project apollo end item specification boilerplate number 16

8/6/2019 Project Apollo End Item Specification Boilerplate Number 16

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* CLASSIFICATlON CRANGE

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Copy No. S I D 6 3-6 91PROJECT APOLLO END ITEM

SPECIFICATION BOILERPLATE NUMBER 16(U)12 December 1963 NAS9- 150

Paragraph 4. , Exhibit I

. , . 1 , - , I ~ ~ r ii YhirULL - E 1.national defense ok he .n of its contents in anylaw.

This document contaiUnited States within ge Laws Trtle l8M.S .C. -Section 793 and 794manner t o an unautho

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TABLE O F CONTENTS

P a g e1.1 . 11 .1 .11 . 1 . 21. 1. 32.2. 12 . 1 . 12 .1 .22. 23.3 .13 .1 .13 . 1 . 23 . 1 . 2 . 13 . 1 . 33 . 1 . 3 . 13. 1. 3 .23. 1. 3 .33 . 1 . 43. 1. 4.13 . 1 . 53. 1. 63 .1 .73 . 1 . 83 .1 .93.1 .103 .23.2. 13.2.1.13.2. 1.23. 2. 1 . 33. 2. 1.4

SCOPEScopeSpecification OrganizationMissionObj ect ves

APPLICABLE DOCUMENTSApplicabilityGove rnmen t Do cum en sNon -G ov e rn m en t Doc um ent sPrecedence

R EQU IR EMEN TSG en era1WeightM ater ialsF a b r i cationDesign Cr i te r iaE le ct r omagne ic In e r f er enc eEnvironmentCheckout Pr ovi s ionsIn te r c han g ea b l ityInte r c hang eab l it y of Ele c tr on ic Equi pm entReplaceabili tyF in i s hIdentification and MarkingIdentif ication and Traceabili tyLubricationReliabil i ty

CONFIGURATIONLAUNCH ESCAP E SYSTEM (L ES )

Nose ConePi tch Control MotorTower Jett ison MotorLaunch Esca pe Motor

334444444445

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TABLE O F CONTENTS (Continued)P a g e

3. 2. 1.53. 2. 1 .63. 2. 1.73.2. 1.83.2.1.8.13. 2. 1.8.23. 2. 1.8.33. 2. 1.8.43. 2. 1.93.2.1.103.2.1.113.2. 23.2.2.13.2. 2.1.13.2.2.1.23. 2. 2.1.33. 2. 2.1.43. 2. 2.1.53. 2. 2.1.5. 1J. 6. L . 1 . 63. 2. 2.1.6. 13.2. 2.1.73. 2. 2. 1.83.2. 2.1.93.2.2.1.103.2.2.1.113. 2. 2.1.123. 2. 2.1. 13

- - -

3.2.33.2.3.13. 2. 3.23.2.3.33. 2. 3.43.2.3.5

St ruc t u ra l Sk i r tLaunch Escap e TowerLES Tower Separat ion Sequen cerElec t r i ca l Sys temMission SequencerHotwire Ini t ia torsHotwire Fi r ing UnitsPyro technic Bat t e r i e sUmbi l ical SystemPyro technic Sys temLES Tower Separat ion Syste m

COMMAND MODULE (CM)Command Module St ruc tureCabin HousingFo rw ard Bulkhead and Eg re ss TubeF o r w a r d C r e w C o m p a r t m en tAft C rew C om par t m en tApex For wa rd Comp ar tment Hea t Sh ie ld CoverCM InsulationAccess HatchAccess DoorsMission SequencerE l ec t r i ca l Pow er Sys t em (E PS )R and D Communicat ions Equi pmentR and D Inst rumentation EquipmentEnvi ronmenta l Cont ro l Sys ternCM-SM Attach Sy stemCM-SM Separat ion

SERVICE MODULE (SM )SM Reaction Control SystemSM I n s e r tAda pt e rSM Purgin gSM Protect ive Bulkhead

i ii

77777888888

999

1010101010101111111111111112121212121212-

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TABLE OF CONTENTS (Continued)

3.2.43. 33 .3 .13.3. 24.4. 14.24.2.14.34.3.14.45.5. 16.6. 1

I

1.

