STS-51G National Space Transportation Systems Mission Report

8/7/2019 STS-51G National Space Transportation Systems Mission Report

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STSS1-GNational SpaceTransportation SystemsProgram Mission Report

JSC-2067-2

July 1985


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I N T R O D U C T I O N A N D M I S S I O N O B J E C T V E ST h e S T S 5 1 - G N a t i o n a l S T S ( S p a c e T r a n s p o r t a t i o n S y s t e m s ) P r o g r a m M i s s i o n R e p o r tc o n t a i n s a s u m m a r y o f t h e m a j o r a c t i v i t i e s a n d a c c o m p l i s h m e n t s o f t h e e i g h t e e n t hS p a c e S h u t t l e f l i g h t a n d t h e f i f t h f l i g h t o f t h e O V - 1 0 3 v e h i c l e , D i s c o v e r y .T h e p r i m a r y o b j e c t i v e s o f t h e S T S 5 1 - G f l i g h t w e r e t o s u c c e s s f u l l y d e p l o y t h eT E L S T A R - 3 D / P A M - D ( P a y l o a d A s s i s t M o d u l e - D ) , M O R E L O S - A / P A M - D , a n d A R A B S A T - A / P A M - Ds a t e l l i t e s ; t o c o n d u c t t h e d e p l o y m e n t a n d r e t r i e v a l o p e r a t i o n s o f t h e S P A R T A N 1 ;a n d t o p e r f o r m t h e o p e r a t i o n s o f t h e A D S F ( A u t o m a t e d D i r e c t i o n a l S o l i d i f i c a t i o nF u r n a c e ) , F P E ( F r e n c h P o s t u r e E x p e r i m e n t ) , a n d F E E ( F r e n c h E c h o c a r d i g r a p h E x p e r -i m e n t ) . T h e s e q u e n c e o f e v e n t s f o r t h i s f l i g h t i s s h o w n i n t a b l e I . T h e p r o l -l e m t r a c k i n g l i s t f o r t h e O r b i t e r i s p r e s e n t e d i n t a b l e I I t o p r o v i d e a c o m p l e t el i s t o f a l l f l i g h t - a s s o c i a t e d p r o b l e m s t h a t o c c u r r e d .

M I S S I O N S U M M A R YT h e S T S 5 1 - G f i n a l c o u n t d o w n p r o c e e d e d v e r y s m o o t h l y w i t h n o u n p l a n n e d h o l d s .L i f t - o f f o c c u r r e d a t 1 6 8 : 1 1 : 3 3 : 0 0 G . m . t . ( 0 7 : 3 3 a . m . , e . d . t . , J u n e 1 7 , 1 9 8 5 )f r o m l a u n c h c o m p l e x 3 9 A a t K S C ( K e n n e d y S p a c e C e n t e r ) w i t h a s a t i s f a c t o r yl a n d i n g a t 1 7 5 : 1 3 : 1 1 : 5 7 G . m . t . ( J u n e 2 4 , 1 9 8 5 ) a t E d w a r d s A i r F o r c e B a s e ,C a l i f o r n i a .T h e c r e w f o r S T S 5 1 - G w a s D a n i e l C . B r a n d e n s t e i n , C a p t . , U . S . N a v y , C o m m a n d e r ;J o h n O . C r e i g h t o n , C d r . , U . S . N a v y , P i l o t ; S t e v e n R . N a g e l , L t . C o l . , U . S . A i rF o r c e , J o h n M . F a b i a n , C o l . , U . S . A i r F o r c e , a n d S h a n n o n W . L u c i d , P h . D . , M i s s -i o n S p e c i a l i s t s ; a n d P a t r i c k B a u d r y a n d S u l t a n S a l m a n A l - S a u d , P a y l o a d S p e c i a l ~i s t s . P a t r i c k B a u d r y w a s a r e p r e s e n t a t i v e o f C N E S a n d S u l t a n S a l m a n A l - S a u dw a s a r e p r e s e n t a t i v e o f A R A B S A T .T h e a s c e n t p h a s e w a s n o m i n a l i n a l l r e s p e c t s . T h e S R B ' s ( S o l i d R o c k e t B o o s t e r s )p e r f o r m e d n o r m a l l y w i t h m o t o r p e r f o r m a n c e c l o s e t o p r e d i c t e d v a l u e s a n d w e l lw i t h i n a l l o w a b l e e n v e l o p e s . S R B s e p a r a t i o n o c c u r r e d a t t h e n o m i n a l t i m e a n db o t h S R B ' s w e r e f l o a t i n g n o r m a l l y a t r e c o v e r y .


