STS-65 Space Shuttle Mission Report

8/7/2019 STS-65 Space Shuttle Mission Report

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--- Pv'A.SANASA-CR-197598 - " " I_. C]7', _9 _'__ '--:, NSTS-08292

STS-65 ', _"' ' SPACE SHUTTLE 1,,IAsA-CR-197598 ,: 19950012195i _,MISSIONREPORTI

-.I_,,!_L_L. (NASA-CR-197598).. STS-65 SPACE N95-18610SHUTTLE HISSION REPORT (LockheedEngineering and SciencesCo.) 64 p Unclas

... G3/16 0037739

C'-"- SEPTEMBER1994


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"4

NOTE L_'_ !TheSTS-65SpaceShuttleMissionReportwaspreparedfrominputsreceivedfromtheOrbiterProjectOfficeaswellasotherorganizations.Thefollowingpersonnelmaybecontactedshouldquestionsariseconcemingthetechnicalcontentofthisdocument.WilliamH.Arceneaux Orbiterandsubsystems713-483-3335C.A.Snoddy,MSFC MSFCElements(SRB,205-544-0391 RSRM,SSME,ET,SRSS,andMPSFranciscoMoreno,JSC Payloads/Experiments713-483-1208G. P.Buoni,JSC DTOsandDSOs713-483-0639F.T. Bums,Jr.,JSC FCEandGFE713-483-1262


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NSTS 08292

" STS-65SPACESHUTTLE

MISSIONREPORT

.. ,,,._Preparedby

LESC/FlightEvaluation_)fficeApprovedby

WilliamH. Arceneaux'fSTS-65LeadMissionEvaluationRoomManager

CampManager,FlightEngineeringOffice


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F"_, STS-65Table of ContentsTitl.__ee Pa_.0.g.e.

INTRODUCTION .......................................... 1 MISSIONSUMMARY....................................... 3PAYLOADS .............................................. 6LIFESCIENCES ..................................... 7AquaticAnimal Experiment Unit 7Biorack....................................... 7Biostack ..................................... 8Extended DurationOrbiterMedical Project ......... 8Linear Compressor EnhancedOrbiterRefri.qerator/Freezer ...................... 9SlowRotatinqCentrifuqe Microscope ............. 9Microqravity Effects onStandardizedCoqnitiwPerformanceMeasures .................... 10Applied Researchon Separation Methods.UsinqSpace Electrophoresis ............... 10Real-Time RadiationMonitorinq Device ............ 11Spinal Chanqes inMicroqravity 11

f_ Thermoelectric Incubator and CellCulture Kit_...... 11MATERIALSCIENCE ................................. 12AdvancedProtein CrystallizationFacility........... 12Bubble, Drop and ParticleUnit.................... 12Critical Point Facility............................ 12Free Flow Electrophoresis Unit 13


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STS-65 Table of Contents F--_,Titl._..ee

Main PropulsionSystem .......................... 21ReactionControl Subsystem ...................... 23Orbital Maneuverin,qSubsystem.................... 24PowerReactantStrora,qeand DistributionSubsystem.. 24Fuel Cell PowerplantSubsystem.................... 24Auxiliary PowerUnit Subsystem .................... 25Hydraulics/WaterSpray BoilerSubsystem............ 25Electrical Power Distributionand Control Subsystem.. .26EnvironmentalControl and Life SupportSubsystem .. 26SmokeDetection and FireSuppressionSubsystem.... 28Airlock Support System .......................... 28Avionics andSoftwareSupportSystem ............. 28Communicationsand Trackinq Subsystems ......... 29Operational Instrumentation/ModularAuxiliary DataSystem ........................ 30Structures andMechanical Subsystems ............. 30Inteqrated Aerodynamics,Heatinqand Thermal

Interfaces. 31Thermal ControlSubsystem ....................... 32Aerothermodynamics............................. 32Thermal ProtectionSubsystem..................... 32REMOTEMANIPULATORSYSTEM.............................. 34FLIGHTCREWEQUIPMENT/GOVERNMENTFURNISHED


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List of TablesTABLEI -STS-65SEQUENCEOFEVENTS..................... 43TABLEII -STS-65ORBITERPROBLEMTRACKINGLIST.......... 46TABLEIII -STS-65GFEPROBLEMTRACKINGLIST .............. 50TABLEIV - MSFCELEMENTSPROBLEMTRACKINGLIST......... 52

AppendixesA - DOCUMENTSOURCES.................................. A-1B - ACRONYMSANDABBREVIATIONS........................ B-1


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F" f_i INTRODUCTION

I- The STS-65SpaceShuttleProgramMissionReportsummarizesthePayloadactivities. as wellas theOrbiter,ExternalTank (ET), SolidRocketBooster(SRB),RedesignedI SolidRocketMotor(RSRM), andtheSpaceShuttlemainengine(SSME)systems. performanceduringthe sixty-thirdflightof theSpaceShuttleProgramandthe! seventeenthflightof the OrbitervehicleColumbia(OV-102). Inadditionto theOrbiter,_ the flightvehicleconsistedofan ETthatwas designatedET-64;threeSSMEsthatwere/ i_ designatedas serialnumbers2019, 2030, and2017 inpositions1, 2, and3,! respectively;andtwoSRBsthatweredesignatedBI-066. The RSRM'sthatwereii installedin eachSRBweredesignatedas360P039Aforthe leftSRB, and360W039B

forthe rightSRB.ThisSTS-65 SpaceShuttleProgramMissionReportfulfillstheSpaceShuttleProgramrequirementas documentedinNSTS 07700, VolumeVIII, AppendixE. Therequirementthatisstatedinthatdocumentis thateachmajororganizationalelementsupportingthe Programwillreportthe resultsoftheirhardware(andsoftware)evaluationandmissionperformance,,plusidentifyall relatedin-flightanomalies.J

i The primaryobjectiveof thisflightwasto completetheoperationof thesecondInternationalMicrogravityLaboratory(IML-2). The secondaryobjectivesofthisflightf ..... _ weretocompletethe operationsof theCommercialProteinCrystalGrowth(CPCG),theOrbitalAccelerationResearchExperiment(OARE),and theShuttleAmateurRadio_-i Experiment(SAREX) II payloads.Additionalsecondaryobjectiveswere tomeetthe_J!_ requirementsof the Air ForceMauiOpticalSite (AMOS) and the MilitaryApplicationofShipTracks (MAST) payloads,which weremanifested as payloads of opportunity.


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flightfortheCommanderandMissionSpecialist1;thesecondspaceflightforMission ..."-_,Specialist2;andthefirstspaceflightforthePilot,MissionSpecialist3, MissionSpecialist4, andPayloadSpecialist1. Eachcrewmemberwasassignedtooneoftwoteamstoprovidearound-the-clockoperationsduringthemission.Theredteamconsistedof theCommander,Pilot,MissionSpecialist1, andPayloadSpecialist1;andtheblueteamconsistedofMissionSpecialist2, MissionSpecialist3, andMission o,Specialist4.


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_'_ MISSIONSUMMARY

TheSTS-65missionwassuccessfullylaunchedasplannedat 189:16:43:00.013G.m.t.(12:43p.m.e.d.t,onJuly8, 1994). Thecountdownproceededina smoothmannerwithnounplannedholds.TheascentphasewasnominalandallSpaceShuttleElementsperformedsatisfactorily.Noorbitalmaneuveringsubsystem(OMS)-1maneuverwasrequiredasa resultofthedirectinsertiontrajectoryflown.Firststageascentperformancewasasexpected.SRBseparation,entry,deceleration,andwaterimpactoccurredasanticipated.BothSRBsweresuccessfullyrecovered.PerformanceoftheSSMEs,ET,andmainpropulsionsystem(MPS)wasnormal.Adeterminationofoverallvehicleperformancewasmadeusingvehicleaccelerationandpreflightpropulsionpredictiondata. Fromthesedata,theaverageflight-derivedenginespecificimpulse(Isp)determinedfortheperiodbetweenSRBseparationandstartof3-gaccelerationwas452.1seconds,whichisslightlylowerthanexpectedbutsatisfactorywhencomparedwiththepredictedvalueof452.57seconds.SSMEcutoff(MECO)occurredat 189:16:51:30.31G.m.t.(510.63secondsMET)whenthevehiclereachedtheplannedMECOtarget.TheOMS-2 maneuverwasperformedat189:17:22:55.2G.m.t.(00:39:55.2MET). Thetwo-enginefiringwas141.3secondsindurationandprovideda differentialvelocity

f-- (AV)of221.8ft/sec.The resultantorbitwas162.9by160.3nmi.Atapproximately189:17:23G.m.t.(00:40:00MET),followingmainpropulsionsystem(MPS)vacuuminerting,theliquidhydrogen(LH2)manifoldpressureincreasedto17psia.ThisincreasecoincidedwiththeOMS-2maneuver.Onpreviousmissionswhenvacuuminertingwasperformedmanually,thepressureincreasedto


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At 199:12:36:12.7(09:19:53:12.7MET),a transientinertialmeasurementunit(IMU)1 _'"_(S/N204)redundant-ratebuiltintestequipment(BITE)messagewasgeneratedwhentheazimuthgyro'sredundantinputaxismeasureda platformdriftrateinexcessof0.7deg/hr.AdditionaltransientIMU1redundant-rateBITEmessagesweregeneratedafterthe initialoccurrence,andthemessageswereinhibitedbythecrewtopreventfurtheralarms.Initially,thetransientconditiondidnotsignificantlydegradethe IMU1performance.However,theconditiongraduallyworsenedandIMU2wascommandedfromstandbytooperatemodeat201:14:29G.m.t.(11:21:46MET)toaddredundancy.Onflightday13,the IMUplatformexperienceda 0.08degreeshiftduringan eventwhichlasted10minutes,andthe IMUwasdeclaredfailedforentryplanningpurposes.At 204:03:34G.m.t.(14:10:51MET),IMU 1wasmodedto standbyfor13minutesandbacktooperateinanattemptto recovernominaloperationbyresettingthe IMUinternalprocessor.The IMUcontinuedoperatingwiththeBITEindicationoccurringrandomly,butnoBITIEindicationsresultingina significantperformancedegradationwereobservedafterthe reset.The IMUwasperiodicallyrealignedtoassurethananyplatformmisalignmentscausedbydrifttransientsdidnotexceedthe redundancymanagement(RM)threshold.IMU1performancewasdeemedacceptableforentry,andtheIMUwasallowedtoremainunderRMcontrolduringentry. IMU1 performednominallythroughoutentry,andnoabnormaloperationwasnoteduntil3 minutespriortothenormalIMU-1shutdownduringthepostlandingoperations.Thefirston-orbitShuttletestoftheSecondTrackingandDataRelaySatellite(TDRS)GroundTerminal(STGT)wasperformedonorbit183. TheS-bandsuccessfully ;"'_,providedaudiocommunications,commanduplink,andtelemetrydownlink.TheKu-bandprovideddownlinkvideofrommultiplecamerasand2megabitreal-timedataonchannel2. ThesecondsuccessfulSTGTtestwasperformedonorbit211. SomeproblemswereencounteredinlockingontheKu-bandchannel2 signal,butthe lock-onwascompleted.


