Abstract: An engine oil system includes a conduit and a strainer assembly. The conduit forms a portion of an oil flow path. The conduit includes a first conduit body and a second conduit body. The first conduit body is mounted to the second conduit body at a flange interface. The first conduit body and the second conduit body form an internal passage of the conduit. The strainer assembly is disposed within the conduit at the flange interface. The strainer assembly includes a tubular body, a first packing ring, a second packing ring, and a strainer member. The first packing ring forms a first fluid seal between the tubular body and the first conduit body. The second packing ring forms a second fluid seal between the tubular body and the second conduit body. The strainer member is mounted to the tubular body within the oil flow path.

Abstract: An engine oil system includes an oil tank and an access port cover. The oil tank includes a wall forming an internal oil cavity. The wall forms an access port extending along an access port axis through the wall. The access port cover is mounted on the wall and seals the access port. The access port cover includes a cover body and a packing ring. The cover body extends between and to an inner axial end and an outer axial end. The cover body forms a cover lip at the outer axial end. The cover lip extends circumferentially about the access port axis. The cover lip extends radially outward and axially outward, relative to the access port axis, along a lip axis to the outer axial end. The packing ring forms a fluid seal between the cover body and the wall within the access port.

Abstract: A pressure regulating valve is provided that includes a housing, a sleeve, a piston, an adjustment nut, and a piston spring. The housing includes a sleeve bore. The sleeve has a side wall that extends axially between a base end and a distal end, an end wall disposed at the base end, an interior cavity that extends axially between the base end and the distal end, and a plurality of ports. The sleeve is disposed within the sleeve bore. The piston extends axially between a land end and a spring end. The adjustment nut is engaged with the sleeve, and is configured for axial translation relative to the sleeve. The piston spring is disposed to provide a spring force on the adjustment nut and the piston. The sleeve includes an asymmetric feature that engages with the housing to prevent rotation of the sleeve relative to the housing.

Abstract: A method for forming a fire shield for an aircraft engine includes forming a case template matching a case body of the fire shield. The case template has a first template side and a second template side. The method further includes forming a fire shield layer at the second template side by spraying a fire shield material at the second template side and attaching the fire shield layer to the case body.

Abstract: An impeller rotor includes a plurality of fluid circuits arranged circumferentially about an axis within the impeller rotor. Each of the fluid circuits includes a first outlet passage, a second outlet passage and an inlet passage fluidly coupled to the first outlet passage and the second outlet passage in parallel. A seal runner includes a bore, a sidewall and a rim. The bore is fluidly coupled to the first outlet passage of each of the fluid circuits. The rim projects radially out from the sidewall to an outer end of the rim. The rim is seated in a recess in the impeller rotor. The rim includes a flat disposed at the outer end of the rim. The flat of the rim is configured to engage a flat of the impeller rotor to rotationally fix the seal runner to the impeller rotor.

Abstract: An engine includes an engine oil system. The engine oil system includes a pump assembly forming a portion of an oil flow path. The pump assembly includes a drive shaft, a plurality of pumps, and a pump housing. The drive shaft extends along a rotational axis. The plurality of pumps are arranged axially along the rotational axis. Each of the plurality of pumps includes a pump rotor coupled with the drive shaft. The pump housing extends along the rotational axis between a first housing end and a second housing end. The pump housing circumscribes and houses the drive shaft and the plurality of pumps between the first housing end and the second housing end. The pump housing includes a plurality of housing body portions axially stacked along the rotational axis to form the pump housing. The plurality of housing body portions collectively form an internal oil passage through the pump housing.

Abstract: An engine includes an engine rotational assembly and an engine oil system. The engine rotational assembly includes an engine shaft and a rotor. The engine rotational assembly is rotatable about a first rotational axis. The engine oil system includes a pump assembly including a drive shaft, a pump, and a pump housing. The drive shaft is coupled with the engine shaft. The drive shaft extends along a second rotational axis between and to a first shaft end and a second shaft end. The drive shaft includes a hand crank pad at the second shaft end. The hand crank pad includes a rotational drive member. The pump includes a pump rotor coupled with the drive shaft. The pump housing extends along the second rotational axis between a first housing end and a second housing end. The second housing end forms an opening at the hand crank pad.

