diff --git a/Luminary099/INTEGRATION_INITIALIZATION.agc b/Luminary099/INTEGRATION_INITIALIZATION.agc
index b18a9bc..d466ced 100644
--- a/Luminary099/INTEGRATION_INITIALIZATION.agc
+++ b/Luminary099/INTEGRATION_INITIALIZATION.agc
@@ -40,11 +40,11 @@
 # IN ORDER TO MAKE THE CSM(LEM)PREC AND CSM(LEM)CONIC ENTRANCES SIMILAR TO FLIGHT 278, THE INTEGRATION PROGRAM
 # WILL ITSELF SET THE FINAL RADIUS (RFINAL) TO 0 SO THAT REACHING THE DESIRED TIME ONLY WILL TERMINATE
 # INTEGRATION.  THE DP REGISTER RFINAL MUST BE SET BY USERS OF INTEGRVS AND INTEGRV, AND MUST BE DONE AFTER THE
-# CALL TC INTSTALL.
+# CALL TO INTSTALL.
 #
 # WHEN THE LM IS ON THE LUNAR SURFACE (INDICATED BY LUNAR SURFACE FLAG SET) CALLS TO LEMCONIC, LEMPREC, AND
 # INTEGRV WITH VINFLAG = 0 WILL RESULT IN THE USE OF THE PLANETARY INERTIAL ORIENTATION SUBROUTINES TO PROVIDE
-# BOTH THE LM'S POSITION AND VELOCITY IN THE REFERENCE COORDINATE SYSTEM.
+# BOTH THE LMS POSITION AND VELOCITY IN THE REFERENCE COORDINATE SYSTEM.
 # THE PROGRAM WILL PROVIDE OUTPUT AS IF INTEGRATION WAS USED.  THAT IS, THE PUSHLIST WILL BE SET AS NOTED BELOW AND
 # THE PERMANENT STATE VECTOR UPDATED WHEN SPECIFIED BY AN INTEGRV CALL.
 #
@@ -80,15 +80,15 @@
 # SETS STATEFLG (THE NAVIGATION PROGRAMS P20, P22.)
 #
 # Page 1206
-# APPENDIX B OF THE USERS' GUIDE LISTS THE STATE VECTOR QUANTITIES.
+# APPENDIX B OF THE USERS GUIDE LISTS THE STATE VECTOR QUANTITIES.
 #
 # 2.1 RESTARTS
 #
 # PHASE CHANGES WILL BE MADE IN THE INTEGRATION PROGRAM ONLY FOR THE INTEGRV ENTRANCE (I.E., WHEN THE W-MATRIX IS
 # INTEGRATED OR PERMANENT STATE VECTOR IS UPDATED.)  THE GROUP NUMBER USED WILL BE THAT FOR THE P20-25 PROGRAMS
-# (I.E., GROUP2) WINCE THE INTEGRV ENTRANCE WILL ONLY BE USED BY THESE PROGRAMS.  IF A RESTART OCCURS DURING AN
+# (I.E., GROUP2) SINCE THE INTEGRV ENTRANCE WILL ONLY BE USED BY THESE PROGRAMS.  IF A RESTART OCCURS DURING AN
 # INTEGRATION OF THE STATE VECTOR ONLY, THE RECOVERY WILL BE TO THE LAST PHASE IN THE CALLING PROGRAM.  CALLING
-# PROGRAMS WHICH USE THE INTEGRV OR INTEGRVS ENTRANCE OF INTEGRATION WHOULD ENSURE THAT IF PHASE CHANGING IS DONE
+# PROGRAMS WHICH USE THE INTEGRV OR INTEGRVS ENTRANCE OF INTEGRATION SHOULD ENSURE THAT IF PHASE CHANGING IS DONE
 # THAT IT IS PRIOR TO SETTING THE INTEGRATION INPUTS IN THE PUSHLIST.
 # THIS IS BECAUSE THE PUSHLIST IS LOST DURING A RESTART.
 #
@@ -106,28 +106,28 @@
 #
 # PROGRAM INPUTS ARE THE FLAGS DESCRIBED IN APPENDIX A AND THE PERMANENT STATE VECTOR QUANTITIES DESCRIBED IN
 # APPENDIX B OF THE USERS GUIDE, PLUS THE DESIRED TIME TO INTEGRATE TO IN TDEC1 (A PUSH LIST LOCATION).
-# FOR INTEGRVS, THE RCV,VCV,TET OR THE TEMPORARY STATE VECTOR MUST BE SET, PLUS MOONFLAG AND MIDFLAG
+# FOR INTEGRVS, THE RCV,VCV,TET OF THE TEMPORARY STATE VECTOR MUST BE SET, PLUS MOONFLAG AND MIDFLAG
 #
 # FOR SIMULATION THE FOLLOWING QUANTITIES MUST BE PRESET ---
-#										EARTH	MOON
-#										 29	 27
+#															EARTH	MOON
+#										 						29	 27
 #	RRECTCSM(LEM) 		RECTIFIED POSITION VECTOR	METERS		2	2
 #
-#										 7	 5
+#										 						7	 5
 #	VRECTCSM(LEM)		RECTIFIED VELOCITY VECTOR	M/CSEC		2	2
 #
-#										 28	 28
-#	TETCSM(LEM)		TIME STATE VECTOR IS VALID	CSEC		2	2
-#				CUSTOMARILY 0, BUT NOTE LUNAR
-#				ORBIT DEPENDENCE ON REAL TIME.
+#										 						28	 28
+#	TETCSM(LEM)			TIME STATE VECTOR IS VALID	CSEC		2	2
+#						CUSTOMARILY 0, BUT NOTE LUNAR
+#						ORBIT DEPENDENCE ON REAL TIME.
 #
-#										 22	 18
-#	DELTAVCSM(LEM)		POSITION DEVIATION		METERS		2	2
-#				0 IF TCCSM(LEM) = 0
+#										 						22	 18
+#	DELTAVCSM(LEM)		POSITION DEVIATION			METERS		2	2
+#						0 IF TCCSM(LEM) = 0
 #
-#										 3	 -1
-#	NUVCSM(LEM)		VELOCITY DEVIATION		M/CSEC		2	2
-#				0 IF TCCSM(LEM) = 0
+#										 						3	 -1
+#	NUVCSM(LEM)		VELOCITY DEVIATION				M/CSEC		2	2
+#					0 IF TCCSM(LEM) = 0
 # Page 1207
 #										 29	 27
 #	RCVSM(LEM)		CONIC POSITION			METERS		2	2