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('-"_ 203:13:32:42.2G.m.t.(13:20:04:44.1MET)andwas30.4 secondsindurationwitha AVof49.1ft/sec.ThetwoOMSmaneuverswereperformedtoobtainanadditionalend-of-mission(EOM)+ 2 daylandingopportunityat EdwardsAirForceBase.This. opportunitywaslostwhentheplannedlaunchtimewasmovedup20minutestoextendthe launchwindow.Alldeorbitpreparationsforthelandingopportunitiesontheseconddaywerecompleted,andthepayloadbaydoorswereclosedat 204:07:10:05G.m.t.(14:14:27:05MET). Thedeorbitmaneuverwasinitiatedat204:09:40:38.3G.m.t.(14:16:57:38.3MET),andwas152.8secondsindurationwitha _V of255.3ft/sec.MainlandinggeartouchdownoccurredattheSLFonconcreterunway33 at204:10:38:00G.m.t.(14:17:55:00MET)onJuly23, 1994. TheOrbiterdragchutewasdeployedsatisfactorilyat204:10:38:10G.m.t.,andnoselandinggeartouchdownoccurred8 secondsafterdragchutedeploymentwasinitiated.Thedragchutewasjettisonedat204:10:38:42.6G.m.t.withwheelsstopoccurringat204:10:39:08G.m.t.Therolloutwasnormalinallrespects.Theflightdurationwas14days17hours55minutes00seconds,whichistherecord-lengthflightfortheSpaceShuttleProgram.

i


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PAYLOADS

ThesecondIntemationalMicrogravityLaboratorySpacelabmissionbroughttogetherover200 internationalscientistsfrom13 countriesandsixspaceagencieswhodevelopedover80 investigationsforthe IML-2mission.TheagenciesrepresentedweretheEuropeanSpaceAgency(ESA),theFrenchSpaceAgency(CNES),theGermanSpaceAgency(DARA),theCanadianSpaceAgency(CSA),theNationalSpaceDevelopmentAgencyofJapan(NASDA),andtheNationalAeronauticsandSpaceAdministration(NASA).TheareasofscienceinwhichinvestigationswereperformedwereMaterialScience,FluidScience,MicrogravityEnvironmentandCountermeasure,Bioprocessing,SpaceBiology,HumanPhysiology,andRadiationBiology.TheSpacelab,containing19separateexperimentfacilities,wasactivatedat189:21:04G.m.t.(00:04:21MET). FacilitiesflownforthefirsttimeincludedtheReal-TimeRadiationMonitoringDevice(RRMD);thePerformanceAssessmentWorkstation(PAWS);theVibrationIsolationBoxExperimentStation(VIBES);theElectromagneticContainerlessProcessingFacility(TEMPUS);theBubble,Drop,andParticleUnit(BDPU);theQuasiSteadyAccelerationMeasurement;andtheLinearCompressorEnhancedOrbiterRefrigerator/Freezer(LCEOR/F).Carbondioxideconcentration-levelrequirementsweresupportedremarkablywellby F_augmentingtheregenerativecarbondioxideremovalsystem(RCRS)withlithiumhydroxide(LiOH)canisterswithrestricters.LiOHcanisterchangesweremadeat15-hourintervals,andthismaintainedtheaveragepartialpressureof carbondioxideat2.3mmHgwithpeaksto3.0mmHg.


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LIFESCIENCESAquatic Animal Experiment Unit

TheAAEU,whichwasdevelopedbytheNationalSpaceDevelopmentAgencyofJapan,providedanenvironmentforstudiesof livefishandsmallamphibiansundermicrogravityconditions.FortheSTS-65mission,fourexperimentswereconductedusingtheAAEU. Thesewere:a. MechanismofVestibularAdaptationof FishunderMicrogravity;b. Otoconia:EarlyDevelopmentofa Gravity-ReceptorOrganinMicrogravity;c. FertilizationandEmbryonicDevelopmentofJapaneseNewtsinSpace;andd. MatingBehaviorofFish(Medaka)andDevelopmentofTheirEggsinSpace.

Extensivedatawerecollectedontheanimalgravitysensorresponsetomicrogravity,spawningbehaviorofMedaka(guppies),andembryodevelopmentofbothground-andspace-fertilizedeggs.Thecrewreportedthatat least25 Medakafryand32 newteggshadhatched.Twonewtsdiedduringtheflight;however,successfulIFMprocedureswereperformedtoremovethemtopreventcontaminationofthebabynewtsandeggsandpreservethemforpostflightanalysis.It isspeculatedthatstresswasa leadingfactorforthecauseofF_ death;however,postflightanalysiswillbeconductedtodeterminetheactualcause.The aquarium andfishpackagesoperatednominallyforthe majorityofthemission.Thecrewmanuallycalleddownhousekeepingdata untilthe HRM channel7 datathroughputproblemwascorrectedbyan IFMprocedure.A subsequentIFMproceduretoovercomea lowwaterpressureanomalywas successfullyexecutedbyinjecting


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e. CellMicroenvironmentandMembraneSignalTransductioninMicrogravity ;"_,(Signal);f. EffectofStirringandMixingina BioreactorExperimentinMicrogravity(Bioraactor);g. MolecularBiologicalInvestigationsofAnimalMulti-CellAggregatesReconstitutedunderMicrogravity(Aggregate);h. RegulationofCellGrowthandDifferentiationbyMicrogravity:RetinoicAcid-InducedCellDifferentiation(Mouse)i. SeaUrchinLarva,a PotentialModelforStudyingBiomineralizationandDemineralizationProcessesinSpace(Urchin);j. InvestigationoftheMechanismsInvolvedintheEffectsofSpaceMicrogravityonDrosophilaDevelopment,BehaviorandAging(Drosophila);k. TheRoleofGravityintheEstablishmentofEmbryonicAxesinAmphibianEmbryo(Eggs);I. EffectofMicrogravityonLentilMorphogenesis(Lentil);m. RootOrientation,GrowthRegulation,Adaptation,andAgravitropicBehaviorofGeneticallyTransformedRoots(Transform);n. PlantGrowthandRandomWalk(Random);o. EfficiencyofRadiationRepaironProkaryotes(Repair);andp. RadiationRepairKineticsinEukaryotes(Kinetics).

AllexperimentinvestigationsweresuccessfulincludingtheDrosophilainvestigationthatstudiedthe behaviorandagingprocessof fruitflies.ThefailureofM1centrifuge .,_usedforincubatorCwasovercomebyinstallingamakeshiftdrivebeltoverthedrumsof thiscentrifugeandthefunctionalM2centrifuge.Otherfacilityhardwareincludingagloveboxanda coolerperformednominally.However,duringtheBiorackpower-up,theBiorackpowerblowerLEDdidnotlight,buttheblowerranas longasthedoorwasclosed.Powertothegloveboxwascycledandnormaloperationswererestored.


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TheLowerBodyNegativePressure(LBNP)experimentevaluatedtheeffectivenessofa treatmentdesignedto counteractorthostaticintolerance,thelightheadednesssomemembersofa crewmayexperiencewhenreturningfroma 13-to 16-daymission.The LBNPoperations,whichwerenominal,continuedto testthehypothesisthattheeffectsof fluidlossduetotheheadwardshiftof bodyfluidsinspaceflightcanbecounteredbyingestionofa largequantityofsalinesolutioninconjunctionwiththeapplicationofnegativepressureto thelowerbody.TheMicrobialAirSampler(MAS)isa hand-held,batteryoperatedairsampler,whichcollectssamplesof airinpredeterminedplacesatpredeterminedtimes.ParticlesenteringtheMASaretrappedonplasticstripscontainingagar.Thesestripswerereplacedaftertwominutesofsamplingandstoredforpostflightanalysis.TheMASfailedduringthefirstsamplingoperation,andthefirstdata-takewaslost.An IFMprocedurewasperformedinwhichthesamplestripwasreplacedandnormaloperationwasrestored.However,onlyfourofthefiveplanneddata-takeswerecompletedsatisfactorilybecauseofthisproblem.TheAmericanEchocardiographResearchImagingSystem(AERIS)failedto recorddataduringonesession.AnIFMprocedurewasperformedandnominaloperationwasrestoredforthe remainderofthemission.

LinearCompressorEnhancedOrbiterRefriqeratorlFreezer( TheLCEOR/Fencounteredproblemsearlyinthemission;however,thestartingandstoppingtemperaturesforthecompressorwereeachlowered8 CandtheLCEOR/F

operatednominallywitha dutycycleof55 to60percentfortheremainderof themission.Experimentoperations,includinga defrostprocedureandloadingofphase-changematerials(PCMs)andcrewbeverages,werecompletedsuccessfully.Although


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e. GravireactioninCharaRhizoidsinMicrogravity(Chara)(Lostbecauseof F-_,over-temperatureanomaly);f. GravisensitivityofCressRoots(Cress);g, LymphocyteMovementsandInteractions(Motion);andh. ConvectionStabilityof a PlanarSolidificationFront(Moni).

AllexperimentsamplesexcepttheCharasamplewerecompletedasplanned.Anover-temperatureanomalyinwhichtheexperimentmoduleintemaltemperaturerosefrom21 Cto58 Cwasnotedearlyintheflight.Thisproblemwasseenpreviouslyduringpreflighttestingandwascausedbyastickingrelay,butcouldnotbecorrectedbecauseof the lackoftimebeforeflight.Microqravity Effects onStandardizedCoqnitivePerformanceMeasures

The MicrogravityEffectsonStandardizedCognitivePerformanceMeasuresexperiment,whichconsistedofsixcomputerizedcognitiveperformancetestscalledPAWS,willhelpdeterminetheastronauts'mentalabilityto performoperationaltasksinspace.TheCommander,PilotandMissionSpecialist2 successfullycompletedallexperimentobjectivestomeasurehumanworkloadandperformanceinzerogravity.

AppliedResearchonSeparationMethodsUsinqSpaceElectrophoresis (_,TheRAMSESexperimentusesa continuous-flowelectrophoresisunittopurifybiologicalsamples.Anadjustableelectricfieldwasappliedacrosstheflow,causingthedifferentlychargedcomponentstodivergeintoa widebeamconsistingofseparatestreamsofmolecules,whichpassthrough40 outletsintocollectiontubes.These


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F_ scienceteamwasstillabletocompletefiveof sevenflightobjectives(FOs),andthemajorityof thesixthFO. Approximately80to90percentof thetotalscienceobjectiveswerecompleted.

Real-TimeRadiationMonitorinqDeviceTheRRMDmeasuredthehigh-energycosmicradiationintheSpacelabwhileon-orbit,andinturn,transmittedthesedatatothePayloadOperationsControlCenteratMarshallSpaceFlightCenter(MSFC). Inaddition,thedevicecontainedbacteriawithhighradiationsensitivity.Thesecellswereanalyzedduringpostflightoperationstodetermineradiationdamageaswellastheircapabilityto recoverandrepairthemselvesaftera cosmicrayimpact.Radiationmeasurementactivitieswerenominal.However,somedata-takeopportunitieswere lostbecauseof theHRMchanneldatathroughputproblemexperiencedearlyinthemission.ThisanomalycausedatotallossofdatafromtheRRMDfortheseopportunities.Thecrewperformedan IFMprocedureonflightday3thatresultedina solidlock-onofthedata. Also,theexperimentwasinadvertentlypoweredoff. ThecrewfoundthatthepowercircuitbreakeronpanelL4Wwasopenandsubsequentlyclosedit.

SpinalChanqesinMicroqravityF_TheSpinalChangesin Microgravity(SCM)experimentwasdevelopedbecausetwooutof everythreepersonswhogointospaceexperiencebackpain.Asa result,thelengtheningof thespinalcolumnwasstudiedtodetermineif thatconditionisthe causeofthebackpain.


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MATERIALSSCIENCEAdvanced Protein Crystallization Facility

TheAdvancedProteinCrystallizationFacility(APCF)providedanenvironmentforgrowinga varietyof proteincrystalsusingthreedifferentmethods.Thesewere:a. vapordiffusion;b. liquid-liquiddiffusion;andc. dialysis.

Theassociatedcrystalgrowthfacilitiesoperatednominallyduringthemission.,Bubble, Drop and Particle Unit

TheBDPUwasa facilitydevelopedtostudyfluidbehaviorsandinteractionssuchasbubblegrowth,evaporation,condensation,andthermocapillaryflows.Thecrewinterchangedexperimenttestcontainerswithdedicatedfluidcells.TheexperimentsthatusedtheBDPUareasfollows:

a. BubbleMigration,CoalescenceandInteractionwithMeltingandSolidificationFronts; F--_b. ThermocapillaryMigrationandInteractionsofBubblesandDrops;c. BubbleBehaviorUnderLowGravity';d. ThermocapillaryInstabilityina Three-LayerSystem;e. Nucleation,BubbleGrowth,InterfacialMicro-Layer,EvaporationandCondensationKinetics;and


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,"_ c. DensityEquilibrationTimeScale;andd. HeatTransportandDensityFluctuationsinaCriticalField. The reflightofthisfacilityreconfirmedpreviousfindingsfromthe IML-1mission.Animprovedthermostatwasinstalledsincethe IML-1mission,andthisenabledthefacilitytoperformwithoutinterruptionandgathersignificantsciencedata.

