FR541

Looking at the Restart states from Rev 542 we have the following results for FR541.
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	Sep 02 2016 22:47:29.434	42112.469	42102.168	42102.144	-10.30074	-10.32464	0.02390	-0.23%	0.05%	
MMS2	Sep 02 2016 22:47:34.847	42097.450	42102.088	42102.083	4.63805	4.63340	0.00465	0.10%	0.03%	
MMS3	Sep 02 2016 22:47:34.811	42099.266	42102.176	42102.173	2.90928	2.90629	0.00299	0.10%	0.06%	
MMS4	Sep 02 2016 22:47:28.547	42102.196	42102.162	42102.154	-0.03392	-0.04143	0.00750			

Looking at Restart States from Rev 543 gave SMA % error of -0.38%, 0.50% and 0.61% respectively, though the plane change errors were slightly smaller than on Rev 542.  MMS1 was 28% axial; MMS2 was 53% axial; MMS4 was 68% axial.
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_FR541	2016_245/19:15:26 to 2016_245/19:19:36	-0.0018	-0.0615	-1.4604	
		0.002	0.002	0.014604	
		-0.00025	-0.0003	-0.0002	
MMS1_FR541	2016_245/20:42:16 to 2016_245/20:44:36	-0.1528	1.7557	0.0576	
		0.002	0.0017557	0.002	
		-0.00025	-0.00045	-0.00025	
MMS2_FR541	2016_246/01:02:06 to 2016_246/01:04:36	0.4404	0.8361	-0.4938	
		0.004404	0.008361	0.004938	
		-0.00005	-0.0005	-0.0001