Apollo 15 Final Lunar Surface Procedures

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FINALAPOLLO 15

LUNAR SURFACE PROCEDURES

JULY 9, 1971

Y_z_4___PPROVED Br_. G. e(_r "Chief, Le_rFarurfaceProceduresSectionD. C. Sc ultzChief,EVA/IVA Branch

_C hieWf,_i!edwe_Uoceduresivision

Donald K. Slayton fDirectorof FlightCrw_perations


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APOLLO15LUNAR SURFACEPROCEDURES

FINAL

PREFACE

This documenthas been preparedby the Crew ProceduresDivision,Flight Crew OperationsDirectorate,Manned SpacecraftCenter,Houston,Texas and by General Electric,Apollo Systems,HoustonPrograms. The informationcontainedwithin this docu-ment representsthe Lunar Surface Proceduresfor Apollo 15,Mission J-l, the fifth manned lunar landing mission.

J._H. Roberts_nar SurfaceProceduresSection

T. O. Montg_Fmery _--General ElectricCo.

/J. G."Olmsted/ GeneralElectricCo.

General ElectricCo.


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CONTENTSPage

PrefaceList of Tables and Figures ................ v-viil.O INTRODUCTION ................... l2.0 MISSION DESCRIPTION............... -.... 3

2.1 Mission Objectives .................. 32.2 Mission Lunar Surface Priorities ........... 42.3 EVA Requirements................... 52.4 Lunar Landing Site Description........... 62.5 ScientificObjectivesof the Hadley-ApennineRegion 7

2.5.1 Apennine Mountains ........... 72.5.2 Hadley Rille .............. 72.5.3 Mare Materials ............ 82.5.4 Possible VolcanicLandforms .... 82.5.5 SecondaryCrater Clusters .... 82.6 Lunar SurfaceActivity for 67 Hour Stay 8

3.0 NOMINAL LUNAR SURFACE EVA ............ 173.1 EVA GeneralDescription ...... 173.1.1 SEVA .......... 173.1.2 EVA-I ......... 213.1.3 EVA-2 ......... 35

3.1.4 EVA-3 393.2 DetailedEVA Timeiine'Procedures 433.2.1EVA.......... 433.2.2 EVA-I ......... 493.2.3 EVA-2 .......... 913.2.4 EVA-3 ........ 1293.2.5 Samplingand Related Procedures 1653.3 Lunar SurfacePhotographyData .... 1753.4 ALSEP Deploymentand EquipmentData 1793.5 Geology Equipmentand Data ..... 1833.6 EVA Traverses 2173.6.1 Traverse'Assumptions'and'Groundules 2173.6.2 TraverseMaps and StationTasks . . . 2203.7 Lunar Rover Vehicle ............. 2613.7.1 Systems ................ 2613.7.2 Operations ................. 2613.7.3 Performance& Constraints.......... 280

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CONTENTS (Cont'd.)Page

3.7.4 Decals and Checklists .......... 2874.0 CONTINGENTPLANS .................... 293

4.1 GeneralDescription ................ 2934.1.1 EVA-ITwo Man WalkingTraverse ....... 2944.1.2 EVA-2 Two Man WalkingTraverse ....... 2954.1.3 EVA-3Two Man WalkingTraverse ....... 2974.1.4 EVA-IOne Man LRV Traverse . . . *4.1.5 EVA-2 One Man LRV Traverse ....... *4.1.6 EVA-2 One Man LRV Traverse ......... *4.1.7 Min Time EVA - One Man ........... 299

4.2 DetailedContingencyEVA Timeline .......... 3014.2.1 EVA-I Two Man Walking Traverse ....... 3014.2.2 EVA-2 Two Man Walking Traverse ....... 3194.2.3 EVA-3 Two Man Walking Traverse ....... 3454.2.4 EVA-I One Man LRV Traverse ......... 3574.2.5 EVA-2 One Man LRV Traverse ......... 3574.2.6 EVA-3 One Man LRV Traverse ......... 3574.2.7 Min Time EVA - One Man ........... 359

4.3 EVA Walking Traverses................ 3674.3.1 TraverseAssumptionsand Ground Rules . . 3674.3.2 TraverseMaps and Station Tasks ....... 3674.4 Off-NominalPlanning ............... 3835.0 APPENDIX ........................ 385

5.1 Abbreviations .................. 3855.2 OperationalConstraints . _ . ........... 3875.3 ALSEP and ScientificEquipmentProcedures ..... 4035.4 EquipmentDecals ................. 4055.5 References .................. 409

* To be supplied in a Supplementto the Lunar Surface Procedures

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FigureNumber Figure Page2.6-I Lunar SurfaceActivity SummaryTimeline For

67 Hour Stay.................... iI3.l-I SummaryTimeline SEVA ................ 193.1-2 SummaryTimeline- NominalLunar Surface EVA-I.... 233.1-3 LRV DeploymentSequence ............... 253.1-4 MESA Stowage..................... 263.1-5 ProbableAreas for Near - LM Lunar SurfaceActivities..................... 273.1-6 SummaryTimeline- NominalLunar SurfaceEVA-2.... 373.1-7 Summary Timeline - NominalLunar Surface EVA-3.... 413.3-I Lunar Surface PhotographyData............ 1773.4-I Apollo Lunar SurfaceExperimentsData ........ 1813.6-I Lunar Field Geology Equipmentand LRV Stowage .... 1853.5-2 EVA-I Lunar Surface Equipment& Sample Management 1883.5-2a EVA-I MESA and ETB Transfersto LRV ......... 1883.5-2b EVA-I MESA Table Loadingand Transfersto LRV .... 1893.6-2c EVA-I Pre-GeologyTraverse.......... 1913.5-2d EVA-IPre-AlsepDeployment....... 1933.5-2e EVA-I Arrival Back at LM - Post ALSEP ....... 1953.5-2f EVA-I LRV Transfersto MESA and LM......... 1963.5-2g EVA-I ETB Transfer to LM............. Ig73.5-2h EVA-I On LMP Ingress................ 1993.5-3 EVA-2 Lunar Surface Equipment& Sample Management. 2003.5-3a EVA-2 MESA and ETB Transfersto LRV ......... 2003.5-3b EVA-2 MESA Table Loadingand Transfersto LRV .... 2013.5-3c EVA-2 Pre-GeologyTraverse.............. 2033.5-3d EVA-2 Arrival Back at LM............... 2053.5-3e EVA-2 LRV Transfersto MESA and LM.......... 2063.5-3f EVA-2 ETB Transfer to LM............... 2073.5-3g EVA-2 On LMP Ingress................. 2093.5-4 EVA-3 Lunar Surface Equipment& Sample Management 21O3.5-4a EVA-3 MESA and ETB Transfers to LRV ......... 2103.5-4b EVA-3 Pre-GeologyTraverse............. 2113.5-4c EVA-3 Arrival Back at LM.............. 2133.5-4d EVA-3 LRV Transfersto MESA and LM. ....... 2143.5-4e EVA-3 On LMP Ingress................ 2153.6-I HadleyApennine LandingArea............ 2213.6-2 LRV TraversesEVA-I,2,3(Summary) 2233.6-3 HadleyApennineFeatures& Names........... 2253.6-4 Profile of Hadley ApennineLanding Site ....... 2273.6-5 LEGEND - 1:25,000& I:12,500GeologicMap ...... 229Explanation3.6-6a EVA-I 1:25,000 ContourMap............ 2303.6-6b EVA-I 1:25,00D Traverse Map ........... 2313.6-7a EVA-2 1:25,000 ContourMap............ 236

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Figure(cont'd)3.6-7b EVA-2 1:25,000 TraverseMap............ 2373.6-8a EVA-3 1:25,000 ContourMap ............ 2443.6-8b EVA-3 1:25,000 TraverseMap............ 2453.6-ga EVA-I,2 I:12,500 TraverseMap (Part:A)....... 2543.6-9b EVA-I,2 I:12,500 TraverseMap (Part:R1 ...... 2553.6-9c EVA-I,2 I:12,500 TraverseMap (Part:_i 2573.6-I0a EVA-3 I:12,500 TraverseMap (Part:A)....... 2583.6-1Ob EVA-3 I:12,500 TraverseMap (Part:B) 2593.7-I LRV Systems ..................... 2623.7-2 LRV HandcontrollerFunctions............. 2633.7-3 LRV Control and DisplayFunctions .......... 2643.7-3.1 Apollo 15 LRV VelocityConstraints.......... 2813.7-3.2 LRV Dynamic Stability- SteeringStability...... 2823.7-3.3 Stopping Distancevs InitialVelocity- VariousSlopes....................... 2833.7-3.4 LRV Stop Distancevs HandcontrollerPull Force.... 2843.7-3.5 LRV OperationsDecal...... _ .......... 2893.7-3.6 LRV/LCRU MalfunctionProceduresChecklist ...... 2404.3-I Walking Traverses EVA-I,2,3 (Summary)........ 3694.3-2a EVA-I,2,3 1:25,000 Walking TraverseContour Map .................... 3704.3-2b EVA-I,2,3 1:25,000 Walking Traverse Map ...... 3714.3-3a EVA-I,2,3 I:12,500 Walking Traverse Map(PartA)...................... 3724.3-3b EVA-I,2,3 I:12,500 Walking Traverse Map(Part B)...................... 3734.3-4 Off-NominalPlanning Data *5.4-I EquipmentDecals................... 4065.4-2 LRV OperationsDecal... .............. 407

* To be supplied in a Supplementto the Lunar Surface Procedures

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TableNumber Table Page2.6-I Loose Equipment Left on Lunar Surface......... 132.6-2 EquipmentTransferredBetweenA/S-Surface-A/S..... 153.5-I LEGEND - Lunar Field, Geology Equipment& Sample Mgmt. 1873.6-I EVA-I Traverse aridStationTasks (Nominal) ...... 2333.6-2 EVA-2 Traverse aridStationTasks (Nominal) ...... 2393.6-3 EVA-3Traverseand StationTasks (Nominal) ...... 2473.6-4 SummaryTraverse/TaskTimetableEVA-I, 2, 3 ...... 2533.7-I LRV OperationalFunctions............... 2653.7-2 LRV Off-loadFrom LM and LRV Set-upProcedures .... 2663.7-3a LRV Power-Up (EVA l) Procedures............ 2693.7-3b LRV Power-Up (EVA-2, 3) Procedures .......... 2713.7-4 LRV NavigationAlignmentProcedures.......... 2723.7-5a LRV Procedures- Geology/ScienceSite (Nominal).... 2733.7-5b LRV Nav Up-date -.Geology/ScienceSite ........ 2753.7-6a LRV Closeout EVA--I.................. 2773.7-6b LRV Closeout EVA--2.................. 2783.7-6c LRV Closeout EVA--3.................. 2793.7.3-I LRV OperatingLimits,Constraints& Requirements. . . 2854.3-I EVA-I WalkingTraverseand StationTasks ....... 3754.3-2 EVA-2 WalkingTraverseand StationTasks ....... 3774.3-3 EVA-3 WalkingTraverseand StationTasks ....... 3794.3-4 SummaryWalkingTraverse/TaskTimetableEVA-I, 2, 3.. 381

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SECTION 1.0

INTRODUCTION


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1.0 INTRODUCTIONThe Apollo 15 Lunar Surface Procedures is used todocument the plarming for lunar surface EVAoperationson Mission J-l, to describe the crew equipment inter-face, and to document the manner in which the lunarsurface mission requirements are to be implemented.The nominal plan includes three two-man EVAperiodsduring the 66.5 hour stay of the LM vehicle on thelunar surface. The first, second and thir'. EVA's areplanned for seven, seven and six hours, respectively,of activity from depressurization to repressurizationof the LM. Several alternate operation plans are in-cluded in this document to cover such off-nominal casesas higher-than-anticipated workloads which result inshorter PLSStime-to-consumabl es-redl i ne, di ffi cul tiesin placement or deployment of experiments resulting intime loss, and malfunction of an EMUor PLSSbefore orduring an EVAwhich occasions subsequent single-manEVA contingency operation.EMUoperations and procedures (including contingency)are covered in tile EMUAOH, Reference 13.Detailedphotographicand TV cameraoperationsarecoveredin Reference 6 , but are integratedhereinin a summarymanner.This documentcontainssummary and detailedtimelineand proceduresdata, the voice data plan, and copiesof the crew's cuff checklist. The summarytimelinesare essentiallya task flow analysisalong a timebase showingcoincidentactivitiesand pointsofinteractionbetweencrewmen. The detailedtimelineproceduressimply list in the sequenceof performance,the steps requiredto carry out each of the tasksidentifiedin the summarytimeline. It is in thedetailedtimelineproceduresthat the crew/equipmentinterfacesare revealed. Both the summaryand de-tailed timelineprocedurespresentthe CDR's and theLMP'stasks side.-by-sideo minimizethe confusionas to which crev_nanis doingwhat and to show howthey cooperatein the lunar surfaceoperations. Thevoice data plan is providedcoincidentwith the de-tailed timelineproceduresas a device by which cap-corn(capsulecommunicator)is able to keep abreastof the crew'sac'Fivitiesnd to _rovide cap-comwith


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cues, data and data recordingpoints with which toproviderealtimeassistanceto the lunar'surfacecrew during the EVA activities. The crew's cuffchecklistsare includedfor infomation only, showingthe proceduralcues the crew have at their fingertips.The proceduresherein are responsive,to the MissionRequirementsfor SA-SIO/CSM-II2/LM-IOJ-l Type Missioncurrentlyin effect as of the date of this document.