FreeFlowElectrophoresisUnitTheFFEUwasusedto studywhetherspace-basedelectrophoresiswillimprovethepurityof certainbiologicalmaterialswhicharenormallydifficulttoseparateonEarth. Anumberof differenttypesofsampleswereflownfortestingandisas follows:

a. GravitationalRoleinElectrophoreticSeparationsofPituitaryCellsandGranules;b. SeparationofChromosomeDNAofa Nematode,C.e/egans,byElectrophoresis;andc. ExperimentsSeparatingtheCultureSolutionofAnimalCellsinHighConcentrationunderMicrogravity.

Afterovercomingactivationproblems,allFFEUscienceinvestigationswereattempted.Althoughdegradationof onesampleoccurredthatpreventeda pituitaryseparationforf- oneflightobjective,themajorityofsciencewassuccessfullycompleted.Thesuccessis dueto theexcellentreplanningof theexperimenttimelinebythe flightcontrolteam.LarqeIsothermalFurnace

TheLargeIsothermalFumace(LIF)wasusedtoheatlargematerialssamplesina


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0.02Hertz. Datawererecordedthroughoutthemissiononopticaldisks,whichwere -_"_,retumedforpostflightevaluation.Thehardware,whichconsistedoffourrotatingsensors,threestaticsensorsandan --opticalrecorder,successfullyrecordedlow-frequencyaccelerationsintheSpacelab.Severalinstancesofproblemswiththeopticalrecorderwerecorrectedbyeitherchangingtheopticaldiskorperforminga self-test.

Space Acceleration Measurement SvstemTheSpaceAccelerationMeasurementSystem(SAMS)instrumentmonitoredandrecordedhigher-frequencyonboardaccelerationsandvibrationsthatwereexperiencedintheSpacelabmoduleduringflight.Datawererecordedthroughoutthemissiononopticaldisks,whichwerereturnedforpostflightevaluation.AccelerometerheadsinthreeSpacelablocationsnominallyrecordedaccelerationscausedbyOrbitermaneuversandcrewmotion.A problemwithdiskdrive2 wascorrectedbyreseatingthediskinthedrive.

Electromaqnetic Containerless Processinq FacilityTheTEMPUS,a levitationmeltingfacility,providedcontainerlessprocessingofmetallicsamplesinanultracleanmicrogravityenvironment.Thefacilityusedanelectriccurrent F'_flowingthroughcoilsofcoppertubingtoproducemagneticfields,whichcreatedanareaofminimumfieldstrengthinwhichthesamplewouldlevitate.Twenty-twometallicsampleswereaccommodatedduringthemission.A numberofexperimentssharedthisfacilityandthesewere:


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VibrationIsolationBoxExperimentStation TheVIBESinvestigatedtheeffectsofso-called"g-jitter"disturbancescausedbycrewmovementandexperimentequipmentoperationsinspacelaboratoriessuchasSpacelab.

Operationswerenominalforthisexperimentcomposedofspecialmaterialsdesignedtomitigatetheeffectsofaccelerations.COMMERCIALPROTEINCRYSTALGROWTH

STS-65wasthefifthflightoftheCPCGexperiment.Thissecondarypayloadusedthecommercialrefrigerator/incubatormodule(CRIM)intheOrbitermiddeck.Atotalof60samplesfocusingonsixdifferentproteinsinvariousformulationswereflownforthispayload.TheCPCGCRIMexperienceda thermalelectricdevice(TED)signaldropoutat194:08:43G.m.t.(04:16:00MET)thatresultedin lostthermalperformance.Thetemperatureoftheunitrosetoapproximately13Covera 9.5-hourperiod.DiagnosticdatawerecheckedbythecrewwhoverifiedthattheTEDwasdroppinginandout. Toachievea stableenvironment,theCRIMcommandtemperaturewaschangedto 13C,f andthetemperatureoftheunitremainedat 13C__.1.8 C fortheremainderofthemission.ImpactofthetemperatureinstabilitytotheproteinsamplescanonlybeassessedduringpostflightlaboratoryworkatthePrincipalInvestigators'laboratory.Thepostflightassessmentindicatedthatcrystalsweregrowninfiveof thesixproteinsamples.However,onlythreeofthefiveproteincrystalsyieldedx-raydiffraction-gradecrystals,andonlytwoof thesixproteinmaterialsyieldedgoodcrystals.


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aerodynamiccharacteristicsatorbitalaltitudes.Theinitialassessmentofthedata ._"_.dumpedatMSFC indicatednominalinstrumentperformancethroughouttheflight.SHU'I-rLEAMATEURRADIOEXPERIMENT

TheSAREXproject,whichhasflownon13previousShuttlemissions,wasdesignedtoencouragepublicparticipationinthe SpaceProgramandsupporttheconductofeducationalinitiatives.Thisobjectiveisbeingaccomplishedby demonstratingeffectivecommunicationsbetweenthe Shuttleandlow-costgroundstationsusingamateurradiovoiceanddigitaltechniques.All 13scheduledschoolsweresuccessfullycontactedbytheSpaceShuttleColumbiaastronauts.Theseschoolsincludedtwo foreignschools:TatebayashiChildren'sScienceExploratoriuminJapan;anda Germanschool,FranhoferRealschuleinIngolstadt,Germany.Inadditionto thescheduledcontacts,one unscheduledcontactwasalsoarrangedwithGeneralThomasStaffordat theAerospaceAmericaAnnualAirshowin OklahomaCity,OK. CommanderCabanacommunicatedthroughbridgestationsinHawaiiandCaliforniaandwas heardby approximately150,000people.ThepacketoperationaboardtheColumbiathat includeda portionof thecommemorativeApollo11periodperformednominallywithapproximately3,000 ,"_,connectionstotheShuttlepacketradio.

MILITARYAPPLICATIONSOFSHIPTRACKSThe MAST experimentwas sponsored by the Office of Naval Research, and the


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_/-" VEHICLEPERFORMANCE

SOLIDROCKETBOOSTERSAllSRBsubsystemsperformedasexpected.TheSRBprelaunchactivitieswereallnormal,andnoLaunchCommitCriteria(LCC)orOperationalMaintenanceRequirementsandSpecificationDocument(OMRSD)violationswereidentified.Forthisflight,thelow-pressureheatedgroundpurgeintheSRBaftskirtwasnotrequiredtomaintainthecase/nozzlejointtemperatureswithintherequiredLCCranges.ThepurgewasactivatedatT-26minutesforthehigh-flowrateinertingof theSRBaftskirt.Thecalculatedflexiblebearingmeanbulktemperaturewas78 F.AnalysisoftheSRBdataindicatesnominalperformanceofallsubsystems.Twonewmaximumsforexperiencebasesweresetforthethrustvectorcontrol(TVC)system.Onewasestablishedonthe left-handtiltfuelsupplymodule(FSM)pressuredifferencebetweenAPUstartandcutoff.Thesecondnewexperiencebasewastheright-handtiltactuatormaximumrateduringseparationnull. Dataconcerningbothofthesenewexperiencebaseshavebeenevaluated,andnoanomalousoperationwasfound.BothSRB'sweresuccessfullyseparatedfromtheETatT+123.48seconds,andreportsfromthe recoveryarea,whichwerebasedonvisualsightings,indicatethattheSRB(F_ decelerationsubsystemsperformedasdesigned.BothSRBsweresightedduringdescentandwererecoveredandbroughttoCapeCanaveralforretumtoKSCwheredisassemblyandrefurbishmentactivitieswereinitiated.Duringthedisassemblyprocess,twoanomalousconditionswereidentifiedandtheywere:


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Thefieldjointheatersoperatedfor11hours36minutesduringtheprelaunchtime f"_framewiththeheaterson17percentofthetimeduringtheLCCtimeframe. Theigniterjointheatersoperatedfor23 hours11minuteswiththeheaterspoweredup5 hoursearlierthanexpected.Powerwasappliedtotheigniterheatingelements29 percentofthetime.DataindicatethattheflightperformanceofbothRSRMswaswellwithintheallowableperformanceenvelopesandwas typicalof theperformanceobservedonpreviousflights. TheRSRMpropellantmeanbulktemperature(PMBT)was81 Fat liftoff. Thefollowingtableshowstheperformancedataof the RSRMs.

RSRMPROPULSIONPERFORMANCEParameter Leftmotor,81F Rightmotor,81 FPredicted Actual Predicted I ActualImpulsegates1-20,106Ibf-sec 66.16 66.34 66.17 66.431-60,106 Ibf-sec 176.13 176.04 176.16 176.42

I-AT_106 Ibf-sec 296.75 296.06 297.02 296.30VacuumIsp_Ibf-sec/Ibm 268.6 268.0 268.6 268.0Bumrate,in/sec@60 F 0.3679 0.3687 0.3676 0.3694at625 psiaBumrate,in/sec@81 F 0.3735 0.3743 0.3732 0.3750at625 psia Y-'_Eventtimes,secondsa 0.232 N/A 0.232 N/AIgnitioninterval 108.8 109.1 108.9 108.5Webtimeb 118.5 118.6 118.3 117.6Separationcue,50 psia 120.6 120.7 120.5 119.8Actiontimeb 123.5 123.5 123.5 122.5


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F"_ EXTERNALTANKTheET loadingandflightperformancewereexcellent,andallflightobjectiveswere" satisfied.NoET in-flightanomalieswereidentifiedfromthetelemetryorphotographicdata.AllET electricalandinstrumentationequipmentperformedsatisfactorily.NoLCCorOMRSDviolationswereidentified.NoevidenceofunacceptableacreageiceformationwasnotedduringthepropellantloadingforSTS-65. Allobservedicingconditionswerewithinthehistoricalconditionsasreferencedinthe Ice/DebrisInspectionCriteriaDocument(NSTS-08303).Theseacceptableconditionsincludeda recurringthermalprotectionsystem(TPS)defectofasinglecrackintheTPSwherethefoambridgesbetweentheverticalstrutcabletrayandfittingfairing,andthisconditioniscausedbyjointrotationatthatpoint.A reviewof theDevelopmentTestObjective(DTO)312 post-separation35mmphotographstakenwitha 300mmlenswitha 2Xextender,andthephotographsfromtheumbilical-well-mounted35mmandtwo16mmcamerasshowedthefollowing:

a. Twodivots,approximately6 inchesindiameterwithexposedsubstrate,werelocatedintheLH2tointertanksplicejustoutboardofthecabletrayprotuberanceairload(PAL)ramp.(F_ b. A shallowdivot,approximately6 inchesindiameter,waslocatedintheLH2CPRfoamjustaftofthe intertanksplicebetweenthe+YbipodattachmentandtheLO2feedlinesupportbracket.

c. Severalsmall,1-to2-inchdiameter,"popcorndivots"werelocatedontheintertankstringersjustforwardofthebipods.


