Apollo Saturn V Facility Description Vol. 4

8/6/2019 Apollo Saturn V Facility Description Vol. 4

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UC APOLLO SPACECRAFT FACILITIESAND

GSE $Y$T~M DESCRIPTIONOctober 1, 1966


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K-V-

lnselt latest changes; destroy superseded pages.TOTAL NUMBER OF PAGES IN THIS DOCUMENT fS 43, CONSISTING OF:

Page No.

:-: viii2-1 thru 2-283-3. thru 3-26

issueOriginalOriginalOriginalOriginal


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FOREWORD

The Apollo/SaturnV Facilities and GSE Description document consists of the Folloing volumes:

Volume ! KSC lndustria! Area and Remote Facilities DescriptionVolume II Launch Complex 39 Facility DescriptionVolume Ill #SC Provided Saturn V GSE System DescriptionVolume IV KSC Apollo Spacecraft Facilities and GSE System DescriptionThis document is prepared in accordance with the requirement established by the KSCApollo/Saturn V Document Tree, dated October 25, 1966.


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TABLE OF CONTENTS

SECTKIN TITLE PAGI INTRODUCTION1.11.2

purpose*-*---*******-*~**********-----------*-~-**-****** 1-1Scope **___*__~_**~*****~*_______________I____** --_ ----*- 1-l

II SPACECRAFT OPERATiONS AND CHECKOUT AREAS2.12.22.2.12.2.22.2.32.2.3.12.2.3.22.2.3.32.2.3.42.2.3.52.2.42.32.3.12.3.22.3.32.42e4.12.4.22.4.32.52.5.12.5.22.5.32.62.6.12.5.22.6.3;*: 12:7:22.7.3

General------"**-------*---***"***---------**--"---=*****Manned Spacecraft Operations Building (M7-355) ----------==Function - ----****-**------------**----***-*~*----*--*=Locatio~---------------------~~~~~~~~~~~~~~~~~~~~~~~~~~~~Lescription-----------------------------*~--**--*---------Administrative and Engineering Area-------------------------Cafeteria and Mission Briefing Area----------=-------=======Laboratory and Checkout Apa ----I-=-c--I--------___I______Assembly and Test Area --------------------_r_____ em---..--Buildiqg Services Area t-------____------- w-----*-*---*-c**Timing System ~~~~~~~~~~~~~~~~~*~_P__________________~~~*Supply, Shipping, and Receiving Building (M7-505) ----==-==Function ~*~~~*~~~~~~~~~~~~*~_________________I__~*~~*~~~~Location----------------------=**=*~*---*---------------*Description---------------------------------------------==., parachute Building (M7-657) -,,,,,,,,,-,,,,,,,-,,,,----,---Function-------------------------------------------------Location **~~~~~~~~~~~~~*~~~~*~~~~~~~~~~~~~~~~~~~~~*~*~*~~De~sc~iption------------------=------------------~---*---Radar Boresite Range (M7-843, M7-867) --=---------==-===Function-------------------------------------=----=-------Location *--*I=--**-**-----------*---------*------*-*----Description-----------------------------=-=------=---*-~-~Ordnance Laboratory [M7=1417) -_-_------------I_---------~~~ctio~----------------------------------~-----~~~~~~~~~Lo~ation---------------------------------------~~~~~~~~~~~Description----------------------------------------------Ordnance Storage Facility (M7-1472) -=-=====-==--=--==-=-=Function-------------------------------------------------Location *~~~~~~~~~~~~**~~~~*~~~~~~~~~~*~~~~~~**~~~~*~~~~Description------------------------------------------*~---

g::2-l2-12-l.g:;;::2-122-122-122-122- 12- 12= 12-142-142-142= 12-142-142-142-142- 142-142-182-182-182-182-18


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TAELE OF CONTENTS (Continued)

SECTION TITLE PA2.82.8.12.8.22.8.9z-9' 12x22.9.32,PQ2,PQ.l2.10.22.10.32.112.11.12.11.22.11.32.122.12.12.12.22.12.32.132.13.12.13.22.13.3

Pyrotechnic Installation Building (M7-14691------------------ 2-Function--------------------------------------------------- 2Location--------------------------------------------------- 2Description ....-..~..--~~~.l-r..-~~~ --.....-rm,----- - ----- ----------- 2-Flight Crew Support Buildings tM7-4091~--------------------- 2-Function -------------------_________l__l_______--------- 2-Location -_-_-__*___C_C__r-__________1_____C__f_---------- 2-B,ascription --------------------_______l_____l_l____-------- 2-Environmental Systems Test Building No. 1 tM7-9611 --------- 2-Functjon--------------------------------------------------~ 2-Location _--_--__---ce_-_-___s__c__11__1______----------- 2-@scription ----------,---------------------,----------------~ 2-Hypergolic Test Buildings tM7-1210, M7-12129------------- 2-Function------ -----__*---__---_--____s_l________c__c_----- 2-Locatjon-------------------------------------------------~- 2-&scription -------------------_---------------------------- 2-Cryogenic Test Buildings (M-1412, M-1410) ---------------I 2-Functjon-------~----------------------------------------- 2-Locatjon------------------------------------------~-------- 2-@scription -----------------------------------------------* 2-Fluid Test Support Building tM7-1061) ---------------------- 2-Functjon------------------------------------------------~-- 2-Location----------------------------------~---------------- 2-Description -__-____---------------------------------------- 2-

III PROPULSION TEST FACILITY3.13.23.2.13.2.23.2.2.13.2.2.23.2.2.33.2.33.3

General Description---------------------------- I-LI1--.-----Structures --------------------_________r__________---------Control Suilding---------------------------------------------Test Stand-------------------------------------------------Umbilical Tower -------------_-__-------------------------Service Buildjng--------------------------------------------Approach Ramp Facility m-I----- ----------- - ----- ------------Self-Contained Atmospheric Protective Ensemble &CAPE?Bujlding---------------------------------------------------Support Faci I ities jJti 1 ties -mwuw -_-------------_---_---------

3-;::3-3-3-3-3-3-


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TABLE OF CONTENTS (Continued)

SECTION

3.3.13.3.23.3.33.43.5Z:$;*t3:103.113.123.13

TITLE PAElectrical ps,rer and Distribution ---l----_-_-l_-__-_-______I__Water System---.--------------------------------------------Air-Conditioning-------------------------------------------~Communications----------------------------~---------------*Television ------------------.-------------~~----------------propel/ant Facili ties ----c----_- -lr_-_____o-_--I-_------ --___propellant Transfer System------------------------------------Helium Transfer System--------------------.------------------~High Pressure Gaseous Nitrogen System ---_-------------------ACE-S/C Control and Monitor Transmission Links --------------Facility lnstrumenlation--------------------------------------Timing and Countdown---------------------------------------Area Warning System-----------------------------------------

