© 2016 by A. Gatto. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.Unsteady flow around deployed landing gears is a significant contributor to aircraft noise on approach. The farfield sound is largely determined by the fluctuating pressures on the gear surface, quantities that have yet to be fully characterized even for simplified representations. The current work reports axle- and wheel-surface data from a comprehensive set of measurements on a generic, two-wheel, landing-gear model. The results show the expected high levels of unsteadiness on areas exposed to large-scale separated flow, of which some (wheel rear surfaces and forward edges) can be identified from steady data, but others (wheel faces adjacent to axle wakes, flow impingements on sidewalls) cannot. The forward-edge values for the current, untripped configuration are markedly greater than previously reported measurements with artificial transition fixing. Spectral analysis highlights a further category of potentially important contributions that are not easily detected in overall rms values: high-frequency unsteadiness associated with turbulent attached, or attaching, flows. A key implication of these results is the need for accurate representation of the true, full-scale, boundary-layer state in computations and model-scale testing. Copyright