FM505

Looking at the Restart states from Rev 506 we have the following results for FM505.
FM505		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	Jul 29 2016 02:59:04.771	42104.541	42105.499	42105.507	0.95829	0.96600	-0.00771	-0.80%	1.74%	
MMS2	Jul 29 2016 02:59:01.115	42107.974	42105.538	42105.501	-2.43616	-2.47363	0.03746	-1.54%	1.28%	
MMS3	Jul 29 2016 02:58:38.535	42105.514	42105.524	42105.510	0.01055	-0.00340	0.01395			
MMS4	Jul 29 2016 02:58:41.783	42104.630	42105.508	42105.508	0.87782	0.87832	-0.00050	-0.06%	5.46%	

MMS1 was primarily radial and about 0.37 m/s; MMS2 was about evenly radial and axial and about 0.72 m/s; MMS4 was practically all radial about 0.18 m/s (with hardly any out of plane component)
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)	
MMS4_FM505	2016_210/02:49:26 to 2016_210/02:49:36	0.0842	-0.1471	-0.0505	
		0.002	0.002	0.002	
		-0.00049	-0.0011	-0.00043	
MMS2_FM505	2016_210/04:8:16 to 2016_210/04:9:36	-0.2886	0.6086	-0.2594	
		0.002886	0.006086	0.002594	
		-0.0003	-0.00011	-0.00025	
MMS1_FM505	2016_210/05:28:56 to 2016_210/05:29:36	0.1748	-0.2927	0.158	
		0.002	0.002927	0.002	
		-0.00025	-0.00149	-0.0003