The E6-B encountered Limit Cycle Oscillation (LCO) during flutter flight testing while evaluating the aeroelastic stability effects of three new radomes. LCO can cause structural damage from a low frequency, structural oscillation that neither increases nor decreases in amplitude over time. Testing ceased after LCO initiated on the rudder while the E6-B was accelerating at level flight from 0.75M to 0.80M. The E-6B flutter test team developed a methodological, root cause analysis test and identified structural degradation of the rudder as the cause of the observed LCO. The LCO investigation for this event was successfully completed, and lessons learned will be beneficial to other engineers that may encounter these events.
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