Door locking system with a rapid release mechanism

A method for operating a door module that is configured to separate compartments of an aircraft and that includes a door panel, a door frame, and a locking element, the locking element having at least a first state and a second state, and in the first state the locking element being protruded between the door panel and the door frame to maintain the door panel in a closed position and in the second state the locking element being retracted and not protruding between the door panel and the door frame to enable the release of the door panel from the closed position, the method comprising:

• enabling, by a first mechanism, a first movement of the door panel from the closed position to an opened position by a handle of the first mechanism acting on the locking element to retract the locking element from protruding between the door panel and the door frame and thereby transition the locking element from the first state to the second state and enabling, by the first mechanism, a second movement of the door panel from the opened position to the closed position, the first mechanism further including a first locking element release actuator that is coupled to the locking element and that when actuated allows the locking element to be transitioned by the handle of the first mechanism from the first state to the second state;
• enabling, by a second mechanism acting on the locking element, a third movement of the door panel from the closed position to the opened position, the second mechanism including a second locking element release actuator that is coupled to the locking element and that when actuated retracts the locking element from protruding between the door panel and the door frame and thereby performs a transition of the locking element from the first state to the second state, wherein the second mechanism is spatially segregated from the first mechanism and operates independently of the first mechanism;
• using a pressure sensor to monitor a difference in pressure between compartments of an aircraft;
• determining whether the difference in pressure between the compartments of the aircraft exceeds a predetermined air pressure difference threshold;
• in response to determining that the difference in pressure between the compartments of the aircraft exceeds the predetermined air pressure difference threshold, using a controller to direct the second locking element release actuator to perform a transition of the locking element from the first state to the second state;
• and
• actuating the second locking element release actuator to perform the transition of the locking element from the first state to the second state.