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SECTION 2.0

MISSION PLAN


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2.0 MISSION DESCRIPTIONThe followinginfomation is taken fromthe "MissionRequirements,SA 510/CSM-II2/LM-IOJ-l Type Mission,Lunar Landing,"dated January4, 1971 and itsapprovedrevisions.

2.1 MISSIONOBJECTIVESThe primal1missionobjectiveshave been assignedtothismissionby the office of MannedSpace Flight(OMSF)in the Apollo FlightMissionAssignmentsDirective(Referencel). These objectivesare:I) Performselenologicalinspection,survey,andsamplingof materialsand surface featuresina pre-selectedarea of the Hadley - Apennineregion2) Emplaceand activatesurfaceexperiments.3) Evaluatethe capabilityof the Apolloequipmentto provideextendedlunar surfacestay time,increasedEVA operations,and surfacemobility.4) Conduct in-flightexperimentsand photographictasks from lunar orbit.The followinglunar surfaceexperimentshave beenassignedto this missionby OMSF (Referencel):l) M-515 Lunar Dust DetectorExperiment2) S-031 PassiveSeismic Experiment3) S-034 Lunar SurfaceMagnetometerExperiment4) S-035 Solar Wind SpectrometerExperiment


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5) S-037 Heat Flow Experiment6) S-036 SuprathermalIon DetectorExperiment

7) S-058 Cold Cathode Ion Gage Experiment8) S-059 Lunar Geology Investigation9) S-078 Lunar RangingRetro-ReflectorlO) S-200 Soil Mechanicsll) S-080 Solar Wind CompositionExperimentsl through 7 are part of the ALSEP ArrayA-2 package. Detailedobjectiveshave been derivedfrom OMSF-assignedprimaryobjectives,placedin orderof priority,and detailedto the extent necessaryformission planning.Experimentsare detailedand assignedpriorityinthis document only in the event that they requirecrew actionor otherwiseimpact the missiontimeline.All of the detailedexperimentsare in support of theprimarymission objectivesor were assignedby OMSFas a numbered experiment.

2.2 LUNAR SURFACE PRIORITIESThe detailedobjectivesand experimentsare listedbelow in their order of priority. These prioritiesshouldbe used for realtimemission planning.Mission and Lunar Surface Detailed Objectivesand

Priority Exloerimentsl ContingencySample Collections2 DocumentedSample CollectionatApennineFront (Part of LunarGeology Investigation)

3 Apollo 15 ALSEP ARRAY A-24 Drill Core Sample Collection

(Part of Lunar GeologyInvestigation)


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5 Laser RangingRetro-Reflector6 Lunar Geology Investigation7 Lunar Rover VehicleEvaluation8 EVA Communicationswith theLCRU/GCTA9 EMU Assessmenton Lunar SurfacelO LM Landing EffectsEvaluationII Solar Wind Composition12 Soil MechanicsN/A LM Descent EnginePerformance

2.3 EVA REQUIREMENTSThe stay time on the lunar surface is open ended andthe plannedmaximumwill not exceed approximately67hours. After checkoutof the launchcapabilityofthe LM it will be depressurizedfor a SEVA. The crewwill then begin a rest period prior to LM depressurizationto begin the first of three periodsof surface activity.The first and second EVA periodswill be approximately7 hoursduration each while the third period will be a 6 hour EVA.The traverseplanningprovidesfor the capabilityofthe crew to return to the LM under each of the followingsingle-failureconditions:l) Use of the buddy-secondarylife supportsystem

(BSLSS)due to an inoperativePLSS anytimeduringa ridingtraverse(basedupon the assumptionsthat the LRV will operate properlyduring thereturn to the LM).2) Use of two PLSS's for a walking return to the LM

from an inoperativeLRV anytimeduring a ridingtraverse(based upon the assumptionthat bothPLSS'swill operateproperlyduring the returnto the LM).


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The plannedlunar surface activitieswill includethe followingmajor tasks:l) ContingencySample Collection2) Lunar Rover Vehicle Deplojnnent3) Lunar field geologyto the Appinine Front (S-059)4) ALSEP Deployment5) Lasar RangingRetro-ReflectorExperiment(S-078)6) Deep Core DrillingSample7) Lunar field geology (S-059)8) Lunar Rover Evaluation9) Solar Wind Composition(S-080)Televisiontransmissionwill be providedas early aspracticableduring the EVA period to observecrewactivitiesaroundthe LM. Televisioncoveragewillalso be provided at each science stop by the GCTAwhen using the LRV. Photographywill be utilizedthroughoutthe EVA to documentactivitiesandobservations.

2.4 SITE DESCRIPTION2.4.1 Hadley-Apennine

The ApennineMountainsrise up to 2 km above the re-lativelyyoung mare surfaceof Palus Putredinisandmight containmaterialexposed duringexcavationofthe Imbriumbasin. Sampling of such Apenninianmaterialmight provideancient rocks whose originpredatesboth the formationand the 'Fillingof themajor mare basins. Rima Hadley is a V-shaped lunarsinuous rille which parallelsthe ApennineMountainfront along the easterndepressionof Mare Imbrium.The rille originatesin an elongatedepressioninan area of associatedvolcanicdomes and generallymaintainsa width of about l km and a depth of 200-300 meters until it merges to a second rille to thenorth. The origin of sinuous rilles such as RimaHadley is an enigma but probably involvessome type


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of fluid flow and-or collapse. Thus, the study ofthe processof sinuous rille formationmay yielddata on the historyof lunar volatiles.2.5 DETAILEDSCIENTIFICOBJECTIVESOF THE HADLEY-

APENNINEREGION2.5.l Apennine Mountain:s

The ApennineMountainsform part of the southeasternboundaryof Mare Imbriumand are believedto have beenformed at the time of origin of the I_rium basin. TheApenninesare analogousto the CordilleraMountainsin the fresherOrientalebasin on the western limbofthe lunar frontside. Study of these analogousregionsin the In_riumand Orientalebasinssuggestthat theimpact ultimatelyresponsiblefor the formationofthe multi-ringed:structureslso resultedin depositionof a thick blanketof ejecta around and on the rim ofthese basins. This ejectawould mantle large areasaround the Imbriumbasin,thinningaway from the basininterior_and overlyingpreexistingtopographyprobablysimilar in morphologyto highlandregionsof the moon.The materialexposedon the _carps or mountainfrontscould representa cross section of lunar crust severalthousandmeters thick.

2.5.2 Hadley RifleHadley Rille is a sinuousrille originatingin thevicinityof severalelongatedepressionsnear theApennine Mountainfront. The originof these wide-spread lunar featureshas long been debatedand hasvariouslybeen attributedto flowingwater, nuesardentes_tectonism,lava channels,and collapsedlavatubes. Whatevertheir detailedorigin,they appeartobe relatedto volcanicprocessesassociatedwith marebasin filling. Investigationof Hadley Rille couldshed lighton the originof these ubiquitousmarefeatures. Since Hadley has a ratherV-shapedcrosssection, as opposed to flat flooredrillessuch asSchroetersValley and Rimae Prinz,it appearsthat thefloor has been filled in by collapseor talus slump.The approximateslope of the side of the rille is _25and it averages250-325m in depth. Numerousoutcropsand apparentlylayeredmaterialare seen along and justbelow the rifle rim. These layers may representlavaflows and interlayeredregolith. Numerouslarge blocks


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have rolled to the bottom of the rille and severallarge boulder tracks can be seen. Sampling of therille rim and photographyof the walls would be highlydesirable.

2.5.3 Mare MaterialThe major portionof the flat terrain between HadleyRille and the Apennineridgesconsistsof mare materialforming an embaymentinto this area from Palus Putredinisto the west. This unit has been mapped as Imbrian inage. Using the crater dating methods, the Hadley areamare materialappears relativelyyounger than bothApollo II and 12 sites. Examinationof high resolutionphotographsrevealsblocky craters in the 50 - 250 mrange,particularlyin the northernpart of the area,which shouldmake samplingof this unit very easy.

2.5.4 Possible VolcanicLandformsAssociatedwith the MareA wide spectrum of domes, domical hills,and associatedstructuresexist in various places between the ApennineFront and Apennine Ridge to the west of Rima Hadley.Most of these features appear to be superimposedon themare materialand their morphologysuggeststhat theymay be constructionalvolcaniclandforms. In particular,these structuresabound around the origin of Rima Hadleynear the elongate depressionand are also found alongthe Apennine Front and on the northeastbank of RimaHadleywhere it turns northwesttoward Rimae Fresnel.Investigationof this spectrumof landformsmay provideimportantgeochemicaland age data on late stagesofmare basin fill.

2.5.5 SecondaryCrater ClustersSecondarycrater clustersfrom the Copernicanage cratersAutolycusand Aristillus;locatedapproximately150 - 300km to the north, are widespread in this region. Examina-tion of a cluster large enough to yield rocks from thesecraters could provideinformationabout the absoluteageof these Copernicanevents, as well as samples from an-other part of the Imbrium Basin.

2.6 LUNAR SURFACE ACTIVITYFOR 67 HOUR STAYThe nominal plan is for the Commanderand the LunarModule Pilot to remain on the lunar surface for


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approximately67 hours. A summarytimeline for the lunarsurfacestay is presentedin Fig. 2.6-I.Immediatelyafter landingon the lunar surface,the crewwill performpost landing LM systems integrityverificationchecksto establishlunar stay capability. Upon establish-ing the stay capability,the crew will depressthe LM andconduct a Standup EVA (SEVA). In the EVA, the Commanderstandsupon the ascent engine coverwith his head, shouldersand upper torso extendingabove the dockingring to view,take a photographicpanoramaand verballydescribe the lunarlandscapefrom a vantage point at the top of the LM and withassistancefrom _FN determinetheir exact landingsite.This period of time can also be utilizedto describeany un-forseen anomaliesin the lunar surfacewhich might necessi-tate revisionsof any or all of the preplannedtraverses.Followingthe SEVA is an eat period, a 7.5 hour sleep periodand a second eat period after which the crew begins to con-figure the LM systems and cabin equipmentfor the first EVAperiod. PLSS/OPSdonning, systems activationand checkoutand communicationscheckoututilize the final hour preceedingthe first EVA which beginswith cabin depressurizationat ap-proximately16-hoursafte_ touchdownon the lunarsurface. Adetaileddiscussionand timelinefor EVA-I is includedinSection 3.1.2.Upon completionof EVA-I,the crew will reconfigurethe LMsystems for pressurizedcabin operations. The crew willdoff helmets,gloves,PLSS/OPS'sand suits prior to the de-brief and eating periods. Rechargeof the PLSS consumables(battery,LiOH canister,02 and feedwater)will take placeduring the EVA post activities. Duringthe post EVA debrief,the crew discusseswith MSC Houstonthe activitiesof the EVAand surface conditionsexperiencedduring the EVA and whetherany changes are requiredin the planningfor subsequentEVA's.Followingthe debriefthe crew settlesdown to an eat period,an 8.5 hour sleep period and a second eat period prior todonning the suits and beginningthe EVA-2 Prep. DuringthePrepthe crewwill again reconfigurethe LM systemsand cabinequipmentfor depressurizedoperation. The PLSS/OPSunitsare again donned and the systemsand communicationsverifiedprior to depressurizationfor a 7 hour EVA-2 at approximately36 hours 40 minutes after touchdown. A detaileddiscussionand timeline for a 7 hour EVA-2 is included in Section 3.1.3.


