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UNCLASSIFIED
DEFENSE DOCUMENTATION CENTER
FOR
SCIENTIFIC AND TECHNICAL INFORMATION
CAMERON STATION. ALEXANDRIA. VIRGINIA
UNCLASSIFIED
NOTICE: When government or other drawings, speci¬
fications or other data are used for any puipose
other than in connection with a definitely related
government procurement operation, the U. S.
Government thereby incurs no responsibility, nor any
obligation lAat soever; and the fact that the Govern¬
ment may have formulated, furnished, or in any way
supplied the said drawings, specifications, or other
data is not to be regarded by implication or other¬
wise as in any manner licensing the holder or any
other person or corporation, or conveying any ri^ts
or permission to manufacture, use or sell any-
patented Invention that may in any way be related
thereto. '
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SPECIFICATION DOCUMENT NUMBER A. .:
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SECURITY
CLASSIFICATION
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SPECIFICATION DOCUMENT PACE
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REVISION
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FOLLOW DEJCHIPTICN OP CHANGE WITHi REASON PflU CH.AMCE, CHANCE EPPECTIVP.
INFORMATION, PftOOOaiON AND TOOUINC |NF6i(llilATt6N. RERUN BOA'S, ' ETC.
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I A Title Page Hi iiavlaed List of Active Pages
I 'Pagis itevision Added new ..tages for revisiona.
Pa^^e Indejpt Ct Kevised titles of P’igures 3 thru 8 thru j
J.O, and added new J'iguree 15* ^16, liM'tl? t*,.l®d®ito j
'Paj.e 3» Paragraph 2.1. !,• chan .-ud reference' to read *'M1L-E- i
; iii»70A" dated "3 March 1959’* i-ri lieu of «M2L-1S-1|970« |
; ; dated "1 June 1955«’' (Siipet^eded)i.. Deleted refer- ^
■ once to MlL-E-dliipfJ. ’
I ;?aj;,e 4# Paragraph 2.1.3^ Dele toe reference to A? lAdletin 67B. '
I 1 4 (Canoeliod). ■.
iPar.e li, Paragraph 2.2.1, Deleted reference to DM-1011, added |
j I reference to D2«lil23» I
• ;?Rge S- Partigroph 3«1.1.1.2.1, Critical Materlala, deleted all.
j :Pa)f€ 7> Patmgrapn 3*1. 1.1.10, Ilovisoc to road "A?.! case protruf
I i . a’£btli'* in lieu of "all conivsetoro and ether case pro- !
1 truadana." !
iBk®®- 7a,' Partigroph 3*1«1»1»11, Added sentence "Weiglit economy ie
etc." ■ *
Paragraph 3*1*1. 2.6, Rd-written to detail grounding f
; requirowenta.
■ftiga 11, Paragraph 3*1*1*5*2, Last sentence, delotea all after j.
j ' vendbir#
Paragraph 3*1* 2.1.1, Re*writton to provide more 1
datailad information about cooling.
ISgii itf Paragraph 3#i*2,1.3» Ra-writtan to provide more !
* datalled !ir*foraation about power source,^ Added !
! raquirejoerit fo'r'^aedorxlary power fupply and convertor i
; . .A abort circuit protection. . ’
Paga,iii3, ParagzSiiph 3«1*2*1»11, Deleted first eentonco. '
'Pago 13, Paragraph 3*1*2*1*12 Changed t<» read "ground power ‘ .
I auppliaa" In lieu of "auxiliary power aupplieo."
"Accept" in lieu of
!Paga' lit. Paragraph 3*1* 2* 2.5, changed to read "below tiie
f unmodulated carrior level" in lieu of "down from the (
carrier level**. ' ' !
Ipage IS, ‘Paragraph 3*1.2,e.J (Cont’d)., Roylaed first sentence |
I • "lha:RF eection etc.", Added last Sentence "Tlie |
t7;'. .} J _ deviation Shall, etc.". j.,-.
i I7j, 'Paragraph . Deleted second aentenoo# r ;
Page 17, New pawigriiph 3. 2.1. 2.3, added to detail grounding j't
-roquireaerttB. / • /'■ -
'Page 22, Paragraph 3*2.2*l«hO» Wded oentenoe to clarify
I , ro'quirime.hta.
See page Rev. g
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ftOeiHG A!ftf?WNE, COMPANY
ii
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•■VISION
FOLLOW OeiCHIPTION Of CHAMOC WITH. REASON TOR CHANGE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INPORMATION. RERUN DOA'S^ ETC.
to
23*P«r«Kraph 3.2.2.2.1|, Addeo lower lijnit of nirjus 0.1
volt# to net.*tivB potential*
25»IIoie parai'rtiplj 3«3*1*2.3, fiddt.d to raference para,_;raph
1.2.1*2.3 for i^roundiav; requireitents.
jPa^ 28, Bira^ph 3.3*2. 1.2, Rapl;,.ced "(u-5v)" and "(0-50mv)''
with "(0 to ♦ 5 volta)" and "(0 to +30 milliTolta)"
rMpectlvely, all places*
28, Paragraph 3.3*2*1*2 Bsplaced (a) (b) and (c) to read,
coa^likitlsn of, etc*"
i^*»gr*ph 3.d*2*l*7, aeleted all, reference nade to
paragraph 3* 1.2. 1.1 for cooling.
yOf Paragraph 3.3*2. 2*2, Addea noxlaua expected coaiaon
■ode potential. Chaa^jed “now" to "nor"
32, Paragraph 3.U.1. 3*2.1, Added new sentence "'ilie amoieni
teaperature on the .^round le xlO'f",
33, Peragraph 3.U.2.1, fieplaced"l0<.:>T)" and ^(0«5l»mv)"
with "(0 tu volte)" and "(0 to *$0 mlllivolta)"
respectively, axl places, fieplaced (a) (l>) ana [c)
read, "Aigr coablnation of, etc."
33# i^ra^^raph 3.U.2.3, Added more detailed Infomutlon
about cooling.
3ti# Paragraph 3«^*l*l«3f Delated worda "ai^illfler"
and "angilifiers". i
3®# ^rBi^ph 3*5«1.2.3, Slectrlcal Coae Coopliance, I
deleted all.
iVregraph 3.!5»2.1.6, Added definition of operation llfei
12, Paragraph li.i«2*2. Last sentence, deleied "at no i
additional cost to the buyer*
age 111, Paragraph li.3.1*3> Re-written to reference new Figure
8 for Acceptance Test vibration envelope. '
I 111, ftragraph 1.3* 2*1, Wording changed for clarification
I 16, Paragraph 1*3«1«1, Re«written to refezenca new vibrae
tion Flguree 15 and 8 in lieu of specifying r.m.s.
' 17, Airagraph 1.5«1, Re-written to clarify the number of
test units required. Added sentence i "fiach tLst articls
etc."
17, Paragraph 1.5*1. 2, Changed to reference Figures 1 and
5, in li«tt of Figures 9 and lu. !
18, Paragraph 1.5.1.1, Ra-wxd.tten to detail tne tenperature*
altitude test.
18a, Added page for completion of tempera ture-altituds
rsqulreaents.
Paragraph 1.5*!*!.!, Gbanfsd to 1.5.1.1.3 to compensate
for addition of paragrapns 1.5.1. 1.1 and 1.5.1,1.2.
1$>, Paragraph 1.5.1.6, Re-writUn to dsUil the Interfer-
snoo Test roquired.
See page Rev. g
BOEING AIRPUNE COMPANY
SEATTLE 34, WASHINGTON
jikj4r
MODEL
NO.
Wi-itlA
- P^E-
na-ldClLs - fr'-Yitii Wv!
RIVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
INFORMATION, FROOiiCTION AND TOOLINC INFORMATION. RERUN DDA'S, ETC.
jPage Para^aph Ii«5*l«7 moved from page U9 to Page SO due to
rc'writ^g paragraph U.5*l*6t
iPaj^ie So, Paragraph U*5»l»7* Be-witten for clarification,
reference made to Figures 9 and 10 for vibration
requlramonte In lieu of specifying vibration amplitudes^
jPage 5l» ftira,^raph Re-written to clarify the number ef
test units required.
Page Sl4tliew Page added turnip re-writing paragraph h»S»i*
Page Sit Paragraph li*5.2«i).2, Re-written to detail the
temperature-altitude test.
Page
Page
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57,
[Page 5b,
‘Page
iPage
iPdoe
I
jPage
iPage
Page
page
^ge 73,
ftsge 7U,
5U, Paragraph 14.5.2.5.3, Re-writt«n to detail the
tenpsrature-alti.tude test.
55, Paragraph I4. 5.2.7, Re-written to detail the Interfer¬
ence %8ts required. ’
55, Paragraph 14.7.2.6 moved from page 55 to 56 due to I
re-writing paragraph U.5.2.7. j
56, Section 14.5.2.8, Ra-wrltten for clarification, |
reftrence made to Figures 5 and 10 lor vibration j
requirements in lieu of specifying vioratlon amplituues,
56a,liew page added due to re-writing parugrapne 14.5*2.7 andi
14*5*2.8, and due to new para,,rap , 14.5*2*9.
56f,Section 14*5*2*6 (Cont'a) re-written diie to rewriting
section 14*5*2*8*
56a,li«« paragraph 14*5*2*9 added for Shock I)»st requirements!
57, Paragimph 14*5*3, Deleted "acceleration” added "shock”.
Paragraph 14*5*3*1, Re-written to reftrence Figure 3 for!
vibration requirements in lieu of specifying vibration
amplitudes * |
Paragraph l4«5*3*2*2. Changed to read "MIL-E-I497OA” and |
"procedure IV" in lieu of "MIh-li-l4>70" and "procedure
VI"« RBvl^ed to readj "While unpackagod,0tc." j
61, tiew Paragraph 14*7*3 added for Evidence of Acceptance Tbit.
65, Paragraph 6. 1*1*2, Re-written to ciar,.fy Intended use*
65, Para,^raph 6*1*1*14, Added new paragraph to read "Failure j
of the RF Section,etc*"
65a, New Page added due to additional paragrapii 6*1. 2*3*
66, Paragraph 6.2.1, Reference owde to D2-I4I23 for Design
Propesal Approval, in lieu of paragraph 6*14*3*
70, Paragraph 6*3*10, Ravisad definition of reliability.
73, Paragraph 6*l4*3«i*3f Proposal Rsvisions requirements,
deleted all*
Paragraph 6*l4.3*l*5, quotation Program Schedule requlro|
aents, deleted all*
Section 6*Ua3*2, Deleted all specific exhibits listed,
reference made to D2-I4I23 for specific exhibits
required*
MODEL
NO.
PAGE
UiS'ilBA
DID -20402
V
c
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINOTON
SAC 4Ml A>*2
(
■A
REYtSIOM
FOLLOW OfSCHIPTION OF CHANGC WITHt REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN ODA’S, ETC.
jPaijo
See page Bev* g
iPuga 9Uf I'lgure
page 76f Paragraph 6*U*U*3s Inetallataon and Haintenance
Znetructione requirenentSf deleted all.
Uli Paragraph 6.6.1, Request for (^ootatlon re>wurded.
dl. Paragraph 6.6.2, Reference ra£;d» to D2-U123 In limi of
paragraph 6.1»,3, pe^regruph i»e*worded.
Page dl. Paragraph 6.6.3, Deleted last sentence.
^ge dl, Paragrapa 6.6. U, Pina Quotation, deleted all.
dl. Paragraph 6.6.3| Purchase Order, re»vN>rdea.
d2. Paragraph 6.6. 7| Added (e) *• Inter forance Control" etc.
^0, Figure 1(, Re«drawn to show design requireaents of
In lieu of antlcipjted fligi.t vibration of naa.
page 5^1, Figure Re-draun to show deeign requirements of 0.1, j^j
epe 5-1 AX) cps, with 12 db roll-off to 20M cps, in lleji ^
, of antlc^ted flight vibration of 0.03 g /cp- 'i-25 cpsL *
and O.lgVcpfl 5-2000 cp« [
P»g'® 93, 7,Ro-drawn to show U.2g2/cp6 5-lOOOcpe roll-ofi to[2000cp8.
jure 0, Uraimx vibration envelope deleted. '
Hepluced with new Figure 6 for Instrujoentation Conpart-j
ment aqulpuent acceptanoe test vibration envelopes j
^ason for Chan^ta; Clarification of specification. 1
ftge 31, Paragraphs 3*U.1«3*1 and 3*U.1.3*2 changed to read !
"section 3»U«2" In lieu of "esetion 3»ii«2.2" |
yage 37, Paragraph 3«i'«l«3, Changed to read "3»r'»2" in lieu of
; "3.5.2.2." i
Page 37, Paragrupn 3«5«1*3«1«2, Vibration, deleted ail.
iRige 37, Paragraph 3*5«1«3*1*U, Shock, deleted all* ;
:Rige d9, Fl*;ure 3, Re-drawn to show 5(J P«ak in lieu of 3»5g and ;
■ 2g peak in lieu of 1.5g« ’
|Page 92, Figure 6, Re-drawn to ahown 7g peak in lieu of 5d« '
jPage 95, Figure 9, Be-drawn to show lig peak in lieu cf 3^» j
1 Title clianged to read “earelope for reliability tests", >
j in lieu of "to.*5t euveiope for oquiunent opera tlve(in8ti^-
j aantation cooparusent)." ,
yage 9d, Fi|;ure 12, Replaced "0.5 micro sec. nax." with
I "5.0 micro sac. irwix."
jHaason for Change > Engineering Error.
I
iTitle Puga Ii ikdded Reliability (kroup signature,
i^ge 3, Paragrapn 2.1.1, Added reference to .4IL-E-51iUOC &
! M3L-F-lii072.
3hf Hew Page added. Referenoe te HlL-C-25050 added.
(Page 3a, Paragraph 2.1.2 moved from page 3, added reference
I to FED-STD-595.
Pai^e Paragraph 2»2,J added to reference assigned frequency
, for transmitter.
{Page U, Paragraph 2.1.1(, DelsLod reference to ii3335b6 for use
i of metals.
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
•«C iMl A-,2
MODEL
NO.
OtO-20<c2
V.
d
REV LTR
REVISION
FOLLOW description OF CHANCE WITH; REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN OOA'S, ETC.
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ge Ilf Paragraph 242»lj Added reference to BijS 10-26 and to
•jAC 53064
New pa^e added due to addition ef reference above.
6, /^Paragraph Deleted reciuirement for use of
metals to ue In accord with MS 335^6#
6, Para ,iapn 34l.l*l*343«i» New paragrapu added foi'
sDcilar and Diaslsiolar Mtals4
6, Paraipraph Revised p;iragiaph hieading to read
"Mainta inability" in lieu of "Maintenance Convenience",
added sentence "HaintalnabULlty shall oe eonslderad, "et<^«
/, Paragraph 3. 1.1. 1.7, Added reijuireaent for drainajiC
provjsions if unit is not sealed, pi-ra graph re-worded fi^r
clarificaticn.
7, Paragraph 3. 1.1.1. 9. 3f Revised to require test points t^
monitor the cutjut voltage of the pEnne detector.
ti, Paragrapu 3«J-.i«7«3» Daletici "King Electronics".
Changed "ca;a.nen" to "cannon"
ba. New page added due to re-writing 3.1. 1.2. 6.
ba, Paragrapn 3.1»1»2.7 mcved from page d duo to re¬
writing 3*1*1*2.6.
Page 9, Para,;raph 3.1.1.3«i»i>«l» Aided paragraph lo clarify
packaging in the environment specified.
9f laragrapn j. 1.1. 3*1.6, Added reference to 3.1.i.3.1.5*li|
y, ParagrapiL 3*1*1>3*1*7« Added reference to 3*l.l«i*2.2
axid 3.1*i*3*l.
Id, Paragraph 3.1. 1.3. 2. 5» Reviaod to read "15.^" in lieu
of “lOg“.
13, Paragrapn 3.1. 2.1.9* Added feedback current limlUtion.
i3, Paru. 3.i.2.1.iu.3, Changed tolerance to read "13$" in
lieu of "11:1".
page 13, Paragraph 3«i.2.1. td.U* Gfianged rise this to O.i to
0.3 microsecond* in lieu of 1 to 1.5 .micros’econas,
' c:;anged fail time to d.3 to J.7 microsuconds fcn lieu
of 1 to x.> microsecond*.
Ill, P.>L'agraph 3.i.2.x.2, Deieteo.
Hi, Paragrapn 3.1. 2.2.3, Re-written to aau adjustment
requirement.
ill. Paragraph 3.1. 2. 2.5, Revised to require 102db down from
carrier level for alioca tea receivar pussoands and
added Eonteoce "Snould a filter be required, etc."
lit, Paragrapn 3.1*2. 2. 7, Roviseu second s*ot*n'-e to lead:
"The center frequency** specified, etc."
21, Paragraph 3.2.-.1.4.1, Added "or four, etc."
lU, Paragraph 3.1.2.2.13, Revised to reed "IB db/octaVe
in lieu of "I6 db/octave"| Added sentence "^he vendor
will be, etc."
16, Section 3.2, Added sentence to allow for multiplexer
requironent in programmer.
Sea page Rev, g
f'age
rage
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO. 1
WS-niA
D /o- 20402
PAGE !
<± _ I
REVISiOM
FOLLOW OESCRITTICN OF CHANCE WITH: MASON FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, FROOUPTION AND TOOLING INFORMATION. RERUN DOA'S, ETC.
A iPMiie
1
Pa^e
:Pa««
,Pa(iO
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Pag*
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Page
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16, Paragraph 3*2. l.i, Added paragraph 3*1*1*I>10 to
exceptiona*
16, Paragraph 3.2.1.1*!, ReTiaed paragraph headin^ to Head
"Nalatalaablllty" in lieu of "Maintenance. Convenience"jj
added Lenience "Malntaixsabilaty ahail be considered",
added nultiplexer card requirement*
l6a,Mev paragraph 3*2*i*i*5 addeu for Physical Size*
l6a,MeN page added for 3«2*l*l*U*li due to rewriting
3*2.1*1.1*
17, Paragraph 3*2*1*2, Added 3«1*1*2*6 to exceptions*
17, Paragraph 3*2.1. 2*1, Electrical Connectors, revised to
require pigtails in lieu of coni.ectore*
17, Paragraph 3*2. 1.2.1, Deleted "epoxy resin per MlL-1-
l6y23C", added "the type of sealant, etc." |
lb, Paragr.ph 3.2.1.U, Added "with the exception that, etcj"
ly. Paragraph 3. 2. 2*1.1, Changed section to allow for j
nultiplexer capability*. |
19a, Mew page to allow for multiplexer addition. Paragraph!
3.2.2.1.1.^ added "or four multiplexers, etc." |
22, Paragraph 3*2. 2*1*6, Added requirement for sccondaiT- |
power supply and connector short circuit protection, I
reference added to paragraph 3*1*2*1*3 for source |
impedance* Added "or fouT" etc* i
22, Paragraph 3*2. 2*1. 7, Added feedi>ack current l-mitatlonJ
23a, Added new put,e for Detail Bequiremonts of Multiplexer
function of I0-20i402»l* '
2ii, Paragrapn 3«3«1«1, Added paragraph 3*l»i*l*l^ to j
exueptioos*
2U, Paragraph 3*3*1*1*1, Reviseu paragraph heading to read
I "Maintainability" in lieu ef "Maintenance Convenience,^
{ added sentence "Maintainability shall be considered", eljc*
Ipuge 2U, Paragraph 3.3*1*1»5, Mew paragraph added for Physical
Size*
Page 25, Paragraph 3*3«1*2, Added 3*1>1>2*6*
Page 2ba,New page addeo due to revising 3»3»2.1*2*
Page 31, Paragraph 3*l»»l»2, Changed "3.1. i. 2, 3" to read
3. 1.1. 2. 6' and 3.1.1. 2. 7.
Page 31, Mew paragraph 3.U.1.2.U added to reference paragraph
3.2.1.2.2 for bonding requirements*
Page 32, Paragraph 3*1*.1*3.2*5, Qianged to read "15g" in lieu
j of lOg*
iPa,,e 3U, Paragraph 3*5. 1.1.1* Revised paragraph heading to
I read "Itintainability" in lieu of "Mslntensnce
1 Convenience", added sentence "Maintainability shall be
I considered", etc.
Page 3U, Paragraph 3.5.1.i.5 "Physical Siize and Weight" moved toj
I page 3Ua due to rewrltting of tiie paragraph*
i Page 31, Now Psragreph 3.U.1.2.3 added to reference paragraph
: 3*2*1* 2*3 for grounding requirements*
See page Rev* g
BOEING AIRPUNE COMPANY
SEATTLE 34, WASHINGTON
MODEL
NO.
I Page
D JO-
■
_ f- . - ■ -
0 ■
SAC I6ai A-II2
a>7ooo
IREL/B-P
REV LTR
tfVISION
FOLLOW DESCRIPTION OF l^tANGE WITH: REASON FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN OOA’S, ETC.
