A rotor speed indication system for a twin engine rotorcraft having a rotor, the rotor speed indication system comprising: a display configured to dynamically redefine information communicated to a pilot upon entering one engine inoperable conditions, wherein the display comprises three vertical bar gauges (52, 54, 56); a governing reference indicator bar located on the display, the governing reference indicator bar configured to communicate an upper operating range threshold during one engine inoperable conditions; wherein dynamically redefining information communicated to a pilot upon entering one engine inoperable conditions comprises displaying a droop reference indicator bar located on the display during the one engine inoperable conditions, the droop reference indicator bar being configured to communicate a lower operating range threshold during the one engine inoperable conditions, wherein the droop reference indicator bar is depicted as a horizontal bar, and wherein the droop reference indicator bar passes across all three vertical bar gauges (52, 54, 56); a sensor configured to measure a current rotor speed of the rotor; and a dynamic rotor speed indicator located on the display, the dynamic rotor speed indicator being configured to communicate the current rotor speed of the rotor; wherein, during the one engine inoperable conditions, the governing reference indicator bar and the droop reference bar define a rotor speed operating range on the display; and wherein, during the one engine inoperable conditions when the dynamic rotor speed indicator is positioned between the governing reference indicator bar and the droop reference indicator bar on the display, the current rotor speed of the rotor is within the rotor speed operating range. a display configured to dynamically redefine information communicated to a pilot upon entering one engine inoperable conditions, wherein the display comprises three vertical bar gauges (52, 54, 56); a governing reference indicator bar located on the display, the governing reference indicator bar configured to communicate an upper operating range threshold during one engine inoperable conditions; wherein dynamically redefining information communicated to a pilot upon entering one engine inoperable conditions comprises displaying a droop reference indicator bar located on the display during the one engine inoperable conditions, the droop reference indicator bar being configured to communicate a lower operating range threshold during the one engine inoperable conditions, wherein the droop reference indicator bar is depicted as a horizontal bar, and wherein the droop reference indicator bar passes across all three vertical bar gauges (52, 54, 56); a sensor configured to measure a current rotor speed of the rotor; and a dynamic rotor speed indicator located on the display, the dynamic rotor speed indicator being configured to communicate the current rotor speed of the rotor; wherein, during the one engine inoperable conditions, the governing reference indicator bar and the droop reference bar define a rotor speed operating range on the display; and wherein, during the one engine inoperable conditions when the dynamic rotor speed indicator is positioned between the governing reference indicator bar and the droop reference indicator bar on the display, the current rotor speed of the rotor is within the rotor speed operating range.