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Upon completionof EVA-2, the crew will again recon-figure the LM systems for pressurizedactivitiesandwill proceedon the Post EVA activitieswhich consistof doffing helmet and gloves, stowingequipmentandsamples,rechargingof the PLSS consumables(battery,LiOHcanister,02, feedwater). The crew then dofftheir suits and proceed to debrief with MCC Houstondiscussingthe EVA activities,any new observationsof surface terrainencounteredduring the EVA, andwhether any changesare requiredin the EVA-3 pre-planned activities. Followingthe debriefing,thecrew enjoys anothereat period, a 7.5 hour sleepperiod and anothereat periodwhere upon they againdon their suits before proceedingwith the EVA-3Prep activities. Duringthe EVA-3 Prep the crewwill again configurethe LM systems and cabin equip-ment for depressurizedoperations. The PLSS/OPSunits are donned and the systems and communicationsreverifiedprior to cabin depress for the thirdEVA periodwhich will begin at approximately57.5hours after touchdownand last for 6 hours. A de-tailed descriptionand timeline for EVA-3 is in-cluded in Section 3.1.4.At the completionof EVA-3 the crew will ingresstheLM and connectto the LM ECS and begin the EVA-3Post activitieswhich includedoffing the glovesand the PLSS's, and preparationof all excess equip-ment in the cabin for jettison. After the crew hasdonnedthe gloves, depressedthe LM, jettisonedtheexcess gear and repressedthe cabin they turn to thetask of stowing all equipment and samples and re-configuringthe LM cabin for lift-off. When the EVAPost activitiesare completed,the crew again debriefswith MCC Houston, does a P57 update, enjoys theirfinal lunarmeal and performsthe final prelaunchchecklistfor a liftoffat approximately66.5-67 hoursafter touchdown. This final activitywill concludethe fifthmanned lunar landingmission and the fourthlunar landing.

lo


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TABLE 2.6-I LOOSE EQUIPMENTLEFT ON LUNAR SURFACEI. JettisonDurin9 EVA-I: (In a JettisonBag)2 - OPS Pallets3 - Arm rests

Used LiOH cartridge& BracketBSLSS Bag2. DiscardedOn Lunar Surface During EVA-IMisc Pip Pins and FasteningsThermal CoversLRV Thermal BlanketTV CameraBracket

ALSEP RTG Dome RemovalTool and Fuel TransferToolPSE Gird'leALSEP SubpalletLRRR Dust CoverLunar Surface Drill,Treadle and RackLEC BagTV TripodLCRU/GTCAPalletPallet lSRC Dust Skirt and Seal Protector

3. OperationalEquipmentDeployedand Left On EVA-IFlagTV CameraLRVALSEP: PSE, LSM, HFE, SIDE/CCIG,SWELRRRSWC

4. JettisonDurin9 EVA-2 (In JettisonBag)l LM ECS LiOH Cartridgeand BracketUsed Food Containers2 PLSS Batteries2 PLSS LiOH Cartridgesand Canisters

5. Discardedon Lunar Surface During EVA-2EVA-2 Palletl - Core Tube Cap,DispenserSRC Dust Skirt and Seal Protector

6. JettisonedDuring EVA-3 (In JettisonBag)2 PLSS Batteries2 PLSS LiOH Cartridgesand Canisters

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1LM LiOH Canister and Bracket2 HammockAssys and Sleep RestraintsUsed Food ContainersUsed Towels2 LCG's2 CWG'sLGCAdapterUrine Receptacle2 ICG Assys7. Discarded on Lunar Surface During EVA-3

LRV w/GCTA, LCRU, QUAD Ill Pallet,3-LCRU BatteriesHand Tool Carrierw/toolsPenetrometer(lessdrum)Lunar Hand ToolsGnomonPolarizingFilter2-70mmData Cameraw/Bracket,Handle, Trigger16mm Lunar Data AcquisitionCameraAssy w/staffLunar EquipmentConveyor500mm lens CameraSWC StafflO0' Tetherw/2 lens BrushesBSLSSDust BrushUnused DocumentedSample BagsReseau Plate Cover

8. Jettisonedto Lunar SurfaceAfter EVA.-3Iln JettisonBag)2 pr Lunar Boots2 PLSS2 Drink BagsUsed Food ContainersUrine Bags (if used)Used TowelsUsed EmesisBagsMisc Small Itemsl Armrest

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TABLE 2.6-2 EQUIPMENTTRANSFERREDETWEENASCENTSTAGE/SURFACE/ASCENTTAGEI. Transferred to Surface EVA-IETB and contents

Map holder w/lunar surface maps and LRV checklist3-70mmmags (2-HCEX mags KK,NN, I-HBW mag 00)3-16mmmags CC,DD,EE (CEX)500mmlens camera w/lens camera w/mag MM(HBW)1-70mmcamera (HBW-magLL)BSLSSEmpty EVA-I palletCSRC

2. Transferred into Ascent Stage EVA 1EVA 1 pallet w/ECS LiOH canisterCSRCSCB#3SCB #4SRC#IETB and contentsLunar surface maps2-70mmmags LL(HBW), NN(HCEX)3-16mmmags (CEX)Mag MMfrom 500mmlens camera (HBW)2-70mm cameras (HCEXmag KK,HBW-mag00)

3. Transferred to surface EVA-2ETB and contentsLunar surface maps3-70mmmags PP,QQ,RR(HBW)3-16mmmags FF,GG,HH (CEX)Mag MMfor 500mmlens camera2-70mm cameras (HBWmag 00, HCEXmag KK)

Empty EVA-2 pallet

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4. Transferred into Ascent Staqe EVA-2EVA 2 pallet w/ECS LiOH canisterSCB #2SCB #6SRC #2ETB and contentsLunar surface maps

3-70mmmags O0,RR(HBW).KK(HCEX)3-16_ mags FF,GG,HH (CEX)Mag MM from 500mm lens camera2-70mm cameras (HBW-magsQQ,PP)5. Transferredto surface EVA-3

ETB and contentsLunar surfacemaps2-70mmmags UU,VV,WW(HBW}2-16mm mags II,JJ (CEX)Mag MM for 500mm lens camera2-70mm cameras (HBW mag SS, HCEX mag TT)

6. Transferredinto Ascent Stage EVA-3SCB #7SCB #8BSLSS Sample BagETB and contentsLunar surface maps4-70mm mags SS,VV,UU,WW(HBW)2-16rammags II,JJ (CEX)Mag MM from 500mm lens camera (HBW)SESC 21-70_ mag TT(HCEX)

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SECTION 3.0

NOMINAL LUNAR EVA


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3.0 NOMINALLUNARSURFACEEVA3.1 EVA GENERALDESCRIPTION

In the nominal lunar surface activities plan, two crewmenwill spend a total of 20 hours outside the Lunar Moduleand on the lunar surface for a total of 40 man hours ofEVA time. This period is divided into three smallerperiods of seven, seven, and six hours respectively forEVA-I, 2 and 3. These EVA periods are separated by adequ-ate periods of LM cabin activity for housekeeping, eatingand sleeping. In addition to the surface EVAactivities,a SEVA


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APOLLO5SUMMARYIMELINELUNARURFACEEVA"rIME SCALE () ]'0 2'0 3'0

IV COVERAGE . JSEQ. CANL COVER,

OSTAND ONASCENTENGINECOVER DESCRIBE INITIAL IMPRESSIONS DESCRIBE SURFACECONDITIONOFFRONT RILLE, NORTHCOMPLEX, IN IMMEDIATEVICINITY OFLM_C_S.:RVE _*;JDESCR'.SELM S_TE MARE SURFACE, BOULDER FIELDS (CRATERDISTRIBUTION,BOULDERPOPULATION,FRAGMENTATIONAND ANY NOTICEABLEDPS EXHAUSTCOMMANDER 70 MM VERTICAL STEREO PAN EFFECTS ON SURFACE) 500 MM LENS CAMERA PHOTOA CT I V I TY OFFRONT, RILLE, NORTHCOMPLEX, GENERAL SURFACE DESCRIPTION BOULDER FIELDSAND OTHER FEATURES OTERMINATE SEVA

--I ASSIST CDRWITH CAMERA ASSIST CDRWITH I_ASSISTCDRASREQUIRED500 MM LENSCAMERA DESCRIBESURFACEFEATURESTHROUGHLM WINDOW TERMINATE SEVALM

PILOTACTIVITY

T IME- -SC ALE ]i0 Z'O 30I

NAME INITIAL ORIGIN NATIONAL AERONAUTICS& SPACE ADMINISTRATIONR. BLEVINS //_ MANNED SPACECRAFT CENTER HOUSTON. TEXAS

APOLLO ]5 SUMMARY TIMELINELUNARSURFACESEVA

FIGURE.1-IOR/C.HENDRICKS_J/' GE pn(pwu_o_YENERAL_)ELECTII IC[ BASICJUNE1971


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actual landing site as well as highlighting possible referencelandmarks for use during the EVAtraverse and perhaps takingsightings on these landmarks with a simple sun compass. PostSEVAactivities include replacement of the drogue andreconfiguration of the tunnel hatch, LM and crewmen forpressurized cabin operations.3.1.2 EVA-IThe first lunar surface activity period begins with de-pressurization of the LM cabin at approximately 15 hoursI0 minutes after touchdown. The Commander(CDR) egressesfirst by backing out of the hatch, feet first on his handsand knees to the LM porch. As the CDRpasses through thehatch, the LM pilot (LMP) deploys the CDR's PLSSantenna.The CDRthen moves to a position at the top of the LMladder which provides him with convenient access to theMESAunlock/deploy lanyards. The CDRthen removes acover from the MESArelease mechanism, unlocks the MESAand activates tlqe MESAdeploy mechanism which allows theMESAto revolve out of its QUADIV stowage and ratchetdown to a position approximately 120 to the verticalside of the LM. In this position the TV camera mountedon the MESAwill cover most of the activity in thevicinii_ of the LM ladder. The CDRthen retrieves thejettison bag which has been placed in the hatch by theLMPand discards it to the lunar surface. The LMPthenpasses one end of the LEC to the CDRwho, inturn, deploysit to the lunar surface. The CDRthen descends the ladderto the footpad and after checking his capability to regain

the bottom rung of the ladder, steps to the lunar surfacewhere he will spend a few moments becoming accustomed tothe lunar environment, restowing the jettison bag underthe LM and discussing briefly surface conditions andLM landing effects on the surface and the LM struts. TheLMPmeanwhile has verified the LM cabin and circuit breakerconfiguration and prepared the ETB for transfer to thesurface via the LEC. After completing this transfer, theLMPdisconnects the LECfrom the overhead handhold andstows it on the RHSC.The LMP after making a final check of the LM cabin proceedsto egress to the LM porch. After partially closing thehatch he then descends the ladder to the lunar surface wherehe spends a few moments becoming acclimated to the lunarenvironment and making his initial observations of theluraine in the vicinityof the LM site.