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using the left OMS engine. The RMS (Remote Manipulator System) was deployed andthe wrist camera was used to observe the PKM (Perigee Kick Motor) firing of thesatellite.Flight day 2 was mainly characterized by the activities surrounding the deploy-ment of the ARABSAT-A satellite. Initially, data indicated that the solar ar-rays were deployed on the satellite while it still was covered by the sunshield.After opening the sunshield, a survey was made with the RMS end effector TVcamera of the satellite and all systems appeared to be ready for deployment.The satellite was deployed on time at 169:13:56:56 G.m.t. on June 18, 1985. ThePKM burn was again observed by video camera and all activities associated withthe satellite appeared normal. Other activities of the second day included per-forming the two French experiments and Earth observations.Much of flight day 3 was devoted to preparation for the deployment of theTELSTAR-3D satellite. The satellite was deployed within 1 second of the plannedtime at 170:11:20:36 G.m.t. The usual separation maneuver after satellite de-ployment was performed, and the RMS was positioned so that the TELSTAR PKM burncould be observed on TV.The HPTE (High Precision Tracking experiment) was unsuccessfully attempted dur-ing the third day. Two errors in the Crew Activity Plan data caused the Orbiterto be oriented to the incorrect attitude for successful acquisition. Addition-ally, the two French experiments and the ADSF experiment were all operatedsuccessfully. Also, the advanced autopilot performance DTO (detailed test ob-jecti ve) (0 909) wa s performe d successfull y.On flight day 4, the SPARTAN 101 spacecraft was deployed and released at171:16:02:39 G.m.t., followed by two RCS separation maneuvers. The French Echo-cardiograph exper iment was also successfull y p erformed.On flight day 5, all activities with the ADSF experiment were completed and theexperiment was deactivated. Also, the French echocardiograph experiment was


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E a r l y o n t h e e i g h t h f l i g h t d a y , a l l c a b i n s t o w a g e w a s c o m p l e t e d a n d t h e p a y l o a db a y d o o r s w e r e c l o s e d i n p r e p a r a t i o n f o r e n t r y . T h e , 5 1 - s e c o n d d e o r b i t m a n e u v e rw a s i n i t i a t e d a t 1 7 5 : 1 2 : 0 7 : 3 0 G . m . t . T h e e n t r y w a s n , r m a l i n a l l r e s p e c t s w i t ha l l P T I ( P r o g r a m m e d T e s t I n p u t ) m a n e u v e r s w e r e p e r f o r m e d a s p l a n n e d . A f t e r c o m -p l e t i n g t h e 2 4 0 - d e g r e e h e a d i n g a l i g n m e n t c i r c l e t u r n , t h e f i n a l a p p r o a c h i n t oE d w a r d s A i r F o r c e B a s e r u n w a y 2 3 w a s c o m p l e t e d w i t h m a i n g e a r c o n t a c t a t1 7 5 : 1 3 : 1 1 : 5 2 . 4 G . m . t . A f t e r a r o l l o u t o f 7 7 4 3 f e e t , t h e O r b i t e r w a s s t o p p e d a t1 7 5 : 1 3 : 1 2 : 3 3 . 7 G . m . t . , a n d t h e S T S 5 1 - G m i s s i o n w a s b r o u g h t t o s u c c e s s f u l c o n -c l u s i o n .A l l s e v e n p l a n n e d D T O ' s a n d f o u r D S O ' s ( D e t a i l e d S u p p l e m e n t a r y O b j e c t i v e s ) w e r ec o m p l e t e d b a s e d o n d a t a a v a i l a b l e a t t h i s w r i t i n g . I n a d d i t i o n , a l l t h e G A S( G e t a w a y S p e c i a l ) e x p e r i m e n t s w e r e c o m p l e t e d .


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ABLE I. - STS 51-G SEQUENCE OF EVENTSEvent Actual time, G.m.t.

