report of 204 bqard · c/m rcsc c/m r csc data function/input adapter separa-tion + 2. 5 seconds or...

REPORT OF APOLLO 204

REVIEW BQARD

THE ADMINISTRATOR ! - NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

APPENDIX C

II '',: .

SM2A-03-SC012

Ai_OLI.O OPERATIONS HANDBOOI'_

SYSTEMS DATA

SECTION g

SUBSECTION 2. _)

SIEQLIENTIAL ,_YSTEMS

L,. •[NTI_ODL' CTI()N,

The _equential _ystt'ms consist ol controland detectien sy._tems

which function durinb_ aBet'lit and entr}, pk_t_tion_ of a mi_._ion or in pre-

orbital ab0rl_. The control function._ ari, sensing 1./\ r _tatus, displa.ving

[,IV _tatu_ to the crew, ,u_tomatically initiating IA_18 aborts in an e|m'r-

gtulcy duri_lg ('arly a_cent, and automatically _equencing Ihe E[,8 during

descent. Backup control_ are provided for critical function_ and normal

e\'ent,_. The systemu are the sequential e\'elll8 COIlll'O[ syStelu (SI'ICS),

¢lnt, t'geucy detection _vslcl_l (F:I')S). launch escape 8yslt, lll (I.,I,,;S). alld.

earth [,uldill_, _yslt'[ll (l.'l,S), The 8yslel/18 illterfact' wtlh the rcaclton

t.0nlrol ,_ystt'ln (IICS),, guidance and navigation (G&N), ,_crvice propulsion

_y._lcm (SI)N), stal)iliaalion and conlrol u}/sli'm (SCS), clectrim_l power

_yslenl (I';PS), lclecommu|_ications (T/C), and cont|'ol8 and displays (t'&l)),

I"UNC I'IONA.I, i)I,:SCRI|'I'ION,

The purpose ol Ihc _cqucntial syslem_ is to provide 8aft, tg Ior lilt'

t'l'l'%V (llll'itlg tho alNl.'t'lll ,llld dt!8_'_.'l'tl [._}/.I.'A_.'.'4 O|' li llliS:;itlll, dlld Ill pt'l"[Ol'llt

normal sep,lration t'ullcl.ioua. Tlu" I,:DS monitor8 ope|',',l.ion oI the I,/V ,ind

\viii iuitiat,e an atltolll,ttlt' ahort ul ,in cn_ere,0tlc}'. The 1,1".S is proxid,'d

|'Of I1._t" dtll"itll_ all t'lllt'l"l.#,t'llC.V .ll*iNitl._ |'1'OIII tll.t|l'ttllCliOll ol l|11" I,/\" or

other ,_ystcms all'eclitlg crew s,llt't}', The l,t':S will be.utilized to itbol't

the lnission in an emc|'gt'nt'y h_" Sel_al'ating the C/M trotn tile I,/V aud

S/M. The IA-:S can he oper,_tional lroII1 II11" 1,lunch pad until tilt' launch

t'Ut',lpt" lov_'er is jt. lli:;tllll'd, l,'ollmving ,ccond stage hot_:_tcr i..t/,llilion, lilt'

l,i':N IOV¢I'I" iS cllisoUCd Irom ihv t'SM-I,/V collll_inalion, The I':I,S i:_

pro_ hlcd Io ,_lahillzc aml decch'|'.lt,' Ihc I,'/M t't_llo_i'ing .in cllll'y iuio the

earlh ,ltl,_obphcrc or ulloi_\'l|l_a ,m abort. The l.;I.N p,lrachutcs will lo,,vcr

,h,, c ,' .,,.,, l, ,, .1u t i,, "\t'uncti,mat dt, scription ot thc scqul,t_t_al_,_,"_tc_'_u },,_ _u}nt,_l't(,¢/ _fl'lltlJ\'?r _,Iolll_\ving p,i r.l!/r,_phs, It '

I.

,Ncquenti;ll l'Nenl._ t'onlrol S_'utcnl ISl':_'_). " _ '_ k:Z'._

Flu' NI"L',N coil,_i.st,_ Ol controllcr:_ (fi,_urc dT'_Ol) that provid,' aut,-.

Ill,tlt_ . st'llll,llllOlll,tlit', 01111| 11hllllt,t| t'Ollll'Ol-lOf [ll[li,l|itlll 111" II, l"I11111A|I_MI

Of ltlllt'tlOII,t[ _"_l'llt_ I|lll'illg _,'.tl'[I.ItIN }.)ll,lNt'N _.lt |lu' Ap_lh_ IIIi.'A._LtIII, III1'

controlh'r_ .11'_' the m.18ter vvcnl,_ ._.qucnt'e t-m_troller (,MlqS('), earth

landing _equl,ncc ..ontl'ollvr (}it,S{'). C/M r_,.lct, ion _,'OI1|1'Ol ,"i}'.'ltt'lll i"Oll-

trolh, r (('_MR_'.Nt'). _of'vict- lllt_dul,'-,l_'ltt_OII cmlt:,_ll,'r (SMJC). Each

_Q}t Iql_

NI,:Q!It,',N I'IAI. ,_ Y,"i _.l'.;Mb

[1Ate I,_ Nov Iql_l_ _'hant:,' D.Iti _2.. '_- I

$MZA-03-SC0 IZ

APOLLO OPERATIONS HANDBOOK

SYSTEMS DATA

ii Hi I

controller consists of redundant relays, timers, and other devices to

control systems operation and automatic timing of events. Two controllers

are provided in all cases for dual redundancy. The SECS will contr0_ the

automatically sequenced events during a mission abort, normal CSM-SLA

separation, normal C/M;-S/M separation, and events during the earth

landing phase. The SECS provides conditioned signals to telemetry

equipment through the data distribution box so that vital information may

be telemetered to MSFN. i

The SECS will control the launch escape system (LESt during at,

abort up to the time of normal IAtmch escape tower jettison. The SI°S

engin6 is utilized during an abort after LES tower jettison to propel the

CSM away f:omthe L/V, Normal separation of the SLA is 15erfornacd

by the SECS following manual initiation after earth orbit is attained.

Emergency separation of the SLA is performed automaticall_r 1.7 s_conds

after an SPS abort is naanually initiated. C/M-S/M separation is per-

fortned by the SECS, and is mb.nually initiated during the entry phase or .

subsequent to an SPS abort. During a LES abort, the C/M-S/M sepat'a-

tion is performed automatically by the SECS. Events performed by the

earth landing system are automatically controlle.d by the SECS during

normal descent. Switches are provided for manual backup of critical

events.

The basic functions performed by thd SECS ard as follows:

Event

Auto abort _nable

LE and PC

motors fire

Pitch motor

inhibit

Auto RCS oxidize#

dump inhibit

LES towcr

jettison

CSM-SLA

separation

Originatesi

MESC

MESC

C/M R CSC

c/M Rcsc

MESC

MESC

Function/Input

Lift.off _ignal

C/M-S/M separa °

Manual Control

EDS AUTO fiwitch

(M DC- 16)

LES MOTOR FIRE

tion relays

Lift-of_ + 61

seconds

LiftLoff. + 61

seconds

ELS armed, and.

sWitela (MDC- _)

ABORT SYSTEM-

OX DUMP switch

(MDC- 16)

ABORT SYSTEM-

OX DUMP switch

(MDC-16)

ABORT SYSTEM-

Z4H ft baross_tch

closure on

LEs aborts,

manual 3 fix!autos

atttSt _ lift-off

Trafisl[ition con-

trol _ 1.7 ,econds

MODE switches

A and B (MDC-16)

ADAP SEP switch

(MDC-S)

lMis st.,t: , Basic Date 12

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Nov 1960, Change Date , (i) " i-, Page 2 .... 2

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Event

RCS/SCS enable

LES abort

initiation

C/M-S/M

Separation

Canard deploy

SPS abort

initiation

RCS/SCS, disable

Apex cow. r

jettison

Drogue parachute,

deploy

Drogue pa rachutos

release and main

parachutes deploy

RCS propellants

bttrll

RCS purge

SYSTEMS

Originates

VIESC

MESC

MESC

MESC

MESC

MESC

MESC

ELSC

ELSC

C/M RCSC

C/M R CSC

DATA

Function/Input

Adapter separa-

tion + 2. 5 seconds

or C/M-S/M

deadface + 1 second

EDS abort signal

from L/V-IU

C/M-S/M d_ad-

face relays

+0. 1 second

LES abort lockup

relaFs +II

seconds

Manual

ELS armed and

Z4K ft baroswitch

closure

ELS armed and

24K £t baroSwitch

closure

+0. 4 second

ELS armed and

24K ft b&roswitch

closure

+i seconds

ELS armed and

24Kft baros_dtch

closure

+ 14 seconds +

10Kit barosx_/tch

closure

Manua I

Manual

Manual Control

REACTION CONTROL

SYSTEM-CMD

switch (MDC- 16)

Translation control

C/M-S/M SEPSwitches A and B

(MDC- 15)

CANARD DEPLOY

switch (MDC-5)

Translation control

REACTION. CON.TR O I,

SYS-CMD switch

(MDC- 16)

APEX COVER .

JETT switch

(MDC-5)

DROGUE DEPLOY

s_vitch (MDC-5)

MAIN DEPLOY

switch (MDC-5)

C/M PROP JETT

DUMP switch

(MDC -8)

C/M PROP JETT

PURGE switch

(MDC-8)

Mission __ Basic D&te

SEQUENTIAL SYS.TEMS

12 Nov 1906. Chanue Date .. - ,, Paga-- ", ,_,-3 ....

SM2A-03-SC0 IZ


Evc.nt

Main parachutes

release

Po stlanding

antenna deploy

SYSTEMS DATA

Originates

ELSC

MESC

Function/Input

Manual

Manual

Manual Control

MAIN CHUTE

release switch

(MDC- 16)

POS T LANDING-

AN T ENNA- DEP LO Y

switches A and B

(MDC-Z 5) ,

_.9.,2Z Emergency Detection System.

The EDS is designed to detect and display status and emergency

conditions of the launch vehicle-spacecraft combination to the astronaut.

The EDS also provides automatic abort initiation, under certain condi,-

tions, after lift-off up to the norn-al time of LES tower jettison.

The EDS display circuitry is enabled When the EDS POWER switch

(MDC-24) is in. the ON position and will illuminate lights on MDC-5 to -

indicate L/V statuS. The red L/V RATE light will illuminate, when .

L/V rates are in excess of 20 degrees per second in roll and 5 degrees

per second in pitch and yaw. The rates are sensed by three rate gyrosmounted on each L/V axis in the instrumentation unit (IU). The red

L/V GUID light (MDC_5) illuminates to indicate failure of the guidance.

unit which is also located in the instrumentation unit. The yellow L/V

ENGINES lights (lxCDC-5) illuminate when a respective S-I booster engine

is developing less than 90 percent of total thrust output. The L/V

ENGINES lights are monitored for engine status during thrusting periods.

During staging, the L/V ENGINES lights arc monitored for illumination

to indicate BECO and extinguish to indicate stage separation. After

staging, the number 1 L/V ENGINE light indicates the stat_s of the

S.-IVB Stage engine, it will be extin_uishedwhen the engine is producing

65 percent rat6d thrust. The ABORT light (MDC-3) is a red lamp

assembly containing 4 bulbs. TwcLbulbs are in System A and two bulbs

are in syst6n_ B for redundaricy. The ABORT l_ght is illuminated if

an abort is requested by launch control center for. a.pad abort or an

abort during lift-off via radio. The ABORT light can be illuminated

after lift-of.f by the Raf_ge Safety Officee [ransmitting a destruct arm

command. The destruct arm command will also initiate BECO. An

abort may also be requested via radio from the MSFN after lift-off

*10 seconds.

The EDS automatic abort circuitry is enabled at lift-off providing

the EDS AUTO switch (MDC-16) is it the AUTO position, (See

figure 2.9-2.) A circuit is completed through the lift-off enable and

first motion relays at lift off. The lift-off enable relays are latchifi$

S EQU I::NTIAI. SYSTEMS

Mission ...... Basic Dat- _..1.2 Nov 1966 Chan_e Date , Pa_e 2.9-4

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SMZA-05-SC012

APOLLO O P_'P'ATIONS HANDBOOK

SYSTEMS DATA

type and are latched closed by GSE just prior to lift-oft. The normally

closed first motion relays remain energized by GSE until actual lift-off

occurs. A circuit is completed through the relays and the EDS AUTO

switch upon lift-off. The white LIFT-OFF light (MDC-5) illuminates and

the red NO AUTO ABORT light (MDC-5) should remain extinguished.

The astronaut presses the NO AUTO ABORT switch-light if it illuminates.

The NO AUTO ABORT switch-light should also be pressed if the LIFT

OFF light does not illuminate at lift-off. This would indicate that the

circuit was not completed for illuminating the LIFT OFF light and ener-

gizing the auto abort enabling relays. Pressing the NO AUTO ABORT

switch-light will energize the auto abort enabling relays through circuitry

in the MESC. The EDS AUTO Switch must be at AUTO to complete the

circuit. The LIFT OFF light would not illuminate in this case. (Refer

to Malfunction Procedures in Section 9.) The LIFT OFF light i._extin- .

guishedby circuitry in the L/V IU at approximately 5 seconds after

illumination at lift-off. The EDS will automatically initiate an abort

when two L/V engines fail Qr L/V excessive rates are sensed if these.

tWO functions are enabled. The two functions are enabled with the

ABORT SYSTEM - 2 ENG OUT switch (MDC-16) and ABORT SYSTEM -

RATES switch (MDC-16). The two switches are set to off to inhibit the

two functions prior to S-IB staging. L/V guidance failure will not initiate

an automatic abort. The crew will contact MSFN and a decision made

on the action to be taken. If a destruct arm command is transmitted

priol to inhibiting the two-engine out auto abort capability, the EDS will

detect BECO and initiate an automatic abort. If a destruct arm command

is transmitted after the two-engine out auto abort capability is inhibited,

a manual abort must be initiated immediately when the ABORT light

illuminates. Structural breakup or s.eparation of the structure between

the IU and C/M will also be detected by the EDS and an automatic abort

initiated. During ascent on a n0rmalmission, the EDS AUTO switch must be

set to OFF prior to launch escape tower jettison. Inhibiting of the

auto abort capability _ensures that an automatic abort can not be initiated

at the same time that the launch escape tower is being jettisoned. An

abort may be initiated manually b), rotating the commander's translation

control to the counterclockwise detent positio n (20 degrees).

The pararo.e_ers being sensed h7 the EDS are extremely time-

critical at various periods during the boost phase. When these param-

eters are exceeded, an LES abort is automatically initiated to pr.opel

the cscapi_ g vehicle (C/M and LES) safely away fron_.the launch vehicle

prior to a catastrophic conditioh. Concurrently vcith abort initiation,

either atttomatically or manually, logic circuitry will shut down engines

in the L/V activate stage. The engine shutdown signal is inhibited by

circuitry in the IU fo_ the first 40 seconds of launch because of range

safety restrictions.

A Q-ball (figure 2.9-3) mounted above the LES motors, provides

an el6ctrical signal input to the L/V AOA/SPS Pc indicator on MDC-3

and an electrical signal input to ground cotitrol via telemetry.

- " " SEQUENTIAL SYSTEMS

_iis-:konL -- _Baste Date Iz Nov 1966 ,Chani_e Date_. Page

2.9-9

Q*I_LL

PITCHCONTROt

SMZA-03-SG01Z


SYSTEMS DATA

SURMCES

COMPARTMENT

,ONMOTOR

SKIRT

LAUNCHESCAPETOWER LAUNCH ESCAPETOWEk

SEPARATtON NUTS(4 PLACES)

-y

PROTECTIVECOVER

5M-." a,-',; ,,

Fi_2. '_-3. I_aunch E_cape S3"st.,,m

The Q-ball has four static port.,, for mc,lsuring _P which _._ a

function ofangl,:- of attack. Fhe..M _ i_ related Io pitch ae, d yaw, a,_,! _._

elcctronitall_- analyzed and displayed on the t,/V AOASi-_S Pc inctic._,,r

on MDC-3. The indicator i_ gracl,mt_,d to lq0 percent hccause of _',:_

transients of the SPS. 'Flat" indicalor is mo:utor_.d tot Ihc 1,i'V .\t._A

function from 40 seconds after lift-off until approximatt, ly one mi.autc

and 40 seconds.

Position of the red line is based on vchlv:e .slvu_.tural lip,',:t,, .::-,:

laamch vd_iclc capabilitie_._. A dccisi_,n to_- mamml abort initi,ltltm x_;/

be made when the indicator pointer reaches thL' red line and .l ::-,_,.c,

i_ also observed on the FDAI.

Launch Escape Svstt,_,.

Purpose of the I,F:S (figure 2. ')-._) is lo provide imnledi,_le abort

capahilith,._ frOlll the latlnch pad to lh,. llt'll'lllffl tIIll¢" t,lf I,_]S [o'_,t" I it,ill :,

Thv &BORTN'I'S'I'EM - MODI'_ aw_tcl_es 1 and 2 (MDC-Ib) ar,' m tl:,.

LI}]S MODI" po_iihon prior to LES lower iettts_vn, and an ab_rt _tll l,_.

a_ton:pli._hed by ut_h.'.itq4 tlu' l,tlltl_!: c:.t.lpe :¢¥:,[_'111. A lll._llu,_l o|

SF'QUI':NT|A! S_S I'I-;M._

tl, asti" Date ld Nov |_)hb _'h _:_' Y_atO-- , . l.'_i_1_, ' ,). l0

F ..

SM?A-03-SC012


SYSTEMS DATA

I

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automatic initiated abort signal will activate a masl-cr event scqucnc,

controller (MESC). The MESC will initiate C/M-S/M separation. -and

ignite the launch escape and pitch control motors. Firing of the pitch

control motor is automatically inhibited 61 seconds after lift-off by a

tirnd-delay relay. The LES motors provide sufficient thrust for the lift

and lateral translation of the C/M away from the launch pad, or trajec-

tory of the launch vehicle. Two canard surfaces (figure 2.9-3) ari.

deployed 11 seconds after abort initiation to orient the C/M to a blunt-

end-forward attitude. (R0fer to Abort Procedures in section 9.)

During a normal mission, the LES tower is jettisofled shortly after

second stage booster (S-IVB) engine ignition. LES tower jettison is

manuall3_ initiated approMmately 3 minutes after lift-off by setting the"

ABORT SYSTEM • MODE switches 1 and 2 (MDC-16) to the T.WR JETT

SPS MODE position. E[ther switch will enable systems A and B of the

redundant circuitry. Both switches should be set at the same time.

Any abort, after LES tower jettison, must be accomplish6d in the SPS

mode by utilizing the SPS engine. (Refer to Abort Procedure_ in

section 9.)

A boost protective cover (BPC) completely covers the conical

section oi the command module. Tke. cove_' protects the command

module and windows from heating during the ascent phase, and soot at

launch escape tower jettison in the event of an abort. The cover is

attached to and is jettisoned with the LES tower. A removable Section.

allows access to _he C/M crew.compartment. The cover has one window.

fabricated of fused silica glase and is located over the forward viewing

wifMow_

, n _ 4 Earth Landing System.

The ELS provides for safe return of the command n,.odule and

crexv following anearth orbital mission, a hmar mission, or mission

abort. The ELS consists of two earth landing system controller's (EL,SC)

and paraclmte_. The ELS logic circuitr},, is armed automatically durhig

an abort in the l..ESmode, and is a_med manually with tht, ELS LOGIC

switch on MDC-8 during a SPS abort or normal entry. The ELSC con-

tains bare switches and time-d_lrty relays. After _he logic.circuitry i,_

armed, the Ei,SC'automatieall,.,';enses altitude and initiates deployr_ent

of the parachutes at tl, e proper time. The time-delay relays control

initiation of automatic events after the 24,000 feet bare s_('itch closes.

The parachutes (figure 2.9-4)are located Jr, the forward compartment ot

the C/M. under the apex cover. Duringa normal entry or descent _'rom

an abort initiated ahoy0 30,000 feet, the 24,000 feet hare switch closes

and completes a circuit.to the MESC whic.h jettisons the launch rscapv

tower. The MEsc initiates apex cover jettison 0.4 seconds aftvr launch

escape tow_-r jettison. Closing ot the 24,000 feet bare switch comph.tcs

a circuit to a 2-second time delay and a 14-second time delay to jettison

tht, dro_:ue parachutes in 2_econds. The 14-second tim_, delay comph-tcs

a circuit to tht, 10,000 feet bare switcl;.

SI_QU ENTIA L SYSTEMS

M_sslon. Ba.s:c Date 12 Nov Igbb Change flato - Page 2. q-ll ,.,

SMZA-03-SC01Z

APOLLO OPERATIONS HANDB00K

SYSTEMS DATA

I

• ,.._ _ DROGUEPA_C_UIE$

_.. _ APEX COVER

MAIN PARA(_IUYEg .

• ,_ ''/(3 I'LAC_S).

:. _ __ I_ROGUE PARACHUTES

g: " ,' _!1 -_'--- \ ANOMORTA_"- .,;/ J . _-" " _X CaPu_c_s)

I%|ilsion

Fil.lt_re 2. g-4. EL_ Phr,_chute Equipment

$1_,QU F,N'I'IA I S YS T EI_LS

-Basic _late IZ Nov 1966 Change l'_t_, Pa,ap

SM',_A'7 ;'_

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SMZA-03-SC012


SYSTEMS DATA

The drogue parachutes are held in a reefed condition for 8 seconos

by two reefing lines. Each reefing line has two reefing line cutters. A

pyrotechnic time-delay train in each reefing line cutter is ignited at the

time of drogue parachute line stretch, causing automatic disreefing after

8 seconds. The drogue parachutes remain attached to the command

module until descent to approximately 10,000 feet where the I0,000 feet

bare switch closes to initiate drogue parachute disconnect. Simultane-

ously with drogue parachute disconnect, three pilot parachutes are

independently mortar deployed, which removes the main parachute packs

from the C/M and extracts the main parachutes from their deployment

bags. The main parachutes are reefed for 8 seconds. Disreefing then

occurs, and the parachutes fully inflate to lower the C/M safely to

landing. Three reefing line cutters are employed on each of the two

reefing liges for the main parachutes.

A 27-1/2-d.egree hang-angle of the C/M is maintained by means of

the main parachutes attachment. The hang-angle contributes to the crew

tolerance impact by ensuring that impact occurs at the specifically

designed C/M structural attenuation point. This attenuation point is on the

+Z-axis.

Special note should be made that the apex cover jettison.and deploy-

ment of the drogue parachutes ma.y be manually "initiated at 45,000 feet

during a normal .entry if the flight characteristics of the .command

module become unstable. (Refer to operational limitations and

restrictions. )

An ELS - AUTO/MAN switch (MDC-16) is provided for the crew to

inhibit automatic deployment of the main parachutes during a low-altitude

abort initiated prior to 61 seconds after lift-off. The Switch is set to the

AUTO position prior to launch. In the event of an abort prior to 61 seconds

after lift-off, the crew will ue£ the switch to MAN after drogue parachute

deployment if the C/M is above an alt{tud6 of 3300 feet. Deployment of the

main parachutes will be manually initiated by pressing the MAIN DEPLOY

switch on MDC-5, when the althueter pointer reaches the adjustable marker

setting (3300 feet) on the altimeter face. This action will preclude the

possibility of the ten, mend module drifting back on a land area. The EI, S

switch should 1,e returned to AUTO after the nlain parachutes are deployed.

This will allow a 14-.second time delay to time out and permit release of

the main parachutes when the MAIN CHUTE RELEASE swltch is actuated

after touchdown.

5}':(Q(" F]N'['[,.\ i. S'_'5 [ }':.kl_

T_,.ls[¢ D,_te l" X,,x' lqot, . ("h,an,_,t, Date - ....

SM_A-03-SC0 IZ


SYS TEMS DATA

2.9.3

1.9.3.1

The postlanding recovery aids consist of a sea dye marker,

swimmers umbilical, C/M vent fan, C/M uprighting system, HF

recovery antenna, and a flashing beacon light. The sea dye naarker and

swimmers umbilical are deployed automatically when the recovery

antenna is deployed. The marker and swimmers umbilical are tethered

to the C/M forward compartment deck. The sea dye marker will last

approximately 12 hours. The C/M vent fan (partofthe ECS) is turned on

after landing to vent the C/M to the Outside atmosphere. The C/M

uprighting system is activated only if the C/M is in a Stable inverted

attitude. (Refer to Command Module IJprighting Systen_in section 2. )

The flashing beacon light and two VHF antennas located on the

forward compartment deck on the C/M are automatically deployed to

an upright position after main parachute deployment. The risers of

the main parachutes actuate reefing line cutters, which cut retention

ties and allows the beacon hight and VHF antennas to be extended in 8 seconds.

The beacon light has a self-contained power Supply capable of operating

the light for three 8-hour duty cycles. The flash rate is 15 per minute

at an intensity of 1.2 candle-seconds per flash.

The postlartding control switcheS are located on MDC-25. A

recovery pickup cable is provided on the command module for retrieval

by recovery forces.

MAJOR COMPONENT/SUBSYSTEM DESCRIPTION.

Each of the sequential systems employ redundant circuits for

reliability. Seven batteries are provided in the spacecraft to furnish

electrical power for the spacecraft portion of the systems during opera-

tion. Entry batteries A, B, and C, and two pyro batteries are located

in the command module, and two S/M jettiSon batteries are located in the

service module. Entry batteries A, B, and C are the only batteries that

are rechargeahle during the mission.

Entry batteri_ A and B furnish power for the EDS displays and

MESC logic circuitry,. The pyro batteries furnish poxver for detonation

of pyrotechnic devices during aborts, separation functions, and,para-

.nute operation .during the normal landing sequence. (See figure 1.9-_

for a C/_,{ battery bus tie-in schematic.) A description of each of the

sequential systems i$ contained in the following paragraphs.

Sequential Events Control Systen_.

The SECS consists of two master events' sequence controllers

(MESC), two earth landing sequence controllers (ELSC), two command

Misslon

SEQUENTIAL SYSTEMS

Basic Date I,Z Nov 1966 . Change Date

'I

t

!

[

[

SMZA-03-SC01Z


SYSTEMS DATA

ENTRY I_ATTE RY A

"lBAT A

100A F PWR (LEB-15C)

MESC-

LOGICA-BAT A MESC ARM .

(MDC- 5A _ A-BATA22) (MDC-22)

,SA)

5AEDS 1

_BAT A

(MDC-25)

EDS POWER

(MDC-24)

I ENTRY IBATTERY C .

÷I, BAT C

|00A ).i PWR (LEB-150)

I_ EI.S2BATC5A _ (MDC-Z_)

J ENTRY JBATTERY 8

EDS 3

5A 4BAT B(MDC-25)

MESC ARM

B- BAT 8

B

(LEB-150)

MASTER EVENT !MASTER EVENT

SEQ CONT,|. SEQ CONT-2

SAFE PYRO PYRO_ARM ARM

PYRO A PYRO B

SEQ A (LEB-I50) SEQ B (LEB-IS0)

F 0A 20A

• RELAYS

PYRO

BATTERY8

NEGATIVE

LOGICARM OFF q

VOLTAG

MESC-

LOGIC8-BAT B

(MOC,

22)

Figure 2.9-5, C/M Battcr.y Bus Tic-In Schematic

SEQUENTIAl. SYSTEMS

Basic Date 12 Nov 1906 Chan_e Date_Page

$M-2A-757E

_. "-lbf |

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SM2A-03-SCOI2


SYSTEMS DATA

module reaction control system controllers (C/M RCSC), and two service

module jettison controllers (SMJC). The SMJC is located in the service

module. All other controllers are located in the command module. Each

controller consists of relays, timers, and other devices to provide auto-

matid and semiautomatic control of the systems.

