FR540

Looking at the Restart states from Rev 541 we have the following results for FR540.
FM504		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 01 2016 22:55:07.503	42102.428	42112.712	42112.737	10.28384	10.30842	-0.02458	-0.24%	0.06%	
MMS2	Sep 01 2016 22:54:52.642	42102.429	42097.776	42097.715	-4.65331	-4.71458	0.06127	-1.32%	-0.06%	
MMS3	Sep 01 2016 22:54:28.412	42102.440	42099.501	42099.530	-2.93903	-2.90960	-0.02944	1.00%	0.14%	
MMS4	Sep 01 2016 22:54:35.397	42102.444	42102.444	42102.460	0.00000	0.01596	-0.01597			

MMS1 53% axial; MMS2 60% axial; MMS3 was 79% 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_FR540	2016_245/04:06:11 to 2016_245/04:11:21	-0.4233	-0.904	1.3748	
		0.01	0.01	0.013748	
		0.0002	-0.00125	-0.00025	
MMS1_FR540	2016_245/05:41:11 to 2016_245/05:44:41	-0.8285	0.2591	1.2624	
		0.01	0.01	0.012624	
		0.0005	-0.0015	-0.0004	
MMS2_FR540	2016_245/07:06:11 to 2016_245/07:12:11	1.231	-1.1986	1.6059	
		0.01231	0.011986	0.016059	
		0.00125	-0.00225	-0.0007