5 o
> UJ z z
« * Cl
Pa,'e 3i4M*PMg« added to inolad* reviaion, P&ragraph 3»5*l*i>5 '
Raviaed apace and weight requiraoanta for clarification*
35i Paragraph 3*5*1*1*6*» Revlaed finiah raquiranenta to
ue in accordance with D2«JltO^ in lieu of HIL»K-Ul5u*
Changed colur nua^er to be 36^92 in Ilaii of 26329*
Adaed color nuad>er 31t300 and type TT-S>^27 ea^aal*
Ps^B 35* how paragraph 3*5*l*i*6*i added to reference M1L«F» I
lii072 for uae of disaiailar aetala.
Page 3^j hew paragraph 3*5*i*i*7 added to reference MlL-E-Ul5fc>B q\
for safety requlresients* '
Page 36* New paragraph 3*5*l*2*li added for grounding require- |
menta* . |
Page 36* hew section 3*5*1*5 added for Hujoan Factors requlre-
aonts* i
Page 36a, New page added for continuation of section 3*5*1*5* |
Page 5'.>A,New page added for new Siook Teat para ,raph.
Page Shi Paragraph U. 5* 2* 5*3* Deleted. , 1
Page 56* Para,^raph U. 5*3*2. 1, Free Drop Tost, deleted ali. , j
Page 96, Figure 10, Re-drawn to showw0,03g^/cpa 5*25 cps, ;
d.lgVcpa 25-1000 CDS with 12 db roll-off to 2000 ; |
1 cps in lieu of O.lgvcps 5*1000 cps with roll-off ,
to 0.025 f^/epa at 2000 epe* Title changed ^ :
"envelope for reliability testa" in l::.e« of "test
envelope for equipment operative (Jnatruaentation
compartoant) . "
Page 99* Figure 13, iepreeentative waveform for digital output
complex to RF section revlaed to show a rise time of
0*1 to 0.3 microseconds and a fall time of 0.3 to 0.7
microseconds.
Pbga IdOa, New Figure 15 added for Interstage equipment
Acceptance l%6t vibration envelope* i
Page j.:X)b, New Figure 16 added for Shock Test ^ctrua.
Pa.^e IdOc, Mew Figure 17 for Temperature-Altitude Teats. ^ '
Reason for Chungei Completion of basic design*
Revision A change Sffectivei B&D Hisslles 003,00li and on*
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
MODEL NO.
\Wi-ll3A
D/o-
B«c iMi
REV LTR
i
REVISIOM
FOLLOW DESCRIRTION OF CHANGE WITH: REASON FOR CHANGE, CHANCE EFFECTIVE
INFORMATICN, PRODUCTION AND TOOLING INFORMATION, RERUN DOA’S, ETC.
o
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FRgG BtTrision h addad
Bags Indax "a** add«d parat^raph 3*6 for daaign of alad trana-
mlttar and paragraph U.5*lt for (quallfleatlftp) teat of ali.-d
transmitter.
Page Indax "c* added Figure lb to index.
Page i. Section X, added died tranaKLttRr to scope of the
apeciflcatlon.
Page Paragraph 1.3 added paragraph to complete scope of
sled tranauittar apeciflcatlon.
Page 3« Added MlL<-£-005272B to Cbtremnant Docuaanta.
Page U6ay Page added to include revision, paragrapn U.3<6y
"Individual tests for 10-20U02-5".
Page U7f Changed paragraph U.3*6 to U.3.7 due to addition of
sled transmitter test requiromenta.
Page lt7» hrsgraph U.5.1* added paragraph U.5*l>6.1 to
exceptiona.
Bags 5bj Paragraph h.5«U. Preproduction tesi. aa applicable to{
sled transmitter.
Page 3>ba, New age added to complete sled transmitter quallfi«
cation taeU.
Page 65a, Paragraph 6.1.3, dddad paragraph to show Intended
use of aled trananitter.
Page liOa, Added page to Include Sled transmitter oesign
requirements.
Page UUb, Added page to inciuue sled tpnsaiitter, electrical
requirements and environmental condltlona.
I^ge liUc, Added page to include aled trananitter reliability
requireaienta.
Page UOd, Aoded page to include sled transmitter detailed
requlreiMnts.
Page UUe, Added page for continuation of detailed requirements
for sled ti'ansmltter.
Page hQff Added page for oompletion of detailed requirements
for the aled transmitter.
Page liOg, Added page to include aled transmitter prinary
power variation requirement.
Page lOOdfMew Figure 18 for Holloamn AFB test sled for PCM/fTI
telemetry.
Baason for Change i Procure pi;rts for Downey & Holloman Inte-
gratlon Testa.
Raviaion B Change effectlvet h40 sled testa Downey-HollomanAPi|
Page lU, Paragraph 3.1.2.2.3t Changed to read "17 watta" in
lieu of "15 watte". (PRE 9$CO)
Page 17, Paragraph ]«2«l-..2«d,?Baleted ”
power and". (P£R 9500)
Page 50, Paragraph U«I>*1.6.i added new paragraph for addition
cross-modulation teat requirement. (PER 9^00)
Raaeon for Changai Completion of basic design.
Raviaion B Changa affeotivei RbD Missilas 003,00U and on.
'Individual signal,
5g
C
iNil
_ L .
BOEING AIRPLANE COMPANY
SEATTLE 34, WASHINOTON
J
MODEL
NO.
PAGE
WS*)5»A
D10«20k02
h
me L&Fl
> QUAES' ASMA.,. aAmb. m«.'<
RtV LTR
itevisiON
1.
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANGE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DOA'S, ETC.
Title Fkge 11 Sivlaed llBt of active pages
Title ^ge 111 Mew Page added for additional specification
pages
O
a
Ui
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C !>■
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0.
Q. i .J
< ■'£.
Hags Revision ifj«k t Add new pages for revisions
Page Index a^ added section 3*7 for -6 requirenentSf deleted
•3 requirements.
I
I
Pago 1,
Page 2,
Page Ua,
Page 3a,
Page 10,
Page 1$,
Pago 16,
Page I6a,
Page 17,
Page Iti,
ftigo Iv,
ftge 19a,
Page 21,
Page 22,
Page 22,
Page 23,
Page 23a,
Page 2U,
Page 27,
Page 28,
Page 29,
Page 16,
Paragraph 1.1«3, Deleted -3 from scope, (PHR 9500)
Paragraph 1,U, Added multiplexer system (>6) to
scope (PRR 9500)
Paragraph 2.2.3» Referenced date and added "2-UliU6.
-8-36h" in lieu of "2.1iUl*6.8-3U5" (PRB 95oo) J
Parmepraph 2.1.2, Revised MIL«STI>>12h in lieu of {
-12A (PBR 9500)
Paragraph 3*1.1«U*1, Revised to include Reliability |
of coa^jlete telemetry system (PRR 95uo)
Section 3.2, Deleted multiplexer function from i
programmer. i
Paragraph 3.2.1.1.1, Delated reference to aultiplexet
function. i
Paragraph 3*2. 1.1. 5, Deleted last sentence (PRR 9500 )|
Paragraph 3.2.I.2.1, Revised connection requlremonto j
(PRR 9500) i
Faragrap^i 3.2.1.U Removed reliability requirement
for the multiplexer function of progremraer j
Paragraph 3,2,2,1.1, Revised logic requirement for
channel "fa"
Paragraph 3,2. 2. 1.1. 2, Deleted "’Ihe three or four"
Paragraph 3.2.2.1,J^1, Deleted "throe or four" and ;
"(aa required)" •
Paragraph 3*2. 2,1. 6, Deleted "three or four" '
Paragraph 3*2.2.1.U.3, Added ". . ,1^ for 0 to plus ;
10 mv channels (H® 9500)
Paragraph 3, 2, 2,2. 2, Added 0 to +.10 mv accuracy
(PRR 9500) '
Paragraph 3. 8. 2.3, Deleted multiplexer requirements
for the programmer
ParagTApR 3*3' • « Revised to >100 cards in lieu
of -10 cards (PRR 9500)
Paragraph 3*3<1*U, Deleted last sentence (PRR 9500)
Paragraph 3.3«2.1«2, Rmvlssd to increase capacity
of multiplexer -2
Paragraph 3.3* 2.1. 6*1, Revised sampling rate to
16,00 sps total.
Paragraph 3* 2. 1.1. 2, Deleted reference to multiplexer
function.
CqmUI
I BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO.
PAGE
W&H35A
010-20402
"r
S? !
REVISION
0
- h-
v.v*
Age
30,
Page
Age
30,
Ages 31,
Age
3U,
Age
3Ua,
Age
UOh,
Age
Uoi,
Age
Uu j
Page
UOk,
Age
UU,
Page
U5,
Age
U6,
Page
1*7,
Age
U7,
Page
U8,
Age
51,
Age
52,
Page
53,
Age
53,
Page
56,
Page
56a,
Age
50,
Age
50a,
Page
58,
Age
58a,
Age
U7,
FOLLOW OCSCRIFTION OF CHANGE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
_i - '’"OOUCTION AND TOOLING INFORMATION. RERUN OOA’S, ETC.
Alga 30, Paragraph 3*3*2*2*S, Raviaed to includa 0 td ♦ lOor
channala. (PfiR 95U0)
Page 30, Paragraph 3. 3. 2.2.6,l, Included 0 to ♦lOanr feed back
VBi tm»f <tuir»«iept/(?ilR 9500}
Phragrapn 3«3*2.2.7t2, Revlaed to *U to 10 nv"
In lieu of "leif^ level”. (PER 9500)
Payee 31,32,33, Deleted Dealgn Requlroeenta for 10-20U02-3
(PKR 9500)
Paragraph 3. 5. 1.1, Added paragraph 3. 1.1. 1,5 to
exception. (PRR 9500)
Page 3U, Paragraph 3.5.1.1.6, Added new paragraph to delete
D5-2300 requireNlnt. (PHE 9500)
Page Uoh, Page added for Design Requirements of 10-20li02-6
(PRR 9500)
ftige Uui, Page added for General Requirements of 10-2ol»02-6
i (PRR 9500)
Ptge liU j, Age added for detail requirements of 10-20li02-6 i
(PRR 9500) I
Page ItOk, Agn added for completion of requirements for ■
10-20li02-6 (PRR 9500) '
Paragraph U. 3.2,1, Avlsed second paragraph to
include ”-6'' in lieu of "-3" (PRR 950O) '
Aragraph l.3.li, Revised to . tests for !
l(K20U02-6" in lieu of ", . . 10-201*02-3" (PRR 950Q)
Aragraph U,3.U.l, Avlsed to include "-6" in lieu '
of "-3" (PRR 9500) I
Aragraph li.3.7, Added ", . . -6" deleted ", . . -3j"
(PRR 9500) ;
Aragraph U.l*,!, Added " , . -6" delated " . , -3" i
(PHR 9500) I
Paragraph 1*,5.1.U.2, Avised to include -6 system
in lieu of -3. (PHR 9500) !
Paragraph U.5.2, Revised paragraph to include i
system in lieu of -3 multiplexer. (PRR 9500)
Paragraph U.5.2. 3* 2, Revised to Include -6 system
in lieu of -3 multiplexer, (PRR 950o)
Aragraph U.5.2.U.1, Revised to include 76 system
in lieu of -3 multiplexer. (PRR 9500)
Paragraph U. 5. 2.5. 2, Bsvlsed to includa -6 system
in lieu of -3 multiplexer, (PRR 95uo)
Paragraph U.5.2, 8, Deleted (PRR 9500>
Page Aragraph U.5.2.8, Delated (PRR 9500)
Arat,raph U,5,l,7, Avised reliability tests to
include complete telemetry system. (PHR 950O)
Age 50a, Aragraph U.5.1.7, Bisviaed for new reliability
tests, (PRR 9500)
Aragraph U.5.U.U, Avised temp. -alt. test (9RR
Age 58a, Paragraph U.5.1(.U, Revieed to Include new temp.-
alt. test. (FRR 9500)
Aragraph U.5.1 Delated paragraph U.5.1.7 from
exceptio|M.
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BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
L.
HAl i,»l A-«?
MODEL
^ ' - ! _
NO.
PAGE
DIO- 20^2
- - - - J
Re\/
J
CHECKED
STRESS
approved
REL/B~P
REL DATE
ky
^ RIVISION
_i _ _
> FOLLOW DESCRIPTION OF CHANCE WITH; REASON FOR CHANCE, CHANCE EFFECTIVE
ac INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DOA’S, ETC.
Page 60| Paragraph U*6«2f Added ”•6", deleted (PHR
9500)
Page 63f Paragraph 6.1*I.2« Reviaed fourth sentence to read
"The aultlplexer eystem . . •* in lieu of "Ihe
■ultiplexer -3"» 9500)
Page 63« Paragraph 6«l.l*Uy Added "aultiplexer aystea (-d)"
•7 and -6 for intended uae. Deleted "O"* (PHR
9500)
Page 97$ Figure 11« Reviaed teat dlagran to include •6
syatema in lieu of *3 units* (PRR 9500)
Page 100c* Figure 17* Revised Tisap.-Alt* test set-up to
include two -6 systems* (PHR 9500}
Page 101* Hsvised to include -6 logic in lieu of -3 logic.
(PRR 9500)
Reason for Changei Completion of Basic Design
Revision C Change Effectives R&D Missiles U03»00U and on*
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: BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
I _ _
me 1681 «-«
MODEL NO.
WS-J33A D 10-20^0 2
PAGE
K
aPEHOVgD
REL/S-P
REL DATE
RKVir/.OK
f DiscfJinr.cN o. chancc wi h jrason ron chance, chance FEEfiCTivn' ^
PRO!.LICriON AND too.h;; INf ormation. rerun dda’s,' etc.
ir . . •
D .Title Page itevisod llao oT active pages.
Page Jievision L New Revisicin Pag;o added
Pago 12, Paragraph 3«1»2.1.3> tiavieed to Include ripple
j requirement.
jPace 13j Paragraph 3.1.2.1.12, Revieed transient potential
I to 28 ± 12 volts In IJou of twice the nominal
j primary potential.
I Page 22, Paragraph 3. 2. 2. 1.6, Deleted second' eantence,
! referred groundiiip requirements to paragraph
j 3.1. 2.1.3
jflaaBon for Change! Clariflcat Lcn of %3eciflcation
jpage 78a, Paragraph 6.U.6, Added new page for photographic
I requirements
^ Page lia, Added D2-ii751 to I\iblications
j Reason for Change t Air Force recjuost per IM Li9.
BOFIMG AIRPjlANE.' COMPANY,
, i4;. washinctok' ';-'
.1 ';!'L
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DOA'S, ETC.
r
^ I Title Page I, II, III, Rarlsed list of active pages.
Rev. M,N Added new pages for revisions.
Page 3, Paragraph 3. 1.1. 2.3, Revised last sentence.
w ; ^
U lu
u' (K
o| S
Rev. n
Page 3a,
Page 9t
Page 9,
Parigraph 3. 1.1.2. 7, Last sentence revised to "nay"
Page 9,
•Page 10,
Page 12,
Page 17,
Page 22,
Page 35.
in lieu of "shall"
Paa*agraph 3.1.1. '.1, Revised to include "out of
shipping container".
Paragraph 3*1. 1.3.1.^. Deleted "as encountered in
shipment of packaged equipment".
Revised non-operative environmental conditions to
35,000 ft. and -65*F in lieu of 50,000 ft. and -80°?.
I^ragraph 3. 1.1. 3. 2. 6, Revised to include "RMS....
overall (37 1/2 - 4800 cps) -Random".
Paragraph 3. 1.2. 1.1, Revised to include "56 con¬
secutive hours" in lieu of "indefinite period".
Paragraph 3. 2. 1.2. 3, Revised shield grounding
requirements.
Paragraph 3.2.2. 1.4.4, Added tolerance + 10?^.
Paragraph 3.5.1.1.6,®evised paint specifications.
Page 40a, Paragraph 3.6. 1.1.1, Revised Heat Sink Requirements
on sled transmitter.
Page 40e, Paragraph 3. 5. 2. 1.1.1, Revised transient potentials
Page 40J, Paragraph 3. 7. 1.3. 2. 6, Revised to include "RMS....
(37 l/2-’t300 cps) Random".
Paragraph 4. 3.1, 3, Added "upwards or . etc."
Page 46a, Paragraph 4. 3. 6.3, Added "upwards or... . etc."
Page 47, Paragraph 4, 5. 1.2, Revised third sentence to contain
sweep definition.
Paragraph 4.3.1. 3, Added "13g min. i.e. >t the
point of connection to the centrifuge".
Revi.^ed non-operative conditions to 35,000 ft.
and -65«F in lieu of 50,000 ft. and -80®F
Paragraph 4. 5. 1.4. 2, Added note to include option
of one -6 system in test chamber.
Page 50a, Paragraph 4, 5. 2. 5. 2, Restated test requirements.
No test required, and deleted note. •
Paragraph 4,%2.3.2, Revised t nird sentence to
contain sweep definition.
Paragraph 4. 5.2. 5.2, Restated test requirements.
No test required, and delated note.
Revised non-operative conditions to 35.000ft. and
-65®F In lieu of 50,000 ft. and -30®F.p*r». h. 5. 2. 5.1
P^agraph 6.3.17, Revised power distribution of
programmer .
’9, 90, 91. 92, 93, 94, 95» 100a - Added tolerance to
vibration envelopes.
i Pa.i'C 58, Para. Revised to ft. and -65*F.
Pa(je UOk, Para. 3«7.2.3» Kavised "indaf io "3'’ etc."
Reason for Change; Clarification of specification. (PRR 9500)
c^oN'ir
Page 44,
Page 48,
Page 48
Page 48a
Page 52,
i Page 53,
Page 53,
Page 71,
Page
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
NODEL^ j NO.
WS-li3A
DlO ' 2 04C'.i
REL DATE
REV LTR
REVISION
h
FOLLO* DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE, CHANGE EFFECTIVE
information, PRODUCTION AND TOOLING INFORMATION. RERUN OOA'S, ETC.
CP Af 'T -
P»g* 1, Paragraph 1.1.2, Rovised to show power for -2 only.
Page 22, Paragraph 3. 2, 2. 1,6, -Hevlaad to allow,. eajiyer tars
for -2 only, in prograamer.
Page 39 2evised to include power to -6 system,
j Pago 39a, Adddd new page due to revising of previous page,
I Page 40K, Paragraph 3,?.2.'i, Added Power requirements for -6
I system,
j Page 97, Revised Test Diagram
Reason for Completion of Basie Design (PfiH 1105)
i ReTFision S Change Bffcctivet R & D 'Missiles 003, 'JOL and on.
•■4
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BOEING AIRPLANE COMPANY
SFATTLF 24, WASHINGTON
RIVIUON
FOLLOW OeSCKIFTION OF CHANOt WITHi MASON FOR CHANOC, CHANOE EFFECTIVE
INFORMATION. FROOUCTION AND TOOLINO INFORMATION, RERUN DOA'S, ETC.
s s
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u
Pp) Title Page I, II, III; Revised list of Active Pages
Page Rev. 0, P, Q, R,
Added to include Rev. T.
Page 2, Paragraph 1,3 Re-written to amplify description
of the -3 Transmitter by defining a-9 iEIxciter Unit, I
a-10 Attenuator, Multiplier, Amplifier Unit and a j
-11 power supply. i
Page 2, New Paragraph 1.3.1 added for -9 Exciter Unit of the -3
Transmitter System i
Page 2, New Paragraph 1.3.2 added for -10 Attenuator, I
Multiplier, Amplifier Unit of the -5 Transmitter |
System
Page 2, New paragraph 1.3.3 added for -11 Power Supply Unit
of the -5 Transmitter System
Page 6, Paragraph 3.1.1.!.^ Deleted "and with a maximum of 10
bolts or screws".
Page 7, Paragraph 3.1. 1.1. 9*3 Deleted
Page 7, Paragraph 3. 1.1. 1.7, Revised to allow use of RF
mounting surface for heat sink during bench operation. ‘
Page 8, Paragraph 3. 1.1. 2. 6 Transmitter-power amplifier-added
"Modulation" between words "all" and "signal’'.
Page 9, Revised altitude and Temperature Requirements to ;
20P00 ft. and -45«F. faraqrafh 3.1. 1.3,1, 1
Page 12, Paragraph 3. 1.2, 1.1, Revised to allow external
cooling during bench operation. Deleted sentence
relative to approximation of mounting surface tempera- '
ture.
Page 13, Paragraph 3. 1.2, 1.6 Deleted
Page 13, Paragraph 3.1.2.1.10.4, Revised rise and fall time to .
be 0.3 ^ 0.1 micro seconds in lieu of rise time of
0.1 to 0.3 micro seconds and fall time of 0.3 to 0.7
microseconds.
Page l4 Paragraph 3.1.2.2.3 Cliirified VSWR requirement. '
Page l4. New paragraph 3.1.2.^i.5.1 Adaed requirement for VSWR
5:1.
Page 14, Paragraph 3. 1.2. 2.7 revised Definition of Center
Frequency.
Page l4a. Continued paragraph 3. 1.2. 2. 7 revision.
Page l4a. Deleted requirement that vendor be required to
conduct tests to determine optimum filter to miaimize
RF bandwidth and preserve coded data, 3. 1.2.2, 6
Page 15, Pauragraph 3. 1.2. 2. 9 Added tolerance to deviation
sensitivity.