;:g3-3-3-3-3-3-3-3-3-


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LIST OF ILLUSTRATIONS

FIGURE TITLE PAG2-2$1;

2-l KSC fndustriai Area, Spacecraft Operations Area ------------------2-2 Manned Spacecraft Operations Building Layout --------------------2-3 ACE - Spacecraft Data Links _-c---c--------________ ~---~~-.-...-.Spacecraft integrated Test Stands, GSE Locations and

'2-52-62-7;I;2-102-112-122-132-142-152-163-l3-2

Communications _Tf-v _ .._____________.m_- - _--_e--_..-- m-sw -----r---Spacecraft Altitude Chambers, GSE Locations---------------------Supply, Shipping, and Receiving Building ------------------------parachute Bujidjng---------------------------------------------Radar Baresite Range-------------------------------------------Ordnance Laboratory- *_C*FI*C_UI*_C-_-3_--------------C---C--Ordnance Storage Building -----------------____________o________pyrotechnic installation Building -------I-- -- ----- ---....-..---------Flght Crew Suppo& Buildings _______- ------ws wms--w----------- --Environmental Systems Test Building No, l-----------------------HypergoI c Test Building No. 2 ___________-__ J& aw----wwms cm -------

Cryogenic Test Buildings _-___________-_--*_----------------Fluid Test Suppo& Bu dng---------------- ------------ ---e-----

Propulsion Test Facility (Complex 161 -.-----_----------------..---Propulsion Test Facility (Complex 161, Service Building WorkPi&form Locations __--___---_---_------------. -s---s-m----------Propulsion Test Facility (Complex 161, Electrical PowerFacilities ---------__-_----_____r_________________------------Propulsion Test Facility (Complex 161, Facility Electrical PowerDistribution (Single Line Block Diagram? ___-___-----_-_-_-------3-5 Propulsion Test Facility (Complex 161, Wat,er System(Block Diagram)--- -----_----_---------_______________I____-----3-6. Propulsion Test Facility (Complex 161, Pneumatic andwater systems-------------------------------------------------

3-7 Propulsion Test Facility (Complex 161, Service BuildingAjpCondjtjc:~er -______ - _--- ----- -------- -----------------------3-8 Propulsion Test Facility (Complex 161, TV and CommunicationsSystem [Location Drawing) -- ______--_-_-------_---------------3-9 Propulsion Test Facility (Complex 161, Operationalintercommunication, TV Camera, and TV Timing Systems(Block Diagram) --____------- ---- ..e--C---..r - -------------- ------

Propulsion Test Facility (Complex 161, Control and SignalFlow Dagram--------------------------------------------------

2-72-92-132-152-162-172-192-202-212-232-252-262-283-23-43-73-93-113-12

3-133-14

3-153-21


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LIST OF ILLUSTRATIONS (Continued)

FIGURE TITLE PA3-11 Propulsion Test Facility Kompiex 151, Typical Command

Response Flow Diagr~----------------------------------------- 3-23-12 Propulsion Test Facility (Complex 141, InstrumentationBlock Diagr~-------------------------------------------~------ 3-243-13 Propulsion Test Facility (Complex IL), Warning System------------ 3-2


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SECTION IINTRODiJCTION

1.1 PURPOSEThis volume is tothe facilities and be used as a reference document for obtaining general descriptions oGSE systems located at the Spacecraft Operations and Checkout Area(Kennedy Space Center) and the Propulsion Test Complex (Cape Kennedy).1.2 SCCPEThe facilities and GSE systems described herein have been provided for the assemblyand test of the Apollo spacecraft. Section II contains a description of the facilitiesand GSE sy:tems at the John F. Kennedy Space Center (KSCI, and Section Ill containsa description of the facilities and GSE systems at Cape Kennedy (Air Force EasternTest Range).


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SECTION IISPACECRAFT OPERATIONS AND CHECKOUT AREA

2.1 GENERAL

This Section describes the facilities and ground support equipment (GSE) systems inthe Spacecraft Operations and Checkout Areas which are available for the assembly andcheckout of the Apollo spacecraft. Figure 2-1 provides locations and listi~ng of thevarious facilities.2.2 MANNED SPACECRAFT OPERATIONS BUILDING (M7-355)2.2.1 FUNCTION, The Manned Spacecraft Operations (MSO) Building (Figure 2-2)is used for modification, assembly, and nonhazardous checkout of all manned spacecraft2.2.2 LOCATION. The Manned Spacecraft Operations Building is located in theKSC Industrial Area on First Street.2.2.3 DESCRIPTION. The building is a multi-story structure of approximately600,000 square feet providing floor space for an Administrative and Engineering (A&Earea, Cafeteria and Mission Briefing (C&M) area, Laboratory and Checkout (L&Cl are2Assembly and Test (A&T) area, and Building Services area.2.2.3.1 Administrative and Engineering Area. This section is located in the northwing of the building and its primary use is office space for administrative and engineerinpersonnel. There are conference rooms, storage rooms, equipment rooms, etc. provided2.2.3. Cafeteria and Mission Briefing Area. This section of the building is locatebetween the A&E and L&C areas. The cafeteria provides services for both NASA andcontractor pe,;onnei and can be used as a conference room. The mission briefing roomaccommodates approximately 300 personnel.2.2.3.3 Laboratory and Checkout Area. Laboratory space is provided for checkoutand maintenance of spacesraft and GSE components. The Acceptance Checkout Equip-ment/Soacecraft (ACE-S/C) Ground Station is located on the third and fourth floors ofthis area. The astronauts quarters consist living quarters, exercise room, conferenceroom, etc. , and are located on the third floor of this area.2.2.3.3.1 ACE-S/C System. ACE-S/C is an advanced, integrated, checkout SYStern that provides centralized, programmed control of Spacecraft Checkout Operations.It has the capability of testing the individual independent systems and up to and includinthe integrated spacecraft.


