Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

Abstract: A thrust mount assembly includes a thrust link-lever that has a first end region, a second end region, and a fulcrum region disposed between the first end region and the second end region. A thrust link-lever may be coupled or couplable to a fulcrum body of an aft engine-mount at a fulcrum position of the thrust link-lever. When coupled to a turbomachine, the fulcrum position of the thrust link-lever may be laterally offset and/or laterally adjustable relative to an axis of rotation of the turbomachine. A load translated from an engine frame of a turbomachine to an engine-mounting linkage system may be determined and a fulcrum position for the thrust mount assembly may be adjusted laterally relative to an axis of rotation of the turbomachine.

Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

Abstract: Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.

Abstract: A system and method for detecting faults and optimiz-ing power usage of solenoid valves. The method includes obtaining a current signature of the solenoid coil, using a dedicated circuit to detect various features and using a pulse width modulation controller optimize the power output of the system. Additionally, using machine learning, the system can be optimized using data from the dedicated circuit.

Abstract: An information processing system acquires an action history including at least one of a purchase history including an item purchased by a user and a browsing history including an item browsed by the user, selects one or more items from the plurality of items as a first item by a first selection method based on the acquired action history, selects one or more items from the plurality of items as a second item by a second selection method different from the first selection method based on the acquired action history, and adds the first item and the second item to the same list.