STS-51B National Space Transportation Systems Mission Report

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

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STS 51-8National SpaceTransportation SystemsProgram Mission Report

JSC-20S78


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IN TR OD UC TI ON AN D M IS SI ON OB JE CT IV ESThe STS 51-B Nat iona l STS (Space Transpor ta t ion Systems) Program Miss ion Repor tconta ins a summary of the major act iv i t ies and accompli shments of the seven-teenth Space Shutt le f l igh t and the seventh fl igh t of the OV-099 vehic le , .Chal lenger . The problem tracking li s t is presen ted to provide a comple te l is to f a l l Orb iter problems tha t occurred .

The primary objec t ives of the STS 51-B f l igh t were to carry out the ass igned

Space lab 3 sc ient if ic ac t ivi t i es and to deploy the Northern Utah State Sa te l l i t e(NUSAT) and the Global Low Orbi t Message Relay (GLOMR) Sate l l i t e . The sequenceof events for thi s f l igh t a re shown in tab le I . The problem tracking li s t forthe Orbiter is presen ted in tables II .

M IS SI ON S UM MA RY

The STS 51-B mission , the seventh for the OV-099 vehicle , Challenger , waslaunched on Apr i l 29, 1985. The f inal countdown proceeded smoothly unt i l T-4

minutes when a fai lu re of a f ront end processor in the LPS (launch process-ing sys tem) caused a 2-minute 18-second hold . This fa i lure resul ted in thel iqu id oxygen faci l i ty rep lenish va lve and liqu id oxygen vent valve notautomat ical ly clos ing as scheduled. The valves were manual ly posi t ioned dur ingthe hold , in i t ia t ing l iqu id oxygen drainback. The countdown, once re in i t ia ted,resul ted in a l i f t -off at 119:16:02:18 G.m. t . (11:02:18 a .m., e .d . t . ) fromLaunch Complex 39A at KSC (Kennedy Space Center ) on Apri l 29 , 1985. The missionwas successful ly concluded with a landing at Edwards Air Force Base , Cali forn ia ,at 126:16:12:03 G.m. t . , on May 6, 1985.

The crew for th is seventeenth f l igh t of the Space Shut t le and second f l igh t ofSpace lab were Rober t F . Overmyer , Col . , U. S . Mar ine Corp. , Commander ; Freder ickD. Gregory , Col . , U. S. Air Force, Pi lo t ; Don L. Lind , Ph.D. , Norman E. Thagard ,M D and Will iam E Thornton M D Miss ion Spec ia l i s t s ; Lodewijk van den Berg


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The fi r s t day 's ac t iv i t i es cons is ted of opening the payload bay doors , deployingthe NUSAT sate l l i t e , and a t tempt ing to deploy the GLOMR sate l l i te . A n anomalyoccur red to the canis te r door for the GLOMR sate l l i t e , p reventing th is sa te l l i t ef rom being deployed . Other ac t iv i t i es of the f ir s t day inc luded ac t ivat ing theSpacelab and in i t ia l izing per formance of many of the Space lab exper iments .These exper iments were divided in to four broad disc ip l ines and are as fo l lows:

1 . Mater ia l s Processinga . F lu id Exper iment Sys temb. Vapor Crys ta l Growthc . Mercury Iodide Crys ta l Growth

2 . Envi ronmenta l Observa t iona . Atmospher ic Trace Molecules Spec t roscopyb. Very Wide Field Camera

3 . F lu id Mechanicsa . Geophys ica l Flu id Flow Cel l

4 . Li fe Sciencesa . Ames Research Centerb . Urine Moni tor ing Inves t iga t ionc . Autogenic Feedback Tra in ing

The crew was div ided in to two teams, each working a 12-hour sh i f t . Thus , theSpacelab was opera ted 24 hours a day throughout the 7-day miss ion .

The VWFC (Very Wide Fie ld Camera) exper iment was discont inued on the second day .Except for th i s opera t ion , the exper iment ac t iv i t ies for day 2 were a repea t ofthe f i r s t day . Addi t iona l ly , an Aurora l Imaging Exper iment in the Envi ronmentalObserva t ion disc ip l ine and the Drop Dynamic Module exper iment in the Flu idM ec han ic s d is ci pl in e w er e p er fo rm ed .