Many operations in the SECS are accomplished by pyrotechnic

dex4c6s of varieus types.. Apollo standard initiators (ASI) are used

throughout the spacecraft to in{tiate firing of the pyrotechnic devices.

The initiator acts as a primer, in most applications, for the main

pyrotechnic device. Pins in the initiators are electrically connected

with a one.ohm-resistance wire. When a current of at least 3.5 amperes

at 28 volts is applied, the one.ohm-resistance wire ignites a primary

explosive. The primary explosive, in turn, ignites a secondary explo-

sive to fire a detonator,, igniter, or gas cartridge assembly. The

detonator assemblies are used to transfer detonation from.the AS1/

detonator combination to explosive components to perform a specific

function• The other high explosive devices are flexible, linear-shaped

charges (FLSC).and mild detonating fuzes (MDF) that. are employed

during module separation functions. The igniter assemblies are used

to ignite the LES motors. The gas cartridges are used to actuate the

apex cover thruster assemblies, canard thrusters, SLA thrusters,circuit interrupters, and parachute deployment mortars. A control

relay maintains a shunt across each. pyrotechnic device prior to firing

and simultaneously removes the shunt upon receiving a firing command.

The Apollo. standard initi_.tor (ASI) acts as _ pressure cartridge for RC5

pyrotechnic valve s.

The major pyrotechnic functions performed by the SECS arc

listed below.

Function and

Pyro Device

Spacecraft LEM Adapter

(SLA) separation

a. Umbilical disconnect

b. Adapter separation

(explosive tratty)

c. Panel thrusters (8)

Apex cover jettison

a. Thruster cartridges

b. Apex cover pilot

parachute mortar

Normal Actuating

Control

Automatic signal from

MESC during SPS abort and

manual control from

ADAPT SEP switch


MESC

Backup Control

Comrrland pilots translation

control (left arm rest)

APEX CO_v'ER JETT s\vltch

( MDC- 5)

Mission

!

SEQUEN.TIA I. SYSTEMS

Basic Dhte 1g Nov 1.966 Change Date= Paue 2"()'Ir'" ' i

(:..

[-

I

I

_r-u_T_," _--_,

'.,p_. • .• .

SMZA-03-SC012


SYSTEMS DATA

Function and

Pyro Device

RCS oxidizer dump

a. He isolation valves

b. He interConneCt valv,

c. Oxidizer isolation

valve

d. Gas chromatograph

Oxidizer and fuel

burnoff

a. He interconnect

valves

b. Fuel interconnect

valve

c. Oxidizer interconnect

valve

RCS purge

a. Oxidizer bypass

valves

b.. Fuel bypass valves

Drogue parachute

mortars

Pilot parachute

mortars

Main parachute release

mechanism

C/M-S/M separation

a. Tension-tie cutting

charges

Normal Actuating

Control


RCSC during a LES abo.rt_

initiated prior to 61

seconds after lift-off.

Manual actuation of the

C/M PROP JETT-DUMP

switch (MDC-8)

C/M PROP JETT - PURGE

switch (MDC-8)

Automatic signal fromELSC

Automatic signal fromELSC

Manual actuation of MAIN

CHUTE RELEASE switch

(MDC_I6)


MESC during a LES abert

or C/M-S/M SEP

Switches 1 and Z

during normal mission •

Backu;) Control

None for fast r.,amp.

C/M RCS - He DUMP/OFF

Switch (MDC-Z6), and also.

opposite commands from

rotational controllers one and

two for roll and yaw. One

Controller also commands

minus pitch.

DROGUE DEPLOY switch

(MDC-5)

MAIN DE PLOY switch

(MDC-5)

None

Command pilots translation

control (left arm rest) for

LES abort and C/M-S/M

SEP switches I and Z if

translation control does

not work.

Mission

SEQUEN TIA L- SY5 TEMS

Basic Date 12 Nov 1966 Change Date Page 2.9,1Y ....

FunctionandPyre Device

b. C/M-RCSpres-surizing valves

c. Circuit interr.upters

d. C/M*S/M umbilical

guillotine

e. LE and Pc motors

i_niter cartridges

LE tower (TWR) jettison

a. TWR to C/M attach-

ing nuts •(explo sire)

h.- TWR jettison motor

igniter cartridges

1)ostlanding antenna

deploy

SMZA-03-SC01?-


SYSTEMS DATA

Normal Actuating

Control Backup Control


MESC or manual control

from ABORT SYSTEM -

NIODE switches i and Z

ABORT SYSTEM - MODE

switches 1 and 2 (MDC-16)

Manual actuation of

POS TLANDING -

DEPI,OY switches 1

and Z (MDC-25)

i_L

1:t

il

Z.9.3.1. I

2._.3.1.2

_,Itss_on-

_Master Events Sequence Controllers (MESC).

The MESC (figure 2.9-6) provides the logic and _iming to initiate and

terrninate events associated with the ascent and abort modes. Controller

A is in system A and eofitroller B is in system B of the r.edundant sg, st_ n_s.

Crossover circuitry between controllers A and B ensures correct outpuL_

for. detonating pyrotechnic devices even if one redundant circuit is lnupera-

live. The logic circuitry is armed .with the two MESC-LOGIC ARM

switches. 1 and Z on MDC-25. The pyre circuitry is arn_cd with th,, tw,..,

MASTER EVENT SEQ CeNT-PYRe ARM switches I and 2 on MDC-Z4.

Backup controls are provided for most of the events controlled by the

MESC.

Earth Landing System Controllers (ELSC).

The ELSC (figure 2.9.-7) provide automatic and manual control of

drogue parachute deployment, drogue p,_rachute release, and pilot par;_-

chute deployment. Two redundant controllers _rc provided for du.t[

redundancy. Relays are energized in the ELSC and a pyre continuity

verification box (PCVB) to control pyrotechnic devices ancLpe rfornx ti_,

_vents. The _'CVB provides an access for checkout of pyro circuitry,

and conb_lns relays that work in _onjunction with the EI,SC. Tht. El.So

contains bare switches that inhibit automatic operation of the ELS ab,,,vt.

r ........

SEQUEN TIAI. SYSTEMS

Basic Date !Z Nov 196t_ Chantze Date -.- Page .....

SM2A-03-SC012

APOL ?,O OPERATIONS HANDBOOK i

I i SYSTEMS DATA - . I

I

I. the bar0 switch setting. Other events a re controlled by time-delay rela! after the bar0 switches close. Refer to functional description of the ELS.

2.9. 3. 1. 3 Command Module P,eaction Control System 'Controllers (C/ M RCSC).

The C/ M RCSC (figure 2.9-8) provide automatic and manual control

I' of events that occur in the reaction control system. Two redundant controllers a r e provided for dual redundancy. During a n abort initiated

I % prior to 61 seconds after lift-off, the C/M RCS oxidizer and helium a r e 1 ! automatically dumped. When the abort signal i s received, the following pyro valves a r e fired by initiators to pressur ize and dump the RCS i- oxidizer :

1 j I 1

a. Two helium isolation valves b. . Helium interconnect valve I c . Oxidizer interconnec t valve d. Two oxidizer overboard dump valves

i

1 - The oxidizer overboard dump valvee route the oxidizer to a blow-out plug in the aft heat shield of the C/M. P r e s s u r e buildup shears a pin which

h - releases the blowout plug and dumps the oxidizer overboard. 1 I The helium pressure is dumped into the aft compartment 18 seconds

after abort initiation when the following pyro valves a r e fired by initiators:

a . . Helium interconnect valve b. Two oxiditer tanks bypass valves c. Helium overboard dump valve . I The three entry batterieB a r e automatically connected to d-c main

f buses A and B during an LES abort o r normal C/M-S/M separation, RCS I

i controI i s transferred (S/M to C/M). (See figure 2. 9-9 fo r RCS control I

schematic. ) The controllers inhibit automatic oxidizer dump, helium I dump, and LES pitch control motor firing ailtorriatically a t 61 seconds after lift-off. RCS propellant burn.and purge rnus t be manually selected.

'The pyro buses are armed when the MASTER EVENT SEQ CONT - PYRO ARM switches 1 and 2 a r e set to the PYRO ARM position. Backup controls a r e provided for most of the functions p ~ r f o r m e d by the RCSC.

1. 9. 3 . 1. 4 Service Module Jettison Controll.st-s (SMJC).

The SMJC (figure 2. 9-10) program the operation to impart a dcsircd motion to the service module after C/M-S/M separation. The S/M reaction control system will be controlled by.the SMJC and command - continuous firing of the -X jets. It i s possible that the resultant -X

I thrusticg will be offset from the S I M X-axis; therefore, the S / M RCS a roll jets a r e activated for a 5.5-second interval, 2 seconds after

separation. This ensures that a majot componeht of the jettison thrusting wil l be in a direction that was parallel to the CSM (-?() axis a t - . . " -. . . ..,".." . . ., . . . . - .. -. .

S E Q L ~ ~ N T I A L SYSTEMS

Bflssion - . B a s i c Date 12-,xo?' ! 9 6 b , ~ h a n ~ l Date P a 2.9-23

. . - . . - - - ... -.

i

S.M2A-03-SC012

APOLLO oPERATIONS tIANDBOOK

2. ,l. 3. 1.'_

2.,I. 3. l.t_

2.,1. _._'.

_YSTEMS DATA

,_ta\,er.mce. Tile du&l controller_ are powered b v droll ,ep_lrati,m

batteries located in tile S/IM. The battetqc_ art, not rectlartac,lblc

during tile fni,_$ion.

C/M-S/M 8cpa ration Mrchani,_ln.

['hc C:'M-$/M separation nlech,lni_In (figure 2, '+-It) col+,_ists of

el('¢tl:ica[ circuit inter:ruptrr+, shear ctltnl3P(,ssion pad,4, lcn_iot't tics.

linear-shapcd charges, aud,l dual_blad6 guillotine (umbilical sever.thee

device), l'_edtu'_dartt sy_tenxs (A and 13) irt tile _NII::SC provide dual ,'cdun-

dant connalands to fire du,ll initi,ltor_ and cltarges to t,tlsttl't_' sttddt-tl

complete tension and umbilica 1 scve ra,c,c with ,id(,qu,ltc reliability.

Drier to unxbilic,lL severance. ,ensitix'e circuits in the' umbilical ,ire

doadf,lced by circuit intcrrupturs. 'l'ke _lxear ¢on/prcs_iou p_3ds arc

dt'sig|le(I for itltc,rtcrellco_t'rOe sepat'atiotx after tilt, tension ttcs ,IFc

se\'crcd, A :_0paration signal is scnt to dual redundant service i_,odulc

jettison controll.crs which control tile S/M after it separ,lte8 from theC "M.

Spalteci',lft I.F:M Adapter (Sl-,\) S(,p,lr,ltlon Xtechanisln,

A comtx_and for CSM-SI.A separatior,.is ,lutor_latically _cnt to the

Mf,:Su" when ,i SPS ,Ibort is ll_anu,tlly initiatcd. An -\DAt'T 81']1' switch

Ol_ iXll)C-5 llllty be lised a8 ;l b,ltkup ;llld for nornl,iL C_;,Xt-SI.:\ sepalration

dl.lrill,K ,I IIOl'il'U,l.l llli88iOll. Sep,_l l.'_.l[_iOll of the adapter intt_ four p,lncls

(tigllrt.' 2. '1-12) i:_ accot'nptisllcd by an explo_ive tf'ain. The cxplosisc

re,tin consis(s of 28 dlargc )loldct_s. 2 initiators and shirld,_. S p,lncl

tl'trtlsters, ,R initiator prcs,_urc cartridgr_, ,tlld ,ill unlbilical scp.,,r.llion

8Vstol'tl. [{t'dlllld,llll. dcton, tto:' ,I,_,_el/Ibiie:_ fii'c dU,t[ llllC, _I O[ la/ilti dcto-

ll0tiillt,_ tusc (,Xll)I") insl,liled l_etweeu tilt, ad,lptcr panels, top.,trial hottoux.

.Itad bctwocll e,lcll p,trtcl, . Either line will sere," the ._plicc pl,ltcs l_ctwct,n

tile. tour pllllt'ls ;.tlld ;ll'ol, lnd both t, lldg. t.*Po88OVel ° boo,_ter._ are uscd hi

tile chat'go holder .ioint_ to ensue0 that both lines are. tirlflg SillXtl[t,ll/t'-

ou,_ly for ¢olllpictc rcli,lbility. Tl_e dt, ton,lting lines arc cordilxuotl,,_ Ic.ld

._ht',tlh_ _ul-roundtng ,ill oxplo,_iw' ¢orc ,,vlucll is ,,irgtn lit'IX, cl,l.,,_ tl,

rile Iniid defoliating ruse separate._ tilt' ,id,ipter p, ltlci.s ,_nd lirc_ c,lr-

tl'idges for tilt', p,lllt°l thrusters v,'htth open the totlr p.lncls. ,%illXttit.ltlco

ousi V wit}l this oporilt.ion, ulnbilt¢,ll disconllott taM', pl,tte. I"out"

spring-logldcd rcels }told the panels in .t .l_,-dcgrec opcn position. Ihr

p.lnels are stopped ill tile opi'n position IW eight ,Ittcllu,ttor_ that h.lvc

hell I,' y't" Ollll} CO I't'_.

l';tner_,,nc_" lSetection ,"iv,,,totn.

Thr I-:DS constst, of _ensors. lol_ic cirrtntry and stgltal condi-

tioner:, located in tilt, Iatnich velndo, di_t)lay_ .lltd controls totaled Ill

tilt, C/M. and t_-ball which-is located oil tile lorw,ird tip el tilt, 1,I,;S toxver

above tilt, canard. Tile dit_plavs arid cotttl-Ols ¢olisi:_t of t./X' rate.-i. |.7 _,'

guidance, ahort, anti t, ftgineti IiRhttt. along wltil an at_glr-ut-att.lck

hE_UI',NTIAI. ',_Y._ l'l'2,XIS

.tlt.ttt Date 12 Nov l'lt,t, t'hahRe Date ..... i'i,.,. -4-u'211 _,

i

\

t

lI

t .

t!

SMZA-03-SC0 IZ


SYSTEMS DATA

SPS ABORT

INPUT

G&N, !ICS ANDROTATION

CONTROL INPUTS(ENABLED)

(MDC-16)

ADAPTERSEP

IL

Fr_n : DC

MAIN BUS A

Fr_ : DC MAIN

BUS A

From: IX: MAIN

BUS B.

LES ABORT OR

C/M-S/MSEPARATIO N INPUT ,CMD

ON

AUTO

DIRECTRCS

$CS-RCS CONTROL FUNCTIONAL BLOCK DIAGRAM

S/M RCSULLAGE

PITCH ANDYAW INHIBIT

I

• I

• _r, _"1011 iI , , ! _ [ II ROTATION CONTROL I (MDC-B) t i

I No. i (o_RECTMANUAL_I CONTROL oF RCS _ "

I lJ /I"OTAT'ONCONtROLI I

NO. 2 (DIRECT MANUALL_ j=7 CONTROL OF RCS !_

1 ENGINES) -. _

I I

S/M RCS ]

AUTOMATIC COILS

C/M RCSAUTOMATIC COILS

S/M RCS I

DIRECT COILS

C/M RCSDIR_:CT COILS

SM-,_k-93G

Figure Z. 9-9. SCS-RCS Functional Bluck Diagram _

Mis s;.on ...

SEQUENTIAL SYSTEMS

,Basic Date IZ Nov 1766 Change Da_e Page 2.9-27

$I,,t2 A-0._-SC0 1a

APO IA.O OPERATIONS HANDBOOI¢,

SYST I£'MS DAI'A

I;'tgttre 2. ti. lO. _ervlct" Nl_du|t, Jt, ttt,_ola Ctmtt*ollct 8('|lt'll_itttc

4tt

tat

I

I

I8_;tdl*l']N I L.\I. SYSI'I'7.MS

I

1

SMZA-03-SC01Z

APOLLO OPERATIONS HANDBOOt_

SYSTEMS DATA

tl

tl

-+

I

l

II

•__ _, 45*

I I , L \

+_ PISTON I "

NEGATOR SPRING REEL

ATTEI'qUATOR (4 PLACES)(0 PLACES)

SM-2A-895A

MLss_on

Figure 2.9-12. _Adapter Separation htechanism

+,

SEQUENTIAL SYSTEMS

• Basic Da.te lZ Nov 1966 _Change D_,t.e_, Page 2.9._31 ,

-f - ~ - - " - ~ . .

,* - \ . . I . ,

, .. S ~ 2 2 ~ - 0 3 - ~ ~ 0 1 L


SYSTEMS D A l A

indicator and control switches. The L / V portion oi thc EDS and the Q-bal l a r e po\vered by eight L!V ba t te r ies . Tllc displays a r c po\vt.red by t\vo entry bat tkr ies A and n.

2. '3. 3. 3 Launch Escape Systt.hl.

~ t l e 1,ES collsists o f two lilsjor ;~ssc l l~bl ic*s ( f i g u r ~ 2. 9 - 3 ) that L I~C ' . ins tnllcd on top o i thc co~llnland ~ u o d u l c p r i o r to laluich. , Tht. ii iest s t ructur i . is a ioilr-li.ljgi.ci, \vclded tubiilar t i t au i~un tower. Tllc tower i s i1ttachc.d t,o tlrc conlnland ~ilodiilt; \\tit11 fottr iralrpiblc nuts on stttds. Two de t .ona tor .asscn~bl ics a r c i t~ s tn l l cd in bac11 ntit to b r ~ a k it \vllrl~ 1,ES to\ver jcttison i s conlmanded. The second s t ruc tur c i s cylindric3 in shnpc topped by the Q-bal l , and hous r s the laiincl~ c s c a p r , tower jc t t i - son, . and pitch.contro1 niotors . A canard subs ) r s t rn~ is installt*d tic.ar.tl~c, lo rward end bclo\v the Q-bit 11.

2 . l?. 3. 3. 1 I,ES hlotors .

Each oi thc tl lrcc tllotors in t11c IAES ( t igurc 2. 9 -2 ) a r c i i rcd by t a o igtritrr n s s c ~ l l b l i ~ ~ s . . Tlrc tllrcc lrlk~tors a r c the 1.1unt.h t.scnpc mo to r , to\v~.r jc-ttiso11 lotor or, a l ~ d pitch cont ro l nlator . Tllc p~tclr co r~ t ro l t:lotor \ ~ o r I i s in cvnjl;uctio~l with the launch escnpc ~ l l u t o r ditrirlg a LES abort initiated p r io r to 61 sccollds attt.1. l ift-vif. T l ~ c pi:.c.l~ control l~ lo to r 11~1s ;I

i isvd zc ro-tlcpccc, s i ~ l g l e - ~ x \ ~ a u s t ~ ~ o z z l c and i s t1~0~11ltcc1 bclo\v thc hal las t ctlclositrc in a horizontal position. Thc nlotur prodircc-s approsirl~.rtt~Iy 2 6 0 0 pcr~tnds o i t h r i ~ s t for about 11. 5 sccond to t'orcc, the, n a s r ot' t!re I..k:S t~)wc.r in tllc -Z,.di r r c t i o ~ l . F i r ing of thc pitctr C L I I I ~ rol 111otot. i$ inlr il>ill*d 61 st.conds aitc-r l ift-oii by a s ignal Iran1 thc C /1\1 KCSC. Tlrc I . I I I I I C ~ L - S C ~ I ~ X ! nlotor 11.x~ i o t ~ r 11ozk1t.s thLtt l ~ a v c a c c ~ t t r r l i l ~ c cant ,111pl1~ i ~ t

35 dCgrcc*s. 1 ' 1 1 ~ rfislllt,ig~~ thritst \ . ~ c t o r ' d r i l + c L i o ~ ~ i s obt.li:lc>ci b y o*'lsi::il~s the noz;!lc throat d iamctcru and producitig a t h rus t vcctol. t r l tht. - / d1r1.c- tion. Thrus t output i s appros imntc ly 150,000 pourids which s t a r t s dropping i l l approsiftlately 1 s rcnnds . La t c fn l t rans la t ion oi thc ilsc:.~pc \ , l ,hiilc i s aidcd by thc th rus t vcc tnr alignnlctlt oifsct du!- in^ an 1,ES abort . The. tower j r t t ison nlotor has two nozz les in wi~icll t l ~ c th rus t a.vcctc.r a l ~ g n n ~ ~ . n t is oit'sr:t nppros~rxlatoly 4 dcg rces to producix a t l t r ~ s t c ~ n ~ p o t l c r r t i n 111:

ti' d i r c c t i ~ n , 'l 'hrust output is approsin.atCl*: 33, 009 poi~nd.i.

Tlrc cana rd subs)-stcrr? (tiy;trc 2 . 9 - 3 ) cons is ts oi two tlcp1oy;tblu s ~ r r f a z c s I,rirzd into tlre oiitcr skin of the LES bclo\v the Q-bill1 intcrf,\cc%. E-ic!~ si1rfal.t. 1s mouutcd on tbvo hitlycs and i s opcra tcd open by .I pyro- tccllntc t t~ r i i s t e r \ n t h redundant g a s i.;irtl:idjit.s. Thr s l i r iaccs a r c * p i > r o s i r ~ ~ ~ t c l y 4 7 inchcs long, c lam-sl lc l l shaped, drlcl cons t r~ ic t r t l . a f doiiblr -skin ribbed ~t iconel . Thc c a n a r d s u r f , ~ c c s .irtb ,~\rtor~r,tt~c.;l l l \ . opcnerl during a LES abort and aerodynntnic io rzcs act ing o n tile s r t r - i a ~ v s control a tirrnarou~ici t~lanci ivcr o t the C!Xl. (Reicr to t\l)ort P r o ~ . c d ~ t r c s in s e c t ~ t ~ n '?. )

. . , u . - . .. . - SEQU ENI'IAL SYSTEXIS

. P ':,.. . . . . . -

SMZA-03-SC012

APOLLO' OPERATIONS HANDBOOK

SYSTEMS DATA

2 . 9 . 3. 4 Ear th Landing Subsystem.

The ELS consists of the parachute subsystcm (iigure 2 . 9 - 4 ) , two ea r th landing sequence coi~t ro l lc r s (figure 1. 9-7) , and t t ~ c apex covcr jettison mechanism.

Thc parachute subsys tem i s comprised of two fist-ribbon-type nylon drogue parachutes, 13.7 feet in d iameter ; t h ree ring-slot-type nylon pilot parachutes, 7.2 feet in d iameter ; three ring- sail-type nylon main parachutes, 83 . 5 feet in d iameter ; deploymcnt bags; br id les ; sus - pension l ines; m o r t a r s ; and the necessa ry hardlvarc for attachment to the CJM. The Parachute subsysti.m is housed in the forward compar t - . mcnt under the apex cover of the C/M. .

The ear th landing sequence cont ro l le rs a r e locatcd in the. right equipment.bay o!' the C / M and controls automatic operation of the ELS, Crossover c i rcu i t ry between the cont ro l le rs ensu res c o r r e c t output signals. Backup emergency, switchi.s a re . provided on MDC- 5 fov-apex cover jettison and parachute deployment. The apex covcr . i s jettisoned by four gas-operated thrus ters . Two gas-type ca r t r idges a r c employed for redundancy and opera te two th rus t e r s cach. Either pair .of t h r u s t e r s will jettison the apex cover. A pilot parachute and m o r t a r a r e installed. in the iorwPasd end of the a p e s covct , Thc nlortal* i s fircd a t exactly. the saille time a s the apcx covcr t h rus t e r s to.deploy thc.parac11utc.. T h t parachute \\,ill pull the apcx cower fro111 thc negative prcss t i rc a r ea followil~g tllc C/M. -

PERFORhIANCE AND DESIGN DATA.

Entry descent veloci t ies , altitude, and t i r .e a r e contained in thc following tabulated data. The f igures a r e based on a command module recovery tifright of 1-l., 000 pounds and a standard day ba romet r i c prcssurc'.

The tabulated data s ta tes the a u t ~ n ~ a t i c cvcnts that nornlally occur- in the ELS dui-ing descent. . Under cer ta in cntry conditions, the apcx covcr may be manually jettisoned, and.thc drogue parachutes manually deployed at 45, 000 fobt. Rcfcr to ophrational linlitations aild rcstr ict ions that follow thc tabulated data.

A , . . . . . . . . .......... - . .

SFQUENTIAI . S Y S T C ~ I S

h l i c DitC No3 i9b6 Chankc DBtc

7 .. ..>- ..... - .

' i

SM2A-03-SC01Z


Oc¢ll r l'ence

TWO DROGUE PARACHUTES

24, 0t0 .'vet baro switch cJ0ses

Ape. cover jettison

Drogue paraehut0s (2) deploy

10,000 feet bato switch

closes

Drogue parachutes (2) release

aud main parachutes deploy

Main pa.rachutes open (reefed)

a fte r two d rog.ue p:a ra chute s

release

MMu parachutes disreef

ONE DROGU E PARACIIU TE

Drogue parachute (1)releasOs

alad main chutOs deploy

Main parachutes open

(rected) after one drogue

parach',,te releases

,Main parachutes disreOf

I'ouchdown (3 main

p,i rll _."h/lit, s,

t',mchdown (2 tuain

parachutc.*)-

SYS TEMS DA'._A

Time on

Altitude Parachutes

24,900 tO 21, 500 feel

24, tOO feet baro

switch closure + 0.4:

._0condS

24,000 feet baro

switch closure +2.0

seconds

10,950 to 9, 10t feet

it, 000 feet baro

switch closure

84t0 ±Stt feet

10,000 feet baro

switch clOSttrd

8-'.00 :_500 feet

45 to 46 seconds

8 seconds after

line. stretch

40 seconds

8 seconds after

lihe stretch

5 -nlinu t e s

4. 2 llliuutc s

SEQI'I?:N TIAI_ SYSTFMS

Ba_it- Date 12 No,v 19bts, Chang6 Date

Descent

Velocity

425 ff/st.c

410 ft/sec

225 ft/sec

235 ft/sec

1 I0 ft/sec

275 it/see

2n0 ftlsec

ll0 ft/sec

28 ft/sec

33.5 ft/sec

I

l:!

i, I

Mission ........ ,:, Page .fi.,9.-.3:t, ...... , , '

SIVI2A-03-SC012


.

f

.

i

I-

2.9.4.1

2.9.5

SYSTEMS DATA

J

Power Requirements.

The SECS requires power only during the launch and ascent phase, for

CSM-SLA separation in orbit, for C/M-S/M separation during the pre-entry

phase, and during the parachute descent phase. Most all events performed

by the SECS occur instantaneously, and not on a continuous duty cycle. In

accordance with the Mission Modular Data Book (SID 66-I177), dated

1 S_ptember 1966, there are no power requirements for the SECS.

OPERATIONAI_ LIMITATIONS AND RESTRICTIONS.

Under certain entry conditions, the spacecraft may bec6me unstable.

Because of the erratic aerodynamic damping coefficients, wind gusts, and

shears, the astron_.ut may not be able to damp the oscillations with single

RCS, If this should occur, the apex cover and drogue parachutes may be

manually deployed at 45,000 f_et. This will stabilize and keep the C/M in

a heat shield forward descending attitude. Figure 2.9-13 portrays thedrogue development design envelope. The following precautions should beobse fred,

• Manual initiation of apex cover jettison and drogue parachut_

deployment should never be accomplished above 45,000 feet

during entry.

