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Background: This cross-sectional study investigates the educational background and entry routes of otolaryngology higher surgical trainees in the UK. Method: A survey was disseminated to trainees through training programme directors and 60 responses were received. Results: Most trainees decided to pursue otolaryngology early in their training, with 50 per cent making the decision four or more years before applying for a higher surgical traineeship. Similarly, 68.3 per cent of trainees undertook otolaryngology-themed core surgical training, while two-thirds had an otolaryngology rotation during their foundation training. Most trainees (86.7 per cent) were accepted into core surgical training on their first attempt, and 71.7 per cent gained entry to higher surgical training on their first attempt. Conclusion: The findings highlight the importance of early exposure to otolaryngology and the pursuit of themed core surgical training programmes for building a competitive application. However, unsuccessful first attempts at core surgical training or higher surgical training should not discourage candidates from pursuing a career in otolaryngology. [ABSTRACT FROM AUTHOR]

A comprehensive design cycle of a nose landing gear strut having an oleo-pneumatic shock absorber for a lightweight aircraft is proposed. Design and analysis of a retractable nose landing gear according to Airworthiness Standards FAA FAR Part 23 have been carried out. This research is focused on mathematical modeling of an oleo-pneumatic strut with an analytical solution of design variables at static and dynamic loading conditions. The variation of spring and damping characteristics of an oleo-pneumatic shock absorber with the stroke length is also presented. Feasibility of equivalent mechanical spring and damper along with comparison of pneumatic as air spring and oleo as hydraulic damper is studied. Numerical integration technique was used to solve the dynamic model of an oleo-pneumatic strut with forcing function of an impact force during touch down scenario. Energy conservation principle was used to determine height required for drop tests. Parametric study of anteversion angle within the constraints of ground clearance and volume in the fuselage determined an optimized angle of nose landing gear strut. Based on the maximum pressure and impact force encountered during landing, the hydraulic cylinder and piston design was finalized. In order to validate the proposed design cycle for preliminary phase, a structural integrity of cylinder and piston assembly was carried out using finite element analysis. Deformation, maximum stresses and factor of safety validated the proposed design cycle of a nose landing gear strut specific to a general aviation aircraft having all up mass of 1600 Kg. [ABSTRACT FROM AUTHOR]