Abstract: An engine oil system includes an oil tank and a scavenge pump assembly. The scavenge pump assembly includes a drive shaft, a plurality of scavenge pumps, and a scavenge return manifold. Each of the plurality of scavenge pumps includes a pump rotor coupled with the drive shaft. The scavenge return manifold includes a manifold body forming a common outlet passage and a plurality of inlet passages of the scavenge return manifold. The common outlet passage includes a manifold outlet of the scavenge return manifold connected in fluid communication with the oil tank. Each of the plurality of inlet passages includes a manifold inlet of the scavenge return manifold connected in fluid communication with a respective one of the plurality of scavenge pumps. Each of the plurality of inlet passages extends in an oblique direction from the manifold inlet to the common outlet passage.

Abstract: An engine oil system includes an oil tank and an access port cover. The oil tank includes a wall forming an internal oil cavity. The wall forms an access port extending along an access port axis through the wall. The access port cover is mounted on the wall and seals the access port. The access port cover includes a cover body and a packing ring. The cover body extends between and to an inner axial end and an outer axial end. The cover body forms a cover lip at the outer axial end. The cover lip extends circumferentially about the access port axis. The cover lip extends radially outward and axially outward, relative to the access port axis, along a lip axis to the outer axial end. The packing ring forms a fluid seal between the cover body and the wall within the access port.

Abstract: An engine oil system includes a conduit and a strainer assembly. The conduit forms a portion of an oil flow path. The conduit includes a first conduit body and a second conduit body. The first conduit body is mounted to the second conduit body at a flange interface. The first conduit body and the second conduit body form an internal passage of the conduit. The strainer assembly is disposed within the conduit at the flange interface. The strainer assembly includes a tubular body, a first packing ring, a second packing ring, and a strainer member. The first packing ring forms a first fluid seal between the tubular body and the first conduit body. The second packing ring forms a second fluid seal between the tubular body and the second conduit body. The strainer member is mounted to the tubular body within the oil flow path.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a fluid reservoir structure, an aircraft engine housing structure and a mounting assembly. The fluid reservoir structure includes a first mount. The aircraft engine housing structure includes a second mount. The mounting assembly connects the first mount to the second mount while providing controlled intercomponent movement between the first mount and the second mount to reduce internal stress and/or wear. The mounting assembly includes a first bushing, a second bushing and a fastener.

Abstract: A lubricant filter assembly includes a filter cartridge including a cylindrical filter medium and a top cap. The cylindrical filter medium extends circumferentially about a longitudinal axis of the filter assembly. The cylindrical filter medium extends between and to a first filter end and a second filter end along the longitudinal axis. The cylindrical filter medium forms a filter passage extending from the first filter end to the second filter end. The top cap is disposed on the cylindrical filter medium at the first filter end. The top cap includes an inner diameter ring, an outer diameter ring, and an interior packing. The inner diameter ring forms a first filter outlet passage coincident with the filter passage. The inner diameter ring includes a first set of locking tabs. The outer diameter ring radially circumscribes the cylindrical filter medium.

Abstract: An apparatus for an aircraft powerplant includes an impeller rotor and a seal runner. The impeller rotor includes a plurality of fluid circuits. Each of the fluid circuits includes a first outlet passage, a second outlet passage and an inlet passage fluidly coupled to the first outlet passage and the second outlet passage in parallel. The seal runner includes a bore, an inner guide surface and an outer land surface. The seal runner extends circumferentially about the axis and radially between the inner guide surface and the outer land surface. The bore is fluidly coupled to the first outlet passage of each fluid circuit. The inner guide surface forms a radial outer peripheral boundary of the bore. The inner guide surface radially diverges away from the axis as the inner guide surface extends axially away from the impeller rotor and to a distal end of the seal runner.

Abstract: A method for forming a fire shield for an aircraft engine includes forming a case template matching a case body of the fire shield. The case template has a first template side and a second template side. The method further includes forming a fire shield layer at the second template side by spraying a fire shield material at the second template side and attaching the fire shield layer to the case body.

Abstract: A lubricant filter assembly includes a filter cartridge including a cylindrical filter medium and a top cap. The cylindrical filter medium extends circumferentially about a longitudinal axis of the filter assembly. The cylindrical filter medium extends between and to a first filter end and a second filter end along the longitudinal axis. The cylindrical filter medium forms a filter passage extending from the first filter end to the second filter end. The top cap is disposed on the cylindrical filter medium at the first filter end. The top cap includes an inner diameter ring, an outer diameter ring, and an interior packing. The inner diameter ring forms a first filter outlet passage coincident with the filter passage. The inner diameter ring includes a first set of locking tabs. The outer diameter ring radially circumscribes the cylindrical filter medium.