Abstract: The present disclosure relates to aggregating and sharing wellness data. The wellness data can be received by a user device from any number of sensors external or internal to the user device, from a user manually entering the wellness data, or from other users or entities. The user device can securely store the wellness data on the user device and transmit the wellness data to be stored on a remote database. A user of the device can share some or all of the wellness data with friends, relatives, caregivers, healthcare providers, or the like. The user device can further display a user's wellness data in an aggregated view of different types of wellness data. Wellness data of other users can also be viewed if authorizations from those users have been received.

Abstract: A catcher pin assembly for attachment to a catcher link of an aircraft frame, the catcher pin assembly having an engine mounting element, a catcher pin, a compressible element, and a nut, which is lockable to the catcher pin, the compressible element being compressed between the pin and the mounting element and/or between the mounting element and the nut, in the assembled condition of the assembly, such that the compressible element applies a predetermined resistance to rotation of the catcher pin relative to the mounting element. The invention also relates to a method of testing a catcher pin assembly to determine if the catcher pin is carrying load from the catcher link, the method including applying a predetermined torque to the catcher pin sufficient to overcome the resistance to rotation of the catcher pin when it is unloaded, and determining whether the catcher pin rotates relative to the mounting element.

Abstract: Mounting of gas turbine engines in aircraft requires use of thrust struts associated with mountings. It is important should there be failure that a load path is maintained. Furthermore, on a wing or in-situ inspection is highly desirable with respect to reducing maintenance costs. Of particular concern is failure as a result of cracking both sideways and vertical which may result in loss of all load paths through the mounting. By provision of independent cranks which are associated through crank pivots in apertures of the cranks and then articulation about central pivots provided in apertures and a central element along with pivot association of the struts through pivots created about apertures in the cranks load paths are maintained. By independent provision of the cranks sideways and vertical cracking cannot cause failure in both load paths to the arrangement from the struts.

Abstract: A catcher pin assembly for attachment to a catcher link of an aircraft frame, the catcher pin assembly having an engine mounting element, a catcher pin, a compressible element, and a nut, which is lockable to the catcher pin, the compressible element being compressed between the pin and the mounting element and/or between the mounting element and the nut, in the assembled condition of the assembly, such that the compressible element applies a predetermined resistance to rotation of the catcher pin relative to the mounting element. The invention also relates to a method of testing a catcher pin assembly to determine if the catcher pin is carrying load from the catcher link, the method including applying a predetermined torque to the catcher pin sufficient to overcome the resistance to rotation of the catcher pin when it is unloaded, and determining whether the catcher pin rotates relative to the mounting element.

Abstract: A catcher pin assembly for attachment to a catcher link of an aircraft frame, the catcher pin assembly comprising an engine mounting element 23, a catcher pin 23D, a compressible element 40, 41, 42, 43, and a nut 38 which is lockable to the catcher pin 23D, the compressible element 40, 41, 42, 43 being compressed between the pin and the mounting element and/or between the mounting element and the nut 38, in the assembled condition of the assembly, such that the compressible element 40, 41, 42, 43 applies a predetermined resistance to rotation of the catcher pin 23D relative to the mounting element 23. The invention also relates to a method of testing a catcher pin assembly to determine if the catcher pin 23D is carrying load from the catcher link, the method comprising applying a predetermined torque to the catcher pin 23D sufficient to overcome the resistance to rotation of the catcher pin 23D when it is unloaded, and determining whether the catcher pin 23D rotates relative to the mounting element 23.

Abstract: Mounting of gas turbine engines in aircraft requires use of thrust struts associated with mountings. It is important should there be failure that a load path is maintained. Furthermore, on a wing or in-situ inspection is highly desirable with respect to reducing maintenance costs. Of particular concern is failure as a result of cracking both sideways and vertical which may result in loss of all load paths through the mounting. By provision of independent cranks which are associated through crank pivots in apertures of the cranks and then articulation about central pivots provided in apertures and a central element along with pivot association of the struts through pivots created about apertures in the cranks load paths are maintained. By independent provision of the cranks sideways and vertical cracking cannot cause failure in both load paths to the arrangement from the struts.