The day 3 exper iment ac t iv i t i es aga in were a repea t of those conducted on day 2wi th one addi t ion - Ioniza t ion of Solar and Galac t ic Cosmic Ray Heavy Nucle i -in the Envi ronmenta l Observa t ion discip l ine .


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TABLE 1.- STS 51-B SEQUENCE OF EVENTS

EventAPU activat ion (1)

(2)(3)

SRB HPU activat ion command (LH-A2)MPS start command sequence (engine 3)SRB ignit ion command from GPC (lift -off)MPS throt t le-down to 94 percent (engine 3)

MPS throt tle-down to 65 percent (engine 3)Maximum dynamic pressureMPS throt tle-up to 104 percent (engine 3)SRB separat ion command from GPCMPS throt tle-down for 3g accelerat ion (engine 3)3 g a cc el er at io nMain engine cutoff (MECO)External tank separat ionOMS 1 ignitionOMS 1 cutoffOMS 2 ignitionOMS 2 cutoffNU SAT d ep lo yFlight control system checkout - APU 2 star t

APU 2 shutdownAPU 1 act ivat ionDeorbi t maneuver ignit ionDeorbi t maneuver cutoffAPU activation (2)

(3)En tr y i nt er fa ceEn d bl ac ko utTerminal area energy management (TAEM)

Actual t ime, G.m.t .

119:15:55:08119:15:55:09119:15:55:10119:16:01:47.411 9: 1 6 : 02 : 11 .4119:16:02:1811 9: 1 6 : 02 :3 6 .8

119:16:02:45.511 9: 1 6 : 0 3: 0 9119:16:03:18.6119: 16 :04 :24119:16:09:50.6119: 16 :09 :51119:16:10:53119 : 1 6: 11: 11119:16:12:5311 9: 1 6 : 1 5 : 07119:16:48:33119:16:50:5811 9 :2 0 : 1 7 :0 0126:01:04:17126:01:08:40126:14:59:51126:15:04:48126:15:09:12126:15:26:59126:15:26:59126:15:40:04126:15:54:44126:16:04:42


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During propellant loading, a hydrogen leak occurred at the GUCP (groundumbil ical carr ie r plate ) . Hydrogen concentrat ions as high as 12000 ppm were

observed for a short t ime while the valve was open. The valve was cycled and nofur ther evidence of leakage was seen.

Liquid oxygen drainback was not ini t iated as planned at T-5 minutes. Due tofai lure of a front-end processor at the LPS (launch processing system), thel iquid oxygen faci l i ty replenish valve did not close as scheduled, nor did the-ET liquid oxygen vent va lve. This caused a short hold to be ini t iated a t T-4minutes . During the hold the valves were manually posi t ioned, in i t ia t ing liquidoxygen dra inback. Resumpt ion of the count was then delayed approximately 1 ad-

dit ional minute to achieve a tota l l iquid oxygen drainback of 5 minutes . Thisproblem is being fur ther invest igated.

Ascent performance appeared to be normal . Orbi ter main engine 2 gaseoushydrogen pressurant-supply pressure fa i led a t approximately T+6 minutes. Thisproblem did not affect performance.

ORBITER

At li f t -off , the right ET door open indicat ion B was lost . Later , when the ETdoors were closed , motor B did not operate . Motor A closed the door in s inglemotor t ime.

On orbit , the crew reported a pro trus ion from the thermal protect ion system atabout the center of the r ight OMS pod. The protrusion was viewed by te levisionand determined not to be a f l igh t-safety issue . On f l ight day 3, MMCA (midmotor cont rol assembly)-2 operat ions status 5 (V76X2225E) indicated zero. Powerwas cycled on MMCA-2, but the status b it did not rese t . During payload bay door

closure, no la tch A or B latched indica t ion was rece ived on the port-a ft doorlatches . All re lease and ready-to-Ia tch indicat ions were rece ived . The crewreported tha t from visual indicat ions the port -aft latches were in the latchedposi t ion . The planned PTI maneuvers were deleted from the ent ry prof i le to

h d l d h l d b d l h f h


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During the miss ion , v ir tual ly a l l sc ien t i f ic objec t ives were met , and several

experiments were able to gain addi t ional da ta beyond the i r miss ion expecta t ions .I t i s es t imated that more than 250 bi l l ion bi t s of da ta were obta ined from allins t ruments combined , and more than 3 mil l ion video images were recorded .Although i t wil l take severa l months to analyze the data f rom the 7-day miss ion ,pre l iminary indicat ions are tha t Spacelab 3 wil l produce a number of majord iscover ies .

