Abstract: This invention relates to compounds of Formula (I): and enantiomers thereof, and to pharmaceutically acceptable salts of Formula (I) and said enantiomers, wherein L1, L2, R1, R2, R3 and n are as defined herein. The invention further relates to pharmaceutical compositions comprising such compounds and salts, and to methods and uses of such compounds, salts and compositions for the treatment of abnormal cell growth, including cancer, in a subject in need thereof.

Abstract: Provided for herein is a method of cell transplantation using an injection attachment having a hub containing a plurality of cells and a cannula extending from a distal end of the hub. The method includes orienting the injection attachment such that the cannula points downwardly until the plurality of cells settle together proximate the distal end, inserting the cannula into a tissue of a subject, and injecting the volume of cells into the tissue of the subject using the injection attachment.

Abstract: Methods and apparatus consistent with the invention provide the ability to organize, index, search, and present time series data based on searches. Time series data are sequences of time stamped records occurring in one or more usually continuous streams, representing some type of activity. In one embodiment, time series data is stored as discrete events time stamps. A search is received and relevant event information is retrieved based in whole or in part on the time stamp, a keyword indexing mechanism, or statistical indices calculated at the time of the search.

Abstract: A support structure for an aircraft includes a structural member having a generally planar shape, a longitudinal axis defining a longitudinal direction and a transverse axis orthogonal to the longitudinal axis, and a plurality of rounded holes formed along the longitudinal direction. Each rounded hole has a respective major axis with a major length and a minor axis orthogonal to the major axis with a minor length that is less than the major length. Each rounded hole is oriented with its major axis rotated more than 0 degrees and less than 90 degrees from the longitudinal axis of the structural member. The structural member is configured for bearing external loads acting on the structural member in a principal loading direction that is not parallel with the longitudinal axis or the transverse axis. Each rounded hole may be oriented with its major axis aligned generally parallel with the principal loading direction.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.