This paper had not been easy to prepare because any adequate treatment of recent investigations and research would have to pre-suppose in the engineer-reader a whole body of information which it would not be reasonable to suppose he has. Further, the author's pitch had been cleared, for nearly three years ago the Institution of Production Engineers published a paper by him entitled : "A Survey of Selection and Allocation for Engineering Occupations."

After much thought, he decided to deal mostly with some of the fundamental ideas underlying selection, and to offer a bibliography to assist readers who so desire, to gain further knowledge of the underlying facts and theories of Occupational Psychology and of the application of these to investigations which have been carried out in the allied fields of vocational guidance and selection, and to procedures which are being increasingly used.

If the motion of an aircraft is restricted, near the ground, to zero bank, comparatively simple solutions to the resulting equations of motion can be obtained, enabling the response to an applied yawing moment to be calculated rapidly. In this paper the analysis is made for three simple forms of applied yawing moment. From the results obtained in a particular case it is possible to judge the suitability of the fin and rudder design chosen on the basis of maximum sideslip reached. A general curve of overswing, in terms of the aerodynamic derivatives of the aircraft, enables the maximum sideslip to be calculated rapidly in a particular case.

Because of typogiaphical difficulties the symbols ^ have been replaced by ° with v, r and t throughout the paper.

A description of a test made recently in this test rig should prove of interest to those engaged in the design, stressing and structural testing of large aircraft structures, particularly wings, in that it would appear to represent a considerable advance over any previous test of this nature made in this country, and opens up new fields in simplicity and speed of application of the loads. The full load was applied to the wing in this test by one operator in approximately 50 seconds, thus approaching much more nearly than on any previous test made here the conditions which occur in flight.