The mission demonst ra ted the capabi l i tes of Spacelab for mul t i-d isc ip l inaryresearch in microgravi ty . Once again , ai r - to-ground teamwork between the crew,

the pr incipa l invest igators , and the ground suppor t teams culminated in asuccessfu l f l igh t . Excel len t da ta f low and downl ink video cont r ibuted sub-s tan t ial ly to the enhancement of sc ien t if ic research.

This mission was par t icular ly successfu l in providing a high-quali tymicrogravi ty envi ronment. The gravity-gradient a t t i tude of the Shut t le provedto be qui te s table and conducive to the per formance of de l ica te experiments inmater ia ls sc ience and flu id mechanics . Impor tan t work was a lso accompl ished inthe discip l ines of l ife sc iences and atmospher ic observa t ions.

Of the 15 inves t iga t ions in four scien ti f ic d iscip l ines, a l l bu t the Very WideField Camera experiment met the i r pr imary object ives . The handle on the SAL(Scient i f ic Air lock) was bent and ai r lock opera t ions could not be comple ted.This anomaly resu l ted in the loss of VWFC act iv i t ies for the mission.

A f inal pos tmission repor t is in preparat ion by the Marsha ll Space Flight Centerand should be avai lable in the near fu ture .

F LUI D E XPE RI ME NT S YST EMDuring the f i r s t f l igh t of th is new FES (f luid exper iment sys tem) fac i l i ty, twoTGS (t r iglyc ine sulfa te) crys tal s were successfu l ly grown in space from a


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VAPOR CRYSTAL GROWTH SYSTEM

A mercury iodid e c rys ta l measur ing 14mm x 8mm x 7mm, about the s ize of a sugarcube , was success fu l ly grown from a seed crys ta l 20 t imes smal le r in th i s newVCGS (vapor crys ta l growth sys tem) fac i l i ty by a vapor t ranspo r t proce ss . Thecrys ta l was grown at a carefu l l y con t ro l led ra te tha t var ied f rom Imm to 3mm perday o ver a 104-hour growth per iod . Downl ink v ideo and crew repor t s of v isua l .observa t ions were major benef i t s to inves t iga tors on the ground, who were ableto fo l low the course o f the inves t iga t ion in de t a i l .

The sample mercury iodide cry s ta l produced in the VCGS wil l be ana lyzed andevalua ted to de t e rmine i t s qua l i ty and proper t ies as an X-ray and gamma ray

detec tor for appl i ca t ions in sc i en t i f ic resea rch , medic ine , and indus t ry .

Crys ta l s g rown in a micrograv i ty envi ronmen t , wi thout the in te r fe rence ofg rav i ty-dr iven convec t ion , a re expec ted to be more uni form and , thus , to haveimproved per formance a s d etec tor mater i al s .

MERCURY IODIDE CRYSTAL GROWTH

The MICG (Mercury Iodide Crys ta l Growth) exper iment was a ref l igh t of a Space-lab 1 exper iment , wi th modi f i ca t ions as a resu l t of da ta ga ined on the f i r s tmis s ion . S ix car t r idges of mercury iodid e mater ia l wi thout seed crys ta l s , eachhav ing di f fe ren t growth condi t ions , were processed for 70 hours a t a t ime.Pos t f l igh t ana lys i s of the resu l tan t c rys ta l s wi l l y ie ld impor tan t new dataabo ut the nuc lea t ion process in a micrograv i ty envi ronment .

DROP DYNAMICS MOD ULE

After in i t i a l s ta r t -up di f f icu l t ies , the DDM (Drop Dynamics Module) fac i l i ty

und erwent inf l i gh t main tenance and opera ted success fu l ly for exp lora toryresearch in the behavior o f f ree- f loa t ing f lu id drops . For the f i r s t t ime , apr inc ipa l inves t ig a tor opera ted and repa i red his own exper iment in space as aSpace lab crew member . Close in te rac t ion be tween the crew and ground teams, as


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GEOPHYSICAL FLUID FLOW CELL

The purpose of the GFFC (Geophys ica l Flu id Flow Cell ) inves t iga t ion was to s tudyf lu id motions in microgravi ty as a means of understanding convect ion on the Sun,in plane tary atmospheres, in Ear th 's oceans , and in bas ic f lu id physics . Meteor-o logis t s and as trophys ic i st s are in te res ted in the large-sca le c i rcu la t ions offlu ids under the inf luence of ro ta t ion , gravi ty , and heat ing .

