Patent ID: 7631837

Claim:
An interlock and indication system for use with an aircraft having a hinged tail section comprising: a latch/lock actuation system located in the tail section and having a mechanical interlock component; a ground tail support for engaging the mechanical interlock component and for providing power to the tail section from a power source independent of the aircraft to enable operation of the latch/lock actuation system, and the tail support providing an electrical interlock signal from a ground electrical bus to the latch/lock actuation system; a plurality of electrical control circuits located in the tail section and in an aircraft fuselage portion, wherein the electrical interlock signal provides power to the electrical control circuits; an over rotation power shutoff switch that provides a first electrical signal to the tail support to inhibit over rotation of the tail section by the tail support; and the latch/lock actuation system having a plurality of limit switches that each provide a second electrical signal to the tail support to prevent operation of the tail support to open or close the tail section if a plurality of latch pins in the tail section are not fully retracted.