APU activation (1)(2)(3)

SRB HPU activation command (LH-A2)MPS start command sequence (engine 3)SRB ignition command from GPC (lift-off)MPS throttle-down to 83 percent (engine 3)MPS throttle-down to 65 percent (engine 3)Maximum dynamic pressure .MPS throttle-up to 10 4 percent (engine 3)SRB separation command from GPCMPS throttle-down for 3g accer"eration (engine 3)3g accelerationMain engine cutoff (MECO)Ex ter na l ta nk se pa rat io nOMS 1 ignition (not required)OMS 2 ignitionOMS 2 cutoffM OR EL OS d ep lo yA RA BS AT d ep lo YT EL ST AR d ep lo yS PA RT AN d ep lo ySPARTAN grappleFlight control system checkout - APU 3 start

APU 3 shutdown

168: 11:28: 11168:11:28:13168:11:28:14168:11:32:29.4168:11:32:53.4168:11:33:00168:11:33:19.1168:11:33:30.3168: 11:33:50.5168:11:34:08.2168:11:35:05168: 11 :40:35.2168:11:40:36168:11:41:36168:11:41:54

APU 1 activationDe or bit m an eu ver i gn it io nDe or bit ma ne uve r cu to ffAPU activation (2)

168:12:13:29168:12:16:27168:19:37:51169:13:56:56170: 11 :20: 36171:16:02:39173:13:31:54173:17:17:44173:17:26:27175:12:02:32175:12:07:30175:12:10:01175:12:28:32


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VEHICLE ASSESSMENTSOLID ROCKET BOOSTERS

All SRB systems performed as expected. The SRB prelaunch countdown was nominal.Performance of both SRM's (Solid Rocket Motors) was close to predicted values,and well within the allowed envelopes. Propellant burn rates were near predict-ed v3Jues. Preliminary data indicate that the SRB separations occurred at thepredicted time. The SRB recovery system performed nominally, and both SRB'swere reported to be floating normally when visually located by the recovery shippersonnel. Recovery ship personnel reported that all parachutes had deployedproperly.

EX TERN AL T ANKAll ET systems and instrumentation performed as expected. No LCC (Launch CommitCriteria) violations were experienced and no significant ice buildup was ob-served. Hydrogen ullage pressure transducers nos. 2 and 3 experiencedintermittent open-circuit indications on the low end of the scale. The sensorsperformed as expected during prepressurization and flight. Photographs of ETseparation showed larger than expected divots in the intertank insulation.

SPACE SHUTTLE MAIN ENGINEAll SSME parameters appeared to be normal during the prelaunch countdown andcompared well with prelaunch parameters that were observed on previous flights.Preliminary data indicate that SSME performance at start, mainstage, shutdownand propellant dump was very good. All temperatures appeared to be very closeto predictions, and there were no problems detected.

MAIN PROPULSION SYSTEMOverall performance of the MPS was excellent. Liquid oxygen and Liquid hydrogenloading was accomplished as planned and the loads were very close to the plan-


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The manifold 2 thrusters were reprioritized to the last priority for the remain-der mission. No problems were encountered with this configuration during theentry and landing phases.

Thermal Protection System DamageThe postflight TPS (Thermal Protection System) inspection showed approximately315 debris hits of which 144 were equal to or greater than 1 inch in area. Themajority of hits (231) were on the Orbiter underbody and were concentratedin the right-hand wing glove area. This is a significantly higher number ofdebris hits than has occurred during any of the last 10 Orbiter flights, andrepresents the highest number of an upward trend that has occurred during thelast three Orbiter flights. The glazed condition of the debris craters in-dicates the damage occurred during ascent.Review of ET separation photographs shows a number of large divots in the inter-tank installation areas where one type of foam insulation is bonded to another.Review of the ET insulation application progress has identified a faulty batchof bonding resin used on the external tanks flown on the last 3 flights. Theresin caused a chemical reaction at the dissimilar insulation bondline thatresulted in trapped gas bubbles. The bubbles expanded during ascent, forcingejection of pieces of the insulation from the ET. The faulty bonding has beenisolated toLWTs (lightweight tanks) 10 through 13. Three of these tanks haveflown on the last 3 flights and LWT 12 is scheduled to fly on STS 51-F.Additional core-sample pull tests have been conducted in the affected areas ofthe ET scheduled to be flown on STS 51-F. Core sample density and subsequentrepair has established a reasonable level of confidence that any insulationshed during ascent would be limited to small areas and would result in limiteddebris hits on the Orbiter.

