An aircraft landing gear comprising: - a first oleo strut configured for connecting, towards its upper end, to an airframe of an aircraft and configured for supporting, towards its lower end, a first axle and a first wheel mountable on the first axle, the first oleo strut comprising a sleeve portion and a slider portion, the slider portion being slidable to act as a piston rod within a hydraulic fluid chamber of the sleeve portion of the first oleo strut, - a second oleo strut configured for connecting, towards its upper end, to the airframe of the aircraft and configured for supporting, towards its lower end, a second axle and a second wheel mountable on the second axle, the second oleo strut comprising a sleeve portion and a slider portion, the slider portion being slidable to act as a piston rod within a hydraulic fluid chamber of the sleeve portion of the second oleo strut, - a hydraulic fluid balancer comprising a balance chamber (55, 56, 57) and at least one separator piston (53, 54), the separator piston fluidly separating the balance chamber into first and second end sections, the first end section being located on a first side of the separator piston and the second end section being located on a second opposite side of the separator piston, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber of the hydraulic fluid balancer and wherein the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer, further comprising a frame including a number of bracing struts (41, 42, 44) between the first and second oleo struts, wherein the balance chamber of the hydraulic fluid balancer is located within a bracing strut of the frame, wherein the bracing strut containing the balance chamber is connected towards an upper end of the first and second oleo struts, wherein the bracing strut acts to connect the first and second oleo struts to the airframe and wherein the bracing strut containing the balance chamber is configured for pivotally mounting to the airframe such that, in use, the landing gear can pivot about the bracing strut between stowed and deployed positions with respect to the airframe. - a first oleo strut configured for connecting, towards its upper end, to an airframe of an aircraft and configured for supporting, towards its lower end, a first axle and a first wheel mountable on the first axle, the first oleo strut comprising a sleeve portion and a slider portion, the slider portion being slidable to act as a piston rod within a hydraulic fluid chamber of the sleeve portion of the first oleo strut, - a second oleo strut configured for connecting, towards its upper end, to the airframe of the aircraft and configured for supporting, towards its lower end, a second axle and a second wheel mountable on the second axle, the second oleo strut comprising a sleeve portion and a slider portion, the slider portion being slidable to act as a piston rod within a hydraulic fluid chamber of the sleeve portion of the second oleo strut, - a hydraulic fluid balancer comprising a balance chamber (55, 56, 57) and at least one separator piston (53, 54), the separator piston fluidly separating the balance chamber into first and second end sections, the first end section being located on a first side of the separator piston and the second end section being located on a second opposite side of the separator piston, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber of the hydraulic fluid balancer and wherein the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer, further comprising a frame including a number of bracing struts (41, 42, 44) between the first and second oleo struts, wherein the balance chamber of the hydraulic fluid balancer is located within a bracing strut of the frame, wherein the bracing strut containing the balance chamber is connected towards an upper end of the first and second oleo struts, wherein the bracing strut acts to connect the first and second oleo struts to the airframe and wherein the bracing strut containing the balance chamber is configured for pivotally mounting to the airframe such that, in use, the landing gear can pivot about the bracing strut between stowed and deployed positions with respect to the airframe.