ENGINEERING FLIGHT TEST OF UH-1B/540 ROTOR HELICOPTER EQUIPPED WITH XM- 16/M-5, XM-21/M-5 OR XM-3/M-5 ARMAMENT SUBSYSTEM
Final test rept. 13 Nov 1965 - 5 May 1966
ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA
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This report presents the results of an engineering flight test of the UH-1B540 rotor helicopter equipped with the XM-16, XM-21, or XM-3 armament subsystem in conjunction with the M-5 armament subsystem. The test was conducted by the U. S. Army Aviation Test Activity USAAVNTA. Overall test objectives were to verify safety of flight, develope data for the operators manual, and assure that aircraft modifications did not degrade the handling qualities or limit the operational characteristics of the subsystems. Specific objectives were to determine quantitatively the effect of the armament subsystems on stability, control and performance of the aircraft, to determine the rocket launcher jettison characteristics, and to define the usable limits of the flight envelope for safe jettison of the launchers. Testing was conducted at Edwards Air Force Base, California, and at sites in Fort Irwin and Bakersfield, California. A total of 152 flights for a productive flight time of 116.4 hours was flown on aircraft SN 64-14105 between 13 November 1965 and 5 May 1966. This included 30 jettison flights and 35 firing flights.