diff --git a/Luminary099/CONIC_SUBROUTINES.agc b/Luminary099/CONIC_SUBROUTINES.agc
index f3a5960..b92783b 100644
--- a/Luminary099/CONIC_SUBROUTINES.agc
+++ b/Luminary099/CONIC_SUBROUTINES.agc
@@ -417,47 +417,51 @@
 
 # Page 1169
 # PROGRAM DESCRIPTION - TIME-RADIUS SUBROUTINE		DATE - 11 OCTOBER 1967
-# MOD NO. -1						LOG SECTION - CONIC SUBROUTINES
-# MOD BY KRAUSE						ASSEMBLY - COLOSSUS REVISION 88
+# MOD NO. -1							LOG SECTION - CONIC SUBROUTINES
+# MOD BY KRAUSE							ASSEMBLY - COLOSSUS REVISION 88
+#
 #
 # FUNCTIONAL DESCRIPTION -
 #
 #	THIS SUBROUTINE, GIVEN AN INITIAL STATE VECTOR AND A DESIRED RADIUS TO WHICH THE
-#	STATE IS TO BE UPDATED ALONG A CONIC TRAJECTORY, CALCULATES THE CORRESPONDING TIME-OF-FLIGHT AND, IN ADDITION,
-#	PROVIDES THE OPTION OF COMPUTING THE NEW UPDATED STATE VECTOR.  THE RESULTING TRAJECTORY MAY BE A SECTION OF A
-#	CIRCLE, ELLIPSE, PARABOLA, OR HYPERBOLA WITH RESPECT TO THE EARTH OR THE MOON.  THE USE OF THE SUBROUTINE CAN BE
-#	EXTENDED USING OTHER PRIMARY BODIES BY SIMMPE ADDITIONS TO THE MUTABLE WITHOUT INTRODUCING ANY CODING CHANGES,
-#	ACCEPTING THE INHERENT SCALE FACTOR CHANGES IN POSITION AND VELOCITY.
-#
+# STATE IS TO BE UPDATED ALONG A CONIC TRAJECTORY, CALCULATES THE CORRESPONDING TIME-OF-FLIGHT AND, IN ADDITION,
+# PROVIDES THE OPTION OF COMPUTING THE NEW UPDATED STATE VECTOR.  THE RESULTING TRAJECTORY MAY BE A SECTION OF A
+# CIRCLE, ELLIPSE, PARABOLA, OR HYPERBOLA WITH RESPECT TO THE EARTH OR THE MOON.  THE USE OF THE SUBROUTINE CAN BE
+# EXTENDED USING OTHER PRIMARY BODIES BY SIMPLE ADDITIONS TO THE MUTABLE WITHOUT INTRODUCING ANY CODING CHANGES,
+# ACCEPTING THE INHERENT SCALE FACTOR CHANGES IN POSITION AND VELOCITY.
 #	IF THE DESIRED RADIUS IS BEYOND THE RADIUS OF APOCENTER OF THE CONIC OR BELOW THE RADIUS OF PERICENTER,
-#	APSESW WILL BE SET AND THE SUBROUTINE WILL RETURN THE APOCENTER OR PERICENTER SOLUTION, RESPECTIVELY.
+# APSESW WILL BE SET AND THE SUBROUTINE WILL RETURN THE APOCENTER OR PERICENTER SOLUTION, RESPECTIVELY.
+#
 #
 # THE RESTRICTIONS ARE -
 #	1. THE ANGLE BETWEEN ANY POSITION VECTOR AND ITS VELOCITY VECTOR MUST BE GREATER THAN 1 DEGREE 47.5 MINUTES
-#	   AND LESS THAN 178 DEGREES 12.5 MINUTES.
+# AND LESS THAN 178 DEGREES 12.5 MINUTES.
 #	2. THE PARAMETERS IN THE PROBLEM MUST NOT EXCEED THEIR SCALING LIMITS SPECIFIED IN THE GSOP.  IF THE LIMITS
-#	   ARE EXCEEDED, THE RESULTING SOLUTION WILL BE MEANINGLESS.