AAB

LAUNCH VEHICLEPERFORMANCE

Tr a j e c t o r y Par am eter sFl ight Plan

QUAL ITY ASSURANCEGen era l Qual ity Assurance P rov i s ionsPr inc ipa l C on t r ac to r ' s Qua li ty AssuranceP r o g r a mReliabil i ty DataExaminationComponentsT e s t s

PREPARATION FOR DELIVERYPrese rva t io n , Packag ing , and Pack ing

NOTES

LIST O F TABLESEst imat ed Weights and Cent er of Grav i ty

LIST O F ILLUSTRATIONSConfigurat ion - Boi lerp la te Number 16

APPENDICESDrawingsDrawings (continued)F l igh t Hardwar e

P a g e12121212

1313131313131314141414

15

16

A - 1A -2B -1

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PROJECT APOLLOEND ITEM SPECIFICATIONBOILE RPLA TE NUMBER 16

1. SCOPE1. 1 Scope. -Apol lo sp ac ec ra ft consis t ing of a l aunch e scape s y s t em (L E S) , com m andmodule (CM), se r v ice module (SM), and adapter here inaf t e r re fe r r ed toas Boi le rp la t e Number 16.

This speci f icat ion defines the requ i rem ent s for a s imula ted-

1. 1. 1 Specificat ion Organizat ion. - This speci f icat ion is organized asfollows :

Basic sec t ionAppendix A - DrawingsAppendix B - Fl igh t Hardware

1. 1. 2 Miss ion . - Boi le rp la t e Number 16 is t he veh ic l e fo r the m i c r o -meteoro id exper iment.1. 1. 3 Object ives. -vehic le qual if ication and micr ome teoro id ex periment .ives w i l l be de te rm ined by MSFC.

Boi l e rp la t e Number 16 sha l l be u sed f o r t he l aunchOther t e s t ob jec t -

2. APP LIC ABL E DOCUMENTS2. 1 Applicability. -t he da te of con t ra c t fo rm a pa rt of this s pecif icat ion to the extent specifiedhere in .

Th e following docu men ts of the is su e in effec t on

2 .1 .1 Gov ernm ent Documents. -SPECIFICA TIONS

Mi l i t a rvMIL-E- 5400 Elect ronic Equipm ent, A ir c raft,

Ge ner al Spzci f icat ion f or

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MIL - 1-8 5 0 0

MIL-L-688 0

MIL-R-27542

STANDARDSMIL-STD-130

SPACE end INFORMATION S Y S T E M S DIVISIONO R T H A M E R I C A N A V I A T I O N , I N C .

Interchangeabil i ty and R eplaceabil i ty ofComponent Parts f o r A i r c r a f t a nd M i s s i l e s ,Specif icat ion fo rLubricat ing , Ai r c ra f t , G enera lSpecif icat ion fo rRe l iab il i ty P r og ra m Requ i r emen t s fo rSys terns, Subsys e ms , and Equipment ,Specif icat ion fo r

Identification Marking of U . S. Mil i taryPropPr ty

National Aero nautics and Space Adininis rat io n (NASA)NPC 200-2 Qual i ty Assu rance Provis ions for Space

Cont r ac to r s , da ted 20 Apr i l 19622. 1.2 Non Gov ernm ent Documents. -e SPECIFICATIONS

North Am er ic an Aviation , Inc . , Space and Informat ion Sys tem sDivision (NAA/S&ID)MA 0116-012 Prepara t ion fo r D e l ive ry and T ranspo r t ofApollo Boilerp lates , Specification f or

Elect romagnet ic In ter feren ce Contr o l forthe Apollo Spac e Syste m, Specif icat ion forMC 999-0002B

OTHER DOCUMENTSSID 62-109 Gene ra l Tes t P lan , Res ea rc h and Deve lop-

men t fo r P ro j ec t Apollo Spacecra f tSID 62-223 Apollo P ro g ra m PlanSID 63-313 Apollo Master Spacecraf t Specif icat ion

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3. 1. 1 Weight. - Weight, ce nte r of gra vity , and mo me nts offo r Boi l e rpla t e Number 16 a r e li s t ed in Table I.3. 1. 2 Mater i a l s . - Mate rials shal l be compat ible wi th desand load c r i t e r i a .

inert ia data

gn, weight,

3. 1 .2 .1 Fab ricat ion . - Struc tural design concepts of B oi lerplate Number16 emp hasiz e employm ent of proven manufacturing techn iques and methodto the gr ea tes t possible extent.oped "off-the-shelf" components fab rica ted by dependable ma nu fac tur ers .

