damper with heat energy from the heater prior to flight this feature greatly reduces the time and costs associated with preparing the aircraft for flight it should be appreciated that these features overcome the problems commonly associated with conventional damper systems electrical subsystem 507 is configured to provide electrical energy to the fluid disposed within damper 303 in the contemplated embodiment electrical subsystem 507 is positioned within chamber 309 and conductively coupled to an electrical energy source 513 during operation the electrical subsystem 507 induces electrical energy in the fluid to achieve this feature fluid 515 is an electrorheological fluid that changes in viscosity as electrical energy is added u201c induced u201d another unique feature believed characteristic of the present application is changing the spring rate of damper 303 in real time by changing the viscosity of the fluid by utilizing the electrorheological fluid and the electrical subsystem 507 thus the damper allows selective controlling of the spring rate in real time according in accordance with different flight conditions this feature overcomes the problems commonly associated with dampers for example dampers having a single spring rate in the contemplated embodiment sensor 505 is operably associated with both heater 503 and electrical subsystem 507 for sensing energy output and operation of damper 303 and is configured to relay the sensed data to control subsystem 509 the control subsystem 509 then either autonomously or manually regulates to heat and or electrical input thereby warming the components of damper 303 and or changing the spring rate by regulating the electrical energy it is apparent that.