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.