Inverted? No, it is erect, and you can see that from the close up photos of the wreckage.
In response to a number of flat spin accidents in the Beech Baron, the US Army spin tested the airplane in 1974. One of the most noteworthy published findings was that it took less than one second for the airplane to spin following a single-engine stall. Immediate recovery action was needed to avoid spinning. In 1998 and 2002 the Raytheon Aircraft Company published safety communiqués reporting the results of 229 spins in Baron Models 58 and 58P. With the windmilling left engine idle with max continuous power on the right engine throughout the stall, entry to beyond 270 degrees of rotation, the spin was unrecoverable requiring the deployment of the spin chute. Part of Raytheon’s published recommendations was:
“During single-engine operation (actual or simulated), at the first indication of approach to stall (the stall warning horn, buffeting, or both) stall recovery must be initiated immediately … if this instruction is not followed, a stall will occur and a dangerous spin is likely to occur”.
Just my observation, the 421 having the swept back fin, the same as the Baron, the rudder would be blanked from the airflow by the tailplane and rendered useless ie irrecoverable spin, unless caught during the first turn, as in the Baron case. Just guessing,
DAR would be able to give insight.
http://www.faa.gov/news/safety_brief...sepoct2012.pdf