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SPACESHU'I'I'LEMAINENGINES F"_AllSSMEsperformedsatisfactorilythroughoutthecountdown.Dataweretypicalofprelaunchparametersobservedonpreviousflights.Engine"Ready"wasachievedatthepropertime;allLCCweremet;andenginestartandthrustbuildupwerenormal.Engineperformanceduringmainstageandshutdownwasnominalandaspredictedwithcutofftimesof 516.95,517.07,and517.20seconds(referencedtotheenginestartcommand)forSSMEs1,2, and3, respectively.TheengineIspwasratedat452.1secondsbasedontrajectorydata. BlockII controllerandsoftwareperformancewassatisfactory.MECOoccurred510.63secondsafterliftoff.Noin-flightanomalieswereidentifiedinthedatareview,norwereanysignificantproblemsnoted;however,thefollowingobservationsweremadeduringthe review.

a. TheSSME2 highpressureoxidizerturbopump(HPOTP)intermediatesealpressureshiftedupwardatenginestartplus270seconds.Thisshiftwaswithintheexperiencebaseandwassimilartothegreen-runperformanceofthispump.b. TheSSME1 highpressurefuelturbine(HPFT)channelBdischargetemperatureoscillatedduringthethrustbucket.ThisconditionwaspreviouslyseenonSSMEno.2019duringSTS-26andisattributedtoturbinecoolantflowredistribution.c. TheSSME2 POGOpressurepurgeandancillarymonitorlowerlimit(0 psia)wasviolatedafterengineshutdown,anda failureidentification(FID)wasposted.The F"_lowerlimitrequirementhasbeenineffectsincethefirstflightofBlockII software(STS-49).ThisconditionwasnotseenbeforeSTS-65sincethepropellantvacuum

inertwasalwaysperformedaftertheenginecontrollerswerepowereddown.Withthenewvehiclesoftware,OI-23,propellantvacuuminertisautomatedandmayoccurwhenthecontrollersarepowered.Sincethislimitisnotrequired,itwillbeeliminatedfor


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F'_ ORBITERSUBSYSTEMSMainPropulsionSystem

TheoverallperformanceoftheMPSwasnominalwithnohardwarein-flightanomaliesidentified.STS-65wasthefirstflightoftheMPSdumpandvacuuminertingproceduresdevelopedfortheOI-23software,andperformanceduringthedumpandentryrepressurizationwasdifferentthanexpected.Liquidhydrogenloadingoperationswerenormalthroughall phasesoftheactivity.Theanalysisof loadingsystemdatashowthattheLH2loadattheendofreplenishwas231,791Ibm.Comparedtothepredictedloadof231,853Ibm,theloadingaccuracywas-0.03percent,whichiswellwithintherequiredloadingaccuracyof__.0.37percent.LiquidoxygenloadingcontinuedsatisfactorilyuntilaboutnineminutesafterfastfillstartwhenanoverspeedindicationwasreceivedfrompumpA127andaLO2revertoccurred.Duringtherevert,pumpA126wasbroughtonlineandloadingcontinued.Theanalysisof loadingsystemdatashowtheLO2loadwas1,387,731Ibm.Comparedtothepredictedloadof 1,387,828Ibm,the loadingaccuracywas-0.01percent,whichiswellwithintherequiredloadingaccuracyof__.0.43percent.Real-timeanalysisofhydrogenleakdetectorandhazardousgasdetectionsystemdataF-_=-...r showednoviolationsofthehazardousgasconcentrationlimits.ThemaximumhydrogenconcentrationlevelintheOrbiteraftcompartmentwas95ppm(corrected),whichcomparesveryfavorablywithpreviousdataforthisvehicle.Leakdetector56and57 indicatedlowsamplingrates,possiblyduetoa lineblockage.However,leakdetector57wasusedastheprimarydetectorbecauseof thehighersamplingrate. TheHydrogenUmbilicalMassSpectrometer(HUMS)servedasthesecondarydetector.


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dataevaluation.Consequently,SSME3FCVperformancewasnominal,anda FileIX ,"-'_.changeis beingmadeto changetheallowabledifferentialpressurebandfor SSME3.The LH2manifoldpressureunexpectedlyincreasedto a maximumpressureof17 psiafollowingthevacuuminertingprocedure(FlightProblemSTS-65-V-08). An initialpressureriseratewasevidentas the solidhydrogenchangedtoa liquid. The pressureriserate increasedas liquidhydrogenstartedtoboil-offtoa gaseousstate. A thirdchangeinthe rise ratecorrespondedto theOMS-2 firingwhichcausedsolidandliquidhydrogento come incontactwiththe '_Narm"feedlinewallsand rapidlyflashoffto gas.Postflightanalysisof the MPS dump/vacuuminert performance indicatedthat this firstuse of the new OI-23 software automated dump sequence resulted in a lower amount ofresidual hydrogen after the dump (estimate of 2 Ib,which is lowest in flight history).However, preflight predictionsfrom the MPS PropellantDumpmodel has indicatedthatresiduals after the dump should have been less than 1 Ibm (about 0.3 Ibm). Since theresiduals were greater than the predicted value, the 5-minute coast time between dumpand vacuum inert was insufficientto allow all of the solid hydrogen to sublimate to gas.This resulted in the hydrogen residual after the vacuum inerting that caused theobserved manifold pressure increase.Theevaluationof thedumpperformancealsoindicatedthatalltheheliumthatwasbudgetedtobe introducedintotheLH2systemviathereturn-to-launch-site(RTLS)repressurizationvalvesdidnotenterthemanifoldasapproximately50 percentwasblownoutofthemanifoldreliefvalve.Anevaluationisbeingmadetodeterminethe _correctiveactionsthatwouldeliminatethe residuals.Oncethemanifoldpressurereacheditspeakvalueof 17psia,itquicklybegandecayingandreachedambientpressureinapproximately90minutes.Thisobservedleakratecorrespondedtoa systemleakageontheorderof7,000scim.Thisleakrate


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manifoldrepressurization.Asa result,theheliumpressurebeingprovidedfortheblowdownremainedapproximately100psihigherthantheaveragesingle-regulatorpressure,thusprovidinga greatermassflowdudngthepurge.Analysisindicatesthat- approximately3 to4 IbmmoreheliumconsumptionshouldbeexpectedwhenusingtheOI-23software.Adding4 IbmtothenominalOV-102flowof55.7Ibmresultsinaconsumptionveryclosetothe59.37 IbmthatwasusedduringSTS-65.Asa resultof theSTS-65missionfindings,theFileIX requirementwillbemodifiedtospecifytheexpectedconsumptionforeachvehiclewiththeOI-23entryconfigurationincludingthe3-sigmavaluesthatarecalculatedwithallthedataavailablesinceSTS-26.

Reaction Control SubsystemTheperformanceoftheRCSwassatisfactory.RCSpropellantconsumptionforthemissiontotaled5,036.5Ibm.TheRCSwasnotinterconnectedtotheOMSduringthismission.At 196:11:58G.m.t.(06:19:15MET),thecrewreportedthatwhilereconfiguringtheRCSfromtheAtotheBheliumregulators,the leftRCSBeventindicator(talkback)aswellastheAeventindicatorshowedbarberpolewhentheBswitchwastakenfromCLOSEtoGPC. Theprocedurewasrepeatedlaterintheflightandnoanomalousf- indicationswerenotedvisuallyor inthedata. Duringpostflightcrewdebriefings,thetalkbackwas reportedtobepresentonlymomentarilyandonlyaftermovingtheBswitchfromGPCtoOPEN. Thisconditionisconsistentwithpreviousoccurrencesofvalvebouncecausedbya pneumatichammereffect.At 199:09:14:20G.m.t.(09:16:31:20MET),vernierthrusterR5Dwasfailedoffbythe


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OrbitalManeuverinqSubsystem F'_TheOMSperformedverysatisfactorilyduringthefourfirings,and13,694.9Ibmofpropellantswereconsumedduringthe355.78secondsoffiringoneachengine.Datashowedthatalloxidizerprobesforthequantitygaugingsystemoperatedsatisfactorily,butonlytheleftaft fuelprobewasoperatingproperly.ThefollowingtableprovidesdataconcerningtheOMSfirings.

OMS FIRINGSFiring AV,

OMS firing Engine Time,G.m.t./MET duration, ft/secsecondsOMS-2 Both 189:17:22:55:2G.m.t. 141.3 221.8000:00:39:55.2METOMS-3 Both 203:12:47:44.1G.m.t. 32.1 51.0013:20:04:44.1METOMS-4 Both 203:13:32:42.2G.m.t. 30.4 49.1013:20:49:42.2METDeorbit Both 204:09:40:38.3G.m.t. 152.8 255.3014:16:57:38.3META biaswasnotedinthe rightOMSaftfuelquantitygageduringthedeorbitmaneuver.The quantitygagewasreadingapproximately15percenthigherthanexpected.This F'_,conditiondidnotimpactthemission.

Power Reactant Storaqe and Distribution SubsystemTheSTS-65missionwasthefourthflightoftheExtendedDurationOrbiter(EDO)


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,f_ approximately48 hours.Theloadsonthefuelcellsforthismissionwerehigherthanonthepreviousmission,andthiscontributedtothemorerapidperformancedecay. Duringthe postlandinginertpurgingof thefuelcells,theoxygenmanifoldpressuredecayedatanunacceptablerate.Excessiveleakagewasmeasuredfromtheoxygenpurgeport. Theleakwasisolatedtofuelcell3,andasteady100-sccmleakratewasmeasuredwithanincreaseto400to500sccmleakagerateevery8 to11seconds.Asa result,the fuelcell(S/N122)willbereplacedpriorto thenextflight.

AlsoduringpostlandingoperationsatKSC,thefuelcell2 coolantpressureincreasedforanunknownreasonfrom65.3 psiato73.2psia.Thefuelcellwasdepressurizedandthenrepressurized,andagainthesamesignaturewasobserved.Thefuelcellisdesignedtoventwhenthecoolantpressurereaches70 psia. ThisisthefirsttimethisbehaviorhasbeenobservedduringtheSpaceShuttleProgramandthebehaviorisunexplained.Asa result,fuelcell2 (S/N121)willalsobereplaced.

AuxiliaryPowerUnitSubsystemTheAPUsubsystemperformednominallywithnoanomaliesnoted.TheAPUswereshutdownafterlandingintheAPU2,APU1,andAPU3orderto fulfilltherequirementsofDTO414. APUfuelconsumptionandruntimeareshowninthefollowingtable.Flightphase APU1 (S/N409) APU2 (S/N308) APU3 (S/N408)Time, Fuel Time, Fuel Time, Fuel

min:secconsumption,min:secconsumption,i min:secconsumption,Ib Ib IbAscent 20:58 48 20:45 53 21:05 50


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review.Oneitemofinterestfromthismissionwasthatthetotalnumberofcirculation _"_pumprunswasthehighestofanymission(279)intheSpaceShuttleProgram.Electrical Power Distribution and Control Subsystem

Theelectricalpowerdistributionandcontrol(EPDC)subsystemperformednominallythroughoutthemissionwithnoproblemsoranomaliesnoted.Environmental Control and Life Support Subsystem

Theactivethermalcontrolsubsystem(ATCS)performednominallywithnoproblemsoranomaliesidentified.TheflowproportioningvalvesonFreoncoolantloops1 and2wereswitchedtothepayloadpositionat 189:19:23G.m.t.(00:02:40MET)and190:16:08G.m.t.(00:23:25MET),respectively,tosupportSpacelabcoolingrequirements.Bothloopswereretumedtothe interchangerpositionat203:03:46G.m.t (13:11:03MET)afterSpacelabdeactivation.The radiatorcold-soakprovidedcoolingduringentrythroughlandingplus11minuteswhenammoniaboilersystemBwasactivatedusingthesecondaryBcontroller.SystemBoperatedfor40minutesandwasdepletedentirely.Groundcoolingwasestablishedat204:11:33G.m.t.,55minutesafterlanding.WaterwasmanagedthroughtheuseoftheFESforsupplywaterbecauseofa supply- ;"-'_waterdump-nozzle-icinganomalydiscussedonthefollowingpage.Threesupplywaterdumpswereperformedat anaveragerateof 1.52percent/minute(2.5Ib/minute).Thesupplywaterdumplinetemperaturewasmaintainedbetween74and112Fthroughoutthemissionwiththeoperationof thelineheater.


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('_ Wastewaterwasgatheredatapproximatelythepredictedrate.Thewastewaterdumplinetemperaturewasmaintainedbetween53 and81 Fthroughoutthemission.Threewastewaterdumpswereperformed.Thefirstdumphadanaverageflowrateof 1.95percent/minute(3.2Ib/minute).Thesecondwastewaterdumpwasinitiatedat198:06:33G.m.t.(08:13:50MET)andwasperformedinthreesegments.Duringthesecondsegment,whichdumpedthewastetankfrom42to26percentovera10.5-minuteperiod,thedumpratedegraded.Theratewas2.03pereent/minuteduringthefirst3 minutesanddegradedto 1.11percent/minutebytheendofthissegmentofthedump.Thewastetankpressureincreasedslightlyduringthissegment,whichisindicativeof blockage.Therewasnoevidenceof iceonthedumpnozzle.Duringthefirstandthirddumpsegments,theratewasanominal1.8to1.9percent/minute.At202:05:39G.m.t.(12:12:56MET),thethirdwastewaterdumpwasinitiated.Thedumpwasperformedinsevensegments,eachlasting5to7minutesbeforetheminimumtemperaturelimitswerereached,andthedumpratesweredegradedtothe1.2to1.4Ib/hrrate(FlightProblemSTS-65-V-06).Attheendof thethirdwastewaterdump,enoughullagewasavailableto reachend-of-missionplus39 hours.TheEDOwastecollectionsystem(WCS)performedadequately;however,threeanomalieswereidentifiedandthesearediscussedinthefollowingparagraphs.TheWCSwasremovedpostflightandsentto thevendorforcleaningandrefurbishment.