The unique GFFC faci l i ty, which models var ious f lu id motion and tempera turescenarios , opera ted exce l len t ly ; a l l planned scenar ios were performed dur ing an

84-hour per iod , and a bonus of 13 unscheduled scenar ios in 18 hours of ext raopera t ions was gained . These pioneer ing experiments , the f i r s t labora toryexper iments of convect ion in spher ica l rota t ing shel ls wi th a radica l gravityf ie ld, were preprogrammed and monitored by the Space lab 3 crew. Approximate ly46,000 images were recorded on f i lm for post f l igh t ana lys is .

AMES RESEARCH CENTER LIFE SCIENCES PAYLOAD

The ARCLSP (Ames Research Center Li fe Sciences Payload) cons is ted of 2 RAHF's

(1 hous ing 24 rodents , the other hous ing 2 pr imates) , a bio te lemet ry sys tem, anda dynamic envi ronment measurement sys tem. The purpose of the Space lab 3 ARCLSPinvest iga t ions was to perform an engineer ing ver i f ica t ion of the new equipmentin prepara t ion for fur ther l i fe sc ience research on future miss ions .

The Space lab 3 miss ion successful ly demonst ra ted tha t the new fac i l i t i es providea sui table animal habi ta t . There were some in i t ia l di f f icu l t ies wi th conta in-ment of food and waste par t ic les , but the workaround procedures minimized theproblem. Ref inements to the des ign are necessary before ref l igh t . Per formance

of the food, water , and ac tiv i ty moni tors was sa t i s factory and provided goodengineer ing data about the ac t iv i ty, as wel l as the s tatus , of the animals .Accelerat ion data f rom the RAHF envi ronment dur ing launch and ent ry were taperecorded and wi l l be avai lable for pos tf l ight analys is .


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A UR OR AL I MA GI NG E XP ER IM EN T

Of the 21 scheduled oppor tun i t ies for aurora l observa t ions , 18 were accompl i sh-ed , wi th auroras c lear l y v is ib le on each o bserva t io n . This miss ion marked thef i r s t t ime s ince Skylab tha t aurora l observa t ions have been made on a mannedU. S. spacef l igh t and the f i r s t t ime ever tha t a manned Amer i can space vehic lehas passed d i rec t ly through an aurora (3 such passages occur red) . The resu l t~ntda ta a re the most comple te se t of aurora l images ye t f rom a manned miss ion .

The o rb i ta l i nc l ina t ion and vehic le a t t i tude of the Space lab 3 miss ion wereespec i a l ly f avorab le for ve iwing auroras , and Nature obl iged wi th a show ofgrea t var ie ty . The aurora passes covered the evening , midnight , and morningsec tors of t he South Pole aurora l ova l and occur red dur ing di f fe ren t leve ls ofgeomagnet ic ac t iv i ty . More than a ha l f mi l l ion video images were recorded , aswel l as an undete rmined number of 35mm exp osures . The video tapes wi l l beprocessed pos t f l igh t to cons t ruc t thr ee-d imens iona l images of aurora l s t ruc turea nd m ot io n.

The inves t iga t ion demons t ra ted the u se of s tandard orb i te r equipmen t forsc i en t i f ic resear ch ; no exper iment -unique hardware was requi red to col le c t thewea lth of informat ion .

ATM OS PHE RI C T RA CE M OL EC UL ES S PE CT RO SC OP Y

Although the ATMOS (Atmospher ic Trace Molecules Spec t roscopy) ins t rument wasdeac t iva ted ear l ie r than p lanned when a pre ssure l eak dis ab led i t s laser , theinves t iga t ion was one of the most success fu l of t he Space lab 3 miss ion . In 193 -minute ope ra t ions ATMOS made 150 independent a tmosphe r ic spec t ra , each ofwhich con ta ins a t leas t 100 ,000 ind iv idua l spec t ra l measuremen ts . The to t a lharves t of da t a i s es t imated to be more than 300 mi l l ion measurements of thea tmosphere a t a l t i tudes f rom 10 to 150 km . Fur thermore , dur ing 5 solarca l ib ra t ions , de ta i led inf ra red spec t ra of the Sun were obta ined .

