Patent ID: 6409121
Filing Date: 2002-06-25
Classification: B64C

Abstract:
An automatic lubrication system for an aircraft's landing gear comprising;said endcap further comprising a pressure outlet and fill inlet disposed thereon; and said piston assembly urges towards the endcap pressurizing the reservoir in response to the pressurized hydraulic fluid supplied to the pressurized chamber. a lubricant reservoir; a lubricant pump for providing motive force for moving lubricant; a lubricant distribution; system fluidly coupling the lubricant reservoir to the pump; said lubricant pump fluidly coupled to at least one lubrication point; means for producing a lubrication signal in response to sensed aircraft parameters; means for activating the lubricant pump in response to said lubrication signal;- a housing having a stepped chamber defining a piston bore and piston-rod bore; a piston assembly disposed in said housing free to reciprocate axially wihtin the chamber and dividing into a lubricant reservoir chamber portion and a pressurized chamber portion; an air exit passage extending from the reservoir side piston face axially through the piston assembly to the piston-rod; an endcap terminating one end of the housing defining the reservior chamber.