F , Atapproximately190:13:09:45G.m.t.(00:20:26:45MET),theEDOWCScommodefaultlightindicateda problemduringthethirdcompactioncycle(FlightProblemSTS-65-V-03A).Dataindicatedthatthecompactorpistonhadstoppedapproximatelyat thebottomof thetransporttube,ormidwayintheretractionstroke.Thecrewinspectedthetransporttubeforhardwaredamageandfoundnone,andtheyreportedthatthepistonwasdownapproximately7 to8 inchesinsidethetransporttubewiththe


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Onflightday6, thecrewreportedsmellingodorswheneverthecommodewasrunning. F-_Thecrewchangedthecommodeodor/bacteriafilterandinstalleda charcoalfilterintheatmosphericrevitalizationsystem(ARS)inplaceof theLiOHfilter;thesituationwasimprovedtosomedegree.Thenextday,thecrewchangedtheEDOplenumfilterandreportedthattheodorswereeliminated.At 202:15:36:43G.m.t.(12:22:53:43MET),WCSfanseparatorI exhibitedanunusualsignatureandthecrewreporteda gurglingnoiseandodorfromfanseparator1duringoperation(FlightProblemSTS-65-V-3C).Dataindicatedliquidwasstillinthebowlwhenthefanseparatorshutdown.Twofanseparatorcycleswereimmediatelyperformed,andtheseparatorrpmdidnotreachthenormalspeedduringeithercycle.Onthethirdcycle,theurinalfanshutdownthreeminutesbeforetheseparatortumedoff. Thiscausedtheurinalfaultlightto illuminate.Followingthisoccurrence,thecrewswitchedto fanseparator2,whichwasusedfortheremainderof themission.Duringpostflightactivitiesonthedayfollowinglanding,liquidbackflowfromthewastetankthroughthecheckvalvesoccurredwhenthewatertankswererepressurizedforsupplywatersampling.A four-gallonreductionofthewastewaterquantitywasnoted,andwateroverflowedintothemiddeckarea. Themiddeckareawascleanedanddisinfected.TheARS performedsatisfactorilythroughoutthemission.

Smoke Detection and Fire Suppression Subsystem F-,_Thesmokedetectionsystemshowedno indicationsofsmokegenerationduringtheflight.However,the leftflightdecksmokedetectorconcentrationindicationdroppedoff-scalelowfortwo seconds,followed14secondslaterbynegativespikesfora periodof fiveseconds(FlightProblemSTS-65-V-10). Also,afterlanding,a masteralarmwas


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(_"_, All fiveprogrammedtestinputs(PTIs)forDTO251 (EntryAerodynamicControlSurfaceTest - AlternateElevonSchedule)(Part7)wereexecuted.ThesubsonicmaneuverforDTO254 (SubsonicAerodynamicsVerification)wasalsosuccessfullyperformed.Theflightcontrolsubsystemperformednominally.TheaftRCSvernierthrusterR5DI =failedoffandthecauseis believedto bean anomalyin the reactionjet driver,themultiplexerldemultiplexer,orthewiringbetweenthesecomponents.Thisanomalyisdiscussedinthe ReactionControlSubsystemsectionof thisreport.IMUs2 and3 operatedproperly;however,the flightsoftwareissuedan IMU1redundantrate fail at 199:12:36:12.7G.m.t.(09:19:53:12.7MET)andonesecondlater,RMdeclaredIMU1 failedanddeselectedit (FlightProblemSTS-65-V-04).Examinationof the filteredredundantgyromonitordata,whichis usedby thegeneralpurposecomputer(GPC)to determinethe failure,indicatedthat thedatawere inexcessof the fail limitof0.7deg/hrfor a periodof22 seconds,whichis consistentwith the redundantrate fail. Dataalsoshowedthatthefrequencyandlengthof theseBITEscontinuedto increase;however,the platformvaluesretumedto normalvaluesaftertheBITEcleared. Late in themission,thedriftduringtransientswasasgreatas 30 sigmawiththe longestBITE lasting93minutes. Onflightday 13,datafromoneoftheeventsshoweda platformdrift of 0.08degree,andasa result,theFlightControlTeaminvokedFlightRule8-39,andIMU1wasdeclaredfailedforentryplanningpurposes.Priortoentryat 204:03:34G.m.t.(14:10:51MET),IMU1wasmodedto standbyfor 13minutesf_ andbacktooperateinanattempttorecovernominaloperation.The IMUcontinuedoperatingasnotedpreviouslyandwasrealignedperiodicallytoassurethatplatformmisalignmentscausedbydrifttransientsdidnotexceedRMthresholds.Anagreementwasreachedto leaveallthreeIMUsselectedforentryandtoallowRMsoftwaretocontrolIMUselectionduringentry. IMU1operatedsatisfactorilywithnoBITEindicationsduringentry.The IMUwasremovedfromthevehicleandhasbeensentto


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ascentand itperformednominally.On-orbit,theFMsystem1transmitteragainexhibitedfluctuatingtransmitteroutputpowerwithnodegradationinthedatanoted.However,FMsystem2wasselectedandusedforthe remainderof themission.OperationalInstrumentation/ModularAuxiliaryDataSystem

Theoperationalinstrumentation(OI)/modularauxiliarydatasystem(MADS)subsystemsperformedadequately.Twoin-flightanomalieswerenotedandarediscussedinthefollowingparagraphs.At approximately191:12:30G.m.t.(01:19:47MET),thego-to-markcommandwassenttothesystemcontrolmodule(SCM)forexecution.TheSCMexecutedthecommandwhichpositionstheOrbiterExperiments(OEX)recordertoa pre-determinedpointforrecordingdata. At191:21:08G.m.t.(02:04:25MET),thego-to-markcommandwasagainsentto theSCMforexecution.Thecommandswereverified,butthecommandswerenotexecutedbytheSCM. TheSCMwaspowercycledandthego-to-markcommandwasagaincommandedwithoutsuccess(FlightProblemSTS-65-V-01).WiththeSCMmalfunction,allOEXon-orbitandentrydatawerelost.Postlanding,thebatteryboardwasremovedanda powercyclewascommandedtotheSCM,andsuccessfulSCMoperationswererestored.Aftertherecordeddataweredumped,theIockupconditionwasreproducedwiththebatteryboardremovedusingthesameredundantcommandsequenceasusedon-orbit.Thistestprovedthatthebatteryboardwasnotatfault.Asa result,a ShuttleOperationalDataBook(SODB)addition ,"_.willbemadetodocumentthecommandsequencelimitations.At201:00:34G.m.t.(011:07:51MET),poorqualitydumpdatawerereceivedfromtrack2 ofOperations(OPS)recorder2 whiledumpingatthe8:1ratioandwasevidentinboththe forwardandreversedirectionsthroughKu-bandchannel2 (FlightProblem


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Thedragchutewasdeployednominallyat204:10:38:08.0G.m.t.,approximately8secondsaftertouchdownand10secondspriortonosegeartouchdown.Thedragchuteoperatedproperlyandwasjettisoned24.6 secondsafterdeploymentata groundspeedof52.9 knots.

LandinqandBrakinqParametersFrom

Parameter threshold, Speed, Sinkrate,ft/sec Pitchrate,ft keas deg/secMaingeartouchdown 3025 199.2 ~ 3 N/ANosegeartouchdown 8313 131.6 N/A 4.90Brakeinitiationspeed 110.0knots(keas)Brake-ontime 44.4secondsRolloutdistance 10,211feetRollouttime 68 secondsRunway 33 (Concrete)KSCOrbiterweightat landing 229r308feetPeak

Brakesensor pressure, Brakeassembly Energy,location psia millionft-lbLeft-handinboard1 960 Left-handoutboard 18.04(F_ Left-handinboard3 1140 Left-handinboard 15.80Left-handoutboard2 1080 Right-handinboard 17.96Left-handoutboard4 1164 Right-handoutboard 20.75Right-handinboard1 876Right-handinboard3 888


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Theaerodynamicandplumeheatingduringthe ascentphaseofthemissionwas ,"-'_nominal,basedontheevaluationofvehicletelemetrydataandthephysicalappearanceoftheplumes.Theentryaerodynamicheatingwasnominal,butheatingcalculationsarecontinuing.NoOEXentrydataareavailableforevaluationbecauseofthefailureoftheMADSrecorder.Theperformanceof thethermalinterfaceswasnominalwithall temperatureswithinlimits.

Thermal Control SubsystemThethermalcontrolsystemperformancewasnominalandallOrbitersubsystemtemperaturesweremaintainedwithinacceptablelimits.

AerothermodynamicsThe entryacreageandlocalheatingwerewithinlimits. Allstructuraltemperatureswerenominal,theTPSdamagewaswithinexperience,andthetrajectoryandcontrolsurfaceparameterswerenominal.The potentialfora structuralover-temperatureconditionwasindicatedfromtheTPSdamageontheleadingedgeof the left-handOMSpod.Therewasnoelevoncoveoverheating.However,the lackofMADSdatapreventsa detailedanalysisofthisarea.

ThermalProtectionSubsystemTheTPSperformedsatisfactorily.Basedonstructuraltemperatureresponsedata(temperaturerise),theentryheatingwasslightlybelowaverage.Peaktemperatureswerealsobelowaverageandatorneara minimumforthisvehicleinsomelocations,


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t"-_ barriers(new,mechanicallyattacheddesign)weredamagedinseveralareas,andsix' barriersegmentswillbe replaced.AnAmesgapfillerwasprotrudingjustforwardof theright-handMLGD. Theelevoncoveareawasingoodconditionwithnoabnormalitiesthatcouldbe relatedtotheDTO251up-elevonschedule.Onelargeimpactdamagesiteontheright-handinboardelevonwillresultinreplacementof theelevon.Twotilesonthelowerleadingedgestructuralsystem(LESS)panel8 haddamagedcomers,localtileglazing,andhardened"horsecollar_gapfillers.Discolorationwasnotedtobemorethanusualontheupperinboardelevons,butthefeltreusablesurfaceinsulation(FRSI)wasstillresilient.NoobviousTPSdamagesorconfigurationproblemswerenotedontheTPSsurroundingthe left-handwater/urinedumpports.TheETdoorthermalbarrierswereinnominalconditionoverall.A left-handETdoorhinge-linetilesustaineda largeareaofdamageonthe lipofthetile.Theenginedome-mountedheatshieldblanketsweredamagedinthefollowingareas:

a. SSME1from5to7o'clock;b. SSME2 at3 o'clock;andc. SSME3 at1o'clock.Baseheatshieldtilepepperingwasnormal.Also,dragchutedeploymentcausednotiledamage.Windows3 and4 exhibitedmoderate-to-heavyhazing,andwindows2,f_ and5 exhibitedlight-to-moderatehazing.Onlya lighthazewaspresentontheotherwindows.


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REMOTEMANIPULATORSYSTEM F-_,

The remotemanipulatorsystem(RMS)wasnotflownontheSTS-65mission.


