STS-61C National Space Transportation System Mission Report

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STS 61-CNational SpaceTransportation SystemMission Report

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61-C NATIONAL SPACEMISSION REPORT (NASA)

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N/_ANational Aeronautics andSpace AdministrationLyndon B. Johnson Space CenterHouston, Texas


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NSTS-22301

STS 61-C

NATIONAL SPACE TRANSPORTATION SYSTEM

MISSION REPORT

Michael A. Collins, Jr.Manager, Flight Dataand Evaluation Office

Richard A. ColonnaManager, Orbiter and GFE Projects

Richard H. KohrsDeputy Director,

National STS Program

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONJOHNSON SPACE CENTER

HOUSTON, TEXAS

August 1987


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INTRODUCTION AND MISSION OBJECTIVES

The STS 61-C National Space Transportation System (STS) Mission Report containsa summary of the major activities and accomplishments of the twenty-fourth SpaceShuttle mission and the seventh flight of the OV-102 vehicle, Columbia. Thesequence of events for this flight is shown in table I. The Orbiter problemtracking list is presented in table II.

The major objectives of this flight were to successfully deploy the SATCOMKU-2/Payload Assist Module-Delta Class (PAM-D Ii) and SYNCOM IV-5/UNQ satellitesand to perform the planned operations of the Material Science Laboratory-2(MSL-2). An option was maintained to fly the Getaway Special (GAS) BridgeAssembly (GBA) and the Hitchhiker G-I (HG-I) to replace the SYNCOM, if it wasnot ready for flight. This option was exercised since the SYNCOM-IV-5/UNQ didnot fly during STS 61-C.

The crew for this twenty-fourth Space Shuttle mission were Robert L. Gibson,Commander, U. S. Navy, Commander; Charles F. Bolden, Lt. Col., U. S. Air Force,Pilot; Franklin R. Chang-Dias, Ph. D., Steven A. Hawley, Ph. D., and George D.Nelson, Ph. D., Mission Specialists; Robert J. Cenker and William Nelson,Payload Specialists. Mr. Robert J. Cenker is a representative of the RadioCorporation of American (RCA). Mr. William Nelson is a member of the U. S.House of Representatives.

MISSION SUMMARY

The 5-day STS 61-C mission was planned for launch on December 18, 1985. Thelaunch was scrubbed and rescheduled on six different occasions because ofhardware problems or unacceptable weather. The mission was launche6 on January12, 1986, at 6:55 a. m. e.s.t., and was scheduled for landing 5 days later onJanuary 17, 1986. The final countdown was normal. The ascent phase was normalin all aspects with main engine cutoff (MECO) occurring at the planned time.Both solid rocket boosters were recovered and the external tank impacted withinthe predicted footprint. After the first two planned orbital maneuvering system(OMS) maneuvers were completed, the vehicle was in the planned 175 nmi. circularorbit.

During the first day, the RCA SATCOM-KU satellite predeployment checks werecompleted and the satellite was deployed at the planned time. The MSL-2 carriersystems were activated and operating properly, and the infrared imagingexperiment (IRIE) camera was used on revolutions 3, 4, and 5. Also, of the 12GAS experiments, five were activated. The Hitchhiker-G payload was activatedabout 3.5 hours after launch, and a minor data problem was corrected. Thecapillary pump loop operations appeared nominal, and the particles analysiscameras were operated satisfactorily.