The ATMOS spec t ra wi l l be used to cha rac te r ize the phys ica l and chemica l pro-


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TAdLE 11.- uRdlTEk PRGdLEM TRACKING LIST+++~"_.+'_'~.""''''~'''++''.f!?~.y~~~ ~ __~~~~ __.-~~ _'+__ _+_ - __ ._.++.... +++ .. __ ...... ~

TITLE

JSC OV 4099 STS 51 +B P ROB LEM TR ACK ING LI ST

I T IM E, G M T I

JUNE 21 , 1985

I NO . I R ES P. M GR .COMMENTS

1 WATE R SP RAY BOIL ER 3 C ONTR OLLE R AINOPERATIVE.

2 RI GHT ET DOO R MOTO R B INOP ERATIVE .

3 INSTRUMENTATION:

A SS ME 2 GH 2 OU TLE T PRE SSUR E( V 4 1P I 2 60 A ) FA I LE D .

B HY DRAU LIC SY STEM 2 M AIN PUM PP RE SS UR E B ( V5 8P 02 15 C) B IA SE D L OW.

4A BO RT A DV IS ORY L IG HT M AL FU NC TI ON EDAND L ENS WAS CRA CKED .

5 S YS TE MS M AN AG EM EN T O NB OA RD D IS PL AYD ATA E XH IB IT ED E RR AT IC VAL UE S.

119:16:12

119:16:21

119:16:07:17

119:16:02

119:10:19

119 :17 :32

AT 119:16 :11 :33, BFS FAULT 1 INDICATED SM2 APU D. HAINESTEMP 3. CREW SWITCHED TO CONTROLLER B, CAR 24F013TEMPERATURE STARTED TO COOL AND APU 3 WAS SHUT CLOSEDOFF. LUBE OIL TEMP REACHED 335 DEG F, LIMIT IS OS/29/85355 DEG F. R&R CONTROLLER A AT KSC.

AT LIFTOFF, RIGHT ET DOOR B OPEN INDICATION R. BALCIUNAS(V56X4015X) WAS LOST. AT ET DOOR CLOSURE, B CAR 24F009CLOSED INDICATOR WAS NOT RECEIVED. BOTH A AND B CLOSEDINDICATED LATCHED. DOOR CLOSED IN SINGLE MOTOR 06/14/85

D RI VE T IM E. C ON NE CT OR 5 0P 88 4/ J2 F OU ND D EM AT EDAND WITH A WEAK SPRING. REPLACED CABLE HALF ANDR ET ES TE D. P RO CE DU RE S C HA NG ED .

REA D O FF.S CALE HIGH A FE W M INUT ES BEF ORE ME CO.R&R AT KSC.

RE AD AB OUT 80 PSI LOW. MEA SURE MENT SCAL ED FR OMo TO 4000 PSI . BIAS WITHIN SPEC. FLY AS IS .

THE ABORT LIGHT DID NOT GO DIM WHEN ABORT ACOM MAN D WAS REMO VED . CRE W REP ORT ED LEX AN LIG HTCOVER WAS CRACKED. LIGHTS OPERATED AT KSC.C HA NG E C HE CK OU T P RO CE DU RE . R &R L IG HT A SS EM BLY.

FIRST NOTED WHEN SPEC 67 AND 69 DISPLAYED ERRATICIFUEL CELL DATA. TELEMETRY DATA WAS NORMAL.IU PL IN KE D G -M EM PAT CH C OR RE CT ED T HE P RO BL EM .ITWO SPACEL AB POW ER PAR AMET ER FD A LI MITS OV ER-ILAYED TWICE THE AREA ALLOCATED IN DATA TABLE.ISOFTWARE UNIQUE FOR STS 51-B. SOFTWARE DR.I

I

CLOSED06/05/85

P. COTAC AR 2 4F 00 2

D . H AI NE S

R . B UR GH DU FFCLOSED06/05/85

W. C. YOUNGCLOSED06/19/85


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TABLE 11 . - O kBIT Ek PRO dL E M T RAC K IN G LIST(Cont 'd). . . . ++.++4~~~ ! +.~ .. ~~+?- ........ .__.+ ..~-..... +++ ... ~ ++---.. ~+_.+.++.-+++"~, , ,+.+, ,++_'~~.+++ t+.~

JSC OV-099 STS 51+B PROBLEM TRACKING LIST JUNE 21, 1985++.. ++.+t~~~ ~ + ++ ++ .. - ~-+~++ ..... -.~+~.. -.+?++.-++.- .... +++- . . . ++-+.. +.+...~ . .. . - - + . .--++--+++- ..++++~ ..... +~I NO . I TITLE I T IM E, G .M .T. I COMMENTS R ES P. M GR .