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Having transferredthe ETB down, the CDR hangs it on theladderhook and proceeds to open the MESA thermal blankets.He then unstows and deploysthe TV camera tripod,andunstows and mounts the TV camera on the tripod. The TVcable is then unstowed from its location of the MESAand the TV is then carried to a 12 o'clock positionapproximately50 feet from the LM and oriented to viewthe LM QUADS I and IV to cover the MESA and LRV offloadactivities.The LMP has proceededto his first lunar surface task,that of getting the contingencysample. He removes theCSC from his suit pocket and deploys the handle and bag.He then selects a suitableundisturbedarea, preferablywithin view of the cabin window and scoops approximatelyl kg of material from the lunar surface. He then removesthe bag from the contingencysampler, seals it and climbsthe LM ladder to interimstow the CSRC on the LM porch.While in position at the top of the ladder,the LMP willverify that the CDR has deployed the left-handand aftLRV deploy tapes and is holding the right hand LRV deploytape in a position at least 15 feet from the LM/LRV.The LMP then pulls the D-ring to unlock the LRV, allowingit to rotate outward from its stowage cavity in QUAD Iapproximately4 degressfrom vertical. The LMP thendescends the ladder to assist the CDR with the LRV off-load.The CDR, having observed the LRV unlock and initialmovement to the 4 position,now pulls the right-handLRVoffload tape until the rear wheels rest on the lunar sur-face. (Note:The LMP will assist by maintainingtensionon the aft deploy cable.) With the rear'wheels resting onthe lunar surface, the right and left outriggercablesare detachedand the CDR begins to pull the left-handoff-load tape until the front wheels rest on the lunar surface.The LMP then assists the CDR in deployingthe LRV fenderextensions,checkingthat the hinges are locked,erectingthe seats, lockingthe console into place,positioningthefootrestsand disconnectingthe LRV from the LM. Aftercompletingthe post deplojnnentchecklistthe the CDR mountsthe LRV, powers it up, test drives it, and parks it nearthe MESA.

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FIGURE3.1-3 LRV DEPLOYMENT SEQUENCE

LRV STOWED IN QUADRANT ASTRONAUT LOWERS LRV AFT CHASSIS UNFOLDS ASTRONAUT REMOVES INSULATION FROM STORAGE BAY WITH OREAR WHEELS UNFOLD

BLANKET. OPERATING TAPES RIGHT HAND TAPE AFT " ^e _ ,-,.,,,.,..,_H,_S,S ,nr,v .,,_"4 ASTRONAUT REMOTELY INITIATES POSITIONDEPLOYMENT

0"I

AND LOCKS ASTRONAUT DISCONNECTS SSE FRONT WHEELS UNFOLD ASTRONAUT LOWERS LRV

TO SURFACE WITH LEFTHAND TAPE


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LUNARRAKE SRC #2 PLSS LiOH CANS. TV CABLE SRC #1

SOLAR WIND ',.-, / 70 MMCOMPOSITION CAM. ASSY.& FLAG STOWED ECS CAN.ON SIDE W/STRAP16 MM CAM.LCRU ANT. EVA 2 W/STAFFSTW CONT.W/HGA & LGA SAMPLE BAGJ

PLSS / EVA 1BATTERIES , TVLCRU FOOD

., I _ v _ LCRUBATTERYSRC TABLE (2)

HEAT FLOW TCU LCRU TV TRIPODDRILL W/3 FT. CABLE W/BATTERY

SA_MPL TV FILTER W/BAG

STOWED INSIDE THE10 FT. CABLE BAGE CONTAINMENT BAG (6 EA.)SOLAR WIND COMPOSITION BAG (ON BOTTOM) Figure 3.1-4 MESA STOWAGE


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LRV OFFLOADAREA OF ACTIVITY

m6

FIGURE3.1-5 PROBABLE AREAS FOR NEAR _ LUNAR SURFACE ACTIVITIES


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The LMP, having unstowedand assembledthe 16mm LDAC,photographsthe CDR as he test drives the LRV.in thevicinityof the LM. He then mounts the 16mm camera onthe LRV. Returningto the MESA area the LMP performsthe followingMESA housekeepingand LRV stowage activities:unstow the 70mm DC, attach a magazine from the ETB andstow on LRV; unstow the EVA-I pallet and attach to theMESA table; discardthe 16mmcamera rack from MESA;unstow the ECS LiOH can and stow in EVA l pallet pocket;removethermalblankets from QUAD III geologypallet,offload pallet and stow on LRV; unstow SRC l, place onMESA table and open; remove SCB #1 from SRC l andattach to HTC (on QUAD III pallet). The LMP then pullsthe HTC pip pin to allow HTC to swing out on theQUAD III palletprovidingaccessto tools stowed on thepallet. He then assemblesthe extensionhandle andsmall scoop and stows them on the HTC; unstows anddeploys the gnomon and restows on the CDR's seatback;restows penetrometeron the pallet;unstows and attachesSCB #2 to the HTC and SCB #3 to the front of the pallet.Then he transfersthe followingequipmentfrom SCB #1:6 core stems and core stem cap to SCB #2, a 20 DSBDto the CDR's floor pan and a 20 DSBD to the LMP's floorpan. The rake is then unstowed from the MESA and re-stowed on the QUAD III/LRVpallet. The LMP then pro-ceeds to ingressthe LM, retrievingthe contingencysample in route.The CDR, having parked and powered down the LRV, unstowsthe LCRU and the TCU from the MESA and mounts them onthe front of the LRV and makes the requiredcable con-nections. He then unstowsthe LGA and HGA from MESAcanistersand mounts them on the LRV connectingtheproper cables, i_e TV camera is retrievedfrom thetripod, turned off, mounted on and connectedto theTCU. The LCRU is then poweredup, the antennas orientedand the LCRU systemchecked out for acceptablecommuni-cationswith MSFN and MCC-Houston. The CDR then bringsthe ETB to the LRV, offloads and stows the contents:2-70mm mags, 2-16mm mags and the 500mm lens camera to theCDR's underseatbag; 1-16mmmag to the 16mm camera;map holder to the LMP inboardhandhold;and the BSLSSto the LMP seatback.The LMP having ingressedthe LM and stowed the con-tingencysample,modifies the configurationof the LMcomunications by switchingPower Amp - OFF, Bit Rate -LOW, TV cb - OPEN and modulationswitch - PM. He then

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connectsthe LEC to the overheadhandholdand transferstheEVA l pallet from the surface After offloadingthe foodpackages,batteriesand [iOH from the palletand stowing them,the LMP egresses the cabin, discards the pallet to the sur-face, closes the LM hatch and descends again to the surfaceto tidy up the thermal controlblankets around the MESA be-fore departingon the geology traverse.The CDR having attached the EVA-I pallet to the LEC and havingaccomplishedthe pallet transferinto the LM cabin, returnsto the LRV to stow the HGA and configurethe LCRU for traverseoperations. He then mounts the LRV, performsthe power'upsequenceand positionsthe LRV for initializingthe LRV navi-gation system.The CDR and LMP then configureeach other for the geologytraverse. The CDR installsthe hammer, core tubes cap dis-penser and SCB #4 on the LMP's PLSS tool harnessand thentethers his tongsand dons his 70mm DC with 20 DSBD attached.The LMP attaches SCB #1 to the CDR's PLSS tool harnessandthen tethersthe extensionhandle/scoopand dons his 70mm DCwith attached20 DSBD. Both crewmen then mount the LRV anddepart to geology station#1.

(NOTE: For purposes of the final editionof theLunar SurfaceProcedures,the geology traverseinformationis contained in Section 3.6.)After completingthe EVA-I geology traverseto the Front, thecrew returnsto the LM site to preparefor the ALSEP deploy-ment. The CDR parks East of the LM, heading West, reportsNav readings,pulls the Nav cb and then powers down the LRVand configuresthe LCRU and HGA for TV coverageof the ALSEPoffload. The tools, cameras and SCB's are removedfrom theEMU's and stowed on the LRV.The LMP retrievesthe SEQ Bay door lanyardand opens the SEQBay door. He then offloads the ALSEP power package (Pkg 2)and positions it for fueling the RTG. He then removes twoUHT's, tethersone and gives the other to the CDR. He alsoremovesand hands to the CDR the carry bar sections. Next,he retrievesthe fuel cask deploymentlanyardand rotates thefuel cask to a positionconvenientfor removingthe fuelelement. He then retrievesthe dome removal tool from thepower package,engages it with the fuel cask dome, removesand discardsthe dome/tool.

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After retrievingand engagingthe fuel transfertool withthe fuel element,he withdrawsthe fuel element from thecask and installsit in the RTG. He then disengagesthefuel transfertool and discards it. He attaches the powerpackageto the carry bar, completingassemblyof the ALSEPbarbell. Before leavingthe QUAD II area the LMP closesthe SEQ Bay doors.The CDR offloadsthe ALSEP experimentspackage (Pkg l)and positionsit clear of the SEQ Bay. He receives aUHT from the LMP and tethers it. He also receives thecarry bar sectionswhich he assemblesand attachestothe bottom of the experimentspackage. The CDR then re-trievesthe ALSD from the MESA and interimstows it onthe LMP's LRV floor pan. He then offloads the LRRR fromLM QUAD Ill and stows it on the LMP seat, lashingit downwith the LMP seat belt. After configuringthe HGA andLCRU for traverseoperations,the CDR mounts the LRV anddrives to the area of the ALSEP deploymentsite at leastlOOm West of the LM, and selects a specificALSEP deploysite.The LMP retrievesthe ALSEP barbellfrom the SEQ Bay areaand carries it to the ALSEP site. Upon arrivingat thesite he placesthe experimentspackage in the desiredlocation,disconnectsthe power packagefrom the barbelland deploys it lO feet East of the experimentspackage.Next he unstows the RTG power cable and connects it tothe C/S (experimentspackage). After removingtwo BoydBolts,the subpalletcontainingthe SIDE and the ALSEPantennagimbal is removedfrom the power package andplaced on the surface lO feet to the North. The SIDE/CCIGis then removedlO feet from the subpalletby releasingfour Boyd Bolts. Before placingthe SIDE on the surface,the cable reel is unstowedand the SIDE legs and deployed.The SIDE connectoris unstowedfrom the subpalletandconnectedto the C/S. Next, the PSE stool is removedfrom the subpalletand emplacedon the surface9 feetWest oF C/S. The PSE is removedfrom C/S after releasing4 Boyd Bolts, emplacedon the PSE stool, the thermalskirt deployedand the PSE leveledand aligned. Afterremoving4 more Boyd Bolts the SWE is removedfrom C/Sand deployed 13 feet North of C/S with the legs extendedand locked. The SWE is then leveledand aligned. Next,the LSM is releasedfrom C/S by removing2 Boyd Boltsand positioned50 feet WNW of C/S. After the legs aredeployed and the LSM aligned,the LSM sensorarms aredeployed,the dust coversand PRA cover are removedandthe unit is leveled.