+# ARE EXCEEDED, THE RESULTING SOLUTION WILL BE MEANINGLESS.
 #	3. AN ACCURACY DEGRADATION OCCURS AS THE SENSITIVITIES OF TIME AND UPDATED STATE VECTOR TO CHANGES IN
-#	   RDESIRED INCREASE.  THIS WILL OCCUR NEAR EITHER APSIS OF THE CONIC AND WHEN THE CONIC IS NEARLY CIRCULAR.  IN
-#	   PARTICULAR, IF THE CONIC IS AN EXACT CIRCLE, THE PROBLEM IS UNDEFINED AND THE SUBROUTINE WILL ABORT.
+# RDESIRED INCREASE.  THIS WILL OCCUR NEAR EITHER APSIS OF THE CONIC AND WHEN THE CONIC IS NEARLY CIRCULAR.  IN
+# PARTICULAR, IF THE CONIC IS AN EXACT CIRCLE, THE PROBLEM IS UNDEFINED AND THE SUBROUTINE WILL ABORT.
+#
+#	THE AGC COMPUTATION TIME IS APPROXIMATELY .363 SECONDS
 #
-#	THE AGC COMPUTATION TIME IS APPROXIMATELY .363 SECONDS.
 #
 # REFERENCES -
 #	R-479, MISSION PROGRAMMING DEFINITION MEMO NO. 10, LUNAR LANDING MISSION GSOP-SECTION 5.5, SGA MEMO 67-8.
 #
-# INPUT - ERASABLE INITIALIZATION REQUIRED.
-#			* SCALE FACTOR	*
-#	VARIABLE	*IN POWERS OF 2	*	DESCRIPTION AND REMARKS
-#	--------	*--------------	*	-----------------------
-#	RVEC		* +29 FOR EARTH	*	DP INITIAL POSITION VECTOR IN METERS
-#			* +27 FOR MOON	*
-#	VVEC		* +7 FOR EARTH	*	DP INITIAL VELOCITY VECTOR IN METERS/CENTISECOND
-#			* +5 FOR MOON	*
-#	RDESIRED	* +29 FOR EARTH	*	DP TERMINAL RADIAL DISTANCE ON CONIC TRAJECTORY FOR WHICH TRANSFER TIME IS TO BE
-#			* +27 FOR MOON	*		COMPUTED
-#	SGNRDOT		* NONE		*	SP TAG SET TO +.5 OR -.5 ACCORDING TO WHETHER THE RADIAL VELOCITY AT RDESIRED IS TO BE
-#			*		*		POSITIVE OR NEGATIVE, RESPECTIVELY.   THIS TAG REDUCES THE DOUBLE-VALUED PROBLEM TO A
+#
+# INPUT - ERASABLE INITIALIZATION REQUIRED
+#
+#			* SCALE FACTOR *
+#	VARIABLE	*IN POWERS OF 2*	DESCRIPTION AND REMARKS
+#	--------	*--------------*	-----------------------
+#	RVEC		* +29 FOR EARTH*	DP INITIAL POSITION VECTOR IN METERS
+#			* +27 FOR MOON *
+#	VVEC		* +7 FOR EARTH *	DP INITIAL VELOCITY VECTOR IN METERS/CENTISECOND
+#			* +5 FOR MOON  *
+#	RDESIRED	* +29 FOR EARTH*	DP TERMINAL RADIAL DISTANCE ON CONIC TRAJECTORY FOR WHICH TRANSFER TIME IS TO BE
+#			* +27 FOR MOON *	COMPUTED.
+#	SGNRDOT		* NONE	       *	SP TAG SET TO +.5 OR -.5 ACCORDING TO WHETHER THE RADIAL VELOCITY AT RDESIRED IS TO BE
+#			*	       *	POSITIVE OR NEGATIVE, RESPECTIVELY.   THIS TAG REDUCES THE DOUBLE-VALUED PROBLEM TO A
 # Page 1170
 #			*		*		SINGLE-VALUED PROBLEM.
 #	X1 (38D)	* NONE		*	INDEX REGISTER TO BE SET TO -2D OR -10D ACCORDING TO WHETHER THE EARTH OR MOON,