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EAST


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LEGEND FOR FIGURE 2-l

Buildinu No.M7-355M7-409M7-505M7-657M7-863M7-867M7-961M7-1061M7-1142M7-1210M7-1212M7-1412M7-1410NJ7-I.417~7~~4~9M7-~472

NameManned Spacecraft Operations BuildingFlight Crew Support BuildingSupply, Shipping, and Receiving EuildingParachute BuildingRadar Eoresite Range, TowerRadar Boresite Kange, Control BuildingEnvironmental Systems Test Building No. 1Fluid Test Support BuildingSewage Treatment SubstationHypergolic Test Euilding No. 2Hypergo~jc Test Building No. 1Cryogenic Test Euifding No. 1cryogenic Test Building No. 2O~nance ~b~r~~~~P~te~bnjc ~nstallatjon~rd~a~c~ ~~~~~ Facility


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SERVICE AREA

ASSfMBLV & TEST AREA

l!!cfla 00

LAEORAlORV I CHECKOUT MA

ADMlNlSlRATlVE & ENGINHAING AREA

Figure 2-2, Manned Spacecraft Operations Building Layout


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The system provides the remote stimuli control, monitoring, data conversion, processindisplay, response measurement, and the communications necessary to ccnduct checkouof spacecraft systems. Larye quantities of test data can be processed and displayed engineering units in real time and simultaneously recorded for later analysis.The ACE-S/C Ground Stations located in the MS0 Building operate in conjunction witthe spacecraft carry-on checkout equipment, spacecraft-vicinity equipment, flight instrmentation, and onboard checkout equipment via the Data Link System (Figure 2-3).2.2.3.4 Assembly and Test Area. The assembly and test area is 86 feet wide and650 feet long. One-third of this area has a crane hook height of 85 feet, and the re-maining two-thirds has a hook height of 50 feet. Each of the three bridge cranes inthe assembly and test areas has a capacity of 25 tons. Space is provided for two alti-tude chambers and two integrated systems test stands. Rising panel doors allow themated spacecraft elements Lunar Module (LM), Command Module KM!, Service Modu(SM) to be moved vertically from the integrated test area to the Vehicle AssemblyBuilding WAB).2.2.3.4.1 Integrated Test Stand. The Integrated Test Stand (Figure 2-4) consistsof a stee! structure with fixed and movable platforms, that provide access to the exterioof the spacecraft. The stand is located between columns 1 and 4, adjacent to the norwall of the Assembly and Test Area of the MS0 Building.The stand is approximately 39 feet wide by 76 feet long. The column foundations arelocated on elevation minus 12 feet. A fixed platform is located at elevation zero,which is the main floor of the area.The stand is divided into t;vo areas. Each area has three movable platforms, positionedby a hoist system. Platform No. 1 may be located between elevations +lO feet and+20 feet; platform No. 2 may be located between elevations +25 feet and +35 feet;platform No. 3 may be located between elevation +40 feet and +45 feet.fn the east area, the fixed platform has a clear circular opening of 21 feet. Hingedsections lift to give a maximum opening of 23 feet 8 inches. Platforms No. 1, 2 and3 each have an opening of 15 feet.fn the west area, the fixed platform has a clear opening of 15 feet. Hinged sectionslift to give a maximum opening of 17 feet 8 inches. Platforms No. 1, 2 and 3 eachhave an opening of l-5 feet.2.2.3.4.2 Apollo Altitude Simulation System. The two altitude chambers (Figure2-51 in the MS0 building are designed to support various pressure and simulated alti-tude tests of spacecraft systems. Each chamber is capable of achieving an altitude of250,OOO feet within one hour, and eetuming to sea-level in 16 to 30 minutes undernormal operation, or 2 minutes under emergency conditions.


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P-:IIIII!

LAUNCH PAD A

LitlUlO TEST FACILITIESENVIRONK~NTAL SYSTEMSTFST BUILOINGHYPERliOLlE TEST BUILUINGCRYO6ENIC TEST BUILOINfi

.e.....* VEHICLEMOYEUENTc--) DATA LINKS

LEGEN


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Electrical and fluid connections are provided through the chamber wall to furnish powgases for cabin sea level leak checks, leak detection equipment, and EnvironmentalControl System (EC.9 support. Additional connections for radio frequency (RF) closeloop checkout, ACE-GSE, television and intercom coverage, chamber evacuation eqment, and spacecraft system GSE are provided.

The chambers are cylindrically shaped with an overall length of approximately 50 feeand an inside diameter of approximately 34 feet.E?ch chamber is supported by four i-beam columns. The columns rest on elevationminus 12 feet of the A&T area of the MS0 Building. The top head is removable toallow the spacecraft to be positioned in the chamber.2.2.3.4.3 Electrical Power and Distribution. Electric power distribution to theintegrated Test Stand and the Aititude Chambers is an integral part of the MS0 5uiltiinpower distribution system. In this description, only those parts of the system involvedin distribution to the Integrated Test Stand and the Altitude Chambers will be describeSixty-cycle industrial power at 13.2 kv is supplied to substations in and around theMSCI Building. Power to the Integrated Test Stands and the Altitudeq Chambers issupplied by substations 5, E, J & Z.Substations D and E supply power at 480 v/277 v and substations J and Z supplypower at 205 v/120 v. A switching provision in each of these substations allowspower to be supplied from one of two feeders. This provides an alternate source ofpower should one feeder fail. Emergency power could be made available by connectingportable generator units to the connections provided for this in the substations.2.2.3.4.4 Communications. communication is provided by the RF operationallnte~ommun~cation System (OIS). This system provides voice ~om~uni~at~on betweenstations in the MS0 Building and can be interfaced with other audio systems in theCape and KSC areas.The RF OIS system is a radio frequency, single sideband, multiplex system providing112 separate communI:ation channels. ~peratiog channels are dial selected at eachstation. The low band covers channels 111 tbro~gh T.88, and the high band coverschannels 211 through 268. Each statioti has the cap~jl~ty of operating on anychannel and there 5 no limit to the number of stations that can operate at one time ona single channet. One charmet is provided to give selected stations access to theOpe:ational Paging System @PSI. This channel will be automatically selected whenthe aage butt< r is depressed.Operatct stations in the altitude chamber area are ~~~a~-proof units. Stations in thecontrol rooms are of the ra~k~ou~ted type.