N

10

11

6 R IG HT O MS P OD T HE RM AL P RO TE CT IO NS Y ST E M P R OT R U SI O N.

7 GALLEY DID NOT DISPENSE WATER.

8 APU 3 SEAL CAVITY DRAIN LINE HEATER3 A FAI LE D.

9 SMOKE DETECTOR IN AVIONICS BAY 2AFAI LE D S EL F T ES T.

RIGHT RCS THRUSTER R4DI NJ EC TO R H EATE R FAI LE D.

S+BAND UPPER RIGHT ANTENNA RE+FLECTED POWER HIGH AND UPPER LEFTA NT EN NA R EF LE CT ED P OW ER E RR AT IC .

119:17:27

119:19:02

120:13:26

119:19:42120:13:10

120:10:02

119 :16 :04(R)123:13:29(L)

PROTRUSION FROM ABOUT CENTER OF RIGHT OMS POD.A 6 BY 16 INCH AREA ON CARRIER PANEL Y WEBB DOORWAS LAID BACK AFTER PULLING THROUGH A FASTENER.REPAIR IN PLACE. REPAIRED NEW PANEL ON OV-I03L EF T P OD .

GALLEY WORKED AFTER CREW BANGED ON DOOR ANDSIDE. DID NOT DISPENSE HOT OR COLD WATER AT KSC.P RO BA BL E I NT ER MI TT EN T I N C ON TR OL PAN EL M IC RO -PROCESSOR. R&R AT KSC. FIAR.

HEATER FAILED TO CYCLE BACK ON AT ABOUT 60 DEG F(V46T0386A). SWITCHED TO HEATER 3B, CYCLEDNORMALLY. R&R THERMOSTAT S132A AT KSC.

THE 28 ALARM WORKED, BUT THE 2A ALARM FAILED.TEST REPEATED HOLDING BUTTON IN FOR 60 SECONDS,2A ALARM FAILED AGAIN. R&R AT KSC.

INJECTOR HEATER DID NOT CYCLE UNTIL AFTER HOTFIRE. HEATER CYCLE WAS OFF NOMINAL. DID NOTDRAIN AND PULSE PURGE RIGHT MANIFOLD 4 OX ANDFUEL AT DRYDEN. NO LEAK DURING FERRY OR AT KSC.HEATER FAILED ON AT KSC. R&R THRUSTER.

17 TO 18 WATTS INDICATED ON UPPER RIGHT. S+8ANDF OR WA RD L IN K P ER FO RM AN CE T HR OU GH T DR S O N B OT H. FW DAND AFT BEAMS MARGINAL. REMOVED BOTH UPPERANTENNAS AT KSC, RECYCLED BOTH IN ONE WEEK ATVENDOR FOR OV-099. REINSTALLED AND RETESTED.

J. SMITHC AR 2 4F OO ICLOSED06/19/85

R . T RAVA NI NOH EN 0 05 0FCLOSED06/14/85

W. SCOTTC AR 2 4F 01 2CLOSEDOS/29/85

H . R OT TE RC AR 2 4F 00 4CLOSEDOS/29/85

G. GRUSHC AR 2 4F 00 7CLOSEDOS/29/85

D . E GG ER SC AR 2 4F 00 5C AR 2 4F 00 6CLOSED06/18/85


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T ABL E 11.- O Rt3IT ER PR O BL EM T RAC K II'JG L IST (C ont'd)

