Accident Summary
On 30 April 2024, at approximately 1144 local time, an F-16C Fighting Falcon (tail number 87-0358) assigned to the 49th Wing, Holloman Air Force Base, New Mexico, crashed about six and a half nautical miles southwest of the departure end of Holloman AFB Runway 25. The aircraft was conducting a Basic Surface Attack training mission within the local airspace. Weather conditions were clear skies with unrestricted visibility and light winds from the west.
Sequence of Events
Thirty-six seconds after takeoff, while at an altitude of 1,030 feet above ground level, the mishap aircraft experienced a loss of engine thrust. The mishap pilot initiated corrective action procedures. Due to low altitude and decreasing airspeed, the pilot ejected one minute and eighteen seconds after the engine loss of thrust. Shortly after ejection, the aircraft was destroyed upon impact within White Sands National Park. The estimated total loss was valued at $21,702,152.
Pilot and Egress
The pilot sustained only minor injuries from the ejection and was recovered by an Army Air helicopter within minutes. The pilot was current, qualified, and medically fit. No relevant aircrew discrepancies or maintenance write-ups were noted on the aircraft when flown the day prior and on the day of the accident. Normal prelaunch and launch procedures were followed.
Maintenance and Inspections
Local maintenance actions leading up to the mishap were conducted in accordance with applicable guidance; however, local maintainers could not access or inspect the fifth stage of the engine. No deviations from publications or directives were identified.
Investigation Findings
The Board President determined, by a preponderance of the evidence, that the cause of the mishap was a misaligned, or turned, number ten position variable stator vane in the fifth stage of the engine. Over time, the airflow disturbance from the turned vane caused high cycle fatigue of a fifth stage compressor blade. The blade eventually separated during flight, causing additional engine damage and significant airflow disruption, resulting in an engine loss of thrust. There was insufficient evidence to determine the cause of the turned vane.