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Flight day 2 operations were conducted in general accordance with the flightplan and consisted mostly of experiment operations. All Orbiter systemsoperated well and no restrictions were imposedon on-orbit operations. TheMSL-2carrier subsystems continued to operate properly and activities with theThree-Axis Acoustic Levitator experiment were completed. Someproblemsdeveloped with the other two experiments on the MSL-2carrier and futureoperations were evaluated. Three more GASexperiments were activated. Also,attempts were madeto monitor the CometHalley.Flight day 3 proceeded smoothly with no vehicle anomalies affecting payloadoperations. Mission Specialist Chang-Diazpresented the first Spanish broadcastwhich consisted of a systems/vehicle tour. Operations with the MSL-2 systemscontinued with an attempt to operate the Electromagnetic Levitator (EML)experiment on sample 4. Proper heatup did not occur and the unit wasdeactivated. No further EMLoperations were planned. AutomatedDirectionalSolidification Furnace (ADSF)operation was also attempted, but it did notindicate proper furnace power levels at the start on sample 4 or whenattemptedagain after stepping to sample I. At this point in the mission, all GASpayloads had been activated. The Argon Injection and Paper Fiber Formationstudent experiment activities were also accomplished. OneCometHalley ActiveMonitoring program (CHAMP)data take was attempted without satisfactory results.An inflight maintenance procedure was not successful in recovering the failedhardware. Consequently, no further CHAMPactivities were planned for theremainder of the flight.Infrared imaging data were taken. The data included cargo bay scenes and aground track on Hawaii. The infrared imaging observations madethe first daywere downlinked and the quality of these observations was excellent.STS61-C orbit operations continued on schedule during the fourth day with aplanned deorbit one day early on January 16. The reaction control system (RCS)hot-fire test and flight control system (FCS) checkout were completed withoutany anomalies. Day 4 experiment activities included ultraviolet experiment scanoperations on three targets plus MSL-2operations with the EMLand ADSF. Themost extensive operations were with the IRIE during numerousobservationalperiods.The flight was extended one day from the flight day 5 planned landing because ofunacceptable weather at KSC. In preparation for landing, the payloads had beendeactivated and secured. Following waveoff, various activities were undertakento reactivate payloads and makeproductive use of the extension day.TheMSLsubsystemswere re-activated successfully and all subsystems operatednominally until the seconddeactivation on day 5. During this period, thecoolant flow rate to the payload heat exchanger was reduced to low flow. Thisled to higher than normal temperatures in the MSLsubsystems; however, thesetemperatures were well within acceptable limits.The IRIE was operated for 45 minutes collecting images of targets ofopportunity. Also, the crystal growth and amateur radio experiments of GAS007were continued.

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Plans for landing at KSCon day 6 were cancelled because of unacceptable weatherconditions, and a decision wasmadeto land one revolution later at EdwardsAFB,CA. Final stowage and preparation for entry were completed as scheduled and the232-second deorbit maneuverwas initiated at IS:12:54:30 G.m.t. _ne entry wasnominal in all respects. After a 195-degree heading alignment circle maneuver,the Orbiter was landed at 18:13:58:51G.m.t. on runway 22 at EdwardsAFB, CA.Rollout required 10,202 feet and lasted 59 seconds. The postlanding inspectionof the Orbiter showedit to be in very g0od condition.

VEHICLE ASSESSMENT

Marshall Space Flight Center (MSFC) has published a detailed evaluation reportcovering the elements for which MSFC has design responsibility. That report isMSFC-RPT-1227 - Space Shuttle STS 61-C (32)-Fiight Evaluation Report - ShuttleProjects dated January 27, 1986.

SOLID ROCKET BOOSTER

The STS 61-C flight utilized lightweight solid rocket motor (SRM) cases. SRMpropulsion performance was normal and within specification limits, withpropellant burn rates for both SRM's near predicted values. Solid rocketbooster (SRB) thrust differentials were within specification throughout theflight.

The SRB support-post loads data at lift-off showed that footpad compression,tension, and bolt loads were within design allowables and were comparable withloads observed on previous flights. The SRB base-moment calculations, based onmobile launch platform (MLP) support strain data, indicated a maximum bendingmoment of 95 percent of design during Space Shuttle main engine (SSME) thrustbuildup.All thrust vector control (TVC) prelaunch redlines were met with ample margins.Analyses verified that the TVC subsystem operated normally.

Evaluation of the electrical and instrumentation system indicates that theignition and separation pyrotechnics fired as planned. The recovery sequencewas performed satisfactorily on both SRB's with pyrotechnic initiation capacitor(PIC) firing and system reset properly initiated. All location aids performednormally. All SRB instrumentation measurements performed properly throughouttheir required flight periods.

The flight structural temperature measurement response was as expected. The SRBthermal protection system (TPS) performed as predicted during ascent with littleor no TPS acreage ablation.

The performance of the separation subsystems was normal with all boosterseparation motors (BSM's) expended and bolts severed. Nose cap jettison,frustum separation, and nozzle jettison occurred normally on each SRB. Alldrogues and main parachutes were recovered and are reusable.

