VICKERS VC10 Part Five—Systems, Equipment and Testing: Brief Descriptions of the Flying Control, Hydraulic, Electrical, Pressurization, Fuel and Anti‐Icing Systems and Auxiliary Equipment

Abstract

THIS has already been dealt with in some detail in the first article describing the aerodynamic features of the VC10, but it is relevant here to discuss the controls from the systems viewpoint. Eleven powered flying control units are incorporated in the system; four aileron units, four elevator units and three rudder units. The units are fully‐powered and arranged such that each operates, independently, a portion of a split control surface. A high degree of interchangeability has been achieved by manufac‐turing a basic unit which can be readily adapted for the operation of any one of the three control surfaces, so that the spares and maintenance problem is eased. Each unit consists basically of the standard Boulton Paul hydraulic pump which supplies fluid to a hydraulic ram connected directly to a control surface. The power control consists of two pumping elements one of which operates on the ‘live‐line’ principle and generates a servo pressure of approximately 280 lb./sq. in., together with a main pressure pump, controlled by a servo valve, which supplies fluid direct to the hydraulic ram.

Citation

(1962), "VICKERS VC10 Part Five—Systems, Equipment and Testing: Brief Descriptions of the Flying Control, Hydraulic, Electrical, Pressurization, Fuel and Anti‐Icing Systems and Auxiliary Equipment", Aircraft Engineering and Aerospace Technology, Vol. 34 No. 6, pp. 182-184. https://doi.org/10.1108/eb033570