Page 10, Paragraph 3.1.i.U.l Deleted "RF Section" and reduced
reliability requirement from .995 to .994.
Page 14, Paragraph 3.1.2.25, revised receiver paseband from 4.9
-5.1 Kmc to 4.9 - 5.7 Kmc.
See Rev. Psgs, r
MODEL
NO.
W3-I33A
VI 0-20402
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
PAGE
f^ev. o
IIVISION
FOLLOW OCSCRIPTION OF CHANGt WITNi RtAtON FOR CMANOC, CHAMGR EFFICTIVE
INFORMATION, PRODUCTION ANO TOOLING INFORMATION. RERUN OOA'S, ETC.
m
PagR
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PagR
I
Pag*
I
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Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
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40a, Paragraph 3*6 re-urltten to define -9, -10, -11
units as being part of the -3 transmitter system. j
40a, Pvagraph 3.6. 1.1.1, deleted requirement that internal
components not be exposed thru the removal of IneulationT
skin.
40a, Paragraph 3.6.1.1.P, deleted requirement that not over
10^ of tube circuits nay contain trimming adjustments, i
and requirement for no necessity of adjustment after
replacement .
40a, Paragraph 3. 6. 1.1. 5, Changed to read ^'transmitter
system" in lieu of "transmitter", (two places)
V>a, Paragraph 3. 6. 1.1. 3.1, revised to read "heater
voltage, and plate voltage, in lieu of "output power, '
frequency and waveform".
40a, Paragraph 3. 6. 1.1. 3.2, Deleeted.
40b, Paragraph 3*6. 1.2, Changed to read "3. 1.1. 2. 3" in
lieu of "3.1. 1.2. 6".
40b, Par.^graph 3.6,1. 2.1, Qrounding, deleted.
^b. Paragraph 3.^. t *2.2 Deleted sentence "Part numbers i
of modified connectors will be specified at a later date^
40b, Paragraph 3. 6.1. 3^.1 Changed to read "-IC’D to i
+70«C" in lieu of "as high as l60»r" ... i
hOd, Paragraph 3>6.2.1, Deleted requirement in regard
to production variations etc.
40d, Paragraph 3. 6.2. 1.2, changed toread. "transmitter !
syste '" in lieu of "transmitter".
40d, Paragraph 3. 6. 2, 1.3, Changed max. power drain to
read "12 amperes" in lieu of "10 amperes", "transmitter ■
system" in lieu of "transmitter". (2 places)
Paragraph 3*6.2. 1.4 Delete "Such adjustments —
components"
40d, Paragraph 3. 6.2. 1.3, Changed to read "Exciter" in ®
lieu of "transmitter". '
40d, Paragraph 3. 6. 2. 1.6. Deleted.
40d, Paraigraph 3.6. 2. 1.7, Changed to read "transmitter j
system" in lieu of "transmitter".
40e, Paragraph 3.6. 2. 1.8, Changed to read "transmitter j
system" in lieu of "transmitter". ' '
40e, Paragraph 3. 6. 2. 1,9, Changed to read "system" in. '
lieu of "unit", specified requirement appilicable to ;
the -9 and -11 units. |
See Rftv. t
BOEING AIRPUNE COMPANY
SEATTLE 24, WAfHIN0T0(l
MODEL
NO.
PAGE
WS-I33A
t)l0^2O4OZ
^y. p
«.C 16S1 ^-*2
_ _
ATOM
tlVItlON
FOLLOW OeSCIIIWTION OF CHAMOE WITHi RCAION FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, FRODUCTION AHO TOOLING INFORMATION, RERUN OOA*I, ETC.
O
IS
Ui
3,
iili
© P*8®
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
Page
•I
I
i Page
40e, Paragraph 3.6.2.1.10t Changed to read "tranamitter
system" in lieu of "tranamitter".
40e, Paragraph 3.6,2.1.10.4. Rerlsed rise and fall tine
to be 0.3 4 0.1 microseconds in lieu of rise tine of
0,1 to 0,3 nicroseconds and fall tine of 0.3 to 0.7
microseconds.
40e, Paragraph 3. 6. 2. 2, Changed to read "transmitter
syslem" in lieu of "tranamitter".
40f, Paragraph 3. 6. 2. 2. 2, identified power output as
being' from the -10 unit, deleted maximum pbworoutput
requirement, of 17 watts,
40f, Paragraph 3, 6. 2. 2. 3, Changed to read "'transmitter
system" in lieu of "transmitter".
40f, Paragraph 3. 6. 2. 2. 6, Re-defined center frequency. .
40f, Paragraph 3.6.2.2,7« Revised to read "resistance^'
in lieu of "impedance". Deleted sentence "The vendor _
will be required". .
40f, Paragraph 3. 6. 2. 2. 8, Changed to read I'transmitter
system" in lieu of "RF Section” (Two places) Re-' iv
defined a "one" to be represented by a minus 2 volt ' .
potential instead of by a zero potential,;"yAdded^^^V^ j
tolerance to deviation sensitivity. j
40fl, New page added for new paragraph 3».6. 2.2.8. 1^
40fl, New paragraph 3.6.2.2.S.1 added to j^specify'iJ, ,';^,,, ',,'.
modulation input sensitivity of
40g, Paragraph 3.6.2.2.9« Changed to read "transmitter ^
system" in lieu of "transmitter,'' ■ ^
43, Paragraph 4, 3. 1.2 Deleted method of conducting the
stability check. Revised center frequency test to:;;^;
"during warm-up the transmit ter-----’'_. V'
44, lew paragraph 4. 3. 1.2.1 Added test for ;5sl VSWR
requirement. ■ • ■
46a, Paragraph 4.3.6, Changed to read "transmitter system"
in lieu of "RF Section", '
46a, Paragraph 4. 3.6.2, Changed to read "transmitter
system in lieu of "RF Section",' ’
46a, Paragraph 4. 3.6.2 Deleted method of . conducting the
stability check. Revised center frequency test to ,
"during w^rm-up the transmitter — " I
40, Paragraph 4.5.1,4..1, revised temperature and altitude i
to -45*F and 20,000 ft.
SaaftEV. PMe r
BOEING AIRPLANE COMPANY
SEATTLE 34, WASHINGTON
MODEL
NO.
W5-I3JA
:)\o-2o4-oz
PAGE
Rev.q^
lAC 1611 A-F2
ATOOO
REV LTR
REVItlOH . S ^ S
9 s C$ S ^ > <v
- - - - >iu* zkIqA
FOLLOW OESCRIFTION OF CMAHOt MTM: REAWN FOR CHANCE, CHANCE EFFECTIVE $3«S2|£^
INFORMATION, FRODUCTION AND TOOLING INFORMATION. RERUN DOA’S, ETC. _
^ Pag* 48, Paragraph 4.5.1.4.,2 Rewrot* oomplet* paragraph
^ deleting reference to miatiplexlng equipment and
I figure 17. iJ
. ' Page 48a, Continuation of 4. 5. 1.4.2 revision changeifiv* to n
t four minutes, two places ^
I Page 49, Paragraph 4. 5. 1.6 Deleted test Cl. ■5^ V ^
i Pag* 50, Paragraph 4. 5. 1.7 Deleted RF Section from O j 5*
1 reliability requirements. OC \ t ‘
Page 53, Paragraph 4. 5. 2. 5. 2, Describes the multiplexing g CV 'll'
. tests previously Included in 4. 5. 1.4. 2. Ui ^ Z J
Pag* 58, Paragraph 4. 5. 4. 2, Deleted requirement for random Of — xJ
vibration. rVigO^X?* t> ^
Pa(^ 58V Paragraph 4. 5.4.5, Acceleration, deleted <>“ * (“ is
‘ PRC® 58* Paragraph 4. 5.4.4, Temperature-Altitude, deleted > > n: K
Page 58a« Paragraph 4. 5.4. 5, Humidity, Deleted.
Page 58a , Paragraph 4, 5.4.6, Revised to limit testing to
V':.. 1000 'me. ■
'4 Page 58a, Paragraph 4.5.4.?, Revised shock requirements to
lOOg with rise time of six milli-seconds in lieu of
X;-.,, ■ ' "^-’iv Figure • ,
Page 100c, Deleted reference to RF unit.
Page lOOd,'* Revised Terminology of -5
: Pag* 100e,{New page added for -5 transmitter system diagram,
‘ Pafa* Index Added -5 l!ran;,mitter system (Fig, 1?) to
■'v''' . ■ Figure. Index . ■
.A’ Reason for Change! Completion of Basic Design - Vendor Def icier jy
'-'I'''' '.if''..;., -vff., .•■>., '
Revision (F), Change Effective; ABOl and on
'2',: ■ ■ ACOl and on
, 3 ADOl SUld On
■ HAOI and on
\ 4’ ’. 'iS--'' SBOl smd on
SCOl and on
SDOl and on
i , SEOl and on
; SFOl and on
' SQOl and on _ _
©Page 50, Paragraph 4. 5. 1.7, Specified that Reliability
test system was to be refurbished from Qualification
and/or Flight Proof test unite. ^
Revision (F) Change Effective: ABOl and on N
ACOl and on ^
ADOl and on O
HAOl amd on Snl 3
SBOl and on u/q | 3
SCOl and on 8 2 '
j SDOl and on ^ ^ ‘ ^
SBOl and on H ^ 5 J
STOl and on . ■'fl
SQOl and on 0 5 o: Otf sd
r._, V-';';,,'
BOEING AIRPUNE COMPANY
SEATTLE 24, WAtHINOTON
MODEL
NO.
W$>I39A
DlO-20402
Rev.t(
lU I6U A-M
aTooo
REL DATE
p
n
1)
©
RIViSIOII,.
FOLLOW DftClirTION Of CHANOC WITHi MAKM fOI CMANOt. CHAMOt CffeCTIVE
MFOMMATION. fWOOOCTION AND TOOLINO WfOOMATION. REMIN OOA*l, ETC.
i
Pwg*
Page
'*0
S’
S
Pago 34, paragraph oompletoly rovUod to clarify
malntonaneo and troublo-shootlng tost points.
Pago 37, Granted oxeoptlons to noa-oporating environaontal
roquiroaents for certain compoaonts of the •4. F6>ra.9.5.k^
Pago 39, paragraph 3. 5. 2. 1.1, added power input frequency
toleranoe.
Page 39, Section 3. 3.2. 1.2, Completely revised for general
clarification, to separately list the inputs to the
multiplexer prograLniner and the multiplexers, deleted
requirement for capability of inhibiting a specific
number of command pulses, added requirement that
command and reset pulses be derived from a crystal
controlled bit rate oscillator, added requirement
that all three signal input levels be available^
added requirement that an external signal soxirce can be
used in place of Internal source.
39a, Section 3. 5. 2. 1.2, the above revisions continued
on this page.
39a, Section 3. 3. 2. 1.3, mcvm4>^ this page due to
revision of section section completely
revised for general to define type of
reset test, added requirement for sen. -automatic mode
of operation, added requirement for interchangeable use
of internal or external voltage source, added requiremei^t
for capability of continuous sampling of source only or
sample only, revised description and number of test
points and included them under this section.
Page 39b, New page added to continue the above revisions to
section 3. 3. 2. 1.3.
Page 39o, New page added to continue the above revisions to
section 3. 3. 2. 1.3.
Page 4o, Paragraph 3.5.2. 1.4, deleted, this information now
contained in revised form in paragraph 5. 5. 2. 1.3. 2.
Page 40, Paragraph 3.5.2.1.5 deleted, this information now
contained in revlaed form in paragraphs 3. 3. 2. 1.2. 1.2
and 3.3.2. 1.3. 2.
Pegs 37, Deleted section 4.3.3, preproduction test for
10-20402-4.
Page 38, Contlnuatix>n of the above revision.
Besson for Change > '.Custsmer Sirechion
Bsvision (F) Cnangs Effsctlvet ABOl and on
ACOl and on
, AOOl and on
HAOl and on
SAOl and on
$B01 and on
SCOl and on
5001 and on
SK>1 and on
SFOl sad on
^ , T- SQOl and on
%
oe
oe
BOEING AIRPUNE COMPANY
SEATTLE M, WASHINOTON
MOOEU
^ _ 1 i 1. u.
NO.
WtrtMMI
DK)'204-02
r'
'1
PAGE
R«V. S
lAC 16*1
S7aM
i-.' -
I
« tIVISIOM
t—
•J ■ . — --- - . - .
^ FOLLOW OetCRVTION OP CHAMOl WITH> lltASON POR CHAHBC, CHANOf EPPECTIVE
at' IMORMATION, PRODUCTION MID TOOLMC MPORMATION, RERUN DOA’S, ETC.
Page 30a, New paragraph 3.3.2«2«*^ added to detail oonunon
mode requlrenenta,
Pac* UOa, Fu«^ph Dalatad rafaraaoe to
as balflg an aaespilen.
Bags UOa, Paragraph 3*8«l*l«2t Cmpoaanta dalatad.
9 g d S
- a i 8
> 8 oe < ui
IS S V S 5
O Ml
Ml . H
> "i *
e a o
a j j
a Ml Ml
4 « a
Reaaon for Change : Engineering Error
Revision (F) Change Effective:
ABOl and on
ACOl and on
ADOl and on
HAOl and on
SAOIa and on
SBOl and oh
SCOl and on
SDOl and on
SEOl and on
SFOl and on
SGOl amd on
Page ■ 39cT; added paragraph 3. 5. 2. 1.5.1.^ requiring a printer
■ • and 'detailing it 's requirements, > .
aP,'
d x-
bkx'
Page 46,* 'Added requirement'for printer checkout on acceptance
: V teats for -4. Pere^r’a.rh 4. i.S.l '?>'*-■; A ■
Reason for Chang^ Design Improvement
Revision (F) Change Effective: ABOl'and on “ ■
■ ^^'-r ■AC01»'and*on ■ ,. ' '■■ : .■ .
^ SAOl and on •
• '^3?^ -'^4 .SBOl and on' ; ■
- 'S SCOl and on .
• jiy V>*v^
. Hi?" 'v •’.,-1 .*'•
- ■'f-: • *
SDOl and on ; •. !
SEOl and on ,:
SFOl and on
SQOl and on ,
BOEING AIRPLANE COMPANY
SEATTLE 34, WASHINGTON
)EL I NO.
W$*I9»A
^10-20402^
lAC IMI A-A2
IIVItlOM
FOLLOW OCtCRIFTIOM OF CHANOC WITHi REASON FOR CHANGE, CHANGE EFFECTIVE
RIFORMATION, FROOUCT KM AND TOOLING R4FORMATION. RERUN ODA'S, ETC.
Pag* 1, paragraph 1.1. 3t Rovisad -100 ate. to -12 etc.
Paga 2, paragraph 1.4, Ravisad -100 a to. to -12 ate.
Index a, Reviaad -100 etc. to -12 etc. (two places)
Page 2a, Added to include revisions of paga 2.
Page 3, Paragraph 2.1.1, Reference to MIL-E-4970A delated
Paga 4a, Paragraph 2.2.1, Added reference to BAC Docunents
D2-4861 and D2-5051
Page l6. Section 3.2, Added logic card design requirements to
programmer section.
Page l6a. Paragraph 3.2.r.l.4.-2, Deleted statement about
■ assigning dash numbers to cards at a later, date.
I^ge 19*,. Paragraph 3.2. 2, 1.1.1. Revised to specify, occurrence
."Vi'S during la.stlbitjtirae of , last word in lieu of first bit,
!^4^;i^-1^itinM,/of^fir^t|^^dr§“^^ • ■ . . . '4
Page 22,^^Paragraph'$3.2r2i,l,4.3,\Deleted requirement for fall,^
time'; and 'added*ma'x,}'aample''on’% time. ....pi's
Page 22 Paragraph^ 3 ,♦ 2 r2 i 1 .4 , 4 Impedance , Deleted
Page 22,^^P*ragraphl3ii2i2lli4.5,‘^Hevi8ed to require 1.0 oilli-
amnslto 'coder ?in'^lie>f of one’ railli-ainp for the first -,4
p bit ^time,''* and a;.decr ease'' in current by a factor of two
ffi.i for .each^successive ^it'time.' ' ■ '
Page 22,'” Paragraph *3.2. 2II, 6, revised power drain to 1.10
amps "in '■'lieu'''d'f‘li 50 amps.
Page 23, Pafagraph^3«2..^i2. 4, .Revised to extend limits of faul^
r isolation^frora’-O.'l,'' >5.1 volts to -2.5, +5*8 volts,
Page 24, Section 3. 3»^Revi8ed logic card numbers to -12 etc.,
referenced section specifyin : card functions.
Page 24, Paragraph 3.3.1.1.1j revised sentence to "a minimum"
in lieu of "without".
Page 24, Paragraph 3.3.1.1.4, Revised assignment of test cards
Page 30, Paragraph 3. 3. 2. 2. 2, Deleted maximum expected common
mode of 200 mill i- volts.
Page 30a, New. page added for paragraph 3. 5. 2, 2. 8.
Page 40b, Paragraph 3.P.1.2.2, added new paragraph to
H include connector requirement.
Page 4ok, Paragraph 3. 7.2. 4 added sentence to include current
drain requirement of 0.7 amps.
l^ga liOp, New paragraph 3.8.21 and 3*6.22 addad to Idontify
«32 and -33 r^ialator oarda
Page 17, Paragraph 3*2. 1.2. 3, Added rsquireawnt for case
ground to be brought out to connector pin.
y 5, I • ‘ '
'V -”4
V';
MODEL
_ 1 _ _
NO.
BOEING AIRPUNE COMPANY
ICATUE U, WASHINGTON
PAGE
Rev. u
BAC 1611 A-BZ
B-ZOM
Vv
ifr
ii.-
f..,- . ■:
^h, -'■%’
. A
,S •’■ ':•' '£y A
.’• S'!’' •; '■“(l.V'.rj
;ll., V 'vf-’-v
r'?i- ■ ,. 1,
"Vit
' '■ ■ ' ;^ ’I'
KIVISION
'FOLLOW DCSCRIFTieN OF CHANOt WITHi RIASON FOR CHANOt, CMANOE EFFECTIVE
INFORMATION. FROOUCTION AND TOOLINO INFORMATION. RERUN DDA't, ETC.
iX:
\>
Pages 401, ^Om, New pages added for incluRlon of logic
40n, 40p, card functions.
Page 4C»i, Paragraph 3*7» Revised -100 etc, logic cards to -12
etc. logic cards.
Page 45, Paragraph 4. 3. 2. 3, Revised requirements for checking
programmer design.
Page 45, Paragraph 4.3.3, Revised -100 cards to -12 etc.
Page 45, Paragraph 4.3.3.?, Revised requirements for checking
multiplexer design.
Page 45a, New page added to continue revision.
Pegs 45a, Paragraph 4.3.4 Revised -100 cards to -12 etc.
Page 47, Paragraph 4.3.8 paragraph changed due to addition
of acceptance tests for logic oeurds.
Page'47, Paragraph 4.3.8 Revised logic cards to -12 etc. in
? lieu of -100 etc.
Page 47* paragraph 4.4.1, Revised logic cards to -12 etc.
' ■ in lieu of -100 etc.
I^ge 48, Paragraph 4. 3. 1.4.1, revised temperature and altitude
to -45»F and 20,000 ft.
Page 5^b, Added new page due to revision of paragraph 4. 5. 1.7
on page 30a.
P®S®i,51t P^agraph 4.5.2, Revised -100 etc. cards to -12 etc.,
deleted "this set shall not be used for any other tests
PRB®.51i Paragraph 4, 5. 2. 1,2 definition of data channel of
each representative type expanded.
Page 53, paragraph 4, 5.2, 5.1, Revised non-operative altitude
and temperature test requirements to 2iC|pOO ft, and
• . -45*F.
Pa^ 60, Paragraph 4,6.2, Revised -100 etc, to -12 etc,
identified BAG Functional Test Document.
Page 0, Paragraph 4,6.3, New paragraph to Identify BAG
Functional Test Document for -4.
Page 93, Figure 7, Revised to require 0,2Gvcps from 25 to
, 2000 ops in lieu of 0.5G^/cp8.
Page 98, Revised command pulse time and analog output,
* G .. also revised identification code allocation.
Page 99, Revised digital pulse to be symmetrical, also
revised identification code allocation.
Page 101, Revised -100 etc, to -12 etc.
_ 1 _
BOEING AIRPUNE COMPANY
SEATTLE 34. WASHINGTON
Mooeu
- 1 _
NO.
PAGE
R«v. V
»*c i6ex k-n
/ '
T)
J
%
ilVItiON
FOLLOW OetCRIFTION OP CHANCB WITH’ KCASON FOR CHANOE, CHANGE EFFECTIVE
INFORMATION, FROOUCTION AND TOOLING INFORMATION. RERUN OOA'S, ETC.
©
Rwaaon for Change! Completion of Basic Design
Revision (F) Change Effective: A801 and on
AOOl and on
ADOl and on
HAOl and on
SAOl and on
SBOl and on
SCOl and on
SDOl and on
SEOl and on
SFOl and on
3301 and on
Page 4a, Deleted reference to D2-4571 "Film Report-Still
and Motion Picture Photography"
Page 78a, Section 6.4.6, Photographic Coverage Requirements
deleted.