Maximum use sh al l be made of devel-

3. 1. 3 Design Cr i te r ia . - Design c r i t e r i a sha l l be in accordance wi thrat ion al design p rinciple s as spec ified in Specificat ion SID 63 -313.3. 1. 3.1 Electro mag netic Interfe rence . - Elec tromagnet ic in t e r fe rencecontr ol sha l l be in acco rda nce with SID Specificat ion MC 999-0002.3. 1 .3 .2 Environment. - The envi ronmenta l des ign c r i t e r i a fo r B oi l e r -plate Number 16 sh all be as spec ified in Specification SID 63-313.3. 1 .3 .3 Checkout Prov isions. - Boi lerplate Number 16 sha l l bedesigned with provisions for s yste m and integrated syst em s checkoutand tes t capabi l i t ies .3. 1.4 Interchangeabi l i ty . - Interchangeabil i ty as defined for the ApolloP ro g ra m sh all be in acco rdan ce with Specificat ion MIL-1-8500 and shal lapply to a l l completely f inished ass em bl ie s , components , and partswhich shal l be ca pable of being read ily instal le d, r em oved , o r r epl acedwithout a l terat ion, misal ignment , o r damage to parts being instal led o rto adjoining parts. No fabricat ion operat ions, such a s cut ting, f i ling,dri l l ing, ream ing, hammering , bending, prying, o r forcing, shal l berequi r ed fo r ins a l la t ion .3. 1. 4. 1 Interchangeab il i ty of Electro nic Equipment. - Interchange-abil i ty of e lect ron ic equipment shal l be in acco rda nce with SpecificationMIL-E- 5400, whe re applicable. Interchangeab il i ty of electro nic equip-ment fo r the Apollo Pr og ra m sha l l requ i re tha t mechanica l and e l ec t r i -ca l in terchangeabil i ty shal l exis t between l ike as sem bl ie s , subassembl i esand replaceable parts be easi ly effected wi thout physical or e lect r icalmodification to an y pa rt of the equipment, including; cabling, wiring , andmounting and without res or t in g to selec t ion; however , adjus tment , t r im-ming, o r ca l ib ra t ion may be made.

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( a ) Nose cone(b) P i t ch cont ro l motor ( iner t )(c ) Tower je t ti son motor(d) Launch escape motor ( in er t )( e ) S t ruc t u ra l sk i r t( f ) LES t ower(g) LES ower separa t ion sequencer .

3 . 2 .1 .1for accommodat ing 1,500 pounds of lead bal las t and a pi tch con trolmo tor mounted no rma l to the X axis .

Nose Cone. - The LES nos e cone sh al l provide the capabi l ity

3. 2. 1. 2 Pi tch C ontrol Motor. -an in er t sol id propellant moto r and sha l l be mounted aft of t he nosecone.motor .

The pitch con t rol motor shal l beIt sh all simu late the weight and c.g . of an act ive pi tch contro l

3. 2. 1 .3 The tower je t ti son mo tor shall b e asolid propellant motor 55.6 inches in length and 2 6 inches in diameter .The motor shal l have two f ixed thru st nozzles canted 30 degre es f ro mthe mean moto r cen te r l ine. The resu l t a n t th rus t axis sha l l be loca ted2. 5 degre es p lus o r minus 30 minutes f ro m the mean motor cen te r l ineof the pitch plane.pounds, which includes the inters t age s t r uc tur e , sha l l develop 33, 000pounds of t h ru s t and sha l l f i r e fo r 1 . 2 seconds .be ignited by a pyrogen type ign iter which sh al l ut i l ize two hotw ireini t ia tors .

Tower J et t i son Motor . -

The jet t ison mo tor sha l l weigh approximately 534The rocke t moto r sha l l

3 .2 .1 .4 Launch Esca pe Motor. -iner t s ol id propel lant motor with an app roxim ate length of 183 inchesand 2 6 inches in diameter with a gr os s weight of approximately 4 ,826pounds. Approximately 3 ,20 0 pounds of sol id propellant fuel wi l l b esim ulat ed to ac qu ire the weight and c. g. of an act ive launch esc ap emot0 r .

The l aunch escape motor sha l l be an

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3. 2.1.5 Str uct ura l Skirt . -ut i l ized to mount the launch escape m otor to the tower .shall be cons t ruc ted of a forged r ing wi th longerons , welded to ash ea r sk in , tha t sha l l t r ans f e r un i form load f ro m the launch e scapemo tor t o four point s at the launch escap e tower legs .sk ir t sha l l be bol ted to the LES tower.

