STS-38 Space Shuttle Mission Report

8/7/2019 STS-38 Space Shuttle Mission Report

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U/_/_-:_-_o5,_,.__: NSTS-08308

C:' STS-38SPACESHUTTLEASA-TM-10547819920008315MISSION REPORT

January 1991.?

" I (NASA-TM-105478) STS-38 SPACE SHUTTLE N92-17534MISSION REPORT (NASA) 19 p CSCL 22B

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UTTL: STS-38 Space Shuttle mission reportAUTH: A/CAMP, DAVID W.; B/GERMANY, D. M.; C/NICHOLSON, LEONARD S.CORP: l.lational Aero'nautics and Sp,'-_-eAdministrati_-,n. Lyndon B. Johnson SpaceCenter, Houston7, TX.SAP: Avail: NTIS HCiMF A03CIO: UNITED STATESHA.IS: i_ATLANTIS (ORBITER)/-.*SPACE MISSIONS!*SPACE SHUTTLESi.*SPACE TRANSPORTATIONSYSTEM FLIGHTSMINS: / DEFENSE PROGRAM/ EXTERNAL TANKS/ SPACE SHUTTLE BOOSTERS/ SPACE SHUTTLEMAIN ENGINEABA: AuthorABS: ['he STS-38 Sp_ce Shuttle Program Mission Rep_-,r'tcc,ntains a summary of the

vehicle subsystem activities on this thirty-seventh flight of the SpaceShuttle and the seve'nth flight of the Orbiter vehicle Atlantis (0V-104).In addition to the Atlantis vehicle, the flight vehicle consisted of anExternal Tank (ET) (designated as ET-_O/LWT-33), three Space Shuttle mai_;e_Tgine-s (SSME'_s) (serial numbers 2019, 20ee, 20_?), and two Solid RocketEc_,o:_ters (SRB'_s), designated as BI-039. The STS-38 mission7 ,,,_asaclassified Department of Defense mission, a_Td as much, the classified


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events for this mir.--.,si_.,ni.s shc,wn. The -:ignificant problem._ that occuried_.n the Space Shuttle Orbiter subsystem during the missic,n are summarizedand the ofi:icial problem tracking list i.s presented. In additic0n, eachSpace Shutt].e Orbiter problem is cited in the subsystem discussion,


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". NSTS-08308

STS-38SPACE SHUTTLEMISSION REPORT

___vid< Camp_/ Manager,FlightData andEvaluationOffice

D M.Manager, GFE Projects


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INTRODUCTION

The STS-38SpaceShuttleProgramMissionReport containsa summaryof thevehiclesubsystemactivitieson this thirty-seventhflightof the Space Shuttleand the seventhflightof the OrbitervehicleAtlantis(OV-104). In additiontotheAtlantisvehicle,the flightvehicleconsistedof an ExternalTank (ET)(designatedas ET-40/LWT-33),threeSpaceShuttlemain engines(SSME's)(serialnumbers2019, 2022,2027),and two Solid RocketBoosters(SRB's),designatedasBI-039.The STS-38missionwas a classifiedDepartmentof Defensemission,and as such,the classifiedportionsof the missionare not presentedin thisreport.The sequenceof eventsfor this missionis shown in tableI. The reportalsosummarizesthe significantproblemsthatoccurredin the Orbitersubsystemsduring the mission,and the officialproblemtrackingllst is presentedintableII. In addition,each Orbiterproblemis cited in thesubsystemdiscussionwithin the bodyof the report.The crew for this thirty-seventhflightof the Space Shuttlewas RichardO.Covey,Col., USAF, Commander;FrankL. Culbertson,Capt.,USN, Pilot;CharlesD.Gemar,Capt.,U.S. Army, MissionSpecialistI; Robert C. Springer,Col.,USMC,MissionSpecialist2; and Carl J. Meade,Major,USAF,MissionSpecialist3.i- This was the thirdflightfor the Commander,the first flightfor the PilotandMissionSpecialists1 and 3, and thesecond flightfor MissionSpecialist2.

MISSIONSUMMARY

The STS-38missionwas launchedat 319:23:48:15.006G.m.t. (6:48:15p.m.e.s.t.


