Military Potential Test of Primary Helicopter Trainers.
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 22, 1967
- Accession Number
- ADA031688