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Analyses indicate that the performance of the Shuttle range safety systemhardware for both SRB's and the ETwas normal.A postflight evaluation of the SRMstructure to determine the extent of damagerevealed the following significant items:

a. A gas path was noted at the 154-degree position of the aft field jointof the left S_M. Soot was found from the 140-degree to the 178-degree position,and soot was found in the primary groove from the 68-degree to the 183-degree(115 degrees arc) position. C-ring damagewas noted at the 154-degree positionwith a maximumerosion depth of 0.00_ inch and erosion length of 3.5 inches.The 0-ring was affected by heat over a 14-inch length in this area.b. A gas path was found from the 273.6-degree to the 309.6-degree (36degrees arc) position of the left S_Mnozzle joint. Soot was found in theprimary 0-ring groove over the entire 360-degree circumference. A potentialimpingement point was located at the 302.4-degree point; however, no 0-ringdamagewas found.c. A gas path was found at the 162-degree point with soot in the primary0-ring groove from the lOS-degree to the 220-degree (112 degrees arc) point onthe right SRMnozzle joint. 0-ring damagewas found at the 162-degree pointwith the maximumerosion depth being 0.011 inch and the erosion length being8 inches. The0-rlng wasaffected by heat over a 26-1nch length in this area.d. A gas path was found on the outer surface of the igniter at the130-degree point of the left SRM. Soot was found on the aft side of the outerGaskoseal, approaching the primary sea! over a 70-degree arc (130 to 200degrees), and on the outer edge of the inner Gaskoseal over a 130-degree arc

(ii0 to 240 degrees), however, no seal damagewas found.e. A gas path was found on the outer surface of the igniter at the250-degree point of the right S_. Soot was found on the inside edge of theouter Gaskoseal over the entire 360-degree circumference, however, it did notprogress beyond the edge of the seal. There was a slight discoloration of themetal on both sides of the seal over the entire 360-degree circumference. Therewas no soot, and no seal d_age found on or near the inner Gaskoseal.EX_fERNALTANK

The external tank propellant loading was accomplished satisfactorily. There wasno excessive ice or frost bul_up. Flight performance was excellent. Entry wasnormal with the impact in the footprint as predicted. Tumbling was verified.All ET prelaunch thermal requirements were met.expected for the existing ambient conditions.were similar to previous flights.

TPSacreage performance was asSkin and componenttemperaturesTwoOperations and Maintenance Requirements and Specifications Document(OMRSD)violations occurred during propellant loading. First, liquid hydrogenullage-pressure transducer no. I read approximately 0.9-psia high during fastfill, thus violating a requirement that all 3 transducers must read within 0.8


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psia of each other. Second, the lower liquid-hydrogen ullage pressurerequirement (40.7 psia) was violated when the pressure cycled to a minimumvalueof 40.2 psia just prior to transition to reduced flow rates. Theseviolationsdid not affect vehicle performance.Liquid oxygen pressure transducer no. 3 experienced intermittent control banddropouts beginning at approximately lift-off + 7.5 minutes for a period of about8 seconds. This occurrence had no impact on vehicle performance.

SPACESHUTTLEMAINENGINEAll prelaunch purge operations were executed successfully. The launch supportground support equipment (GSE)provided adequate control capability for launchpreparation. All conditions for engine start were achieved at the appropriatetimes.All three SSME'sstarted properly. Buildup, mainstage, and shutdown performanceof all engines was within specifications. The SSMEcontrollers provided propercontrol of the engines throughout powered flight.Engine dynamic data generally comparedwell with previous test and flight data,and no problems were identified.All on-orbit activities associated with t_e main engines were accomplishedsuccessfully.

MAINPROPULSIONSYSTEMAll pretanking purges were performed as planned. Liquid oxygen and liquidhydrogen propellant loading, prepressurization, and pressurization systemsperformed satisfactorily. Ullage pressures were maintained within the requiredlimits throughout the flight.Main propulsion system (MPS)performance was satisfactory. Trajectoryreconstruction indicated that the vehicle specific impulse was near the MPSassessment tag values. At main engine cutoff, liquid oxygen residuals were 849ib less than predicted, and liquid hydrogen residuals were 106 ib more thanpredicted.Feed system performance was normal. The liquid oxygen and hydrogen propellantconditions were within specified limits during all phases of operation, and netpositive suction pressure (NPSP)requirements were met.