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The OMS-3 maneuverand two reactioncontrolsubsystem(RCS)maneuversweresatisfactorilycompletedand all parametersremainedwithinacceptableranges.The power reactantstorageand distribution(PRSD)hydrogentank 3 quantitysensorfailedoff-scalehigh. The crew reportedthat the onboardmeteron panel02 also indicatedoff-scalehigh. This failuredid not impact the mission.Circuitbreaker29 on panel L4 openedwhile the vacuum cleanerwas being used.The vacuumcleanerwas subsequentlystowed. No furtheruse was made of thevacuum cleaneror of the electricalsocketinto which it had been plugged.The two-engineOMS-4maneuverwas completedwith nominalperformance.On flightday 3, the RCS hot-firetestwas successfullycompleted. The flightcontrolsystem(FCS) checkoutwas completedusingAPU 3, and performanceof allsubsystemsduring the FCS checkoutwas nominal.During preparationsfor the initialentry opportunityon flightday 4, theswitch talkbackindicationfor generalpurposecomputer(GPC)3 indicatedthatthe GPC failed to go to run. The crew reinitializedtheGPC and returnedit tothe redundantset in which it operatedproperly.Three landingopportunitieswere canceledon flightday 4 becauseofunacceptableweatherconditionsfor landingat EdwardsAir Force Base. On thefirstopportunity,the headwindsexceededthe flightrule limitof 25 kts onrunways22 and 23. Excessivecrosswindsas well as winds varyingfrom theforecastcaused the cancellationof landingon the secondand thirdopportunities,and the missionwas extendedone day.Weather forecastsfor landingat EdwardsAir ForceBase on flightday 5 showedunfavorablewinds on all runways. As a result,the decisionwas made to changethe primarylandingsite to KennedySpace Center becauseof the very favorableweatherconditionsexistingat thatlandingsite.


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VEHICLEPERFORMANCE

SOLIDROCKETB00STERS/REDESIGNEDSOLIDROCKETMOTORSAll solid rocketbooster(SRB)systemsperformedas expected. Power-upof alligniter,jointand case heaterswas accomplishedroutinely. All redesignedsolidrocketmotor (RSRM)temperatureswere maintainedwithinacceptablelimitsthroughoutthe countdown. Groundpurgesmaintainedthe nozzlebearingandflexibleboot temperatureswithin the requiredlaunchcommitcriteria(LCC)ranges. The SRB prelaunchcountdownwas normal,and twoRSRM in-flightanomalieshave been identified. RSRM propulsionperformancewas well withintherequiredspecificationlimits,and thepropellantburn rate for each RSRM wasnormal. RSRM thrustdifferentialsduringthebuildup,steadystate and tailoffphaseswere well withinspecifications.All SRB thrustvectorcontrolprelaunchconditionsand flightperformancerequirementswere met with amplemargins. Allelectricalfunctionswere performedproperly. No SRB or SRM LCC or Operationsand MaintenanceRequirementsand SpecificationsDocument(0MRSD)violationsoccurred.The SRB flightstructuraltemperatureresponsewas as expected. Postflightinspectionof the recoveredhardwareindicatedthat the SRB thermalprotectionsystem (TPS)performedproperlyduringascentwlth very littleTPS acreageablation. Separationsubsystemperformancewas normalwith all boosterseparationmotorsexpendedand all separationbolts severed. Nose cap jettison,-- frustumseparationand nozzlejettisonoccurrednormallyon each SRB.The entryand decelerationsequencewas properlyperformedon both SRB's,withsubsequentparachutedeploymenton each SRB being performedsatisfactorily.TheSRB'swere successfullyrecoveredand returnedto KSC for disassembly.The two in-flightanomaliesthatwere identifiedwere as follows:


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TPS performance was as expected for the existing ambient conditions. There wereno LCC or OMRSD violations during the countdown. No significant ET problemshave been identified.ET flight performance was excellent. All ET electrical equipment andinstrumentation performed satisfactorily. The operation of the ET heaters andpurges was monitored and all performed properly.The ET pressurization system functioned properly throughout the engine start andflight phases. The minimum liquid oxygen ullage pressure experienced during theperiod of the ullage pressure slump was 13.5 psid.The ET tumble system was inactive on this flight. Radar data from Bermuda andAntigua confirmed that the ET did not tumble. The ET entry and rupture/breakupdata are not available, but ET entry and breakup was within the expectedfootprint.

SPACE SHUTTLE MAIN ENGINEAll prelaunch operations associated with the SSME's were executed successfully.Launch ground support equipment provided adequate control for the SSME's duringlaunch preparation. All SSME parameters appeared to be normal throughout theprelaunch countdown, comparing very well with prelaunch parameters observed onprevious flights. All engine-related conditions for engine start were achievedat the proper time, all LCC were met, and engine start and thrust buildup werenormal. -Flight data indicate that SSME performance during mainstage, throttling,shutdown and propellant dump operations was well within specification. Allthree engines started and operated normally. High pressure oxidizer turbopumpand high pressure fuel turbopump temperatures were normal throughout the periodof engine operation.


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Prior to SRB separation, the SRB S&A devices were safed and SRB system power wasturned off as planned. The ET system remained active until ET separation fromthe Orbiter.

ORBITER SUBSYSTEM PERFORMANCEMain Propulsion System

On June 29, 1990, the first STS-38 tanking test was conducted as a precautionarymeasure because of the hydrogen leak that was discovered on STS-35 (0V-102).During the test, unacceptable hydrogen concentration readings were recorded onthe external liquid hydrogen umbilical drag-on sensors. Two more tanking testswere conducted (July 13 and July 25) in an attempt to isolate the source of theexternal leakage. The Orbiter was demated from the ETISRB stack and the ET17-inch disconnect and ET feedline were removed and sent to Marshall SpaceFlight Center for testing that revealed that the follower arm seal and shaftseal were leaking. The new ET disconnect were installed, and a successfultanking test (fourth) was performed on October 24, 1990.The overall performance of the main propulsion system (MPS) was excellent.All pretanking purges were properly performed and liquid oxygen and liquidhydrogen loading was performed with no stop flows or reverts. There were noOMRSD or LCC violations identified.A comparison of the calculated propellant loads at the end of replenish versus

I- the inventory loads showed in a loading accuracy of +0.047 percent for liquidhydrogen and -0.004 percent for liquid oxygen. Throughout the preflightoperations, no significant hazardous gas concentrations were detected, and themaximum hydrogen level in the Orbiter aft compartment was 237 ppm, whichcompares very well with previous data for this vehicle.