Reason for Change; Customer Direction
Revision (F) Change Effectives
.,3
jglu.
8
lodl
a
V
?
ABOl
and
on
ACOl
and
on
ADOl
and
on
HAOl
and
on
SAOl
and
on
SBOl
and
on
SCOl
and
on
SDOl
and
on
SBOl
and
on
SFOl
and
on
SOOl
and
on
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
<
0^^
rr
MODEL
_ 1 - t.i-L
NO.
Dl0^^04^2.
I
PAGE
Rev. w
SAC iMi A-n
ATOM
RfVlSION
'sr 'j v.«
^ ‘trj'ji ' i( N AN
Pagu Numbering Completely Hevisod
Title Page 11 - Revised list of Active pages.
Title Page 111 - Revised list of Active pages.
Revision’ Pages - '
Added to include Fiev. G.
' ,V. • ‘
Index a page Revi8ed^sub-headinr]3.1^; through and
; ■|ii"»5J^l|,throughlliT_5.li;,bylremoying Part ''
I Numloers^a ixiyadd rjigl'par t^ Nomenclature . ; ' ■ .
A ■ Page*numb'^'’rs f were J revised. "> ■ ’■ ''"'/'V'
• 'f Sect^3;8?^'‘3.9 ‘a'ded"'- -
Index ,b page-;’ ’'Page^numbors; we: e revised. # Fr t'v ■
^ j lr!?ex c page ■,-^,^F':' Figures'_,V,),andi;lu^,are^ael'- ted.' . '* ‘
o'.- A ■■ Pa(uTnumberE'-Vlre’'*^:'cvisedf1.V.:/'' ,
» t-ii, -.ov,.
I.:; Inaex u pa^^e Figures ■■2u>tnrou ,h^?3^;.are. new.
! 't-'"' . vv.oOJ'V-r’-'-, Page*"'numb'ers’“were‘'revisedl •
Pa, 2-
I itit.e I tiiruugn 22.,werfc pages -i througn ;li>. V'- if :'
' , i^f;e'i- f,.,o'¥Para^a^h 1.1.2, "(lo-^..u02-i^;i(K;^02-Ul)'' f ,
ParatXapn'- i. w3, "Multi. lexer' (i'J-20Uu2^2,
. . ii0-20U02’-ii2)" was f 'Mul t iplexer| CaTel ( 10->'Vo' - '
f?0ir02-2)tand'''io ie'ear-.s .( i0-/'Jlj02-i'2;H,-i3,' \ t. F
' ' : t(^ ) . v' ^
.-V r)„ — ^ O . hM n ' O .l./i"'. I.-' T o. 1 ). \fl
■ 10-2Uli02l6) ",fand:J^all*' places/within"
ReferencesHo' specif ic' part "numbers -.’re
•' deleted. •'. ■'“'o -fi- .o'.
. .aragraph l.li.l, "(10-20102-7, 10-20L02-U7)".
was "(i0-20li02-7 ■'. . • - ' '• . ’
Part numbers' were replaced by part nomenclature.
liijrOlLi AIR^'LAnE ^
NS-133A
D1U-20U02
LTR -
REVISION
> FOLLOW OESCRIFflON OF f.MWNGt WITH RFAjOn M'.R 1.,'*,,' ' ll
UJ I
OC : INFORMATION, PRODUCT ION ANI' TO'.'I l"<0 INF-. Rf < ' i .in. RLR'N I
I
0
Page 3'
Paragraph 1.U.2, ••(10-20U02-6, 10-20Uu?-U6)"
was "(10-201^02-8)", line 3, "Control Box was
10-2uli02-7 (Multiplexer Control)."
Paragraph 1.5 and 1.6 are new.
Page 7- D2-7667 and D2-9129, Boeing Documents - new.
"D2-U751 (Film report Doc.)" was "deleted"
by Rev. 0 21-50000 , 21-50065 and '21-50)105 '
Boeing Drawings - new.
Pages 23-. throu^ 37 were pages 16 through 23a.
Page 23- Paragraph 3'2, "Design Requirements - Multi¬
plexer Progranmer and Logic Cards" was "Design
Requirements for 10-20U02-^ (Multiplexer Pro¬
grammer case) and -12 etc. (Logic Cards)".
Lines 2 and 3 " . . • 10-201102-1, 10-20U02-la
0 ... "added to first sentence.
Page 27- Paragraph 3.2. 1.2. 5, last sentence, D2-9129
was D5-228fa.
Paragraph 3.2. i. 2.6, lirte lii, sentence "Ihe
multiplexer system ^rounoing etc.", was aaded.
Page 32- Paragraph 3*2.2.i.i,, xine 16, "128 channel
portion of the area "C"' multiplexer unit"
was "larger multiplexer unit (10-20u02-2)".
"(Ca)" and "(b)", com. letely revisca.
Page 3li- P^^fraph 3.* •2.1.1i.3, completely revised.
V Paragraph was rewritten and requirements
■ redefined.
' ■ Paragraph 3.2, 2.1.1. U, "Irapedanci - the'
output etc." was deleted by rev.
■ . Requirements were reinstated.
Paragraph 3.???.1.U.5, line 2, "to the coder •
for a full etc." was "to the coder,."; line 6,
"Milliamperes." was "Mill-amps.".
.a
r. t
•JL
,
See Rev. Page ah
1 _ , .1
130EINC AIRPLANE COmPMnV
I'xGi
saJOti. 'NO.
W-133JI
D10-20L02
Rev. y
4
REVISION
HOL«.OW OESCRIPTICN OF CHANGE WITH REASON EOR .HANGS, i.HANor EFfU' Vvf
INFORMATION, PRODUCTION ANO TOOUNG INI OmmaTiON, RERUN :,OA'S ETC-
S ; ■ < O' ’ a-' !
8e« Rev. Page ah
Page 35-
fege 36-
Pa£e 37-
Paragraph 3>2.?.1.6 WHS rewritten. Power drain
llinltatlons and references were revised.
Paragraph 3. ^.2.1.6.! was previously referenced
Inforaatlon of paragraph 3.I.2.I.3. CoBi{,letely
revised.
Paragraph 3. 2. 2. 1.6. 2 was previously ref^eeneed
Information of paragraph 3. 1.2. 1.3. Completely
revised.
Paragraph 3. 2. 2. 1.9, Kew specification
Paragraph 3.2. 2. 2. 2, Completely revised.
Paragraph 3«2.2.2.2.1, hew sub-paragraph.
Paragraph 3*2.2. 2. 2.2, New sub-paragraph.
Paragraph 3* 2. 2. 2. It, Completely revised.
Pages through U3 were pages 21t through 30a.
Page 38-
Bage 39-
Page lt2-
Paragraph 3*3, "Design Requirements for Multi¬
plexer and Logic Cards" was "Design Requirements
for lU-20ho2-2 (Multiplexc * Case) and -12, etc.
{Logic Cards)".
Paragraph 3*3, First sentence, " . . .Milti-
plexer (iO-2oitU2-2 or ij-2Dlt02-lt2) for ..."
was *. . .Multiplexer Unit for ..."
Paragraph 3*3*2. 1.3, line 3, "the conmand
logic to be used etc." was "the represent¬
ative command logic to be used etc.".
Paragraph 3*3*2. 2, line 2, "and applicable
input data etc." was "and input data signals
in accordance etc.". Paragraph 3*3*2. 2. 2,
completely revised. Paragraph 3*3. 2. 2. 3,
"Delete" was "tho DC drift over the operating
etc.". Paragraph 3.3.2.2.li, "Delete" was
"paragraph 3*2. 2. 2. 2 is applicable".
Paragraph 3*3*2. 2.5, "Delete" ws "The
3.inearity of low level signal e’tc,".
Paragraph 3*3*2. 2. 6, Completely revised -
requirements reduced.
BOEING AIRPLANE COMPANY
MQDFl. i
D10-2Q1«02
Rev. z
RF
REVISION
a(
► f’fStR'PTiCN or ri-ANCt Wl.'M ‘.'j'-'S M' K^
.hJK'^MATION. P‘?Or>ur7 tON Ar^f) '••Cl'N', / v>» - *. .n V'. ^r-.
0
Paf,e li3- Paragraph 3*3» .2.8, line 2, "20,000 to 1"
was "100,000 to 1".
Pa^es US through $6 were pages 3U through IiO.
See Rev. Page ah
Page li3- Paragraph 3»i>, "Design hequirements -
Simulation anu lest Equipment" was "Di.sign
Hequirements for 10-20ao2-li".
Ihe general explanation was oomj- lately rewritten
to incloOe both 10-2Uh02-U -na lu-20l;02-Ui
equipment.
Paragraph 3.!>‘l.l*i, completely revised to expand
specifications for special tools.
Page U- Paragraph 3.5‘1.1.5, completely revised to expand
requireme;.t6 for weight variance.
Paragraph 3* 5* 1.1*6, line 2, "02-7687" was
"D^-i 300".
Page li7- Paragraph 3*5*l.l*iJ.l, new specification.
Paragraph 3* 5* *.2.1, uequirement for h.F.
filters aoded.
Paragraph 3*5. 1.2.?, line "A:'P laper Block
Assemblies etc.", exception added,
Paracraph 3*5. 1.2.3, N' w paragraph. Require¬
ment for metal enclosures ;aded.
l^ge Itfa- Paragraph 3-3.1.li, linos 1 and 2, "v;ith the ex¬
ception etc,", added reference change only.
Pa,e U9- Paragreph 3.3.1.5.1.C, lines li,l? and 13,
Added to para,;,raph.
Paragraph 3.3.1.5.1.3, liries 6 and 7, "Commer¬
cially supplies units are osc.", auded.
Pago 3.- Paragraph 3.3. 2.1, completely revised.
Paragraph 3*5. 2. 1.2, "Multiplexer equipment"
was "Multiplexer and Multiplexer programmer",
requirement.
Paragrapn 3. 3. 2. 1.2. 1.1, lines t, 9, 10 are new,
exception added to requirement.
'V^
I
ROWING AIRPLANE fw 'An,'
lOIr i-
WS-133A
D10-20l)02
Rev. aa
RtV
REVISIOH
HOlI tjw rt 'iTRirTlC'N OF ‘_MANr,t »I1H R' Av. N M)i/ 'H-in,!' .-Mv I;v^
INFORMATICS, FRODUCTION AND 'I'jCI ING ISF 0(ts AT |On, RiRIS ..I'A'i '
See Rev. Page ah
Pa^e 51-
Paragraph 3.5»2*i*2*2.1, "10-201102-6" removed
from aenterct.
Paragraph 3»5.^*l*2.c.2, completely revised.
Paragraph 3.5.^.1*^«2.Ua second sentence was
deleted.
Paragraph 3.5.^«l«^.2.U.lf added to describe
coifimon moae signal inpst requirement of
lu-2 juU2-iT equipment.
Paragraph 3.5*P.1.2:.2.1i.2, aaded to describe
common moae signal input requirement of
10-20li02-Uit equipment.
rarafiTaph 3*5»2.1.3.1» lines 6 and 7, "and
Multiplexer equipment feedback current." added
to sentence.
Page 52- Paragraph 3*5.2.1.3»1» Item (,), added.
Paragraph 3«5*2.1.3.1»1> completely revised.
Separate requirements for 10-20^02-1; and
10-20h02-Ul; equipment aeded. Sub-paragraph
"(a)" completely revised.
Page 53- Paragraph 3«5«2.1.3.1»3> Completely revised.
Reference tc a relay was deleted.
Pares 53 & 5li-
Paragraph 3.5.2.1.3.1.U, ^mplktely revised.
To specify applicable printers for respective
equipment 10-20^02-1* ana 10-201*02-1*1*.
Page 5h- Paragraph 3.5.2.i.3.1.U.2, ^ine 2 of sub-para¬
graph "(a)" "... of the basic unit" was ".. .
of the b>.sic lo-20Uo2-i*".
Page 55- Paragraph 3»5»2.1.3«2, lines 13»ll4 and 15
added. •
Pages 57 through 63 were pages UOa through hog.
Page 57- Paragraph 3.6, "Design Requirejdants - Sled
Dransmitter System” was "Design Requirements
for lo-20l*02-5".
r ,
BOEING AIRPLANE COmF'aNY
MjOcI. . NO.
WS-133A D10-20U02
'tM
Rev. ab
-T OP
(
REVISION
> FOLLOW OFSCRIPTION OF CHANCE WITH. REAbON FOR CHANGE, CHAHCE EFFFCTIV!
0: 1 INFORMATION, PRODUCTION AND TOOLING INFCHM AI ION, H' RlN I'.DA’;, E’-v..
I^ge 61- Paragraph 3«6.2.I.6j DeBuriptlve Criteria waa
deleted.
>■ i.)! 2 z, V , c! ij, '
> , ^yj -j < ‘u . ^ u _i w I
' Uj ‘ ^ a. I T ' r. : M Uu' t
c ce : J ‘ LJ '-v , ■«/ ' 1 i ct ■
See Rar. Page di
Pages 6li through 6? were pages UOh through Uuk.
Page 61*- Paragraph 3. 7# "Design Requireiaents , Multiplexer
System" waa "Design hequironents lor 10-201*02-6
Multiplexer systen consisting of 10-201*02-7
and etc.".
Paragraph 3.7* Descriptive Criteria, Completely
revised.
Paragraph 3«7.1.1, line 2, "3. 2. 1.1* was
"3.3.1. 1".
Paragraph 3.7. 1.2, line 2, "3. 2. 1.2" was
"3. 1.1. 2 and exceptions".
Page 67- Paraa*aph 3.7. 2,1, line 5, "Auxiliary Box" was
"-8 Cauxilliry box)"j line 6, "Auxiliary Box"
W.HS "system"} line 8, "with each -8 (Auxiliary
Box) etc." was deleted from sentence.
Paragraph 3.7. 2.2, line 2, "Auxiliary Box" was
"-8"} lino 3, "Control Box" was "-7"| line 1*,
"Multiplexer Programmer" was "-1 Multiplexer
Programmer".
Paragraph 3.7.2.1*, line 1, "Multiplexer" was
"-6"} line 1*, "-7" deleted from sentence.
Paragraph 3.7. 2. U> line 7, "-7" deleted from
sentence.
i^ges 68 through 83 were pages 1*0 1 .through l*0p.
Section 3.11 « Completely revised to reflect new
part numbers and aau.ify description.
lu-2uU02-12, and 10-2ul*o2-13 were deleteu,
’10-2l;1*02’’30 aescriptioD traniTfered to new section
3#9 • '
10-2Ul*02r36 through 10-201*02-38, 10-201*02-1*9
through iu-20l*ui -67, and 10-201*02-1*9 through
10-201*02-77 added to section 3.11 with applicable
descriptions and usage.
BOEING AIRPLANE COMPANY
I
I
I _ _
MijOEL ! NO.
-I
ie-13JA ; D10-20l*02
Rev. ac
» At', .6fll
PEV L.TR
REVISION
(
’-'CL'.O* ./( j.'AK (h'N 01 ‘itAl.Ot ♦'Tl-' • ■ --Jl’i M'.V
INFOKMAI ION, PROOllCT inr. AMO tOL- >■
See Rev. Fags ah
0
i’a.ges till anu bS-
Section 3«9 New section Tor accei-sory equip¬
ment.
i0-20li0y-30 transferea from section 3»ti.
10-20iij: -39, 10-2uliJ2-li3, 10-^01102-115, and
10-2olio2-6b addeu.
Pages 86 through llU were pages lil through 61.
Page 86- Paragraph u.1.1.2, line 9, "Changes to the
approved procedure etc." was "Changes to the
procedure etc."j lit.e liv, "only after BAG con-
currance." was "only after EAC approval".
Page oti- Parappraph li.3. Descriptive si^edif ications con¬
tained within parapraph were referenced to
pfirapraph h.l.l. Rewritten
Paragraph li.3.1, "Individual tests for
10-2ul;C2-0, 10-20li02-lx';" was "Individual tests
for 10-20U02-0".
Page 89- Paragraph li.3. 1.3, "a minimum operational teat
consisting etc." was "equipment operation within
the performance etc.".
Paragraph li.3«2, "Individual tests for 10-20li02-
i, 10-20li02-iil" was "Individual tests for
10-201ij2-1".
Page 90- Paragraph li.3.E.l, line 3 "’Ai’itli logic cards
inserted . . . etc." was "with -12 etc. cards
inserted . . . etc.". Lines 7 tlirough 11 -
new specification.
Paragraph li.3.2.3, lines 1 and 2, ". . . Sim.
and l^st Equipment . . . etc." was ". . .
test equipment (-li) . . . etc.".
Page 91- Paragraph li.3.3, "Individual tests for
lU-20liu2-2, 10-20liU2-li2" was "Individual
tests for io-cOU02-2".
1
NV'
BOEING AIRPLANE C0‘>PANY
•-ODtl.
W-131A
NO.
DIO-2OI1O2
t-A
Rev. ad
f.K( J.n A-J*.
REV
REVISION
HOLLOW DESCRIHTiGN OF '.haNGF wHh H- a.O.'. Ki w
information. PRCOOLT ion ANO tool ir.r. I- I .'•VM H-fhll'N
.i I ■ I '
Page 92- Paragraph iintjs ti through 12, new
specification.
Paragraph "Inhiviuual tea os for 10-2oiiu2
-6, lU-2oUo2-ii6" was "Inaividual tests for
lU-2uU0k'-6".
Paragraph U.3.U» line 2, "performed with logic
caras Inserted." was performed with ^2 etc.
caros inserted".
Paragraph U.3.li.l» line li, "10-20h02-6 or
10-20lLU2-li6 Multiplexer System, Figure 15
etc." was "-6 the envelope of Figure 15 etc."
Paragraph Ii.3.U.2, lines 2 and 3> new.
Paragraph U.3.5, "Individual tests for (10-
20li02-li or 10-2 .h02-Uh)" was "Individual
~ tests for 10-20li0?-U".
Page 93“ Paragraph 1l.3.5*2, "Performance of 10-20U02-h"
was "performance of -U"; descriptive criteria
completely revised; Items 12 through 15 - new
specification.
Page 911“ Para^praph h.3.5.2. Items 16 and 17, new
specifications.
Page 96- Paragraph 1*.3»7, Completely revised.
Page 97- Paragraph U.3.6, "Sampling tests for 10-20U02
-u, -i, -2, etc." was "Sampling tests for
10-20h02, -1, -2, -U. -5» -6, -12 etc."
Paragraph ii.li.i, "Component testing for
10-20ho2-o, -1, -2, etc." was "Component
testing for 10-20Uu2, -1, -2, -U* -5, -6,
-12 etc."
Paragraph U.5»l» "Preproduction (flight Proof)
tests for I0-20UO2-UO" was "Preproduction
(flight proof) tests for 10-20li02".
Paragraph li.5.1.2, line 6, "l/2 octave/minute"
was "one octave/minute"; "botn upwards and
downwards etc." removed from sentence.
Page 98- Paragraph li.5.1.1i.2, "Flight conditions for
10-20li0?-h0" was "Fli^t conditions for
10-20a02".
BOEING AIRPLANE C''^MrAr^Y
A* . . ' NU.
M5-113A
D10-20U02
See Rev. Page ah
t' Vtii
Rev. ae
REVISiOM
I
> : l=OLLOw description of chance kith RE*S;n for CMANCE, FfFF.T'VC
^ I
a INFORMATION, PRODUCTION AND root INC IM Cliy.-.TIUN, RfkON OLA" f.T.,
'T
^ ir
< !aJ
.j . (t . r.
' a
Page 9$
Page 100'
Page 101
Paragraph U<5*1*U*2 (d), lines 2,U>9» and 11,
"600* F" was "700* F".
Paragraph U.5<1>^> test c?, nev specification.
Paragraph li.5«1.7, ReliabiLlty tests are
deleted.
Page 103- Paragraph U.5.2, "Preproduction (flight proof)
taste for Hiltiplexer Programmer, Multiplexer,
and Multiplexer System" was "Preproduction
(flight proof) teats for liJ-20h02, -1, -2, -6
and -12 etc.". Criteria completely revised.
Paragraph U. 5. 2. 1.2, Completely revised.
See Rev. Page ah
Alga lOli- Paragraph It. 5. 2. 1.2, Rewritten, intent un¬
changed.
Page 1U5- raragraph It. 5*2. 3.1, line 1, "Multiplexer
Programmer (10-20lt02-Ul) and Multiplexer
(10-20U02-lt2)" was "ia-20lt02-l and -2"|
line 3, deleted "10-2UiiU2-l, (10-2alt02-2)".
Paragraph It. ^.2. 3*2, line 1, "Multiplexer
System ( 10-20h02-U6) " was "io-20ltu2-6"j
i.ne b, "l/2 octave/ffllxatte” was "one octave/
minute"; line 9> "both upward and downwards
etc." deleted from sentence.
Page 10€- Paragraphs U.3.2.U«1 and It. 5. 2. 5. 2, heading
reviseu to reflect new part numoers.
Paratraph it. 5.2. 5. 2, Item (C), lines 2 and 3»
"600* F" was "700" F".
Page 107- Paragraph It. 5.2.5.?, lines U and 5» "600*F"
was "700* F".