A s t r u c t u r a l s k i r t a s s e m b l y s h a l l b eThe s k i r t

T h e s t r u c t u r a l

3 .2 .1 .6 Launch Escape Tower. - The launch e scap e tower sha l l bea four- legged welded tubular a l loy, t runcate d rec tangula r c ro ss -sec t ioned pyramid, approximate ly 120 inches in length with a b a s e46 inches by 50 inches .s t ru c tu re be tween the CM and the launch escape moto r . A t the topof the tower , immedia tely be low the s t ru c tu ra l sk i r t s ep a ra t ion p lane ,an aerodyn amic f lap sha l l be ins ta l led no rm al to the minus Z axis.At the bot tom of the tower , qu ic k- re leas e mech anism s sh a l l be incorp-or a te d to a t tach the tower to the CM inne r s t ruc ture and to the forwa rdheat shie ld.

The tower sha l l fo rm the in te rmedia te

3. 2.1.7 LES Tow er S epara tion Sequencer . - The two LES towersepara t ion sequ encers s ha l l control , upon rece ipt of tower se para t io ns ignal , (1 ) launch esc ape tower se para t io n and ( 2 ) ignition of the LESje t t ison motor .redundant bus ses , A and B.

The sepa ra t ion s igna ls sh a l l be t r ansm i t ted through

3 . 2. 1.8 Elec t r ic a l Sys tem. -of the following m aj or components :

The LES e l e c t r i c a l s y s t e m s ha l l c ons is t

( a ) Miss ion sequence r ( loca ted in C M )(b) Hotwire ini t ia tors(c) Hotwire f ir ing units(d) A ssocia ted pyrotechnic ba t te r ie s , wir ing, and a t tachments .

3 . 2.1.8.1 Miss ion Sequencer . - The miss ion sequence r sha l l au to-ma t ica l ly cont ro l LES tower sepa ra t ion sequence r and CM-SM s e p a r a -tion.this da te .

Other funct ions of the miss io n seq uence r a r e undetermined a t

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3. 2. 1 . 8 . 2 Hotwire Ini t ia tors . -e lec t r i c a l high res i s t a n t wi res th readed into pyro technic c ar t r idg es which

The hotwire ini t iators contain twofi re the igni ter of the rock et motor .fo r in crea sed re l i ab il i ty .

The in i t i a to rs sha l l be redundant

3. 2. 1 . 8 . 3 Hotwire F,irin g Units. -pyrotechnic car t r id ges which shal l be detonated by cur re nt passingthrough the h igh re s i s t an t e l ec t r i ca l ho twi re in i t i a to rs .car t r id ges sha l l then f i re the rocket motor ign i te rs .

The hotwire f i r ing unit s shal l beThe pyrotechnic

3. 2. 1 .8 .4 Py ro t echn ic B a t t e ri e s . -LES sh all be housed in the CM.means by which cur re n t w i l l be ca r r i ed f rom t he ba t te r i e s t o thepyrotechnic f i r ing uni t s .

The pyrotechnic bat ter ies for theEle ct r ica l wir ing shal l provide the

3. 2. 1 . 9 Umbil ical System. -electrical wiring between the CM and LES.detached by fo rc e on the lany ard type discon nect when the LES jet t isonmotor causes CM-LES separa t ion .

The umbi l ical sy ste m shal l containThe umbi l ical sha l l be

3. 2. 1 . 1 0 Pyrotechnic System. -of t he following:

The pyrotechnic sys t em sha l l cons i s t

( a ) Pyro technic ba t t e r i es(b) Hotwire ini t ia tors(c ) Di sconnec t asse mbl i e s .

3 . 2 . 1 . 1 1 LES Tower Separat ion System. - The LES tower separat ionsy ste m sha l l cons is t of explosive bol t s , used for LES tower - CMattachment , and f lexible l inear shaped explosive charg es placed atthe four a t tachments that se cur e the tower to the CM. Redundanthotwire ini t ia tor s s ha l l be u sed to detonate the explosive bol t s andflexible l inear shaped explosive charges.be ac tua ted by 28 vol t dc s ignals which sha l l be re ceive d fr om theredundant LES tower sepa rat ion sequencer . To accomp l ish LES towerje t ti son , t he tower sep ara t ion sequencer w i l l simul taneous ly apply detona-t ion sign als to the explosive bolt ini t iators and the tower je t t ison mo torf i r in g un i ts . The LES a s s e m b l y w i l l be r e l eas ed and prope ll ed c l ea r ofthe bo i l e rp la t e t ra j ec to ry .