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0ut-of-specification response times were noted for the liquid oxygen and liquidhydrogen outboard fill and drain valves (PI0 and Pll) at vacuum inertinitiation. The specification requires a minimum response time of no less than2.9 seconds, and the response times were 2.771 and 2.510 seconds for PIO andPll, respectively. These short response times did not impact the mission oroperation of the valves as the valves are certified under anti-slam conditions.

Reaction Control SubsystemThe performance of the RCS was satisfactory with one anomaly noted. A total of5124 lb of propellant was consumed with no forward RCS dump firing beingperformed. Primary thruster RIU chamber pressure was below the nominal 150 psiaby approximately 20 psi (Flight Problem STS-38-07). This occurred consistentlyfor several pulses on entry day. Earlier data were nominal. Thruster RIU wasplaced in last priority for entry usage and the anomaly did not impact themission. In addition, thrusters R3D, R4U, and F3L all showed transient periodsof low chamber pressure, and the discussion of the anomalous operation of thesethree thrusters is also a part of flight problem STS-38-07.

Orbital Maneuvering SubsystemThe OMS operated satisfactorily throughout the mission. No anomalies wererecorded; however, both forward fuel probes failed. These units, which are notconsidered to be critical, have failed for several missions and will be replacedon an opportunity basis. During prelaunch operations, the left-hand gaseousnitrogenfill/ventvalveleakagewasabout83scchandshouldnothavebeenmore x--than15 scch. Thisconditionwas waivedto flyas-is,and no significantdecreasein nitrogenpressurewas notedduringthemission.Fivedual-engine0MSmaneuverswereperformedduringthemissionwithnominalperformance.A totalof 13,458ib of propellantswereconsumedduringthemission.


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Fuel Cell PowerplantSubsystemThe fuel cell powerplantsubsystemsatisfactorilysupportedthe ll8-hourmission. Two incidentsoccurredwithin the fuel cell subsystemduringthemission. The oxygenflowmeterfor fuel cell 3 indicatedincorrectflow ratereadings,and fuel cell 1 hydrogenpump motor voltageindicationprior to launchwas within one data bit of exceedingthe LCC. Neitherof theseconditionsimpactedthemission.The fuel cells produced1570kwh of electricalenergyand 1214 ib of potablewater from 1079ib of oxygenand 135 Ib of hydrogen. The averagetotalOrbiterelectricalpower was 13.3kW and 416 A. The fuel cellsremainedpoweredup forapproximately34 hoursafterlanding.

AuxiliaryPowerUnit SubsystemThe APU subsystemperformancewas satisfactoryduringthe mission. Threeanomalieswere noted duringthe mission,none of which impactedthe mission.The followingtableshows the run timeand fuelconsumptionfor each APU duringthe flight.

APU 1 APU 2 APU 3Flight phase Time, Fuel Time, Fuel Time, Fuelmin:sec consumption,min:sec [consumption,min:sec consumption,Ib ib ib_- Ascent 00:19:27 46 00:21:12 59 00:19:26 51FCS checkout 00:05:09 17Entryscrub 00:00:38 1

Entry 01:15:50 131 00:58:09 137 00:58:09 121Totala 01:35:55 178 01:19:21 196 01:22:44 189a A total of 14 minutes19 secondsof run time occurredafter landing.


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HFdraulics/Water Spray Boiler SubsystemThe hydraulics/water spray boiler subsystem performed nominally with theexception of the system 2 WSB core freeze-up that occurred during ascent whileoperating on controller A. Also, the APU lubrication oil was not cooledadequately following main engine cutoff (Flight Problem STS-38-01). When WSBcontroller B was selected, cooling the lubrication oil outlet and bearingtemperatures began I minute 6 seconds after the switchover. Controller A wasused on all three WSB's during entry and all WSB operations were nominal.

Pyrotechnics SubsystemThe pyrotechnics subsystem operated nominally.

Environmental Control and Life Support SubsystemAnalysis of the flight data shows that the performance of the atmosphericrevitalization system, pressure control systems, and active thermal controlsystems was satisfactory. One heater anomaly was identified on the flashevaporator system B water supply accumulator in which heater strings 1 and 2showed a shift in the control band (Flight Problem STS-38-02).Early in the mission, the flash evaporator system (FES) secondary feedline watersupply accumulator temperature measurement dropped below 50 F. When the heatersystem was switched from heater string I to 2, the temperature slowly recovered.In addition, the supply and waste water systems were managed successfullythrough the use of the overboard dump system and flash evaporator system. Foursupply water dumps and one waste water dump were made.The potable water quantity transducer in tank C indicated an instantaneouschange to a high value. A mechanical problem is suspected in the transducermechanism. This condition did not impact the mission.


