Airworthiness and Flight Characteristics of the JOH - 58C (OH-58X surrogate) Helicopter
Final rept. 27 Jun-23 Oct 1985
ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
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The US Army Aviation Engineering Flight Activity conducted a limited airworthiness and flight characteristics test of the JOH-58C Light Combat Helicopter LCH from 27 June through 23 October 1985. The JOH-58C LCH configuration includes a stability augmentation system manufactured by the SFENA Corporation and a larger-diameter tail rotor. Handling qualities were evaluated at test sites from near sea level 488 feet to 9980 feet. A total of 49 flights were conducted for a total of 34.6 productive flight test hours. Primary emphasis during the evaluation was placed on evaluating the handling qualities of the JOH-58C in comparison to the standard OH-58C. The overall handling qualities of the JOH-58C were significantly improved as compared to the standard OH-58C. The JOH-58C exhibited less than 10 longitudinal control margin in rearward flight at speeds of approximately 17 knots and above at azimuths between 180 and 210 degrees. This characteristic is a deficiency. The pitch, roll and yaw excursions during low speed flight of the JOH-58C are significantly reduced as compared to the standard OH-58C. These handling qualities characteristics, which were a deficiency in the OH-58C, have been improved shortcomings or were eliminated under the conditions tested in the JOH-58C. Two additional shortcomings were identified in maneuvering flight.