The hotwire ini t ia tors s hal l

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3 . 2.2.1.2 Fo rw ard Bulkhead and Eg res s Tube . -head s t ru c tu re sha l l cons i s t of a double skin with r ive ted s t i f fene rs .The c loseout skin sha l l be a t tached to s t i f fen ers by bl ind fas ten ers .The egr ess tube sh a l l consis t of a welded she et tube of alum inumwelded to the for wa rd bulkhead.top of the eg re ss tube.

The forw ard bulk-

A cov er plate sh all be bolted to the

3. 2.2 .1 .3 Fo rwa rd Crew Compar tment . - The f o r w a rd c r e w c o m -par tm ent sha l l con sis t of mult i -s t i f feners welded to the outer skin.The s t i f feners sha l l consis t of four m ain longerons a t tached to thelaunch esca pe tower f i tt ings in ' the forward bulkhead and te rminate inthe mid -r ing spl ice joint at the aft end of the fo rw ar d sectio n of thec rew compar tment .load t ran sfe r f ro m the forward bulkhead to the mid-r ing .ing s t i f fene rs sha l l a s s i s t the skin in re s i s t ing a i r loads .

Seve ra l secondary longerons sha l l be ut i l ized forThe rema in -

3 .2 .2 .1 .4 Aft Crew Compartment . -compar tmen t sha l l cons i s t of a s idewall with s t i f f ene rs , corresponding

The aft section of the cr ewto those of the forw ard sec t ion of the crew c omp artmen t , f ro m themating aft sec t ion of the crew co mpa rtmen t mid- r ing to the machinedr ing forging a t the junction of the sidew all and the f loor.3.2. 2.1.5 Apex Fo rw ard Compartment Heat Shield Cover . - The apexf o r w a r d c om pa r tm e n t he a t s h ie ld c ove r s t r uc tu r e s ha l l f o r m , the f o r w a r dsectio n of the CM st ru ct ur e and shall con sist of an aluminum allo y skinand s t i f fe ners ut i l izing r ive ted and bol ted construc t ion. .A lightweighti nne r sk in sha l l be used to in sure a smooth su rfac e such tha t the forwardcom partm ent cove r sh a l l not inte rfer e with the parachute bags o r equip-me nt upon ejection. The nose cone w i l l be a luminum.3. 2. 2.1.5 .1 CM Insulation. -with sui table co rk insula tion to pro tec t the module f r om aerodynamicheating during the launch phase.

The CM ex ter i or sha l l be provided

3.2. 2.1.6 Acc ess Hatch. - The main ha tch sh a l l provide ac ces s to theC M In te r ior .pla te and s ha l l b e bol ted into place .wall ov er the head of the c enter couch posit ion.

The ha tch sh a l l be co nstruc ted of re info rced a luminumIt sha l l be loca ted in the CM s ide -

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3. 2.2.1 .6.1 Acces s Doors. - Access doors sha l l be provided in thesk i r t s t ruc ture for se rv ic ing the hea t sh ie ld a t t ach s t ru t s .ings sha l l be provided in the forward c rew compar tment s t ruc ture ,approxima te ly 90 degrees ap a r t , for t e leme t ry an tennas .

Four open-

3.2. 2.1.7 Miss ion Sequencer. - The miss io n sequ ence r sha l l au to-mat ica l ly con trol LES-CM and CM-SM sep ara t ion .functions of the mi ssi on seq uence r wi l l be at the discre t ion of theMSFC.

Other poss ible

3. 2. 2.1 .8 E lec t r ica l Power Sys tem (EPS). - The CM EPS s ha l l supplyand dis t r ibute e lec tr ica l power and sha l l con sis t of the following ma jo rcomponents :

(a ) Main power ba t te r ies( b ) Py r o - ba t te r i es(c ) E le c t r i ca l di s tr ibu t ion sys tem

(1 ) CM-LE S umbil ica l( 2 ) CM-SM umbilical

3.2. 2.1.9 R and D Commu nications Equipm ent. - NAA/S&ID ha s nor e qu i r e m e n t f o r R and D commu nciations equipment in Boil erplateNum5er 16.3. 2 . 2.1.10 R and D Instrumentation Equipment . - NAA/S&ID ha s nor e qu i r e m e n t f o r R and D ins t rumenta t ion equipment in Boi lerpla teNumber 16.3.2.2.1.11men t for an ECS in Boi le rp la te Number 16.

