Abstract: A component configured for use in a gas turbine engine, including: a wall portion formed from sheet metal and extending between two end portions, the wall portion being stamped with a plurality of instances of a pre-defined three dimensional shape structured to increase a stiffness of the wall portion in a direction normal to the wall portion, each instance of the plurality of instances of the pre-defined three dimensional shape being orientated at 90 degrees with respect to each other adjacent instance of the plurality of instances, wherein the three dimensional shape has a pair of curved distal peripheral end portions that are at opposite ends of the three dimensional shape and each pair of curved distal peripheral end portions are connected to each other by a pair of opposing concave peripheral portions that curve towards each other at a mid-section.

Abstract: The relative position and orientation between an auxiliary gearbox and a casing of an aircraft engine can be set including engaging a localizing feature of the accessory gearbox with a localizing feature of the casing; and a load path between auxiliary gearbox can subsequently be defined including securing at least two brackets between the accessory gearbox and casing.

Abstract: The gas turbine engine can have a casing, a rotor rotatable around a rotation axis relative the casing, the casing extending along and around the rotation axis, a first component mounted externally to the casing by a first mount, the first mount defining a torsion axis extending along a vertical radial orientation normal the rotation axis, the first component having a center of gravity located on a first side relative the torsion axis, a second component mounted externally to the casing on the second side, extending along the vertical radial orientation from a bottom portion to a top portion, a second mount structurally connecting the bottom portion to the casing, and a structure connecting the top portion to the first component on the second side relative the torsion axis.

Abstract: An adjustable mount for an aircraft engine accessory. A first bracket adapted to be coupled to the engine accessory has a first bore with a first annular bushing with a threaded radially inner surface extending through the first bore. A second bracket operatively coupled to the engine at mounting location has a second bore with a second annular bushing with a threaded radially inner surface extending through the second bore. A threaded stud extends axially through the first and second bushings and is engaged with their threaded inner surfaces. Rotation of the first and/or second bushings varies the relative axial positions of the first and second bushings on the stud, thereby adjusting an axial gap between first and second brackets. First and second nuts fastened to first and second ends of the threaded stud axially retain the mount together with the axial gap between the first and second brackets fixed.

Abstract: The gas turbine engine can have a casing, a rotor rotatable around a rotation axis relative the casing, the casing extending along and around the rotation axis, a first component mounted externally to the casing by a first mount, the first mount defining a torsion axis extending along a vertical radial orientation normal the rotation axis, the first component having a center of gravity located on a first side relative the torsion axis, a second component mounted externally to the casing on the second side, extending along the vertical radial orientation from a bottom portion to a top portion, a second mount structurally connecting the bottom portion to the casing, and a structure connecting the top portion to the first component on the second side relative the torsion axis.

Abstract: The relative position and orientation between an auxiliary gearbox and a casing of an aircraft engine can be set including engaging a localizing feature of the accessory gearbox with a localizing feature of the casing; and a load path between auxiliary gearbox can subsequently be defined including securing at least two brackets between the accessory gearbox and casing.