ORBITEROrbiter subsystem operation during STS61-C was excellent with only minorexceptions (table II). Themost significant problem occurred during theprelaunch countdown on January 6, 1986.At launch minus 4 minutes 40 seconds on January 6, 1986, the closed indicationfor the MPS liquid-oxygen replenish valve was not received. Even though thereplenish valve closed indication was not available, the auto sequencer


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continued operation using other instrumentation to status the position of thevalve. At launch minus 4 minutes 20 seconds, a messageindicated that theinboard fill and drain valve did not close and this resulted in the autosequencer initiating a launch hold. The inboard fill and drain valve was notcommandedclosed because the replenish valve closed indication was not received.A continue commandwas issued at launch minus 2 minutes and 55 seconds thatallowed the liquid oxygen terminal count sequencer to open the tail-service mastvent drain valve without closing the Orbiter inboard fill and drain valve. Thisunknowingly permitted the off-loading of liquid oxygen until the Orbiter inboardfill and drain valve was noted to be open and was then closed. Liquid oxygenprepressurlzation was initiated; however, the ground helium gas supply wasunable to satisfy the control-band pressure requirement because of theullage-volume increase resulting from the rapid off-loading of liquid oxygen.During the llquid-oxygen off-loading, it was recognized that the low-levelcutoff sensors temporarily indicated dry. This was probably caused by thetermination of the helium feedline anti-geyser injector approximately 20 secondsafter the tail-service mast drain valve was open.A hold was initiated at launch minus 31 seconds to review the previousout-of-sequence loading termination and obtain a 5-minute llquld-oxygen drainthrough the main engines. During the hold, the llquld-oxygen maln-englnetemperature dropped below the englne-start requirement of 168.3 degrees R byapproximately 3 degrees. The countdownwas recycled to launch minus 20 minutesand oxygen replenish flow was re-established. The launch was scrubbed when itwas determined that the vehicle could not be recycled within the allowablelaunch window.

PAYLOADS AND EXPERIMENTS

SATCOM-KU SATELLITE

The RCA SATCOM-KU satellite was deployed on time at 12:21:26:29 G.m.t. Therange instrumentation aircraft were on station to monitor the payload assistmodule D-2 firing which was satisfactory. The satellite was placed ingeosynchronous orbit and Began operating satisfactorily.

MATERIALS SCIENCES LABORATORY

The MSL carrier (support) systems were activated on schedule. Of the threeexperiments that were a part of the MSL, only the three-axis acoustic levitator(3AAL) operated normally during the first four days of the mission. Of theremaining two experiments - EML and ADSF - only the ADSF operated for a shorttime on day 2.

HITCHHIKER-G PAYLOAD

The Hitchhiker-G payload, consisting of three individual experiments, operatedvery satisfactorily throughout the STS 61-C mission. Extra data runs werecompleted during the mission extension. As an example of the wealth of dataobtained, 24 data runs were planned for the capillary pump loop (CPL) and 31data runs were completed. Also, the particle analysis cameras were operatedmany more times than planned.

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INFRAREDIMAGINGEXPERIMENTThe IRIE operated very satisfactorily. Downlinked images of the SATCOMdeployment as well as images of the ground scenes provided excellent data forevaluation. All planned activities were completed and the experiment wasreactivated during the mission extension for data gathering of additional scenesof opportunity.

COMETHALLEYACTIVEMONITORINGPROGRAMTheCHAMPexperiment appeared to have failed early in the flight. An inflightmaintenance procedure was performed without success.

GETAWAYSPECIALEXPERIMENTSOnly five of the II Get AwaySpecial (GAS) experiments were operated as plannedduring the STS61-C mission. Twoof the ii GASexperiments have not reportedtheir results as yet to the GASProject Managerat Goddard SpaceFlight Center.The successful experiments were:a. G-O07- ALABAMASPACEANDROCKETCENTER

TheG-007 canister contained four experiments:i. The solidification of alloys were studied for lead antimony and analuminum-copper combination.2. A comparative morphological and anatomical study of the primary root

system of radish seeds was conducted.3. Crystal growth of metallic-appearing needle crystals in an aquaous

solution of potassium tetracyanoplatimate was studied.4. The Marshall Amateur Radio Club provided information on the"Project-Explorer-Payload-Elapsed Time" and the operational status of theexperiments during the flight by downlinking data to all amateur radio stationsand shortwave listeners around the world.