Envi ronmenta l Cont ro l Sys tem. - NAA/S&ID has no req ui re -

3. 2. 2 .1 .1 2 CM-SM Attach System . - The CM-SM a t tach sy s tem sha l lut i l ize pos i t ive tension t ies through the th re e SM compres s ion pads .The th ree pre loaded tension s t ra ps sha l l be secu red to the CM inne rs t r uc tu re and the SM a t the uppe r beam.

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3 . 2 . 2 . 1 . 1 3 CM-SM Separation. - Capabil i ty for CM-SM sep arat ionis not provided for B oilerplate Number 16.3. 2. 3 Ser vic e Module. -124 inche s in length and 154 inches in diameter .be aluminum s emi-monocoqu e construction consist ing of skin , longerons ,a n d f r a m e s .

The SM sh a l l b e a cylinder approximatelyThe s t ru c tu r e sh a l l

3. 2 .3 .1sha l l be ins ta l led at stat ion 325.

SM Reaction C ontrol Syste m (RCS). - The SM RCS enginesThe RCS quad packages shall be

dummy mot ors s imula t ing the s iz e , weigh t, shape , locat ion, andaerody namic char ac ter is t ic s of the ul t imate sp ace cra f t RGS.3. 2. 3 . 2 SM In se r t . - The SM ins er t sha l l be loca ted be tween theadapte r and SM.monocoque construction approxim ately 52 inches in length and 154inches d iameter .

The inse r t sha l l be an a luminum cy l inder of se m i -

3. 2 . 3 . 3 Adapter. -s e m i -monocoque construction approxima tely 9 2 inches in length and154 inches d iameter .th e S-IV st ag e of the S-1 Launch Vehic le.

The adap ter sha l l be an a luminum cy l inder ofI t sh all be located between the SM i n se r t and

3. 2. 3 . 4 SM Purg ing. -GSE GN purging lines.

Provi sions sha ll be ma de in the SM to at tach2

3 . 2 . 3 . 5 SM P rote ctiv e Bulkhead. -attach ed to the lower r ing in the SM adapte r .a n a ir condi tion ing ba r r ie r to i so la te the S-IV cool ing s ys tem f ro mthe adapter cavity .

A protect ive bulkhead sh all beThis bulkhead shall be

3. 2 . 4 Launch Vehicle. -wi l l be the Satu rn I Block I1 configuration.

The launch vehicle for B oilerp late Number 16

3. 3 Per fo rman ce . -outlined by the MSFC.

The per formance of Boi lerp la te Number 16 wi l l be

3. 3. 1 T r a j e c t o r y P a r a m e t e r s . - To be d ete rmi ned by the MSFG.3. 3. 2 Fl igh t Plan . - To be de termi ned by the MSFC.

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4. QUALITY ASSURANCE4.1 Gen era l Quali ty Assuranc e Provi s ions . - The principal cont r acto r(S&ID) sha l l be respons ib le f o r the per form ance of a l l i nspec tion re qu i re -men ts a s speci f ied herein . Except as othenvise speci f ied, the principalcon t racto r m ay ut i lize his own or any other inspect ion faci l i t ies andse rv ice s acceptable to the NASA.tions an d te st s sh al l be kept complete an d ava ilable to the NASA a sspeci f ied in the cont r act .

Inspect ion records of the examina-

4.2 Pr i nc i pa l C on t rac t o r ' s Q ua li ty A ssu rance P rog ram . - The principalcont rac tor s ha l l es t ab l i sh a qual ity ass ura nce prog ram in accordancewith the req uir em ent s of pa rag rap h 6 of Exhibit I of the cont ract .t ions and t es t s to de te rmine conformance of Boile rplate Number 16 tocon t ra ct and specif ication requi re men ts shal l be conducted prior to sub -mi ssio n of the ar t i cl e to the NASA for ac cepta nce .

