Preliminary Airworthiness Evaluation of Modified Second-Generation Pneumatic Boot Deicing System on a JUH-1H
Abstract
The U.S. Army Aviation Engineering Flight Activity conducted a Preliminary Airworthiness Evaluation of a modified second-generation Pneumatic Boot Deicing System (PBDS) on a JUH-1H helicopter. This consisted of a structural loads survey, level flight performance evaluation, and a qualitative handling qualities evaluation. Twelve flights were conducted for a total of 7.8 productive flight hours. Rotor system structural loads were generally lower than those reported for the unmodified second-generation PBDS. With the PBDS inflated, main rotor pitch link load reached the endurance limit at 100 knots indicated airspeed in level flight. Power required in level flight was less than or equal to power required by the unmodified second-generation PBDS. Inflating the PBDS generated moderate right yaw rates and engine torque rises as great as eight pounds per square inch. One previously identified shortcoming, the aircraft response to PBDS activation during level flight, still exists. Keywords: Endurance limit, Handling qualities, Level flight performance, Pitch link load, PBDS activation during level flight, Structural loads, Helicopters, Rotor blades (Rotary Wings).
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1988
- Accession Number
- ADA206255
Entities
People
- Charles E. Cassil
- James D. Brown
- Michael K. Herbst