• The C/M RCS must be turned off prior to apex cover jettison.

• The LES tower and apex cover should never be manually jettisoned

above the automatic mode of g_ 000 feet during LES aborts.

5O

l\\r \\,_o t. \ \. \

\\,\\I \

30

=..¢

20

10 _ ....

o 0.1 0,2 0.3

umt_bl*.

0.4 0.5 0.6 0,7 0,8

MACH NUMBER

ENTRY ENVELOPE1

bemanvQlly_epl_l ot45,000 foot cluHngontryif the C./'M i_come_

Figure 2. a-13. Drogue Parachuto Deployment Design Envelope

0.9

SM_2A-896

i • i - , i i

SEQUENTIAL SYSTEMS

Missiofl Basic DatelZ Nov 1966 Chaflge Date_ Page 2.9-35

s l \ r 2 A - o 3 - s ~ o l z


SYSTEMS DATA

2 , 0.6 TELEMETRY MEASUREMENTS.

The following i s a conlplete l i s t of a l l sequential sys te lns t c l c ~ n c t r y data that i s nlonitored by flight cont ro l le rs and ground support personnel . The l a s t colu111n contains the name and type of S / C c r ew display. Thc display ut i l izes thd sanle pickoff o r s ignal s o u r c e s a s t e l c l l ~ e t r y , dn l c s s a s epa ra t e measurel i lent nulnber i s included in the display column.

hf iss ian . Basic D,ltc 1: NO!. !?"-. chatigr Date paS,? .. 2 , '!- 36..

An a s t e r i s k ( 6 ) by the mttadurement number denotes i n fo rn~a t ion \vhicIl i s not available fop recording o r t$l$metry t r ansmis s ion dur.ing PChd lo\!'

X.lcasurement Nunlbc r

C13 0136 X

CD 0140 X

C D 0141 S

CD 0170 X

CD 0171 X

CD 0173 X

CD 017.4 X .

:I;CD 0200 V

:::CD 0201 V

CD 0230 X

C D 0231 X

CD 0315 X

CD 0316 X .

CI) 1006 X

CI) 1007 S

C E 0001 X

CE'"OOO2 X

CE (1005 X

bit r a t e ope ration. .....

ScnSor Crew Descript ion Range Display

EDS abor t logic ou t B Evcnt Nonc

Direc t ullage, on A Event Nonc

. . . . . . . . . . . . . . . . . Direc t ullage 011 3 E\.cnt i\'onc

RCS act ivate s ignal A Evcnt Sonc

RCS act ivatc s ignal B E\.c nt Nonv

CAM-RCS p r e s s u r i z e s ignal A Evant Konc

CMIRCS pressurize signal B Evcnt Konc

DC voltage logic bus A t0.4-37 vdc Konc . -

DC voltage logic bus B +0/.+3? vdc None .

Forward heat shield jettisol1 -4 E\-c nt Konc

Fo rward heat shield je t t ison R Event K\'anc

EDS cnablc A Evc nt Nonc

EDS cnablc B Exc nr K\'onc

LES tnotor f i rc . initintc A Event Non~,

LES mo to r f i r e initiate B Evcnt N o n ~

Drogue d tp loy re lay close A Ev~.n t Nonc

Drogue deploy re lay c losc I3 Evcnt None

Main parachutt* deploy-droguc r v l ~ * a s e relay A Evcnt None . . . . . .

SEQUENTIAL SYSTEMS

SMZA-03-SC012


SYSTEMS D A T A !

I - Sensor Crew I .Measurement Range Display I Number Description i.

I CE 0004 X I Main parachute deploy-drogue r e l ease re lay B Event I None 1 I

Baroswitch lock-in re lay close A

Baroswitch lock-in re lay c lose B

B a r o n ~ e t r i t p re s su re s tat ic re ference

Main chute disconnect relay A . . . -. ... ... - .. ... , .

Main. chute disconnect re lay B .

Q-ball vector sum output

Launch vchicle guidance fail A

Launch vchicle ra te excessive A

Engine No. 1 out A

Engine No. 2 out A

Engine KO. 3 out A

Engine No. 4 out A

Enginc No.. 5 out A

Enginc No. 6 out A

Engine KO. 7 out A

Enginc KO. 8 out A

Lift-off signal B

Event

Event

-Colt15 psia

Evetit

Event

+0/+.5 vdc

Event

Zvent

Evcnt

Event

Event

Event

,I Event

i Evcnt

Evcnt

- -

SEQUENTIAL SYSTEhlS

None

None

Indicator

None

None .

f n d i c a ~ o r

L/ V .GUID light

L / V RATE l ight

ENGINES 1 light

ENGINES e .- light

ENGINES 3 l i gh t

ENGINES 4 light

light

ENGIKES 7 light

ENGINES 8 light

LIE'S O F F light

hIission Basic Date 12 NOV 1966- Change Date Page 2-9-37

SMZA-63-SC0 12

+POLLO OPERATIONS HANDBOOK.

5 y S 7 ' " . . . .* US 1IP.TA

Measura 1 , . . Sensor Crew u ' Descriptiot; Rznpe Display , - - r . . .%- .-. CS t i $ * ~ - . e i ; FL7S abort request A Event APORT

I light

' ' . ' 1 1 .% Tower physical separation monitor A Evcnt Node

1 . .i Tower physical separation inonitor i3 Event None

( . Y CM-Slvi physical separation m a i t o r A Event - None

! i CI\I*SA,l physical separation nlonitor B - ----- Event None .

2 X Shlladaptcr physical scparati.oh monitor A Event None

,. . . 1 . ' X Shlladaptcr physical separation manitor B Event r None

SEQUENTIAL SYSTEhlS

' , ' isston R a s i c Datc 1966 ,C:hange Date page -2 -9-38

1.10.1

.'.10.2

2.10.3

SM2A-03-SC012

APOLLO OPERATIONS I-IANDBO(bK

qYSTEMS DATA

SECTION 2

SUBSECTION Z. I0

CAUTION AN0 WARNING sYSTI_M (C&WS)

INTRODUCTION.

The C&WS monitors cr{tical parameters of most S/C system._ in th6

C/M and S/M, When a malfunction or out-oi-toleranc0 condition occurs in

any of these syst6ms, the crew is immediately alerted in order that cor-

r6ctive action may be taken, ,

FUNCTIONAL DESCRIPTION.

Upon receipt of tnalfunction or out-of-tolerance signals, the C&WS

Simultaneously identifies the abnormal condition and alerts the crew to its

existence. Each signal will activat _ an appropriate systems status indica-tor and a master alarm circuit. The master alarm circuit visually and

aurally attracts the crew's attention by alarm indicators oh the MDC and analarm tone in the headsets. Crew acknowledgement elan abnormal condition

consists of resetting the master alarm circuit, but retaining tl_e particular

systems status malfunction indication. The capability exists for the crew to

select scvcralmodes of observing systems status and master alarm indi-

cators, and of monitoring C/M. or S/M systems.

MAJOR COMPONENT/SUBSYSTEM DESCRIPTION.

The C&WS consists of one major .component, the detection unit. It is

located behindMDC-13 and, therefore, is neither visible nor accessible to

the crew during the mission. The balance of the system is made up of

visual indicators, aural alerting and associated clrcuits, and those switches

required to control the Various Systbtu functions. Visual indicators includethe five uppcr-most electromechanical event devices on MDC-18, as well

as all systc:ns status and mast0r alarm lights.

ThO detection unit circuits consist of comparators, logic, level

detectors, lamp driver_, and a master alarm and tone generator. Also

incorporated are two redundant power supplies that furnish regulated +12

and -12 d-c voltages for the electronics. Inputs to the d_tection unit con-

sist of both analog and event.type signals.

The analog signals, totaling 51 inputs, are in the 0- to 5-volt d-c

range. Alarm limits for these signals trigger voltage comparators, which,

in turn, activate logic and lamp-driver circuits. This causes activation ofthe master alarm circuit and tone gen_rato_, illumination of applicatiou

systems status lights on MDC-10 and -i1, and/or activation of applicableclectromechanical event indicators on MDC-18. A total of 25 event inputs

arc fed to the C&WS detection unit. These signals originat_ from solid

state and mechanical switch closures in malfunction sensing devices. Of

this number, 19 signals will directly illuminate applicable system status

lights, and through logic circuitry, activate the master alarm circuit (and

tone generator). Two other event signal_ directly illuminat0 _he system

_Itsslon ', ,

CAUTION AND WARNING SYSTEM

Basic. Date 12 Nov 1966 Chang 0 Date ..... PaRe 2, I0-I

.... qlb .. " '

SM2A-0 3-$C012


SYSTEMS DATA..... i i 11 hall i

,_tatus light,_, but r¢_quirc level detect¢_r,_ to _ctivate the _:_a,qter alarm cir-cuit. l_ach of the four remaining evm:t _ignals to set to an OR gate, which

i,,, also f0d by two analog sig1_als. The resulting output will activate lamp

dri_er-q and the master alarm circuit. OIxe other event signal, orxginating

within the det('ction unit directly, iklumihates the CAUT/W:\RN FAIL Light,

out a_ztLvates only the MASTER ALARM lights o_ the MASI_ER ALARMcircuit.

The mastel" alarm, circuit alOrts c rowmembers whe,_eVer abnormal

conditions are d_tbcted. This is accomplished visually by the illuminatiol_

of remote MASTI_R ALARM switch-Lights on MDC-3 and -18, and the

.MASTERAL:\RM light on LEBoI03. An attdio, alarm ton0, gent to the three

h_,adset_, aurally alertg the crew, regardless of whether the telecom syst0m

is activated. The otttput signttl of the tone genOrator is a sqttare wa_,'0 thatis altei'natel.v 750 cps and ?000 cps, chaugii_g at a irequi_ncyof 2.5 cps,

Although tile tone is attdible above the cotlversation level, it does not render

normal conversation indistinct or garbled, When the crew htXs noted the,tbuormal conditioil, the tl_ree alarm lights and the. tone g0neratot are

deactivated and react by pr0ssing either NIASTI(R ALARM switch-light, both

or' wllich iacorporate a puah-switch. This action leaves tl_6 systems status

lights illuminated, and resets the master alarm circuit _or alerting the crewto the next abnormal condition, "i'he indivxdual systmh status lights will

remain illuminated until the malfunction or out-o/-tok, rance Condition is

corrected.

t'he C&WS power suppl:_s inchtde ._ensing and switching circuitry that

assure unit. serf-pr0tection should high-input current, or high° or low-

output voltage ocmtr. Any of these conditions will cau:_e the illumination of

tiw master alarm lights and the CAUT-WARN FAIL systems status light,

The tone generator, however, will not be activate4 due to requiring the

12-volt. output from the mathtnctioned power supply for its operatiot'_. The

c_;ew must then manually select tht_ redundant power supply to return the

C&\VS to operation. In so doing, the CAUT./WARN FAil status light is

extinguished, but_Uhe_master alarm circuit is &ctivated,. thus requiring it tobe _eset_

Incorporated ii_to the C&WS is th{' capability to test the lah_l_sof sys-

tems _tatus and master alarm lights, Position I of the LAMP TEST switch

(M 1)C-23) cent rois the ilhtn_ination of s"_tus lights on MDC- 10 and the

M:XSTI':tLAI_;kR.M ._witch-lights on _ID_ .3 and MDC-IS, Position 2 tests

only the status lights on. MDC-ll. The remaining MASTER ALARM light

is on IA".I3-103, and is t0sted ,._long with tl_e nine G&N condition lights on ,tixat panel by pressii_g tile CHECK CONDITION LAMPS push-switch on

LE_B-I,05. Although those nine [ight_ a#_' not part of the G&WS, all but threeof thenl (PGNS, ZERO ENCODER, and IXIU DISPLAY) are dtmticated on.MDC- 10.

.Switches on the MDC enable the crew to select C&WS operationalllIodes. '['he position of tile MODE switch (MDC-I 1) establishes the SIC

systems to be monitored. Before separation and entry, systems in both theC 'M and S/.X[ are fnonitored _or rltalt'tanCtion Or out-of-tolerafice conditions.

After C.%,Xl st, p.tration, however, only those systems in tile C/M ate moni-.

toted. Repositioning tile switch also prevents SIM systems statu._ ligl_ts,tlld eVellt indicators from remaining activated after separation.

I'he C!W switch (MDC-13} permits thre_" modes of status and alarm

light i[lUllitn,itlon. For motet of tt_e mislion the _witch is ._et to tile

NORM,\I. p,_sition to girt' hernial C&WS light operation; that is, upon receiptOf atmortnal co::dition stgnai._, all systen_ statt,._ Lights _tnd ma_ter alarxh

t

I

.i

SM2A-0_-SC012

A P0 LL00P_IRATIONS HANDBOOK

• 10. _. 1

2. 10..t _

' 10,4 I

10 ",

' 10. "_ 1

SYST I_MS DATA

i i i

lights are capable of illumination. During th,_ ascent phase the switch il a¢,t

to the BOOST position, so that although all other C&WS lights operate nor-

really, the MASTt:'R AI,ARM switch-light on MDC-] will not illuminate.

This prevents possible confusion on MDC-] between the red MASTIqR

AI,ARM light and the adjacent red ABORT light. The ACK switch petition

is selected when the crew dolirel to adapt their eyes to orbital darkness, or

if a contimtously illuminated sy,tems stratus light is undesirable. While in

this mode. incomin_ signals will activate only the master alarm light_ and

the tone generator. TO detortuine the abnormal condition, the crew must

pr6** either MASTI_;R Ai,ARM _witch-l{ght. This illuminates the applicable

sv_tetus ,tatu, light, and deactivates and rE, aet_ the mhster alarm circuit.

T'be i$.,tem* _tatu_ llght will rein&in tlhtmhthted only a* long a, tbb _vitch-

Hght ii pr6_,ed, l lbwever, it t_ay b0 r_call('d a_ lofig as th/_ abno_ _m,_l

rendition exiitt by ag_tif_ pretiing either Switch-light;

Electrical Power Dt,trtbution.

The C&WS only _.6c6tves pow('r from 18-volt d-c _out'ce_. (See

figttre l, 10-|, ) I_(,for0 CSM separation, the pow¢r _oUrce is from th6 ,fuel

celia in thc ,q/M. and following ,eparatl,m. from b.ttteries located tiIthO

CIM.

PI.:R1;'ORMANCI':- AND DI'SIGN DA'i'A.._

C&WS Power Consumption Data.

Total power ¢otxsutued by the C,& X%:S ;u_tXout_ts to 7._ watt,, which i, the

maxhuun_ qtttescent powi:r for d(_t0ction xmit operati0n. Verx Sfuall &tuoum_

o_.power arc aHto requirdd to ilhmtifiate several lafups whenever _ the C&\VS

is activated by malfunction input sigtutl*. Thi'*_' _tuall aiuouuta, however.

are i_ot considered ifi the overall C&WS power t_equiri'tuents.

OP I::l,I AT ION A I, I .iMITATB3N-- q _A_N_D R t,:ST R IL:'F IONS.

t'& WS General lSata.

\Vitl_ _he C/W switch in thi' fXOOST position during ascent, the

MAS'{'f'IR AI,A_'_M thvttch-light on MDC-'_ will not ilhttuiuate should it t_,tl-

function occur. The tXla_te# ahtrtu circuit rt,_i,t capability of the light i_

al*o diaabh, d dul_ingthis tiu'_e,. This requirO_ tht, MASI'I.IR AI.ARM _witch-

light on MDC-18 to he used exclusively for monttof'ifig ahd resetting

functions.

,_cveral peculi,trttte 't,ihOuld be iIoted in re_a rd to t lie t'AUT. W ARN-

I'OWFIR switch. Whetlever this switch tl IBOVed t'rom, or through, the Ot;'["

position to either power ttupply position, the master ,tlaf'ti, circuit iS actt-

v.tted, which then requires it be t'eset. Also. switching froin oite power

supply to another (whetx tl, ete is not power suppl% fallure_ will cause the

cane :\%'ARN FAll statu* light to tlhnninc, te at the OFt" position, and then

be exthlgutJhed when the Other power supply positiolt iS #ea_:hed.

lkitSstoB

CAUI'ION AND WARNING SYS'I'I:IM

..... Ba.tt_ D.tte_ A.' N,,v iq(*t, Chatn_e Date Page

i | .... , ....

2. I0-t

SMZA_03-SC0 IZ

A PO L LO OPERATIONS HANDBOOK

.qYST EMS DATA

DETECTION UNIT

p _ n a_l n Immm m m 1

-- POWERSUPPLY

I -I, ,VDC NO. I

I OFF

CAUT/%NARNPOWER

(MOC=I ! ),11

CAUTAYARNMN A

(MDC-25)

MDC-I8

MASIER

^LARM

_A i

I

(_oo 3)i

I""F-I

IACK

I

I

; ; : ACI_II

r=

rEST /

MOC'2_,;.. !

CSM

CAUT3WARN IMODE

4I Fe-

C,"M

CA U_T_WARN

MN a(MOC-U)

'_i)0A

I

J

, q

To, C/M To. S_M 1o: S/M, To: C:M T& S/MI)ltlnt lyltilm e¥4HIt l_ll_t l_llnt

ltQtlal It_lhA _hQhnell ch_l_ Indl_ltom|m, lm (_'3_ lim_pt(15) (4) fo, (II) hil (_)

ACK modi ACK ,i,_

l%1_sslon $,LIA

_';g_lr_" '. It_-l. C&W._ Power D*_tri._utiou Diagram

i n • -

('AL'I'tON,AND WARNING SYSTEM

._,_t,* I-_.i:,, l_ N,_" 19t_t)mChanle 15ate, pase Z,.IO-4

SM2A-03-SC01 _'


SYSTEMS f)AT :X

Should the redundat_t power supply also {all. the C&WS is degraded to

the, following extOtlt. Rcnder_,d inoperative is t|l,,coml_let/" mast¢,r aIarl_.

circuit, a_ \veil as those 8tatu_ lights that illuminate as the result of at_alog-

t);pe input signals. This leaves olxly those statu_ lights operative that

require ex, ent-type input aignala. Included arc the follo,,ving S/M and ('/M

light,: CDU _AIL. G&N ACCV, L I_AIL, IMU FAIL. G&N F/RROR. I,MU

TEMP, GMBL LOCK, AGAP TI'_MP, SPS ROUGII F:CO, I-t2P ACCU.NI

t_'AIL, PITCtt GMBL DR FAIl.., YAW GMBL I3R FAIl., SPS PU SNSR

F'AII., 02 FLOW itI, F/C BUS DISCONN['_CT, AC 1 BUS FAIL, AC BUS 1

OVERLOAD, AC 2 BUS NAIl., AC BUS 2 OVERLOAD, MN BUS A

UNI_ERVOLT, MN BUS B UNDERVOI.T0 and CAUT_WARN D_:XII..

The CAUT/WARN-MODIC ,witch must be in the CSM po_itiotx it\

order to conduct a lamp teat of tho*c statu_ light_ associated with S; M _.vs-

to.m-_, The atatus.light_ of C/M systems may be teated _'ith the MOISt"

_witch iix either position. Circuit de,igtx also perth\its a complete lamp test

to be co|_ducted with the C/W switch in the ACI.i 1._ositiola. .

Normally, each abnormal cotxditiotx signal will actix'ate the C&\VS

master alarm circuit and tone ge,_erator, and illuminate a_ applicable-s.x's-

toms _tatus light. The ot_e exception to this concept is \vhctxthe C&\VS

power supply fail_. The vi-_ualindicator_ will futxction, but not the totxe

getxe.rator portion of the master.alarm circuit. This is due to the tot_o

gcl_era.tor requiring the _12 at_d -12 d-c voltage output of the failed power

_upply for its operation.

The NtASTER AI.AI/M. iight on I.I:;B-103 is part of the master, alarm::

circuit.of ill _ C&WS. As such, it is illuminated \vhet_e_-et.tl_e master

alarm circuit ia activated by an i_coming, ab_ort_at co_dilio_ signal. _'\

lamp cht, ck of this light, however, it t_ot ;_ccomplished bv the C_.Wb.

It\stead, tht' light is checked b_ pressing tile CtlI::CK CONI_ITION 1.AM}_S

pttsi_-switch ot_ I 1.',l_t-10:_. Tht, prim,_r.x ftlllctiotl _f this _x_ilch is lt_ qlxt'_'t,

the' lamps of the hint' G&N ._'oi_diti_i_ liilht._ otx 1 }';B-10_. llOllt' of %%'hit'h ill't'

part' of t}_,, k'g \VS.

N_,_tt, txx Stat_xs l.tght I'_at,_.

l'ht, toll**wmg li_t proxitlt,_ the, lamp tt'igg_,r x,llm,s am! ,_ss_,_,_tt,tl

lil:,,t'I:'alt_ll :t,l" all :;_:;t,.t_" ::tatti:; 1-g!-'.:_ ,,i1 SII_ " 10 ._i_,.! : 11.

,.\l'lIt'N .\NI) %\.k""...... '"t h x,.%l .;,ki'

.!, 10- , .....

all

SMZA-O3-SC012

A_OLLO OPERATIONS HANDBOOK

8_ SI"EM8 DAYA

Status Lq4kt

CDU PAIl.

IMU FAli.

IXIV "I'T.'MI'

AGAP I'HMP

G&N As,'C PI.

I-'AI 1

GMBI 10CI_

I|, I'i_ 1-'88

C .M RCS A

l.iill_p I riilllt'r \'aluc

I. L_,,_ (-_0'%) 2',, _q_.<" ._upply

_ I.{.IIP.'I {'_0" 'I ll%kItOr t_XC&[.% -

lion

_. ICDU error >1,2 )nr for

¢_ _10con_],l

4. XIi'D(' ,,trot :i I. P' uu" lot

.%cl OllL] S

_, {._CDL' error 3,1. 2 n_r for

I, l.oaa {-_0",4 _'00 ,'pa

2. Lo.._s l.r'O"q 800 cps _h,,_q

po _,' L,r

) _ c ¢ orld._

l, IRIG h,u ,I <1%2" l"

L, Ill, IL; teiup>l_,B"l"

_,. I_IDA I,,t_H}<I12"I +"

4. PIPA ,cuq+_)L3._"l"

l, AIw ILMAt;<lo0"F

2, Any BXIAG>ITI"Ic

l. X t'IPA crror,'_27 nil. for

2. ¥ DIPA error'S2; ntr tot

,'ii'V oI%_I S

I,. ." PIll'\ error'S2." i_u" tot

. _evoi%¢|._ --

lullh _,r low

.'.. U|_ t'1%1 bit rat,, too high

_. I.'_-_likk dAtA Ht ,'l'I'Or

TLXI

Code No,

CGS00LX

C GB001 X

C G_O0t_X

CII20 hi\'

CG_OOOX

C G_i,}0-'_ X

{." G'_ 00 ;+X

sic

Other Indlc_it*on Mode-

PGNS hRht dlutuknaleci C/M

LEB- I03).

I}GNS IiRl_i dluuunated C/M

L_2B- I0 q.

None _" / M

None " C / I%l

PGNS lil_ht llhuum.tted C.' XI

{I. F211- tO I),

DSI,;,Y-TM FAlL

(LEB- 10o) _nd PGN8 -

hRhl_ (LEB-IOI)

iIhtiutnated.

L" ,' ,M

I"DAI ,tttitude ball t'rd C M

Retu_rk_

LtRht enabh.d in ttn(,

ahiln mode only,

hilikblt_-d (b_ ABC

proRrim) in co&r_ ah_n

rhode.

IRIG icsup (13S_I ") tel

title PI%,%I ;tnd I%ot end _:&p

tOll%l) 1

I. l.uxk l•.'..t0 psta

2, lank 1"2;0 psla

t, l'ank 2 • 220 ++sla

4 l.utk d _,' ,'0 p:_ia

I. l'Ucl lk Ih" pr,..,ll ,..'l+._ plitii

2, I u,,l tk Ih" |H+e.s"_t '' tl.'lla

t, t +_. ti, Ih" liro.lll _..h,._ p_l,tl

t ! U,'I tk I1,, llr,,ss %'2(, • ll'liA

I. ! U,'i tk I h" Ill c._,'i ." t _ ' ll,lia

I t'_ tk Ih, l_l_,Pll+/_l, , l_lit_l

_," R000 +_P

t" R0 0 1 I P

;one tlniil_l" tit_tt, • ili_.l_l

Ind t ¢,l|l.] i ,

I'ANK Pltl"8:4tq_P-ll_,- l

H%dt c&?o t"

LANK I_RI_8,_VltE lI_,-tlil¢l I i.' !lto i"

t','M lit'8 PRP+sS- I'

inthcato f

lillt %l'l I_ :

C,M l,lt'_'i PRFSS. F"

kni, hcAto P

• M 1¢{'.i4 Plll.t8S-t)X

in(_ It" 31to f

s M

C. ,XI

(" 'M

1.1ilhi ttinctlonlll otily

xvht, i"i ('At" I'/'IVAliN.

XI_?I)F." switch in C.'W

l,ltlhl Ituli'tlonal only

whrn GAUr•WARN.

_%lk}l'lF +l_l+tch in ',+', M

Phge ,, : I0.{,

SMZAo03-SC012


I •

i ,

I

I

S M RC5 A

S .xt RCS B

S :,I RCS C

S .',I RCS D

SPS ROI.'GIt

t.:CO

1120 ACCL'.XI

FAIL

I' C BUS

DISCONNECT

.t'.C I

tII.YCOL

; HXlt _ I.OW

Lamp TrigRar Value

1. Tank 1 4800 psia

l. Tank I >_)S0 psia

3. Tank t,c, S00 pain

4. Tank I >950 psta

I. _ tsmp<6$*F

;'. Pkst tamp >IT5"F

3. Re8 He press < 155 pain

4. R611 He press >el 5 pS_.a

1, Pk 8 tamp <63'F

_, Pk 8 temp >|75"F

3, Rag He press<IS5 psit

4. Rag He I_ress>al5 psia

• Pk$ temp<63°l "

" Pkl temp >I 75 " [."

3. ReR He press<f55 psla

4. ReSt He press>215.psia

l. Pkg temp<63"F

2, Pkg ternp >175"F

3, Rag Ha pretis<155 psia

4, Reg He press >215 psia

l. 180G's tot. 70 m seconds

2. 360C,'s for 30 m seconds

Three O) bubbles (rain) in

,outlet W{ter hne

I. F_ad current at 75 ilmpa

for 15 rain. or at II_ imps

for 25 t6 100 seconds

_. Reverse current at 4 amps

for tO sec, or 20 stops for

I See.

1, H a fl0w< 0.018 lblhr

a. H 2 flow >0.16 Ib/hr

3• O l flow<0.14 lblhr

4. O 2 flow_l.2? lb/hr

5. At pH factor of q

6. Skin tem[5< ]60'F

7. Skin temp>5OO'F

_l. Cond exh <,IS_'F

q. Cond exh >175'F

10. Rsd out temperature-

below *30"F

I1. H 2 rag p_'est >7_ psii

12. O_ reg press >75 p_ta

IL N2 _eg _ess >70 psta

At _41*F

At -]0*F " •

SYSTEMS DATA

TLM

Code No.