Inspec-

4. 2. 1 Relia bility Data. - The pr inc ipa l con t rac tor sh a l l ac t as a t es th i s to r i a n and accumula te appli cable da ta on spac ecraf t t es t s , plans, andperforma nce f r om prepara t ion to de livery . The data s hal l be used inqual i ta t ive and quant i tive as se ss me nts of r e l iabi l i ty and performance ofeach sys t em , and of the ul t ima te spac ecr aft .o ther appro pr i a t e da ta , such as accep tance da ta , sha l l be in t egratedw ith t ha t accum ula t ed f rom p r i o r t e s t s t o fo rm a s s e s sm en t s . Thus ,a probabil i ty of su cc es s ma y be provided f o r any given phase. There l i ab i l i t y da ta ma y a l so be compared with p rogr am objec t ives inor de r to as su re tha t t hese have been a t ta ined .

This data , together wi th

4. Examination. - Each assem bly and a l l majo r component s submi t -ted for ac ceptance sh al l be sub jected to a visual examinat ion to dete rmin econformance to ma ter i a l s , des ign , cons t ruc tion , d imens ions , color andfinish, product mar king , and workmanship.4. 3 . 1 Components. - The pr inc ipa l con t rac tor sha l l asce r t a in tha t ,p r i o r to a s s embly, all par t s , components , a s s embl ies , and s ys tem sprocured under s epa ra te spec if i ca t ions o r d rawings have been inspec ted ,t e s t ed , and acce pted in accordance wi th thei r r espe ct ive spec i f icat ions o rdrawings.4.4 Test s . - Each assembly , majo r component, and sys t em submi tt edf o r accep tance sh a l l be sub jec t t o per formance t es t s as spec if i ed inSID 62-109.

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N O R T H A M E R I C A N A V IA T IO N , I N C. SPACE an d INFORMATION SYSTEMS DIVISION

5. PREPARATION FOR DELIVERY5. 1 Pr ese rva t ion , Packaging, and Packing. - Preserva t ion , packaging ,and packing s hal l be in accordance with the principal co nt ra cto r ' sprocedure s speci f ied in SID Process Speci f icat ion MA 0116-012.6. NOTES6. 1 De live ry of Modules. - The SM , Adapter and In se rt w i l l bedel ive red sep ara tely to the MSFC for inst rume ntat ion.G M w i l l be de l ivered a t a l a t e r da te .

The LES and

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N O R T H A M E R I C A N A V IA T IO N , I N C . SPACE an d I N FO R MA T IO N SY ST E MS D I V ISI O N

Launch Escape Sys temCom mand ModuleService ModuleInsert

TABLE I

ESTIMA TED WEIGHTS AND CEN TER O F GRAVITY

aWEIGHT* X

6,290 1293.84,660 1036.63,930 949.71,130 840.1

I CENTER O F GRAVITYIT EM

AdapterTotal

I 2,090 I 763.218, 100 1063.2

Y

0.00.30.10.00.0

z

0. 01.20.50 .00 .0

0.1 0.2

NOTE: *NO ba ll as t included.

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APPENDIX ADRAWINGS

1. Scope. -components for B iolerplate Number 16.

The following l is t const i tutes the top drawings of m ajo r

Nom enc latu r eG e n e r a l A s se m b ly B P 16Gene ra l Assembly LES 12Body Group Assem blyTower AssemblyT ow er S t ruc t u reSki r t A s s emblyPower Supply Ins ta l la t ion, CompleteRocket Motor SetEl ec tri ca l Ins tal lat ion, CompleteEle ct r i cal Installa t ion, TowerWiring DiagramEle ct r ic al Installa t ion, MotorGen era l Assembly , CM 22Stru ctur e Assembly, Complete CM22S t ruc t u re A ssem bl ySt ruc ture , Aft C rewA f t BulkheadBulkhead-Forward AssemblyS t ruc t u re - Aft Heat ShieldCo ver Instal lat ion, Ablat iveEle ct r ic al Ins ta l la t ion, CompleteEle ct r i cal Installa t ion, Crew Compartm entWiring DiagramCover-SequencerE l e c t r i c a l Ins ta l la t ion, ForwardCom par tmentEle ct r i cal Ins ta l la t ion, Aft Compar tmentGene ra l Assembly , SM5St ruc ture , Comple teSt ruc ture . As s emblySt ruc ur e Ins e rSupport A s s embly

NumberB14-000002-231B15-000002-171V 15 -300001 -7 1V 15 -300 100 -11V 15 -300 10 2-241V 15 - 300202-41B 15 -400001 -71B 15 -410001 -41B 15 -450 016B 15 -451 40 1B 15-450401B 15 -451410B 16-000002-281B16-300016B 16-301006-401B 16- 3 11006B16-301081B 16-301 073-401B16-327006-91B16-320013B 16-450016B 16-45 140 1B16-450430B16-451207-11B 16-456401B16-457401B17-000002-191B 17-300016B 17 -320 101B 18-320 113B 17 - 320 140- 1 01