b. G-449 - ST. MARY'S HOSPITAL LASER LABORATORY

There were four parts to this experiment named JULIE (Joint Utilization ofLaser Integrated Experiment):

I. The first, called BMJ, was an experiment to determine the biologicaleffects of neodymium (Nd) and helium-neon (HeNe) laser light upon desiccatedhuman tissue undergoing cosmic radiation bombardment.

2. The second, called LedaJo, was an experiment to determine cosmicradiation effects upon medications and medical/surgical materials.

3. The third, called Bloty, was an experiment to analyze contingencies thatdevelop in blood typing due to zero gravity.

4. The fourth, called Crolo, was an experiment designed to evaluate laseroptical protective eyeware materials, which have been exposed to cosmicradiation.


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c. G-462, 463, and 464 - GSFC/NASAHEADQUARTERSCODEEThe ultraviolet experiment consisted of two scientific instruments and an

avlonies assembly mounted in three adjacent canisters. Canister G-464 containedthe Bowyerultraviolet spectrometer from the University of California, Berkeley.Canister G-463 contained the Feldmanultraviolet spectrometer from Johns HopkinsUniversity. Canister G-462 contained the avionics.d. G-481 - VERTICALHORIZONS

The objective of this experiment was to determine howunprimed canvas,prepared linen canvas, and portions of painted canvas react to space travelunder conditions encountered during Shuttle flight.e. G-470 - GSFC/U.S. DEPARTMENTOFAGRICULTURE

The purpose of this was to expose wild and laboratory research gypsy motheggs and engorged female American dog ticks to weightlessness during the Shuttlemission.The unsuccessful experiments and the reasons for failure were:a. G-062 - GENERALELECTRIC/PENNSTATEUNIVERSITY

This experiment was to have measuredthe effect that convection has uponheat flow in a liquid. The experiment failed for reasons that are unknownatthis time.b. G-332- BOOKERT. WASHINGTONSENIORHIGHSCHOOL

The brine shrimp artemia was flown to determine the behavior andphysiological effects of mierogravity on cysts in space. The experiment faileddue to experiment wiring error.

c. G-494 - NATIONAL RESEARCH COUNSEL OF CANADA

The purpose of this experiment was to measure the 0 and 02 terrestrialnightglow emissions and make Shuttle glow observations. The experiment faileddue to internal high-voltage arcing.

d. EMP - GSFC ENVIRONMENTAL MEASURING PACKAGE

The EMP was to measure the response of the GAS bridge to the Shuttleenvironment during lift-off, on-orbit operations, and landing. This experimentfailed to turn on.

The results of the following experiments are unknown at this time.

a. G-310 - USAF ACADEMY/DEPARTMENT OF ASTRONAUTICS

The objective of this payload was to measure the dynamics of a vibratingbeam in the zero-gravity environment.


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b. G-446- ALL TECHASSOCIATESThe purpose of this experiment was to learn what effect gravity has onparticle dispersion of packing materials in high performance liquidchromotography analytical columns.

LAUNCH AND LANDING DELAYS

As shown in table III, the STS 61-C mission was originally scheduled for launchon December 18, 1985, but the countdown was behind schedule because of Orbitercloseout work and the launch was rescheduled for December 19, 1985. A turbineoverspeed problem developed in the SRB hydraulic power unit, forcing the launchto be rescheduled to January 4, 1986. Subsequent scheduling moved this date toJanuary 6, 1986. Launch vehicle and facility problems delayed the launch to thepoint that the payload had reached the end of its launch window and the missionwas rescheduled for January 7, 1986. Unacceptable weather conditions at KennedySpace Center (KSC) and the trans-Atlantic abort sites caused a recycle of thelaunch to January I0, 1986. Because of unacceptable weather again at KSC, thelaunch was recycled to January 12, 1986. Lift-off occurred at 6:55 a. m. e.s.t.on January 12, 1986.