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2.2.3.4.5 Television, An Operational Television (OTW System is provided forspacecraft checkout operations and interconnects with the &em in the Fluid TestArea and the documentation and briefing system in the MS0 Building.Checkout operaticns in the altitude chambers wili have OTV Joverage. Monitors areprovided in the Spacecraft Cf.pckout Rooms and the Altitude Chamber Control Room.The cameras may be remotely controlied from the Altitude Chamber Control Room.Control of the system originates in the ACE-S/C TV Control Room which contains thenecessary equipment for control, testing, distribution, and processing of the TV signals.The S/C Control Rooms are the control centers for the S/C checkout. The OTV systemprovides these rooms with television coverage of the checkout operations. The two S/CControl Rooms each have nine 21-inch monitors and one dual &inch monitor. TheAltitude Chamber cc. trof room contains six 21-inch monitors and two camera controlunits with pan/tilt/zoom conti,ols.Cameras assigned to the Altitude Chambers are hazard proof and capable of remote con-trol. There are two -ameras in each chamber, one for general surveillance and one inthe air lock for viewing personnel therein.2.2.3.5 Building Services Area. Air-conditioning, vacuum pump, spacecraft-,..,,.,mechanical sho[J, and other building service rooms are located in the south wing of thebuilding.2.2.4 TIMING SYSTEM. A sub-central timing station is located in the MS0 Building.There is a propagation time delay between the central timing station, located in the Cen-tral Instrumentation Facility (CtF) Building, and the sub-central timing station. Thisdelay is compensated for by the sub-central timing station. Timing signal distributionis Facilitated by cable between major KSC locations. This cable minimizes interferencesand improves mechanical integrity.Timing terminal units are supplied to the rack-mounted equipment areas of the usingactivity from \bdhich the individual instrumentation medi; are energized. modular designis used to facilitate expected expansion.For more detail explanation of the timing system see Volume ill of this document.2.? SUPPLY, SHIPPINGS AND RECEIVING BUILDING (M7-505)2.3.1 FUNCTION. The Supply, Shipping, and Receiving I? wilding (Figure 2-6)provides space for maintenance and modification shops, and space for storages and con-trol of GSE and parts required to assemble and prepare a spacecraft.


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6u!pl!ng 6u!n!am~ pw Ku!ddy!S f;lddnS 9-z a.mt!j


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2.3.2 LOCATION. This building is located in the KSC fndustrial Area on 2nd Streetbetween D and E Avenues.2.3.3 DESCRIPTION. This building contains a shipping, receiving, processino, ancontrolled storage area. Ready storage space for items requiring controlled environmentto prevent deterioration are available. Also, storage area for ground support equipmentand spare parts are located within the building. Shop facilities are provided withinthe building for ground service equipment, cleaniI:g, maintenance, and plasticshops.2.4 PARACHUTE BUfLDING (M7-657)2.4.1 FUNCTION. The Parachute Building (Figure 2-7) provides checkout spacefor the inspection and packaging of parachutes.2.4.2 LOCATION. The Parachute Building is located in the KSC Industrial Area atthe intersection of 3rd Street and E Avenue.2.4.3 DESCRIPTION. This building has a low bay and a central office area. Thelow bay is for inspecting and packing parachutes. The central office area contains spacefor bonded storage, for a machine room, and four supporting offices.2.5 RADAR BORESITE RANGE (M7-863, M7-867)2.5.1 FUNCTION. The Radar Boresite Range (Figure 2-8) provides equipment andstructures to conduct final preflight qualification of spacecraft radar systems.2.5.2 LOCATION. The Radar Boresite Range is located in the KSG Industrial Areaon Fifth Street.2.5.3 DESCRIPTION. The range is located in a controlled, RF-quiet area suitablefor qualification of onboard radar transmitters, receivers, and antennas. tt consists oftwo towers 1,000 feet apart. A two-story control tower iapproximately 20 feet highand 20 feet square), supports the position fixtures, and spacecraft mock-up and radarmodule. The radar target fixture is supported on a 50-foot high Lower.

2.6.1 FUi~.~~iDN. The ordnance Laboratory (Figure 2-5) is used for dis-assembling,checking, testing, and storing small pyrotechnic devices.2.6.2 L~GA~~DN. This laboratory is located adjacent to and west of the Pyrote~bni~installation Eui~$ing in the KSG ~~d~str~al Area on Tenth Street. This facility is isolatedfor safety reasons.


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2.6.3 DESCRIPTION. The Ordnance Laboratory contains two test ceils, a controlroom, laboratory, washroom, and machine shop. The test cells are approximately 400square feet each. The building is air-conditioned and has fans to remove conbustiorlgases from the test cells. The control room is constructed with blast-resistant walls.2.7 ORDNANCE STORAGE FACfLlTY fMi-147212.7.1 FUNCTION. The Ordnance Storage Facility provides a machine shop andstorage area for pyrotechnic devices and for launch escape towers.2.7.2 LOCATION. The Ordnance Storage Building (Figure 2-10) is located adja-cent to and east of the Pyrotechnic Installation Building in the KSG Industrial Area onTenth Street.2.7.3 DESCRIPTION. This buiiding contains approximately 3,780 square feet ofmachine shop, storage, and utility space. About 3,240 square feet of the total spaceis for ordnance storage. The building is environmentally controlled for storage of pyro-technic devices and solid fuel motors used on the spacecraft. A crane is provided forhandling ordnance items and the aligned launch escape towers. Crane hook height isabout 18 feet.2.8 PYROTECHNIC INSTAL~TI~N BUILDING &l7-146912.8.1 FUNCTION. The Pyrotechnic Installation Building (Figure 2-11) is used forweighing, balancing, and determining the center of gravity of the spacecraft and foroptical alignment of certain pyrotechnics.2.8.2 LOCATION. The Pyrotechnic Installation Building is located in the KSCIndustrial Area on Tenth Street.2.8.3 DESCRIPTION. This building contains approximately 18,000 square feet.An area measuring 80 feet by 150 feet by 110 feet and two service areas of 29 feetby 150 feet will be used for optical alignment of certain critical components such asthe spacecraft escape towers, and retrorockets. The building contains a 90-foot highmotorized door at the south side of the high bay area which permits entry of a fullymated spacecraft, (LM, Apollo, etc.1 and has an overhead crane with a hook height of95 feet. The building is air~ond~tioned.2.9 FLIGHT CRE-W SUPPDRT EUILDIN~S ~~7-4~9~2.9.1 FUNeT~~N. The Flight Crew Support Buildings [Figure 2-121 are for simu-lated lunar mission training of the astronauts and checkout of the other lunar missionsupport facifities.