Paragraph lt.5.2.5.2, line 9, "(lO-20lt02-U6)"
was "10-20lt02-6".
Phge 109- Paragraph It. 5. 2. 7, test a3,. "and Control
Boxes" - newj test.dl, "and Control Boxes" -
new; test d2, "and Control Boxes" - new.
ff
'
BOEING AIRPLANE COMPANY
' NO.
WS-133A. I Di0-20li02
r> V '* c
Rev* af
ijA' A-J-;
2. K>^)0
K ! REVISION
- .
> |•Olt.O» OFSCSIPTICN Ot 'HANliF XiMH UFAii.tJ (OR rHANl'.f, C>AOLl; ' , f
UJ I
CK I INFORMATION, PRODUCT ION ANf> TCOu INO tNF C*Jv 4 lOt< RTKJN Cr/‘‘S, fT-.
Page 110- Paragraph h.5*ti»2» l^at sentence deleted.
■ Page 113- ftiragraph "Multiplexer equlpaent" was
"lO-PJltO;. , -1, -2, -6, -5, -12 etc."
Pages (15 through 117 '^ere pages ^1 through 6h.
Pages 11b through 139 were pages 65 through 83.
Ihge ;18- Paragraph 6.1. i. 2, "Area "C" Multiplexer" was
"10-^0U02-1 and lO-:.OU02-2"; "Area "A" and "B"
was "10-201402-6"; "(See Figure 21 etc.)" - new.
Paragraph 6.1.1. h. Completely revised.
Page 119- Paragraph 6.i.i.i4, Completely revised.
Pages lliU through 166 were pages dl* through loOe.
Vibration envelope fro... luoO cps to 2U00 epa
changed 4 20o0 cps point, U.0063 oVeps wa-s
0.025 g2/cps.
Figure 9 - Deleted.
Figure 10 - Deleted.
Figure 11 - Completely r vised to reflect new
part numbers.
Figure 12 - Waveforms revised.
Figure II4, Completely revised to reflect new
part numbers.
part numbers and test arrangement.
Page I6I- Figure 19, "Attenuator" removed from Multiplier.
i^ges 162 and 163-
lew Pigures 20 end- 21 respeqtivlly.
Pages I6J4 and 165-
New Figures 22 and 23 respectively.
Page 166- Ihble 1, ueleted.
Page 113- Paragraph I*. 6.3, "lo-20i402-U, IU-20I4U2-I4U"
was "IO-20UO2-U"
Pag^
II47-
P^(ge
151-
Pape
152-
Page
153-
Page
15U-
Page
156-
Page
159-
Page
161-
BOEING airplane COMPANY
L . I'iO.
ie-133A
r‘r
r ,*•
^ , :i: <■ ■•(.>> a.
. . ■ 0- p r- ,
> i " ' ! 'Z' ‘ <
<-6 0,
See Rev. Page ah
D10-2UU02
PaC-K
Rev* ag
fAv. i' -i. i - R A
REV LTR
(
REVISION
! FOLLOW DESCRIPTION OF CHANGE WITH REASON FOR CHANGE, CHaNGF rfFiCIlvt
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DDA'S, ETC.
I -
Reason for Chan£*i
Completion of basic design*
Vendor deficiency.
Revision G Change Effective*
SAOl - SOOl (003b)
ABOl - AB08 (Owlib)
EWA 301^
EWA 3205
ACOU
fHOl & On
AEOl & On
id
o
5
U)
Ui
Od
u.
vi
t\
y
K
BOEING AIRPLANE COMPANY
, MODEL ' NO.
‘ 1
WS-l3aA
D10*20U02
Page
Rev* ah
h Vl .tHi i-
. •
'N^'w
RIVItlON
.L
FOLLOW description OF CHANCE WITH: REASON FOR CHANCE, CHANCE EFFECTIVE
information, PRODUCTION AND TOOL INC INFORMATION, RERUN DOA'S, ETC.
FS£ lls9li
AkgM 1 through 22 w«r« pages 1 through 15*
Page 1- Faragraph 1.1.1, "(10-201*02-0, 10-201*02-1*0)"
was "(10-20li02-0)".
Page 2- Paragraph 1.3.2 "Multiplier and Amplifier Unit"
was "Attenuator, Multiplier and Amplifier Unit".
Rage 8- Paragraph 3.1, "Design Reqmts. RF section" was
"Design Reqmts. f<» 10-201*02"; line 3,
*(10-201*02-0 and 10-201*02-1*0)" added to sentence.
Rage 12- Paragraph 3.1. 2.5, "D2-9129" was "D5-2288".
Rage 13- ftiragraph 3.1.1. 2.6, line 3, "3. 2.9.1" was
"3. 2.2.1".
I^ge Hi- ftiragraph 3.1. 1.3. 2.1, line 5, "600*F" was
"700*F"; line 6, "600*F" was "TOO’F"; line 7
"3ainutss" was "1* minutes".
Page 15- Paragraph 3.1.1.U.1, Completel/ revised.
Paga 17, 18-Raragraph 3.1. 2.1.3, completely revised.
Ikge 19- Paragraph 3.1.2.1.8, Deleted.
Paragraph 3.1.2.1.11, Ctompletely revised.
Rage 20- Paragraph 3*1. 2. 2*3, line 5, "18 watts" was
"17 watts".
BOEING AIRPLANE COMPANY
«AC *681 A-«?
Z
i U)
g|5is
See Rev. Page aj
MODEL
NO.
010-201*02
*
PAGE
Rev. ai
REL DATE
REV LTR
\A
REVISION
FOLLOW ntSCRIPTION CiF CHANCE WITH Rt *iON tCH HANOE, CHANOfc EFFfni'/.
INFORMATION, PROUUCTION ANf) rOOl-INt il;rC'K'MMTiOi., Pr.PLN DEa'S, ( TC.
I
i Q
I
i
i
I
Reason for Changei Correction of design ceficiencies,
deoign lOrrov, ment and correction
to apecafication requirements.
Revision (G) Change EiTective: SAOl - SGOl (003)
SAOl - SGOl (003b)
ABOl - AHOb (OOlj)
ABOl - AB08 (’iOlib)
E.;A 3019
FV.’A 31tl
ADOl On
AEOl & On
AC 1 - ACOh
BOEING AIRPLANE COMi’AS''
‘AX'H
WS*I33A
NO.
DlU-20i*02
a
SI
\ ,
1
fT
N
^ 1
PACt
Rev. aj
(
'
i'TTTTT"'
~rn
or
>
<x
REVISION
FOLLOW DESCRIPTION OF CHANCE WITH REASON FOR CHANGE, CHANCE CFFrCTWI.
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DOA'S, ETC-
T ' ^ ‘ ^
V . 0 • : VO ! ^
> ..J 2 , ^ 1 0
■ ; J ; U 1 uj «
> • a Of ■ < ! ua ■ j c*
•
1
is;
rii
Uj UU
X*
See SWT. Pfige ap
PRR 9500
1
1
0
Pages 23 through 37 ware pages I6 through 23a.
i
!
Page 23- Paragraph 3.2. 1.1, lines 1,2, and 3 were deleted.
Referenced applicable paragraphs of section
i
1
3.1. l.i were iv typed und included as sub¬
sections of 3. 2. 1.1.
Paratraph 3. 2. J-. 1.1 was referenced paragraph
3.1.1.i.i.
Paragraph 3.^'.1.1.1.1« was referenced para¬
graph 3 . 1 . 1 . 1 . . 1 .
Paragraph 3.2. i. 1.1. 2, was referenced para-
gxj^ph p. 1.x. 1.1.^.
Paragraph 3. 2. j.. 1.2, was referenced paragraph
3.t.x.l«2«
Page 2li. Paragraph 3.2. 1.1. 2.1, was referenced para-
gr^ h 3. 1.1. 1.2. 2.
Paragraph 3. 2. 1.1. 2. 2, was referenced para¬
graph 3. 1.1. 1.2. 3.
Paragraph 3. 2. 1.1. 2. 3, was referenced para¬
graph 3.i;i.l.2.3.1.
Paragranh 3.2. 1.1. 3* was referenced para¬
graph 3. 1.1.1. 3.
Paragraph 3.2.1.1.U» was paragraph 3. 2. 1.1.1.
Paragraph 3 .2. 1.1.$, was referenced, paragraph
3.1.1.!.$.
Paragraph 3 .2. 1.1.$, was referenced paragra]^
3.1.1. 1.6.
Page 2$- Paragraph 3. 2. 1.1.7, was paragraph "3. 2. 1.1.2.",
Paragraph 3. 2. 1.1. , was paragraph "3.2.1.1.3^»
Paragraph 3.2.1.1.9f was paragraph "3.2.1.1.1|".
Paragraph 3. 2.1. 1.9.1* was paragraph *3.2.1.-
l.U.l".
Paragraph 3. 2. 1.1.9. 2, was paragraph "3.2.1.-
1.U.2".
„ « [ MODEL ! NO.
BOEING AIRPLANE COMPANY ^ - ] D10-20l*02
l»>133* :
. ' «i i.t.
PAGE
. ak
REV LTR
—r' -T* ■
I REVISION
I FOLLOW OFSCRIFTION OF CHANCE WITH: REASON FOR CMANOt , '.f:aN'JE IFFtCTivr
I INFORMATION, PRODUCTION AND TOOLING INFORMATION, MEHUN l/TM'F, fc r C.
Sa« But. Pag* ap
Q
» ■
Be
III !
c ' or ! 5
^ , UJ
t :
it
CL '
.1 ; '*i
4 I i:
'0
Page 26»
Paragraph 3*2«1.1.9«3 was paragraph 3«2.1.1.1i.3*
Paragraph 3.2.1.1.9.U was paragraph 3.2.I.I.U.U.
Paragraph 3.2.1.1.10 was paragraph 3.2. 1.1.5.
Paragraph 3.2.1.1.11 was referenoed paragraph
3.1.1.1.11
Paragraph 3. 2. 1.2. Referene* to Paragraph
3. 1.1.2 and sub>paragraphs thereof deleted.
Requirements defined In detail In sub*para-
graphs of 3* 2. 1.2.
Paragraph 3. 2. 1.2.1, was referenoed para>
graph "3.1.1.2.1".
Paragraph 3.2. 1.2. 2, was referenced para¬
graph "3.1.1.2.2".
Paragraph 3. 2. 1.2. 3, was paragraph "3.2, 1.2.1".
Paragraph 3. 2. 1.2.1*, was referenced paragraph
"3.1.1.2.11".
Pag* 27- Paragraph 3.2. 1.2.5, was referenced paragraph
3.I.I.2.5.
Paragraph 3. 2. 1.2. 6, was paragraph "3. 2. 1.2. 3".
Paragraph 3. 2. 1.2. 6, line 11, "3. 2. 9.1" was
"3. 2. 2.1",
Paragraph 3.2. 1.2. 7, was paragraph "3.2. 1.2, 2".
Paragraph 3.2. 1.3, lines 1 throu^ 5, were
deleted. Previously referenced paragraph
of section 3.1. 1.3.1 ^nd 3.1.1. 3.2 vev re-. (./.
typed and Included as subsections of 3.2. 1.3.
Paragraph 3.2.1. 3.1, was referenced para¬
graph "3. 1.1. 3.1".
Paragraph 3. 2. 1.3. 1.1, was referenced para¬
graph "3.1.1. 3.1".
MODEL. NO.
BOEING AIRPLANE COMPAN'- •
I PW-133A
010-20U02
a
PAGE
rev. al
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH' REASON FOR CHANGE, CHA.NGf EFFECT IVfc
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN ODA'S, ETC.
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Paragraph 3.2.1. 3.1.2, was referenced para*
graph •'3.1.1.3.1.2".
Paragraph 3.2.1*3*1«3> was referenced para*
graph "3. 1.1. 3. 1.3".
Paragraph 3.2.1. 3.1.U, was referenced para¬
graph "3.I.I.3.I.I1".
Paragraph 3.2. 1.3.1.$* was referenced para¬
graph "3.1.1.3.1.5".
Paragraph 3.2.1. 3.1.$.!* was referenced para¬
graph "3.1.1.3.1.$.l".
Paragranh 3.?. 1.3.1.$, was referenced para¬
graph "3.1.1.3.1.6".
Paragraph 3. 2. 1.3. 1.7, v&a referenced para¬
graph "3. 1.1. 3. 1.7".
Paragraph 3. 2. 1.3.2, was referenced para¬
graph "3.1.1.3.2".
Paragraph 3.2.1. 3.2.1, was referenced para¬
graph "3.1.1.3.2.1".
Paragraph 3. 2. 1.3.2. 2, was referenced para¬
graph "3.1.1. 3.2.2".
Paragraph 3. 2. 1.3.2. 3, was referenced para¬
graph "3.1.1.3.2.3".
I
Page 29- Paragraph 3.2.1. 3.2.U, was referenced para¬
graph " 3. 1.1. 3.2. U".
Paragra^ 3.2. 1.3.2.$, was referenced para¬
graph "3.1.1.3.2.$".
Paragraph 3.2.1. 3-2.6, was referenced para¬
graph "3.1.1.3.2.6*.
Paragraph 3. 2. 1.3.2. 7, was referenced para¬
graph "3. 1.1. 3.2. 7".
Paragraph 3.2.1.U, previously referenced pura-
graphs of section 3.1.1.U were retyped and
included as sub-paragraphs of paragraph 3.2. l.U.
Paragraph 3.2.1.U.1, was refer*'need paragraph
"3.1.1.U.1''.
■Vt
BOEING AIRPLANE COMPANY i ^
ie-i33A
"a ^
D10-20lt02
PAGE
I rev.
REV LTR
(
i
1
I
REVISION
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANOt CHANGE (FFLCriVi
INFORMATION, PRODUCT ION ANO TOOLING INFORMATION, RERUN DLa’j L '
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See Rev. Page ap
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Page 30-
Faragraph 3.2 .1.$, reference ' to paragrafAi
3.1.1.$ dele^d. Detail requirements for
product Identification defined in detail
In 3.2.1.$ sub-paragraphs.
Paragranh 3.2.1.$.!, was referenced para-
gTEph “3.1.1.$. 1".
Paragraph 3.2.1.$. 2, was referenced para¬
graph *3. 1.1. $.2".
Paragraph 3.2. 1.5.3, was referenced para¬
graph "3.1.1.5.3".
Page 31- Paragraph 3.2.1.$.U, new paragraph added.
Paragraph 3.2.1.$.li.l, new paragraph added.
Paragraph 3.2.1.$.li.2, new paragraph added.
Page 3U- Paragraph 3. 2. 2.1.$, reference to paragraphs
3. 1.2. 1.1 and 3.1.2.1.U were deleted. Require¬
ments restated in detail in paragraphs 3.2. 2.1.$,
and 3. 2. 2. 1.9 respectively.
Page 36- Previously referenced paragraph of subsection
3.1.2.1.12 was retyped and included in para-
graiph 3.2.2.I.B.
Previously referenced paragraph of subsection
3. 1.2. 2.1 was retyped and Included in para¬
graph 3. 2. 2. 2.1.
Pages 36 through UU were pag^^iSlt through 32
t
Page 38- Paragraph 3.3.1.1> line 2, “3. 2. 1.1" was
“3* 1.1.1") with the exception of etc. is
deleted.
Para-.raphs 3. 3. 1.1.1, 3.3.1.1.2, 3>3.1.1.3,
3.3.1.1.1i,*and 3. 3.1.1.$ are specified in
reference of paragraph 3* 3. 1.1.
Paragraph 3.3. 1.2, line 1, "3.2. 1.2" was "3.1.1.2“|
"with the exception etc." is deleted.
Paragraph 3. 3.1.2. 1, reference paragraph "3. 3. 1.2"
was "3.2. 1.2.1".
Paragramh 3.3. 1.2. 2, reference paragraph "3. 3.1. 2"
was "3.2.1.2.2*.
Paragraph 3. 3.1.2. 3. reference paragraph "3. 3.1. 2."
was "3.2. 1.2. 3".
Paragraph 3. 3.1.3, line 3, "3.2. 1.3. 2" was
"3.1.1.3.2"| line 5 "3.2.1.3.1" was "3.1.1. 3.X".
I — -
BOEING AIRPLANE COMPANf
: MODEL ; NO.
r -
i MB-X33A
D10-20i)02
I
PAGE
r« an
itH. A-f</
4K- 2-7oro
REV LTR
j-TTr
REVISION
FOLLOW OESCRIPTItX OF CHANCE WITH' REASON FOR CHANGE, CHAnGF CFFCtriVf
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DOA'S ETC.
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Paragraph 3>3*1*U» lina 1, "B.P.l.U* was ”3.1.1.tiP.
Paragraph 3.3«1*$* line 1, ''3.P>1>^'' was
Page Itl- Paragraph 3. 3.2,1.7» "3.2. 2. 1.5" was
”3ela2«lal''a
Paragraph 3. 3. 2. 1.8, "3. 2. 2, 1.9" was
"3.1.2. l.Ii".
Sea Rar. Page ap |
1
Page U2- Paragraph 3. 3. 2. 2.1, "3. 2. 2. 2.1” was
"3.1.2.2.1".
Paragraph 3. 3. 2. 2. 6, Descriptive criteria
new contained within paragraph was described
under paragraphs 3.3.2. 2. 6.1 and 3. 3. 2. 2. 6.2.
Pages U5 threugh 56 were pages 3U through UO
Page li5- Paragraph 3.^. 1.1* line 2, "3.2, 1,1" was
•3.1.1.1"| line 3 and 4, "3.2.1.1.U,
3.2.1.1.5, 3.2.1.1.7, 3.2. 1.1.8, 3.2, 1.1.9,
were "3.1.1.1.^, 3.1.1. 1.5, 3. 1.1.1. 7,
3.1.1.1. e, 3.1.1.1.9, 3.1.1.1.10, 3.1.1.1.11 '
and 3. 1.1. 1.2. 3 respectively. ^
Page U6- Paragraph 3.5.1.1.6, "3.2. 1.1.5" was "3.1.1.1.5"} j
Paragraph 3. 5. 1.1.7, was paragraTh "3. 5. 1.1.6".
Para,<7raph 3*5.1. 1.7.1, was paragraph
"3.5.1.1.6.1". j
Page U7- Paragraph 3. 5. 1.1.8, was paragraph
T.S-i,a.7-
Paragraph 3. 5.1.2, completely revised to j
incorporate new references. i
I
Page U8- Paragraph 3. 5.1. 3, referenced paragraph
changed ter compatability with other
revised paragraphs as follows i 3. 2. 1.3.1
was 3* 1. 1. 3* lf2^^was 3*1. 1.3. 1.2, and .
3.2.1.3.1. U was 3.1.1. 3. l.U.
Paragraph 3.$.l*lk, line 1, "3.2. 1.5" was
■3.1.1.5".
^ - - - -
^ i BOEING AIRPLANE COMPA^J^
MQOEL -JNO.
I W-133A I agr20Jl02
; ^.AGf
r«r« ai
2- TOCO
iRF',. DATE
REV LTR
-
RfVISION
FOLLOW DESCRIPTION OF CMANOE'wITH' REASON FOR CHANCE. CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN [DA'S, ETC.
P»g«8 57 through 67 were pages UOa through UOk.
Page 6U-
Page 65-
Page 67-
Paragraph 3*7«1*1« line 2, "3.2. 1.1” was
”3.3.1.1.".
Paragraph 3«7«1.2« line 2 ”3. 2. 1.2” was
”3«1«1«2”} ”wlth the exception ete.” is
delated.
Paragraphs 3. 7. 1.2,1 and 3.7. 1.2. 2 are
specified per referenee of 3.7. 1.2.
Paragraphs 3.7. 1.2. 3 and 3.7. 1.2. U# are
specified per reference of 3. 7. 1.2.
Paragraph 3.7. 2.1t, line 8, "3.2. 2. 1.8”
was ”3.1.2.1.12"! lino 9, "3.2.2. 1.6”
was ”3.1.2. 1.3".
Pages 68 through 96 were pages UOe throu!^ U6b
Pago 90- Paragraph li.3.2.2f "Product Exanlnation"-
new heading.
Reason for changes Clarlfioation and eonsolidatlan
of 8peolfleatlon requireraents »
'J|
•—1
I
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ol^
X
1:
BOEING AIRPLANE COMPANY
L.._
MODEL j NO.
)a-i33A '
D10-20l|02
... -L
PAGE
rer. ap
tIVItlOM
FOLLOW DCtCIIIPTION OF CNANOt WITHt MASON FOR CHANOf, CHANCE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLINO INFORMATION. RERUN DDA’S, ETC.
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Title Page II • Revised list of active pages
Title Page Ill « Revised list of active pages.
Rev. X page - "Figures 20 through 23 are new" was "Figures
20 through 25 are new".
Revision Pages • Added revision pages aq thru az.
Index b Page - Added paragraph U.6.U.
Page 3 - Paragraph 1.5 In third sentence "10-2Ql|02»&£" was
"10-20U02-77".
Page 6 - Paragraph 2.1.3 " 'Specifications and Standardi’,
Use off dated 19 August 195U" was " 'Specifications
and Standards'} Use of* dated 19 August 195U”.
