On 3 January 1967, the US Army Test and Evaluation Command directed the US Army Aviation Test Board to conduct a military potential test of commercial off-the-shelf primary helicopter trainers to assist the US Army Aviation Materiel Command during evaluation of the first-step proposals Test Helicopter C was received for test on 19 April 1967 and testing began on 19 April 1967. Helicopter C has a two-bladed, semirigid main rotor and a two-bladed antitorque rotor. The helicopter is powered by a 260 shaft horsepower, Lycoming VO-435-B1A, six-cylinder reciprocating engine. The two-place helicopter has side-by-side seats and dual flight controls. The cabin area is inclosed in a bubble-type tinted plastic canopy. The helicopter has skid-type landing gear. The main fuselage and tail boom are of truss-type construction with all drive components visible. The engine drives the rotor system through a self-engaging centrifugal clutch which transfers power to the two-stage planetary gear system in the transmission. A sprag-type overrunning clutch disengages the rotor for autorotation. The engine is vertically mounted within the truss frame of the fuselage.
Military Potential Test of Primary Helicopter Trainers
1967
14 pages
Report
No indication
English
Online Contents | 1995
|Potential of Part-Task-Trainers for Military Training
British Library Conference Proceedings | 1993
|American military aircraft -- Liaison-trainers
Engineering Index Backfile | 1943