SF003?P

SF0038P

SRS065T

SR5729P

SRS066T

SR5776P

SR_067T

SR5817P

SRS068T

SR5830P

None

None None

SiC ;

Other IndLcation

TANK PRESSTJR E-O_- l |/M

indicator

TANK PRESSURE-O_-_

ind tc ate r

S/M RCS TEMP-PKG _IM

indicator

S/M RCS PRESS-MANF

indicator

S/M RCS TEMP-PKG $/M

indidator

aIM RCS PRE$fi_MANF

indicator

SIM RCS TEIMP-I_KG S/M

indicator

SIM RCS PRESS-MANF

indicator

S'M RCS TE_IP.PKG ' S/M

ndicator

S/M RCS PRESS-MANF

ndicator.

Engine cuts off. $]l_t

C/M

SC2120X MR BUS A event S:.\I

SCaI21X indicator (3)

SC2122X

SCl125.X MN BUS B ecent

SC2126X indtcat6r (3)

SC2137X

SC2139R ICUEL CELL-FLOW-

H 2 indicator

SC2142R FUEL CELL-FLOW-.

02 indic&tot

SC2160X pH HI event inli

SC2084T M'O DULK TEMP*SKIN

indicator

,_tC2081T MODULE TEMP_COND

EXH indicator

8C2087T Ir/C RAD TEMP LOW

event indicator

SC2069P REG OUT PRE_ HI

"H2 event indSC2066P- REG out PRESS Ill

-O 2 event md

$C_0b0P REC OUT PRg'-$S IlI

-N 2 event tnd

C F00Z0T GLY EVAP-OUTLET

TEMP indic ator

S/M

C/M

C/M

Remarks

G-levels are peak-to-

peak,

Event indicators ptl.

HI. FlU RAD TEMI 5

LO, tq _,_rss. oaPRE_-_, and N a PRK_Sare activated at lamp

trigger values.

MtssioA

ii ! ....... r •

CAt'TIt)N AND WARNING sYSTP.M

Basic Date • _ c, Change Date ,--- pare ,t., Io-7_ _

,'.,, ,, . .m

SMZA -03-SC012

A POLLO OPERATIONS HANDBOOK I"

SYSTEMS DATA

VC2

INV 2

TEMP 111

PITClI GMBI.

DR FAil.

SPS WALL ,

TF.MP 111

TEMP Ill

Larup 1 rigger Value

1. Fuel tk lie press<lo0 psia

_. Fuel tk He press >200' psia

3. Ox tk lit, press <160 psia

4. O_, tk lie press >200 psia

I. tl2 flow<0.018 lb/hr

?. 112 flow >0. It, Ib/i'r

:_. 02 Iluv,' <O, 14 lb,'hr

4, 02 flow >1.27 Ib/hr

_. At pli facto| _ of _

¢_= Skln temp<3_0°F

7, Skth tep_p _t,00"|."

8. Cond exh <155°F

'_. Cond exh >I7_'F

10. l";,'|d otis telHpbelow - 30" F"

11, i12 reg press>7_ paia

At 240 _ F

TLM

Code No.

Sla_006P

SP0003P

8C2140R

SC_I43R

8C2161X

8C2085T

SC_082T

SC._O88T

SC2070P

8C2067P

SC_'O_ I P

CC0176T

SPl000X

SPU0_'0 T

SC2141R

sc-,t44R

SC216,_X

SC2086T

SC2083"1"

SC2089T

SC2071F •

Sc2o_SP

8c2062 P

CC0177T

SPl0OIX

None

Other Indication

PRESSURE* FUEL

indicator

PR ESSURE-OX

indicator

FU EL. CELL- FLOW.

1{2 indicator

FUEL CELL- FLOW-

02 indicator

pH HI Went Lad

MODULE TEMP*$1_N

indicator

MODULE TEMP-COND

EXH indicator

F/C RAD TEMP LOW

ev0nt indicator

REG OUT PRESS HI,

}{_ event indicator

REG OUT PRESS HI-

e 2 event indicator

RI_-G OUT PRESS tII-

N Z cvettt.indicato r

None

None

None

Ft_EI-- CELL, FLOW--

H 2 indicator

FUEL CELL-FLOW-

indicator

tH event ind

MODULE TEMP-SKIN

ihdtcat6r

MODULE TEAiP-COND

EXII indicator

FIC RAD TEMP LO%V

event indicator

RE(_3 OUT PkESS HI-

t{ 2 event indicator

REG OUT PRESS I[I-

02 event indicator

REC, OUT PRESS I[I-

N_. event indicator

None

None

UNBALANCE mdtca-

tOr (for over ._O0

lbs only|

Mi_aion Ba,_i¢ Date

CAt'TICN AND WARNING SYSTEM

II \',,, 1'it,r, ChAnge Date__

S/C

Mode

S/M

S/M

C/M

S/M

S/M

S/M

C/M

s / M

S,'M

Remarks

Event indicator pH }ll,

F/C RAD TEMP LO,

H_ PRE&S, O_ PRESS..

and N 2 PRES_ ara

activated at litrnp _

t rigi_er Valtae s,

Overcurrent condi-

tions dependent upgn.

tired and temp_

Event indicators pHHI; F/C RAD TEMP

LO, H Z PRESS, O Z

PRESS, and N:_ PRESS

are ai:tivkted at lamp

trigger values.

OverCt_r rent condttton

dependent upon time

and temp.

Light ftmcttonal only

d_rm 8 SPS ftrtnll,

Page _. 10.a,

.i

i

SM2A-03-SC012


,

SYSTEMS DATA

•qt a!tl_ l.',_ht

>.l.x, !_I'S A

!N.r'q.:l_ \ CL r

kIN I_t S 1_,

•'XDF:RVOLT

Ct'2 PP IH

AI'I',WARN

:'All=

C 2 i LOW III

.\(" BUS I

C\ }-'.I 1.CAD

AC BUS 2

C V '..'.ItI,OA D

Lamp Trigger Value

At 26.2:,±0. I vdc

At 2o.25i0.1 vdc

At 7.6 mm Itg

1. At _ vdc

2. A1 130_2 vdc

1, At 05,3 vdc

2. At 1t0,2 vdc

1. At *11,,7 vdc or *11.7 vdc

2. At +13, n vdc or -13.9 vdc

At 1.0 lb/hr

1. 30 at a.amp:0 :or 15,5 sec

2. 10 at ll-amp for ¢.+1 see

I. 30 avq amp/0 for 15±_ aec

2. t0 at I1 amp for 5-1 sec

TLM

Code No.

CG020bX"

CG0207V

C F000513

CG0200V

CG0201V

CG0202\'

CC0203 V

CC0204V

CC0205V

_ono

No.t2

_Ollt?

_ono

Other indtcatton

DC \'OLTS meter

DC VOLTS rnt.ter

PART PRESS CO 2

indtcator

AC \'OL'I'S tixeter

AC \'OLTS meter

MASTKR ALARM

lights 13_

FLOW 02 in_dicator --

AC VOLTS mcter

AC \'¢)LTS meter

SiC

Mode

C/M

C/M

C/M

CI,M

C/M

C/.M.

C, .M

C/M

C/M

Remarks

Alarm tone inopefattve.

Overload diaconnccts.

ittVcrter froin bug.

Overload disconnects

inverter frot'_x bus.

Nlts _ion

CAt" Ilc:; AND 9, AI_:;I.NG SYS I FiXt

Basic Date t':,,, I ..... , Change, Date PagP =- 5: .Io-. , . ,

SM2A-03-SC012

A I_OLLO OPERATIONS HANDBOOK

,i

Z, 10.6

SYSTEMS DATA

i

TELEMETRY MEASUREMENTS

The following is a complete list of all C&WS telemetry data that is

monitored by flight controllers and ground support personnel. The laet

column contains the name and type of S/C crew display. The display

utilizes the same pickoff or signal source as telemetry, unless a separate

measurem6nt number is in_:luded in the display column.

Measurement

Number

CS0150X

Descr[pti6n

M_st_r caution-Warning on

Sensor .Range

Off/on event

Crew Display

MASTER ALARM lights

)

• J.

Mis siott,

i

CAUTION AND WARNING SYSTEM

Basic Date 1.2 Nov 1966 Chang e Date,, Page _ 2.10-i0

{

2. LI.I

2.11.2

2.11.3

2.11.4

SM2A-03-SC012


SYSTEMS DATA

SECTION 2

SUBSECTION 2. Ii

MISCELLANEOUS SYSTEMS DATA

IN TROD UC TION.

Miscellaneous systems data pertain_ to items that were not covered in

a previous system. These items consist of clockS, timers, aceelerometers

(G-meter), interior lighting, etc.

CLOCKS.

Two clocks and two clock-like event timers, all mechanical, are

provided for the crew in the command module. The 400-hour clock

(MDC-12), used in monitoring mission elapsed time, is illuminated by

floodlights. The GMT 24-hour clock and two 10-hour event timers are

located on panel 306 in the LH forward equipment bay and lighted by integral

bulbs controlled by the CLOCKS-BRT/OFF/DIM s_4tch on LEB I00. For

further.itlformation, refer to section 4.

DIGITAL EVENT TIMERS.

The digital event timers provide the Crew with a means of monitoring

and timing eventS. One event _imer is located on MDC-5 the other is

located on MDC-II. The event timers start automatically when lift-off

occurs, and the timer located on MDC-5 will be reset if an abort is auto-

matlcally or manually initiated. For further information, refer to

section 3.

ACCELEROMETER (G-METER).

The accelerom.eter or G-tneter (MDC-2), provid6s the crew with a

visual indication of spacecraft positive and negative G_loadS. This meter.

is illuminat_.d by floodlights controlled by the LH area control panel

(MDC-26). For detailed information on the accelerometer (G_meter), refer

to section 4.

COMMAND MODULE INTERIOR LIGHTING.

The interior lighting _rovides light for the main display console and

LEB panels in the command module.

Missiofl

NLISC!_LLANEOUS SYSTEMS DATA

Basic DAte. 12 Nov 1966 Chan_e Date Page 2. 11-1

SMZA-03-SC01Z


SYSTEMS DATA

Z. i I. 5. 1 Functional Description.

The interior lighting equipment consists of eight floodlight fixture

assemblies and three control panels. Each fixture assembly contains two

fluorescent lamps (one primary and ,:me secondary) and a Converter. The

interior lighting is powered by 28 volts de, from n_ain buses A and B for

redundancy (figure 2.11-I). This assures a power source for lights in all

areas in the event that either bus fails. The converter in each floodlight

fixture converts 28 volts dc to a-c power to operate the fluorescent lamps.

The floodlights are used to light three areas: the main display console

(left and right areas) and the LEB area. Control panel (MDC-Z6) is located

on the left and control panel (MDC-23) is located 0*% the right of the main

display consol_ (figure 2. 11-2). The third control panel is located in the

lower equipment bay area on LEB-100. The floodlight fixtures are located

around the interior of the command module. (See figure Z. ii-2.)

Each control panel has a primary and seconda_:y contro]_ for the flood-

lights in its respective area. The primary control is a rheostat that con.

trols brightness of the primary floodlight_. The _econdary control is an

ON-OFF switch for the secondary floodlights and is turned to ON when

additional brightness is desired. The floodlight circuit breakers a_e on

MDC-25. The operational use, or brightness level of the floodlights

depends on t_,o factors: the g-level and the task being performed. The

floodlights should be turned up bright during ascent and entry. The flood-

lights will be adjusted as required while in earth orbit. The FDAI (MDC-4)

is lighted by integral bulbs which are controlled by the FDA/ LTG switch on

MDC-25 and FDAI BRIGHTNESS rheostat on MDC-2. A switch is provided

on the LEg floodlight control panel to control lighting for the clocks on

LHFEB-306.

2.11.6 COMMAND MODULE UPRIGHTIMG SYSTEM.

The C/M uprighting system is manually controlled and operated after

the C/M has assumed a stabl_ inverted floating attitude. The system con-

sists of three inflatable air bags, two relays, three Solenoid control valves,

two air compressors, control switches, and air lines. The inflatable bags

ar_ located in the C/M forward compartment and the air compressors are

located in the aft compa#tment. The control switches and circuit breakers

are located in the cr6w compartment. Switche_ 1 and 2 are powered by the

postlanding bus switch 3 and the compressors are powered by battery buses

A and B. (Se_ figure 2. II-3.)

Z. ll.6.1 Functional Description.

POSTLANDING - FLOAT BAG s_itch i controls inflation of the air

bag on +Y a.,ds, switch 2 control_ inflation of the air bag on the -Y axis,

and switch3 controls inflation of the air bag on the +Z axis of the C/M.

(See figure 2. ii-3.) Each bag is 43 inches in diameter and has a capacity

of approximatel T 24 cubic feet _.her_ inflated. If the C/M becomes inverted

.<

#-

Mission . •


Basic Date 12 Nov 1966 Change Date. Page ?.. ll-Z _ r

ISM_A-03-SC01Z


SYSTEMS DATA

U

uu_

,=

0

......

L)

1

°

I..,

Mtss_on

MIS CE LLANEOUS SYSTEMS DATA

]_asir Date 12 Nov 1966 Cha,:u,, Dat,, Pa R P Z. ll-3

SM2A-03-SC012

APO LLO 0PER.ATIONS 13ANDBOOK

SYSTEMS DATA

(LEP AREA CONTROL) I

(TYPICAL LH AREA AND RH AREA CONTROLS)

s - FLOODLtGHTS,-l

OFF

Figure 2 . 1 1 - 2 . C/M lntcrior Lighting Configuration . . . . . . . . -. . . . . - .

MISCELLANEOTJS SYSTEMS DATA

SMZA-03-SC01Z


SYSTEMS DATA

i .

CONTROL VALVE NO. t+Y BAG

COMPRESSOR. _

CONTROLRELAYS [ KI !

i

PRESSFILLNORM CLOSED

CONTROL VALVE NO. 2.-_( BAG

II

I

CONTROL VALVE NO. 3+Z BAG

BATTERYBUS A

i [

BATTI_RYBUS

UPRIGHTING sYSTI_M-25A

COMP NO. 2 /"

(RHES-20S) " ]

:: s2.

1COMPRESSOR •

NO. 2

SM-2A-E82C

Figure Z. ll-3. C/M Up_ighting System Electrical Schematic


M i_ s ion _n_ic Date II Nov 1966 Chan_.e Date . . @a_6 Z. ll-5 .

o

A P O L L ~ OPERATICNS HANDBOOK : 1 SYS'l'EILtS 6.4'1'~

. .

af tvr landing, tllc crt*\\~rnc~tnbc~ r a t s ta t io~r I i n i t l . l t ~ s f i l l i l ~ g t ~ i thc 'hrce Lays 1,). s c t t i ~ ~ g t h ~ ~~- 'OST~~. \NT)ING - FLOAT 1\ 4 G s\titclrc*s 1, 2 . a~rd I t o FILL. \!'11(.11 ti)<. C/X! i s -uprighted, tllc thrcc I.'ttC?t\T I\:\Ci s\vitc*lr6w \ \ i l l Ilc s c t to OE'F. . A 4. 25&0. 2 % pSi l'c1ic.i \..11\11* i : i luc,~tcd i n thc iu lct a i cach bag. i?clckup rc1ic.f \falvcs s e t ;it 1.3. S pdi a r c lt?c.i\tcd i n tht\ ot~tlr%t of csch

_3M2A-03-SC012APOLLOOPERATIONSHANDBOOK

CONTROI_ AND DISPLAYS|i i i

SECTION 3

CONTROLS AND DISPI,AYS

INTRODUCTION,

Thi:_ _,ction iflefltifiCseach control arid diSplAy in the command modul6

and lists panel loc_'ition, itcx_ nomcn¢lhtur6. 0ouitiofls and r_,|atcd

func'ti6ns, l_owcr _ource, tt, lOinetry i_(-aSur6n_ei_t numb6r, and associated

explana_oi'y dicta. Controls and displays are presented in a t_lbulatedlist

in nun_erical order by panel number. Panel numbers are those appearing

on the main display cohsole drawing and the lower 6quipi'nent bay drawing

in figure 3-1. (The.comn_and f'nodnle itself doe_ not incorporate fiml_b(,rs

on tke panels.) The, following is a detailed explanation of the ¢olunmai _

data pre_iented in thO tabulated list.

I.o,'atiotx Gives the location of a pat_ticular control or

display by.panel number or oth(_r descriptive

inforn_ation such as- "!,H couch armre.qt,

etc. ,.

Natne and Position Givrs tho exact nonx(.nclature of a particular

control or display and the cofltrol pt_ition.s.

as placarded on th(" pan01, ha the absi, tlco ot

a placard, a functi_lflal flatne is assigned anti

the pogitions ar6 describ6d physically ("up, l'

"dOWltl " etc_.

l;'tuxct ton Dvscrth_.,s the flmttion of ,_'a¢l_ control in ,,._lt'h

pos it ion_

(" ti_,'titt I_ re.tkt" r Gtv0is the flati_e arid location of the ¢irctttt

bri, akt. r(,,;l) controlling tl_c i.h, ctricAl p_l_,t-r to

t'ach ct_ntrol & dtsplaV.

identdtea _u_d givr# thv ratihg of the it ntnedt

ate bus or' source ,,iupplying po_;,ler to a

part tetilar ¢oft! rol or di.splay.

Teletl_etr_, ('ode No..tied

Idet_tit_

Gives the ini.a..lttrt.ittellt httlttberll t'or teh'

ttlotry itti_ttili|s whit'h art' U.'li_d to ntolltto, r tilt,

perft:rttti_nce of t't_ntporetits, xystvtn_, and

_ttlixytltetiis. tile xtattts of conltttitat_le ileitis.

and the lirotlei ' si, qiti, l't_ trig Of critical

t

IM t s ._ion Baltic Date

i

coNrRo {_ AND DLSPI..4YS

I,'. N?v I,.ll;i,..Ctt*nil l- Diitei___ iia/le---.3 1........

SM2A-03-SC012APOLLOOPERATIONSHANDBOOK

CONTROi,,_AI'4D bISPI,AYS

i i . m

operation8 during all phase,_ of the spa, e_ l aft

n_issmn. Tiffs tnfornlattoll ts nxol/ttored at

MSFN stations for apacecraft management

from the ground by ua_ of vow(' or ci_mmland

links. Measurement numbers arc entered

only for uisplayed measurcnlents. Thoat, for

undisplayed nteasurctncnts are included in thc

tei6metry lilc;lsuret'notlt8 tabU: for the

appropriate sy_tetn in ._0ctioh 2 of this

hanflbook.

The, nut_lbcr cafl_istS el' _t'vt_n cluiractt_rs:

two letters followed by to_xr nutnber._ hrM on4,

lettOr, AnexAmplc i_ a_ follows:

Modulo code letter

C .'X S.

1l.'uncttortal _v_tett't code Icttcr

Dtacretc nttttlbcr,

Me,t_ttrctttcttt classific&tion

a. Thi, t'trst letter desigtlat¢,s the modulo in _.htch the melXsuretnent

ortgltxkt_,_. Modttle todd [cttOr_ art' as follows:

A Adapter L I,aunth escape tearer

B Boo,to r S ."It, rvicc nxodul0

C Conmtand modul(,

b. Tht' tiecond letter detlt_t_,,ti tilt;

orxgifl.ltes. F_tltxcttofiAl Systt, fll code

ti'y:.ttclll lttwhtvh lilt" tllt'ii.'4ttrctllt'tltlett_,rs are .t_ foliovtS;

A 5trttcturo.'_ ,1 l,tfe sy.att, ti_s

C Hlcctrtcal po_vci" K. li'light tt, chnol_gy

D 1.aunch e_/ape P l_ropulston

I': l':arth l,uulmg R Rt, actton _ ont rol

l" l':llvlrontllelltal Colltrol N Cr0w sltt'ety

k] k_tlitlatlll'e alltI llltvig,ttioll T Tt'lt'_'t_ltltlltlnl_ .ttt,_ll,_ and

I! 8t,il'_lll;:ilitloll and c,ontrol tnstrllttlt, lltattOll

c. l:hai',tctt, t;_ three throttgh six at'i, Ittltnerltis _'otl_prl_ttlbl & Iltltll|)t'r

which 15 assigned I,, a parttcttlar tlWiistlretlletlt point. These tllllllbt'l'S _lirt,

II_tt'd _t'qlit'lltl,tllV or .Irt" grotl|lt'd for t'lltrltv withlll t'ach ._$'stt'lfl.

i

hits_te:_

¢:ONTROI.S AND DISPI.AYS

,Ba,_tc Dat_ 12 N,_ Iqt,¢, Chanlle Date _ . PaRr I 2 _ ,,

SM/A-03-SC012


3.1

CONTROLS AND DISPLAYS

d. 'Flat. sex;enth letter denotes rneasuremcnt classific_ition.

cation code letters art, as folloxvs:

Classifi -

A Acceleration N Camera

B Phase P Pressure

C Current Q QuantityD Vibration R Rat0

E Power S Strah_

i_" Frbquency T Temperatur0

G Force V Voltage

II Position W Tim6

J Biom0dical X Discrete 0vent

K Radiation ........ Y Acoustical

L. Volcotiy Z pH - acidity

M Mass

Remark s Contains additional data and explanatory rema rks.

CONTROLS/DISPLAYS LOCATER INDEX.

To aid in .finding data within this section, a locator index precedes

the tabulated list. The index is sub-divided into spacecraft systems.

Und0r each System is listed, in alphabetical order, all controls and dis-

plays associated with. fl_c particular systdm with cross reference to the

panel on which the control or display is located..Where it6ms, such as

circuit breakers, are associated with more thanone system, such items

are repeated under each applicable system. Each panel number is

preceded by an .abbreviated descriptor to aid in quickly determining the

general location of e_tch item, as follows:

MDC

[. IC 13

l,l[l.:B

I,}[FEB

RIIEB

RIIFF.I_

main digplay console Ipanels I thru 2o)

lox_er equipment bay tpanels 200 thru 107, 120, 150)

left hand equipment bay (pan,,ls _07 thru _17 and _lq)

left Iialid forward equipment bay _pan01s ._00 thru _Oo and _18)

right, hand equipment bay (pahel.., .'01 thru 20t,)

right hand for_ard cquipmont bay (panels 200 and 2071

The controls/displays locator index *s sub-divided as follows:

Mi-_sion

Guidance aad Navigation

Stabilizatmn and Control .

Service Propulsion Sy_te:uReaction Control

F.lectrlcal Poxve r

Svquential Systems (ELS, I.ES, EDS, SECS}'I'¢" I _' C O lllliltllli_.'a t ions

Env,ronmental Control

CONTROLS AND I)LSPLAYS

Basic Date 12 Nov lqtib Change Date PAge

Page

3-5

3-7

3-q

3-II

3-13

3-17

3-18

3-20

3- 3

SMZA-03-SC0 IZ


(_ONTROLS AND DISPLAYS

Cauti6n and Warning

Miscellaneous Systems

Sc ientific E×pe ri_ents

Page

3-23

3-24

3-Z5

CONTROI,S AND DISPLAYS

Basic Date. 12.Nov..10_o Change Date

SMZA-03-SC012


GU/DANCE AND NAVIGATION SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

Control/Display Name

ACCEL FAIL

ACTIVITY COMP

AGC MODE

AGC PWR FAIL

ATT CONT MODE

ATTITUDE IA4PULSE

ATTITUDE IAIPULSE ENABLE

BRIGHTNESS

CDU FAIL

CDU MAN MODE

CIIECK CONDITION LAMPS

CHECK COOLANT

CHECK COOLANT

CHECK FAIl,

CHECK MODE LAMPS

CLEAR

COARS ALIGN MODE

COMP FAiL

COMPUTER.

CONDITION LAMP

COUNTER FAIL

DOOR LATCH

DSKY

ENTER

£NTRY MODE

ERROR RESET

FINE ALIGN MODE

GMBL LOCK

G_N ACGELFAIL

G& N ERROR

G&N VIEWER

IMU- CDU DIFFER ENCE

IMU

IMU DELAYIMU FAIL .

IMU HTRI_,tU TEMPIMU TEMP MODE GAIN IRIG

LMU TEMP MODE GAIN PIPAIMU TEMP MODE

LMU TEMP MODE ZERO

INNER GI/MBAL (PITCIi)KEY RLSE

KEY RLSE

MANUAL ALIGN

M A R KMASTER ALARM

Typer

Lt

LtSwLt

LtControl

SwControl

LtLtSw

Sw

Windows (2)Lt

Sw

Sw

Lt

Lt

CB (21Sv,'

Lt

C ont rol

KeysSw

Lt.Sw.Lt

Lt

LtLt

S%vIndCB (_,)

Lt .

Lt

CB (_)Lt

Sw

S%%'

Mode _w

Sw

Ind

Lt

Sv,,

Lt

Sw

Lt

Panel Locator

LEB-103

MDCI4, LEB-106LEB- 107

MDC-10, LEB- I03LEB-101LEB-105

LEB.105

MDC- 14, LEB- I06

MDC- I0, LEB- I03

LEB-101

LEB-105 ......LEB-105

LEB-105

LEB-106

LEB-105

MDC- 14. LEB- I06

LEB*I01

MDC-14MDC-ZZ

LEB-105

LEB-106

LEB-105

MDC- 14, LEB- I06

MDC- 14, LEB- I06LEB-101

MDC- 14, LEB- I06LEB-101

MDC-10, LEB-103.

MDC- 10

MDC- 10

MDC-22

LEB.101

MDC-22

LEB-103

MDC- 10, LEB-.103MDC-22

MDC- I0, LEB-103LEB.105

LEB- 105LEB- 105LEB- I05

LEB- I02

MDC- 14, LEB- I06MDC- 14, LEB- 106LEB- I01

LEB- I05

MDC- 3, LEB- I03

GUIDANCE AND NAVIGATION SYSTEM-CONTROI_IDISPLAYS LOCATOR INDEX

Mission Basic Date.l! ,_gv I?_;t, ChanBe Date ImiBe 3-5

m ,,,

SMZA-03-SC012


GUIDANCE AND NAVIGATION SYSTEM-CONTROLS/DISPLAYS i,OCATOR INDEX


MIDDLE GIMBAL (YAW)

-(minus sign switch)

NOUN

NOUN

OPTICS

OPTICS CONTROLLER MODE

oPTICS CONTROLLER SPEED

Optics hand controller {no placard)

OPTICS HOLD

OPTICS

OPTICS SLAVE TELESCOPE

OUTER GIMBAL (ROLl,)

PANEL BRIGHTNESS

PARITY FAiL

PGNS

+ (plus sign switch)

PROG ALM

PROGRAM

REGISTER 1

REGISTER 2

REGISTER 3

RUPT LOCK

Sextant (not placarded)

SCALER FAIL

SHAFT ANGLE

SIIAFT

Telescope (not placarded)

TC TRAP.

TM FAlL

TRANSFER

TRUNNION ANGLE

TRUNNION

UPTEL ACCEPT BLOCK

% ERt

V_RB

VIE-..WE R

ZERO ENCODE MODE

ZERO I_NCODER

2X TRUNNION

Type

lad

Sw

Sw

End

CB (Z)Sw

Sw

Control

Sw

Mode s_

Sw

ladContz.ol

Lt,

Lt

Sw

Lt

lad

lad

lad

lad

Lt

SXT

Lt

lad

Manual drive

SCT.

Lt

Lt.