TITLE

JSC OV-D99 STS 51~B PROBLEM TRACKING LIST

I T IM E, G .M .T. I

JUNE 21, 1985

I NO . I R ES P. M GR .COMMENTS

w

12 RIGHT OMS OXIDIZER LOW+POINT DRAIN~ 120:00:02LI NE H EAT ER S ET P OIN T D RIF TED .

13 KU~BAND RADAR MODE FAILED SELF TEST. 119:18:20

14 APU 1 FUEL BYPASS LINE HEATER BFAI LE D O N.

15 MID MCA 2 OPS STATUS 5 (V76X2225E)I ND IC AT ED Z ER O.

16 SSME 2 L02 PRE-VALVE NO OPENIN DIC ATI ON DU RIN G L OX D UMP.

17 HIGH OXYGEN FLOW ON PRESSURECO NTR OL SY STE M 2 .

123:06:11

121:20:07

119:16:12

125:00:12:01

TEMPERATURE (V43T6237A) CYCLING LOW, 51 TO 65DEG F. LOWERED FDA LIMIT FROM 50 TO 45 DEG F.AT 121:07:07:01 FELL TO 45 DEG F, CREW SWITCHEDTO B HEATERS AND TEMP CYCLED NORMALLY. T/S ATKSC FOUND THERMOSTAT FAILED. R&R Sl111.

COM MODE OPERATING PROPERLY. T/S AT KSC.NO REPLACEMENT AVAILABLE. SUSPECT EA1. JSCEVALUATE AGC SPIKE DATA. PASSED SELF TEST ATKSC. FLY AS IS.

REACHED 206 DEG F. SWITCHED TO HEATER A ANDT EM PE RATU RE ( V4 6T OI 28 ) R ET UR NE D T O N OR MA L.P RO BAB LE C ON TAM INATIO N I NTE RNA L T O S WIT CH. R &RTHERMAL SWITCH AT KSC.

POWER ON MMCA+2, PL2 AND FF4 WAS CYCLED FOR K7,K26, AND K30"THE LEFT AFT BULKHEAD MOTOR 2LATCH AND THE VENT DOORS 4 AND 7 MOTOR 1 OPEN ANDCLOSE RELAYS. THE STATUS BIT WAS NOT RESET.FOUND K7 RELAY STUCK ON AT KSC. R&R MMCA-2.

O PEN IN DIC ATI ON ( V41 X12 34X ) WA S NO T PR ESE NTDURING MPS DUMP. THE CLOSED INDICATION(V41X1235E) ALSO WAS NOT PRESENT DURING THE DUMP.VALVE CYCLED PROPERLY AT DRYDEN. R&R ACTUATOR.

CLASS 2 HIGH 02 FAULT SUMMARY MESSAGE FOR PCS 2.CDR REPORTED A LOUD BANG AS 14.7 PSI REG 2 WENTTO SECOND STAGE FLOW. CHANGED TO PCS 1. T/S ATKSC DID NOT REPEAT PROBLEM. FLY AS IS.

J . HO OPE RC AR 2 4F 01 7CLOSED06/14/85

J. GRIFFINC AR 2 4F 00 8CLOSED06/18/85

W. SCOTTC AR 2 4F 01 1CLOSED06/12/85

R . E GU SQ U IZ AC AR 2 4F 01 5CLOSED06/05/85

P. COTAC AR 2 4F 01 6CLOSED06/18/85

J . W HA LENCLOSED06/14/85


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TABLE 1 1 . - ORBITER Pf\GdLEIVI TRACKIi~G Ll3T (Cont 'd)~~+-T++.tT .. ~-+.. ~ . ~~ -~~+++++++~~~~~.- .+. .~.++~ .. +++ . . +~...... ~+ ~ .... ~ ... ~.+-_..~.... + + + -- . . . . . ~ .

JSC OV-099 STS 51+B PROBLEM TRACKING LIST JUNE 21, 1985

I NO . I R ES P. M GR .TITLE I T IM E, G .M .T. I COMMENTS

18 PAYLOAD BAY DOOR CLOSE SEQUENCEFAILED ON PORT AFT LATCHES.

19 BACKUP FLIGHT SYSTEM ERRORU PD AT IN G R UN WAY.

20 LEFT MAIN LANDING GEAR BRAKESDAMAGED.

21 MPS HELIUM SYSTEM DECAY RATE HIGHD UR IN G E NT RY R EP RE SS .

22 MAIN LANDING GEAR DUMP VALVELEAKED3 D AY S A FT ER L AN DI NG .

23 PAYLOAD BAY BLACK AND WHITE TVCAMERA "A" DID NOT RESPOND TO ALCP BI C OM MA ND S.

24 WCCU LEG UNIT A PTT BUTTON STUCK.

126:12:28:16 NO LATCH A OR B INDICATION ON LEFT AFT LATCHES.R EC EI VE D A LL R EL EA SE A ND R EA DY-T O~ LATC HIN DI CATI ON S. C RE W R EP OR TE D P ORT A FT L AT CH ESVISUALLY IN LATCHED POSITION. PROPER LATCHO PE RATI ON D EM ON ST RATE D AT K SC A FT ER V ER IF YI NGLEFT AFT LATCHES WERE NOT FULLY CLOSED.

