Engineer Design Test 2 Hughes YAH-64 Advanced Attack Helicopter
Abstract
In general, the performance of the helicopter in terms of power required has deteriorated from DT 1, although there is a slight performance improvement in level flight between approximately 50 and 90 knots true airspeed (KTAS). Tail rotor performance has markedly deteriorated from DT 1. The starting procedure utilized on the YAH-64 helicopter is an enhancing characteristic and should be incorporated in future Army aircraft where possible. There were seven deficiencies (2 previously defined) and 43 shortcomings identified (16 previously defined). The deficiencies include: the possibility of dual-engine fuel starvation with useable fuel remaining; the restricted forward field of view during the landing flare; the inability to control heading with Automatic Stabilization Equipment disengaged at the critical azimuth between 25 to 40 KTAS; insufficient left directional control margin in right sideward accelerations; the lack of adequate cues to warn the pilot of a partial power engine malfunction; low activation threshold of the Low Main Rotor RPM warning; excessive 4/rev lateral vibration (pilot seat) during the termination of the approach and in level flight at airspeeds less than 50 and greater than 130 knots calibrated airspeed (KTAS). Canopy drumming characteristics had improved from Engineer Design Test 1 (EDT 1) but remain a shortcoming.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1979
- Accession Number
- ADA098923
Entities
People
- Ralph Woratschek
- Richard C. Tarr
- Steven J. Snackenberg
- Tom P. Benson
- Vernon L. Diekmann