P AY LO ADS A ND E XP ER IM ENT SMORELOS-A/PAM-D


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solar arrays and double aperture antenna were deployed and systems tests werein progress. All satellite systems were operating nominally.

ARABSAT/PAM-DOn day 1 of the mission, upon review of the ARABSAT health check data (acquiredshortly after payload bay doors opening), an indication of a partially deployedspacecraft solar panel was noted. Initial evaluations theorized that theindication was caused by a microswitch failure, and that the solar panels werein their correct stowed position within the closed sunshield. However, to veri-fy the proper configuration, the RMS wrist TV crunera was used to gain confidencethat the solar panel clamps were latched. The sunshield was opened on orbit 18,and the inspection revealed that the arrays were in the correct configuration.The deployment occurred as planned at 169:13:56:56 G.m.t. on June 18, 1985, (day2). The PAM PKM burn occurred 45 minutes later. The burn was slightly under-speed (406-nmi. low apogee altitude), but was within 3 sigma tolerance. Threeapogee burns were performed to place the ARABSAT into a geosynchronous driftorbit. As of this writing, the solar panels have been deployed as planned, thespacecraft is in nominal configuration, and testing is underway.

TELSTAR-3D/PAM-DThe TELSTAR-3D/PAM-D satellite was successfully deployed at the first plannedopportunity at 170:11:20:36 G.m.t. on mission day 3, within one second of thep la nn ed t im e.The Orbiter altitude was within 1 nmi. of the planned 191-by-211 nmi. orbit.Attitude errors were less than 0.1 degree in all axes and rates were less than0.01 deg/sec. The PAM-D PKM burn occurred as planned 45 minutes after deploy-ment and was monitored with the RMS wrist TV camera. The PAM burn was slightlyunderspeed (230 nmi.-low apogee altitude), but within 3 sigma tolerance. Theapogee burn occurred on the third apogee at 15:05 G.m.t. on June 20.


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o b s e r v e d t h a t t h e r o l l a l t i t u d e o f t h e S P A R T A N w a s a p p r o x i m a t e l y 9 0 d e g r e e s d i f -f e r e n t f r o m t h a t p l a n n e d , p l a c i n g t h e g r a p p l e f i x t u r e f a c i n g t o w a r d t h e p a y l o a db a y r a t h e r t h a n o u t t h e p o r t s i d e a s p l a n n e d . C a p t u r e w a s p e r f o r m e d w i t h o u t i n -c i d e n t , a n d t h e s p a c e c r a f t w a s b e r t h e d a n d l a t c h e d s a t i s f a c t o r i l y .T h e r e s u l t s o f t h e S P A R T A N 1 0 1 e x p e r i m e n t s a r e b e i n g a n a l y z e d w i t h t h e i n i t i a la s s e s s m e n t t o b e a v a i l a b l e w i t h i n 3 0 d a y s a f t e r l a n d i n g .

H I G H P R E C I S I O N T R A C K I N G E X P E R I M E N TT h e H P T E i s t h e f i r s t o f a s e r i e s o f t e c h n o l o g y - d e v e l o p m e n t e x p e r i m e n t s f r o m t h eS t r a t e g i c D e f e n s e I n i t i a t i v e O r g a n i z a t i o n ( S O l O ) . T h e H P T E i s a n 8 - i n c h d i a m e -t e r r e t r o r e f l e c t o r w h i c h w a s s t o w e d i n a m i d d e c k l o c k e r a n d i n s t a l l e d i n t h eO r b i t e r s i d e h a t c h w i n d o w o n - o r b i t . D u r i n g t h e o r b i t 6 4 p a s s o v e r t h e i s l a n d o fM a u ; , H a w a i i , t h e O r b i t e r w a s m a n e u v e r e d t o p o s i t i o n t h e s i d e h a t c h w i n d o w i nt h e l i n e - o f - s i g h t o f t h e L B O ( L a s e r B e a m D i r e c t o r ) . A 4 - w a t t g r e e n l a s e r b e a mf r o m t h e g r o u n d L B O w a s r e f l e c t e d b a c k f r o m t h e H P T E r e t r o r e f l e c t o r . T h i s r e -f l e c t i o n s u c c e s s f u l l y d e m o n s t r a t e d t h e a b i l i t y o f t h e g r o u n d L B O t o a c c u r a t e l yt r a c k a n o b j e c t i n l o w - E a r t h o r b i t .