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The CDR, after parking the LRV and configuring the LCRUand HGA to provide TV coverage of the ALSEP deployment,offloads the LRRR and the ALSD to the lunar surface.He then removes the HFE pallet from the subpallet byreleasing two Boyd Bolts, connects the HFE cable to theC/S and then carries the HFE pallet to a position 30feet North of the C/S. The HFE probe container is thenremoved from the pallet, opened and one probe and theemplacement tool are interim stowed on the pallet. Theother probe is placed on the surface 16 feet West ofthe HFE. The remaining probe is then placed on thesurface 16 feet NE of tile HFE. The HFE electronicsbox is removed from the pallet and emplaced on the sur-face and the pallet discarded. The CDR retrieves theALSD and places it on the LMP's LRV seat. The bore tuberack is removed from the drill package and the legs ex-tended. The drill chuck is reset and the drill is re--moved from the treadle and the drill and rack are carriedto the HFE site. The first two bore stem sections areremoved from the rack, assembled and inserted into thedrill chuck. The bore stems are then drilled into thesurface until approximately I/3 of a section protrudesabove the surface at which point the chuck is releasedand the drill is removed. A second pair of bore stemsare assembled and attached to those already emplaced inthe surface. The drill chuck is reset and the drill placedatop the new bore stem sections and the total bore stemassembly is drilled further into the surface until againapproximately I/3 of a section remains above the surface.The drill is again removed, a third pair of bore stemsassembled and added to the bore stem in the surface. Thedrill chuck is reset and the drill attached to the newbore stem section and the total bore stem is again drilledinto the surface until the top of the stem is approximately15 cm above the surface. The drill is removed from thebore stem and the HFE probe is inserted as far as possibleinto the bore stem using the emplacement tool. The depthof penetration is indicated by ruled markings on the em-placement tool. The drill and rack is carried to thesecond probe site and the above bore stem and probe em-placement procedure is repeated.The LMP, after completing the LSM deployment, returnsto the C/S to deploy the sunshield. Using the UHT hereleases 16 Boyd Bolts on the C/S perimeter, 2 Boyd Boltson the ALSEP antenna, releases the antenna rf cable, and 3inner Boyd Bolts. As the sunshield is raised, the sun-screen curtains are automatically deployed and positioned32


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except for velcro tabs at the corners which the LMP secures.The antenna mast and gimbal are retrieved from the sub-pallet. The mast is installed on C/S and the gimbalmounted on the mast. The ALSEPantenna is then insertedinto the gimbal and the gimbal is leveled, aligned andadjusted to the predetermined azimuth and elevation off-sets. He then gets the SIDE and carries it to a position55 feet NE of C/S. The ground screen is removed and de-ployed on the surface. Next the CClG is removed from itscavity and installed on the ground screen tube which alsoserves as a CCIGdeployment arm. The ground screen tubepin is removed and the SIDE is oriented and placed on theground screen in a position such that the CCIG when de-ployed will be clear of the ground screen. After levelingand aligning the SIDE, the CCIG is rotated to the surface.Upon returning to the C/S, the LMPthen activates C/S bydepressing the shorting switch, turning Astro SW#I CWand requesting a transmitter turn-on commandfrom MSFN.Next_ the LMPmounts his 70mmcamera on his RCU, picksup the LRRR, carries it to a position at least 25 feetWest of C/S, deploys, aligns and levels it. He thenproceeds to photograph the ALSEPexperiments using the70mmcamera and HCEXfilm. See Figure 3.3-I.The CDR, having completed the HFE probe emplacement,then selects a suitable site to obtain the deep coresample. This site will be in the vicinity of the LRVsince LRV mounted equipment is utilized in the coringoperation. The drill treadle is placed on the surfaceand the first two core stems are removed from SCB #2(on HTC), assembled and threaded onto drill. Then,with the core stem inserted through the treadle thecore stem is drilTed into the surface until approximately15 cm protrudes above the surface. The drill is removedand the second pair of core stem sections are assembledand threaded onto the core stem in the surface. Thedrill then is attached to the new section and the totalcore stem is drillied further into the surface untilagain approximately 15 cm remains. The drill is re-moved and the final pair of core stem sections areassembled, threaded onto the existing core stem, thedrill re-attached and the core stem drilled the finalincrement into the surface until approximately 15 cmof the core stem _s exposed. The CDRretrieves his70mmcamera and _ikes a pan from a position 7 feet Southof the implaced core stem. After restowing the cameraon the LRV, the drill is decoupled from the core stem and33


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the core stem is withdrawnfrom the surface, the joints brokenand the individualcore stem sectionsare disassembledandcapped. Before the core stems are stowed,SCB #2 is removedfrom the HTC and placed under the LMP's seat. SCB #4, whichis under the LMP'S seat is attachedto the HTC and the coretubes in SCB #1 are transferredinto SCB #4. The capped corestems are then stowed in SCB #1.After the ALSEP deploymenthas been completedand the neces-sary documentationphotographstaken,the CDR and LMP surveythe undisturbedareas in the proximityof the ALSEP site tocollect additionaldocumentedsamples of any unusualfeaturesnot previouslyencounteredand to documentthe types of mater-ial in the vicinityof the ALSEP. However, sufficientvolumemust be retained in the SCB's to accommodatethe samples thatwill be taken during the polarimetricstudy to be done in thevicinity of the LM.The CDR then configures the HGA ,andthe LCRU for traverseoperationsback to the LM. Both crewmen then mount the LRV,carefullydepart the ALSEP site to minimize the dust contami-nation of the ALSEP and traverse back to the LM where the LRVis parkedcross-run,heading North and powereddown.The CDR then opens the MESA thermal blanketsand unstows thepolarizingfilter and installs it on his 70mm camera. Then,taking the gnomon and tongs, he surveysthe area to find asuitablerock/soildistributionsite suitablefor the polari-metric sample series. After completingthe distant and nearpolarimetricphotography,a suitablequantityof representa-tive samples are takenfrom the site.The LMP meanwhile unstowsthe SWC from the MESA, extends thestaff, unfurls the foil shade and emplaces the SWC experimentapproximately60 feet NW of the LM taking cross-sunand down-sun photographswith the 70mm camera. Followingthis, theLMP conductsa rather detailedLM site inspectionand descrip-tion noting particularlythe conditionof the landingstrutsand the surface/footpadinteraction. During this site in-spection,the LMP pauses to take three photographicpanoramas,one each at the 12, 4 and 8 o'clockpositions.

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The flag kit is then unstowedfrom the MESA. While theLMP drives the staff into the surface the CDR unfurlsthe flag and then mounts the upper staff and flag ontothe lower staff. The crewmenthen take each other'spicturesstandingnext to the flag.Having completedthe tasks for EVA-I, the crewmen beginthe EVA closeout tasks. The LMP places SCB #1 intoSRC l which he then closes and seals. He then retrievesSCB #3 and #4, ,closesthem and places them atop theSRC. He tidys the MESA thermalblanketsand pre-pares to dust off the CDR's EMU.The CDR transfersall 70mm and 16mm magazinesfrombeneath the LRV seats into the ETB along with themagazinesfrom 'the500mm lens camera and the 16mmcamera and the maps from the LRV map folder.Using the MESA brush, each crewmen brushesthe loosesoil from the other's EMU. The LMP then retrievesSCB #3 and ingressesthe LM. The CDR then attachesthe LEC to SRC #1 and transfersit into the LMafter the LMP has completed his ingress. The ETBis then transferredinto the LM via the LEC.The CDR powers,downthe LCRU, retrievesSCB#4 andingressesthe LM. The LM cabin is then repress-urized,,terminatingEVA-2.

3.1.3 EVA-2The second period of surface EVA activityis planned to beginapproximately36.5 hours after touchdownand is planned for7 hours duration. The CDR again backs out of the LM hatchonto the porch and receivesa jettison bag from the LMP whichhe discardsonto the surface. The CDR then passes the LECto the LMP and descends to the lunar surfacewhere he unstowsthe EVA 2 pallet from the MESA and prepares it for transferinto the cabin. The pallet is transferredinto the cabin andthe ETB transferredto the surfaceand carriedto the LRV.After uncoveringthe BSLSS and the 500mm lens camera, the16mm and 70mm magazinesare offloadedand stowedunder theLRV seats (one magazine is attached to the 500mm lens camera).The maps are placed in the map holder and the ETB returnedtothe MESA table.

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The LMPcompletes his cabin housekeeping activities and thenegresses the cabin bringing with him the empty EVA-2 palletwhich he discards to the surface before closing the hatch.He descends to the surface, retrieves the two spare LCRUbatteries, stows one in the +Y footpad and places the otheron the LRV. The CDRthen turns off the LCRU, installs afresh battery and turns the LCRUon again. The LMP then un-stows and opens SRC2 and off loads SCB #5 to the HTC. SCB #6and #7 are unstowed from the pallet. SCB#7 is hung on theHTC and SCB #6 is attached to the geology pallet. Excessequipment in the form of 3 core tubes, one core tube cap dis-penser, 2-20 DSBD's and one SESCare removed from SCB #5 andstowed in SCB #7 which is then removed from the HTC and stowedunder the LMP's LRV seat. SCB #2 is removed from the under-seat location and attached to the HTC.The CDRand LMPthen assist each other in configuring thePLSS tool harnesses for the geology traverses. The LMPwill carry a hammer, the core tube cap dispenser, and SCB #2.The CDRwill carry SCB #5 which contains the 3 core tubesand one SESC. The 70mmcameras with 20 DSBDare installedon the RCU's and the HGAand LCRUare configured for traverseoperation. Both crewmen mount the LRV, drive to the initi-alization site to initialize the navigation system, and beginthe traverse to geology station #5.

(NOTE: For purposes of the final edition of theLunar Surface Procedures, the geology traverseinformation is contained in Section 3.6.)Upon returning to the LM after geology station #8 thenavigation and LRV displays are read out and the LRV parkednear the MESAand powered down. "TheCDRconfigures theHGAand the LCRUfor TV coverage and then begins offloadingequipment from the LMP's PLSS tool harness. SCB #2 isstowed on the HTCand the LMPremoves SCB#5 from the CDR'sPLSS and stows it also on the HTC. The CDRretrieves theETB and stows all 70mmand 16mmmagazines (including themagazines on the 500mmlens camera and the 16mmcamera).The lunar surface maps are also stowed in the ETB whichis then attached to the MESAtable.The LMP places SCB #5 into SRC #2, closes and seals it.SCB #2 and #6 are removed from the HTC and geology palletand placed atop SRC#2.Using the MESAbrush, the crewmen dust off their EMU's.The LMP, carrying SCB #6, climbs the LM ladder and in-gresses the cabin. 36


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The CDR meanwhileplaces the BSLSS and the 500mm lenscamera on the LMP's LRV seat and covers it with thethermal blanketpreviouslyused for this purpose. Whenthe LMP is set, SRC #2 and the ETB are transferredintothe cabin via the LEC. The CDR then picks up SCB #2and climbs the ladder to the porch. After handingSCB #2to the LMP he receivesthe LEC, stows it on the porch,and ingressesthe cabin to terminatethe secondsurfaceEVA period.

3.1.4 EVA-3The third and final periodof lunar surface EVA activitybeginsapproximately57 hours after TD and is planned for6 hours duration.The CDR egresses to the LM porch and pauses, receivingajettison bag from the LMP which he discards to the surface.The CDR hands the LEC to the LMP and continues his descentto the lunar surface. The ETB is transferredto the sur-face and carried to the LRV where, after configuringtheLCRU for TV coverage,the CDR offloads the ETB contents tothe proper LRV stowagecompartments. The BSLSS is restowedbehind the LMP's seat and the 500mm lens camera is restowedunder the CDR's seat. After returningthe ETB to the MESA,the CDR replacesthe LCRU battery.The LMP, after transferringthe ETB, egresses the cabin,closes the hatch,,and descendsto the surface for his lastlunar expedition,.He retrieves the last LCRU battery fromthe +Y footpad and places it on the LRV floor pan and stowsthe BSLSS samplebag on the geology pallet forward hooks.He retrievesSCB #7 from beneath the LMP's seat and attachesit to the HTC along with SCB #8 from the geology pallet. The20 DSBD's are removed from SCB #7 and placed on the LRV seats.The CDR and LMP then assist each other restowingtoolsand equipmenton the PLSS tool carrier,then mount theLRV, power it up and depart the LM site for geologystation #9.