Sv¢

ladManual drive

SV,'

lad

Sw

CB (a)Lt

Lt

Ind

Panel Locator

LEB- 10Z

MDC- 14, LEB- I06

MDC-14, LEB-106

MDC- 14, LEB- I06

MDC-22

LEB-105

LEB- I05

LEB- 105

LEB-105

LEB-105

LEB-105

LEB-10P

LEB- 105

LEB- 106

LEB,103

MDC- 14, LEB- I06

LEB- 106

hiDC- 14j LEB- I06

MDC-14,. LEB- I06

IviDC- 14, LEB- I06

MDC-14, .LEB- 106

LEB-106

LEB-104

LE B -1 06

LEB- 102, LEB- I04

LEB-104

LEB-104

LEB-106

LEB-106

LEB-101

LEB-104

LEB-104 •

MDC- 14

MDC-14, LEB-106

MDG-14, LEB-106

MDC-22

I,F.B-101

I,EB - 103

I,EB-102

GUIDANCE AND NAVIGATION SYSTEM-CONTROLS/DISPLAYS LOCAT-OR INDEX

Mission Basic Date 12 N_v I'*,,,_ Change Date ........ Page .. :,_-_ ........

[i

[

[

[

I

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F

I

SM2A-03-SC012


-_TABILIZATION AND CONTROL SYSTEM--CONTROLS/DISPLAYS LOCATER INDEX


AGAP TEMP

ATT DEADBAND

ATT SET

ATTITUDE iMPULSE-ENABLE

ATTITUDE/MONITOR/ENTRY

ATTITUDE SET-ROLL, PITCH, YAW

ATTITUDE SET-ROLL, PITCH, YAW

BMAG POWER

C/W-NORMAL/BOOST/ACK

CAUT/WARN_MNA, MNB

CAUTION/WARNING- MODE

DIRECT RCS

DIRECT ULLAGE

FCSM AUTO/OVERRIDE

FCSM ON/RESET

FDAI

FDAI ALIGN

FDAI BRIGHTNESS

FDAI LTG

FDAI SELF TEST

.05G ENTRY

GLIVIBA L POSITION

G&N/SCS

G&N SYNC

LCL VERT

L!AIIT CYCLE

MASTER EVENT SEQ .CONT-A LOGIC B=

BAT A, BAT B

NORMAL/OFF/DIRECT ON

PARTIAL SCS POWER

RATE GYRO POWER

RATE GYRO-ROLL, PITCH, YAW

REACTION CONTROL SYS-TRANS

Rotational Controllers (not placarded)

ROTATION CONTROL POWER

SCS CHANNEL-A&C ROLL, BAD ROLL,

PITCH, YAW

STABILIZATION & CONTROL SYSTEM-

A&C ROLL-MNA, MNB

BAD ROLL-MNAo MNB

DIRECT CONT-MNA, MNB

GROUP I-ACI, AC2

GROUP I-MNA, MNB

GROUP 2-ACi, AC2

GROUP 2-MNA, MNBm • ......... :- ............... i ......... ."

Type

Warn It

Sw

Sw

Sw

Sw

Thumbwheel (3)

_nd (3)

Sw

Sw

CB (2)Sw

Sw.

SwSw

Sw

Ind.

Sw

Control

Sw

Sw

Sw

Lnd

Sw'

Sw

Sw

Sw

CB (2)

Sw

Sw

Sw (3).Sw

Controls (2)

CB (l 8)

Panel Locater

MDC- I0

MDC-8

MDC-6

LEB-105

MDC-8

MDC-6

MDC-6

MDC-24

MDC- 13

MDC-25

MDC-11

MDC-8

MDC- 7

MDC-2

MDC-2

MDC-4

MDC-6

MDC-2

MDC-25

MDC-2

MDC-8

MDC-6

MDC-8

MDC-25

MDC-8

MDC-8

MDC-22

MDC-7

MDC-24 .

MDC-24

MDC-8

MDC- 16

LH couch,, RH arm.-

rest, RH couch,

LH armrest

-24

MDC-8

MDC- 2 5

STABILIZATIONANI) CONTROL SYSTEM-CONTROLS/DISPLAYS LOCATER INDEX

Mis'Sion BaaiC Date 12 _ov 106(_ Change Date , Page,3-7 .- .,,

SMZA -03-SC0 IZ


STABILIZATION AND CONTROL SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

ControllDisplay Name Type Panel- Locator

THRUST ON Sw MDC-7

Translational Controllers (not placarded) Control (2) LH c0uch,LH armrest

TVC i POWER Sw. MDC-24

TVC Z POWER Sw MDC-24

AV Sw MDC-8

AV REMAINING Ind MDC- 7

AV SET Sw MDC-7

YAW, PITCH ......... Thumbwheel (2) MDC-6

sTAI_II,IZATION AND CONTROl, Sy._TEM--CONTROLS/DiSPLAYS I.OCATOR INDEX

Mission ...... Basic Date II Nosy 19_,h .Change Date. .Page 3.-8

I

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[

[

[

f

f

i

I

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1

!

SM2A-03_SC012


SERVICE PROPULSION SYSTEM-CONTROLS/DISPLAYS LOCATOR INDEX

Control /Display Name

ABORT SYSTEM-TWR JETT SPS MODE--A (B)

two

CAUT/WARN-MNA (MNB)

-%V

AV REMA LNING

AV SET

DIRECT ULLAGE

F CSM-G& N

FCSM-SCS

G&N/SCS

GIMBAL POSITION- PITCH

GIMBAL POSITION-PITCH -

GIMBAL POSITION-YAW

GIMBAL POSITION-, YAW

H e TANK-PRESS

H e TANK-TEMP

INSTRUMEINTS-ESS- MNA (MNB)

L/V AOA/SPS Pc

L/V AOA/SPS Pc

MASTER EVENT SEQ CONT_A LOGIC B-

BAT A (BAT B)

NORMAL�OFF�DIRECT ON (Thrust}

OXID FLOW

OXID FLOW-DECREASE

OXID FLOW-INCREASE

PITCH GMBL DR FAIL

PRESSUR E - ENG INLET-.FUEL

PRESSURE-ENG INLET_OX

PRESSURE-FUEL

PR ESSU R E -OX

QUANTITY -FUEL

QUANTITY -OXLD

SENSOR

SERVICE PROPULSION SYSTEM-.

GAUGLNG-AC 1 (AC2)

GAUGING-MNA (MNB)

GIMBAL MOTOR CONTROL -I PITCH

-BAT A (PITCH 2-BAT B)

GLMBAL MOTOR CONTROL -I YAW

-BAT A (YAW Z-BAT B)

f{e VALVE-MINA (MNB)

SPS E_GINE LNJECT VALVE -.1 (2, 3,. 4)

SPS GAUGING

SPS HELIUM (left hand and right hand}

SPS HELIUM (left hand and right hand)

SPS-INJECT PRE-VALVFS-A (B)

SPS-GLMBAL MOTORS -I PITCH (PITCH Z}| , | ,

Type

Sw

CB (Z)Sw

Sw

Sw

Sw

Sw

Sw

Sw

lud

Thumbwheel

Lad

Thurnbwheel

Lud

Lad

CB (Z)Lud

Sw

CB (2)

Sw

Sw

Ind

Lnd

Status Its

Ind

Ind

Ind

Lad

Display

Display

SW

cn (z)

cB (2)CB (2)

n_d (4)Sw

_d (z)

Sw (2)Sw (2)

Sw (z)

Panel

MDC-16

MDC -25

MDC -8

MDC - 7

MDC-7

MDC-7

MDC -2

MDC -2

MDC-8

MDC-6

MDG-6

MDC.6 -

MDC -6

MDC-20

MDC-20

MDC -22

MDC- 3

MDC-3

MDC-22

MDC-7

MDC -20

MDC -20

MDC-20o

MDC- 11

MDG-20

MDC-20

MDC-20

MDC-20

MDC-20

MDC-20

MDC-20

MDC-25

MDC-25

MDC-25

MDC-25

MDC-25

MDC-20

MDC-25

MDC-20

MDC-20

MDC- 3

MDC- 3

Locator

SERVICE PROPULSION SYSTEM-CONTROLS/DISPLAYS LOCATOR iNDEX .

Mission Basic Date 12 Nov !766 Change Date .Page 3-9

SM2A-03-SC01Z


SERVICE PROPULSION SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX


SPS-GIMBAL MOTORS -i YAW (YAW Z)

SPS LINE HTR

SPS PRESS

SPS PU SINSR FAIL

SPS ROUGH ECO

SPS TANK PRESS

STABILIZATION & CONTROL SYSTEM

-DIRECT CONT-MNA (MNB)

-I GROUP-AC I (GROUP 2-,AC Z)

-i GROUP-MNA (GROUP 2-MNB)

TELECOMMUNICATIONS--GROUP 5

TEST/AUTO/TEST (propellant quantity)

THRUST ON

TK PRESS-N.

UNBALANCE _

VALVE

Type

Sw (2)Sw

Status Its

Status Its

Status Its

Sw

CB (Z)CB (Z)

CB (Z)CB

Sw

Switch-light.

Ind

Ind

Sw

w

Panel Locatori i

MDC - 3

MDC -19

MDC- 11

MDC-11

MDC- 10

MDC-20

MDC-25

MDC-2_

MDC-25

MDC-2 :_

MDC-20

MDC,. 7

MDG-20

MDG" 2 0

MDG-20

SERVICE PROPULSION SYSTEM-CONTROLS/DISPLAYS LOGATOR INDEX

Mission Basic Date II Nov Icst_ Change Date Pa_e 3-10

L

J

l,I

I

!

SM2A-03-SC012


R EACTION CONTROL SYSTEM-- CONT ROLS / DISPLAYS LOCATOR INDEX


ABORT SYSTEM-OX DUMP

CM PROP JETT-DUMP

CM PROP JETT-LOGIC

CM PROP JETT-PGRGE

C/M RCSC/M RCS

C/M RCS

C/M RCS

C/M RCS

C/M RCS

C/M RGS

ClM RCSC/M RCS

CIM RCS

CIM RCS

A

B

HTRS

PRESS F

TEMP H ePRESS OX

PRPLNT-A

PRPLNT-A

PRPLNT-B

PRPLNT-B

C/M RCS TEMP He

C/M-S/M-SEP-A (B)

DIRECT RCS

INST RUME NTS- ESS- MNA (MNB)

MASTER EVENT- SEQ CONT"

-A ARM B-BAT A (BAT B)

-A LOGIC B-BAT A (BAT B)

PROPELLANT QUANTITY-FUEL (bottom

window)

PROPELLANT QUANTITY-OXIDIZER

(top window )PYRO A-RCS FUEL DUMP

PYRO B-RCS FUEL DUMP

RCS HEATERS-A MNB

RCS HEATERS-B MNA

RCS HEATERS-C MNB

RCS HEATEKS-D MNA

RCS INDICATORS selector

C/M section

S/M section

R.EACTION CONTROL SYS-CMD

REACTION CONTROL SYS-C/M PRESS

REACTION CONTROL SYS-TRANS

P_ACTION CONTROL SYSTEM

-C/M-S/M TRANSFER-MNA (MNB)

-GAUGING-MNA (MNB)

-PROP ISOL-MNA (MNB)

S/M RCS-A(B, C, D)-HELIUM I

S/M RCS-A (B, C, D)-HELIUM 1

S/M RCS-A (B, C, D)-HELIUM 2

S/M RCS-A(B, C, D)-HELIUM Z

S/M RCS PRESS. H e

Typem

SwSw

Sw

Sw

Sw

Status Its

Status Its

Sw

Ind

Ind

Ind

SwEvent indSw

Event ind

Ind

Sw (z)Sw

CB (Z)

cB(z)

CB (Z)

Digital ind

Digital ind

CB

CB,

CB

CB,

CB

CB

Sw-

Sw .

SwSw

Sw

CB (Z)

CB (Z)

CB (2)

Sw (4)Event ind (4)

Sw (4)EVent ind (4)

Ind

Panel Locator

MDC= 16

MDC -8

MDC -8

MDC-8

MDC-Z6

MDC- I0

MDC - 10

RHFEB-200

MDC - i 2

MDC= 12

MDC-12

MDC- 15

MDC - 15

MDC- 15

MDC - I

b_DC- IZ

MDC- 15.

MDC =8

MDC- 22

MDC-ZZ

MDC=2Z

MDC=12

MDC - IZ

LEB- 150.

LEB=IS0

MDC-21

MDC -21

MDC=21

MDC-21

MDC - 1Z

MDC- 12

MDC- 16

MDC- 16

MDC- 16

MDC-.25

MDC- 25

MDC- 25

MDC- 15

MDC- 15

MDC - 15

MDC- 15

MDC-12

....... j - ,: .... , -

REACTION CONT'ROL SYSTEM- coNTRoL_/DiSPLAYS LOCATOR INDEX.

Page 3-11Mission Basic Date. 12 Nov 1966 Change Date

SM2A-03-SC012

APOLLO. OPERATIONS HANDBOOK

REACTION CONTROL SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

Control/D_splay Name

S/M RCS PRESS MANFS/M RCS-A (B, C, D).PROPELLANT

S/M RCS-A (B, C, D)-PROPELLANT

S/M RCS TEMP PKGS/M RCS A

S/M RCS B

S/M RCS C

S/M RCS D

Mission

Type

Ind

Event ind (4)

sw (4)Ind

Status Its

Status Its

Status ltsStatus lts

Panel Locator

MDC- 12

MDC-15MDC= 15MDC- 12

MDC- 10MDC-10

MDC-10MDC- I0

REACTION CONTROL SYSTEM--CONTROI,S/DISPLAYS LOCATOR INDEX

3-12..... Basic Date lZ Nov 196b Change Date Page .

L

t

SM2A-03-SC012

APOLLO OPEI_ATIONS HANDBOOK

ELECTR/CAL POW ER SYSTE M--CONT ROLS/DISPLAYS LOCATOR INDEX

ControU Display Name

AC BUS 1 FALL

AC BUS 2 FAIL

AC BUS 1 OVERLOAD

AC BUS 2 OVERLOAD

AC INDICATOI_

A.C INVERTER--AC BUS 1-RESET

AC INVERTER--AC BUS Z-RESET

AC INVERTER-- 1

AC INVERTER--I-AC Bus I

AC INVE_tTER--I-AC BUS 2

AC INVEI%TE R-- 2

AC INVERTER--Z-AC BUS i.

AC INVERTER--2-AC BUSZ

AC INVEI%TER-- 3

ACINVER.TER--3-AC BUS I

AC INVEI%TER--3-AC BUS 2

AC SNSR SIG- ACI

AC SNSR SIG-ACZ

AC VOLTS

BAT A PWR-ENTR.Y

BAT B PWR-ENTRY

BAT CHGR

BAT" CHGR-BAT C

BAT-C PWR-POSTLANDING ENTRY

• BAT ILLY BUS-BAT A

BAT RLY BUS-BAT B

BATTERY CHARGER

BATTERY CHARGER-AC PWR

BATTERY CHARGER-BAT A CHGE

BATTERY CHARGER-BAT B CHGE

BATTERY CHARGER- MNA

BATTERY CHARGER-MNB

LtLt

LtLt

SwSw

Sw

SwSwSwSwSwSw

CRYOGENIC SYSTEM-QTY AMPL-AC l-PC

CRYOGENIC SYSTEM-QTY AMPL-AC 2-%C .

CRYOGENIC SYSTEM-TANK HEATERS-H 2CRYOGENIC SYSTEM-TANK HEATERS-O2CRYOGENIC TANK FAN MOTORS-AC l-%A

CRYOGENIC TANK FAN MOTORS-AC l-%B.

CRYOGENIC TANK FAN MOTORS-AC l-pC

CRYOGENIC TANK FAN MOTORS-AC 2-_A

CRYOGENIC TANK FAN MOTORS-AC Z-%B

CRYOGENIC TANK FAN MOTORS-AC 2-%C

DC AMPS

DC INDICATORS

DC SNSR. SIG-MNA

DC SNSR SIG-MNB

DC VOLTS

Type Panel Locator

MDC- 1 1M DC -.11

MDC- 1 lMDC-11

MDC°18

MDC-18MDC-18

MDC- 18MDC- 18

MDC- 18........ MDC- 18

MDC- 18MDC- 18

Sw. MDC- 18

Sw. MDC- 18Sw MDC- 18

CB MDC- 25CB MDC- 25

Meter MDC- 18CB LEB-150

CB LEB- 150

Sw MDC- 22

CB LEB-150.

CB LEB- 150

CB MDC-Z2

CB MDC-22Sw MDC- 18CB MDC-Z2

"_B MDC-22

CB MDC-2ZCB MDC-22

CB MDC- 22CB . MDC-22

CB MDC-Z2

CB MDC-22

CB MDC-22 .CB MDC-22

CB MDC-Z2

CB MDC-22

CB MDC-Z2CB MDC-22

CB MDC-22

Meter MDC-18Sw MDC- 18

CB MDC.22CB MDC.22

Meter lVKDC. 18

i ........... i l "• f f

ELECTR/CAL POWER SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

3-13Mission BaSic Date 12 Nov 1966 Chanse Date Page .....

]

°

SM2A-03-SC012


ELECTILIC-AL POWER SYSTEM--GONTROLS/I_ISPLAYS LOGATO[_ INDEX

G6ntrol/Dispihy Name

D(" VOLTS (auxiliary}

F/C-BUS DISCONNECtF/C RAD 'rEMP LOW

FIC V:\ l,V V,SFIG I

F/C "

FIGFREQU F,N(_Y

FUEL CELL-FLOW-H2

FUEL CELL-FLOW-O_

_UEL CELL INDICATOr'S

FUEL GEL, L-, I_lAIN BlJS A-RESET

FUEL CELL-MAIN BUS B-RESET

FUEL CELL-MODULE TEMP-COND EXH

FUEl, CELL-MODULE TEMP-SKIN

FUEL. CE:LL I._BUS CONT

FUEL CELL 1-CIR &.SEP MOTORS

FUEL CELL I-Hj&O2 VAt'\rE

I}'UEL C#,LL 1-PURGE

FUEL CELL- I-I_L'XIN BUS A

FUt:L GEL, L- l-MAIN BUS A

FUEL CELL-I-MAIN BUS B

FUEL GEI,L-I,-MAIN BUS B

FUEL CELL-I purge

FUEL GEt,L- I-REACTANTS

FUEL., CELL- I - REACTANTS

FUEL CELL l-BUS CONT

FUFI.

FUEL

FUEl,

FUEL

FUEL

FUEL

FUEl,

FUEL,

PUEI,FUELFUEL[.'UEI.

FUI.:L

FUI,:I,

I:'UEL

FUEL

FUEL

FUI':L

FUEl,

FUFI,

F U I': t.

CELL 2-CIR & SO:.P MoToRS

CELL 2-Hl&O2 VAI.VV

CELl, 2-PURGE

CFI,L-2- MAIN BUSA.

CELL-l-MAIN BUS A

CELL-2-I_tAIN BUS I3

CELL-2-MAIN [_US B

C ELL- -_ purge

C FI.L- 2- REACTANTS

C E LL- I- R.EAGTA NTS

GEl,l, 3-BUS CONT

CEI,I, 3-GIR &.SEI' MOTORS

CI,:LI. l-l[,&O2 VAI.VI':

CELL t-PURGE

CEI,L-_-htAIN BUS A

CELL,-)-I_LAIN l'lIJS A

CI':L,L-4-MAIN BUS B

GEI,L-_-hlAlN BUS B

GEI,L-{ purge

C El,I,- _-REACTAN'I'S.

C FI.I.._ _= RHACTANTS

Type

Meter

Lt

Iud

Sw

I,t

Lt

Lt

Me te r

Ind

Ind

SwSw

Sw

Ind.

Ind

cnCB.

CB

CB

hid

Swlnd

Sv_'

Sw

lnd

Sw

cBCB

CB

CB

Ind

S_

Ind

lnd

S'_v

GB

CB

CB

GB

lnd

Sw

Ind

S,,,.

lmI

S_

Panel Locator

RHFEB -200

MDC- 11

M DC - 18

MDC- 19MDC-I I

MDC-I 1

MDC- I1

MDC- 18

M DC- 18

MDC- 18

M DC- 18

MDG., 18

MDC-18

MDC- 18

MDC-18

MDC_22

MDC°22

M DC - 22

M DC - 22

M DC - 18

MDC* 18

MDG- 18

MDC- 18

blDG- 18

MDC- 18

MDG- 18

MDC - 22

IvlDC -21

MDC-22

MDC -2-'

MDG- 18

MDC- 18

MDC- 18

MDC- 18

M DC - 18

MDG- 18

MDG- 18

MDC -22

MI_-22

MDC-22

M DC - 22

M DG - 18

MIK]- 18

MI}G. 114

NIIIC- 18

hlllC- lE

hi IM3 - 11_

EI ,ECT RIGA I. POW I_:R SYST E M-- (;ON;I" ROI,S/DLSPLAYS LOCATOR INI)I.:X_.!4

B.t.qh" D,itd _' 12. N,,_ I 'k*'t' Chanie Date , Pallf ......

ti

SXI2A-03-SC012


E:LECTRICAL POWER SYSTEM--CONTROLS/DISPLAYS LOCATOR iNDEN, r


FUEl, CELL PUMP-I

FUEL CELL PLIMP-2

FUEL CELL PUMP-3

FUNCTION S ELEC'I"

If2 FANS- I

El, FANS- 2

I[2 IIEAT E[_- I

l[ , I[E.-VI" EiL_-2

lI , PRESS

II_'VERTER CONT if.Of.,- I

tNVl.:It'r En CON'r _OL-,-"INVERT ER CONT R.OL-3

INVFRTER I_WR-NO. I MNA

INVERTER PWR-NO. 2 MNB

INVEP, TEK PWR-NO..3 MNA

INVI£I_,TER PWR-NO. _ MNB

INV I TEMP lit.

INV 2 TI'.'.I_iP 1{I

INV 3 TEMP }{[

KUkIN A-BAT BUS A

MAIN A-BAT C

MAIN B-BAT BUS B..

MAIN B-I_.\ l" C

NL-XIN BUS TIE-f_AT A&C

MAIN BUS TIE-BAT BhC

MN BUS A UNDERVOLT

NIN BUS B UNDEI_,VOLT

NON ESS 13US

¢._, FANS- 1

O 2 FANS- 2t,, 11l.:..x't_ it.s- l

t_ 2 l ! _L,\'r FILS - 2

i,) 2 })RESS

Ill[ IllI_t)ST I.,I_I-BA_" BI.IS A

I'tXClT IAX}-BAq_ BUS B

l't.k_l" LDG-BAT C

I'OS F LDG-MAIN A

POST I.DG-MAIIN B

I(EG OU'I PkE_ HI-I[?

REG OUI t)RFSS HI=N2

itl-Xi OUr PRF2'K_ tlI-CI.i,,4NsR UNIT-AC f_IJS- ISNSlt UNII'-AC flUS--'

SNSit UNIT-I)C tttl_-A

SNSR t'NIT-DC I_US-tl

S%v

Sw

Sw

S_

Sw

Type

Sw

l,t

CB

CB

ct_CB

CB

CB

CB

Lt

Lt

l,T

cB

CB

CB

CB

S_v

Sw

IA

Lt

S%v

S_Sw

S_v

Lt

hid

CB

C.B

CII

Cn

Ind

lml

liid

Ctl

CFt

CB

CB

Panel Locator

MDC-22

MDC=22

MDG=22

R HFEB - 200

MDC- 13

MDC-13

MDC- 13

MDC- 13

MDC-10

MDc-22

MDC-22

MDC-22

ItIIIT]B- 20

RIIHB-20

It t l F: B - 203

R ILI':B-20 _

MI)C- 1.1.

MDC- 1 1

MDC- II ---

RtIF:t/-:0

RtII,:B-20 _

R III.:11-70

It IIF:II-20 t

M DC - 22

MDC.22

MI)C- I I

MDC- I 1

M DC - 2 2

MDC-I_

MDC - 13

M IIC- l

MDC- 13

MDC- I0

MDC- 18

II tlt.'lt- 20

RItI.'II-20 t

lllll.:lt- 20

RIIt.;It-20

RIlI.:It-20 t

MI)C- 18

MDC- 18

MI)C- I8

ML)C- 21

M IJC - 21

M liC - 2 !

MIIC-2I

E I.F:CT ItICA I. poW FIR S yS'l"l-:_l-- tlt_NT ItOl,S ! DISI'I ,A YS I.OCATOR INIiF:X

_il_sl,'ll ll,lltl" l),ltl" I ' "i,_ I'i',l ', C.h_lnlli," D,It,' _ p,lill _ t-I_

SM._A-03-SC01 _-


ELECT RICAL POW ER SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX


TANK PRESSURE-H_- 1

TANK PRE2SSURE-Hz- Z

TANK PRESSURE-Oz- I

TANK PKESSURE-Oz- Z

TANK QUANTIT Y-H2- I

TANK QUANTITY-Hz- 2

TANK QUANTIT Y-O 2- I

TANK QUANTITY'O2- Z

TEST SELECT

H ! PURGE LINE HTRINV. PtIASE LOCK

Type Panel Locat0r

Ind MIX;- 13

Ind MDC- 13

Ind MDC- I 3

Ind M DC - 13

Iad M DC- 13

lnd MDC- 13

Ind MDC- 13

Ind MDC- 13

Sw RHFEB-Z00

Sw M DC - 1

Sw RHEB 208

t

,Misszov.

SM2A-03-SC012APOLLOOPERATIONSHANDBOOK

SEQUEN'rl;\L SYSTEMS-- CONTROLS/DISPLAYS LOCATOR INDEX

Cont roE,' DisphLv Namei

ABORr

ABOR T SYSTEM- MODII2

ABORT SYSTEM-L/V RATES

ABORT SYSTEM-OX DUMP

ABORT SYSTEM-2 ENG OUT

.\D.kP 1_ SEP

;\ L I"I,ME I'E R

AP!'X COVER 3ETTCANARD DI_DLOY

c/xt.g/.,,_ .qEPCOUCH UNLOCK

Digital Ex'E'iU Timer Indicatbr (no placard)I_IGIF..\L EVI_NT J,'IMER-MIN

I]IGIPAL EVENT rIMER. RESET

DIGITAL EVENT TIMER. SEC

DIGITAL EVEN 2' '['IMER- START

Digital Fv{'nt Timer It_dicator (no placard)DIGITAL EVENT PlMI:2R-MIN

DI'-]II'AL EVENT TIMER-RESET

DIGII.'A L .EVEN F PIXIE I{- SI<G

DIGII,'AL EVENT FIMF.R-STARI"

DROGUE DEPLOY

I.:I_S

l-.'.D S

}<I_S -POW ER

t:LS LOGIC

EVENF TIMF-RLHS XlOTOR FIRE

I.IF ['-OFF

LOCI< _UN LOCK

L V AOA/SPS PC •i. 7) '" "V ALA bPS PC .I._V ENGINE

L. V GUID

L \" R.\ I"F

Xl kin CtWrt¢ IxELI:.A,,I.

.MAIN IM<P LOY

,MAIN DEPI,OY oAUFO

M.\.qFFI< l::\'l_.Nr SEQ CONI'-ARM

.MASFI:R EVEN rSEO COX r- LOGIC

M.kSFHR EVFNT SEQ CON_-PYRO ARM

.MIk_C- LOGIC ARM

NO AUFO ABOR r!k]S F LI)G BEACON LIGIq rs

_,vRO A- RCS FUEL Dr'NIP

PYRO A-SFQ At'YRO B-RC_ FUEL DUMP .

|"fRO B-SI<Q ll

Ty pc Pane I. Lo c ato r

Lt .MDC -3

Sw (2) MDC- _oSw MDC° It,

Sw MDC- It)

Sw MDC- 1 o.