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Avionics and Software SubsTstemsThe avionics and software subsystems performed nominally; however, several minoranomalous conditions were noted during the mission.The integrated guidance, navigation and control subsystem performance wassatisfactory for all phases of the mission. The flight control subsystem (FCS)performance was satisfactory during all phases of the mission includingoperations during the FCS checkout two days prior to entry.The performance of the inertial measurement units and the star trackers was alsosatisfactory in all respects. Two minor problems were noted during preparationsfor entry when operating the data processing subsystem/flight software. Whenactivating general purpose computer (GPC) 3 during deorbit preparations, theGPC 3 talkback did not indicate run when the GPCwas taken from halt to standby.A GPC initial program load was performed and the GPCoperated properly.Analysis of the dump from GPC 3 indicated that the GPC was not allowed tocomplete standby processing during freeze-dry procedures. The problem did notimpact the mission. Also, during the IPL of GPC 3, a temporary loss ofcommunications occurred. This condition was caused by the stored programcommand not completing execution prior to the backup flight system GPC beinggiven the payload data busses. Crew action reenabled communications.The electrical power distribution and control subsystem operated normally;however, two anomalies were noted. The short circuit in the vacuum cleaner

- (flight problem STS-38-04a), which caused circuit breaker 29 on panel L4 toopen, is discussed in the Plight Crew Equipment section of this report.Approximately 1 minute prior to landing, the main bus A mid power controller 1current dropped to zero (Plight Problem STS-38-03c). No change in fuel cell 1current was noted when this event occurred, indicating a sensor failure.At approximately T-20 minutes in the final countdown, the fuel cell 1 hydrogen


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The operational instrumentation subsystem performed nominally during themission, except for APU instrumentation problems (Plight Problem STS-38-05) thatare discussed in the Auxiliary Power Unit Subsystem section of this report.A tire pressure fault detection annunciator (FDA) message was annunciatedcontinuously after landing (Plight Problem STS-38-08). Inspection of the tirepressure connectors showed no anomalous condition existed in that part of thesubsystem.

Communications and Tracking SubsystemThe communications and tracking subsystem performance was satisfactory with twominor problems and one anomaly noted during the mission.A Ku-band power amplifier problem was noted, and the problem was isolated to acircuit breaker which had not been closed. The crew closed the circuit breakerand subsequent subsystem performance was nominal.Closed-circuit television (CCTV) cameras C and D were reported by the crew to bemalfunctioning (Plight Problem STS-38-4c and -4d, respectively). Camera C couldnot be focused by the crew, and camera D had no indication of power. The crewcycled the TV system power and these problems were corrected. The two camerasoperated properly for the remainder of the flight.An over-current condition in the low-voltage power supply of TV monitor 2 wasnoted (Plight Problem STS-38-O4b). The crew performed malfunction procedures, --but satisfactory monitor operation was not recovered. Monitor 1 was used forthe remainder of the mission.

MechanicalSubsystemsThe performanceof the mechanicalsubsystemswas nominalthroughoutthe missionexcept for one anomalythatoccurredat OPS 9 transitionafter landing.


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AerodynamicsAscent and entry aerodynamics were nominal in all respects with the vehicleresponding as expected.

Thermal Control SubsystemAll Orbiter structural and component temperatures were maintained withinacceptable limits throughout the mission; however, one anomaly was noted duringdata evaluation. The flash evaporator system (FES) secondary feedline watersupply accumulator heater indicated on-orbit cycling in a lower and narrowerband (48 o to 54 F) than the nominal band of 55 o to 75 F (Flight ProblemSTS-38-02). Since other measures of this heater's performance appeared nominaland the off-nominal temperature response was observed on both heater systems,it was postulated that this response may have been the result of a faultysensor. This postulation was confirmed during postflight turnaround activities.

Aerodynamic Heating and Thermal Interface TemperaturesAnalysis of heating data indicated nominal aerodynamic and plume heating, butanalysis of these data are continuing. Aerodynamic heating on the SSME nozzleswas within the TPS limits based on data analysis and the postflight inspection.All thermal interface temperatures (ET/Orbiter) were maintained withinacceptable limits during prelaunch operations and ascent. No LCC were violated

o--I and all OMRSD requirements were met. In addition, all Orbiter/SSME hydraulicinterface temperatures were maintained within the nominal limits established ininterface control documentation.