(NOTE: For purposes of the final edition of theLunar Surface Procedures,the geology traverseinformationis containedin Section3.6.)Upon arrivingat the LM site, the LRV is again positionedat the initializationsite and the nav parametersand LRVdisplays read out. The LRV is then parked near the MESA

39


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and powered down for the EVA closeoutactivitieswhile theLMP takes cross-sunand down-sun photographsof the LRV. TheCDR reconfiguresthe HGA and LCRU for TV coverageand thenthe crewmen proceed to offload the equipmentfrom their PLSSharnesses.The LMP then places SCB #7 and #8 and the BSLSS sample bag(from the geologypallet) on the MESA table. After checkingthe LRV to verify all samples have been removed,he removesthe 16mm camera from the LRV and prepares to photographtheCDR driving the LRV to the site from which the TV camera willcover the LM A/S lift-off.The CDR gets the ETB and offloads fPom the LRV: the 70mm mag-azines, 500mm lens camera magazine,,the 16mm cameramagazines,and the lunar'surfacemaps; and returns the ETB to the MESAtable. The LRV is then powered up and driven to the lift-offobservationsite approximatelylO0 meters East of the LM suchthat the LM is on a bearingof 276 from the LRV. The LRV isparked and powereddown except as requiredto support the TV/LCRU operations. The HGA is aligned and the LCRU switchedto the TV/REMOTEmode. LCRU power is switched to EXT toutilizethe remaining energy in the LRV batteries. The LRVis parked in this locationto permit observationof LM lift-off via remote controlledTV.The LMP stows the 16mm camera on the MESA and then retrievesthe SWC foil, stowing it in a bag provided for its protectionand then stows it in the ETB along with the final 16mm maga-zine.When the CDR has returned to the LM site, the MESA brush isused to dust off the EMU's as much as possible prior to in-gressing the cabin. The LMP ascends the ladder carrying theBSLSS bag and enters the cabin. The LEC is used to transferSCB #7 and the ETB into the cabin. The CDR ascends theladder to the porch carrying SCB #8 which he then hands tothe LMP. The CDR discards the LEC now lying on the porch andingressesthe cabin to concludethe final surface EVA periodof the Apollo 15 mission.

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3.2 DETAILEDEVA TIMELINEPROCEDURES3.2.1 SEVA

The det_tiledtimelineproceduresfor SEVA are shownon the followingvertical format pages. In the SEVA,the activityis primarilycenteredaround the CDR whostands on the Ascent Engine cover with his head andshouldersprotruding throughthe LM tunnel and abovethe LM. The LMP supports the CDR's activity byequipmentmanagementand secondarylunar surfacedescriptionsas viewed from the cabin windows.

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MISSION: APOLLO15 DATE: 4/19/71EVA: SEVAE FUN rlON

LMP ACTIVITIES; IT MEI CDR ACTIVITIES cA _ cM P R-- 0+00 Stand on Ascent Engine coverwith head and shoulders pro-truding through docking tunnelhatch

Describe lurain and landmarksto assist in LM landing sitelocationHand CDR'S 70mmcamera to CDR Receive 70mmcamera from LHPstanding in docking tunnel

Using 70mmcamera obtain 360vertical stereo panorama (useDescribe lurain, surface approximately 36 frames)conditions and landmarkfeatures as observed throughLM windowsInterim stow 70mmcamera Hand 70mmcamera to LMPDescribe general surfacecondition as they appear indirections of preplannedtraverses for possibletrafficability, landmarks and0+I0 ALSEP site locationDescribe in general the initialimpressions of the Front,

Rille, North Complex, MareSurface and Boulder fields

Hand 500mmlens camera _ CDR Receive 500mmlens camera fromLMPDo long lens photography of Front.Rille, North Complex, Boulderfields and any other prominentfeatures

Interim stow 500mmlens camera 0+20 Hand 500mm lens camera to LMP45


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MISSION: APOLLO 15 DATE: 4/19/71EVA: SEVA

_UN( ION

LMP ACTIVITIES ITIMEI CDR ACTIVITIES ,_ cDP RInterim stow 500mm lens camera 0+20 Hand 500mm lens camera to LMP

Describe lunar surface conditionsin immediate vicinity of LMsuch as crater distribution,fragmentation,boulder popu-lation, and any noticableaffects of DPS exhaust on thesurface

SEVA Termination 0+30 SEVA Termination(For termination procedures, see (For termination procedures,Lunar Surface checklist) see Lunar Surface checklist)

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3.2.2 EVA-IThe detailed proceduresfor EVA-I are shown on thefollowingverticalformatpages. The crew cuffchecklistpages which correspondapproximatelytothe timelineare shown on the far left-handfacingsheetsalong with the Voice Data Plan with whichcap-comcan assure that the requiredinformationis given by the crew to MCC-H and which assistscap-com in essentialcommunicationswith the crew.The crew'scuff checklistdoes not necessarilycorrespondto the verticaltimeline in content orverbageas this is a crew preferenceitem and con-tains those cues the crew feels they neeC to accom-plish the requiredtasks.

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CREWEVA CHECKLIST VOICE DATAEVA 1

CODE(I) MANDATORYREQUIREMENTFORDATAAT TIMEOR EVENTDESIGNATED

(2) DATAMAY BE DEFERREDUNTIL LATER IN EVA ORDEBRIEFINGNOTE: AT START OF EVA 1

SUN ANGLE_ 19 LM SHADOWENGTH= 20.2m(66.8ft) ASTRONAUTSHADOWENGTH= 5.28m(17.4ft)

i MU STATUSTABLES @ 30 MIN INTERVALS0+0( (I) CDR/LMPEVA WATCHSTART- MARKPLSS TO LM H20 TRAMSFER '_To_5o Tied_ - L_OS_ as req_ _*J PLSS P_mo - OFFJisconnect PLSS H20Connect L,4H20E_(_&) EtS: LED _u_p -CLOSELM TO PLSSH20 TRAHSFERCBII6) El.S:LED 9u_p - OPEHDisconnectLM H20Connect PLSS H20PLSSPump . ON

I To_so Tiedown - Tighten asi _egdIJ

I"PLS.._S._OLMH2.___ORANSFER _:_

Torso Ttedov_ - Loosen as reqd__

PLSSPump - OFFOt,_QnP_:% PLSS H20Connect LMHL_OCB(_6) ECS: LEG Pump- CLOSEL_ TO _.SS H2Q T_$FER IIIIB (1 6) E CS : L CG Pump- OPENDisconnect LMHZO I tC_nl_ec'L9'LSSZOPLSS PL,mp- ONTorso TledoWn - Tfghten asreqd

)+IO5O


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FinalJune 28, 1971Ap01I0 15Mission J-I

NOMINAL TIMELINELUNAR SURFACE EVA 1

IEVA ' "":FUNITlO_lLMP ACTIVITIES , , CDR ACTIVITIES _' "r---_-ITIME, , , oI I v p RSTART EVA WATCH 0+00 START EVA WATCH (CALL "MARK") -o "om; irrl m_') G')I'rl ;_O0 O_0 C)"0 -0m

NOTE: DETAILED PROCEDURESRE _ --.PRESENTEDN "LUNAR SURFACE _zCHECKLIST", "EQUIPMENTPREP u= u_EVA I"SECTION

OPENHATCH 0+I0 EGRESS

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CRE:.IEVA CHECKLIST VOICE DATA

O+l_Om._ c_-[,_l (I) LMP -. Deploy CDR PLSS antenna_:-10 Move T_rougn _atch - Co_ Ck

PLSS Antenna - DeployMESA . Deple}Jett Sag - DiscardLEC - Deployto LRV :_ideDescend to Surface

I 1 F_ - 3 Minutes

I dett Bag - Under lH

OET,-T...... _n (2) CDR -. Jettison BagETB - TO Ladder Hook_SA Height- Adjust81ankets - Open[LMP: Egress]LMP PLSS Ant. - Unstow

LMP - EVA 1 IIR _SS Antenna - Deploy I

,ttgag-PlacelnHatch I (I) CDR -. Stability & MobilitybEC-oCOR discussionRecorder - OFFVOX SENg (2) - _k_XUtiltoy ' Flood Lts - OFF _ CDR -. LM checkLEC- To Overhead HandholdETB - Transfer ,1LEC - Stow to SideEgressHatch - CloseDescend to Surface_OR: LMPPLSSAnt.-Unsto_

-- CDR - EMUcheck CDR LMP02_T_,.o,..s_o_ FLAGS

_c......o,ripod PRESS TV - Position 12:00/50 rt,

l .... Set f-l), '2.... Pk, COOLCheck IlQUTV Reception0.29F_1 T_al Blanket - R#_loveI I Ck - Walking himges - Lo(ked

--I - Chassis - Parallel

- Outrigger Cables - TautLRV Left Tape - over StrutLRVR_gntt... Deploy (l) LMP -Stability & Mobility[LMP: O-ring & Aft lanyar_

I Right Tape - P ull - MARK; Aft discussion

Chassis Deploy - Fwd Unlock0utrlg3er Cables - DISCNTLeft Tape- Pull

0+37 LRV- SetOp"d.'Ch......LockingePiBs-Check"'.s,u,, (2) LMP - Verify cb configuration - OK

>0+25k Fam m ) minutes

ContingencySample - CollectS.pl,-To,l,tfo_ (I) CDR- Deploy LMP PLSS antennaCheck CDR ReadyLRV - Unlock from LMDescend toSurfaceAft Lanyard - Unstow- Pull to assist- _ardPalletPost-Erect (I) CDR - TV position OK+3 LRV - getupCbass,,.i,_,.s-che_k Settings Peak f 11 12.5mmBattory Covers-Check Closed _ 1_

CDR LMPIII LMP - EMUcheck 020+_t CS on LM porch FLAGSPRESS52 COOL


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MISSION: APOLLO15 DATE:6/2/71EVA: lI ', T_EVA l FUh Tl_LMP ACTIVITIES , CDR ACTIVITIES _ -c--c-TIMEI , _ oI v P R

--Assist CDR 0+I0 Move through hatch _Deploy CDR PLSS antenna Deploy PLSS antennaPlace Jettison bag in hatch Descend ladder to deploy MESARemove LEC, loop end, from Deploy MESAstowage bag Retrieve & discard jettison bag _-_Qinto Quad IPass LEC, loop end, to CDR Deploy LEC

mRecorder-OFF Descend ladder to surfaceVerify VOXSENS (2)-MAXVerify CB configuration Check footing, stability, andmobilityUtility & floodlights - OFFAttach LEC to overhead handhold _Kick Jettison bag under LM

-Transfer ETB to surface 0+20 Transfer ETB to surface _Hang ETB on LEC stowage hookAdjust MESAheight

Remove from handhold & s'i;ow LEC Loosen MESAblanket aroundMove through hatch TV camera _----Open MESAblankets _ _Close hatch Deploy LMP PLSS antenna _lUnstow deploy, and place \\ _Descend to surface TV tripod on surface _nstow and mount TV cameraDeploy PLSS antenna on tripodPosition TV at 12:00/50'Check footing, stability,, and to view Quads I & IVmobility Adjust TV per MCCrequest

Remove CSC from pocket _=Deploy CSC handle & bag _-Collect contingency sample Remove LRV thermal blanketRemove handle & close ba_ Check walking hinges latched

Climb LM ladder & place cont O+ Deploy left LRV offload tapesample on platform across secondary strut53


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CREWEVA CHECKLIST VOICE DATA

0+30

(2) ETB Contents:__ cam w/mag LL(HBW) 2-70rnm mags KK,NN (HCEX) 1-70mm mag O0 (HBW) 3-16ram mags CC,DD,EE 500mmLens camera/mag MM(HBW)

_ MapsLRVLRVo.toplo_.tDoc_ _ BSLSSTest Drive LRVLNP: Photo CDR on LRV]

Power Down & Dismount LRV0+46 Post Locks - Lift

- TO LAVC_ble * Connect[LMP: EVA , Pallet to MESA]Rak - To MESA Side F._-To Handhold /_/LC,A Ceble - Connect TO LCRU J_J

(2) LMP-RpL 16mmmag ____ on 16.mm cam2_6.c.-_.,.._,-_._.ca_ _ I) LMP-Piloto LRV 16mmcam (f8,1/250,24fps)ag'CC_ - on ,_ Photo * CDR/LRV_1_ ( f8.1/250,B4FPS) -1F_,_IR....o.._-To_SA- Amp-Hr Bat 1 ITemp Bat 1CDR 70mmCam - TO LMPRCU_'NN'-ToCO,o_c. _ _np-Hr Bat 2 Temp Bat 2cob_ C.-ToB,oo_.. Amps Bat;l Temp LF mtr50 EVA #l Pallet - To MESATable_ssL_o.,.,-cDo__._ Amps Bat:2 Temp RF mtr16_ Cam Bracket - OfscardLIOHan(kndff) - TOPa]let Volts Bat 1 Temp LR mtrVolts Bat 2 Temp RR mtr

