherein the first planetary gear set includes a first sun gear coupled to the input shaft, at least one first planet gear, and a first ring gear and the second planetary gear set includes a second sun gear coupled to the input shaft, at least one second planet gear, and a second ring gear; further comprising a first one way mechanism associated with the first ring gear and a second one way mechanism associated with the second ring gear; and wherein the first one way mechanism is configured to restrict rotation of the first ring gear in a first direction and the second one way mechanism is configured to restrict rotation of the second ring gear in a second direction. at least one motor; a gear ratio mechanism having an input shaft and an output shaft, the at least one motor being operably coupled to the input shaft, the output shaft being operably coupled to the plurality of components, wherein the gear ratio mechanism is capable of driving the output shaft using a plurality of gear ratios, and one of the plurality of gear ratios is selected based on a corresponding component of the plurality of components; wherein the gear mechanism further comprises: a first planetary gear set, which includes a first sun gear; a second planetary gear set, which includes a second sun gear; wherein the second planetary gear set is positioned downstream from the sun gear relative to the input shaft; a gear ratio mechanism of a power drive unit for controlling a plurality of aerodynamic surfaces of an aircraft; a carrier link associated with an output shaft, the carrier link connecting the first planetary gear set and the second planetary gear set; and wherein the first planetary gear set is operably coupled to a first aerodynamic surface of the aircraft and the second planetary gear set is operably coupled to a second aerodynamic surface of the aircraft; wherein the first and second aerodynamic surfaces include flap control surfaces and slat control surfaces and the actuation of the first and second aerodynamic surfaces are associated with the input shaft rotation direction; a first planetary gear set, which includes a first sun gear; a second planetary gear set, which includes a second sun gear; wherein the second planetary gear set is positioned downstream from the sun gear relative to the input shaft; a gear ratio mechanism of a power drive unit for controlling a plurality of aerodynamic surfaces of an aircraft; a carrier link associated with an output shaft, the carrier link connecting the first planetary gear set and the second planetary gear set; and wherein the first planetary gear set is operably coupled to a first aerodynamic surface of the aircraft and the second planetary gear set is operably coupled to a second aerodynamic surface of the aircraft; wherein the first and second aerodynamic surfaces include flap control surfaces and slat control surfaces and the actuation of the first and second aerodynamic surfaces are associated with the input shaft rotation direction; wherein the first planetary gear set includes a first sun gear coupled to the input shaft, at least one first planet gear, and a first ring gear and the second planetary gear set includes a second sun gear coupled to the input shaft, at least one second planet gear, and a second ring gear; further comprising a first one way mechanism associated with the first ring gear and a second one way mechanism associated with the second ring gear; and wherein the first one way mechanism is configured to restrict rotation of the first ring gear in a first direction and the second one way mechanism is configured to restrict rotation of the second ring gear in a second direction.