Fabrication, Instrumentation, Flight Test and Evaluation of an F-4 Beryllium Rudder.

The report describes a program performed to establish the durability of a beryllium aircraft structural component in an actual service environment, to validate the design data and manufacturing techniques used, and to establish confidence in beryllium load carrying aircraft structures. Strain gages were installed to permit in-flight recording of rudder bending strains and hinge moments. Prior to flight testing, the rudder was static proof tested to 100 of design limit load for the maximum rudder airload and hinge moment condition. Early in the flight test program, steady yaw and rolling pullout maneuvers were performed and the resulting rudder strains and hine moments recorded. Author