C *17 I 
November the 3d, at i6 l >. 47 1 JEq. T, at London.) 
here, fince the mean Anomaly is many times greater 
than f of a Second, the Rule in the fecond Cafe of 
the firlt Corollary may be ufed j that is, by taking the 
Sine of A = N— ~ 
N 
j 
But the Number N or V— m is =0,0 <7941 34 5 
Til R *' 
P 
and will be = 0,0030827 ; wherefore 
p 
~=) 0705763307, will be the Sine whofe Arch 
3 °> 3°397 is the Angle and the multiple Angle 
n*A=z io Q . 26'. 53'', 07, will be the Angle to be firft 
aflumed for the Anomalia Eccentri s the Error of 
which will be found to be lefs than a Second. 
The true Anomaly , computed from this Angle ac^ 
cording to the Rule in the Example for Mercury , will 
appear to be 171 0 . 38'. 24". from the Perihelion. 
By thefe Examples it appears, that the. Solution is 
uniyerfal in all refpeds j for the two firft, compared 
with the two laft, ferve to fhew that it is not confined 
to any particular Parts of the Orbit, but extends to all 
Degrees of mean Anomaly : And by comparing the 
fecond with the laft, it fufficiently appears to be 
univerfal with refped to the feveral Degrees of Eccen- 
tricity 5 fince in one the Equation of the Centre for 
the Redudion of the Mean to the true Motion is not 
fo much as the 775 th Part of the whole s whereas in 
the other it amounts to almoft 3000 times as much as 
the mean Motion itfelf. 
?OST r 
d 
