Preliminary Airworthiness Evaluation of the OH-58C with 3-Axis Stability Control Augmentation System and Improved Tail Rotor System.
Final rept. 20 Jun-11 Sep 83,
ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
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This preliminary airworthiness evaluation was conducted on an OH-58C helicopter configured with a 3-axis digital stability control augmentation system SCAS and an improved tail rotor. Additional testing on the standard OH-58C equipped with the 3-axis SCAS was required in response to questions which surfaced during working sessions of the Joint Special Study Group investigating 0H-58 loss of tail rotor effectiveness. Testing was accomplished at Arlington, TX elevation 630 feet, Leadville, CO elev. 9927 feet and Alamosa, CO elev. 7535 feet. Test time totaled 44.2 productive flight test hours. With the improved tail rotor, adequate directional control margins were available for flight at all azimuths out to the wind limits 35 KTAS sideward and 30 KTAS rearward of the aircraft at density altitudes up through 11,000 feet for a gross weight of 3,040 lb. The overall handling qualities of the OH-58C helicopter equipped with a 3-axis digital SCAS in either tail rotor configuration were significantly improved over the unaugmented aircraft configuration except as stated in the report. TWo handling quality deficiencies were noted.