The method 3400 of FIG. 34 thus enables dynamic modification to the initial trajectory profile 232 in response to impermissible flight conditions. As a non-limiting example, the initial trajectory profile 232 can indicate that the first turn has a turn radius of 5 kilometers to pass through the waypoint 234. However, due to impermissible flight conditions (e.g., an airspeed of 880 kilometers per hour), completion of the first turn at the turn radius can result in an error condition. For example, completing the first turn at the airspeed of 880 kilometers per hour violates the operational rule 226. Thus, to ensure a better flight experience for passengers, the flight management system 202 modifies the initial trajectory profile 232 to comply with the operational rule 226.
FIG. 35 is a block diagram of an illustrative implementation of the aircraft 100 that includes components of the system 200. As shown in FIG. 35, the aircraft 100 includes an airframe 3518, a plurality of systems 3520, and an interior 3522. Examples of the plurality of systems 3520 include one or more of a propulsion system 3524, an electrical system 3526, an environmental system 3528, the system 200, and a sensor system 3532. The sensor system 3532 includes one or more sensors onboard the aircraft 100 and configured to generate sensor data during operation of the aircraft 100. The system 200 includes the flight management system 202, the memory 204, the input interface 206, the flight condition monitor 208, and the display screen 210.