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2.9.2 LOCATION. The Flight Crew Support Buildings are located on 2nd Streetand E Avenue in the KSC Industrial Area.2.9.3 DESCRIPTION. This facility is comprised of the Flight Crew Training Build-ing and the Equipment Support Building. The Flight Crew Training Building measures200 feet IcJrig by 152 feet 6 inches wide and is constructed of reinforced concreteframe with masonry exterior walls. This building is constructed with a single-storysection o! 12,900 square feet, accommodating office and operational support functions.The remainder of this structure is designated as low and high bay areas, 6,600 and11,OOrJ square feet, respectively. These latter areas are the operation areas and areequipped with a false floor. The false floor is constructed of modular 3-foot by 3-footremovable panels supported by a sub-structure of metal stringers and screw adjustablepedestals. The metal of this floor sub-structure is tied together by a continuous ground-ing conductor which is connected to building ground. The sub-floor area, approximatelytwc feet deep, is a plenum chamber used to supply cooling air to the electror.rc equip-ment. The equipment cooling system is equipped with alarm devices to indicate malfunc-tions and cut-of-operating tolerance. This alarm device allows for the manual shutdownand the securing of the electronic equipment until repairs to the cooling system can beaccomplished. The walls of these operation areas are covered from floor to ceiling withacoustical tile,The single-story portion of this building consists of the following areas: office area,tape file room, telephone intercom and data interface room, program preparations room,shop, locker room, and experimental training aids room. Computers, peripheral equip-ment, and consoles are located in the adjacent low bay area.Two lunar mission simulators and two part task trainers are located in the high bay area.The clear height in this area, false floor to ceiling, is 25 feet. The electrical powersystem for the electronic and instrumentation equipment consists of an uninterruptedpower source of 200 kw for operatron of the simulators and trainers with their associatedcomputers and peripheral equipment. A separate and distinct grounding system has beenincorporated into the building design for the electronic and instrumentation equipment.This ground system is isolated from the static/building ground system except for earthconductivity to prevent ground-loops which may indtice disturbing voltages into theelectronic equipment.The Equipment Support Building, measuring 40 feet by 45 feet, is located 50 feetsouth of the Flight Crew Support Buildings.2.10 ~NYIRONMENTA~ SYSTEMS TEST BUILDING NO. I (M7-96112-10.1 FUNCTION. The Environmental System Test Building No. 1 (Figure 2-13)isused to test the spacecraft environmental contra! system (life support).


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2.10.2 LOCATION. The Environmental Systems Test Building, an integral part ofthe Fluid Test, Area, is located in the KSC Industrial Area at the intersection of FifthStreet and G Avenue.2.10.3 DESCRIPTION. This facility contains two test ceils, a control room, equip-ment storage rooms, and storage for liquid oxygen iLOx) and gaseous oxygen. Cleanroom conditions are provided through most of the building by means of design featuressuch as smooth walls, ceiliny, and floors, and by providing special air filtering. Spaceis provided for testing cf the ECS of the command and service modules stacked verti-cally or placed side by side.2.11 HYPERGOLIC TEST BUILDINGS CM7-1210, M7-121212.11.1 FUNCTION. The Hypergolic Test Buildings (Figure 2-14) provide facilitiesfor checkout of the spacecraft hypergolic systems.2.11.2 LOCATION. The Hypergolic Test Buildings, an integral part of the FluidTest Area, are located in the KSC Industrial Area on Seventh Street between F Avenueand G Avenue.2.11.3 DESCRIPTION. The two buildings are irregular in shape and each contain7,100 square feet of floor area. Each has a two-story central structure and two testcells 40 feet square and 60 feet high. The test cells are located on opposite sides ofthe central structure.Each test cell has an overhead crane with a hook height of 45 feet. The test ceils havelarge capacity exhaust systems and a flcor system which collects and dilutes hypergolicspills. Chilled water storage tank, c!>illed water basins, washdown systems and con-taminated effluent tank to control and cant~,1.. inadvertent spilling of toxic and combus-tible propellants are provided. The central structures include contrcl rooms, equipmentrooms, and a rr:chine room.The buildings are air-conditioned and have special features to provide for safe handlingof the hazardous fuels and oxidizers. The control rooms are designed to protect opera-tors from possible explosions or toxic fumes during testing of the spacecraft hypergolicsystems.2.12 ~R~~~GEN~~ TEST BUILDINGS (M-1412. M-1410)2.12.1 FUNCTION. The Cryogenic Test Buildings [Figure 2-15) provide equipme~~tfor bench testing of spac.ecraft cryogenic fuel system components, and for the fuel ceilliquid hydrogen supply system of the Command Module.


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2.12.2 LOCATION. The two buildings, an integral part of the Fluid Test Area, arelocated between Ninth and Tenth Streets in the KSC Industrial Area. Cryogenic TestBuilding No. 3. (M7-1412) is on G Avenue and Cryogenic Test Building No. 2 is onF Avenue.2.12.3 DESCRIPTION. Each building consists of one test cell having an overheadcrane with a 45foot hook height , a laboratory, and a dressing room. The four wallsof the test cells have 40-foot high motorized doors, A deluge fire protection system isprovided in the test cell. The buildings are equipped with a gas detection and alarmsystem,2.13 FLIJID TEST SUPPORT BUILDING (M7-106112.13.1 FUNCTION. The Fluid Test Support Building (Figure 2-16) provides sup-port for all test operations conducted in tlie Spacecraft Operations (SC01 fluid test area.2.13.2 LOCATKIN. The Fluid Test Area Support Building is located in the KSCindustrial Area on Sixth Street.2.13.3 DESCRIPTION. Laboratory, shop, office space and storage areas are pro-vided for processing spacecraft components. Components enter the building via theproduction control area and are then cleaned, inspected, and stored.


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SECTION IIIFRDP~~SIDN TEST FACILITY

3.1 GENERAL DES~RlPTlDN

The Propulsion Test Facility (Figure 3-l) is located at Complex 16, IGBM Road,Cape Kennedy, and is used for static firing tests of the Apollo Service Module ServicPropulsion System. The following buildings and areas are a part of the PropulsionTest Facility:a. Control Building.b. Service Building.; : Transfer Room.iimbiiicai Tower,e. Oxidizer and Fuel Pads.f, Oxidizer and Fuel Disposal Pads.g. Helium Area.h. GN2 Areas.i. SCAPE Building.Utilities.t Air~~onditioning Shelter.

3.2 STRUCTURES3.2.1 C~NTRDL ~~ILD~N~, The Control Building (blockhouse) is a two-story circular reinforced concrete dome building. An earth overburden, protected by shotcrete,covers the entire dome. On the second level is the control room .(approximately 4,300square feeti, which houses and provides protection to operating personnel, emergencycontrols, monitoring equipment, and instrumentation during static firing tests. ,Peri-scopes are provided for viewing purposes. On the first level is office and equipmentspace For air-handling equipment, junction boxes, etc.An annex, attathed to this building, houses facilities, electrical power equipment,water chiller units I emergency diesel power, etc.A balk-thy cafbeway is provjded TV house the control and inst~men~t~on cabies be-tween the Control Euilding and Test Stand a There is no personnel access provided tothe ~u~t~~ Building from the ~~!e~ay.3.2.2 TEST STAND- The Test Stand consists of an Umbilical Tower, ServiceB~i~d~ng~ and Approa~b Ramp Facility.