AerothermodTnamics and Thermal Protection SubsystemAcreage heating was'nominal during entry with nominal structural temperaturerises observed in the data. Postflight inspection and analysis revealed that


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Overall,all reusablecarboncarbon (RCC)parts appearednormal. A gap wasevidentaround the chin panel441 gap filler. The noselandinggear door TPSwas in good conditionwith only one looseNicalonsacrificialthermalbarrierpatch. The rightmain landinggear door thermalbarrieroutboardsectionhadtwo breachedareas. The ET door thermalbarrierswere in good conditionwithevidenceof a minor flow path on the right-handbarrier. No evidenceof damagewas apparentfrom the ice seen in the debris films. The elevon cove TPS andelevon-elevongap tileswere all in good condition. Six left-handrudder speedbrake (trailingedge) tiles had a brokencoating. The engine-mountedheatshield thermalcurtainswere damagedon all threeengineswith the worst damageon engine two. The uppersurfaceand OMS pod TPS was in good condition.Orbiterwindows2 and 5 were lightlyhazed,and moderatehaze was found onwindows3 and 4.

FLIGHTCREWEOUIPMENTThe flightcrew equipmentperformednominallyexcept for thevacuumcleaneranda minor water leak in thegalley.When the crew compartmentvacuumcleanerwas turnedon at 321:02:29G.m.t.,circuitbreaker29 on panelL4 opened(FlightProblemSTS-38-O4a). Data reviewindicatedthata short existedin the vacuum cleanermotor;however,as aprecautionarymeasure, the outlet to which the vacuumcleanerwas connectedwasnot used for the remainderof the mission. Alternateprocedureswere used tocleanscreens,etc., after loss of the vacuumcleaner. Postflighttestingrevealeda short circuitin the vacuumcleanermotor.A small water leak was notedat the MV3 valve in the galley. This leak issimilarto thatnoted on STS-41. The leak was wipedup with a toweland theleak did not impact the use of thegalleyin any manner.The crew also reportedthat the galleyrehydratlonstationinitiallydispensed


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Six video films plus NASA select video of the landing at KSC were reviewed andno anomalies were noted. Also, seven films of landing were reviewed, and noanomalies were noted. Sink rates could not be determined as the KSC cameraconfiguration was not compatible for providing these data.

DEVELOPMENT TEST OBJECTIVES AND DETAILED SUPPLEMENTARY OBJECTIVES

DEVELOPMENT TEST OBJECTIVESThree of the five planned development test objectives (DT0's) were completed.DTO 301 - Ascent Structural Capability Evaluation - The objective of DTO 301 isto verify the adequacy of the Shuttle structural capability at (or near) designconditions. Data were recorded during flight, and the evaluation is underway.DTO 309 - Ascent Flutter Boundary Evaluation (Test 4) - The objective of DTO 309is to verify Shuttle performance near the ascent flutter boundary. Data wererecorded for the period of interest, and the evaluation is underway.DTO 517 - Hot Nosewheel Steering Runway Evaluation - DTO 517 was not performedbecause of the KSC landing.DTO 785 - BUD Backup to COAS - The objective of DTO 785 is to verify the

_-- suitability of the head up display (BUD) as a substitute star-sighting deviceto replace the crewman optical alignment sight (COAS) when performing inertialmeasurement unit alignments. The DTO was successfully completed and the dataevaluation is underway.

(DTO 805 - Crosswind Landing Performance - DTO 805 was not performed.


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TABLEI.-STS-38 SEQUENCEOF EVENTS

Event Description Actual time,G.m.t.APU activation APU-IGG chamberpressure 319:23:43:24.25APU-2 GG chamberpressure 319:23:43:25.91APU-3GG chamberpressure 319:23:43:27.14SRB HPU activation LH HPU systemA start command 319:23:47:47.24LH HPU systemB start command 318:23:47:47.30RH HPU systemA start command 319:23:47:47.52RH BPU systemB start command 319:23:47:47.55Main propulsion Engine 3 start commandto EIU 319:23:48:08.436Systemstart Engine 2 start commandto EIU 319:23:48:08.578Engine I start commandto EIU 319:23:48:08.692SRB ignition command SRB ignition commandto SRB 319:23:48.15.006(lift-off)

Throttleup to Engine 3 commandaccepted 319:23:48:18:916104 percentthrust Engine 2 commandaccepted 319:23:48:18.939Engine 1 commandaccepted 319:23:48:18.933Throttledown to Engine 3 commandaccepted 319:23:48:41.15772 percentthrust Engine 2 commandaccepted 319:23:48:41.179Engine I commandaccepted 319:23:48:41.173Maximumdynamic Derivedascentdynamic 319:23:49:04pressure(q) pressureThrottleup to Engine 3 commandaccepted 319:23:49:17.158104 percentthrust Engine 2 commandaccepted 319:23:49:17.180Engine 1 commandaccepted 319:23:49:17.174 -Both SRld'schamber LH SRM chamberpressure 319:23:50:13.61pressureat 50 psi mid-rangeselectRH SRM chamberpressure 319:23:50:13.33mid-rangeselectEnd SRM action LH SRM chamberpressure 319:23:50:16.376mid-rangeselectRH SRM chamberpressure 319:23:50:16.129


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TABLEI.- CONTINUED

Event Description Actual time,G.m.t.OMS-I cutoff Left engine bi-prop valve 320:00:00:06.8positionRightenginebi-propvalve 320:00:00:06.6positionAPUdeactivation APU-IGG chamberpressure 320:00:02:51.59

