Monitoring and/or control system for a dual-engine helicopter for one engine inoperative flight operations

摘要

A monitoring and control system for a dual-engine helicopter for OEI flight operations includes a parametric indicator operative in response to sensor signals for monitoring an engine gas generator speed parameter N1 during dual-engine and OEI flight operations. The indicator includes a rotatable needle that provides an analog indication of the current value of the N1 parameter. For dual-engine flight operations, the indicator includes a first DE indicia defining a normal operating range for the N1 parameter, a second DE indicia that defines a precautionary operating range for the N1 parameter, and a DE indicium that defines a take off power limit for the N1 parameter. For OEI flight operations, the indicator further includes an expanded scale, OEI indicia that defines an OEI precautionary operating range for the N1 parameter having a lower limit of that defines a maximum continuous OEI power rating for the N1 parameter, a first OEI indicium that defines a 2- minute OEI power rating for the N1 parameter, a second OEI indicium that defines a 30-second OEI power rating for the N1 parameter. The first and second OEI indicia in combination define a 30-second OEI operating range for the N1 parameter, and the first OEI indicium and the DE indicium in combination define a 2- minute OEI operating range for the N1 parameter. The indicator further includes a first dedicated bi-colored lamp fixture disposed in combination with the first OEI indicium that is operative in response to a first activation signal to illuminate in a first color to indicate that the 2-minute OEI power rating is enabled and is operative in response to a second activation signal to illuminate in a second color to indicate that the helicopter is being operated in the 2-minute OEI operating range, and a second dedicated bi-colored lamp fixture disposed in combination with the second OEI indicium that is operative in response to a first activation signal to illuminate in a first color to indicate that the 30- second OEI power rating is enabled and is operative in response to a second activation signal to illuminate in a second color to indicate that the helicopter is being operated in the 30- second OEI operating range. Control during OEI flight operations is provided by a three-position OEI switch assembly integrated in combination with the grip of the cyclic control stick, the three- position OEI switch assembly including a three- position select switch that is manually operable to select the 30-second OEI power rating, the 2-minute OEI power rating, or the maximum continuous OEI power rating for OEI flight operations by manual manipulation of the three-position select switch to a first position, a second position, and a third position, respectively.