Paragraph 2.2.1 "GM07-59-2617A" was "D2-fl»UU"
"SHi Document 'Electro Interference Control
Requirement for Minutenan'" was "Boeing Docujnnt
'Electro Interference Control Requlrenents,
Equipment'". .
Page 7 * Paragraph 2.2.1 "02»5051 Boeing Document, 'Fhnctlona](
Test . . . Equipment 10-2Uli02-UU' " was "D2-5051
Boeing Docusmnt, 'Functional Tbst . . . Equipment
10-20U02-h'".
Paragraph 2.2.1 Added D2*10365 and D2-U658.
Page 12 • Paragraph 3.1.1<2.1 "... the requirements of
dlL Document CiM07'59*26l7». Ihe •quipment is
defined as Class 1 per GM07-55-2617A." was "...
the requirements of BAC Document D2-2UUh. Ihe
equipment is defined as Class 1 per D2«2hUi."
Paragraph 3.1.1. 2*3 "... on BAC Drawing 10-20U02"
was "... an BAC Drawing IQ-Z0l|02".
Page 13 - Paragraph 3. 1.1.2. 6 "Kie provisions of GM07-59-
2617A, paragraph 3. 2.9.1 apply. " was "Ihe provision^
of D2-2UUU, paragraph 3.2. 9.1 apply,"
Paragraph 3. 1.1.2, 7 "Ihe provisions of GM07-59-
2617A} paragraphs 3*2.3 und 3.2.U apply." was
"Ihe provisions of D2-2Uhli, paragraph 3.2.3 apply."
Page 26 • Paragraph 3. 2.1. 1.9*3 Entire pura^aph deleted.
^e Rev. page aw
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO.
WS 133A
D10-20U02
_Ll
PAGE
Rev. aq
1681 1-82
ATOM
RIVIUOM
> FOLLOW OeSCRIFTION OP CHANGE WITH) EEAIOH' PON CHANOE, CHANCE EPFECTIVE
et mPOEMATION, PRODUCTION AND TOOLMO MPORMATION, RERUN OOA’S, ETC.
H
Page 26 <• Paragraph 3»2. 1.2.1 *![he equlpownt shall teet the
requireaents of S1L Docuaent QN07*^9 *26171. lha
equipaant is daf iasd as dass 1 par 0^07*59*26171. "
was "The aqulpaent shall aaet the req^iraasnts of
&AC Oocuaant D2-21tUU* lha aqulpaent is daflnad as
Class 1 par 02*2liltU."
Page 27 • Paragraph 3*2. 1.2.6 **1ha provisions of (M07*59*
26171. paragraph 3.2.9.1 apply*, was ”Iha provisions
of D2-2UUii. paragraph 3* 2.9.1 apply.*
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Paragraph 3. 2.1. 2.7 *lha provisions of GM07*59*
26171. paragraphs 3*2.3 and 3*2. U apply.* was
"The provisions of D2-21il4ii paragraph 3.2.3 apply.*
Page 28 - Paragraph 3. 2. 1.3.1. 5.1 "D2-kl23" was "D2-U132".
Page 30 • Paragraph 3*2.1. 5 In second sentanca delated
"stock nusbar*.
Page 36 • Paragraph 3. 2. 2. 1.8 rewritten to define aora
accurately equipaant capability with respect
to transients in the power system.
Page 37 - Paragraph 3*2. 2. 2. 2. 2 "... in paragraph
3. 3*2. 2. 6 for a ^r undad canter-tapped IX source."
was "... in paragraph 3.3*2. 2. 6 for an ungrounded
(floating) data source.*
Page UO - Paragraph 3. 3*2. 1.6.1 Paragraph expanded to
include a outhod of sauisfying the raquirenent
for saapling rates in excess of 8U0 sps by the
cros8*strapping of analog input lines.
Page U5 * Paragraph 3*5. 1.1 "... 3.2.1.1.10 and
3.2.1.1.11.* Mb *. . . 3.2.1.1.10, 3.2.1.1.11,
and 3.2.I.I.2.I.2."
Page U7 * Paragraph 3.5*1. 2 "to 3*2.1. 2.5" delated.
Paragraph 3.5.1.2.1 ". . . requirements of STL
Docuasnt 0(107*59*2617 A. Tie equiponent is defined
as Class III per GM07*59*26l7A." was *. . .
reqalreoents of BAG Document D2-2UUli. The squip-
■ant^ defined as Class III per D2*2Ulili."
Page U9 - Paragraph 3*5*1.5*1*3 Deleted.
C
- * -
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
MODEL
- 1 - ^
NO. '
PAGE
WS 133A '
D10*20U02
Rev* ar
B*C 1681 A-U
a. TOO!
REL DATE
LTR
tIVItlON
FOLLOW OeSCRIFTION OF CMANOC WITH: RCAION FOR CHA»40e, CHANGE EFFECTIVE
INFORMATION, FRQPUCTIOM AND TOOLINO INFORMATION. RERUN OOA’*, ETC.
H
Ftgo >1 • Parograph 3*5*2.1.2.2.2 "Thia power aupplj- shall
be floating with respect to the 28 VDC power
supply." deleted.
See ReT. page aw
^ge 53 ~ Paragraph 3*5*2.1. 3*1.1 (a) Added ”1he autoaatlc
node applies to paragraph 3.5*2.i.3.1 (a) and (e)
only".
Paragraph 3«5*2.1. 3*1.1 (b) Added *1he seml-auto-
■atic node applies to paragraph 3*5*2. 1.3*1 (a)
thru (g)."
Paragraph 3. 5. 2.1. 3*1.1 (c) Added "The manual mode
applies to paragraph 3*5*2. 1.3.1 (a) thru (g)."
Paragraph 3*5*2. i.3.1.U Added the following at the
end of paragraph "This requirement does not apply
to paragraph 3. 5. 2. 1.3. 1.3."
fage 55 - Paragraph 3.5.2.1.3*l.ii*3 ^ew paragraph modifying
color requirements of paragraph 3. 5. 1*1. 7 for
Hewlett-Packard printer supplied with 10-20h02-m;.
Paragraph 3. 5. 2. 1.3. 2 ". . . inadvertent shorts to
ground during testing . . ." was ". . . inadvertant
shorts during testing. . ."
Page 61* - Paragraph 3.7 In last sentence of first sub-paragrapli
"10-^0hu2-86" was "lu-2Uh02-77’'.
Page 67 * Parugrapn 3.7 .2. 2 Expanded to Include a method of
satisfying the requiremente for sampling rates In
excess of 800 sps by the cross-atrapping of analog
input lines.
Paragraph 3.7. 2. L Second sentence - "1.05 amps"
was "0.95 amps".
Page 68 - Paragraph 3.8 In second sentence "10-201*02-66" was
"10-201*02-77".
Paragraph 3.6.3 Added new sub-heading aa follows
"(d) Channel "B" Inhibit pulses to tha Analog
Sequencer Oats".
to describe more accurately the signals generated.
'
-
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO.
PAGE
WS 133A
D10-20U02
KST. as
ItVItlON
FOLLOW DESCRIFTION OF CNAMOC WITH) RiASON FOR CHANOf, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN ODA'S, ETC.
a
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Page 71 * Paragraph (b) "A 'start* and 'stop* signal
for the Voltage and Currenti CQanps of this
Maltlplaxer." was "A 'start* signal for the
Voltage and Current Clamps of this Miltiplexer."
Paragraph 3.6.8 Added statement giving additional
descriptive information for the Countdown (2B)
C.'ird.
Page 72 - Paragraph 3.6.9 Third sentence - "count" was
"current" .
See Rev* page aw
Page 83a* Added page 83a.
Page 83b* Added page 83b.
Page 83c* Added page 63c.
Page 85 * Paragraph 3.9. 2. 2 "10*20li02-68" was "ld*20U02-UU".
Page 86 * Paragraph U«l.l Added tlie following to paragraph
U.i.l "Individual tests described . . . upon BAC
j approval".
I Page 89 * Paragraph li.3.2 "Bach Multiplexer Progranner shall
I be individually tested. lasts must be conducted
with logic cards inserted." was "The following
tests shall be performed on each Multiplexer
Programmer shipped."
Paragraph U. 3*2.1 Transferred to page 89 after
coa^)lete revision. Deleted the test procedure
specified and replaced it with a requirement
that the vendor furnish BAC with the test
procedures used.
Page 90 • Paragraph U*3*2.3 Deleted first sentence and
replaced with "The tests shall check the Programmer
design requirements of section 3*2 for the following
Added the following "5. Ability to supply the proper
secondax*y DC voltages which are required by the
various multiplexers."
Paragraph U.3*3 First sentence * "Each Multiplexer
shall be individually tested." was "The following
tests shall be performed on each Multiplexer unit
shipped." Third sentence deleted. Paragraph U.3.3
transferred from page 91.
Paragraph U.3.3.1 Transferred from page 91.
subject. "That ft'ocedureB"^ replaced "Product
Examination" under this paragraph mmber
BOEING AIRPUNE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO. !
PAGE
WS 133A
D10-20U02
Rev* at
e*c 1681 A-82
Z-ttK
REV LTR
RIVItiOM
FOLLOW DESCRIPTION OP CHANCE WITHi REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION. PRODUCTION AND TOOL INC INFORMATION. RERUN OOA'S, ETC.
u
Paragraph ii.3>3*2 Subject of tbia paragraph
"IVoduct ExasitMLilon") waa subject of paragraph
U«3>3*1*
See Rev. page au
Paragraph U.3*3«3 Men. Subject of this paragraphf
"Perfomance", was subject of paragraph U.3.3*2.
After aaalgnlQg new paragraph nujiber U.3*3.3 to
this subject the first sentence was deleted and
replaced with "The tests shall check the Multl«
plexer design requirewnts of Section 3>3 for the
foUowingt Added "7. Individual channel data
degradation due to current feedback."
Paragraph li.3.ii Transferred from page 92. Rewritten
to state requirenent for individual testing of each
subajrstea and to describe each subsystem.
Paragraph li.3«ii«l Transferred from page 92. New
subject, "Tbst Procedures", replaced "Product I
Examination" under this paragraph number. j
Page 92 » Paragraph U.3.1i.2 Subject of this paragraph |
"Product Bxamination" was subject of paragraph |
lt.3.1t.l.
Paragraph U.3«U.3 Mew. Subject of this paragraph
"Performance" was subject of paragraph li.3>li.2. |
After assigning new paragraph nuri»ar U.3>U.3 to i
this subject changed ". . . paragraph li.3*3>2. .." !
to read ". . . paragraph U.3.3.3 ...” I
I
Page 93 ^ Paragraph U.3.6 waa paragraph U.3.^* Paragraph 1
U. 3.6.1 was paragraph li.3>b*l> Phragrapb 1|.3»6.2
was paragraph U.3.5.2. "Perforamnce of 10*20U02-lt,
10-20U02-UU" was "Perfarmance of ia-20Uu2-l|".
Deleted "With the test equipment connected as shown
in Figure 11 to Impose a representative load and ".
"... compliance of the 10»20U02>U, 10»20l;02«Ui
Teat and Slaulation Equipment ...” was "...
compliance of the 10o20li02>U Tbst and Simulation j
Equipment. .
Page 9U * Paragraph U.3.6.2 was paragraph U.3.5*2. "lU.
External multiplexer analog input facilities to
section 3*5 requirements." was "lU. External
multiplexer input facilitlea to section 3*5
requirements." Sub«paragraph 17. Third sentence
rewritten to reflect replacement of D2»2ltl4i by
0107-59 -2617 A.
BUkING AIRPLANE COMPANY
MODEL
NO.
PAGE
SEATTLE 24, WASHINGTON
WS 133A
010-20U02
Rev* au
etc 1681 «.82
ATOOO
RIVItlON
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>-
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INFORHATIOH, FROOUCT ION AND TOOLING IHFORWATION, RERUN DOA'S, ETC.
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P&g* 95 *• Ftiragraph U.3*7 wm paragraph U>3«6.
Paragraph U«3*7*l was paragraph U«3*6.i.
Paragraph U«3*7«2 was paragraph U. 3*6.2.
Paragraph U*3.7«3 was paragraph U.3.6.3.
Paragraph U.3*7.3 In last sentence "U*3*7*2''
was "U.3.6.2''.
Sea Rev. page aw
Page 96 - Paragraph U.3.8 was paragraph It. 3.7. Ratrittan
to specify Individual card tests according to
procedure recommended by Vendor.
Page 97 - Paragraph I*. 3*9 was paragraph U.3.h.
Page 100 & 101 - Paragraph Ii.5.1.6 Completely revised to
reflect replacement of D2-2ijUli by Grt07-59-26l7A.
Page 101 - Paragraph U.5. 1.6.1 » . linear receivers such
as those used in SIL Document GM07-59-2617A
tasting ..." was "... linear receivers such
as those used in BAC Document D2>2UUlt testing * * "
"... of paragraph ii.3*3.2 of SU* Document
0M07«59-2^7Aj " was ". . . of paragraph li.3*3.2
of Boeing Drcument D2-2l»Ui>'’
Page 103 - Paragraph U.5*2 At the end of the paragraph
added "Figure 22 is to be considered . . .
characteristics of a given test requlri."
fturagraph h. 5. 2. 1.1 "... to comply in principle
with ..." was "... to comply in all respects
with ..."
Pige 106 - Paragraph h.5.2.5.1 hast sentence rewritten to
specify U5 minute equipment warmup after temper¬
ature stabilization of chanter and before equip¬
ment is operated according to paragraph U.5.2.
Paragraph 1**5. 2. 5. 2 (c) ". . . test chamber to
600*F ± 50* . . ." was ". . . test chamber of
600"F ± 50* . . ."
Page 107 - Paragraph 1.5. 2. 5.2 (c) "NOIBi Only one MulU-
plexer ^stem • • •" was "NOTEt Only Multiplexor
Syatem ..."
Page 109 - Paragraph h.5.2.7 Completely rewritten to reflect
replacement of D2-2Uhl* by (W7-59-2617A.
BOEING AIRPLANE COMPANY
SEATTLE 24. WASHINGTON
MODEL
_ 1 -
NO.
PAGE
MS 133A
D10-20b02
Rev. av
i*c uai «-i)2
»-70»
tIVISIOM
FOLLOW OeSCNIPTION OF CHANOf WITHt RfAION FOR CHANOC, CHAMOE EFFECTIVE
INFORMATION, FROOUCTION ANO TOOLMO INFORMATION. RERUN DOA’S, ETC.
Fhg« 109a- Addad paga 109a* Flaragraph lt*5>2.7 rawittan
coQtiauad on this page.
Paga il9 -
Paga 120-
Page 121 -
Paragraph 6.1*2 "Slaulation and Test Equlpa»nt
(10-20h02-U* 10-20a02-ltii)'' was "Simulation aid
ftst Equipawnt (lO-POliOP-U)".
Paragraph 6. 1.2.3 "Failure of the 10-2Qti02-U,
10-20U02-Ult Simulation and last Equlpmant. . ."
was "Failure of the 10-20li02>U Simulation and
Hast Equlpmant ...”
Paragraph 6.2 Revised paragraph by replacing refer*
ancaa to specification drawings with references to
the documents D2-10365 and D2-li&56 in two places.
Page 122 - Paragraph 6.2.5 (a) Deleted "preproductlon"
Paragraph 6.2.5 ^c) revised to read "Ihe article
is cleared for system testing and installation on
a United nunber of non-flight system components."
Page 126 - Paragraph 6.3.16 In first sentence "Iteration" was
"Interation" In second sentence "commutation" see
"cunoutation".
i
' Page 13o - Paragraph 6.U.U "Data Required for Hentative and/or
; Final Approval" was "Date Required for Ibntatlve
j and/or Final Approval".
1 Page 153 ■* Figure 11 revised to show new part numbers.
i
j Page 16U ** Figure 22 revised to show equipnent conimctlons in
i greater detail.
j
I Reason for Cbaogei Ib clarify correct and bring up to date
the specification requirements.
I
; Revision (H) Change Effective! 003C
i OUliB
OOliC
EWA 3019
ETi^A 31(51
ACOl - ACOU
ADOl k on
I AEOl k on
Os
V
BOEING AIRPUNE COMPANY
SEATTLE 34, WASHINGTON
MODEL I NO.
WS 133A
D10-20U02
PAGE
Rev. aw
«*C 1681 *-82
»Toao
'(
/
RlVItiON
I'OtLOW DESCRIPTION OF CHANGE WITH: REASON FOR
information, production ano tooling information.
change, change effective
RERUN ODA'S. ETC.
Page 68 •
Paragraph 3.8 "The logic cards, ( 10-20li02-U9
through 10'*20l402*06) shall be . > was "The
logic cards, (10-20U02-1*9 through 10-201^02-77)
shall be . . .«
I 1 M r
Ui IS
rr
ft I t
1 > i 2; 1 § 1 z w 1 S 0
•uujuiaxi^a.
il 0
-j 1
Ui UJ
QC QTj
1
See Rev. page as
Page 83a - Paragraph 3*8«26 New paragraph. Rostated and
expanded Voltage and Oirrent Clanq) Card description
of paragraph 3.8.15.
Paragraph 3.6.27 New specification. Amplifier
and Clamp Assembly,
Paragraph 3. 6. 2b New specification. 5 Volt
Amplifier and Clamp Assembly, Matched. ,
Paragraph 3.b.2fa.l New specification. 5 Volt
Amplifier and Clamp Assembly, "A" Comaand l\uactions,
10— 2Ui02-bu.
Pat* J3b - Paragraph 3.8.20.2 Now specification. 3 Volt
Amplifier and djusp Assembly, "B" Command ftonctions,
i0-2UU02-fa3.
Paragraph 3.8.25.3 New specification. 3 Volt
Amplifier and Clamp Assembly, Commaxid PUnctiona,
10-20u02-86.
Paragraph 3.8.29 New specification. 30 MV
Amplifier and damp Assembly, Matched.
Paragraph 3.6.29.1 Mew s ecification. 50 MV
Amplifier and Clamp Assembly, "A" Command fanctions,
1 ..-20502-79.
Paragraph 3.8.29.2 New specification. 30 MV
Amplifier and Clamp Assembly, "B" Command Panctions.
10-20U02-62.
Paragraph 3.6,29.3 New specification. 30 MV
Amplifier and Clamp Assembly, "B" Command IVnctions,
10-20U02-85.
Rage 83c - ftiragraph 3.8.30 Sew specification. 10 MV
Amplifier and dam, Asseibly, Ibtched.
Paragraph 3.8.30.1 Sew specification. 10 MV
Amplifier and Clamp Assembly, "A* Cooaand Fjanctlons,
10-201*02-78.
V'S
BOEING AIRPLANE COMPANY
f'Ai; A-Ri
RIVISiON
FOtLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE, CHANGE EfFECriVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DOA'S, ETC.
1 — r-
'n
31'
S I at i « i ! ,v I I
Ui I 0! ! X tC I
>1 i
8k*
olid
<u
H
I
Pag® 83e -
Page 92 •
Paragraph 3* 8*30.2 Hew apecif ication. 10 MV
Aapllfier aad Claap Assenbly^ *B" Ccnniaad 9inctienat
10-20li02-ijl.
6m Hev. page &i.
Paragraph 3*8. 30. 3 Hew specification. 10 KV
Anplifler and. Clamp Assemblyi **3" Command ^ctiona«
10-20U02-8h.
Paragraph li.3*5 New specification "Final Acceptance
Tfests" replaced "Individual Ibsts for 10-20102-U
or i0-20Uu2-Uii" under this paragraph number.
Paragraph U. 3.3*1 New specification "Vibration"
replaced "Exanimtion of Product" under this
paragraph nuober.
Paragraph 14.3*3.2 New specification "Performaoce"
replaced "Performance of 10»20l4U2-U" under this
paragraph number.
Page 96 • Paragraph U. 3*8.1 Test Procedure. New specification
Paragraph I4.3.8.2 Card Tests. New specification
Piragraph It. 3*8.3 Insertion into Sub-System. New
specification.
I^ge 113 • Paragraph Ii*6.1t F\inctional Ibst for Structural
C.rds lb»^QLt02-U5* New specification.
I
V>s
ax-
I MODEL
'WS 133A
BOEING AIRPLANE COMPANY
i NO.
1 D10-2Q||02
! -PAGE
Est. ay
‘‘•C i-M.
Reason Tor Chsaget Incorporation of design inproveaents in
specification requlroMnts*
Revision (U) Change Effective t 003C
OOltC
EUA 3019
AOOl - ACOU
ADOl & on
ABOl k on
RIVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN OOA'S, ETC.
Vs
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
qE
Id
O
LU
a
4
4
NO.
DlO-2aU02
e,
4
i'-j
ft'’
PAGE,
Rev* as
«*C 1681 A-fl2
a>Tooo
REV LTR
FOLLOW DCSCRIFTION Of CHANOC WITMi MAiON TOW CHANCE, CHANGE EFFECTIVE
WFOWMATIOW, FWOOUCTION AND TOOLING iNFORMATION, WERUN DOA’*, ETC
SliHiy
i
h
Roaoon for Ctetiget Incorporation of Radiation. Inc. » | '
a^ceptlone to revlaion "H”. FAR 9500 Ihless othorvisa apeclflad*
.Pag® 3* Paragraph 1.5 Change 10-:^0U02-77 to
j Page 35* Paragraph 3.2«2.1.6 The aaixlmun dradn la Inoroaaad
to 2.0 angieres.
i Page 37» fta»graph 3.2. 2. 2. It Revise plua 5*8 volts to 7.0
volts In the first sentence.
