The OH-58A light observation helicopter has a single main rotor and a two-bladed, semirigid, and teetering antitorque tail rotor. The tail rotor also has a delta-three hinge. The cockpit provides side-by-side seating for a crew of two (pilot and copilot/observer), and the cargo compartment has seats for two passengers. Dual flight controls are provided. The cyclic and collective controls are hydraulically boosted and irreversible, while the tail rotor control is unboosted. The landing gear consists of fixed, energy-absorbing skids. The helicopter is powered by an Allison T63-A-700 free gas turbine engine with a takeoff power rating of 317 shaft horsepower (shp) under sea-level, standard-day uninstalled conditions. The main transmission has a rating of 270 shp for continuous operation, with a takeoff power limit of 317 shp (5-minute rating). A list of the aircraft flight instruments and navigation equipment is shown.
Instrument Flight Evaluation OH-58A Helicopter
1972
60 pages
Report
Keine Angabe
Englisch
Aeronautics , Aircraft , Instrument flight , Attitude control systems , Helicopters , Performance(Engineering) , Flight testing , Stability , Control , Pitch(Motion) , Yaw , Roll , Recovery , Takeoff , Climbing , Handling , Failure , Pilots , Performance(Human) , Aviation safety , Level flight , Night flight , Oh-58a aircraft , H-58 aircraft
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