Abstract: A helicopter speed display for displaying the maximum speed of a helicopter under current conditions is disclosed. The display includes a first scale indicative of the actual airspeed of a helicopter and a second scale juxtapositioned on the first scale for displaying a maximum airspeed under current conditions of altitude, temperature and weight in order to avoid retreating blade stall.

Abstract: A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.

Abstract: A tactile warning system for warning a helicopter pilot of a pre-selected altitude during a landing maneuver includes a collective control arm for control of the aircraft and a tactile warning device operatively connected to the collective control arm. The system includes a radio altimeter for sensing the actual altitude, a computer and keyboard for inputting a pre-selected height above the ground into the computer memory. A signal generator generates a signal indicative of the actual altitude as the aircraft approaches the ground. Then, when the actual altitude is equal to or less then the pre-selected altitude the system activates the tactile device. The warning system indicative of reaching a pre-selected height is also combined with a tactile warning system for avoiding “hot starts” and for avoiding other dangerous conditions.

Abstract: A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.

Abstract: An airborne obstacle detector for a helicopter includes a visual display, a GPS receiver and an altimeter for indicating the position and course of an aircraft. A computer provides moving map data indicative of a topography of an area which surround the position of the aircraft. The computer determines a first hazard zone within a first preselected distance from the aircraft and generates a first color display of a first hazard zone based on the moving map data. The computer also detects a more danger zone within a second preselected distance from the aircraft which is less then the first preselected distance and generates a second color display of the more dangerous zone. A detector then senses a physical obstacle which is within a third preselected distance from the aircraft which is less than the first preselected distance from the aircraft and sends a signal to an alarm. The alarm then produces a series of audible clicks which increase in frequency and/or volume as the aircraft approaches the obstacle.