APU-2 GG chamber pressure 320:00:04:38.12APU-3 GG chamber pressure 320:00:02:52.830MS-2ignition Leftenginebi-propvalve 320:00:25:48.2

positionRightenginebi-propvalve 320:00:25:48.2position0MS-2 cutoff Left engine bi-prop valve 320:00:27:21.0positionRight engine bi-prop valve 320:00:27:20.8positionFlight controlsystemcheckoutAPU start APU-3GG chamberpressure 322:20:24:48.60APUstop APU-3GG chamberpressure 322:2029:57.14APU activation APU-I GG chamber pressure 324:20:41:14.41for entry APU-2 GG chamber pressure 324:20:58:56.02APU-3GG chamberpressure 324:20:58:56.89._ Deorbit maneuver Left engine bi-prop valve 324:20:46:15ignition positionRight engine bi-prop valve 324:20:46:15

positionDeorbit maneuver Left engine bi-prop valve rcutoff positionRight engine bi-prop valve

positionEntry interface Current orbital altitude 324:21:11:52


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TABLE II.- STS-38PROBLEMTRACKINGSUMMARY

Number Title Reference Comments

STS-38-01 WaterSpray Boiler(WSB}2 Ascent WSB 2A failedto cool APU lubricationoil afterend of the pool boilingnot CoollngWhilo on IM 38RF01 periodduringascent. WSB was switchedto B controllerand APU 2 was, ControllerA lefton afterAPt/1 and 3 were shutdown. Effectivelubricationeoilcoolingwas obtainedI minute6 secondsafterthe switchto8 controller.Analysiscontinuing. Fly as is. Workednominallyduringentry. Apparentspraybar freeze-upon ascent. Removeandreplace.

STS-38-02 FES Water Supply 320:02:00 G.m.t. Heater 1 did not cycle within its prescribed range of 55-75 F.AccumulatorHeaterSystem IN 38RF02 When temperaturereached49 F, string2 was activated. String2BiasedLow PR ECL4-08-0462 cycledin 48-54F rangewith normalappearingduty cycles. Suspecttemperaturesensor (V63TI760A)problem. Temperaturesensorfounddebonded.STS-38-03 Instrumentation:a) PRSD H2 Tank 3 a) 320:07:05G.m.t.a} Transducerwent from 97 percentto off-scaleduringLOS. CrewQuantityTransducer IPR 37V-0005 verifiedpanel meterreactingoff-scale,too.Fall Off-Scale IM 38RF03PR FCP 4-08-0124

b} APU 3 X-Axls b} 324:21:10G.m.t.b} Accelerationtraceerraticduringentry. KSC to check connectors.AccolerometerErratic IM38RF04 APU 3 beingremovedand replaceddue to life/timecycle.PR APU 4-08-0223

c} _q_AMPClAmps c) 324:21:41G.m.t.c) One minuteprior to landing,the MNAMPCI currentdroppedto zeroTransducerFailure PR EPD 4-08-0864 {V76C3085A}.No changein fuelcell Iamps detected. OPS STATS_-_ IM38RF07 did not go to zero. Removeand replacetransducer.O_

STS-38-04 GFE:a} VacutumCleanerShort a} 321:02:29G.m.t.a} When crewturnedvacuumcleaneron, CB 29 on panel L4 was openedCircuit FIARBFCE-213-F005 open by a currentsurge. No furtheruse of utilityoutletEPD-4-08-184 MOI3Q for remainderof flight. KSCto performCt4RSDV76AWO.030-B.Outlettest completeand nominal. Vacuumremovedand shipped11/21. Troubleshootingfoundshortof phaseB to case in thevacuumcleaner.

b} ClosedCircuitTV b} 321:19:52G.m.t.b} Fault lightcame on indicatingmonitorovertemperatureor under-Monitor2 Fault Light FIAR BFCE-029-F020 voltage. Crew performedmalfunctionprocedureand faultlightOn IPR 37V-0001 didn'tclear. Monitor2 poweredoff for remainderof mission.Failure reproducedat KSC. Removeand replacemonitor.

c} CameraC Failedto 320:03:51G.m.t. c} Duringfirstattemptto use cameraC, the crew was unable to focusFocus FIARBFCE 029-FO21 the camera. CameraC focuscapabilitywas regainedwhen CCTVsystemwas powercycled.d) Camera D - No Power 320:03:51G.m.t. d} When crew poweredup cameraD, therewas no indicationofpowerFIAR BFCE 029-FO23 to the camera(i.e.,no lightsfor ALC or ganuna).Crew power-

cycledthe CCTVsystemand recoveredthe camerafor the remainderof the flight. Postflight,crewconunentedthat a similarproblemwas seenduringpreflighttesting. Testplan is in work


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TABLE II.- STS-38 PROBLEMTRACKINGSUMMARY

Number Title Reference Co._ents

STS-38-05 APU Instrumentation 321:23:48G.m.t. APU 2 exhaustgas temperaturesensors(EGT's)I & 2 (V46T0242AandInteraction EGT's V46T0240A)andAPU 2 and 3 injectortubeten_eratures(V46T0274AandIPR 37V-0008 V46T0374A|becameerraticduringlaunch. AnalysisshowsmomentaryIM38RF05 shorting-to-groundof EGT'sdrove tube temperatureserratic. Noproblemwithinjectormeasurement,onlyEGT's.

