In this study, quality improvement is performed by applying a dual-mode steering system to alleviate direction control sensitivity at high speeds during takeoff and landing of aircraft. In the dual-mode steering system, a normal (low gain) mode with a steering range of 12 degrees and a low speed (high gain) mode with an existing steering range of 40 degrees can be selected as needed. For applying the dual steering mode, the aircraft configuration is changed by adding electrical resistance and relay, light, and wire harness, and electrical circuits and steering schematics are improved. This quality improvement has been verified by confirming the normal operation through analysis of aircraft system, weight, safety, parts, structural integrity, mode identification, and electromagnetic compatibility. In addition, the operation tests consisted of ground test, ground taxiing and flight test are conducted for further verification. As a result, the normal operation has been confirmed through the ground test, and the pilot's qualitative evaluation is rated 'level 3 or higher' based on the ground taxiing and flight test. Thus, in this study, the quality of aircraft is improved by implementing the dual-mode steering system, and the validity of this implementation and aircraft safety are verified accordingly.