I) LMP-Rpt 70mmmag/frame on CDR cam/

I+554


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MISSION: APOLLO15 DATE: 6/2/71EVA: 1EVA CDR ACTIVITIES ; FUN,_I I -'-MP ACTIVITIES TIME j _--Climb LM ladder & place cont 0+30 Deploy left LRV offload tape _ rsample on platform across secondary strut <


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0+50

_I O.S3_IGAI- Unsto. at HCSA_I Yellow Bracket - DiscardVelcro strap - BlscardCable o Route behind TCU- Connect to LCRU-- LMP: Unstce4 tools

0"56_ll_ip_d to *Z StrutIv PWR SW - OFFw TV Cable - Disconnect & StowTV Camera - To TCUTV Cable - Connecto.-.o.WRSW - INT

I_ I l+O0 CTV PWRSW ONi |

0+52 Geology Pallet - TO LRV_,J ...d.ll.A,a.,._,-_._.e I I (I) LMP -- CLOSEORGANICCONTROLSAMPLESRCB) - TOMESATableC-Bag #l - Unsto_Control Sample - Close [C-Bag #I - TO HTC. (L)

3+56 Unstow from Pal let _*Tongs m TO HTC"Ext. Handle/Scoop - TO BTC.Penetr_ter - To Pallet,gnOmOn - TO COP,_eat-C-Bag #2 - To HTC (g) I*C-Bag #3 - To pallet back IVise - To pallet

_ I+04 Core Stems & Caps-To C-Bag B2 ISample Bags - TO Floor Pansi_ C-,a ,2 - loU_Seat Bag II _ C-Ba_ #4 - To _C {R) m I

-(I) CDRILMP-EMUcheckCDR LMP

+ol Whip Antenna - DeployLCHU Sel - PMI/NB 02Check - AGC, TEMP, B PWRLCRU Sel - TVLCRU Blankets - lOO_ open FLAGS

Conn. c....LCH,IClosed PRESS,,_O_sb-eploy - COOLHGA - Point TO Earth

Contents - To LBV_TB (Empty) - TO Ladder IIookLMP PLSSAnt. - Stow_L_ [L1P IngreSS_

Pallet #1 - TransferLECooksToLadd..... (1) CDR-Rpt LCRUIIGA - Stow

I+IL LCRU Sel - PMlfgB

,+OS Rake-To Pallet ' (I) CDR-LCRU covers open 100%

Secure HTC for Drlvlng

Check Lanyards Clear of Wheels_o,:LMPPLSSAnt.-BtO.] (2) CDR-Rpt mag/frame on CDR cam+06 Ascend LadderCont. Sample - Retrieve /Ingress LMCon_ S_ple - StOwCBOB)O":TV-OPC. _ (l) LMP-Contingency sample into LM_R AMPL- OFF iTLM PCM - LOLEC-ToOverheadHandhold (I) LMP-Re-verify cb configuration OK

+I0 Pallet - Transfer into bM iLEC Hooks toSurface

LEC - Stow to Bide I_"Pallet - StripPallet - To LH Floor

I+I056


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56/337

CREW EVA CHECKLIST VOICE DATA

I+10

(I) CDR-Readout LRV displaysHEADING Temp Bat 1BEARING Temp Bat 2

,[_tRv DISTANCF Temp LF mtr.,3 RANGE Temp RF mtr..vr_V'cB-CLOSE"_".,t. S_te __Bat 1 Temp LR mtr_..-.eado_t Amp-Hr ;at 2 Temp RR mtr_mm SSD ROLL[ [PITCH[t.p.css.t.. ,.s,_ COMPUTFDNAV HEADING_ * Hammer lgl: Core ri_r

Core Tube Caps(Bag #I pkt,lc-Bag- (2) LMP-Oettison Palleto CDR]Tongs - Tether

Geology Equip - LMP EMU: Hammer Core tube cap dispenser Core tube tool SCB #4 Scoop/Ext Hndl (tethered)Geology l-quip - CDR EMU: SCB #1 Tongs (tethered)NOTE: ('()re tubes in SCB #1U--03. L-04. L-IO

t+14 Egress_' tMga"et-,.._d_tc,C_o,e NOTE: 20--DSBDNUMBERSERIESOgs_e_toS._'... 156-164, 166-168, 170-177I 180-182. 186-190, 192-199. 203-206coR:MP PLSS Ant. -UnstowMESA Brackets - Removei J Ttdy MESAThen_l Blanketsi_/ [CDR:GeO[(_-ToLMPEHU] (I) CDR-MaPk depart time (I+25)

oCore Tube Caps_-_.g- (2) kMP-Readout LRV displaysc.Bag #I - TO CDR+2o _.d_eIS:.bTe_b._ Temp Bat 1TC - Check Secure B Closed_0o,sp. To7_ c_ " Temp Bat 20_ Cam - TO RCLI

,6.c..-B,V2BB,,2pB DIS_)-E Temp LF mtrTemp RF mtrIAmp-Hr -Batl Temp LR mtrp_]Bat 2! Temp RR mtr

CDR LMP02FLAGSCDR/LMP (U check PRESSCOOL

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MISSION: APOLLO15 DATE: 6/2/71EVA: 1EVA I TAS,UN( '1_LMP ACTIVITIES IT MEI CDR ACTIVITIES 8|-- 1+10Disconnect LEC from pallet

Stow LEC inside cabin Transfer LEC hooks to surfaceRemove from pallet & stow Stow hooks on ladderfood, batteries & LiOH cans Stow HGAfor traverseLCRUMODEswitch - "PMI/WB"Mount LRVPlace pallet on LM floor Power up LRVMove through LM hatch Orient LRV for Nay systeminitilizationRetrieve & discard pallet Power down LRVLRV Nav CB - "CLOSE"Close LM hatch Nav Reset - ResetDescend to surface Reade Heading, SSD, Pitch & RollRemove & discard TV stowage bracket to MCCTidy thermal blankets aroundMESA& cover cavity Verify Bearing, Distance & Range -ZERODismount LRVAttach geology equipment to EMU Attach to LMP EMU: Hammer Core tube tool Core tube cap dispenser SCB #4Attach SCB #I to CDR EMU I+20Tether handle/scoop Tether tongsCheck tool stowage bars. Secure Attach 70mmcam/bag disp to EMU& close HTC

Mount LRV - Fasten beltAttach 70mmcam/bag disp to EMU Power up LRVCheck 16mmcam set for traverse _ _photography <


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CREWEVA CHECKLIST VOICE DATAI+30

[_]_Gyro - To Hou UpdateI+2S TRAVEL (0:17) I_I

Limea_nts_ fillet$_ moundsRaised r111e rlm (levee)Block d_strlbution

I+R2 _Pl _0_02) Canyon Craterl_R4 tRAVEL _O_U7) | l

_ow _jecta d_stributlon _Orlve close to rim l_III+51 Geolo_f Station #1 (0:15)Sample radiaIly(rlm/blanket)

LRV $y_te_ - Readout I1 0:t7) _'iklnea_nts flllets, _umdso_Is_ r111e rlm (levee)B1=kd,,tr1_Uon (I) CDR-Mark arrival time (I+42)

1+42 CPI (0:02) Canyon CraterI II+d4T_WLo:o7) (2) CDR-Readout NAV displays// oE_ EJecta distributioneOrIve close to rim,+SlO_OlO,yt.to1


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MISSION:APPOL0 15, J-1 DATE: 6/2/71EVA: 1 ILMP ACTIVITIES ITIMEI CDR ACTIVITIESI-- I+30

The traverse to the first checkpointnear CanyonCrater will cross the typical smooth mare fillon the approach to the rim of Hadley Rille.

During this portion of the traverse the crewshould observe and describe characteristics ofthe mare fill material, surface features and blockdistribution and note any differences between themare and Rille rim material,

I+40

Arrive at Checkpoint Arrive at CheckpointReadout NAV displays

Traverse to Station #I (7 min) Traverse to Station #I (7 min)The traverse to Station #I will be around ElbowCrater. The low scarp should be visible aroundElbow Crater and there should be observable dif-ferences between the mare and Rille rim material, oCrew should describe the distribution pattern = =around Elbow Crater.

I+5061


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I+50

" / (I) LMP .-Readout LRV displaysx HEADING Temp Bat 1EARING Temp Bat 2 ' DISTANCE Temp LF mtrRANGE Temp RF mtr_/ , ., .. Amp-Hr Bat 1 Temp LR mtr

" SIAT'I't)N Amp-HR Bat 2 Temp RR mtr

n

o

STATION!

- (1) CDR/LMP EMUcheck CDR LMP02I 1_'o6RA,,_Lo:o,_t 1-I FLAGSI .E,oo.e,o 6a,,st.ibu oo=1Change in SlOpe toward front _ PRESSJChanqe in roc_ type _Change in ground texture COOLSt. George ejecta d_st.2+14 Geology Statlon #2 (0:45)C_mprehenslve sampleOocumented sample "T

(SESC - tO CDR C-Bag)Double core(Trench - SESC and soil)

{ i (Stereo pan-lOOm aTonq front)l I_Fi (_o_> (1) CDR -. Stow gnomon_H ('e"_t_'te_) L_ n Mark depart time ___(2+06)(2) LMP -. Readout LRV displays

2 (O:gS) I I HEADING Temp Bat lI I .--r_.,,di._,bo,io. I=I BEARING Temp Bat 2Change tn slope toward front _.Ch,_t.... kty. ; DISTANCI" Temp LF mtrChlnge in ground texturest._,,J,:ta di,. RANGE Temp RF mtrt t2*_4_.olo_st.to..(o:.)r I Amp-Hr Bat 1 Temp LR mtr

Sample radially J:_r_h_._,,_._. _ Amp-HR Bat 2 Temp RR mtrOocwmented sample ._ Double coreTrench - $ESC a*d So lI I ($ESC - To CDR'S C-Bag)M I

2+i-062


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MISSION: APOLLO15, J-I DATE: 6/2/71EVA: 1 ILMP ACTIVITIES ITIMEI CDR ACTIVITIESI-- I+50Arrive Station #I Arrive Station #IReadout LRV displays Park & powerdown LRVDismount LRV Dismount LRVLCRUSel Sw - FM/TVStation #I geology (15 min) Poiat HGAto earthStation #l geology (15 min)

Station #I is located on the the southern part of theElbow Crater ejecta blanket.m Area #I tasks:I. Radial sampling of Elbow Crater

2. 70mmPanorama

m 2+001

P

Check tools secure & HTC closed Stow Gnomonon seat backStow HGA--Mount LRV LCRU Sel Sw - PMI/WBMount LRV

Readout LRV displays Power up LRVTraverse to Station #2 (8 min) Traverse to Station #2 (8 min)The traverse to Station #2 is along the ApennineFront slope to the North side of St George Crater.

I2+1063


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2+I(

,"" SI, GEURGE_

ii : _ ] _ 5_ (I) CDR - Mark arrival time (2+14)

_ x -37s_ (I) LMP - Readout LRV display--s------i B x_ -z_o .. I HEADING Temp Bat 1- TrFx_-Iz\_ [BEARING Temp Bat 2I_E Temp LF mtr

I RAN.GE Temp RF mtr[.Amp-HrBat l Temp LR mtrTATI_ 2[Amp-HR t 2 Temp RR mtr

rF T_'_ST':GEORGE,_t. _ --_ ,_ At 2+30_' _"_ : ,, -37_ _ CDR/LMPEMUcheck_)_ ,X_ -2_ _Y CDR LMPF - ( 02- "},lr.)L -IZ5 ,,_ FLAGS"" :.; ' " PRESSCOOL

STATION2

2+5064


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MISSION: APOLLO15, J-I DATE: 6/2/71EVA: 1 ILMP ACTIVITIES ITIMEI CDR ACTIVITIESn

-- 2+I00The crew should look for changes in lithology orground texture to locate the base of the frontand compare the mare and Rille rim material tothe Front. A descriptionof the character anddistributionof the St George ejecta blanketis desirable.