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,F_, FLIGHTCREWEQUIPMENT/GOVERNMENTFURNISHEDEQUIPMENTTheflightcrewequipmentperformedadequately.Anomaliesthatoccurredintheflightcrewequipmentarediscussedinthefollowingparagraphs.Thecrewreportedat 191:14:39G.m.t.(01:21:56MET)thattheArriflexcamera(16mm)filmmagazine(S/N1016)hadjammed(FlightProblemSTS-65-F-01).Themalfunctionproceduretoclearthejamwasperformedsuccessfully;however,thejamrecurredashorttimelater.Thefilmmagazinewasreplacedandnormaloperationwasrestored.Thefailedmagazinewasstowedandretumedforpostflightanalysis.Thecrewreportedat 192:23:33G.m.t.(03:06:50MET)thatthe70mmHasselbladcamerahadjammedandthe lenscouldnotberemoved(FlightProblemSTS-65-F-02A).ThecrewperformedtwoIFMproceduresinanunsuccessfulattemptto restorenormalcameraoperation.Additionalprocedureswerecalleduptothecrew,andthecrewwasableto restorenormaloperationsusingtheseprocedures.However,theshuttercontrolbuttoncameapartonthecamera,anda smallspringandretainingringwerelostontheflightdeckwhilerepairingthecamera(FlightProblemSTS-65-F-02B).At 193:00:44G.m.t.(03:17:49MET),thecrewreportedthatthecamerahadjammedagainandthelenscouldnotbe removed.Thecrewwasabletoremovethelensfromthebodyusingan IFMprocedureafterwhichthecrewdeterminedthatneitherthe lensnorthebodywereworkingproperly.Asa result,thecameraandlensF-_ werestowedfortherestofthemission.Closedcircuittelevision(CCTV)cameraDexperiencedintermittentdegradationofthehorizontalsynchronization(FlightProblemSTS-65-F-03).ThisconditioncausedtheNASAGroundTerminalto loselock,whichinturnresultedincolorshifting(tearing)ofthepicture.


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CARGOINTEGRATION -'-'_,Integrationhardwareperformancewasnominalthroughoutthemissionwithnoanomaliesrecorded.


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('-_,. DEVELOPMENTTESTOBJECTIVES/DETAILEDSUPPLEMENTARYOBJECTIVES

Atotalof 16developmenttestobjectives(DTOs)and16detailedsupplementaryobjectives(DSOs)wereassignedto theSTS-65mission.Datawerecollectedon15ofthe16DTOs,andonall16DSOs.Thefollowingparagraphsdiscussthe results,ifknown,foreachDTOandDSO.DEVELOPMENTTESTOBJECTIVES

DTO251 - EntryAerodynamicControlSurfacesTest-AltemateElevonSchedule(Part7) - Allfiveof theplannedPTIswereperformed.ThepreliminaryanalysisofthesedatashowthevehicleresponsecompareswellwiththatpredictedfromtheAmesVMS. Datahavebeengivento thesponsorforevaluation,andtheresultswillbereportedinseparatedocumentation.DTO254 - SubsonicAerodynamicsVerification(Part2) - Thesubsonicmaneuverwasperformedduringthefinalapproachto landing.Thedataweregivento thesponsorforevaluation.Initialresultsindicatethattheaileronandrudderinputswereasexpected.ThefinalresultsofthisDTOwillbepublishedinseparatedocumentation.DTO301D - AscentStructuralCapabilityEvaluation- Thiswasa data-onlyDTOand.Y_ datawerecollectedforthisDTO. Thedataweregiventothesponsorforanalysisandevaluation.Theresultsof theevaluationwillbepublishedinseparatedocumentation.DTO307D- EntryStructuralCapabilityEvaluation- Thiswasa data-onlyDTOanddatawerecollectedforthisDTO. Thedataweregiventothesponsorforanalysisandevaluation.Theresultsof theevaluationwillbepublishedinseparatedocumentation.


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hamperedanalysis.Theaftdome,+X,-Y, and-Z areasof theETwereimaged, r_TypicalcharringontheET aftdomeisvisible.DTO319D- Orbiter/PayloadAccelerationandAcousticsEnvironmentData - Thiswasa data-onlyDTO,anddatawererecordedforthisDTO. Thedatahavebeengiventothesponsorforevaluation.The resultsoftheevaluationwillbepublishedinseparatedocumentation.DTO414 - APUShutdownTest(SequenceA) - TheAPUswereshutdowninthepropersequence(APU2,APU1,andAPU3). DataevaluationshowednoindicationofPDUbackdriving.ThisDTOwillcontinuetobeperformeduntiltwosequenceA's(APU2, APU1,andAPU3 inthatorder)andtwosequenceB's(APU3,APU1,andAPU2 inthatorder)havebeencompleted.DTO623- CabinAirMonitoring- Allscheduledactivitieswerecompletedbythecrew,andthedatahavebeengiventothesponsorforevaluation.The resultsoftheevaluationwillbepublishedinseparatedocumentation.DTO655- FootRestraintEvaluation- ThecrewcollecteddataforthisDTOandthedatahavebeengiventothesponsorforevaluation.Theresultsof theevaluationwillbepublishedinseparatedocumentation.DTO663- AcousticNoiseDosimeterData-Allscheduleddatatakeswereperformed ."_.bythecrew,andthedatahavebeengivento thesponsorforevaluation.Theresultsoftheevaluationwillbepublishedinseparatedocumentation.DTO665- AcousticNoiseSoundLevelData - Allscheduleddatatakeswereperformedbythecrew,andthedatahavebeengiventothesponsorforevaluation.


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F"_ fastenerwithanotherfastenerthatrequiredlessthreads,therebymakingthecycle/ergometerusablefortherestof themission.' DTO805- CrosswindLandingPerformance- ThisDTOofopportunitywasnotperformedbecauseof the lowwindconditionsatKSC.

DTO913- MicrogravityMeasurementDevice-The MicrogravityMeasurementDevice(MMD)wasusedtorecordvibrationsduringavarietyofexperimentoperationsincludingthecycle/ergometerwhenitwashardmountedforonesessionandmountedwiththeIVISfortheremainderof thesessions.Thedatafilesweredownlinkedusingtheportableaudiodatamodem(PADM).Thedatahavebeengiventothesponsorfortheevaluation,andtheresultsoftheevaluationwillbepublishedinseparatedocumentation.

DETAILEDSUPPLEMENTARYOBJECTIVESDSO314 - OV-102AccelerationDataCollection- The objectiveofDSO314wastoacquirehighresolutionaccelerometerpackage(HiRAP)datato furthercharacterizethelow-frequencyaccelerationenvironmentintheOrbiterthatresultsfromcrewactivitiesandvehicleoperations.Theplanneddata-collectionperiodsincludedthecrewpush-offloadtest,avehicleattitudedeadbandchangefrom1.0degreeto0.5 degree,andsixcrewexercisesessionsontheergometer,whichwasusedwiththenewlyr developedIVIS. TheHiRAPoperationswerecontrolledbyuplinkcommandsroutedthroughthe SCM,whichalsocontrolledbyOEXrecorderthatrecordedtheHiRAPdata. TheSCMexperiencedananomalyonflightday3 thatprecludedfurtheroperationof theHiRAPandrecorder.Datafromthreeofthesixcrewexerciseperiodswereobtainedpriortothefailure.Attemptsto revivetheSCMwereunsuccessful;consequently,nootherdatacouldbeobtained.


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DSO487- ImmunologicalAssessmentofCrewmembers- Datawerecollectedforthis "_.DSOduringtheprelaunchandpostflightperiods.Thesedatahavebeengivento thesponsorforevaluation,andtheresultsof theevaluationwillbe reportedinseparatedocumentation.DSO491 - Characterizationof MicrobialTransferAmongCrewmembersDuringSpaceflight- DatawerecollectedforthisDSOduringtheprelaunchand postflightperiods.Thesedataweregiventothesponsorforevaluation,andtheresultsof theevaluationwillbe reportedinseparatedocumentation.DSO603 - OrthostaticFunctionduringEntry,LandingandEgress- DatawerecollectedforthisDSO,andthesedatahavebeengivento thesponsorforevaluation.The resultsoftheevaluationwillbepublishedinseparatedocumentation.DSO604- Visual-VestibularIntegrationasa FunctionofAdaptation- DatawerecollectedforthisDSO,andthesedatahavebeengiventothesponsorforevaluation.Theresultsoftheevaluationwillbepublishedinseparatedocumentation.DSO605- PosturalEquilibriumControlDuringLandingandEgress- DatawerecollectedforthisDSOduringthelandingandegressactivities.Thesedataweregiventothesponsorforevaluation,andtheresultsof theevaluationwillbepublishedinseparatedocumentation.DSO608 - EffectsofSpaceFlightonAerobicandAnaerobicMetabolismDuringExercise- Operationalexercisesessionswerecompletedthroughouttheflightbyallcrewmembers.ExercisestartandstoptimeswerereportedtocoordinatewiththeSAMSexperimentandtheMMD(DTO913). TheCommander,Pilot,andMissionSpecialist2 participatedinDSO608. Allsessionswerecompleted.ThelastDSO608


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DSO901- DocumentaryTelevision- Allscheduledactivitiesinsupportof thisDSOwerecompleted.Thevideodatahavebeengivento thesponsorforevaluation,andthe resultsof thatevaluationwillbe reportedinseparatedocumentation.,=

DSO902 - DocumentaryMotionPicturePhotography- Allscheduledactivitiesinsupportof thisDSOwerecompleted.Thephotographicdatahavebeengiventothesponsorforevaluation,andtheresultsofthatevaluationwillbereportedinseparatedocumentation.DSO903 - DocumentaryStillPhotography-AllscheduledactivitiesinsupportofthisDSOwerecompleted.Thephotographicdatahavebeengiventothesponsorforevaluation,andthe resultsofthatevaluationwillbereportedinseparatedocumentation.

/


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PHOTOGRAPHYANDTELEVISIONANALYSIS F--_,

LAUNCHPHOTOGRAPHYANDVIDEO DATAANALYSISThe STS-65missionwaslaunchedfromComplex39A onJuly8, 1994. Onlaunchday,24 videosof thelaunchactivitieswerescreenedandnoanomalieswerenoted.Followingthe launchdayscreeningactivities,53of54 plannedfilmswerealsoscreened.Onecamerafailedandthefilmwaslost. Noanomalieswerenotedinthereviewofthevideoandphotographicdata.

ON-ORBITPHOTOGRAPHYANDVIDEODATAANALYSISNosignificanton-orbitvideoorphotographicrecordedeventswereobservedthatrequiredanalysis.VideoandphotographicdatafromDTO312wereevaluated.

LANDINGPHOTOGRAPHYANDVIDEODATAANALYSISLandingoftheSTS-65Orbiterwasdelayedonedaybecauseofweatherconstraints.TheSTS-65missionwasconcludedonJuly23, 1994witha landingat KSC. TwelvevideosplusNASASelectof theOrbiterapproachandlandingwereevaluated.Inaddition,15 landingfilmswerealsoscreened.NoOrbiteranomalieswerenotedinanyofthephotographicorvideodata. F--._


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,("_ TABLEI.-STS-65MISSIONEVENTSEvent Description Actualtime,G.m.t.

APUActivation APU-1GGchamberpressure 189:16:38:12.74APU-2GGchamberpressure 189:16:38:13.61APU-3GGchamberpressure 189:16:38:14.59SRBHPUActivationa LHHPUSystemAstartcommand 189:16:42:32.083LHHPUSystemBstartcommand 189:16:42:33.243RHHPUSystemAstartcommand 189:16:42:33.403RHHPUSystemBstartcommand 189:16:42:33.563MainPropulsionSystem ME-3Startcommandaccepted 189:16:42:53.437Starta ME-2Startcommandaccepted 189:16:42:53.585ME-1Startcommandaccepted 189:16:42:53.704SRBIgnitionCommand CalculatedSRBignitioncommand 189:16:43:00.013(Liftoff)Throttleupto104Percent ME-3Commandaccepted 189:16:43:03.078Thrusta ME-1Commandaccepted 189:16:43:03:104ME-2Commandaccepted 189:16:43:03.105Throttledownto ME-3Commandaccepted 189:16:43:26.47867PercentThrusta ME-1Commandaccepted 189:16:43:26.505ME-2Commandaccepted 189:16:43:26.506MaximumDynamicPressure Derivedascentdynamicpressure 189:16:43:51(q)Throttleupto104Percenta ME-3Commandaccepted 189:16:44:00.718ME-1Commandaccepted 189:16:44:00.745ME-2Commandaccepted 189:16:44:00.746("_ BothSRM'sChamber RHSRMchamberpressure 189:16:44:57.613Pressureat50 psia mid-rangeselectLHSRMchamberpressure 189:16:44:58.453mid-rangeselectEndSRMActiona RHSRMchamberpressure 189:16:45:00.053mid-rangeselectLHSRMchamberpressure 189:16:45:00.723


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TABLEI.-STS-65MISSIONEVENTS(Continued) :_Event Description Actualtime_G.m.t.

