GB925225A - Adjustable control means - Google Patents

Abstract

925,225. Aircraft pedal controls. WESTLAND AIRCRAFT Ltd. June 23, 1961 [July 7, 1960], No. 23725/60. Class 4. An adjustable pedal control system for aircraft has two pedals, each comprising a pedal lever having first and second arms lockably hinged together, and a foot pressure member pivotally carried by one arm and spaced from the hinge axis, the other arm being pivotally mounted about an axis parallel to but spaced from the hinge axis. In Fig. 1, a heel board 2 supports brackets 4 and 5, Figs. 1 and 2, mounting concentric shafts 6 and 7. From each shaft extends a pedal lever comprising arms 8, 19 or 9, 20, hinged at 18, and a foot pressure member 24 or 25. The shafts 6, 7, are connected by linkages 10, 12, 14, and 11, 13, 15, respectively, to a lay shaft 16, so that the pedals move equally in opposite directions. Shaft 16 may also carry levers or cable drums operating the aircraft yaw control. Each member 24 or 25 is pivoted to its arm on a pin 26, and is also pivoted to a rod 27 extending within arm 19 or 20 and normally held in engagement with one of recesses 29 in arm 8 or 9 by a spring 31 acting between the end of arm 8 or 9 and a collar on rod 27. To adjust the position of a pedal without effecting a control movement, member 24 or 25 is raised by the pilot's toe, disengaging rod 27 from a recess 29, and the arm 19 or 20 is rotated about hinge 18 to the desired position. Member 24 or 25 is then released so that rod 27 engages in a new recess 29. Alternatively, the lock on hinge 18 may be operated by hand through a flexible cable.