Abstract: A seal assembly of a shaft bearing system of an aircraft propeller system includes an inner seal element fixed to a shaft and rotatable therewith about a shaft axis and an outer seal assembly located radially outboard of the inner seal element and rotationally fixed relative to the shaft axis. The outer seal assembly includes an outer seal interactive with the inner seal element at a plurality of knife edges of the inner seal element, and a lip seal having a seal lip interactive with the inner seal element. The outer seal assembly includes a first circumferential seal segment and a second circumferential seal segment abutting the first circumferential seal segment at a seal joint. The lip seal is positioned axially between the outer seal and a bearing of the shaft bearing system.

Abstract: An assembly includes a rotating seal land, a seal element, a stationary seal support and a mating plate. The seal element axially overlaps, circumscribes and radially sealingly engages the rotating seal land. The stationary seal support axially overlaps and circumscribes the rotating seal land and the seal element. The stationary seal support includes a support notch, a support shoulder, a support inner interior surface and a support outer interior surface. The support notch projects axially into the stationary seal support from a distal end of the stationary seal support to the support shoulder. The support notch projects radially outward away from an axis into the stationary seal support from the support inner interior surface to the support outer interior surface. The mating plate is seated in the support notch and mounted to the stationary seal support. The mating plate axially contacts the support shoulder and the seal element.

Abstract: An aircraft engine oil filler apparatus includes a filler tube configured to be connected to an oil tank such that a bottom portion of the filler tube is disposed inside the oil tank, a valve received in the bottom portion of the filler tube movable between an open position in which the valve hydraulically connects the filler tube to the oil tank, and a closed position in which the valve hydraulically disconnects the filler tube from the oil tank, and a float disposed above the valve and operatively connected to the valve to move the valve from the open position to the closed position when oil inside the oil tank rises to a threshold level. The valve is movable independently from the float when pressure in the oil tank is greater than pressure in the filler tube. A method of operation of an oil filler apparatus is also described.

Abstract: An aircraft engine oil filler apparatus includes a filler tube configured to be connected to an oil tank such that a bottom portion of the filler tube is disposed inside the oil tank, a valve received in the bottom portion of the filler tube movable between an open position in which the valve hydraulically connects the filler tube to the oil tank, and a closed position in which the valve hydraulically disconnects the filler tube from the oil tank, and a float disposed above the valve and operatively connected to the valve to move the valve from the open position to the closed position when oil inside the oil tank rises to a threshold level. The valve is movable independently from the float when pressure in the oil tank is greater than pressure in the filler tube. A method of operation of an oil filler apparatus is also described.

Abstract: A lock washer for preventing relative rotation between an inner component and an outer component in an aircraft engine. The lock washer comprises an annular body having an inner circumferential surface and an outer circumferential surface radially spaced apart to define a radial thickness of the annular body. Radially-inward protruding tabs extend radially inwardly from the inner circumferential surface of the annular body and are operable for engagement with slots in the inner component. Radially-outward protruding tabs extend radially outwardly from the outer circumferential surface of the annular body and are operable for engagement with slots in the outer component. The radially-outward protruding tabs are circumferentially offset from the radially-inward protruding tabs such that the radially-outward protruding tabs and the radially-inward protruding tabs are all free of circumferential overlap.

Abstract: A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.

Abstract: A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.