A U T O M A T E D D I R E C T I O N A L S O L I D I F I C A T I O N F U R N A C ET h e A D S F w a s a n e x p e r i m e n t t o p e r f o r m d i r e c t i o n a l s o l i d i f i c a t i o n o f m a g n e t i cm a t e r i a l s , i m m i s c i b l e s , a n d i n f r a r e d d e t e c t o r s , a n d t o p e r f o r m o f f - e u t e c t i cg r o w t h a n d s o l i d i f i c a t i o n .T h e A D S F w a s o p e r a t e d a t o t a l o f 2 4 h o u r s d u r i n g t h e t h r e e s c h e d u l e d p e r i o d s o ft h e m i s s i o n a n d n o p r o b l e m s w e r e o b s e r v e d .A c o m p l e t e e v a l u a t i o n o f t h e 4 m a t e r i a l s a m p l e s w i l l b e p e r f o r m e d a f t e r t h e A D S Fi s d e l i v e r e d t o t h e N A S A - M S F C a n d t h e c a n i s t e r m o d u l e i s d i s a s s e m b l e d .


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No technical problems were encountered throughout the mission. The quality ofthe signals recorded on the tape was excellent. There WIS a comment that thevelcro foot restraint failed to hold during rapid elevatton of the arms.

D ET AI LE D T ES T O BJ EC TI VE SO RB IT AL E XP ER IM EN T D IG IT AL A UT OP IL OT P ER FO RM AN CE

(DTO 090 9)A total of twelve data gath~ring periods on flight day 3 and 6 were devoted totest runs for the OEX (Orbital Experiment) DAP (Digital Autopilot) Performancen r o (0909). Eleven different tests were completed. Excellent data were obtain-ed and the overall results of the tests were very successful.

WASTE AND SUPPLY WATER DUMPS(DTO 032 5)Se+.,u water dum p s (three waste, four supply) were performedwaste and supply water d umps DTO (0325). Five of the d umpsa warm nozzle attitude and two with a cold nozzle attitude.successful with only insignificant ice formations on two ofof 711 lb of water was expelled during these dtmlps.

in support of thewere performed fromAll dumps werethe dtnnps. A total


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TABL t . 11.- 5T .) Sl-G lJRB lTLk Pku13LEM TkACK Ii~G U ;)T--_ . . . . -----------------.------------------------.------- --------------------------------------- ..~. . . . . . --------------------------------

TITLEJSC OV-I03 STS 51-(; PROBLEM TRACKING LIST

I T IH E, G .H .T . IJULY 16, 1985

, NO. I- - - - - - - - - - - - - - - - - - - - - - ~ - - - - - - - - - - - - - ~ - - - - - - - - - - - - ~ - ~ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -R ES P. ~l GR.COHtiENTS- - - - - - - - - - - - - - - - - - - - - ~ . - - - - - - - - - - - - - - - - . - - - - - - ..- - - - - - - - - - - - - - - - - - - - - - - - - - ~ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -I

IIA I

IIB IIII

C IIjI

2 IIt-' I0 II3 III4 II

A ,IIII

B I,,I

INSTIW:lE1'-:TAnO NSS:lE 2 GIl2 OUTLET PKESSURE 16H: 11 :36: 38( V4 1P I2 hO A) F AI LE D.LEFT MAIN LANDING GEAR IIYDRAULIC ROLL OUTBR AKE P RE SS URE (V 5I P05 22A ) C HA NNE L4 READ LOIJ.LEFT O~lS FEED LINE TEMPERATURE POST FLIGHT( V4 )T 42 16 A) I NC RE AS ED D UR IN GP OS TF LI GH T S AF IN G.

APU 2 FUEL PUMP WATER COOLING VALVE 168:11:59:28SYSTEM A FAILED.

IKS FAN SEPARATOR I 110TOR CURRENT 168: 1 7:51IIIGU.RCS MICROSWITCHES:RIGHT RCS FUEL CROSSFEED VALVE 3/4/5 169:09:)0OP EN I ND ICA TI ON TR ANS IE NT F AI LU RE.

