FM575

Looking at the Restart states from Rev 576 we have the following results for FM575.
FM575		NoBurn	Plan	OD	Plan-NoBurn	OD-NoBurn	Plan-OD	SMA error	PC error	
MMS	Epoch of Plan Apogee	A(km)	A (km)	A (km)	A (km)	A (km)	A (km)			
MMS1	Oct 06 2016 18:49:13.239	42105.505	42105.289	42105.289	-0.21613	-0.21648	0.00035	-0.16%	-3.62%	
MMS2	Oct 06 2016 18:49:15.955	42105.505	42105.192	42105.193	-0.31325	-0.31170	-0.00156	0.50%	-3.44%	
MMS3	Oct 06 2016 18:49:16.416	42105.488	42105.827	42105.824	0.33896	0.33582	0.00315	0.93%	-0.40%	
MMS4	Oct 06 2016 18:49:11.452	42105.483	42105.483	42105.484	-0.00001	0.00065	-0.00065			
MMS1 was 0.047 m/s and 33% axial, MMS2 was 0.083 m/s and 23% axial, MMS3 was 0.41 m/s and 8.5% axial. These small DV values produce larger percentage error values.   
The Table below provides the following information:
•	First row for each maneuver: planned maneuver total delta-V values based on the associated DVTABLEs  
•	Second row for each maneuver: associated final maneuver planning requirements 
•	Third row for each maneuver: predicted velocity error at the time of the maneuver computed by differencing the predicted velocity at the maneuver time (starting with the post-perigee GEONS state prior to the maneuver) vs the definitive GEONS state at the time of the maneuver.
As shown in the table below, all maneuvering spacecraft meet the requirement.
Maneuver ID	Timespan	DVX (m/s)/ 
Req. (m/s)/
DiffVX(m/s)	DVY (m/s)/
Req. (m/s)/
DiffVY(m/s)	DVZ (m/s)/
Req. (m/s)/
DiffVZ(m/s)	
MMS3_FM575	2016_280/00:11:11 to 2016_280/00:11:11	-0.0244	0.0363	0.0182	
		0.01	0.01	0.01	
		-0.001	0.0014	0.0006	
MMS2_FM575	2016_280/01:41:11 to 2016_280/01:41:11	-0.0816	0.0168	-0.0278	
		0.01	0.01	0.01	
		-0.001	0.0015	0.0005	
MMS1_FM575	2016_280/03:06:11 to 2016_280/03:06:11	-0.0411	0.0044	-0.0261	
		0.01	0.01	0.016059	
		-0.0015	0.002	0.0004