The landing was rescheduled from January 17 to January 16, 1986, to saveturnaround time at KSC. However, unacceptable weather resulted in schedulingthe landing for January 17, 1986, at KSC. Again unacceptable weather played arole in delaying the landing until January 18, 1986.

As final preparations were made for a landing at KSC on January 18, 1986, theweather was again determined to be unacceptable. The landing was delayed onerevolution and moved to Edwards Air Force Base, California, where it wascompleted satisfactorily.

STS 61-C DETAILED TEST OBJECTIVES

All Orbiter detailed test objectives (DTO's) assigned to this flight wereaccomplished with the exception of 0237, Forward Reaction Control System (RCS)Flight Test.

The following DTO's required special test conditions or crew activity.

0237-Forward RCS Flight Test. This DTO required a series of five shortprogrammed test input (PTI)-controlled forward RCS firings during entry as afirst step in demonstrating a return-to-launch-site/trans-Atlantic abortforward-RCS dump capability. The DTO was cancelled because it was discoveredthat the two left-forward RCS thrusters had titanium splitters which could causeZOT's with the last three PTI's, and a separate concern that the first two PTI'swould cause TPS scorching which could impact an already tight turnaroundschedule.

0309-Ascent Flutter Boundary Evaluation. This DTO required that structuralPTI's be executed during a high Q bar ascent to evaluate the ascent flutterboundary. The ascent was designed to produce a higher Q bar than on previousflights and OV-I02 was instrumented for flutter.


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0312-ETTPSPerformance. This DTOrequired a +X translation after ET separationso that photographs of the ET TPScould be taken with a 35mmcameramounted inthe Orbiter umbilical well.0321-CrewCompartmentStructure Deflection Investigation. This DTOrequired thecrew to measure the distortion of the cabin to determine the cause oflocker-door binding problems.0901-OEXSILTS. The SILTSexperiment was operated as planned during entry.0902-OEXSUMS. The SUMSexperiment was operated on orbit as planned and anadditional two times during the delays in deorbit. The orbit data were recordedon the OPSI recorder and dumped. Thesedata were of high quality. The SUMSwas operated during entry as planned.0903-OEXSEADS. The SEADSexperiment was operated as planned during ascent andentry.The following DTO's required no special test or crew activity other than theoperation of operational Instrumentation/modular auxiliary data system (OI/MADS)instrumentation and recorders. Postflight analysis of these data will berequired. No instrumentation or recorder problems were reported.

0236-Ascent Wing AerodynamicDistributed Load Verification on OV-102.0301-Ascent Structural Capability Evaluation.

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TABLEI. - STS61-C SEQUENCEOFEvent

APUactivation (i)(2)(3)

SRB HPU activation command (RH-B)MPS start command sequence (engine 3)SRB ignition command from GPC (lift-off)MPS throttle down to 85-percent thrust (engine 3)Maximum dynamic pressureMPS throttle down to 69-percent thrut (engine 3)MPS throttle up to 104-percent thrust (engine 3)SRB separation commandMPS throttle down for 3g acceleration (engine 3)Main engine cutoff (MECO)External tank separationOMS-I ignitionOMS-I cutoffAPU Deactivation (3)OMS-2 ignitionOMS-2 cutoffSATCOM deployFCS (flight control system)APU 3 deactivationAPU 1 activationDeorbit maneuver ignitionDeorbit maneuver cutoffAPU 2 activationAPU 3 activationEntry interface (400,000 ft.)End blackoutTerminal Area Energy Management (TAEM)Main landing gear contact (LH)Nose landing gear contactWheel stopAPU deactivation complete

checkout_APU 3 activation

EVENTS

Actual time_ G.m.t.

12:ii:50:0912:11:50:1012:11:50:1012:11:54:30.312:11:54:53.512:11:55:0012:11:55:33.612:11:55:5612:11:55:56.612:11:56:02.812:11:57:0712:12:02:28.312:12:03:2212:12:03:4012:12:05:2212:12:08:0612:12:09:0412:12:41:0612:12:43:2112:21:26:2915:10:04:5415:10:08:5618:12:49:3218:12:54:3018:12:58:2218:13:15:1018:13:15:1018:13:28:0318:13:45:3218:13:52:4618:13:58:5118:13:59:0718:13:59:5018:14:11:59

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Documents

STS-61C National Space Transportation System Mission Report