APUDeactivation APU-2GGchamberpressure 189:16:58:58.97APU1GGchamberpressure 189:16:59:11.11APU3GGchamberpressure 189:16:59:20.23OMS-1Ignition Leftenginebi-propvalveposition Notperformed-Rightenginebi-propvalveposition directinsertiontrajectoryflownOMS-1Cutoff Leftenginebi-propvalvepositionRightenginebi-propvalvepositionOMS-2Ignition Leftenginebi-propvalveposition 189:17:22:55.2Rightenginebi-propvalveposition 189:17:22:55.2OMS-2Cutoff Leftenginebi-propvalveposition 189:17:25:16.5Rightenginebi-propvalveposition 189:17:25:16.7PayloadBayDoors(PLBDs) PLBDfightopen1 189:18:10:45Open PLBDleftopenI 189:18:12:04FlightControlSystemCheckoutAPUStart APU-1GGchamberpressure 202:07:36:15.04

APUStop APU-1GGchamberpressure 202:07:43:28.70PayloadBayDoorsClose PLBDleftcloseI 203:07:08:29PLBDrightcloseI 203:07:10:39PayloadBayDoorsReopen PLBDfightopen1(BFS) 203:11:27:54PLBDleftopen1 (BFS) 203:11:29:13OMS-3Ignition Leftenginebi-propvalveposition 203:12:47:44.1 F"_Rightenginebi-propvalveposition 203:12:47:44.2OMS-3Cutoff Leftenginebi-propvalveposition 203:12:48:16.2Rightenginebi-propvalveposition 203:12:48:16.2OMS-4Ignition Leftenginebi-propvalveposition 203:13:32:42.2Rightenginebi-propvalveposition 203:13:32:42.2OMS-4Cutoff Leftenginebi-propvalveposition 203:13:33:12.6


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/F_, TABLEI.- STS-65MISSIONEVENTS(Continued)Event Description Actualtime,G.m.t.

DragChuteDeployment Dragchutedeploy1CPVolts 204:10:38:08.0NoseLandingGear NLGLHtirepressure1 204:10:38:17ContactNoseLandingGear NLGweightonwheelsI 204:10:38:18WeightOnWheelsDragChuteJettison DragchutejettisonI CPVolts 204:10:38:42.6WheelStop Velocitywithrespectto runway 204:10:39:09APUDeactivation APU-1GGchamberpressure 204:10:58:10.85APU-2GGchamberpressure 204:10:58:12.14APU-3GGchamberpressure 204:10:58:13.79

TABLE II.-ORBITERPROBLEMTRACKINGLIST

No. Title Reference Comments


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STS-65-V-01 OEXSystemControl 191:21:18G.m.t. DuringOEXrecordercommanding,theOEXSystemModule 002:04:25MET ControlModule(SCM)stoppedexecutingcommands.StoppedExecuting IM65RF01 Powercycles,softwareresetsandrecoverycommandsCommands IPR73V-0003 didnotrestoreSCMoperation.Nofurtheron-orbit,LEVELIII CLOSURE entryorpostlandingdatafromMADS,AlP,andACIP/HIRAP(DSO-314)wererecorded.Normalpostflightdatadumpattemptnotsuccessful.SCMrecoveredandOEXrecorderdumpedafterbatteryboardremoval.Symptomswerereproducedwithbatteryboardremovedusingsamecommandsequenceasusedon-orbit.SODBadditiontodocumentcommandinglimitationsinwork.STS-65-V-02 SupplyWaterDumpNozzle 192:08:00G.m.t. Duringthethirdsupplywaterdump,thesupplyandIcing 002:15:17MET wastewaterdumpnozzletemperaturesdroppedIM65RF02 indicatingicing.Thesupplywaterdumpwaso= IPR73V-0017 terminatedandnozzleheaterswereusedtoevaporateiceuntilnozzletemperaturesreturnedtonormal,thenawastewaterdumpwasperformed.SupplywaterdumpswereperformedusingtheFESfortheremainderoftheflight.DetailednozzleandTPSinspectionsshowedevidenceofRTVdeteriorationaswellasdifferencesinTPSconfigurationbetweenvehicles.Flowrateandspraypattemverificationswereperformed.STS-65-V-03 WCSProblems 193:06:06G.m.t. Compactorpistonstoppedat themidwaypointduring

A.CommodeFaultDuring 003:13:23MET pistonretractionduringthethirdcompactioncycleCompactionCycle IM65RF10 resultingina CommodeFaultindication.Crewmanuallyretractedpistonandfoundnoproblemsduringcompactor,piston,andtransporttubeinspection.Compactoroperationswerenominalforremainderof themission.Possibleoperationerroridentifiedbycrewduringdebriefing.Partsofashearedrollpinfoundinsidetheouteredgeof pistonduringOMRSDcleaning.NoKSCaction.

TABLE II.-ORBITER PROBLEMTRACKING LIST


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No. Title Reference CommentsB.CommodeFilter IM65RF03 ThefirstreplacementcommodeodorbacteriafilterAnomaliesandOdor (SINTBD)didnotfitandtheoriginal(ascent)filterwasManagement reinstalled.Thefilterwassuccessfullyinstalledonflightday12aftera lubricantwasappliedtothegrommetandthefilterremainedinstalledthroughentry.Otherreplacementfiltersdidnotencounterinterference.PlenumfilterreplacementandinstallationofanadditionalARScharcoalcanisterwereperformedto controlodors.Usedplenumfilterwascleananddrybutretainedodors.NoKSCaction.C.FanSeparatorI Stall IM65RF11 CrewreportedgurglingnoiseandodorfromfanandLiquidBackflow IPR73V-0008 separator1duringoperationon flightday13. DataPR indicatenormalfanstart-upbutIowseparatordrumV070-2-18-0326 speed.Liquidbackflowmayhaveoccurredthroughthedualfanseparator1outletcheckvalvesaftertheprevioususefor10secondsresultingin floodingofthefanseparator.The fanseparatorI bowlwasstillpumpingliquidat normalshutdowntime. ThecrewattemptedtoclearfanseparatorI byrestartingwithoutsuccess.Fanseparator2 wasusedfortheremainderof themission.Liquidbackflowfromthewastetank

throughthecheckvalvesoccurredonedayafterlandingwhenwatertankswererepressurizedforsupplywatersamplingresultingina 4-gallonwaste-tankquantityreductionandoverflowintothemiddeckarea. AccessibleplumbingdrainedpriortoWCSremovalforshipmenttothevendor.STS-65-V-04 IMU1RedundantRateBite 199:12:36G.m.t. NumeroustransientredundantrateBITEmessages009:19:53MET weregeneratedwhenthe IMU-1(SIN204)azimuthIM65RF04 gymexperiencedspikesexceeding0.7/hr.duringPR latertransients.NoKSCtroubleshooting.IMUGNC-2-18-0102 removedandshippedto ISL. SymptomsreproducedatISL.

TABLE I1.-ORBITER PROBLEMTRACKING LIST

No. Title Reference Comments


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STS-65-V-05 RCSVemierThrusterR5D 199:09:14G.m.t. VernierthrusterR5DwasfailedoffbytheRM. TheFailedOff 009:16:31MET thrusterwashot-firedsuccessfully,thenreselected.IPR73V-0004 Subsequentperformancewasnominal.DataindicatepossibleintermittentlossofR5DcommandB (enable)signal.MDMFA2BSRwaspolledandindicatedthatnofaultswererecorded.KSCtroubleshootingdidnotreproducetheanomaly.STS-65-V-06 LowWasteDumpFlow 198:07:06G.m.t. Thesecondwastewaterdumpwasinitiatedat008:14:23MET 198:06:33G.m.t.(008:13:50MET)andwasperformedIM65RF05 inthreesegments.ThedumpratedegradedduringIPR73V-0016 thesecondsegmentofthedumpandwasnominalduringthethirdsegment.A thirdwastewaterdumpwasperformedat 202:05:39G.m.t.(12:12:56MET)in7 segments,allwitha degradeddumpflowrate.Nozzleinspection,waterflushandsample,urinesolidsfilterremovalandcitricacidflushwere performed.STS-65-V-07 PoorDumpQuality 201:00:34G.m.t. Poorqualitydatawerereceivedfromtrack2 ofOPSOperationsRecorder2 011:07:51MET recorder2 duringa dumpatan8:1ratioinboththeTrack2 IM65RF06 reverseandforwarddirections.GoodqualitydataIPR73V-0005 werereceivedwith1:1ratiodumpthroughgroundsite.Tracks3 through14onOPSrecorder2 wereusedasanAOSrecorder.PostflightdumpthroughT-Oat 8:1and1:1fromtrack2 notsuccessful.Track2 re-recordedinbothdirections,anddumpreversewasworsethanforwardwithdegradedqualityinbothdirections.RecorderremovedforshipmenttoNSLD.STS-65-V-08 LH2ManifoldPressure 189:17:23G.m.t. TheLH2manifoldpressurerosetoanunexpectedhighFollowingVacuumInert 000:40:00MET peakpressureof 17psiafollowingvacuuminert. AfterIPR73V-0014 reachingthepeakpressure,theLH2manifoldpressuredecreasedfasterthanexpected.FirstuseofOI-23softwarewhichincludedMPSdumpandvacuuminertsequenceautomation.TheOI-23softwarewasverifiedtohaveperformedasdesignedandLH2systemresponsestosoftwarecommandswasnominal.

.J .... J

TABLE II.- ORBITER PROBLEMTRACKING LIST


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No. Title Reference CommentsSTS-65-V-08 LH2manifoldlargevolumedecaycheckfailedat0.696(Continued) psi/hr(max.= 0.601psi/hr).Manifoldreliefvalveleak

checkandlargevolumedecaycheckplanned.STS-65-V-09 HighMPSHeliumUsage 204:10:29G.m.t. A totalof59.7IbofheliumwasusedduringtheDuringEntry 014:17:46MET 650-secondsystemblowdownperformedduringentry.IPR73V-0015 Nominalusageis55.7_ 1.1IbforOV-102. ThisconditionwascausedbytheOI-23softwarechangefromsingletodualregulationsupply.FileIXOMRSDchangeplanned.STS-65-V-10 LeftFlightDeckSmoke 197:15:52G.m.t. TheleftflightdecksmokedetectorconcentrationDetectorTransients 007:23:09MET indicationdroppedoff-scalelowfortwosecondsfollowed14secondslaterbynegativespikesforaperiodoffiveseconds.Afterlanding,a masteralarmwasreceivedfromtheleftflightdecksmokedetectorwithnoconcentrationchangeobservedin thedata.Thesmokedetectorwasreplaced.

TABLEIII.-GFEPROBLEMTRACKINGLISTNo. Title Reference Comments


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STS-65-F-01 ArriflexCameraFilmMagazine 191:14:39G.m.t. Crewreported16mmArriflexCamerafilmJam 001:21:56MET magazineSIN1016jammed.Malfunctionprocedureclearedjambutsubsequentlyrecurred.Filmmagazinereplaced,normaloperationrestored.FilmmagazineSIN1016stowedinthe16mmbaginlockerL100.STS-65-F-02 70mmHasselbladCamera 192:23:33G.m.t. A. CrewreportedHasselbladcamerajammed-Malfunctions 003:06:50MET unabletoremovelens.AnIFMtoclearjamandremovelenswassuccessful;however,cameraA. CameraJammed/LensStuck andlensagainjammedat 193:00:44G.m.t.Cameraandlensstowedfortheremainderof

B. ShutterTrigger flight.Failed/SpringLost B. Crewreportedthe retainingringontheHasselbladcamerashutterreleaseplungerwasmissing.Crewusedgraytapeforretention.olo Duringasubsequentattemptto repairthejammedcameraandlens,theshutterreleasebuttonplungerspringwas lostontheaftflightdeck.STS-65-F-03 CCTVCameraDDegraded 193:17:30G.m.t. CCTVCameraDisexperiencingintermittentHorizontalSync 004:00:47MET degradationof thehorizontalsynchronizationwhichcausedtheNASAgroundterminal(NGT)framesynchronizerto loselock,resultingincolorshifting(tearing).