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APPENDIX A (Continued)DRAWINGS

NomenclatureFa i r i ng Ins ta l la t ion and AssemblyFa i r i ng A ssem bl yE l e c t r i c a l Ins allat ion, CompleteG ene ra l A ssem bl y - Adapter 11St ruc ture , Comple te

A - 2

NumberB17-320142B17-320141B17-450016B18-000002-221

B 18-300016

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SPACE: and I N Y O H L l : \ l I ~ l NS Y S T K L I S D IV ISIOO R T H A M E R I C A N A V I A T IO N , I N C .

APPENDIX BFLIGHT HARDWARE

1. Scope. -de te rmined by the MSFC.The f l igh t ha rdw are for Boile rpla te Number 16 is to b e

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D I S T R I B U T I O N FOR C F E SPEC I F I C A T I ON *(PARAGRAPH 4.2)

A ddr es s C op i e sNational Aerona ut i cs and S pace Admini s t r a t ionAt lan t i c Miss i l e Range Opera t ionsPor t C anave r a l, F l o r i daAttn : Mr . B .P . BrownNASA Headquarters.1520 H Str ee tWashington, D. C.Attn: M r. G.M. Low, MD(P )G r um m an A i r c r a f t E ng i nee r ing C or po r a t i onBethpage, Long Islan d, New YorkAttn: P. G ar d i ne rMIT Ins t rumenta t ion Labora tory75 C am br i dge Pa r kw ayCambr idge 39 , M assachuse t t sNASA Resident Apol lo Spac ecraf t Pr oj ec t Off icerG r um m an A i r c r a f t E ng i nee ri ng C or po r a t i onBethpage, Long Isla nd, New YorkAttn: Mr . J ack Sm al lNational Aeronaut i cs and Space Adm ini s t r a t ionPost Of fi ce Draw er DWhi te Sand s Miss i l e RangeWhite Sands, New MexicoNational Aeron aut i cs and Space Admini s t r a t ionManned Space craf t CenterTranspor t a t ion Of f i cerElington Building 381Houston , TexasAttn: Apol lo Documen t Control CenterEl ington 336 - TO BE OPE NED BY ADDRESSEE ONLY

5

6

1

2

3 5

T h e dis tribut ion for this report has been accomplished in complia nce with paragraph 1.2 of Exhibit I of contract N A SS- 15 0and the N A S A Apollo Docanentation Distribution List ( N A SA - M SC let ter SP-63-478, dated 2 October 1963).


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N O R T H A M E R I C A N A V IA T IO N . INC. SPACE and INFORMATION SYSTEMS DIVISION

A ddr es sNat ional Aeronau t ics and Space Adminis t rat ionHea dqua r ters NASA Plant Off icerP.O. Box 2500Daytona Beach, Fl ori daAttn: Adm inis trati ve Contracting OfficerNat ional Aeronaut ics and Space Administ rat ionManned Spacecraf t CenterResident Apollo Spacecraft Project Office NAA12214 Lakewood Bouleva rdDowney, CaliforniaNat ional Aeronaut ic s and Space Administ rat ionA m es R esea r ch C en t e rMoffett Field, Cal i fornia Attn: Li br ar yNat ional Aeronaut ics and Space Administ rat ionL ew i s R esea r ch C en t e rCleveland, Ohio Attn: Li br ar yNat ional Aeronaut ics an d Space Administ rat ionF l i gh t R esea r ch C en t e rEdwards AFB, Cal i forn ia Attn: Res earc h Lib rar yNat ional Aeronaut ics an d Space Administ ra t ionJet Propul s ion Labora toryPasade na, Cal i fornia At tn: Lib rar yNat ional Aeronaut ics an d Space Administ rat ionLangley Research CenterLangley AFB, VirginiaAttn: Mr. A.T. Mat tsonNat ional Aeronaut i cs an d Space Admini s t r a t ionGoddard Space Fl ight Cent erGreenbel t , MarylandAttn: Manned Flig ht Sup por t Office, Code 512Nat ional Aeronaut ics and Space Admini s t r a t ionGeorge C. Mar sha l l Space F l ight CenterHuntsvil le, Alab ama Attn: M-SAT -AP

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