STS-38-06 RightVent Door I and 2 324:22:06G.m.t. Duringpostlandingventdoorpurgepositioningoperation,the rightPurge PositionFailure PRMEQ 4-08-0319 ventdoorI and 2 droveto the closedpositioninsteadof the purgeIM38RF06 position. KSC troubleshootingreproducedproblem. Failureisolatedto purgepositionlimitswitch. Removeand replaceactuator.

STS-38-07 ThrusterRIU Low Chamber 324:19:57G.m.t. RIU showeda degradedchamberpressureby approximately20 psi. RIUPressure. ThrustersR3D, IM38RF08 will be investigatedand the resultswilldrivethe testingrequiredR4U and F3L TransientLow for the otherthreethrusters. Visualinspectionshowedno anomalies.ChamberPressure Chamberdecaytest of RIU showedno leak. Willborescopeand performthreepointcalibrationon the transducer.Pod RP03 now on OV-103,

and tastingwill be done on thatvehicle.STS-38-08 Continuous"TirePress" 324:21:50G.m.t. Messageannunciatedcontinuously,should annunciateonce. KSC

FDAMessagas Post-landing inspectionof tire pressureconnectorsshowno problem.STS-38-09 smeke Detector Transient Mission Duration Several smoke detectors had event indicators go high, but not highEvent Indications PR ECL 4-08-0460 enoughto triggeralarm. No correspondingincreasein smoke

"4 concentrationsnoted. Removesmokedetectorfromcabinheat exchangerfor analysis. Similar problem seen on STS-32.


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NASA Headquarters CA4/R.Filler ES6/C.W. Norris(2) ZR/Lt.Col.J. McLeroy R. Birman McDonnellDouglas-HoustonQP/B.Greenly CB/D.Brandenstein(I0)PA/R.L. Berry ZRI2/J.A. annie GeneralElectricCo. D2/M.D.PipherQP/R.Perry CB/K.Colgan PA/J.R. German BARR/R.Culpepper SpaceDivision T3A/A.D. HockenburyQT/M.Greenfield CB/R.Covey (5) PT3/S.Morris BARR/H.Jones P.O. Box 8555LB-4/G.L.Roth CB/T.Henricks ET/C.A. Graves,Jr. (8) BARR/R.Herman Philadelphia,PA 19101 D. MolgeardMA/R.L. Crippen DA/Library EK/SSDLibrary EelS/HamiltonStandard 2525BayAreaBlvd.MO/R.Nygren DA2/T.W. Holloway DJ/J.W. Seyl (2) R. Hoey Suite620MOJ/C.Perry DA3/S.G. Bales GA/L.S. Nicholson ExternalDistribution 6510TestWing/TEG/236 Houston,TX 77058ML/W.Hamby DA3/R.K. Holkan GA/J.H. Greene Mr. WillisM. Hawkins EdwardsAFB,CA 93523MES/N.Frandsen DAS/R.Legler GM/D.C. Schultz SeniorAdvisor L.R. Adkins/IBMBldgDAB/Library JL4/R.L. Squires LockheedCorporation Headquarters,SpaceDiv MailCode6206GoddardSpaceFltCtr DF/J.Knight JM2/Library(3) P.O. Box 551 Attn.: SSD/CLP 3700 BayAreaBoulevard_00/R.L. Bauman DF/D.Nelson D_3/T.R. Loe (3) Burbank,CA 91520 Los AngelesAF Station Houston,TX 77058700/J.R. Busse DF7/P.Coma NA/C.S. Harlan P.O. BOx 92960710/T.E. Huber DF72/Q.Carelock NB/D.L. Duston RussellA. Larson WorldwayPostalCenter JamesR.Womack730/E.I. Powers DG/J.A. Wegener ND/M.C. Perry MailStop4A Los Angeles,CA 90009 JPL/233-307730.1/3.P.Young DH4/R.D. Snyder NS/D.W. Whittle CharlesStarkDraperLab. 4800OakGroveDr400/D.W. Harris DH411/E.B. Pippert SA/C.L. Huntoon Inc. JohnWilliams Pasadena,CA 91109400/P.T. Burr DH4/J.F. _hitely SD/S.L. Pool 555 TechnologySquare 1995FerndalePlace410/J.Barrowman(6) 13_45/M.LeBlanc SD2/J.R. Davis Cambridge,MA 02139 ThousandsOaks,CA 91360 T. Myers,Sys Tech,Inc.302/W.F. Bangs DG47/SimSup'e SD24/D.A. Rushing 13766So. HawthorneBlvd.313/R.Marriott DM/J.C. Harpold SD4/N.Cintron Lt. Gen.LeightonI. DavisC.Woodland,Prog.Mgr. Hawthorne,CA 90250DM/C.F. Deiterlch SD5/J.Charles USAF (Ret.) SPARAerospaceLimitedKSC EA/H.O. Pohl SE/J.H. Langford 729 StagecoachRoad, 1235OrmondDrive Mr. JamesV. ZiEmermanNwSI-D/Respository(25) EC/W.E. Ellis SNI5/D.Pitts FourHills Weston,Ontario NASA EuropeanRopMK/B.H. Shaw EC/F.H. Samenski SP/C.D. Perner(5) Albuquerque,_ 87123 Canada,M9L 2W6 c/o AmericanEmbassyEC3/D.F. Hughes TA/C.H. La_d_ert APO New York,NY 09777MSFC EC2/M.Rodriguez TC3/J.Lowe Mr. IraGrantHedrick DarrylStricklandCN22D/Respository(30} EC4/L.O. Casey TJ/L.E. Ball PresidentialAssistantfor P. O. BOx 1940 CommandingGeneralEP51/J.Redus(5) EC3/E.Winkler TJ2/G.W. Sanders CorporateTechnology NorthHighlands,CA U.S. ArmyLogisticsCenterEL74/P.Hoag (5) EC6/J.W. McBarron(5) TM2/J.Bates GrtumuanAerospaceCorp 95660-8940 Attn: ATCL-PS/Col.SenegalFA51/S.P. Sauchier EC3/D.M. Hoy VA/D.M. Germany Bathpage,NY 11714 Ft. Lee,VA 238001-6000JA01/J.A. Downey EG3/R.Barton VA/J.C. Boykin A.S. Jones(2}SA12/O.E. Henson EE/J.Griffin VA/G.A. Coultas Dr. SeyuourC. HiJmel SPARAerospaceLimited Capt. J. BohlingEE2/H.A. Vang VE/P.C. Glynn 12700LakeAvenue,#1501 1235OrmontDr. 6555ASTG/SMSPLan_le_ResearchCenter EE3/A.Steiner VE3/M.C. Coody Lakewood,OH 44107 Weston,Ontario, Cape CanaveralAFS,FL.TechnicalLibrary/ EE3/P.Shack VE4/W.H. Taylor CanadaM9L 2W6 32925Mail Stop185 EE3/T.W. Early VF/D.W. Camp Mr. JohnF. McDonaldEE6/L.Leonard VF2/W.J. Gaylor VicePresident-TechnicalJ.Middleton R.A. ColonnaRockwell-Downey EE6/R.Nuss VF2/J.W. Mistrot Services SPARAerospaceLimited U.S. EmbassyAD75/DataManagement(55)EE7/O.L. Schmidt VF2/B.Johnson TigerAir,Inc. 1700OrmontDrive Box 14