Sw MDC- 5

Indicator .MDC- i

Sw NIDC- 5Sw ,NIDC - 5

Sw (2) MDc- 15

Sw MDC°8\Vindow ,NIDC - 5

Sw ,NIDC-8

Sw MDC-8

Sw .M DC -8Sw MDC-8

Window MDc- i 1Sw M[7)C - 11

Sw .MDC- 11

Sw MDC- 1 1Sw MDC- 1 1

Sw. M DC - 5

5w MDC- lo

CB (3) _t13C-25SW XIDC-24

CB (.b XlDC '"Sw MDC -8

CB (2) MDC-25Sw M D C - 5

Lt MI]C-5

ControI MDC-5

Ind .- MDC-

Sw Xl D C - 3

Lt (8) ML)C- 5Lt M DC- 5

Lt M DC- 5

Sw ,NIDC- I o

Sw ,M I)C'- 5

Sw XIDC- I o

CB (2) MDC "

CB (1} MDC ' 'Sw (21 MDc-2.t

Sw (2) MDC-25Lt ,MDC-

CB LI.:B- 150

CB LI.:B - 1 _0

CB LI.'Iv- 150

GB LI:B - 150

SM2A-03-SC012


T ELECOMM U NIC._T IONS-- CONTROLS /DISP LAYS LOCATOR

Control/Display Name Type

INDEX

BIO- MED GOMM- MNA CB

BIO- MED COMM-MNB CB

C-BAND Sw

CENTRAL TIMING SYS-MNA CB

CENTRAL "rIMING SYS-MNB CB

FLIGHT QUAL RCI)R Sw

R CDR IHF Sw

INST 15W R CONTESSENTIAL I THRU 4 CB (4)

NON-ESSENTIAL 5 THblU 10 CB (6)

INST RUMENTS- ESS- MNA CB

INST RUMENTS- ESS-MNB CB

INST RU ME NTS- NONESS CB

INST RUMENTS- NONESS BUS CB

INST RU MENTS.- R CDR. NON ESS . CB

iNST RU MENTS-SCIEN CB

INTER.COM Sw.

INTERCOM BALANCE Sw.

NONESS BUS Sw.

POSTLANDING ANTENNA DEPLOY Sw

POWER.POWER-PMP Sw

POW ER-SCE Sw.

RECOVERY- HF- ON/OFF Sw

R_COV ERY-HF-SSt_/BCN/AM Sw

RECOV ERY-VHF. BCN Sw

S- hA ND Sw

S- BAND ANT Ind

S- BAND ANT ENNA S_

S- BAND- EMERC, S_.v

S- BAND-OSC S,,v

S- 13AND-PWI_ AMPL S,,v

S- BAND-VOICE- I_.NG/RNG ONLY _'

S. BA ND_ VOICF._TAPI_ S_'

S- BAND-VOICE_-TV Sv,

S. BAND_Xt'-_ONDER/XPONDER PW R AMPL Sw

TAPE RECORDER-F%'D/REV Sw

'TAPE RECORD_R- PLAY Sw

TAPE RECORDER- RI/_COR.I)/PLAY S_v

TAPE RECOR DER-SPI_I_]D Sw

T ELECOM- Ess Sw

T EL_.COM- NONESS Sw

T ELECOMMUNiCATIONS-GROUI' I AC CI%

TELECOMNtUNICATIONS.GROt_rl _ 2 AC CB

T EI.,ECOMMUNICATIONS-GROUP 3 CB

T FI_ECOMMUNICA_'IONS-GROUP 4 , CB

T ELECOMMUNICATIONS-GROUP 5 CB

Panel Locator

MDC - 25

MDC - 25

M DC- 20

MDC-2Z

MDC-ZZ

MDC- 19

MDC- 13, -23, -26

RHEB-204

MDC-ZZ

MDC-22

22

MDC.,22

MDCr22MDC-22

MDC- 13,

MDC- 13,

Mi_-22

MDC-,25

MDC- 13,

MDC-20

MDC-20

MDC-20

MDC-20

MDC-26

MDC-13,

MDC-lq

M DC- Z0

-.90

MDC-20

M [M3 - 20

M[)C-20

MDC-20

M DC - 2 oMDC.-20

MDC-20

M DC- 20

M DC - 20

MDC -20

M l)C - 22

_fl) C - 2 ZMDC - 22

MDC-22

M IX._ - 22

MDC -2Z

hl_ - 2,'.

-23. -26

-23, -26

-23. -26

-23, -26

Mission

TEI.ECOMMUNICATIONS--CONT[iOLS/DLSPLAYS LOCATOR INDf':x

.I-18f_asic [)ate 12 Nov I'),,._ Change Date Pail(" ......

SMEA-03-SC01/


TELEGOMMUNICATIONS--CONTROLS/DISPLAYS LOCATOR INDEX

Control/Display Nan_e Type Panel Locator

T ELECOMMUNICATIONS-PCM TL M A C CB MDC- 22

T ELECOMMUNICATIONS-SIG COND S-BAND CB MDC-ZE

PA AC

TLM INPUTS-BIOMED

TLM INPUTS-PCM

UP DATA

UP TLM CMD

VHF-AM

VHF-AM RCVR.

VHF-AM SQU_.LCH

VHF-AM- T/R/R_..C

VHF-ANTENNA

VHF-FM

VOICE RECORD

VOLUME

VOX SENS

Sw

Sw

SW

SW

Sw

S_'v

Control

Sw

Sw

SwIndicator

Control

Control

MDC - 20

MDC-20

MDG-Z0

MDC- 19

MDC-13, -23, -26

MDC-Z0

MDC-ZOMDC- gO

MDG-20

MDc-z0

MDC- 19

MDc-13, -23, -26

MDC-13, -23, -26

,%,[ i 9 9 t _,"%

TF'I.HCOMMUNICATIONS--CONTROLS/DISPLA YS I.OCATOR INDEX.

B_ic.D,Lte i: N,,_ I_b_, Change Date Page 3-19

SMgA-03-SC012


ENVIRONMENTAL CONTROL SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

Control/Display Namei,

BATTERY VENT

Cabin air control louver

CABIN AIR/AUTO/SUIT AIR

CABIN AIR FAN-.I & 2

CA;kIN PRESSURE RELIEF

CABIN REPRESS

CABIN TEMP

CABIN TEMP-AUTO

CABIN TEMP-AUTO/MAN

CO2-odor absorber diverter

CO z PP HI

DIRECT O z

DRINKING WATER SUPPLY.

A p SUIT COMPR

ECS-CABIN AIR FAN-I 8, 2

ECS-GLYCOLPUMPS-AC'I & AC 2

ECS-GLY.COL-PUMP I/PUMP 2

ECS-H20 ACCUM-MNA & MNB

ECS-PO-T H20 HTR-MNA & MNB

ECS- RADIATOR

ECS .RAD-OUTLET TEMP

ECS PAD OUT TEMP-I & 2

ECS-RAD VALVE-AC I & AC 2

ECS STEAM DUCT HTR-MNA &.MNB

ECS-SUIT COMPRESSORS-AC I & AC 2

ECS-TRANSDUCER-PRESS GROUPS I & Z

ECS-TIL4NSDUCER-TEMP-MNA _ MNB

ECS-TIL_NSDUCER-WASTE & POT H20-

MNA _ MNB

EMERGENCY CABIN PRESSURE

EVAP H20

F LO W O zFOOD PREPAIL_%TION WATER-COLD _ HOT

GAS ANAL

GLY ACCUM-QUANTITY

GLY EVAP WATER CONTROL BYPASS

GLYCOL ACCUMUbATOR

GLYCOL

GLYCOL

GLYCOL

GLYCOL

GLYCOI,

GLYCOl,

GLYCOL

GLYCOL

GLYCOL

GLYCOL

GLYCOL

EVAP-H20 FLOW

EVAP-STEAM PRESS-AUTO/MAN

EVAP-STEAM PRESS-INCR/DECR

EVAP-STEAM PRESS-TEMP IN

EVAPTEMPIN

PRESS RELIEF BYPASS-I _ 2

RESERVE

RESERVOIR-BYPASS

RESERVOIR-INLET

RESK RVOI R-OU T I.E T

TEMP LOW

Typei

Valve

Control

Sw

Sw (Z)

VMve (Z)

Val,¢e

Valve

Control

Sw

Valve

Light

Valve.

Valve

Ind

CB (6)

CB (6)

Sw (Z)

CB (z)CB (2)

Sw (4)Ind

Ind (2)

CB (4)CB (z)

CB (6)CB .(4)CB (2)

CB (2)

Valve.

Valv_

Ind

Valve (2)

CB

Ind

Valve

Valve

S%v

Sw

Sw

Sw

Valve

Valv_ (2)

Valve

Vah-e

Valve

Valve

Light

Panel Locator

RHEB-Z03

LHFEB-303

LEIB- 120

MDC-21

LHEB-307

LHEB-314

LHFEB 303

MDC- 13

MDC-13

LHEB-313

MDC-1 1

MDC-24

LHFEB-304

M DC- I 3-

MDC-22

MDC-2 _.

MDC-21

MDC-2/

MDC -22

MDC-_21 .

MDC- I 3

MDC- 19;

MDC-2!

RHEB -106

MDC-22

MDC-22

MDC-22

MDC-2Z

LHEB - 3 L.I

LtIEB- 311

MDC- 13

LItFEB- _05

MDC-22

M DC- 13

LHEB- 3 l 7

LIt E B- %12

M DC-,I 3

MDC- 1 3

M DC- 1 t

MDC- 13

LIIEB- _I1

I. HE B- %0q

LHEB- 311

I,tlEB- _07

LIIFB- _07

I_HEB- _07

M DC - 1 1

ENVIRONMENTAL CONTROL SYSTEM--CONTROLS/DISPLAY5 LOCATOR INDEX

M_',_,,n ._ .T;,._H Dat,, 12 Nov [oj,_. -(.'h,ln,,,, D_t,,_ . p,,_,,, .... }-2.0. ..........

i .

SM2Ao03-SC012




GLYCOL TO RAD

GLY EVAP-OUTLET TEMP

GLY EVAP STEAM PRESS

HlO ACCUM-AUTO/MAN

FI20 ACCUM FAIL

H20 ACCUM-ON I/ON 2

H20 ACCUMULATOR-I & 2

H20 IND

INST PWR CONT-ESSENTIAL 2

MAIN REGULATOR

02 FLOW HI

O2 PRESS IND

OXYGEN-ENTRY

OXYGEN-S/M SUPPLY

OXYGEN-SURGE TANK

PART PRESS CO 2

PGA pressure

PLSS FILL

PLVC

POST LANDING-VENT FAN

POST LANDING-VENT FANIPL BUS/FLOAT

BAG. 2

POTABLE TANK INLET

POT H_O HEATER

PRESS-CABIN

PRESS GLY DISCH

PRESS-SUIT

PRESSURE RELIEF

START/OFF /PREHEAT

Suit circuit return air

SUIT COMPRESSOR-COMPR 1/COMPR 2

Suit demand pressure regulator selectorSUIT EVAP

SUIT EVAP

SUiT EVAP GLYCOL

SUIT FLOW

SUIT FLOW RELIEF

SUIT lIT EXGH

SUIT TEST

SURGE TANK PRESSURE RELIEF

TANK PRESSURE-O2- I

TEMP-CABIN

TEklP-SUIT

WASTE H20 TK REFILL

WASTE MANAGEMI_NT-OVBD DRAIN

WASTE MANAGEMENT,SELECTOR

Type

VMve

Ind

Ind

Sw

Light

Sw

Valve (2)

Sw

CB

Valve

Light

Sw

Valve

Valve

Valve

Ind

Ind (3)

Valve

Sw

SW

CB

Valve

Sw

Ind

Ind

Ind

Valve

SwValve

Sw

Valve

Sw

ValVe

Valve

Valve (3)

Valve.

Sw

Valve

Valve

Ind

Ind

Ind

Sw

Valve

Valve

Panel Locator

LHEB-307

MDC-I 3

MDC-13

MDC-13

MDC- I i

MDC- 13

LHEB - 311

MDC- 13

RHEB-204

LHEB-314

MDG-I I

MDC- 13

LHEB-307

LHEB-30?

LHEB-307

MDC-13

PGA sleeve

LHEB-314

LHEB-316

MDC-25

MDC-25

LHEB-315

MDC-21

MDC- 13

MDC-13

I%1DC- 13

LHEB-315

LI_B-I20

LHEB-319

MDC-21

LHEB-310

MDC-13

LHE B - 311.

LHEB-311

LHFEB'300, -301,

-302

LHV.B- 311

LHEB-310

LHEB-310

LHEB- _08

MDC-13

MDC- 13

MDG- 13

MDC-13

RHEB-201

RHEB-201

ENVIRONMEN.TAL CONTROL SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

Mission Basic D,_te 12 Nov 1966 ,Chnm:e D._te Page' 3-21

SMZA-03-SC01Z



COntrol/Display Name Type

WASTE TANK INLET Valve

WASTE TANK SERVICING Valve

WATER & GLYCOL TANKS PRESSURE-

REGULATOR-SELECTOR INLET Valve

WATER & GLYCOL TANKS PRESSURE-

RELIEF-SELECTOR OUTLET Valve

WA_fER.QUANTITY ............ Ind

Panel Locator

LHEB-315

LHEB 315

LHEB-314

LHEB-314

M.DC -13

I

• I

:ia

t

t

ENVIRONMENTAL CONTROh SYSTEM--CONTROLS/DISPLAYS LOCATOR INDEX

Missiof_ .Basic Date .i_ Nox' 19f_, Change Date .... Page,, 352.2 _

SMZA-03-SC012

APOLLO OpI;ERATIONS HANDBOOK

CAUTION AND WARNING SYSTEM--LOCATOR INDEX


AC IBUS 1 FAIL

AC BUS 2 FAIL

AC BUS 1 OVERLOAD

AC BUS Z OVERLOAD

AGAP TEMP

AGC PWR FAIL

CAUT /WARN- FAIL

CAUT/WARN-MNA & MNB

CAUT/WARN-MODE

CAUT/WARN-POWER

CDU FAIL

C/M RCS A

C/M RCS B

CO 2 PP HI ._C/W

C/W

F/C

F/C

F/C

LAMP TEST

1

2

3

F/C BUS DISCONNECT

GLYCOL TEMP LOW

GMBL LOCK

G&N ACCEL FAIL

G aN ERROR

H20 ACCUM FAIL

H1 PRESSLMU FAIL

IMU TEMP

INV 1

INV 2

INV 3

MAST E P,ALARM

MASTER ALARMMASTER ALARM

MN BUS A UNDERVOLT

MN BUS B UNDERVOLT

O 2 FLOW HI

O 2 PRESSPITCH GMBL DR FAIL

S/M RCS A

S/M RCS B

S/M RCS C

s/M RCS DSPS PRESS

SPS PU SNSR FAIL

SPS ROUGH ECO

SPS WALL TEMP HI

YAW GIvlBL DR FAIL

Mission

Type

Lt

LtLt

LtLt

LtLt

CB (2)Sw

Sw

Lt

Lt

Lt

Lt-

Sw

Sw

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt.

Lt.

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

Lt

hr._ •

CAUTION AND WARNING SYSTEM--LOCATOR

Basic Date 12 Nov 1968 Change Date ,

Panel Lbcator

MDC = 11MDC-1!

MDC- 1 1MDC - 11

MDC- 10MDC - 10

MDC- 11MDG=25

MDC- I 1

MDC- 11MDG- 10

MDC- I 0MDG- 10

MDC- 11MDC- 13

MDC _23

MDC- 11MDC- Ii

MDC- 11MDC- 11

MDC- 11

MDC- 10MDC-10

MDC-10

MDC-I IMDC-10

MDC-10MDC-10

MDC-IIMDC-II

MDC-I I

MDC -3

MDC-18

LEB-103.

MDC- 11 .

MDC - 11MDC-11

MDC -10MDC- 1 1

MDG- 10MDC - I 0

MDC- 10MDC -10

MDC- I 1MDC- 11

MDC- I 0

MDC- 11

MDC-1 1

INDEX

.... Page .....3=23 ,_....

SM2A-03-SC012


MISC ELLANEOUS SYST ElvIS --CONT ROLS/DISPLAYS LOCATOR INDEX

C6ntrOls/Display Name

COUCH ATTEN- FLOODLIGHTS

ELS-FLOAT BAG 3

FLOODLIGHTS- PRIMARY

FLOODLIGHTS -SECONDARY

FLOODLIGHTS-PRIMARY

FLOODLIGHTS -SECONDARY

LIGHTING-CLOCKS

LIGHTING- FLOODS-PRIMARY

LIGHTING-FLOODS-SEC

POST LANDING-FLOAT BAG

POST LANDING-FLOAT BAG I PL ]BUS

POST LANDING-VENT FAN-'PL BUS.FLOAT

BAG Z

UPRIGHTING SYSTEM-COMPR NO. I AND

NO. Z

Type Panel Locator

CB (Z) MDC-Z5CB MDC-Z5

Sw MDC-23

Sw MDC-Z3

Sw MDC-Z6

Sw M DC -26

Sw LEB -100

Sw LE]3- i 00

Sw LEB- 100

Sw (3) MDC.25

CB MDC-Z5

CB MDC- 25

CB RHEB -ZOS

Mission

I

MISCELLANEOUS SYST EMS-CONTROLS/DISPLAYS LOCATOR INDEX

• Basic Date 12 Nov 196b ,Chanse Date .... Page. 3,"24

SMZA-03-SC01Z


SCLE NTIFIC EXPERIMENTS--CONTROLS/DISPLAYS LOCATOR INDEX

Controls/Display Name

sCIEN EQUIP SEB 1

SCIEN EQUIP SEB Z

INSTRUMENTS--SCIEN (not used)

SCIEN EQUIP HATCH

CB

CB

CB

CB

Type

Mission

Panel Locator

MDC-ZZ

MDC-ZZ

MDC-ZZ

MDc-zz

.. i

SCIENTIFIC EXPERIMENTS--CONTROLS/DISPLAYS LOCATOR INDEX

.... BaSic Date 12 Nov 1966 _Change Date Page 3"_25 .

r T

clc

n~

elr

y

S:t

rne

an

d

Cir

cu

11

P

,,wr

r C

od

e N

o.

i.oc

atr,

,n

Po

srll

un

F

un

ct;

on

I%

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ap

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er

lift

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r th

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ual

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ng

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ns

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ste

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ult

an

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cti

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ou

t-o

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nc

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uti

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au

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nd

icate

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y

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warn

ing

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lrt

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ac

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atu

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gh

ts o

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se

t to

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r~

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e a

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ase

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ly.

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ven

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igh

t lo

ses

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res

et

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cti

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rin

g t

his

ti

me

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ing

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tte

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Th

e l

igh

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erv

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ale

rt t

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cre

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n a

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rt h

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en

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qu

est

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d

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bo

rt

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mer

ger

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n

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ra

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en

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uc

at

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ab

ort

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tely

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lig

ht

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ck

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ice c

om

mu

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fro

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rou

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ulb

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re c

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lle

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y

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om

ma

nd

s th

rou

gh

th

e U

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ie

al-

tim

e c

om

ma

nd

sy

ste

m.

SP

5 s

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he

s

SP

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tte

ry

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ree

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siti

on

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gg

le s

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ch

wit

h

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bu

ses

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nd

u

pp

er

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siti

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rin

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ou

r o

pe

rati

on

all

y

den

tica

l M

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lb

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ed

to

re

turn

sw

itc

h t

o c

en

ter

(ON

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swit

ch

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TR

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p

osi

tio

n w

hen

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lea

sed

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r th

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ain

tain

ed

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en

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0 +

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wo

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r

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neu

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GN

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th

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atn

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via

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l-

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tal

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t)

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fere

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rate

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ba

ll,

wit

h r

esp

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ati

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ly.

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nd

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roll

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gh

t c

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resp

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al

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or

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e d

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ly i

n t

he

fo

llo

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g

gatr

on

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s z

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wo

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sit

ua

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cir

cu

lar

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as

on

th

e

ba

ll s

urf

ac

e d

eno

te. a

ttlt

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en

CN m

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up

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ton

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ich

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hen

cs

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n c

on

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lo

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ll

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isa

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in

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ali

gn

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err

or

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re d

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ttit

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all

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ll

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nd

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on

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pat

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aw.

resp

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tiv

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he

re

ad

ou

ts d

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on

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e

G1

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5.

+5.

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fo

llo

win

g:

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ntr

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a.

Dif

fere

nc

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tween

p

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de

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rn

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he

r th

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LN

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r t

he

S

CS

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he

re

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ts a

re

,

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fcse

nc

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rea

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cu

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lry

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i...n

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roll

r-r

ror

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h-C

b11

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ttit

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e e

rr

or

in

da

ca

tor

de

fle

cta

on

If ,.nt)

is r

efe

ren

ce

d t

o t

he

SIC

GROUP !

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I r,

r lo

r p

osi

tiv

e (

*)

rota

tio

m:

inp

ut

nsv

rqat

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a

xa

s.

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ch a

nd

A

C 1

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2 (v

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co

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r r

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GR

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G);

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2

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Ind

ica

tor

De

fle

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nd

th

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e

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DC

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xis

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tati

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on

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m Z

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er

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r d

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er

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sit

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mm

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d)

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n S

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try

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pre

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en

t S

IC r

rfe

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ltu

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pit

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sto

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WIS

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d a

de

sire

d a

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d i

nto

th

e

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pla

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h th

e A

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DE

SET f

un

cti

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en

ga

ge

d.

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led

in

an

d s

tore

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ttit

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es

ar

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refe

ren

ce

d t

o S

IC n

av

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ati

on

a

xe

s.

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h th

e d

iffe

ren

ce

an

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es

tn

ve

rte

d t

o b

od

y a

xe

s fo

r d

is-

pla

y b

y t

he

er

ro

r n

ee

dle

s.

An

gu

lar

ratr

S

IC a

ng

ula

r v

elo

cit

ies

ar

e d

ig-

'An

gu

lar

rate

in

dic

ato

r c

ali

bra

tio

n

mir

e a

ttr.

n p

lay

ed

r,y

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r fl

y-t

o-t

yp

e

rnd

i-

(fu

ll-s

ca

le d

efl

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n)

ca

turs

rnr

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ed

ab

ov

e,

to t

he

r1

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r,

f,

arid

t,

c!o

w

the

att

itu

de

M

od

es

Ro

ll

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ch

Y

aw

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rre

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nd

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to

roll

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atc

h,

an

d y

aw

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spe

ctr

ve

fy.

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nit

or

(GL

N)

*25

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65

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fS.1

'T

he

rrb

do

btn

ar

e a

lwa

ys

rrfe

r-

GL

Ne

ntr

y

sec

se

c

st

c

en

ctd

to

SIC

tcA

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ax

es

ex

ce

pt

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ntr

y

du

rrn

g a

trr.

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ph

eric

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ntr

y (

aft

er

CJ.

05

g)

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n th

r y

aw r

ate

in

di-

G

&N

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lta

V

tS 'I

65

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c

ato

r IS

re

fere

nc

ed

to

th

e S

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SC

S d

elt

a V

a

sc

a

ce

8

ec

it

at,a

lrty

a

xis

. In

pu

ts t

o t

he

rn

drc

rto

rs o

re s

up

pli

ed

by

eit

he

r C

hN

-att

co

nt

the

SC

S r

ate

py

ros

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rrrr

al)

or

SC.5

ac

t co

n1

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I*/

*lo

/ *

I*/

the

SC

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iGs

(ba

ck

up

).

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cl

ve

rt

se

c

se

c

se

c

An

gu

lar

rate

in

dic

ato

r d

efl

ec

t~o

n f

or

po

siti

ve

(4

) ro

tati

on

al

inp

ut

co

mm

an

d.

Ind

ica

tor

De

flc

c-

hx

is o

f R

eta

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n

tio

n f

rom

Ze

ro

po

siti

ve

co

mm

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d)

(ce

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r)

roll

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ft

pat

ch

UP

yaw

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ft

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emet

ry

I S

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rnc

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tl

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wer

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od

e N

o.

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uto

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6

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lly

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) tc

. i'+

m

inu

tes

and

(M

aw

-25

) 5

') j

rcu

nd

s (5

9-i

9)

are

ob

tarn

able

I

. T

he

cv

rnt

tim

rr s

tart

s a

lit~

,in

~t~

c;r

tly

rn

Lw

ntu

p o

r co

un

tdo

wn

mod

*.

whe

n li

ft-o

ff t

brr

urs

.

In i co

un

tdp

mo

de.

w

hen

59

-59

is

: re

co

rde

d,

the

co

un

ter

wll

p

roce

ed t

o 0

0-0

0 a

n0

co

ntr

nu

e r

o

cou

nl

up.

In a

. co

un

tdo

wn

mo

de.

co

r~tr

nu

ou

s co

un

tin

g r

e a

lso

av

atla

ble

.

L'V ,

UT

E i

~~

ht

n

lur

nl~

trn

red

iu

in

drc

atr

that

E

DS

- 1.

3

Ba

tte

ry

BSO

OLO

X

'Whe

n u

sed

rn

coaj

un

ctro

n w

rlh

rh-

the

pe

rmis

sib

le *

ng

ulr

r ra

tes

rn

BA

T A

b

use

s A

an

d

(hu

nc

h

ang

le-o

f-at

tack

d

isp

lay

an

d t

he

htl

i-

any

of

prt

ch.

roll

, o

r ya

w a

xe

s B

AT

B

B w

hen

th

e v

ehic

le

tud

e e

rro

r re

adin

g o

f th

e F

DA

I,

w~

ll

ho

ve

bee

n e

xce

eded

. R

ate

s in

(M

DC

-25

) EDS POWER

rate

rn

drc

ate

the

ne

ce

ssit

y for m

;r11

ua1

,cnc

emm

of

20

de

gre

esl

sec

on

da

in

sw

itch

e

xc

ess

ive

a

bo

rt t

nit

iatt

on

. T

he

lig

ht

als

o

. . 'r

oll

and

5 d

eg

ree

sfse

co

nd

In.

(M

OC

-24

) A

) ,l

lum

inat

ecc.

wh

en a

n a

uto

ab

ort

is

pit

ch o

r y

aw i

llu

min

ate

(he

rale

'

IS

O

N.

init

iate

d b

ecau

se o

f excessiv

e ra

tes.

Ir~

ht.

L.'

Y C

UD

~a

~h

r

Rlu

nrn

ate

r. r

ed

tn

in

dic

ate

pk

t-

. BS

OO

jbX

form

fa

lure

In

th

e L

I V g

uid

ance

( L

a .mc h

. 'v

ehic

le

mys

tern

(lo

ss o

f at

titu

de

con

tro

l).

:gu

idan

ce

,fa

il A

) --

-

-

LIV E

NG

INE

S l

rgh

ts

All

en

grn

e li

gh

t8 a

re y

ello

w.

L#

ht SG. 1

D

lum

rnat

ea t

o r

nd

rcat

e. S

-IB

or

BS

0030

X

Th

e li

ghts

are

use

d t

o r

nd

icat

e st

ag

-

5-1

VB

en

grn

e Fh.

1 o

per

atin

g

( En

gin

e tn

g a

nd

th

e. n

ec

ere

ity

fo

r in

itia

lin

g a

.bel

ow 9

0 p

erce

nt

of t

ota

l th

rust

,

:NO

. 1

ou

t m

anu

al a

bo

rt w

hen

tw

o S

-IB

rn

~:n

rs

cap

abiJ

tty

. A

) a

re o

pe

ratr

ng

bel

ow

90

prr

crn

t of

b

thru

st.

