On Friday May 6, A SpaceX Dragon capsule successfully completed a pad abort test at Kennedy Space Center. The abort test was performed by the same propulsion system that is envisioned to land Dragon 2 with precision in the near future. Dragon 2's capsule propulsion system differs from the experimental, reusable Falcon 9 booster, and the possibility to experience similar flight instability problems is minor.
However, there is a lesson learned as a result the F9R experimental flights - the fact that the first stage failed to reduce significantly the range uncertainty solely by adjusting supersonic retro-burns. In science and technology, the negative results are sometime more significant than positive results, but this finding was obscured by advertising the "invention" of the ‘X-wings’. The grid fins, by using the lifting body properties of slender rocket body, have made the real breakthrough: reducing the landing point uncertainty from 10 miles to 10 meters. On the other side, experimental rocket landers like Morpheus and Xombe demonstrate less than a half mile lateral maneuvers at very high Delta V loss ( > 500 m/s) even after hard optimization.
As Dragon 2 does not appear to have any aerodynamic controls or significant lifting body abilities at transonic and subsonic speeds, how will it perform a pinpoint landing?
SpaceX animation do not shows the flight phase between hypersonic deceleration and retroburn. SpaceX animation