Arrive Station #2 Arrive Station #2Readout LRV displays Park & power down LRVDismount LRV Dismount LRV

LCRU Sel Sw - FM/TVStation #2 geology (45 min) Point HGA to earthStation #2 geology (45 min)

Geology area #2 is located near the base of theApennine Front north of St George Crater.

t2+20

Area #2 tasks (in order of priority)I. Radial Sampling of St George Crater (slope permitting)2. Comprehensive Sample Area at Front3. Double Core tube4. 500mm lens camera photography - blocks on St. GeorgeCrater rim & Hadley Rifle5. 70mm Stereo pan from high point (lOOm base)6. SESC Sample (from bottom of a trench)7. Penetrometermeasurements.

2+5065


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2+50

{I IZ+58 TRAVEL (0:89) l_,l Block dlstnlbutlon Posslble rock flows Patterned ground Cmpre crater frequency/sLate Observe EVA II route

3+08 Geology Station #3 (0:14)Vertical/lateral changes .c Oocu_nted samples--'Plow"/Front(-Mare)

13+22 TRAVEL (0:28) i i Front/Mare relations Possible ray material _ CDR LMPc_,r,oearl_.... --_ (I) CDR/I'MP--EMU check Extent of "slide" boundar_ U fFLAGSPRESSCOOL

(1) CDR -. Stow gnomon-. Mark depart time (2+59)(1) LMP -. Readout LRVdisplaysHEADING Temp Bat 1BEARING Temp Bat 2DISTANCE Temp LF mtrRANGE Temp RF mtr_mp-Hr Bat 1 Temp LR mtrAmp-HR Bat 2 Temp RR mtr

2+5g TRAVEL (0:09) I_t

3*08 Geology Station P3 (O:14).Verticalateral changes _"*Documented samples-"Flow"/Front(-Mare)

I _3+22 TRAVEL (0:28) | / -_rve EVA ]] routet I Front/M ..... l atlons m-I1 1 .Possible ray_terlal 1-_-

,C_are to earlier are T. Ext_nb 9f "slide" boundary (1) CDR - Mark arrival time (3+08)(1) kMP - Readout LRV displaysHEADING ITempBat 1BEARING 'mTempBat 2DISTANCE Temp LF mtrRANGE TempRF mtrAmp-Hr Bat 1 Temp LR mtr3+I-0 Amp-HR Bat 2 Temp RR mtr

66


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MISSION: APOLLO 15, J-I DATE:6/2/71EVA: 1' EVA I

LMP ACTIVITIES T ME CDR ACTIVITIES-- 2+5

Check tools secure & HTC closed Stow gnomon on seatbackStow HGALCRU Sel Sw - PMI/WBMount LRV Mount LRV

Readout LRV displays Power up LRVTraverse to Station #3 (9 min) Traverse to Station #3 (9 min)

3+00I

The traverse to Station #3 is along the base of theFront and should approach the edge of a debrisflow. Observation ilnddescription of the Frontmaterial should be made for comparisonwith themare material. Appearance of the debris flowshould be described.

o 5"

Arrive Station #3 Arrive Station #3Readout LRV displays Park & powerdown LRVDismount LRV Dismount LRV

LCRU Sel Sw - FM/TV3+I0 Point HGA to earth67


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3+I 0

0 FI_ :"_ [ ' X " L

! STATION3.Tj"i

I,_"-_. _=___ FLC_N ._,, !11 _'1_

i;z STATION3l# (1) CDR -. Stow gnomon, Mark depart time (3+22)- (2) LMP - Readout LRV displays

HEADING Temp Bat lBEARING Temp Bat 2_- Temp LF mtr

Temp RF mtrt l Temp LR mtrt 2 Temp RR mtr

At 3+30r_ (I) CDR/LMP- EMUcheck CDR LMP, O2F-TKPRESS

COOL

3+5068


67/337

MISSION: APOLLO15, J-I DATE: 6/2/71EVA: 1

LMP ACTIVITIES iTIMEI CDR ACTIVITIESl-- 3+10 Point HGA to earth

Station #3 geology (14 min) l Station #3 geology (14 min)Geology area #3 is at the base of the Apennine Frontadjacent to an area believed to be a debris flow.

Area #3 tasks (in order of priority)I. Describe the area and compare to mare & Front2. Documented samples of the Front & flow material3. Describe any vertical and lateral changes inthe Front. Compare to Area #2.4. 70mm pan5. Describe any notable characteristicsof theplanned EVA-2 route.

Check tools secure & HTC closed .3+20 Stow gnomon on seatback

t Stow HGA

LCRU Sel Sw - PMI/WB __Mount LRV Mount LRV _Readout LRV displays Power up LRV m mTraverse to LM (28 min) Traverse to LM (28 min) m mc-e (-FP o oDuring the return traverse across the mare, observe r- r-and describe the characteristicsof the debris flow. _ _:

" Make any additional observationsof the plannedEVA-2 route that are possible. Continue comparisonof the Mare/Front/Rille materials. Describe anypossible ray patterns that may be observed.Jm Ieadout LRV & NAV system Park & Pwr down LRV - Read NAV_ displays 3+50 to MCC

69


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3+50 I) CDR -- Mark arrival time (3+50)-- I) LMP Readout LRV DisplaysHEADING Temp Bat 13._BarkBg BE--_Z--A--_TN--6--TempBat 2Heading SE; facing SEO BayBa.CB-om. D'DI-S-T-A-N-C_: Temp LF mtrLCR.el- TV_ RANGE Temp RF mtrGA _ Point To Earth7o-c,_-To_de,S.t 7im--'__-at 1 Temp LR mtr

Tongs- To HTC p_HR Eidt2 ) RR mtrLMP Geo Equip:Core Tube Caps- Discar(Core r_-_mer - TO HTCtHor - TO HTCC-Bag #4 - Remove From LMITid gelcro Covers_MP: Remove C-Bag EliC-Bag #4 - Under EN_PBeatC-Ban #2 - TO HTC (R}

F"J3+_RV Systems - Readout Dismount LRVLMP Seat - Fold_I 70_com" Under Cogseat

Ext Handle & Scoop - To HTC[C_R; LI_a Eq - To LRV]

.Core Tube Caps & rammer

H_InerC-Bag #4 -To LMP Seat bagC-Bag B2 -ToHTC (R)i"'"-'-"idy Ve|c;oT_o_TeCrs(L)

(I) CDR/LMPEMUcheckCDR LMPN 3._,p,_ -o-,oo 02,_ U_T - T_ther_,_ c_ Ba__oE_p_sk9 FLAGS

_- TO LRV PRESS,o_ COOLHGA - StowLE_/,s_,-_.,_,B FLMP - Rpt Dome Removal Tool Temp-

_.,B,,ooo: L Label Reading

_rive to ALSIP S]iECAUT]OH

DO Sot Polnt IIGA or t&_within*20 of ALSEP

-(1) LMP - Rpt RTG Fueling (time)3+55 SEQBay Doors - Open

i Pwr Pkg - Offload- Position for Fuellnq

I I .ppt.s) -p=. I I _FLMPRpt Fuel Transfer Tool TemPIIt _T'Tetbe_ 1 /abel Reading

Carry Bar - To CBR /Fuel Cask - Tip Down:- _e ToolE._g_CDo_k (2) LMP SEQ Bay doors_ -g_. _Bi,_.rd - - closedFuel Tool - Engage & CheckFuel Element - Into RTG

4+06 _ RTG FueledPwr Pkg - TO Carry BarSEQ Bay Doors - Close

I_'_I ALSEP-To DeploySite I 1

4+170


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MISSION: APOLLO15 DATE: 6/2/71EVA: 1LMP ACTIVITIES ITIMEI CDR ACTIVITIES| I-- Readout LRV and NAV system 3+50 Park & pwr down LRV - Read NAVdisplays to MCCLRV NAV CB - "OPEN"

Dismount LRV Dismount LRVLift seat & fold seat support down LCRU Switch - TV RMTPoint HGA to earthStow 70mm cam under CDR seatStow ext. handle and scoop on HTC Stow 70mm cam under CDR seat

Stow tongs on HTCRemove hammer, core tube caps &tool from LMP PLSS and stow onHTC

Remove SCB #1 from CDR PLSS & Remove SCB #4 & stow under LMPstow HTC seatOpen SEQ Bay doors Remove SCR #2 from under LMPseat and stow on HTCOffload ALSEP pkg 2 (pwr pkg) Offload ALSEP pkg l (expts pkg)

Remove and discard boom-to-pkg-stickRemove & discard boom-to-pkg stick Move expts pkg clear of SEQ bayPosition pwr pkg for fuelingPull tool stowage pip pins (4)Unstow UHT'S pass one to CDR Tether UHTtether 2nd UHTUnstow & pass carry bar to CDR I0 Assemble & attach carry carDeploy fuel cask lanyard to expts pkgRotate fuel cask down & discardlanyard under LM Walk to MESAUnstow & engage dome removal tool Unstow drill from MESACheck tool securely engagedRemove & discard dome/tool Place drill on LMP floor pan &Unstow fuel transfer tool lower seatTip power pkg down Remove thermal blanket fromover LRRR in Quad IIIEngage fuel transfer tool Offload LRRRpallet from LMCheck tool securely engaged Place pallet on surface &- Remove fuel element from cask remove LRRR from palletInsert fuel element into RTG

- Report RTGfueled Place LRRR on LMP seatRemove& discard toolTip pwr pkg up- Attach pwr pkg upCheck offload booms retracted Secure LRRR on LRV using- Close SEQ bay doors seat beltCarry ALSEP pkgs to deployment Stow HGAfor traverse- site LCRUMODESwitch - "PMI/WB"

4+0 Mount LRV71


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CRE_4EVA CHECKLIST VOICE DATA

4+10

'_ _'_:_ I (l LMP-Rpt Short SwAmps= : _" [Rpt Short Sw Connect (time)]_!] (I CDR-Rpt HFE cable connectL'_7 _-Vh3

[LL-_d] l'Vk_ LL/LIL

l CDR LMP02FLAGS(l CDR/LMP - EMU check PRESS4+30 COOL72


71/337

MISSION: APOLLO15 DATE: 6/2/71EVA: 1I EVALMP ACTIVITIES ITIM E CDR ACTIVITIES

-- 4+10 Mount LRV

I Power up LRVDrive LRV to ALSEP deploymentsite

CAUTION: ALSEP damage may result if radiating HGA or LGA isaimed within 20 of ALSEPantenna

Park LRV heading North, facingC/S siteReadout LRV battery tempsPower down LRVDismount LRVOpen LRV battery coversLCRUMODEswitch - "TV/RMT"

Place pkgs on surface with Point HGAto earthexpts pkg in final position ALSEP deployment planDisconnect pwr pkg from bar Offload LRRR from LRV & setReposition pwr pkg lO'East on surface facing sunRemove HFE stowage pip pins (3) 4+20 Offload drill from LRV &Tip pwr pkg down set on surface drill facingsunRelease RTG cable B. bolts (3) Release HFE Pallet B. bolts (2)Deploy RTG cable & discard Lift HFE pallet from pwr pkgcable reel Carry HFE pallet 15'N C/S

mReport shorting switch reading Unstow HFE connectorConnect RTG cable to C/S Place HFE pallet on surface _- Connect HFE cable to C/S mmRelease subpallet B. bolts (2) Q_Z_Lift subpallet from PWRPKG Carry HFE pallet 30' N _ o& place I0' N. of PWRPKG of C/S, deploying cable _

- Release Side B. Bolts (4)& CCIG cover boltLift SIDE from subpallet Place HFE pallet on surface &fold mounting braces

Remove B. Bolt blocking cable Tip pallet downreel Release probe box B. Bolts (4)Unstow cable reelDe

Documents

Apollo 15 Final Lunar Surface Procedures