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3.2.2.1 Umbilical Tower. The Umbilical Tower supports the cabling and pipingwhich connects to the Service Building and provides access to the dome of the ServiceBuilding.3.2.2.2 Service Building. The Service Building houses the Service Module andGSE interface connections between the Service Module and the facility during checkout,propellant loading, and static firing. The Service Building is a cylindrical.steel tankresting on the ramp. This building has a diameter of 30 feet and is 35 feet high. Aremovable roof is provided to allow installation and removal of the Service Module,which rests on a thrust stand. The thrust stand is a steel ring, 13 fe-t in diameterand 11 feet high, mounted on legs. There are two equipment accesses, consisting ofdouble doors, plus personnel openings, to provide entrance to the Service Building.An acoustic attenuation baffle of steel plate has been installed at the first work plat-form level (Figure 3-2) to suppress potentially destructive pressure waves which mayhe generated during static firing. Microphone pickups have been temporarily installedaround the inside of the service building. Noise level information is to be amplifiedand displayed on a readout panel in the control room for continuous monitoring duringstatic firing.Three work platforms are provided inside the Service Building (Figure 3-21. A peri-pheral platform is provided on the outside of the building to provide access to the dome.3.2.2.3 Approach Ramp Facility. This is a steel and concrete structure which sup-ports and provides access to the Service Building and Umbilical Tower. An integralpart of the ramp is the water-cooled flame deflector which is used to dissipate gasesand flame during a static firing. Also located in this structure are various rooms andareas which protect and house equipment, as follows:

a. 1st Level.1. Actuator Pit (14 14 square feet).2 . . Equipment and Shop Room (1086 square feet].3. Hydraulic Checkout Room (4440 square fe&I.4. Transfer Room (998 square feet),5. Toilet.

b. 2nd Level.I. Equipment, Inspection, and Shop Room Pi4091 square feet).2. Winch Room (689 square feet).

These areas are provided with ventilation and air~onditioning.


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3.2.3 SELF-CONTAINED ATMOSPHERlC PROTECTIVE ENSEMBLE (SCAPEIBUILDING. This building is used as a central location for SCAPE operations. Storaspace is provided for the SCAPE suits. The personnel will change from street clotheto the SCAPE suits in this building. Communication between the personnel in theCAPE suits, the test conductor, and the personnel in the SCAPE building will bemaintained at a! ! times during SCAPE operations.3.3 SUPPORT FACILITIES UTILITIES3.3.1 ELECTRICAL POWER AND DiSTRIBUTION. Electric power (Figures 3-3and 3-4) is supplied to the Propulsion Test Faci!ity by a 13.2-kv industrial feederand a 13.2-kv cape critical power feeder. The industrial feeder supplies substationsin the Contro! Building, Air-Conditioning Equipment Pad, and Approach Ramp BuildingThe critical feeder supplies a substation in the Approach Ramp Building. Emergencyback-up industrial power is prosided by a 350-kw diesel generator to the ControlBuilding, Approach Ramp Buitdlng, Fuel Area, Oxidizer Area, and Vapor DisposalAreas (fuel and oxidirerl.~ Automatic transfer switches provide automatic connectionof certain panels to the emergency generator In the event of loss of normal industrialpower. Critical power is availahie at the Controi Building and the Approach RampBuilding. Back-up criticai power can be supplied to certain panels by motor generatorsets which operate on industrial power. DC power1 at 28 v, is available in the ContrBuilding and the Approach Ramp Building from rectifiers which are supplied industrialpower. A remote controlled switching arrangement provides dual supply backup capa-bility to certain DC panels. Figure 3-3 is a perspective drawing showing locations opower equipment and GSE receptacles. Figure 3-4 is a one line diagram of the elec-tric power distribution system at the Propulsion Test Facility.3.3.2 WATER SYSTEM. The water system (Figures 3-5 and 3-61 consists oftwo separate supplies; domestic water and process water. The Domestic Water Systemsupplies fire hydrants, safety showers, sanitary water, propellant areas, servicebuilding deluge, engine deluge, and deck spray. The Process Water System suppliesthe flame bucket, pad washdown and deck deluge. The water is supplied from the PanAmerican Airways (PAA) Pump House at the pressures and flows required to supportthe operations.The fire control systems are activated from the Control Building water panel by openingsystem valving located under the service building area of the test stand. Five fire(or heat) sensors are located in the Fuel Area and are connected to the control systemin order to activate the Fuel Area firex in case of fire. A heat sensor, located in theupper portion of the Service Building and connected to a tight and buzzer on the watercontrol panel, will indicate a fire in the Service Building. The Service Building de-luge and engine deluge are activated from the water system panel located in the ControBuilding. The flame bucket cooling water is controlled from the Control Building wate


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panel. The water panel utifizes 28 vdc to indicate valve positions and 120 vat toactivate solenoids which control water flow from the process and domestic water lines.The water system is shown on the Corps of Engineers D. 0. Fiies No. 201-26671for the original instaliation, and modification on Corps of Engineers drawings D. 0.Fiie No. 201-278 and NASA drawings No. 65K-311.3,3.3 AIR-CONDlTiONING. The Propulsion Test Facility has three air-conditionedareas. They are the Control Suilding , the Service Building, and the Transfer Room.The Control Buiiding air-conditioning system consists of a cooling tower, two chilledwater units located in the annex, and three air-hand!ing units located on the ControlBuilding first floor, Conditioned air is ducted from the air-handling units to the firstand second level of the Control Building for heating or cooling.Service Building air-conditioning (Figure 3-7) is supplied by an Elliott EngineeringCorporation portable unit (part no. PS609900037D-11 located at the air-conditionerpad. The conditioned air is ducted thru a lo-inch diameter pipe to the top of theService Building for heating or cooling. The unit is locally controlled with no remotecontrol provision.The Transfer Room air-conditioning system consist of a C. G. Hokanson Corp, Inc.portable chilled water unit and four air-handling units.3.4 COMI~UN~~AT~ONSThe communications system at the Propulsion Test Facility (Figure 3-8) utilizes threebasic pieces of equipment. In nonhazardous areas, a weatherproof MOPS unit is used.In any hazardous area such as the Service Building or propellant areas, an explosion-proof MITOC is used.There are a total of 19 available channels whose utilization is determined by the parti-cular test being performed. Five channels will be reserved for communications betweenthe Propulsion Test racility and MS0 Building.3.5 TELEVISlONThe television system (Figure 3-9) at the Propulsion Test Facility consists of threeexplosion-proof cameras mounted in the Service Builidng and a Fastex Film Cameramounted on the ramp leading to the Service Building. The receiving system, locatedin the Control Building, consists of three 8-inch control monitors mounted in a singlerack and four 21-inch receivers for viewing by test personnel. Each 21-inch receivermay monitor any of the three cameras.