EET/J.C. Dallas VF2/C.Critzos 3000NorthClaybournAve Weston,Ontario, APORockwell-Houston EK/I.Burtzlaff VF2/K.E. Kau_nski(25) Burbank,CA 91505 CanadaMgL 2W7 San Francisco,CAR12A-130/J.C. Snowden ET5/J.A. Lawrence VF3/D.W. Camp (5} 96404-0006R12A-130/J.P. Shea EG/K.J. Cox VF3/T.Welch Dr. JohnG. Stewart N. PargmtZC01/D.McCormack EG2/L.B. McWhorter VF3/M.Engle Manager,Officeof 5907SunriseDrive USAFRI6D/J.Woodard EG4/J.E. Yeo VF4/E.R. Hischke Planningand Budget Fairway,Kansas66205 2ndSpaceWing/DCK)SR208/R.Pechacek EK5/W.N. Trahan VF4/R.W. Fricke TVA E6C9 FalconAFB, CO.R20B/K.M. Rahman EP/C.A. Vaughn VF5/S.M. Andrich 400 CommerceAvenue R. Peterson

EP2/H.J. Brasseaux VG/F.Littleton Knoxville,TN 37902 MailStop 351-4AJSC EP2/L.Jenkins VK/C.G. Jenkins HoneywellInc.AA/A.Cohen EPS/T.L. Davies VP/C.McCullough(3) TRW 13350Hwy 19AC/D.A. Nebrig EP5/N.Faget VPI2/D.Flits Houston,TX 77058 Clearwater,FL 34624AC5/J.W. Young ER/W.W. Guy VR/D.D. Ewart Attn: C. Peterson/H5APJ/J.E.Riley(4) ES/D.C.Wade _VL. G. Williams AerospaceCorporationAP4/B.L. Dean(3) ES/W.G. Mc_llen (2) W_/L.D. Austin P.O. Box 92957BL/W.L. Draper ES3/J.A. Sadth WE/R.D.White LOs Angeles,CA90009BY4/HistoryOffice(2) ES3/C.R. Ortiz _TJ/W.J. Moon Art_n:W. Smith,145/619CA/D.R. Puddy ES3/Y.C. Chang C07/LESCLibraryES3/P. SomaNotify VF4/R. W. Fricko (FTS-525-3313) of any correction, additions, or deletions to this list.

Documents

STS-38 Space Shuttle Mission Report