Accession Number : AD0907317

Title :   Instrument Flight Evaluation OH-58A Helicopter.

Descriptive Note : Final rept. 8 Jan-24 Feb 72,

Corporate Author : ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA

Personal Author(s) : Smith, John R. ; Benson, Tom P.

Report Date : SEP 1972

Pagination or Media Count : 60

Abstract : 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.

Descriptors :   (*INSTRUMENT FLIGHT, HELICOPTERS), (*ATTITUDE CONTROL SYSTEMS, PERFORMANCE(ENGINEERING)), FLIGHT TESTING, STABILITY, CONTROL, PITCH(MOTION), YAW, ROLL, RECOVERY, TAKEOFF, CLIMBING, HANDLING, FAILURE, PILOTS, PERFORMANCE(HUMAN), AVIATION SAFETY, LEVEL FLIGHT, NIGHT FLIGHT.

Subject Categories : Helicopters

Distribution Statement : APPROVED FOR PUBLIC RELEASE