The evaluation consisted of limited level flight performance tests and stability and control tests. Within the scope of tests all but six stability and control requirements of the detail and military specifications were met. Correction of two deficiencies is mandatory for acceptable mission capabilities. These deficiencies are the static and dynamic longitudinal stability improved helicopter capabilities. Safety of flight was affected by aft rotor blade stall characteristics in maneuvering flight and bank angles above 30 degrees and requires a reduction in maximum bank angles permitted. High aft rotor flight control component stress levels associated with maneuvering flight and operation at limit airspeeds requires that a visual flight loads display be incorporated in the cockpit.
Engineering Flight Test of the YCH-47C Medium Transport Helicopter. Army Preliminary Evaluation II
1969
204 pages
Report
No indication
English
Aircraft , Aeronautics , Aerodynamics , Helicopters , Flight testing , Transport aircraft , Stability , Failure , Acceptability , Maneuverability , Airspeed , Aerodynamic loading , Performance(Engineering) , Noise , Vibration , Helicopter engines , Helicopter rotors , Level flight , Pitch(Motion) , Aviation safety , Stalling , Turning flight , Flight control systems , Yaw , Roll , Takeoff , Aircraft landings , Ch-47 aircraft , H-47 aircraft , T-55 engines , T-55-l-11 engines , T-55-l-7c engines , Ych-47c aircraft