A method to inspect composite components (300, 350) of an aircraft (401, 501), the method comprising: selecting composite components of an aircraft for ultrasonic inspection; traversing a plurality of ultrasonic probe arrays (204a, 204b, 204c) capable of being repositioned at one or more angles from each other on a respective plurality of component surfaces (304a, 312b, 308a; 354a, 362b, 358a) on the aircraft that are either separate from or at angles to each other; passing multiple ultrasonic signals into the plurality of component surfaces (304a, 312b, 308a; 354a, 362b, 358a) of the aircraft (401, 501) from the plurality of ultrasonic probe arrays (204a, 204b, 204c) by transmitting multiple ultrasonic signals from the plurality of ultrasonic probe arrays (204a, 204b, 204c), wherein the component surfaces are either separate from or at angles to each other; and detecting the ultrasonic signals transmitted through or reflected from the composite components of the aircraft at the plurality of ultrasonic probe arrays (204a, 204b, 204c) by: receiving a plurality of response signals to the respective multiple ultrasonic signals at the plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a), each response signal received from a respective composite component surface in response to a respective ultrasonic signal; aggregating the plurality of response signals to form the response to the ultrasonic signals; inspecting the component based on the response to the ultrasonic signal; and repeating the above steps in a new inspection pass, wherein the plurality of ultrasonic probe arrays (204a, 204b, 204c) are repositioned in relation to each other between inspection passes on a respective plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a) of the aircraft (401, 501) that are separate from or at angles to each other. selecting composite components of an aircraft for ultrasonic inspection; traversing a plurality of ultrasonic probe arrays (204a, 204b, 204c) capable of being repositioned at one or more angles from each other on a respective plurality of component surfaces (304a, 312b, 308a; 354a, 362b, 358a) on the aircraft that are either separate from or at angles to each other; passing multiple ultrasonic signals into the plurality of component surfaces (304a, 312b, 308a; 354a, 362b, 358a) of the aircraft (401, 501) from the plurality of ultrasonic probe arrays (204a, 204b, 204c) by transmitting multiple ultrasonic signals from the plurality of ultrasonic probe arrays (204a, 204b, 204c), wherein the component surfaces are either separate from or at angles to each other; and detecting the ultrasonic signals transmitted through or reflected from the composite components of the aircraft at the plurality of ultrasonic probe arrays (204a, 204b, 204c) by: receiving a plurality of response signals to the respective multiple ultrasonic signals at the plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a), each response signal received from a respective composite component surface in response to a respective ultrasonic signal; aggregating the plurality of response signals to form the response to the ultrasonic signals; inspecting the component based on the response to the ultrasonic signal; and transmitting multiple ultrasonic signals from the plurality of ultrasonic probe arrays (204a, 204b, 204c), wherein the component surfaces are either separate from or at angles to each other; and detecting the ultrasonic signals transmitted through or reflected from the composite components of the aircraft at the plurality of ultrasonic probe arrays (204a, 204b, 204c) by: receiving a plurality of response signals to the respective multiple ultrasonic signals at the plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a), each response signal received from a respective composite component surface in response to a respective ultrasonic signal; aggregating the plurality of response signals to form the response to the ultrasonic signals; inspecting the component based on the response to the ultrasonic signal; and receiving a plurality of response signals to the respective multiple ultrasonic signals at the plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a), each response signal received from a respective composite component surface in response to a respective ultrasonic signal; aggregating the plurality of response signals to form the response to the ultrasonic signals; inspecting the component based on the response to the ultrasonic signal; and repeating the above steps in a new inspection pass, wherein the plurality of ultrasonic probe arrays (204a, 204b, 204c) are repositioned in relation to each other between inspection passes on a respective plurality of composite component surfaces (304a, 312b, 308a; 354a, 362b, 358a) of the aircraft (401, 501) that are separate from or at angles to each other.