' Page I42, Paragraph 3* 3.2. 2, 6 Revised feedback current.
Page li3» Paraprdph 3. 3. 2.2. 8 Revised cormon mode rejaetion.
Page 6?, Para^^raph 3.7.2.U The mzlsum ciirrent drain is
increased to I,l5 anperes.
fttge 77, ftira(9raph 3.8.15.U Clarification of amplifier and
clamp re-nuiribering system.
Page 77, Parafraph 3«0«15»5 Clarification of amplifier and
clasp re>nuabering system.
Fhge 77, Paragraph 3.8.15*6 Clarification of amplifier and
clanp re-nuabwing system.
Page 78, Paragraph 3.8.16.2 Clarification of amplifier and
clanp re>muaberlng system.
Pace 7”, ftu:agraph 3.8.17.2 Clarification of amplifier and
clamp re'-nuidbering system.
Page 79, Paragraph 3.8.18.2 Clarification of amplifier and
clasp re-imsia«rii\{[ system.
, Rage 83®# ftra^raph 3T8.2o cross reference listed.
Page 63b, Paragraph 3.8.29 cross reference listed.
Rage 83c, Paragraph 3.8.30 cross reference listed.
■ ifege 65, ftiragraph 3.9.U and paragraph 3.9.5 added. 1
Hounting bolts revised. (¥BSi 2lt82)
^g® 90, Paragraph lt.3.2.3 Ravlsed last paragraph regarding .
feedback lladtatlons.
BOEING AiRPUNE COMPANY
i't \\ 7 ! ' /•/* i r t'.
MODEL
NO.
Dl0-20lt02
PAGE
8AC I6tl
LTR
ftCVISiON
> I FOLLOW description OF CHANCE WITH: REASON FOR CHANCE, CMAHl.E FFI-FCIIV.
« I INFORMATION, PRODUCT ION ANO TOOLING INFORMATION, RERUN OtV'S, FTC-
i J Paf'.e
fege 93»
HIR 9^00 Unl«c6 oth«nil8e sperifiod.
Paragraph h.3.6.2 In the second sentence the word
"opera tin/ " is changed to "non-o-.Te rating". Phrt of
parEtgraph. onltted as follows* "P^'Tforrv-nci' chall ho
monitored and recorded duid-n/:- this toc L. The cards
shall perform vdthout failure or malfunction.
Paragraph lu>.l.l'.2 Revised ?nd sentence regarding
temperat'ire.
Pape 111* Paragraplu li.l.? Added
Phra.Taph Added
Parafraph T’*? Added
Paragraph It. a.?. 3 Added
Para: yap; I .'-.L-.li Added
Paragraph Added
j Page 113 » Paragraph revised
1 Paragraph It. 6. 5 Added
I Paragrapli Added
J Pararyapli h.A.' .«\ddcd
Porapraph Added
■ Page l<'2f Pijnire 20 has been changed to incorporate the
followin,' revislonsi
(1) DouMo shicldinr or. vircc bctv'jeer. oxes.
(2) Radio f re ,,uency suiciding of missile ground
J DOint wires.
(3) Connect amplifier ar.d sample and hold signal
returns to power supply comuion.
(li) TraiJiforwr couplinr of "A" and command
and reset pTilses in pro,rai;c'.er,
i lleza on for Change 1 To clarify, correct and bring up to date
the specification requlrenonts .
i licvision J Change Rffectsf 003C
' OOUB
I OOItC
FrfA 3019
! EWA 3181
: ' FTM U12 On
Ov
I
♦
. model i NO.
BOEING AIRPLANE COMPANY J" ‘
HA
D10-?0ii02
!
i
I
FOLLOW OtICRIFTION OP CHANOC WITHt MAtON FOR CHANOC, CHANOR CPPECTIVR ^
INPORMATION, PRODUCTION AND TOOL MO MPORMATION, RRRUN DOA’S, CTO K
Titlo Pago I - Barlaod to alftow Bar. K
Titla Pago II • Bawiaad ULat of Aotiva Pagoa
Titla Paga III • ReTlaad List of iotlTo Pagaa
Rarlaion Pagaa bo thru b C. Addad aav pagaa.
P*«o 1.
Paga 2y
Paga 3,
Paga 4t
Paga 6,
P*60 7.
Paga 8,
Paga 10,
Paga 12,
Po«a 15,
Page 23,
Pa«o 25,
Paga 26,
Paga 27,
Pa«« 52,
7mg^ 33*
Paga 36,
Page 57,
Paga 58,
Page 39,
pN'Ct.Bu.
iMtCTl b
Para. 1.1.1, 1.1.2, 1.1.3, l>alatad 10-20402-0,-1,
-2.
Para. 1.2, 1*4, 1.4*1, Daletad 10— 20402— 4,— 6,-7*
Para. 1.4.2, 1*5, Ralatad 10-20402-6, 10-20402-12
10-20402-39 raquiraaaata.
Para. 2.1.1, Delated MIL-E-003272B.
Para. 2.2.1, Delated D5-2288.
Para. 2.2.1 and 2.2.2, Deleted D2-4751 and
21-50065.
Para. 3*1, Deleted 10-20402-0.
Para* 3*1«1«1*9, Added "aubparagraph requira-
■anta" .
Para. 3.1.1. 2.1, Addad "Sea drawing 10-20402".
Para* 3*1*1*2*6, Deleted laat aentanoa.
Para. 3.2, Delated 10-20402-1.
Para. 3*2. 1.1. 6, Addad "Sea drawli^ 10-20402".
Para* 3* 2*1. 1*9, Rewritten to define teat pointa.
Para. 3*2*1«1«9*1 & 5*2.1>1*9*2, Deleted entire
paragrapha*
Para* 3*2.1. 1*9.3 R 3*2*1.1.9«4, Deleted entire
paragrapha*
Para. 3«2. 1.2.1, Addad "See drawing 10-20402".
Para* 3«2. 1.2*6, Deleted "The provlaiona of —
ahall be utilized".
Para. 3*2. 2. 1.1 & 3*2. 2. 1.1.1, Changed "Ohannel"
to "CoBunand" (aiz plaoaa)
Para. 3*2. 2. 1.2. 2, Changed "mioroaiorofarada"
to "pioofarada".
Para. 3. 2. 2. 1.4*1, Addad "a naxiaum of".
Para. 3*2.2. 1.9, Added "Sea drawing 10-20402".
Para. 3. 2. 2. 2. 2. 2, Addad "Sea drawli« 10-20402".
Para. 3* 2* 2. 3, Deleted entire paragraph.
Para. 3.3* Deleted 10-20402-2
Para. 5.5.1.1.1* 3.5.1.1.2, 5.3.1.1.3, 3.5.1.1.4*
3.3.1.1.5, 3.5.1.2.1, 5.5.1.2.2, 3.3.1. 2.5*
Delate entire paragrapha*
Para. 3.3.2.1.2, Delated "Channel" (2 plaoaa).
Must ee cto svoctioml.^.
te-ae4oi-4
O HI
8 “ * A ^
* I 8 °
BOEING AIRPUNE COMPANY
Ktr lAm it-w
MODEL
NO.
WSifSA
DlO-20402
PAGE
be
REV LTR
IIYIMON
FOLLOW DESCRIFTIOM OF CHANCE WITH) RIAION FOR CHANGE, CHANCE EFFECTIVE
MFORMATIQH, FROOUCTION AND TOOLING INFORMATION. RERUN OOA’i, ETC.
Pors. 3. 2. 2.1 Addod "MoondAty** boforo "ooaBnad
oulooo”
Pum« 3.3*2*1.5t Roplae«l **21-90065 and 21.50105”
with ”21-50105”.
Panu 3*3*2.1.6.1, Sclotcd ”12800, 6400,5200,
I6OO" Channel A aaavlaa. Salotad ”5200,1600”
Ohaaaal B acEiplaa. Balatad laat 2 aentanooE.
Para. 5.4, Balatad ”I>aal^ Raquixtoaanta for
10-20402-5”.
Para. 5.5, Balatad all aantanoaa rafarrlag to
10-20402-4.
Para. 3. 5.1.1. 6.1, Balatad 10-20402-44 only.
Para. 5.5. 1*2.1, Addad ”Saa drawing 10-20402”.
Balatad ”?iltara for 10-20402-44 only”.
Para. 3. 5*1*2. 2, Balatad ”10-20402-44 only”.
Para. 3.5.1.2.5, Balatad "10-20402-44 only”.
Para. 3.5. 2. 1.2. 2.4, Addad laat aantanoa.
Para. 3.5.2.1.2.2.4.1 and 3. 5. 2.1. 2. 2. 4.2,
Balatad antlra paragrapha.
Para. 3*5. 2.1. 5.1, Belated 10-20402-44 only.
Para. 3;5«2.1.3.1.1, Balatad 10-20402-4
raqulraaanta.
Para. 5.5.2.I.3.I.4.I, Belated entire paragraidi.
Page 54^55 Para. 3.5.2,1.3.1.4.2, Baletad 3.5. 2. 1.3.1. 4.1
(3 plaoaa).
Para. 5.7, Balatad all sentanoaa partainii^ to
10-20402-6.
Para. 3*7*1. 2.1, 3.7.1.2.2, 3*7. 1.2.3, and
3. 7. 1.2. 4, Balatad all paragrapha.
Para. 3.7.2. 2, Balatad 6400, 3200, 1600.
Balatad laat 3 aantanoaa.
Page 68 thru 77 Saotion 3*6, Coaiplataly rewritten to
dafina oarda in nuaarioal order and delate
ohsolata oarda.
Pagea 76 thru 63, 63a, 85b, & 830, Balatad aa a raault of
Saotion 3*6 rewrite.
Page 66, Para. 4.5*1, Changed "Individual” to read
”Aooaptanoa" and delated ”10-20402-0”.
Page 89, Para. 4.5.2 & 4. 5*2.1, Balatad entire para¬
grapha.
Page 90 A 91, Saotion 4*5*2 A 4*5*5, Conpletaly rawrittan
to raorganiaa ayataa and oaxd aooaptanoa teat
requirananta.
Belated page due to raozganization of Sao.
4*5*2 EMd 4*5*5 taata.
Para 5.5.2.19 Baplaoad "ohannala” with "input
EMaauraBanta”
Para. 3*7*2. 3 Raplaoad "35” with "9#”
Figure 21 addad Box daaignationa - lAl, 2A1,
2A2, ato*
P««t 51,
Page 40,
Page 44,
Page 45,
Page 47,
Page 48,
Page 51,
Page 52,
Page 55.
Page 54i
Page 64,
Page 65,
Page 67,
Page 92,
Page 41,
Page 67,
Page 165,
BOEING AIRPLANE COMPANY
MODEL
s
NO.
010-20402
REQUESTED
K
RIVISIOM
FOLLOW DESCmPTION OF CMANOt WITH; HEAiON FO« CHAHO«, CHANCE CFFfCIlVft
INFORMATION. PRODUCTION AND TOOLING INFORMATION. RERUN DDA'S, ETC-
93t
Pa«« 94*
Pf 95»
Pag* 96,
Pag# 97,
Pag* 106,
Pag* 113,
Pag* 119,
Pag* 120,
Pag* 153,
Pag* 156,
Pag* 159,
Pag* 160,
Saotion 4* 3*4, Salatad 10>20402-4 r*qair*Mnt*.
Sao^lon 4* 3*4*2 *** 4* 3* 6* 2a
Saotion 4*3*5 **s Saetlon 4* 3* 7*
Delatad pag* du* to raoxganliatlon of S*o. 4
t**t*.
Par*. 4*3*9 dalotad*
Par*. 4*4*1 ohaagad >0, -1, -2 to b* -40, >41,
& -42.
Para. 4.3.2.4.I, Calotad Aooalaratlon Taats.
Para. 4*6.3, S*l*t*d 10-20402-4*
Para. 6.1.2, D«l*t*d 10-20402-4*
Para. 6.1.2. 3, I>*l*t*d 10-20402-4*
Dalatad 10-20402-1,-2,-4,-6,-7, & -8.
Dalatad 10-20402-0.
Dalatad -l,-2,-7, & -6.
Changad -1, -2, to b* -41,-42.
Baasont To Inolud* oparatlng limitation* (Vendor Dafioieniqr)*
SffeotiTOt FTU 412 & On.
I
O :
BOEING AIRPLANE COMPANY
; MODEL j NO,
010-20402
- ,,...4 -
u
3
i.i.
I I
1 I
i ; i
PAGE
f»>-. I'.Bi A-Rl'
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE CHANGE CFFECTiVF
INFORMATION, PRODUCTION AND TOOLING INFORMATION RERUN DDA S ETC
SfftotlTet ill
-4-
io
a „
< I w iS
> > ui I Z
D
>10
ui ui
O
Title Pages I| II & III > Rarlaad to show Her. II
Rerlalon Page hg - Added new page
Pag* 35i para. 3*2*2. 1.2.1, rewritten to define positive
lewel.
Page 30, pasra. 3*3«2.1.2.1.1, raviaed last sentenoti to
include pulse reference exception.
Para. 3*3<2.1.2.1*2, added sentence "The condition
. this specification".
Page 134, Figure 12, changed amplitude values -t-lO and 0 to
0 and -10 respectively.
Page 133* Figure 13< changed amplitude values -4-10 and 0 to
0 and -10 respectively.
Reason! Clarification of specification requirements
(spec oonplianoe,)^
i 1
o
iOi
i«i
\*\
- i
l/t
qI
UI '
> a
UI
h-
<
i/t
S ; n
a
UI
oc
5 ^
I/I
—
Ok UI
< tt
a 1 J
I I
I !
I I
THE BOEING COMPANY
SEATTLE 24, WASHINGTON
i !
I !
MODEL
NO.
i PAGE
13-1 35A
^ DlO-20402
■ 1
i tog
ij 4 4077 "^GOO
•V-l
A
)
6AC 1681 A-f)2
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGL, CHANGl EFfECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION RERUN DDA'S, FTC
•a.\
P SWA 50050
a.|<
Titl* Pages I, U» A III • Bairlaad to show Ssrislon Po
Srrlaion Page \i • a&Aad new page.
Index b* added para. 4*9>^ Traprodnetlon Tasta for
aadaaaaxjr Bquipa»iik".
Added para. 4*9*9 "Praproduotlon (Plight Proof)
tests for BP Seotlon 10-20402-90
Index dk Pienro 24 added
Page 4* HIL-]>-70527 added to Spooiflaatloa - Mllltaxy
Pages 22a and 22bt Seetioa 5*^*3 "Design Be<{airement8 Bf
Seotion (10-20402-90)" added to apselfy design
oriteria.
Page 99* Para. 4*3*9 "Aooeptaaee Tests for 10-20402-90 BF
Seotion" added.
Page 111a Seetioa 4.9*9 "Preproduetioa (Flid^^t Proof) Teats
for 10-20402-90" added, (lav page)
Page l6d Figaro 24» "Baadoa Tihratlon Inrelope for
8q.\iipaent Operative” aided.
QC
UJ
Q
bj
iQc:
li.
u
z
(5
a
> M
<1-
V
C
Qd
K>
v> ,
V-
Beoaoat To Ineldde revised vibration Isvela and separate the
design and teat reqalxsaents of the WS-1531 ahd
18-1558 BF Ssetions to faollitats fatore revisions.
Sffsotlvei All (1B-155B)
I
I
THE BOEING COMPANY
model'
"no
i PAGE
I
SEATTLE 24, WASHINGTON
fS-155B
-JB-133A.J
DlO-20402
• i
J1 407 7 5000
- r
SPECIfJCATlOH OCCUMfc'NT PAOb
! cm nnptMTS
I 1. SCOPE
(
' 2. APPLICA8I£ COCUMEinS
3. REQUIREMENTS
3.1 IXSEIN REQUIBEMEtlTS RF SECTION
3.2 EESION REQUIREMENTS MULTIPLEXER PBOORAIWER AND LOOUI
CABK
3.3 lESICn REQUIREMENTS FOR MULTIPLEXER AND LOCIC CARDS
3.4 DGIETBD
3.5 E8SICK REQUIRBMENTS-SIMULATION AND TEST EQUIPMENT
3.6 DESK® REQUIHEMENTS-SIND TRANSMITTER SYSTEM
3.7 DESKW RBQUIRa?ENTS.MULTIPLEXER SYSTEM
3.8 DESION REQUIREMEMTS.LOQIC CARDS
3.9 EESIDN REQUIFEMHNTS-ACCESSORr EQUIPMENT
4. QUALITY ASSURANCE PROVISIOK
4.1 CLASSIFICATION OF TESTS
4.2 TEST COKDmONS
4.3 ACCEPTANCE TEST REQUIREI'IN'IS AND PROCEDURES
4.4 COMPONENTS TESTS
4.5 PREPRODDCTIOH TEST REQDIEEM5NTS AND PROCEDURES
4.3.1 FREPRODUCTION (FLIQHT PROOF) TEST5-RF SECTION
4.5.2 PREPHODUCTKH (FUSHT PROOF) TESTS-MULTIPLEXEU
EQUIPMENT
4.5.3 PREPROOUCTION (QDALIFICATIDN) TESTS-SMILATIiCa?
AND TEST EQUIPMENT (DELETED)
1
4.5.4 PREPHODUCTIDN (QUAUFICATIOH) TESTS-6LED
TRANSMITTER SYSTEM
CZ M ' C- I
' ;• l\(, Al- 'M AN': CCi'-VA: . ;
u
8
8
23
38
U5
57
64
68
84
86
86
68
88
97
97
97
103
no
no
010^0402
BQSX a
SPECIFICATION DOCUMENT PAGE
PiflB
4.9 TSEPBOBDariOl TEST BSQUIRBCBHTS AND PHOCEDDBES (OOIT']>)
4.9.9 PBEPRODOOTIOH TESTS FOB ACCISSOBT EQPlIUilT 111
4.9-6 FREPBOSUCTIOB (FLIOHT PBOOP) TESTS FOB BP SECTIOV
10-20402*90. 111a
4.6 BAG BBCBI71B0 IRSPBCTZOB AND FUNCTIOKAL TESTS 112
4.6.1 BBCBITllD IRSPSCTlOir 112
4.6.2 FUMCTIOIAL TESTS FOR ItDLTXPLEXEB BQDIPKEBT 115
4.6.9 roiWriOBAl TESTS FOR 10-20402-44 119
4.6.4 PmKTIOBAl TESTS FOR .STHDCTDRAL CARD, 10-20402-45 119
4.7 QUALITY COBTBOL 114
PREPARATION FOR DELITEST 115
5.1 DELIVERY TO BAC 115
5.2 DELIVERY TO OTHER THAN BAC II6
5.9 MARKING 117
NOTES 118
6.1 INTENDED USE 118
6.2 APPROVALS AND CLEARANCES 121
6.9 D^INITiONS AND ABBRE7IAT10N3 124
6.4 DATA REQUIRBCENTS 127
6.5 CHANGES TO THE ARTICLE OR SPECIFICATION 195
6.6 SEQUENCE OF BAC VENDOR NEGOTIATIONS 197
(i
K
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PREPAREO
BY 1
TYPED BY ■
ST"
BOEING AIRPLANE COMPANY
REVISED BY I DCN OATt bcN LTk.
C S.M , ' G-
SPECinCATION NO.
DlO-20402
I
I pAor
IBlffiX B
BAC 1 1 ;« B
.’-7001'
SKClPICATION DOCUMENT PAGE
Figur* Mo,
1
2
3
4
5
6
7
9
10
11
12
13
14
15
16
17
18
FIOOHE mDEX
Title Page
»
Qualification Diecrspaney Report lliO
Acceptance and Functional Test Summary 1U3
Sinusoidal Vibration Envelope for
Equipment Non-Operative 3^5
Sinusoidal Vibration Envelope for
equipment Operative (Instrumentation Compartment)
Random Vibration Envelope for Equipment
Operative (Instrumentation Comp; rtment) lUT
Sinusoidal Vibration Envelope for
Equipment Operative (Interstages) 1J*8
Random Vibration Envelope for Equipment
Operative (Interstages) jjjj
Sinusoidal Vibration Acceptance Test Envelope
for Equipment Operative (Instrumentation Conpartnent) 150
Sinusoidal Vibration Envelope for
Reliability Tests EELETID
Random Vibratlcn Envelope for
Ileliabillty Tests DELETED
Test Diagram - Multiplexer Programmer &
Multiplexers
Wave Fonns - Multlj lexer Programmer «
Wave Forms - Miscellaneous
Teat Diagram - RF Section
Sinusoidal Vibration Aooeptanoe Test
Envelope for Equipment Operative (Interst-'iges)
Shock Test Spectrum
Temporeture-Altitudo Test Set-Up
Holloman IFB PCK/lM Sled Test
151
152
V
153
l51i »
^155
156
157
158
159
160
PREPARED
BV
irPEO BY
!