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Figure 3-3. Propulsion Test Facility (Complex 161, Electrical Power Facilities


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Figure 3-8. Propulsion Test Facility (Complex 161, TV andCommunications System (Location Drawing)


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Figure 3-9. Prqpulsion Test Facility (Complex 161, Operational Intercommunication,TV Camera, a&TV Timing Systems (Block Diagrams), , , , , , , , , , , , , ~ , , , , , , , , : , , , . , , , , , , , , , , , , , , , , , I I , , , , ,


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The camera control system consists of the necessary amplifiers to con oan, tilt,and zoom for each of the three cameras. These controls and amplifiers ai. located inthe rack with the 8-inch receivers. See Figures 3-8 and 3-9 for equipment locationand system block diagram.3.6 PROPELLANT FACILITIESThe Oxidizer Area of the Propulsion Test Facility is located in the southeast section othe complex and the Fuel Area is located in the northeast section (Figure 3-11. Theseareas are in a remote portion of the complex to avoid possible damage to adjacent build-ings in the event of a catastrophic malfunction within either area.The prime objective of the propellant area is to provide an interface between the facilityand Mobile Propellant GSE, and to provide for a storage area and base of operationduring propellant loading exercises. Beth the fuel and oxidizer areas are connected tothe Service Building via propellant and propellant vapor lines. These vapor and pro-pellant lines allow a vapor/propellant exchange during loading or off-loading to provideclosed loop propellant transfer. Mechanical and electrical interfaces [stub-ups) areincluded to connect mobile equipment to the facility.Adjacent to the propellant areas are the vapor disposal pads. These pad areas areconnected to the propellant areas via propellant vapor lines. Propellant vapors arevented from the Mobile Propeiiant Servicing Units through the vapor lines to the ToxicVapor Disposal Units. The Toxic Vapor Disposal Units mix the propellant vapors withcopious amounts of air from a series of blowers, diluting the vapor which is then re-leased to tne atmosphere. Necessary mechanical and electrical interfaces (stub-ups)are provided to connect the Mobile Vapor Disposal Unit to the facilityy.3.7 PROPELLANT TRANSFER SYSTEMPropellant support for the Service Module at the Propulsion Test Facility may be divideinto two areas: (a) fuel loading system, containing a 50150 blend of UnsymmetricalDimethyl Hydrazine (UDMH) and hydrazine, and (b) oxidizer loading system, containingnitrogen tetroxide. Each system contains necessary mnbile units, plumbing, controls,etc _j to provide its respective propellant fluid to the service module.The fuel loading system and the mobile units needed to support Service Propulsion Sys-tem (SPI requirements are located northeast of the Service Building in the fuel padarea (Figure 3-11. These units include the Fuel Ready Storage Unit, Sl4-058, theFuel Transfer and Conditioning &it, S14-008, and the Fluid Distribution System Control Unit, C14-489. The necessary facility interfacesfor fuel replenishing and powerrequirements are a!so provided.


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Service Building fuel equipment includes the fuel valve box, S14-035, the fuel bletank, S14-124, and associated plumbing and controls which interface with the servmodule. The fuel transfer and conditioning unit supplies fuel to the valve box for distribution to the SPS fuel tanks via cross country supply lines in one of three modes ooperation:

Propellant conditioning.t: Line pre-chill.6. Propellant loading.Propellant conditioning is an operation performed between the ready storage unit andthe transfer and conditioning unit to stabilize the fuel at the desired operating temperature prior to delivery to the Service Building. The two units are set up for this modeand fuel is transferred from the ready storage unit to the transfer and conditioning unitand back to the ready storage unit. This cyclic operation is continued until the desireoperating temperature is obtained. When this mode of operation has been completed,the line pre-chill mode of operation is selected.Line pre-chill is an operation performed with the ready storage unit used as a supplyvehicle and the transfer and conditioning unit used as the transfer vehicle to the fuelbox in the Service Building. Fuel is circulated from the fuel pad to the valve box andback to the fuel pad through interconnecting propellant lines until the desired operatingtemperature is reached. The fluid distribution system control unit provides the commasignals to the valve box for the pre-chili configuration.Propellant loading is an operation requiring all the units for transfer of conditioned prpellant to the SPS propellant tanks. The fuel fluid distribution system control unitcommands the fuel valve box from a pre-chill to a loading configuration. In addition,the fuel loading system contains a fuel toxic vapor disposal area to which toxic fuelvapors are routed from the fuel transfer system. Located in the disposal area is thefuel toxic vapor disposal unit, S14-060, with interconnecting toxic vapor lines tothe fuel pad. During the fuel loading mode of operation, fuel vapors are routed to hefuel toxic vapor disposal unit to be mixed with large amounts of air and blown verticallyinto the atmosphere for dispersion.The propellant oxidizer loading system is located southeast of the Service Building inan area designated as the oxidizer pad (Figure 3-l).Located at the oxidizer pad are the mobile units needed to support SPS requirements.These units inciude the oxidizer ready storage unit, S14-059, the oxidizer transferand conditioning unit, S14-002, and the fluid distribution system control unit,G14-488. The necessary faciiity interfaces for oxidizer replenishing and power re-quirements are also provided.


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Service Suilding oxidizer equipment includes the oxidizer valve box, 514-035, theoxidizer bleed tank, S14-122, and associated plumbing and controls which interfacewith the service module. The oxidizer transfer and conditioning unit supplies oxidizerto the valve box for.distribution to the SPS oxidizer tanks via cross-country supplylines in one of three modes of operation:Propellant conditioning.E: Line pre-chill.