Whe

n en

able

d i

n t

he

auto

L~

gh

t ?:G.

2 ~

lum

tmte

n. to

:n

d~

ca

te 5-I

B

BS

0032

X

abo

rt m

ode,

an

au

tv a

bo

rt u

.111

be

eng

tnc

NG

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op

erat

tng

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elo

w 9

0

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gin

e I

init

rate

d ~

7t

h

two

en

gin

es b

eio

w 90

per

cen

t uf

tu

tal

thru

st c

a~

ab

~li

ty.

No.

2

our

per

cen

t of

th

rust

. a

Ltg

ht

Pic.

3

Illu

mrn

ates

to

~n

dic

ate

S-IB

' BS

0034

X

en

g~

ne

!So.

3 o

per

atin

g.

bel

ow

90

,(

En

gin

e

pex

cen

t of

t

~t

al

th

rust

cap

abil

ity

. i

'NO

. 3

ou

t A

)

Li~

ht tb

. 4

~Il

lum

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ste

s

to r

nd

icat

e S

-IJ3

B

SOO

36X

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ien

grn

c N

o.

4 o

ptn

tin

g. b

elo

w 9

0

:(E

ng

ine

pe

rcrn

t ~

f to

ta!

thru

st c

ap

ab

il~

ty.

'No.

3

ou

t A

)

----. -

, I T

ele

rnrt

ry

~.

t .:

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cu

it

P.,

urr

C

od

e N

u.

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ron

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rea

ke

r S

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rce

an

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den

trty

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1 :l

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rn:~

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tt

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ery

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ep

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tin

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clo

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0

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T A

h

usc

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d

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e

perc

en

t o

f to

tal

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ap

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~ll

ty.

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T B

B

wh

en t

he

N

o.

5 o

ut

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c-2

s)

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OW

ER

L

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ht N

o.

b Il

lum

rna

tes

to ~

nd

ica

tc S-I

B

swit

ch

B

S0040X

e

ng

ine

No.

h

op

era

tin

g b

elo

w 9

0

(MD

C-2

4)

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gin

e

pe

rce

nt

of

tota

l th

rust

cap

ab

ilit

y.

is O

N.

No.

6

.ou

t A

l

I.lq

ht

Nu.

7

Illu

mrn

ate

s to

~n

dic

ate

S-I

B

BSO

O4L

X

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ng

ine

No.

7 o

prr

ati

ng

\,c

law

90

(E

ng

ine

pv

rcrn

t of

tcjt

~1

thru

st c

ap

ab

~li

ty.

No.

7 o

ut

A)

Illr

~m

rna

tes to

Lndic

ate

S-I

R

BS

0044X

en

gin

e N

o.

6 o

pe

rati

ng

bel

ow

90

(E

ng

ine

pe

rce

nt

of to

tal

thru

st c

ap

ab

ilit

y.

No.

8 o

ut

A)

,

LIF

T-O

FF

an

d N

O A

UT

O

BSO

O6O

X

Th

e L

IFT

OF

F/N

O A

UT

O A

BO

RT

B

S0061X

sw

itc

h/l

igh

t co

mb

inati

on

sh

ou

ld b

e

(Lif

t-o

ff

pre

sse

d i

f th

e L

IFT

OF

F l

igh

t d

oe

s si

gn

al

A I B

: not

illu

min

ate

at

lift

off

. (R

efe

r to

m

alf

un

cti

on

pro

ce

du

res,

.

I Th

e re

lay

co

ntr

oll

ing

th

e w

hit

e li

gh

t is

re

se

t 5

sec

on

ds

aft

er

lift

-off

by

a

tim

er

in t

he

LIV

in

stru

me

nta

tio

n u

nll

None

Th

e a

stro

na

ut

wil

l p

res

s t

he s

wit

ch

- li

gh

t w

hic

h. w

ill

ele

ctr

ica

lly

en

ab

le

I th

e L

V-E

DS

au

tom

ati

c a

bo

rt s

yst

em

. If

the

lig

ht

sti

ll d

oe

s n

ot

go o

ut,

it

in

dic

ate

s th

at

on

e o

r b

oth

of

the

du

al

I re

du

nd

an

t E

DS

sy

ste

ms i

s n

ot

en

ab

led

. In

th

is e

ve

nt,

th

e c

rew

m

ust

be

pre

pa

red

to

in

itia

te a

man

ual

a

bo

rt,

if. n

ec

ess

ary

.

CD

OkO

IX

LE

IPc

m

oto

r fi

re

init

iate

A

CD

OIO

ZX

L

E/P

c

mo

tor

fire

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e L

ES

nro

tor

is n

orm

all

y (

au

to-

ma

tic

all

y)

fire

d a

pp

rox

ima

tely

Oi

1

seco

nd

by

th

e M

ES

C f

oll

ow

infi

ab

ort

in

itia

tio

n.

It m

ay

be

use

d f

or

a b

ack

u

p f

or

the

je.t

tiso

n m

oto

r o

nly

aft

er

no

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mea

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of

TW

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ett

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as

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ed

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his

is

ass

um

ing

th

at t

he

L in

itia

te B

T

WR

se

pa

rati

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nu

ts a

re f

rac

ture

d.

I

Nar

ate

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uit

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ca

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un

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ack

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to d

ep

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e

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att

ery

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r.n

t)

ca

na

rd w

hen

it

do

es

no

t d

eplo

y

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EN

T5

b

use

s A

an

d

au

turn

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ca

lly

du

rin

ga

n a

bo

rt.

SE

O C

ON

T-

B

A A

Wd

B.

BA

T A

B

AT

B

AD

AP

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wit

ch

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wit

ch

fo

r n

orm

al

CS

M/S

-IV

B

- E

MD

C-2

2)

sep

ara

tio

n a

fte

r th

e a

sc

en

t p

ha

ac

of

the

mis

sio

n,

(Re

fer

to a

da

pte

r se

pa

rati

on

mecha-

nis

m i

n s

ec

tio

n 2

.)

b.

Bac

ku

p s

wit

ch

fo

r C

SM

.,'S-I

VB

se

pa

rati

on

if

rt d

oe

s not

se

pa

rate

au

tom

ati

ca

lly

du

rin

g

an

SPS a

bo

rt.

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fer

to S

PS

a

bo

rt p

roc

ed

ure

s. )

.

h

z 0

AP

EX

COVER JETT s

wit

ch

B

ack

up

sw

itc

h t

o j

ett

iso

n t

he

ELS A

- ti.

C/M

ap

ex

co

ve

r.

BA

T A

-

i! F

LO

AT

B

AG

3

4

ELS B

-

0" BAT B

5 (M

DC

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r

m

I D

RO

GU

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EP

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wit

ch

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ack

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itch

. to

de

plo

y t

he

9 d

rog

ue

pa

rac

hu

tes.

z I

m

t- lm

hX

IN D

EP

LO

Y s

wit

ch

B

ack

up

sw

itc

h t

o d

ep

loy

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ma

in p

ara

ch

ute

s.

Co

de N

o.

and

Id

en

tity

R

em

ark

s

CD

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P

ush

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pe

sw

itch

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he

ca

na

rd u

sill

C

DC

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n

orm

all

y (

au

tom

ati

ca

lly

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eplo

y

I I

Ca

na

rd

sec

on

ds

aft

er

a L

FS

ab

ort

in

itia

tar;

n.

dep

loy

A

an

d B

CD

Ol Z

SX

Ad

ap

ter/

S

M s

ep

ara

te

init

iate

A

CD

Of

26X

A

da

pte

r/

SM

se

pa

rate

in

itia

te B

CD

O23

0X

Fo

rwa

sd.

he

at

shie

ld

jett

iso

n A

C

D0

23

1X

F

orw

ard

h

ea

t sh

ield

je

ttis

on

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CE

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rog

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lose

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CE

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Dro

gu

e

dep

loy

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lose

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lay

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00

03

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Main

pa

ra-

ch

ute

de

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-dro

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e

rele

as

e

rela

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cJ

30

00

4x

M

ain

pa

ra-

ch

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dep

loy

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re

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re

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Pu

sh-t

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to s

ep

ara

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a

da

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r w

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SF'

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no

t b

e in

itia

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wit

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he

co

mm

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rs t

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co

ntr

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S

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e a

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ng

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b

e m

an

ual

fun

cti

on

s.

Pu

sh-t

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e s

wit

ch

to

je

ttis

on

th

e C

/M

ap

ex

co

ve

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th

e a

uto

ma

tic

sy

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fail

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ng

an

ab

ort

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ea

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g

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er

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he

dro

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ara

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l n

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y (

au

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er

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24.

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s a

lso

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d t

o i

nit

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nu

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men

t o

f th

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ain

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rin

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lem

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bu

tto

n sw

itc

h

(dia

led

in

) a

ttit

ud

e s

ett

ing

s G

RO

UP

1

bu

s A

or

?

wh

ich

mu

st be

he

ld e

ng

ag

ed

un

til

into

th

e S

CS

fo

r al

ign

nh

ent

.MN

A

ali

gn

me

nt

is c

om

ple

ted

. c,

i th

e p

res

en

t S

IC r

efe

ren

ce

M

N B

a

ttit

ud

e s

tore

d i

n t

he

AG

CU

(M

DC

-25

) S

CS

AGCU a

lig

pm

en

t s

lew

ra

les

to

th

e d

es

ire

d r

efe

ren

ce

a

ttit

ud

e.

roll

-

LO

'lse

c

h.

Ve

co

up

les

no

rma

l S

CS

Rh

fAC

. p

itch

-

5'l

sec

in

pu

ts t

o t

he

AG

CU

a

nd

th

e

ya

w

- 5

'lse

c

BM

AG

S a

re f

ree

xy

ros

un

til

the

sw

~t

~h

is

re

lea

sed

. P

erf

orm

th

e F

DA

I/A

GC

U a

lig

n

c.

hll

gn

s t

he

FD

A1

alt

itu

de

ba

ll

fun

cti

on

. to

th

e d

iale

d-i

n a

ttit

ud

e,

I re

fere

nc

ed

to

SIC

nav

igat

ior.

1

ax

es

, in

SC

S f

lig

ht

mo

de

s I

on

ly.

i

I

OF

F

Te

lem

etr

y

Na

me

an

d

Cir

cu

it

Po

we

r C

od

e N

o.

Lo

ca

t~o

n

Po

s&ti

on

F

un

cti

on

S

ou

rce

a

nd

Id

en

tity

R

em

ark

s B

rea

ke

r

?,?P

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AT

T S

ET

rw

icc

-h

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S-

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in

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nc

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r. a

tt~

l~~

alc

sc

t h

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<

tio

n \

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1,

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nt)

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s A

or R

cnab

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a S

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cil

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r 11

, 3 #

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p)

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thr

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de

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fer-

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led

in

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it

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t.

is

,~

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L. f

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rnc

t. ;

angl

e.-s

to t

he

FD

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~I

II

-

MN

B

SC

S f

l5p

tlt

mo

des

or11

y.

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r ~

lca

:~.c

cl

tud

e e

rr

or

in

drc

alo

rs,

(MD

C-2

5)

atta

ttld

c 1s s

ch

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vrc

l by

Ily

inc

*,t

~t lf

it

.

rert

rrc

nrp

d t

o S

/C b

ody

ax

es,

a

ttit

ud

e e

rro

r nc

t.cl1

r.s.

11

sir1

): 1)

1c

b.

Da

co

up

les

no

rma

l S

CS

B~

AG

ro

tati

on

co

nlr

irl.

:n

pu

ts

to t

he

FD

A1

att

itu

de

e

rr

or

in

dic

ato

rs.

(BM

AG

s c

on

tin

ue

to

op

era

te n

orm

all

y

oth

erw

ise

. )

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ibit

s tn

e a

ttit

ud

e s

et

fun

cti

on

.

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BA

L P

OS

ITIO

N g

rou

p

Pro

vid

es

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pla

y a

nd

ma

nu

al

SC

S-

A-C

bu

s

co

ntr

ol

of

gim

ba

led

SPS e

ng

ine

C

RO

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1

No.

1 o

r

thru

st

ax

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ori

en

tati

on

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h

AC

J &

AC

Z

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. Z

res

pe

ct

to S

IC b

od

y a

ne

s.

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OU

P Z

.

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CI

LA

C2

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MD

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rov

ide

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gin

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imb

al

(via

ya

w

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35

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in

dic

ato

r a

nd

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um

bw

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el

ar

e

ind

bc

ato

rs

posi

tion.

rea

do

uts

wit

h r

es

pe

ct

an

d p

ltc

h

(.p

itch

GPI

ca

lib

rate

d i

n 0

.5.

inc

rem

en

ts f

rom

to

S/C

ya

w a

nd

pit

ch

(b

od

y)

EC

As

1 a

mp

de

mo

d

-3.

to C

13'.

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nte

r re

ad

ing

of

t4'

ax

es.

re

spe

cti

ve

ly.

ou

t )

co

rre

sp

on

ds

to

ya

w ~

imh

al p

osi

tio

n

nu

ll.

du

e t

o e

ng

ine

off

set

for

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ITC

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Pro

vid

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an

ua

l y

aw a

nd

pit

ch

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isp

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on

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itc

h i

nd

ica

tor

an

d t

hu

mb

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ee

l a

re

th

um

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he

els

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np

ut c

om

ma

nd

s to

re

spe

cti

ve

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GA

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CA

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ali

bra

ted

in

0.5

. ~

nc

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en

ts fr

om

en

gin

e g

imb

al

po

siti

on

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erv

os

-9.

to t9'.

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nte

r re

ad

ing

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0'

for

ali

gn

me

nt

of

SP

S e

ng

ine

c

orr

esp

on

ds

10 o

itc

h g

imb

al

po

sill

on

thru

st

ax

is t

hro

ug

h S

IC

CG

, n

ull

. p

rio

r to

SP

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hru

stin

g.

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um

bw

he

el

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pla

ce

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nt

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rim

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f g

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al

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siti

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s b

y u

se

po

stli

ve

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rec

tio

n wil

l p

rov

ide

o

f th

e t

hu

mb

wh

ee

ls i

s p

oss

ible

u,h

en

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rela

tiv

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osr

tiv

e g

imb

al

pe

rfo

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g MTVC.

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up

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irc

uit

p

oa

itio

n i

nd

ica

tor

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pla

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i-

pro

vid

es

po

we

r to

MT

VC

c r

rcu

its.

c

att

ng

no

zz

le p

os

~tl

ori

ng

fur

a

po

siti

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d

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pla

ce

me

nt w

he

n

thru

st i

s i

nit

lare

d.

. ,

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Te

lem

etr

y

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ri~

t-

and

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irc

uit

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or

er

C

od

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o.

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nc

tio

n

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ak

er

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urc

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and

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en

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osi

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DII

IEC

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UL

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CE

sw

ttrh

P

rov

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ack

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bil

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ma

tn

Non

e M

om

en

tary

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nta

ct

pu

shb

utt

on

lnit

irti

ng

ull

ag

e (

+X

tra

nsl

ati

on

) D

IRE

CT

b

us

A o

r B

swit

ch

wh

ich

mu

st b

e h

eld

en

gag

ed

pri

or

to S

PS

bu

rns-

C

ON

T

un

til

ull

ag

e i

s c

om

ple

ted

. M

N A

a.

~n

er

hlz

es

inje

cto

r v

alv

e

MN

B

Tra

nsl

ati

on

co

ntr

ol

pro

vid

es

no

rma

l

dir

ec

t c

oil

s of

fo

ur

+X

SM

(M

DC

-25)

c

ap

ab

ilit

y f

or

init

iati

'ng

ull

ag

e.

RC

S e

ng

ines.

b.

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en

ga

ge

s a

uto

ma

tic

at!i

- tu

de.

ho

ld c

ap

ab

ilit

y i

n p

itch

a

nd

yaw

ax

es.

ItiR

US

T O

N s

wit

ch l

igh

t a.

S

wit

ch

ac

tua

tio

n a

pp

lie

s m

an

ua

l S

PS

en

gin

e t

hru

st-o

n

GR

OU

P I

log

ic c

om

ma

nd

to

SC

S

MN

A

illu

min

ati

on

.

b.

Sw

itch

fa

ce

ill

um

inati

on

. C

H43

ZL

X

Sw

itch

fa

ce

do

es

no

t in

dic

ate

ap

pli

- (S

PS

so

len

oid

c

ati

on

of

thru

st o

nlo

ff c

orn-

man

ds v

ia

ind

ica

tes

ap

pli

ca

tio

n o

f SPS

en

gin

e t

hru

st-o

n s

ign

al

fro

m

con

Lro

l v

alv

e

the N

OW

L/O

FF

/DIR

EC

T

ON

e

ne

rgiz

ed

) sw

itch

(M

DC

-7).

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&N

sy

ste

m o

r T

HR

US

T O

N

ow

itch

to

SC

S e

lec

tro

nic

s:

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ht

is e

xti

ng

uis

he

d w

hen

SPS e

ng

ine

th

rust

-off

si

gn

al

fro

mG

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' sy

ste

m. AV

RE

MA

ININ

G c

ou

nte

r,

or

flig

ht

co

mb

ust

ion

sta

bil

ity

m

on

ito

r is

de

tec

ted

in

SC

S

Sw

itch

. is

a t

hre

e-p

osi

tio

n i

ev

er-

loc

k

SC

S-

DIR

EC

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tog

gle

sw

itch

. T

o s

et

the

sw

itc

h i

n

the

NO

RM

AL

po

siti

on

cr t

he

DIR

EC

T

CO

NT

NO

R M

A L

En

ab

les

cir

cu

it c

ap

ab

ilit

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or

ON

po

siti

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ul

l

the

le

ve

r o

ut

pa

st

MN A

en

erg

izin

g o

f'S

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fu

el a

nd

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i-

MN B

th

e l

ev

er

loc

k [

sho

uld

er

sto

p)

and

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ve t

he

le

ve

r u

p a

nd

dow

n.

reo

pe

c-

diz

er

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ntr

ol

sole

no

ids

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ith

er

(MD

C-2

5)

tiv

ely

. T

he

in

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ht

po

siti

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AG

C o

r T

HR

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wit

ch

sw

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OF

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ce

nte

r) p

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li,

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vid

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er

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pli

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h.

DIR

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osi

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i b

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f b

yp

ass

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th

rust

on

lo

gic

c

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uit

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d i

nit

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SP

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ng

ine

fi

rin

g d

ire

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OF

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lern

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y

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rea

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a 51

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er

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e P

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el

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r A

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on

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en

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T

Te

lem

etr

y

Nam

e and

Cir

cu

it

Po

we

r C

od

e N

o.

Fu

nc

tio

n

Bre

ak

er

So

urc

e

and

Id

enti

ty

Re

ma

rks

Lo:

atro

n P

os

~t~

on

atnc

-n

hf I

N

Se

lec

ts m

bn

imu

m d

ead

ban

d o

f SCS-

D-C

ma

in

Non

e M

inim

um

dea

db

and

1s

use

d o

nly

wh

en

[Co

nt )

.O

.L*.

G

RO

UP

1

bu

ses

A o

r

tig

ht

atti

tud

e c

on

tro

l is

re

qu

ire

d;

h4N

A

B

e,. g

.,

du

rin

g n

avig

atio

nal

sig

hti

ng

s

I M

N B

an

d p

rio

r to

an

dd

uri

ng

aV

ma

ne

uv

ers

.

(MD

C-2

5)

No

po

wer

to

th

is s

wit

ch

du

rin

g SCS

or

G&

N e

ntr

y m

od

es:

the

refo

re,

min

imu

md

ea

db

an

d c

an

no

t be

sele

cte

d d

uri

ng

en

try

.

ilA

TE

GY

RO

mw

ltch

cs

Pro

v~

de

ma

nu

al

ca

pa

bil

ity

to

T

he

se s

wit

ch

es

pla

ce a

ny

or

all

. of

pla

ce t

he

ro

ll,

pit

ch,

or

yaw

th

e B

MA

Cs

in b

ack

up

ra

te m

od

e o

f

BM

AG

in

th

e b

ack

up

ra

te m

ode.

~

pe

rati

on

~s

o

that

th

ey

ma

y b

e u

sed

of o

pe

rati

on

. in

pla

ce o

f: th

e r

ate

gy

ros

to p

rov

ide

spa

ce

cra

ft r

ate

sta

bil

iza

tio

n.

In

RO

LL

ad

dit

ion

, w

ith

an

y o

ne

of t

he

RA

TE

G

YR

O s

wit

ch

es

in t

he

BM

AG

po

siti

on

NO

R.M

AL

A

llow

s. n

orm

al

I3M

P.G

an

d r

ate

an

d, a

ny

on

e of

th

e fo

llo

win

g s

ele

cte

d.

gy

ro o

pe

rati

on

. , t

he

rem

ain

ing

tw

o B

MA

Gs

wil

l a

uto

- m

ati

ca

lly

ass

um

e t

he

bac

ku

p r

ate

P

mo

de

of o

pe

rati

on

: .0

5G

EN

TR

Y

0

HW

4G

En

ab

les

Bh

lAG

ra

te- m

od

e of

o

pe

rati

on

re

mo

vin

g r

ate

gy

ro

swit

ch t

o .

05

C E

NT

RY

po

siti

on

. s

sig

na

l fr

om

ra

te i

nd

ica

tors

, e

tc.

mo

nit

or

mo

de

sele

cte

d.

GL

N a

ttit

ud

e

9

co

ntr

ol

mo

de

se

lec

ted

, m

inim

um

z

imp

uls

e a

ttit

ud

e c

on

tro

l m

od

e u

PIT

CH

.

eng

aged

. C

&N

en

try

mo

de

sele

cte

d.

NO

RkW

L

All

ow

s n

orm

al

Bh

UG

an

d r

ate

e

ith

er

rota

tio

n c

on

tro

l o

ut

of

gy

ro o

pe

rati

on

. n

eu

tra

l p

osi

tio

n. SCS l

oc

al

ve

rtic

al.

o

r o

ne SCS c

ha

nn

el

dis

ab

led

wh

ile

in

SC

S a

ttit

ud

e c

on

tro

l m

od

e.

9

RM

AG

E

na

ble

s B

MA

C r

ate-

mode o

f 'o

pe

rati

on

, re

mo

vin

g rate g

yro

2

-sig

na

l fro

m r

ate

in

dic

ato

rs.

etc

.

YA

W N

OR

WL

A

llo

ws

no

rma

l B

MA

G a

nd

ra

te

. W

hen

in a? SCS m

od

e,

the

att

itu

de

gy

ro o

pe

rati

on

. '

refe

ren

ce

ca

pa

bil

ity

is

lo

st w

hen

an

y

on

e of

. th

e B

MA

Gs.

is

in

bac

ku

p r

ate

!

B W

4G

E

nab

les

BM

AG

ra

te m

od

e o

f m

od

e.

Att

itu

de

info

rma

tio

n i

s m

ain

-

op

era

tio

n,

rem

ov

ing

ra

te g

yro

i

tain

ed i

f o

pe

rati

ng

, in

a G

&N

mo

de.

..

,

sig

na

l fr

om

ra

te i

nd

icat

orb

. e

tc.

. 0%

E

ST

RY

sw

ltc

h

En

ab

les

the

SCS f

or

atm

osp

he

ric

.0

5C

EN

TR

Y s

wit

ch

is

eff

ec

tiv

e o

nly

fli~

t.t d

ur~

ng

en

try

an

d. a

fte

r w

hen

a G

LN

or

SC

S e

ntr

y m

od

e is

0. o

sgs

sele

cte

d.

. OiC

EN

TR

Y

A.

Re

mo

ve

s a

ttit

ud

e e

rro

r A

fte

r .0

5G

EN

TR

Y p

osi

tio

n i

s

s~

gn

als

fro

m p

~tc

h an

d y

aw

sele

cte

d,

pla

cin

g a

ny

on

e o

f th

e

f ha

nn

els

In

G&

N m

od

e an

d

BM

AG

s in

ba

ck

up

ra

te m

od

e w

ill

p18c

h.

yaw

., an

d r

oll

ch

an

ne

ls

au

tom

ati

ca

lly

pla

ce

all

BM

AG

s In

1 ~

n S

CS

mo

de

s.

bac

ku

p r

ate

mo

de

co

nfi

gu

rati

on

. T

hlq

OF

F

Te

lem

etr

y

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c,.

r ax

.., C

irc

uit

Powc r

Co

de

No.

c... ..!a

,r r.,

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F

uc

cl~

on

B

rea

ke

r S

ou

rce

an

d l

den

tity

R

em

ark

s

Sl:>l- w

L

. In

cre

ase

s th

e ra

te d

ead

ban

d

SC

S-

'D-C

ma

in

Non

e re

sult

s rn

lo

ss o

f F

DA

1 to

tal

att

itu

de

1 .n

t)

fr

om

0.2

. p

er

se

c t

o 2

' p

er

CR

OU

P I

b

use

s A

or

dis

pla

y,,

oth

erw

ise

, to

tpl

att

itu

de

SCC.

PAN

. A'

B

dis

pla

y i

s p

rov

ided

,.

c.

En

erg

rzrs

a c

rrc

uit

wh

rch

?A

N. B

c

ou

ple

s a

co

mp

on

ent

of t

he

(M

DC

-25

) D

uri

ng

en

try

th

e S

/C i

s m

an

eu

vere

d

roll

ra

te .

rgnaI

rn

to t

he y

aw

abo

ut

the

sta

bil

ity

ro

ll a

xis

ra

the

r c

ha

nn

el.

th

an t

he

bo

dy

ro

ll a

xis

. C

on

seq

uen

tly

th

e y

aw r

ate

gy

ro g

en

era

tes

an

O

FF

A

llo

rcs

no

rma

l sy

ste

m o

pera

tro

n.

un

de

sira

ble

ra

te s

rgn

al.

B

y c

ou

pli

ng

a

co

mp

on

ent

of

the r

oll

sig

na

l in

to

the

yaw

ch

ann

el.

the

un

de

sira

ble

ai

gn

al i

s c

an

ce

lle

d.

LCL V

ER

T s

u,t

ch

E

nab

le.

5C

S f

or

loc

al

ve

rtic

al

CH

.110

3X

. Th

e l

oc

al

ve

rtic

al

mo

de

ma

inta

ins

mo

de o

pe

rati

on

. (S

CS

lo

ca

l th

e S

/C a

ttit

ud

e w

ith

re

spe

ct

to th

e

ve

rtic

al

ea

rth

s lo

ca

l v

ert

ica

l.

mo

de

LC

L V

EH

T (

up

) S

ele

cts

. SC

S l

oc

al

ve-r

tlcal

mo

de

co

ntr

ol)

W

ith

.lo

cal

ve

rtic

al

mo

de e

ng

ag

ed

, a

n

wh

en u

sed

rn

co

nju

nctr

on

mth

o

rbit

ra

te s

ign

al

eq

uiv

ale

nt

to p

itch

. C

L-N

ISC

S s

wit

ch

an

d A

TT

ITU

DE

/ ra

te o

f a

pp

rox

ima

tely

4.

1

pe

r M

ON

ITO

R/E

NT

RY

sw

itch

. m

inu

te i

s ap

pli

ed

to

th

e p

itch

BM

AC

to

rqu

e m

oto

r.

Th

is f

igu

re i

s f

or

a

Dis

eng

ages

lo

ca

l v

ert

rca

l m

od

e.

10

0 NM e

art

h o

rbit

. F

DA

1 t

ota

l a

tti-

tu

de

is r

efe

ren

ce

d t

o l

oc

al

ve

rtic

al.