STS-65-F-04 ErgometerFastenerFailure 195:22:20G.m.t. Crewreportedleftaft fastener(fromseated006:05:37MET crewpersonperspective)broken.Leftaft fastenerswappedwithrightforwardfastener.Ergometerwasusableforremainderofmission.


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TABLEIII.-GFEPROBLEMTRACKINGLISTNo. Title Reference CommentsSTS-65-F-05 GalleyRHSFailedtoDispense 193:07:49G.m.t. Crewreportedgalleyrehydrationstation(RHS)ColdWater 003:15:06MET didnotdispensecoldwaterbuthotwaterwasdispensednormally.Aftergalleypowerwascycled,galleydispensed ounceofcoldwaterwheneither8-ounceor7.5-ouncedispensequantitieswereselected.CrewperformedmalfunctionprocedurewhichrestorednominalgalleyRHSperformance.

O1

TABLE IV.- MSFCPROBLEMTRACKINGLIST


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No. Title Ref.time DiscussionSTS-65-B-01 RHRSSSafeandArm Ascent Theright-handRangeSafetySystemSafeandArmDeviceLooseMounting devicehad twoof four mountingfastenersthatwereFasteners notproperlyseated. Gapsunderthe fastenerheadsmeasured0.06in.and0.078in.withthe safetywireintact. Stressanalysisshowsflight loadare notsufficientto causethe gap. Fail-safeanalysisshowstworemainingfastenerssufficientto retainsafeandarmdeviceonthepanel.Thesafeandarmdevicemountingfastenerswillbeinspectedtoverifythatnoloosewashersorgapsexist.STS-65-B-02 Brokenfasteneron Ascent Left-handintegratedelectronicsassembly(lEA)endLHAFTlEAEndCover coverhasonebrokenfasteneronthesystems-ol tunnelsideof thecover.Noevidenceexistsof

r_ water-impactdamageinthisarea. Lossof thisfastenerdoesnotcauselossof thecover;however,genericimplicationstoothercoverfastenerswillbeinvestigated.STS-65-M-01 AftSegmentStiffener Ascent CracksaretypicallyseenatthecenterlineofcavityAStubCrack crackwasfoundontheleft-handaft segmentfor-wardstiffenerringstubextendingradicallyinwardfromtheouterdiameterof thestub.Thecrackwaslocatedat90.5degreesandwasapproximately114inchdeep.Damageoccurredduringsplashdownandthedamagewaslocatedat thecavitycollapsecenterline.Splashdowndamagetothisstubandstiffenerringswasmoreextensivethanistypicallyseen.


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TABLE IV.-MSFCPROBLEMTRACKING LISTNo. Title Ref.time Discussion

STS-65-M-01 AftSegmentStiffener Cracksaretypicallyseenatthecenterlineofcavity(Continued) StubCrack collapse;however,thiscrackwasunusualinthatitoccurredbetweenholes.Thecrackedsectionwasexcisedandthepreliminaryexaminationresultsindicatethatthecrackwascausedbystresscorrosionaftersplashdown,withnoindicationof anypre-existentflaw. Thefinalgeometryappearstobea half-moonshapedcrackwithamaximumdepthofapproximately112inch.Thefracturesurfacehadanintergranularstructureindicatinghydrogen-assistedstresscorrosioncracking(SCC). Theprobablecrackinitiationlocationwasontheaft outerflangecornerandwasapproximately0.060-inchlongby0.012-inchdeepfromwhichitgrewinwardapproximately0.25inch.ThecrackinitiatedduringwaterimpactdamageandgrewduringtowbackduetoSCC. Allnecessarycon-ditionsforSCCwerepresent,i.e.,residualtensilestressbecauseofwaterimpactcavitycollapseloads,probableinitiationlocation,damagetoprotectionsystem(primer,paint,K5NA,Instafoam,etc.),corrosiveenvironment(saltwater)duringtowback,presenceofzincinprimertohelpacceleratecrackgrowth,andthesusceptibilityof theD6ACmaterialtoSCC.


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DOCUMENTSOURCES

Inanattempttodefinetheofficialaswellastheunofficialsourcesofdataforthismissionreport,thefollowinglistisprovided.1. FlightRequirementsDocument2. PublicAffairsPressKit3. CustomerSupportRoomDailyReports4. MERDailyReports5. MERMissionSummaryReport6. MERQuickLookReport7. MERProblemTrackingList8. MEREventTimes9. SubsystemManagerReports/Inputs10. MODSystemsAnomalyList11. MSFCFlashReport12. MSFCEventTimes13. MSFCInterimReport14. CrewDebriefingcomments15. ShuttleOperationalDataBook

(,.---..


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FES flashevaporatorsystem :"--_FFEU FreeFlowElectrophoresisUnitFID failureidentificationFM frequencymodulationFO flightobjectiveFRSI flexiblereusablesurfaceinsulationFSM fuelsupplymoduleft/sec feetpersecondg gravityGFE GovemmentfumishedequipmentGH2 gaseoushydrogenG.m.t. GreenwichmeantimeGN2 gaseousnitrogenGPC generalpurposecomputerHIRAP highresolutionaccelerometerpackageHPFT highpressurefuelturbineHPOTP highpressureoxidizerturbopumpHRMHUMS hydrogenumbilicalmassspectrometerlEA integratedelectronicsassemblyIFM in-flightmaintenanceIML-2 InternationalMicrogravityLaboratoryIMU inertialmeasurementunit !ISP specificimpulseITEPC InterMarsTissueEquivalentProportionalCounterIVIS inertialvibrationisolationsystemKSC KennedySpaceCenterkW kilowatt


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_7---, MLGD mainlandinggeardoorMMD MicrogravityMeasurementDeviceMPS mainpropulsionsystem' MSFC MarshallSpaceFlightCenterNASA NationalAeronauticsandSpaceAdministrationNASDA NationalSpaceDevelopmentAgencyofJapanNIZEMI SlowRotatingCentrifugeMicroscopeNPSP netpositivesuctionpressureNSLD NASAShuttleLogisticsDepotNSTS NationalSpaceTransportationSystem(i.e.,SpaceShuttleProgram)OARE OrbitalAccelerationResearchEquipmentOEX OrbiterexperimentsOI operationalinstrumentationOMRSD OperationsandMaintenanceRequirementsandSpecificationsDocument

OMS orbitalmaneuveringsubsystemOPS operationsPADM portableaudiodatamodemPAL protuberanceairloadPAWS PerformanceAssessmentWorkstationPCIS powercontrolandinterfacesystemPCM phasechangematerialf-". PDU powerdriveunitPILOT PortableIn-FlightLandingOperationsTrainerPMBT propellantmeanbulktemperaturePOGO longitudinaloscillationPRSD powerreactantstorageanddistributionPTI programmedtestinput


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SCM SpinalChangesinMicrogravity/systemcontrolmodule f--'_SLF ShuttleLandingFacilitySIN serialnumberSODB ShuttleOperationalDataBookSRB SolidRocketBoosterSRSS ShuttlerangesafetysystemSSME SpaceShuttlemainengineSTGT ShuttleTDRSGroundTerminalTDRS TrackingandDataRelaySatelliteTED thermalelectricdeviceTEl thermoelectricincubatorTEMPUS ElectromagneticContainerlessProcessingFacilityTPS thermalprotectionsubsystemTVC thrustvectorcontrolVIBES VibrationIsolationBoxExperimentStationVMS VerticalMotionSimulatorWCS WastecollectionsystemWSB watersprayboiler

NSTS-08292 - STS-65SpaceShuttleProgramMissionReportDistribuitionListNASA Headquarters R12A-130/J.Shea DM/J.Harpold LNW. DraperME/C. Perry R16C/J.Oberg DM22/J.Montalbano MNB. ShawME/D. Dillman R16H/K.Rahman DM22/W. Hollister MNM. SuffrediniMOC/Library R20B/R.Pechacek DT/FoHughes MJ/T.R. Loe (2)


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MZB/H. Miller ZC01/C. Ritrivi EA/L.Nicholson NA2/M. ErmingerQP/R. Perry ZC01/C.Beatty EC/W. Ellis NB/J.McCulloughZC01/J. Woodall EC3/E. Winkler ND/D. DustonGoddard Space Fliqht Center ZC01/W. Scott EC3/H. Rotter(2) ND3/L.Lewallen100/P.Burr ZC01/L. Jenkins EC3/N. Cerna NS/D.Whittle130/T. Jones ZC01/J. Mechelay EC4/I_.Casey PS3/STI Center(3)300/R. Bauman ZK16/M.Mason EC6/J. McBarron PT3/S.Morris302/W. Bangs EE/J. Griffin SNW. Womack313/R.Marriott JSC EE2/H. Vang SD/S. Pool400;V.Weyers AC5/J.Young EE3/P. Shack SD/G. Bopp700/T. Huber AP3/J.Carr (4) EE6/L Leonard SD2/R. Billlca710/W. Meyer AP4/S. Luna(3) EE6/R. Nuss SD24/D. Rushing730/E. Powers AP4/B.Dean (3) EE7/M. D. Schmalz SD4/N. Cintron730.1/J. Young BY4/HistoryOffice(2) EE7/J.Dallas : SD5/J. CharlesCND. Leestma EG/T.JimBlucker: SN15/M.GaunceKSC CA4/R.Filler EG/Library SP/C. Perner(5)Library-D(14 copies) CB/R.Cabana (6) EG3/S. Derry TNR. DittemoreCS-IOD-1/R. Schuiling CB/J. Halsell(5) EG4/K. Frank TC/R. Swalin(2)LSO-410/K.Lathrop CB/K.Colgan EK/FDSDLibrary . TC2/F. BrizzolaraLSO-420/W.Hollis CB/T. Henricks EK5/W.Trahan TC3/D. DeAtkineMK/L.J. Shriver DNLibrary EP2/BranchOffice TJ2/G. SandarsTP-OAO/A. Mitskevich DA15/D.Nelson EP2/L Rhodes TM/W. MoonDA3/S.Bales EP5/T. Davies TM2/G. Nield(2)MSFC DA3/R.Holkan EPJW.Guy VND. GermanyCN22D/Repository(30) DA8/R. Legler ES/E. Chimenti VF/D. CampEE31/C.Snoddy(2) DA8/Library ES/DivisionOffice(2) VF2/W. Gaylor ,,EP51/J.Redus(5) DE4/P. Cerna ES3/Y. Chang VF2/R. BrasherFA51/S. Sauchier DF/J.Knight ES3/R. Sema VF3/B.G. Swan(10) --JA01/C.Griner DF72/Q. Carelock ES6/C. Norris(2) VG/H. Kolkhorst o_SA12/O.Henson DG47/SImSup's ET13/E. Smith VG/J. Goodman _ _,DG66/H. Lampazzi ET3/T. Farrell VK/ResidentOffice o__>Lanqley Research Center DG67/C. Moede ET5/J.Lawrence VM22/C. Critzos Q_Tech. Library/MailStop 185, DO/J.Whitely GNT. Holloway VM22!J. Mistrot _ _DO4/D. Ricked GA2/C. McCullough(3) VM22/K. Kaminski _EDO4/LeadFAO GA2!D. Fitts VFI/ResidentOffice o_Rockwell-DowneyAD75/DataManagement(42) DO41lIE. Pipped GM/D. Schultz WNL. Williams _j=_, DO45/M. LeBlanc JL4/R. Squires WEIR. D. White oRockwell-Houston DO6/J.Clement JM12!D. Portree ZR/Lt. Col.J. McLeroyR12A-130/J.Snowden DJ/J.Muratore(2) KN/NASDA(3) ZR12/L. Dungan ...... r

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STS-65 Space Shuttle Mission Report

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Transcript of STS-65 Space Shuttle Mission Report