126:14:12:25 A BFS ERROR MESSAGE WAS OBSERVED AS THE BFS MAXITABLE WAS UPDATED. ISSUED BFS PROGRAM NOTE TOC LE AR T SC B UF FE R B EFO RE U PL IN K CO RR EC TI ON.

LANDING BROKE STATORS ON BOTH INBOARD AND OUTBOARD LEFTBRAKES. R&R AT DRYDEN. INITIATED NEW BRAKER ED ES IG N S TU DY.

ENTRY POSTFLIGHT DATA REVIEW. PROBABLE TRANS lENT LEAKIN LH2 FEED SYSTEM. BOTH SYSTEMS TIGHT AT KSC.

POST FLIGHT INSPECTION OF LEFT WHEEL WELL FOUND LANDING GEARD OO R S PR AY ED . VALVE E NE RG IZE D A ND OV ER HE AT ED .LEAK IN VALVE BODY. VALVE PULLED AND LINEPLUGGED AT DRYDEN. R&R THREE VALVES. GOLD MYLARTAPE ON SOLENOIDS. MAY CHANGE TAPING PROCEDURES.

ON ORBIT F OLL OW IN G 1 0 SU CC ES SF UL L A UR OR A PAS SE S T HE I RI SDID NOT OPEN AFTER3 ALC PBI COMMANDS. T/S ATK SC F OU ND R EM OT E C ON TR OL U NI T M IS SE D C OM MA ND S.

ON ORBIT CREW DEBRIEFING. UNIT INITIALLY HAD DEADBATTERIES. UNIT OPERATED ON TRANSMIT. T/SUNABLE TO REPEAT PROBLEM. FLY AS IS.

R . B AL CI UN ASC AR 2 4F OI 0CLOSED06/14/85

W. C. YOUNGCLOSED06/20/85

C . C AM PB EL LC AR 0 8F Ol iCLOSED06/20/85

P. COTACLOSED06/14/85

D . H AI NE SCAR AC 9961CLOSED06/14/85

B . E MB RE YCLOSED06/14/85

L . L EO PO LDCLOSED06/14/85


16/16

TAdlE 11.- ORBITER PRGBlE1Vl TRACKING LIST (Concluded)~+~~~+.~~.+ ~ .. -.--+++++-t~.~+.~~~ .... +..~~ ... ~.-+.+~.. ~+.~-++-~~~~+ ...+-~ .- -+~+-.+--+_.+ ...... ~+~ ...

JSC OV~99 STS 51.B PROBLEM TRACKING LIST JUNE 21, 1985~~+~.-""~~~~++~.~"" ... -+~++-+-++-++ ..... ++.. -.-++ -.. +++++ .. ~-++ . . +."+-~++.""-~+T+.+~+."+ +.+++--+', N O. , TITLE , TIME, G.M.T. , COMMENTS R ES P. M GR .

25 ACIP X-AXIS ANGULAR ACCELEROMETER ,LIFT OFFFAILED. ,

,

,,

LEFT OUTBOARD ELEVON TILE , E NTRYSLU MPE D A ND G AP FIL LER WAS B REAC HED .,

I

I

26

P RE PAR E D B Y:/ s /R J WROB ERT J . WA RD

06/21/85DATE

NASA-JSC

R EA D O FF +S CA LE H IG H T HR OU GH OU T F LI GH T. R EM OV EDAND REPLACED FILTER CARD AT KSC. X+AXISACC ELE ROME TER F AILE D RET EST IN V EHI CLE. F LY ASIS FOR STS 51~F AND R&R POSTFLIGHT. FIAR.

R . G IE SE CK EH EN 0 04 9FCLOSED06/14/85

SI MIL AR T PS DAM AGE ON OV+ I03 A FTE R P REV IOUS

FLIGHT. NO STRUCTURAL DAMAGE. STANDARD TPSR EPAI R A ND A DD IT IO NA L P RE FL IG HT I NS PE CT IO NS .

J . SMITHCLOSED06/14/85

A P PR O VE D B Y:/ s /J EMJ OS EP H E . M EC HE LAY

06/21/85DATE

Documents

STS-51B National Space Transportation Systems Mission Report