C. Propellant loading.These modes of operation are identical to those of the fuel loading system except forthe particular parameters desired for the oxidizer system.The oxidizer loading system is also interc,onnected with a toxic vapor disposal area inwhich is located the oxidizer toxic vapor disposal unit, Sl.4041, and connectinglines, It functions in the same manner as the fuel toxic vapor disposal unit.3.8 HELIUM TRANSFER SYSTEMThe helium system consists of the necessary mobile units, associated hardware, andcontrols to accomplish leak and functional tests of the Service Module Service Propul-sion System. The helium area is located on the approach ramp to the Service Building,and the following units are included there: helium transfer unit, S14-009; heliumbooster unit, S14-022; helium ready storage unit, S14-062; and a helium tube banktrailer. Low pressure helium from the tube bank trailer rs supplied to the helium boosteunit, which supplies high pressure helium to the ready storage unit and transfer unit.The ready storage unit provides 6000 psi to the propulsion system checkout unit,C14-075, and provides a ready source of high pressure helium to the transfer unit.The transfer unit conditions and transfers 4000 psi helium to the Service Buildinghelium valve box, where it is available for distribution to the propulsion system duringcheckout.Command signals from the helium fluid distribution system control unit, C14-449,which is located on the second level of the Control Building, control the configurationof the helium valve box solenoid valves as dictated by the requirements of the test inprogress. The control unit also monitors response indications from the helium valvebox to indicate valve positions and fluid parameters in addition to the SPS measureme&and helium pad measurements.3.9 HIGH PRESSURE GASEOUS NITROGEN SYSTEMThe nitrogen system consists of facility supplied gaseous nitrogen tGN21 which is regu-lated, through a nitrogen a nitrogen controller, to various pressures for control and


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purge functions. High pressure GN2 from an off-site pumping station [220&5500 psis supplied to the nitrogen control unit located in the actuator room of the seTvice struc-ture. The nitrogen control unit regulates the supply nitrogen by hand-loaded regulatorsmounted on a face panel to provide regulated nitrogen for distribution throughout the complex. These distribution areas include the fuel pad, oxidizer pad, toxic vapor disposalpads, helium pad, and the Service Building.The fuel pad, oxidizer pad, and toxic vapor disposal pads receive 1500 psi GN2 as acontrol media for valve operation in their associated mobile units, and as a pneumaticsource at their facility interface stub-ups. The fuel pad and oxidizer pad are also pro-vided with 150 psi GN2 to regulator assemblies which provide a 50 psi purge to theelectrical control units. This purge elgminates potential hazards in the propellent areaThe helium pad is supplied with 750 psi GiJ2 to the helium transfer unit and heliumbooster unit for control valve operation.The Service Building is supplied with 1600 psi GN2 for control valve operq.tion at theftuid distribution system valve boxes, and propulsion system fluid checkout unit. Also,a regulator assembly provides a 50-psi GN2 purge to the associated J boxes andcontrol units as part of the safety requirements. Leak testing of senrice module pro-pulsion components will be accomplished with the freon pressurization unit, C14-486,which mixes freon with dry GN2 at the correct temperature, pressure, and flow rates.The l&30-psi GN2 output from the nitrogen controller supplies the pneumatic mediumfor this unit.A liquid nitrogln (LN2) trailer is provided at the helium pad during helium transFeroperations. The trailer supplies LN2 to the helium transFer unit, S14-009, to chillthe helium to desired operating temperatures. These temperatures are sampled atselected points of the system and are monitored on the heiium control unit in the Con-trol Building.The service propulsion system GN2 storage tanks will be serviced by a K-bottle supply,These tanks provide storage for GNz which is used for ensine ball valve operatinnduring functional testing and static firing operations =3.10 ACE-S/C ~~N~R~L AND MONITOR TR~N~~~i$~l~N LINKSThe control system at Complex 16 (Figure 3-101 consists OF he ~~E-~~~ eo~~andlink, the C14-402-101 iSPS Checkout and Firing Unit), and manually ~ont~~~edGSE.The ACE-S/C station performs two control functions: SPS valve commands and ~b~stvector control c~mm~ds.


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These commands (Figure 3-11) originate in the ACE-S/C station and are transmittedin digital form via the A2A hardline system, to the Service Equipment Digital TestCommand System K14-241-501). In this unit the commands are decoded and routedto the proper GSE to initiate the required action.The C14-602-101 has the capability of initiating the following three commands atComplex 16:

a. Vibration safety cutoff commands.b. Emergency shutdown commands.c. Emergency shutdown for the gimbal clutches.The vibration safety cutoff command is an automatic function of the C14-602. Whenthe vibration level of the SM-SPS becomes intense enough to be dangerous, the outputnf thn xrihrstinn +rancdllcer reaches a !evel high enough to actuate circuitry in the. .**.. f.w....*v** - -,.


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Figure S-11. Propulsion Test Facility lComplex 161, Typical Command Response Flow Diagram


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Figure 3-12. Propulsion Test Facility (Compl,ex 161, instrumentation BIock Diagram


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FM signals are sent to the Control Building for recording on magnetic tape. Certain othese signals will also be sent to the Control Building in analog form to be presented Sanborn strip chart recorders as redline functions. The analog signals which are to bsent to the ACE-S/[: station are routed to C14-484 (Signal Conditioning Unit) and tC-14-24D [Servicing Equipment S/C Adapter) where they are converted to digital forarrd placed h&Q a PCM format. Frotn the C14-240 (Servicing Equipment, ACE-S/CAdapts) they are routed to the C14-232 (interleaver) where they are pla,ced into a neformat. The interleaver feeds directly into the A2A system which is the connection tothe ACE-S/C Station at the MS0 Building. This flow is shown in Figure 3-11.By adding either additional C14-240s or carry-on PCM systems, the PCM data capabilities can be increased. The FM system can be increased to 96 data channels by thaddition of summing amplifiers and VCOs. The C14-602 also has additional datacapabilities if required.3.12 TIMING AND COUNTDOWNThe Propulsion Test Facility utilizes range timing in the standard IRIG format. Thethree timing signals distributed from the RCA timing rack located on the first floor ofthe Control Building are one pulse per second (PPSI, 100 PPS coded, and 10 PPSuncoded.The one PPS signal is distributed to all countdown clocks in the Control Building andthe transfer room and to the strip chart recorders located in the Control Building. The100 PPS coded time is distributed to the magnetic tape and strip chart recorders loca-ted on the second floor of the Control Building. The 10 PPS signal is distributed tothe TV Control Systems and the emergency station on the second floor of the ControlBuilding. The coded timing format will be changed when new IRIG standards go intoeffect.3.13 AREA WARNING SYSTEMThe Warning System (Figure 3-U) consists of lights and horns. The.lights (red,green and amber) are located on the Umbilical Tower and on the top of the ControlBuilding, These lights are controlled by switches on the Test Conductor (TCI and PaSafety Officer (PSO) consoles on the second floor of the Control Building. Switchesare also located in the Fuel and Oxidizer Areas and on the ramp for control of the fightT,he area warning horns are located on the Umbilical Tower, in the Control Building,and in the Service Building. Three warning horns are controlled from the TC or PSOconsoles on the second floor of the Control Building or from switches located in #heFuel and Oxidizer Areas and on the ramp.


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Documents

Apollo Saturn V Facility Description Vol. 4