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In recent years, helicopter flight and mission information has migrated from conventional round mechanical dials mounted on the instrument panel to software-dependent head-mounted displays capable of showing many types of information. Test and evaluation techniques have not progressed commensurate with display technology. A formal test and evaluation program is proposed to ensure that new information displays support the pilot’s flight tasks. An outline of test requirements is presented for use in future flight display programs.

A fluid depressant ice protection system has been installed on a Cessna 206 airplane. The system exudes an ethylene glycol solution over the leading edges of the wings, empennage, and lift struts. A slinger ring is used to distribute fluid to the propeller. The windshield is de-iced with a glycol spraybar. The system adds about thirty pounds to the empty weight of the airplane. Installation of ice protection equipment on a fixed-gear, single-engine airplane presents some unique instrumentation problems since probes must avoid the residual glycol spray from the propeller. Satisfactory anti-icing performance has been demonstrated within the FAR 25, Appendix C continuous maximum and intermittent maximum envelopes during flights in natural icing conditions.