A

ttit

ud

e e

rro

r v

alu

es

rep

rere

nt

de

vi-

a

tio

n f

rom

se

lec

ted

lo

ca

l v

eri

ica

l a

ttit

ud

e.

If th

e S

IC i

s m

an

eu

ve

red

aft

er

loc

al

ve

rtic

al

mo

de i

s s

ele

cte

d,

the

4.

1.

pe

r m

inu

te.

orb

rt r

ate

mig

nal

pre

- v

iou

sly

ap

pli

ed

on

ly t

o th

e p

itch

gy

ro

wil

l be

ap

pli

ed

to

all

th

ree

gy

ros.

T

his

is

ac

co

mp

lish

ed

by s

um

min

g

and

re

solv

ing

tir

e n

ew s

tep

pe

r m

oto

r p

osi

tio

n o

utp

uts

wit

h t

he o

rbit

al

rate

si

gn

al

in t

he n

av

-to

-bo

dy

tra

nsf

orm

a-

tio

n c

irc

uit

s.

AV

mw

ttch

E

na

ble

s S

CS

fo

r C

LN

or.

SC

S

CH

OlO

OX

T

his

sw

itc

h w

ork

s in

co

nju

ncti

on

wit

h

JV

mo

de

op

era

tio

n o

r M

TV

C.

(GL

NA

V

the G

&N

/SC

S sw

itc

h a

nd

th

e A

TT

I-

mo

de)

TU

DE

/MO

NIT

OR

/EN

TR

Y

swit

ch

. ,A

pp

l~e

r a.a

ign

a1

to

th

e S

CS

M

TV

C i

s a

ctu

ate

d o

nly

wh

en t

he A

V

ele

ctr

on

~c

s en

ab

lrn

g t

he

sy

ste

m

CH

lIOO

X

swit

ch

is

in

th

e A

V

po

siti

on

an

d w

hen

fo

r J

V m

od

es

of o

pe

ratr

on

an

d

(5cA

V m

od

e)

the

tra

nsl

ati

on

co

ntr

ol

is r

ota

ted

CW

. a

lso

em

ble

m m

an

ua

l th

rust

M

TV

C i

s in

dep

en

den

t of

CL

N/S

CS

v

ec

tor

co

ntr

ol

(MT

VC

), o

f th

e

CH

lIO

4X

swit

ch

. tr

an

sla

tro

n c

on

tro

l SW

sw

itch

[M

TV

C

rs c

lose

d.

mo

de

) In

th

e A

V p

osi

tio

n.

DC

po

wer

is

ap

pli

ed

to

th

e F

CS

M-G

LN

'an

d F

CS

M-

I SC

S rw

itc

he

s IM

DC

-2).

SMZA-03-Sc012


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le

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I3II

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OL

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S-

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ain

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one

CIM

RC

S

B&

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OL

L

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ses

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r

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itch

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un

cti

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ng

ine

On (

UP

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pp

l~e

s tL

8 v

dc

to t

he

no

rrn

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hlN

A

B

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cto

r v,t

lva

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no

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and

M

N

B

BL

D R

OL

L

Ro

ll r

igh

t A

9.

B11

sole

no

id r

l rlv

er

ele

ctr

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ics,

~

nd

B

&D

RO

LL

R

oll

le

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10

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rma

l I<

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gln

e G

RO

UP

1

Pit

ch

up

A

l.

B3

PIT

CH

.

op

er.

~ti

on

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N A

an

d

Pit

ch

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wn

A

Z.

64

P

lTC

H

MN

B

Y

AW

Y

aw ri

gh

t A

5.

B7

Rem

ov

es

tZ8

vd

c Ir

on

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e

(MD

C-2

5)

YA

W

Yaw

le

ft

A8.

B6

OF

F

no

rnla

l in

jec

tor

valv

e s

ole

no

ids

and

th

e d

riv

er

sole

no

id a

mp

li-

AC

ro

ll s

wit

ch

is a

pp

lic

ab

le t

o S

/M-

fie

r.

Inh

ibit

s n

orm

al

man

ual

RC

S e

ng

ines

on

ly a

nd

pro

vid

es

no

rot.

atio

n c

on

tro

l cap

ab

ilit

y a

nd

fu

nc

tio

n a

fte

r C

MlS

M s

ep

ara

tio

n.

0

5C

S a

uto

nm

tic c

on

tzo

l of

R

CS

0

en

gin

e o

pe

rati

on

. z c3.

scs-

T

he

se

sw

.itc

hes

are

use

d t

o d

isa

ble

20

PIT

CH

th

e R

CS

en

gin

es'

in U

le e

ve

nt

of

a r

nal-

O

Ap

pli

es

t28

vd

c to

th

e n

orn

~a

l MN A

fu

nct

ion

or

wh

en

ev

er

it m

ay

be

op

era

-

inje

cto

r v

alv

e s

ole

no

idh

an

d

MN

B

tio

nall

y d

esi

rab

le;

e.

g.,

SIC

fre

e d

rif

sole

no

id d

riv

er

ele

ctr

on

ics.

an

d

for

pu

rpo

ses

of p

rop

ella

.nt

co

nse

rvati

on

: '

allo

win

g n

orm

al

RC

S e

ng

ine

GR

GU

P 1

z

op

era

tio

n.

MN

A a

nd

D

ire

ct

co

ntr

ol

of t

he

RC

S i

s a

va

ila

ble

, M

N

B

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urc

e

an

d I

de

nti

ty

Re

ma

rks

11

DC

- I

3

OL

yr

o~

~p

E

SS

EN

- S

/M I

NS

T

ICc.

nr)

'I

'IA

L-3

PWR D

IST

In

41

c.rt

or

I D

~s

pla

ys

prc

ss

urr

of

02

tan

k

(RH

t:R

20

4)

SF

00

37

P

Wit

h 02 PRESS I

ND

sw

itc

h a

t. T

AN

K

No.

I o

r E

CS

su

kg

e t

an

k a

s

an

d f

usc

in

(P

res

s 0

2

1,

the

in

dic

ato

r fu

nc

tio

n i

s c

on

- se

lec

ted

by

02

PR

ES

S I

ND

S

IM

tan

k N

o.

1 tr

oll

ed

by

a p

res

su

re t

ran

sa

uc

e.~

sw

ltc

h (

MD

C- 13) a

nd

IS

use

d a

s

loc

ate

d i

n 0

2 ta

nk

No.

1

ou

tle

t I

~n

e.

foll

ow

s:

CF

00

06

P

Tra

ns

du

ce

r a

lso

co

nn

ec

ted

to

C&

WS

. (P

res

s

op

era

tin

g 0

2 P

RE

SS

lig

ht

on

MD

C-1

0.

a.

De

term

ine

ta

nk

he

ate

r s

urg

e t

an

k)

02 op

era

tin

g r

an

ge

is

865 t

o 9

35

p

erf

orm

an

ce

. -

psi

a.

Ala

rm t

rig

ge

r v

alu

es

ar

e

b.

Dr-

tect

Ie

zk

s.

80

0 p

sia

lo

w a

nd

95

0 p

sia

hig

h.

Wit

h

c.

Ve

r~

fy

su

rge

t.m

k

pre

ss

ure

. O

L P

RE

SS

1N

.D s

wit

ch

at SURGE

TA

NK

po

siti

on

, in

dic

ato

r d

isp

lay

s si

gn

al

fro

m E

CS

su

rge

. ta

nk

p

res

su

re t

ran

sd

uc

er.

Ind

~c

ato

r 2

U~

sp

lay

s 02

tan

k N

o.

C p

res

su

re

SF

00

38

P

Th

e i

nd

ica

ror

fun

cti

on

is

co

ntr

oll

ed

:~

nd

:s u

se

d a

s f

oli

ow

s:

(P

re

ss

02

b

y a

pre

ss

ure

tra

ns

du

ce

r lo

cate

r!

in

tan

k N

o.

2)

02

tan

k N

o. 2

ou

lle

t li

ne'.

Tra

ns

- a

. D

ete

rmin

e t

an

k h

ea,t

cr

- d

uc

er

als

o c

on

ne

cte

d t

o C

&W

S.

pe

rfo

rmi~

n#

:c.

op

era

tin

p 0

2 IJ

fiE

S.5

L~

ph: u

n M

DC

- 10

. b.

3e

tr;t

1, 3,:s.

02

op

er

rt~

ng

range i

s. 8

65 t

o "

935

ps

~a

. A

iarr

n t

rig

err

va

lue

s ;I

re S

O0

p

sxa

:op,

and 9

50

psi

a h

~g!r

:

TA

NK

OL

'.-\N

TI?

'Y

~n

dic

ato

r

ii

~

~r,

>II

?

Ind

ica

ror

I D

~s

pl.

~y

s

qn

~r.

r::)

- of

132

CR

SD

- A

-C b

ur

SI'O

O30

Q

HZ

qu

an

tity

dis

pla

y r

an

ge

is

0 to

rr

.m.>

l::l

np

it:

tan

k N

o.

1.

GENIC

So.

I b

C

(Qu

anti

ty

28

Ib.

SY

ST

Eh

l-

Hz

tan

k

QT

Y

No.

I)

A

MP

L I

A

C I

-

PC

(M

DC

-LZ

) -

Dis

pla

ys

qn

an

t:ty

ef HL

CR

YO

- A

-C b

us

SF

?0

3 1

Q

rem

ain

ing

tn

ta

nk

No.

L.

GE

NIC

N

o. 2 B

C

(Qaa

nti

ty

SY

ST

EM

- 13

2 ta

nk

Q

TY

N

o. 2)

AMPL 2

A

C 2 - PC

(MD

C-Z

Z)

Ind

icat

or

2

AU

TO

OF

F

Te

lem

etr

y

Na

mr

an

d

Cir

cu

it

Po

we

r C

od

e N

o.

Lo;

atao

n P

osi

tio

n

Fu

nct

ion

B

rea

ke

r S

ou

rce

an

d I

den

tity

R

em

ark

s

x11)

C-

I %

OL

gro

up

(C

on

t )

Ind

icat

or

I D

isp

lay

s q

uan

tity

of

02

C

RY

O-

A-C

bu

s S

F0

03

2Q

0

2 q

uan

liry

dis

pla

y r

an

ge

is

0 t

o

rem

ain

ing

in

ta

nk

No.

1.

G

EN

IC

No.

I

PC

(Q

uan

tity

3,L

O I

b.

SY

ST

EM

- 0

2 ta

nk

P

TY

N

o.

1)

AM

PL

1

AC

1 -

QC

(M

DC

-22

)

Dis

pla

ys

qu

anti

ty o

f 0

2

CR

YO

- A

-C b

us

SF

00

33

0

rem

ain

ing

in

tan

k N

o.

2.

GE

NIC

N

o.

2 P

C

(Qu

anti

ty

1 !$?EM -

02

tan

k

No.

2

) A

Mf

L 2

A

C 2

- b

C

(MD

C-2

2)

HZ

HE

AT

ER

S s

wit

ch

es

Non

e R

edu

nd

ant

he

ate

r e

lem

en

ts i

n e

ach

, H

z t

ank

re

qu

ire

s 1

0 w

att

s o

f p

ow

er

Sw

itc

he

s 1

an

d 2

C

on

tro

ls d

-c p

ow

er

to H

z t

an

ks

CR

YO

- D

-C m

ain

fo

r ea

ch. e

lem

en

t.

No.

1

an

d 2

he

ate

r e

lem

en

ts,

GE

NIC

b

us

A

resp

ec

tiv

ely

. S

YS

TE

M -

4 T

AN

K

En

ab

les

+u

tom

atic

pre

ss

ure

H

EA

TE

RS

- S

wit

ch a

t A

UT

O p

osi

tio

n w

ill

ap

ply

sw

itc

he

s to

co

ntr

ol

d-c

p

ow

er

to

HZ

- 1

d-c

vo

ltag

e to

Hz

tan

ks

No.

1

an

d 2

H

z t

an

ks

Nol

1

an

d 2

he

ate

r ..M

N A

re

du

nd

ant

he

ate

r e

lem

en

ts w

hen

e

lem

en

ts.

(MD

C-2

2)

pre

ssu

re s

wit

ch

es

in b

oth

ta

nk

s a

re

in a

lo

w-p

ress

ure

po

siti

on

at

230

CR

YO

- D

-C m

ain

p

sia

or

low

er.

an

d r

em

ov

e d

-c v

olt

- G

EN

IC

bu

s B

a

ge

wh

en e

ith

er

prr

ss

ure

sw

itc

h i

s

SY

ST

EM

- in

a h

igh

-pre

ssu

re p

osi

tio

n a

t T

AN

K

26

C p

sta

or

hig

he

r.

HE

AT

ER

S -

Dis

co

nn

ec

ts d

-c p

ow

er f

rom

HL

H

z -

2

tan

ks

No.

I

an

d 2 h

ea

ter

WN

5

e?

em

en

ts.

(MIX

;-2

2)

- C

on

tro

ls d

-c p

ow

er

dir

ec

tly

to

S

wit

ch a

t O

N (

ma

nu

al)

po

siti

on

by

- H

Z ta

nk

s N

o.

1 a

nd

2 h

ea

ter

pa

sse

s th

e p

res

su

re s

wit

ch

es

app

ly-

ele

me

nts

. in

g d

-c v

alt

ag

e d

ire

ctl

y t

o t

he

sa

me

re

du

nd

ant

he

ate

r e

lem

en

ts

emp!

oyed

fo

r a

uto

ma

tic

op

era

tio

n.

OFF

ON

Tel

emet

ry

Cir

cu

it

Po

wer

C

od

e N

o.

Fu

nct

ion

S

ou

rce

and

Id

enti

ty

Re

ma

rks

Red

un

dan

t h

eare

r e

lem

en

ts i

n e

ach

02 ta

nk

re

qu

ire

s 77.5 w

att

s of

Sw

ltch

rs I

an

d 2

C

on

tro

ls d

-c p

ow

er t

o 0

2 ta

nk

s C

RY

OG

EN

IC D

-C m

ain

p

ow

er f

or

ea

ch

cle

men

t.

No

. 1

and

L h

ea

ter

ele

me

nts

. S

YS

TE

M -

bu

s A

. resp

ec

t~v

ely

.

AUTO

En

able

s au

tom

atic

pre

ssu

re

Sw

itch

at

AU

TO

po

siti

on

wil

l ap

ply

d

-c

vo

ltag

e to

02

tan

ks

No.

1.

and

L

02

tan

ks

No.

1 a

n% 2 h

ea

ter

red

un

dan

t h

ea

ter

ele

me

nts

wh

en

ele

me

nts

. p

ress

ure

sw

itc

he

s in

bo

th t

an

ks

are

in

a l

ow

-pre

ssu

re p

osi

tio

n a

t 865

psi

a o

r lo

we

r an

d w

ill.

re

mo

ve

d-c

v

ola

age

wh

en e

ith

er

pre

ssu

re s

wit

ch

io i

n a

hig

h-p

ress

ure

. p

osi

lio

n a

t 935 v

ia o

r h

igh

er.

Dis

con

nec

ts d

-c p

ow

er f

rom

O2

tan

ks No.

1 a

nd

2 h

ea

ter

ele

me

nts

.

Co

ntr

ols

d-c

po

wer

dir

ec

tly

to

S

wit

ch a

t O

N (

ma

nu

al)

po

siti

on

.

02 ta

nk

s No.

I a

nd

2 h

ea

ter

by

pa

sse

s th

e p

ress

ure

sw

itch

es.

ele

me

nts

. ap

ply

ing

d-c

vo

ltag

e d

ire

ctl

y t

o th

e

>

sam

e r

edu

nd

ant

he

ate

r e

lem

en

ts

02

PRESS I

ND

sw

itch

TANK PRESSURZ-:-02 i

nd

icat

or

is

sha

red

~y

two

pre

ssu

re s

ign

als.

(MD

C-2

.2).

.

(RH

EB

20

4)

.i

1

.I

..

I

.-

._

.I

.

.-

..

/

-. .

.

..

~

AU

TO

OF

F

O2

FA

NS

su

rtc

he

s

Sw

itch

es

I an

d 2

AU

TO

OF

F

GL

Y E

UA

P S

T W

M PR

ES

S

ind

ica

tur

Hz

tan

ks

No.

1

an

d L c

irc

ula

tin

g

fan

mo

tors

.

Co

ntr

ols

30

a-c

po

wer

dir

ec

tly

to

cir

cu

lati

ng

fan

mo

tors

in

2IL

ta

nk

s N

o.

1 a

nd

2

Ap

pli

es

a-c

po

wer

to c

on

tac

ts o

n

mo

tor

swit

ch

wh

ich

co

ntr

ols

30

a

-c p

ow

er

to c

irc

ula

tin

g f

an

m

oto

rs i

n 0

2 ta

nk

s N

o.

1 a

nd

2.

Dis

co

nn

ec

ts 3

fl a

-c p

ow

er

iro

m

02

tan

ks

No.

1

an

d 2

c~

rcu

lati

orr

fa

n m

oto

rs.

Co

ntr

ols

3D

a-c

po

wer

dir

ec

tly

to

cir

cu

l~ti

ng

fan

mo

tors

in

02

ta

nk

s N

o.

1 a

nd

2.

Pro

vid

es p

res

su

re i

nd

icati

on

of

ste

am

dis

ch

arg

ed

6ro

m w

ate.

r-

gly

co

l e

va

po

rato

r.

TA

NK

FA

N

MO

TO

RS

- 2

- A

C 2

PA

b

B

PC

(M

DC

-22

)

CR

YO

GE

NIC

T

AN

K F

AN

M

OT

OR

S -

1-

AC

1

PA

Q

B

PC

h

f-D

C-2

2)

CR

YO

GE

NIC

T

AN

K F

AN

M

OT

OR

S -

2-

AC

2

PA

.

bB

P

C

tMD

C-2

2)

EC

S -

TR

AN

S-

DU

CE

R

PR

ES

S

GR

OU

PS

2

MN

A

MN

B

MDC-22)

- N

o.

2

wh

en e

ith

er

pre

ssu

re s

wit

ch. 1s

in. a

h

igh

-pre

ssu

re

po

siti

on

at

26

0 p

sia

o

r h

igh

er.

Sw

itch

at

ON

(m

an

ua

l) p

osi

tio

n

by

pa

sse

s th

e p

res

su

re s

wit

ch

es.

ap

ply

ing

a-c

po

wer

dir

ec

tly

to

th

e

sa

me

red

un

dan

t H

z t

ank

fa

n m

oto

rs

em

plo

yed

fo

r a

uto

ma

tic

op

era

tio

n..

Red

un

dan

t fan m

oto

rs i

n each O

2

tan

k r

eq

uir

es 1

48V

A t

ota

l.

.

A-C

bu

s N

o.

1

Sw

itch

at

AU

TO

po

siti

on

wil

l ap

ply

a

-c p

ow

er

to 0

2 ta

nk

No.

1

an

d 2

re

du

nd

an

t fa

lvm

oto

rs w

hen

pre

ss

ure

sw

itc

he

s in

bo

th t

an

ks

are

in

a l

ow

p

res

su

re p

os

it~

on

at

865. p

sia

or

low

er

and

wil

l re

mo

ve

a-F

vo

ltag

e

when

eit

he

r p

res

su

re s

wit

ch

is-

in a

A

-C b

us

hig

h p

res

su

re p

os.

itio

n a

t 9

35

psl

a o

r N

o.

2 h

igh

er.

Sw

itch

at

ON

(m

an

ua

l) p

osi

tio

n

by

pa

sse

s th

e p

ress

ure

. sw

itc

he

s,

app

lyin

g a

-c p

ow

er

dir

ec

tly

to

th

e

sa

me

red

un

dan

t 0

2 ta

nk

fan

mo

tors

em

plo

yed

fo

r a

uto

ma

tic

op

era

tio

n.

D-C

ma

in

CF

00

34

P

No

rma

l st

ea

m d

nct

pre

ss

ure

op

era

- b

use

s A

an

d

(Pre

ss

ti

ng

ra

ng

e i

s 0

.97

to

. 0.1

45

p

sia.

B

gly

col

ev

ap

o

ut

sle

am

)

I

C] 0

z r3 s ;

2 u 2. r

P

r:

rn

Re

mr

rks

No

rma

l *

.ate

?-g

lyco

l p

urn

p o

pe

r-

ati

ng

ran

ge in

drc

ati

cn

s a

re

as

ioil

ow

s:

Pre

lau

nc

h {GSE an

d o

nb

oa

rd p

iun

ps)

: 1

4 t

o 1

8 p

sra

Pre

lah

ch

(o

nb

oa

rd p

um

ps)

: 4

5 t

o

55 p

sia

N

orm

al

f!ig

ht:

37 t

o 4

5 p

sia

E

me

rge

nc

y f

lig

ht:

3

7 t

o 4

5 p

sia

indic

ato

r w

tll

not

sho

w 0

2 fl

ow

u

pst

rea

m o

f tr

an

sd

uc

er,

su

ch

as

th

rou

gh

PLSS F

ILL

val

ve1

LH

EB

- 314

1,

ma

in r

eg

ula

tor

or

su

rge

tan

k r

eli

ef

valv

e a

ctr

on

, o

r li

ce

le

ak

ag

e.

02

FL

OW

HI

ryst

em

. sta

tus l

igh

t (r

ed

) is

lo

ca

ted

on

MDC- I I

an

d

illu

min

ate

s a

% a f

low

ra

te o

f 1

.0

lblh

r.

No

rma

l 0

2 f

low

op

era

tin

g r

an

ge

in

drc

atr

on

s a

re f

rom

0.2

0 ta

0.. 4

5

Ib/h

r d

urr

ng

pre

lau

nc

h a

nd

in

fli

gh

t.

Su

it c

om

pre

sso

r A

P o

pe

rati

ng

ran

ge

ind

ica

t~o

ns are

as

fo

llo

ws<

0'.

7 t

o 0

.9

psi

du

rln

g p

rela

un

ch

0

.3 t

o 0

.4 p

si d

art

ng

-..

-~rm

al s

pa

ce

fl

igh

t 0

.2 t

o a

. 3 p

ni

du

rrn

g.e

me

rge

nc

y

ap

ac

e f

lig

ht.

. C

ap

ac

ity

of

ac

cu

mu

lato

r is

1.3

6 Ib.

No

rma

l a

cc

um

ula

ar

op

era

trn

g r

an

ge

in

dic

ati

on

s a

re

as

fo

llo

ws:

P

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CONTROLS AN^ DISPLAYS

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vid

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).

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to f

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one

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1

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GE

b

use

s A

and

swit

ch p

rov

ides

he

ate

r p

ow

er d

uri

ng

Ap

pli

es t

28

vdc

pow

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o t

wo

and

FU

EL

B

O

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Hz

pu

rge

of f

uel

, cell

s.

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o

2;w

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ate

ls i

n f

uel

ce

ll HZ

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ON

30

min

bef

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k2

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OF

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ov

e t2

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rom

P

osi

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OF

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fte

r co

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Z p

urg

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--

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es

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ur

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ly i

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l RCS-PROP

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gle

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ac

h s

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on

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ls

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spri

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usi

ng

it

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ne

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ium

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EL

IUM

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sett

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it

to t

he

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or OFF p

osi

tio

n.

2 h

eliu

m p

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uri

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tio

n s

yst

em

. (M

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) E

ach

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ve

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tain

s a

po

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ro-

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h o

f'th

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ur

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ack

ages

sw

itch

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cir

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for

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ven

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g in

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ech

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r

A (B. C

. D

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lso

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0

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e

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len

oid

th

at

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s th

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e to

th

e o

pen

po

siti

on

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Ce:

.ter

R

emo

ves

so

len

oid

ex

cita

tio

n;

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em

ain

s in

la

st c

om

man

ded

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p

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t z

OF

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rgiz

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ium

iso

lati

on

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ve

m

l- *

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oid

th

at

d-r

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val

ve

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u.

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ain

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ator

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even

t IS

OL

b

use

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and

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with s

trip

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ispla

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on-

(Co

nt)

in

dic

ato

rs

MN

A

B

tro

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by

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noid

. act

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ray

Str

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N

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pla

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agnet

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A (

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on

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ato

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tical

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ch c

on

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ls

toggle

sw

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rin

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oad

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cau

sin

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one

hel

ium

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on

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ve

in t

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it t

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etu

rn t

o t

he

cen

ter

posi

tion

HELIUM 2

hal

f of

a p

ara

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er

pla

cing i

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e O

N o

r O

FF

hel

ium

pre

ssu

rizati

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sy

stem

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tions.

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ach v

alve

conta

ins

a

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h o

f th

e fo

ur

RC

S p

ackag

es

posi

tion m

icro

swit

ch

whic

h c

om

-

conta

in i

den

tical

syst

em

s.

ple

tes

the

cir

cu

it f

or

op

era

tin

g t

he

val

ve

posi

tion e

ven

t in

dic

ato

r m

ech

an

ism

- E

ach

val

ve

is m

echan

i-

A (

B.

C.

Dl

rall

y h

tch

ed

open

and s

pri

ng

-lo

ad

ed

00

En

erg

izes

hel

ium

iao

lati

on

val

ve

clo

sed

. ON

sole

noid

th

at

dri

ves

the v

alve

to

the o

pen

posi

tion.

Cen

ter

Rem

oves

sole

noid

exci

tati

on:

valv

e r

em

ain

s in

la

st

com

man

ded

posi

tion.

>

z E

nerg

izes

hel

ium

iso

lati

on

val

ve

u

OF

F

sole

noid

th

at

dri

ves

the v

alve

to

the c

lose

d p

osi

tion.

. .

Each

in

dic

ato

r is

a t

wo-p

osi

tion

%I

HE-

Z ev

ent

dev

ice w

ith s

trip

ed

-lin

e d

isp

lay

con-

ind

icato

rs

tro

lled

by

sole

no

id a

cti

on

and g

ray

*

dis

pla

y b

y p

erm

an

en

t m

asm

t ac

tion.

$

A (B. C

. D

l

Str

iped

-lin

e d

isp

lay

in

dic

ate

s clo

sed

condit

ion o

f val

ve

con-

tro

lled

by s

wit

ch

lo

cate

d d

irectl

y

'ab

ov

e e

ven

t in

dic

ato

r.

Gra

y d

is-

play in

dic

ate

s open

co

nd

itio

h

Eac

h @

wit

ch is a

th

ree-p

osi

tio

n

PR

OP

EL

LA

NT

sw

itch

es

Four h

rnc

tio

~ll

y iden

tical

@w

itches.

E

ach

sw

itch

com

t ro

ls

tog

sle s

wit

ch

, sp

ring-1

-ded

. C

PU

S~

"~

two i

sola

tio

n v

alv

es

(one

fuel

. it

to r

etu

rn to

the

cen

ter

posi

tion

one

ox

idiz

er)

wit

hii

eac

h o

f th

e

aft

er

pla

cing i

t to

th

e O

N o

r O

FF

fou

r S

/M RCS p

ackag

es.

posi

tions.

E

ach

val

ve

co

nta

ins

.

posi

tion m

icro

swit

ch

whic

h c

om

ple

te*

th

e c

ircu

it f

or

op

era

tin

g t

he v

alve

posi

tion e

ven

t in

dic

ato

r.

33

ch

val

ve

1s m

ag

neti

call

y l

atc

hed

open

and

, sp

rin

g-l

oad

ed

clo

sed.

I

. . , .

S M ~ A - O ~ - S C O ~ 2



MAIN DISPLAY CONSOLE-PANEL 15

,Basic Date 12 Nav 1966 Change Date

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