LEFT RCS OXIDIZER Of{ FUEL TANKISOLATION VALVE 1/ 2 CLOSEDI ND IC AT IO N F AI LE D.

16'):09:)0

READ OFF SCALE IIIGH ) ~lIN. AN D '38 SEC. AFTEKLAU~CH. R&R AT KSC.READ 1000 PSI WHEN OTIIER CI~NNELS READ 1500 PSI.T/S AT KSC.

READING WENT FROM A.'1BIENTTO 1)0 DEG F IN ABOUTAt\ HOUR. THEN RETUIU';EDTO ANBIENT WITH r-;oCORRESPONDING PRESSURE CHANGE. T/S AT KSC.

CREW SWITCHED ON SYSTEM B AND VALVE HODULECOOLED DOWN GRADUALLY. GGVtl T 1 SYS 2(V46T0271). FOUND VALVES A AND B CROSSWIREDREQUIRING BOTH SYSTEHS ON FOR COOLING.CREW SWITCHED TO SEP 2 AT 168:17:58 AND FANOPERATED NORMALLY. R&R AT KSC.P RO BA BL E C ON TA Nl NA TI ON I N M IC RO SW IT CH ES .

P. COTACA R 2 5F OO IJ. WILTZCA R 2 5F OIl

J . H OO PERL . J OI IN SO };

W . SCOTTCLOSUREI N P RO CE SS

E. W IN KL ERDR 25 F0 03G. GRUSHCA R I) FO OI

VALVE OPENED, BUT GROUND TELEMETRY DID NOT CLOSUREINDICATE OPEN. BOTH OPEN INDICATIONS RECEIVED IN PROCESSAFTER SECOND INTERCONNECT. CREW SWITCHED TO GPCCONTROL. R&R ACTUATOR AT KSC.VALVE OPENED, BUT ONBOARD TALKBACK DID NOT SHOHCLOSED DURING SW ITCIIOVER TO INTERCONNECT. VALVEPLACED IN GPC. R&R ACTUATOR AT KSC.

"


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TA8Lt:. 11 . - ST.3 51-G lJkcllTLk Pku13LtiVl TkACKII~G LIST (CuIHIi\JUEtJ)- - - - - ~ - - - - - - - - - - - - ~ - - ~ - - - - - - - - - - - - - ~ ~ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - , - - - . - - - - - - - -I 1-.u . I TITLI.:

JSC llV -IO ) STS 51-G PROBLEH TRACKINC LISTI T H1E, G. ~i.T. I

JULY 16, 1 '185- - - - - - - - - - - - - - ~ - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

C I RIGI IT Res OX ID IZER TI\N r lSOLA TlO1-.I VALV [ 3 /4/5 B LEG OPEN INDICATIONI FAILED .I

5 S-i)A i\J) L ()\IER LEFT M \TENko. BENISldTCH INTERM ITTENT SLOIJ OR STUCK .

6 tim ! FA3 FA ILU RE .

7 FORWARD PORT AND STARi)OARD ANDFO R\~ AR D B ULK HE AD PA n OA D BAYF LO OD LIG HT S F AIL ED .

8 UTI L ITY POWER AC-3 PHASE fl SPIKESUSING UTIL ITY OUTLET O;'i PANEL A15 .

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TAGLt. 11. - STS 51-G U F < B I T L k PkuBLLtVl TRACKING LbT (Cul~CLUDE.i)- - - - - - - - - - ~ - - - - - - ~ ~ ~ - + - - - - - - - - - . . ~ - - - ~ - - - - . - - - - - - - - - - - - - - - - - - - . - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - ~ - - - - - - - - - - - - - - - - - - - - - - - - - - - -JSC OV-I03 STS 51..,.C PROBLEM TRACKING LIST JULY 16, 1985, NO . ,~ - - - - - - - - - - - - - - - - - - ~ ~ . - - - - - - - - - - - - - ~ . - - ~ - - - ~ - - - - - . - - - - - - - - - - - - - - - - - - - - - - - - . - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -R ES P. nc.TrTLI:. , T It'IE , G .~I.T. ,- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - ~ - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

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Documents

STS-51G National Space Transportation Systems Mission Report