DOPING AIRPLANE COMPANY i
I ‘ ' 'jr'. .M'HAI'ON MC.
HtVtStD ftY '. f.N I'.ATC ptN I TK.'
I ]Bio-ao>i02
mOBE
SPECIFICATIOM DOCUMENT PAGE
FIOURI BPg (CDBt»d)
Flmr» >b. Tltl» tmgf
19
Ik'ansBlttar
161
20
Groundiiig Block DiagrUf Noltiplexcr Equipnent 168
21
Inatallatlon Atm EQ^ek DiagrUf Holtiplexer
Equlpacnt
163
22
Ttst Configuration Diagraa, Hiltlplexar Equip¬
ment PrepiSoduetlon bat
I61i
23
Data Source - Multiplexer Ourrent Feedback
Configure tlone
165
24
Random Flbration Borelope for Equipment
OperatlTti
166
»
1
i
!
PRfPAREtl 1
! j . Sv'f f M , \ I ''>N
BY j ...
PtVlSC;; ’'’‘Tf. bcN \ fvJ
irPLD BY 1
1 ^ i
.-i- . . ! - <5 1 dio*20»»08
1
J^Of lNG AIRPLANE COMPANY
i IMDIX d
«047 *000 (WA* BAC 1I74«)
SPECIFICATION DOCUMENT PAGE
1
1.1
1.1.1
1.1.2
1.1.3
SCOPS
Thli tpvolfioation Otttlinea th« oharaoteristlos and parformanot
raqulraoanta of airboma 701/7VL talaniatxar oomponanta for uaa in
SSJ) flight taats of a ballistlo nlasile. In addition, this spaoi>
fioation outllnaa tha oharaotariatios and parfornanoa raquiranants
of tast aqulpaant for the oomponanta, and the raquiramenta of the
alad trananittar for RSsD alad taats.
COlCPONEin' DBSCRIPTIOK
Refer to Boeing Spaolfioation Control Drawing 10-20402 for a blook
diagraai which shows the function of each component as an integral
part of tha oomplata PCU/^ talamatry system. A general description
of indlTldual oomponant operation follows. !
RP Seotion (10-20402-40^ j ^
Tha RP seotion shall eonaist of an RP transmitter, an RF amplifier, !
and a high woltaga power supply to power tha RP units as required. i
As an altamative to an amplifier unit, tha RP amplification may
be inoorporatad within tha RP transmitter unit. Tha RP section ]
shall be suitable to aooapt a serial pulse train from tha function i
programmer (not part of this spaolfioation) and produce a frequency |
modulated RP signal which will in turn be fed to an antenna triplexer j
(not part of this specif ioation) . The mounting structure for the
units idiloh comprise the RP section shall provide all of the physical
support required for the units, shall contain all inter-unit eleo-
trloal wiring, and shall provide heat sinks as required.
Multiplexer ^10-20402-41) M
This unit reoeives primary reset and primary command pulses from
the function programmer (not part of this specification), to trigger
the operation of the multiplexer units, so as to produce a seried
time-shared signal output for encoding by theooder (not part of |
this specif ioation'). The multiplexer programmer shall be powered
dlreotly from the R':D primary power supply batteries, and shall
in turn distribute power to the Multiplexer. Any regulation '
neoessary of the IMtD primary power shedl be incorporated in the
Bultiplexer programmer unit.
I
EMh multiplexer unit shcdl consist of a case and plug-in oetfds, the j
cards oontalning the unit switching logic. Each multiplexer unit
samples in a programmed sequence the input signals from data sources, !
and produces a sorial time-shared signal output. The unit reoeives
seoondazy power, command pulses and reset pulses from the multiplexer |
programmer.
5 a UY
I-
I
j-
DON I'/i Tl jp. u i r'.
v<
'It . . A ? ! ■ ) I u:
DlO-20402
^N: COMPANY
t y
1
SPECIFICATION DOCUMENT PAGE
1.2
1.3
1.3.1
1.3.2
1.3.3
SIMOUTIOH AXD TiST SQPIPXSRT (10>20402^)
K
Th« p«rfoxwLno« of tho lloltiploxor ProgroaMr and Ifaltiploxar unit!
ahall lx OTtluatod vlillo oparatiog.aa a aaba/stamt as oppossd to
Indlrldual psrfomnes tssts for thoas units. Durloff ths sabsTstsn
tsats« ths sinulation imit shall gsnsrats prinarj rssst pulsss, pri¬
mary eoamand pulsss and analog slaulatlon and shall provlds prinaiy !
powsr for ths aubaystsa. Ths tost squlpnsnt shall bs oapabls of I
▼srlfylng that sslsotsd subsystom opsratlon requireasnts are within i
ths psxforaanos liaito dsfinsd. j
SLED THAHSttlTTER STSTiai (10-20402-5) I
Ths alsd mountsd transaittsr Is rsqulrsd for Holloauu AFB S&D slsd
tssts opsratlng in ths 800 to 828 mo bond. Rsfsr to Flguro (18)
for block dla^raa of Holloman A?B slsd mounted PCM/K system. The
-5 system identification is used for' specif ioation clarity to des¬
cribe ths oomblnsd operation of the -9. -10, and -11 units.
Exciter Unit (1Q-2Q402-9)
Ths sxoitsr is a -0 transmitter modified to operate in the 200 to
207 BO band.
This unit oonalsts of three paoka^s moiuited on a single chassis.
The unit is used to traxxfoxB the output of the -9 exciter unit to
the 000 to 826 mo band.
This unit supplies the required power to the -10 unit from the
26 TDC sled priaaxy power supply.
1.4 WJLTIPLEXEE STSTE34 (10-20402-46)
The Multiplexer System consists of one Multiplexer Control Box and
a msximua of three Aiuciliary Boxes. The 10-20402-46 system identi- |
fioation is used solely for speoifioation elarlty to desoribe the |
oombined operation of the Control and Auxiliary units including
Logio Cards. The system functions in the same manner as that of j
a Multiplexer unit described In 1.1.3. I
1.4.1 Control Box (10-20402-47) |
The Multiplexer Control Box reoeivee seoondsxy reset and oomsuind !
pulses from the Programasr to trigger the operation of eaoh Auxiliary
Box. The control box shall produce serial pulse train(8) for the
pragraomer. Ths Control Box shall operate with one, two, or three
Auxlliaxy Boxes within the limits speoified in paragraph 3. 2. 2. 1.9.
1 _ .J
L 1
^ - - - - - - - - - -
■. .t in:, AlkPLANE COMPANY
j REVISED BY
CCN DATi jD^N LTW.
. . '' k''
sr'Ecii it A nuN M . 1
DlO-20402
- .
PA Of 2
1
1 .
J _
_ _
, A M /4 U
SPECIFICATION DOCUMENT PAGE
l.'r,2
l.'j
1
l.b
1.7
Auxiliary Box (l0~20402-4a)
The Auxiliary Box shall include the cards containing switching
logic# Each Auxiliary Box samples as programmed input signals
from data sources and feeds theoo signals to the Control Box#
LOCIC CAHDE (l0-PO4o?-/>9 through lO-2O4O2-06)
Aie Logic Cards arc modular plu/c-in asaemhlies which contain
the cofu and, gatin':, timin,':, nnplificntion, power, and/or
matching cij'cuitry nocosonry to provide the required functional
capabilities of the Multiplexor Programmer, Multiplexer, Control
Box, and Auxiliary Box#
AGCilioOHY 'viUIJT-Ii'M
K
K
i
i
!
The nccer.sory eeuinmont Includes tpocial tools and equipment
items vfhich do not fall within the classification of Logic Cards
or major functior^il equipment# Epocific doacriptiono of
equipment included in this clnsnif ication are given in Section 5.9.
HF Seotlon riO>2QdQ^«9Q)
The BP Seotlon is identical to 10-20402-40 except for vendor
internal RP Seotlon design# The requirements for 10-20402-90
sre identloal to the 10-20402-40 requirements as speolfled in
Ssfltlons 1, 2, 3. 4, 5 and 6 of this dooument.
l’""”' I'l Ti •' M. >1
:i t ant compamy
1 -
1 'V N I ,- t
1
(
lUi'n 1 1 1;'.'
; )<.i
D10-?0402
..a
1
1
: ^ :
SPECIFICATION DOCUMENT PAGE
2.
2.1
2.1.1
COVESNXENT DOOtnCENTS
Tho following ffovomawnt doouments of the exaot Issue noted,
together with the noted rewisions thereto constitute a part
of this Bpeoifloatlon, hut only to the extent defined herein.
In those oases where the doouaent listed is not dated, the
issue in effect on the date of invitation for bids, shall
form a. part of this speolfloation. uniere eonflloting require¬
ments exist f the requlrenents of this specif loatlon shall govern.
- MlUtary
UlL-S-413aB
"Eleotronlo Equipment Ground! General
Requirements for" dated 5 Januoxy 1933.
MIL-S-46e2B
"Electron Tubes, Gholoe and Application
of" dated 11 January 193^.
MIL-I)-5028B
"Drawing and Data Lists, Preparation of
Uanufaoturers", dated 20 August 193^.
1<IL-B-5400C
"Eleotronio Equipment, Aircraft, General
Speoifioation for", dated 13 July 1958*
iaL-l)-5480C
"Data, Englxteering and Teohnioal
(Reproduction Thereof)", dated 29 September
1954.
MIL-T-9107
"Test Reports, Preparation of", dated
13 July 1953.
10:L-F-14072
"Finishes for Ground Signal Equipment",
dated 25 May 1955.
iaL-D-70327
"Drawings, Engineering and Associated
Lists", dated 16 March i.959.
r
I
i
I
I
! ^
! £>
I
I
I
(
I
('[/( I’AMI I' j
p - — - - - -- -
1 HGVISED UY 1 PCN t'AYC Idcn I. YR.
r.inCAllUN tin,
(ir j _ - . .
lYPK) liY J
! R e,\A/,
r
' K
DlO-20402
S--S-kiP ,l . j
UOE INC AIRPLANE COMPANY
SPECIFICATION OOOiMEHT PAGE
1 ^
2.1.2
M^C»25050
"Cblara# A«roa»utlcta lights sad
Iqiilpasat. OsiMiml BsqairsMots fsr"
dstod 29 Uetsber 1?5U.
A
SUadaxtIs
FSD-sn>-:^5
MlL-3m>28
*Celsrs'' dated 1 Nsrcb 1956
"Abbrsviatisoe for Um on Drawings"
dated U March 1952*
"Apprsvad Method for Asslgiateat of
Drawing Titles", dated 2 iva» 1958*
/
c
M1L-Sm-129B
MIL-Sm-i3uA
t
4
PRPPAWED
BY
•
— r
1
WEVliL.')
DCN DATt
DCN LTR.
SRtOFICATION NO.
TYPED BY
i
- i
D10.20(|02
i
A± -
_<2. ..
30EING AIRPLANE COMPANY
k. n, t4
Li_
PAC' 5
"Meriting for Shlpaoat aad Siorags"
dated 10 April 1957 with Chaage Mo tics
»I dated 6 195&*
"Idantlfleatlea Maxicing of U»S* Military
Propertgr" dated 8 Sspteaber
4
K
SPECIFICATJON DOCUMENT PAGE
i
/
2.1.3
2.1.4
2.2
2.2.1
PttbliotioM
Delet«i
ABA BulUtin l43d
ABA Bulletin
A
"Specification and Standard*", tJao of,
dat«A19 Angoat 1954.
"Stonoi Llfo -> AttreaMcutieal Artlela*",
datod SeptoSbor 21, 1953-, Ineludlng
aamdnent 3 datod July 20, 19^6.
Prayings
Delotod
BOH-aOVBRSMEaiT DOaMBBTS
/
9bo foUovlag aon«gaTTUi>ant dacuneBts, of tbo omet Issnos
shovn, farm a part of this spoolficatlan to tba oxtoot spoei>
flod baraln. In thoeo ea«as iAmto the doeuant is tiot latod,
the latest issue in effaet an the data of laritation fttr bids
shall fam a part of this spoeifieatlen . tee capgr each of
the doeueeats listed belov and marked vith an aetorisk is to
he furnished vith each oepy of this speoifleatian being sent
to a vendor. Where eonflietlng re^uiresiasts exist, the
reqialreneets ef this speoifieatlon shall gevera.
Puhlleations
* BAC 5^6
* BHS 10-26
e GM07-59-2617A
* P2.4051
* D2-4123
Boeing Trocess Specification "Kano- /
feature of Deealcomaniaa A far Marking
Panels vith a Silk Screen".
Boeing Material Specification "Pressure /
Sensitive Plastic Film Decalconania"
STL Document "Electro Interference ! J
Control Kequlrenents.for Biimtcnan" !
Boeing Document "Protective Finish ;
PerfOnaance Document for Modal VS 133A"
Boeing Deennent "Statement ef Work for j y
sub-contract for airborne PCH/m Telan- |
etry Systsm Cemponents"
bciercjD 1^
* D5-2300
0
Boei ng Document "Packaging BeguiremKrts*
Bomare Missile"
r
piiEPAPEP
BY
- — - -
ll
|l REVISED BY
1 DCN pate |Oc.h Lf,?.;
SPECIFICATtON HO.
DlO-20402
•TYPED flY
H T2 TL
1 ' A
UH
i _ - . _ -t. , j
koEING AIRPLANE COMPANY
ii csrf
! I H !
•A.'l- 6'
L -> J I I in
VfW
HtAC t’74B
SPfCIFiCATKM DOCUMENT PAGE
D2-7687
Boeing Docunenty "Electrical Assembly and
Packaging Requirements for A:rborne PO^/FM
Multiplexer Equipment"
D2-lib6i
Boeing Document, "Functional Test Procedure
for PCM/FM Airborne Iblemetry ^stem"
D^-5o51
Boeing Document, "Functional Test Procedure
for Simulation and Ibst Equipment 10-20ho2-UU"
,t>6LeT€X>
D2-9129
Boeing Document, "Airborne PCM/FM Itelemetry
Equipment, Approved ftirts and Components"
D2-10365
Equipment Certification and Clearance Data
for PC>i/FM Telemetry Components.
D2-;,8^)b
Status Report Qualification and Approval
Program Kinuteoan Weapon System
Drawings
1
1
2.2.2
* 10-20Lo2
Boeing Drawing, "Specification for Airborne
PCM/FM Ttelemetry System Components"
* 2I-5OOO0
Boeing Drawing, "PCM/FM Airborne Telemetry j
Program Control Drawii.g". j
JbeLe.Tet>
1
* 21-50105
i
Boeing Drawing "PCP/FM Airborne Telemetry j
Program Control Drawing - Test Matrix MT" i
2.2.3
References
2-UUU6»b-36U "Assigned frequency for PCM/FM JteleniBtxy
iransm liter" ( Confident. al) dated August I3f
1959.
PREPARED
BY
•
REVliED HY
1 I ''Phc iCA 1 fON rio.
DCN [*ATC |Cit.N 1 Ti?..
TYPeo BY
L « H
1 - .i DI0-20I102
i ^ i
C SM
30EING AIRPLANE COMPANY
KM
■ LA ''
i '-Jj IPAUF 7
TTw K
111 4047 MOO (WAt OAC 1l740t
SPEaFiCATION DOCUMENT PAGE
3.1
DESIOM REQUirffiK-J^TS RF SBCTION
• •
The requirements set forth herein describe the RF Section
0.0»2Cy4O2-4O) for an airborne PCM/FM^telemetry
system.
3.1.1
Qenertil Beauii^einAts
3.1.1.1
PhQrsiosl Requirements
3.1.1.1.1
Selection of Specification and Standards • Specifications
andi stcnoLards for necessary eommodlties and services not
specified herein shall be selected in accordance with ANA
Bulletin 143. oxcept as provided in paragraphs 3.I.I.I.I.I
and 3. 1.1.1. 1.2.
i
3.1.1.1.1.1
1
Connercial Parts - Commercial parts having suitable properties !
may be used where, on the date of Invitation for bids, there ^
are no suitable standard parts. In any case, conserclal |
utility parts like screws, bolts, nuts, cotter pins, etc*
having suitable properties nay be used provldedt
(a) They can be replaced by the standard parts (MS or AN)
without alteration.
(b) The corresponding standard part nusbers are rofereneed in j
the parts list and, on the Vendor's drawings* j
3.1.1.1.1.2
Standard Parts • With the exception in paragraph 3.1.1.1.1*li j
^ and AM Standard parts shall be used where they suit ttim pur- {
pose. They shall be identified on the drawings by their part |
noubers. I
1
3.1.1.1.2
1
Materials and Processes - All materials and processes used j
shall be in accordance with government material and process
specifieations whersver applicable. Where the vendor rinds It
necessary or desirable to use materials or processes not
covered by government specifications, th^ shall be entirely
suitable for the purpose. The use of lightweight mA^terlals,
weight and space saving designs is a major consideration and
their use sliall be investigated and elicited to the greatest
possible extent.
3.1.1.1.2.1
Deleted
PRFPAHEO
BY
hoping airplane company
PEVliEO r<Y ^ l)('N iiA!
; 1
r'
M , ' I- S' f U('U UL
010.20U02
Afk«7 fw*t t»kr
f-
t
!. ' .
i r
km ..t ■
snBctfiaTi#»ndqiiiiMf
■■■ ■> ■■ .I'm
; a
-4
3.1.I.1.3
3.1.I.1.U
3*1*1«X*2*2 F«i>giii«Br»»f NiUriAls - MfttarUls Uuit «i» nutrinata for
2li;Bl^.>4iba)l'"iiet h# ummL yuara it la practloal to mvol4 tbra.
Uha#* uMttf itey abaXl traatad wltb a fuBi^ldal agaiit
aaaapU!»la ta lOIOm
3«l«i«X*2*3 ytolahaa • Surtdoai atall Mat tba applicable fi^ah x^quita-
Mota apaelfiad 'tthhlSMiOSI*
3»lal«i»2*3*l Slalilar and Diaaiailar Natela
Aallar.aoct diaalaiilar Mtela shall be grouped In aacordahea
l^th MlL^^4Jt072« lha uaaga of dlaaiallar Mtela shall ba in
aaeerdanee with MJl>B>>$bOOC*
♦
ftraducibilitar » Ibe daaign ahall allaw the uaa of ^foeli aetheds
and praaaaeaa aa vlU raault in »»*■<«■«■» preductioir with a
ilniiiMi axpendltora of aanheura and aaterlalSf eaniaenaunkta
with the quality raqulreaenta unique ta the indiiridual aedal
or type*
IfcintaiMb^lty • Nainteinabllity shall be eenaidtrsd aa a
!faeior along with other aajer design paramatarsk The
doai^o shall provide far slaple anu rapid instellatlen ear
roMval of onita fraa the equipMnt Munt)^ atTMtera (Refer
ta. Boeing Braving 102UUU2} vltbout dlsturoing or daaaging
intereonneetln,^ wiring and cennaetara* and without q>aelal
teals or equipMnt* If a box type atrueture la utllisady the
sever shall be reuavad wltbaut special teals* -
f .-j .1 * r- ii . Angr'gaaketa utilised with the
cever ahall be aaaureo te the cover te prevent lass off or
doMge tof the gasket upon roMval of the caver*
r
tjtertaM^ahlp • Ihe aqulpMnt ahall be fabrioated and finished
In a iliolreughly weriMnlike aannar* Particular attentlan shall
be given te fraeden from defeots of seldar JeintSf aonnasteraf
aondaetarsf insula tian end printed oiroultaf prapar wiring
siqqpartsi circuit arrangaMnt and cenducter apaelngi awl
elaanlineaa during ancL after assambly* Attentien atwll alya
ba given te freadaa fraa blanishasf dafaota* burraf a^ aiftrp
adgaa* aocuraoy of dlwanalanai radii of flUete and vlwiilng
ef parte* |UC DaevMnt l>5e2300 is applieabla*
3*1*1.1*6
3*1*1*1*5
Interchangaabillty « Artlclaa and/ar ccmpananta Mnafaetarad
in SooaroanM with thia specif iMtisn ahall ba fwg^taw<f1ity»
phyaicnllyt and atrudturally intarehangaabla* She paragraph
3*1*1«5«3 far part nanbar changaa far nan-intarchangaabla
artlclaa*
PREPARED
BY
-
REVIUD BV
MUteYt
MNim
TYPED DY
R.*U.
• *
80E*NG AIRPLANE COMPANY
LAH
JsLm
OLO-20t|D2
oaac 9
KAC n?* a
P-JOPO,.
3. 1.1. I. 7
3.1.1.1.S
3. 1.1. 1.9
3. 1.1. 1.9.1
3.1. 1.1. 9.2
3.1.1.1.9.3
3.x.i.iao
Con struct ion - The oonetruotion of the equipment shall be
adequate to obtain the required performance and reliability
under the conditions of this specification. Modular construction
shall be uoed to the greatest extent possible, and each unit as
apeoified in ^paragraph 1.1,1 shall be a plug-in type unit.
The KF unit mounting structure may be utilised to 'serve as a
heat Gink and/or function as an RF shield, however the uso of <,
the RF package raounting surface as a heat sink (except during bench
operation) ahsll not be contemplatod. See paragraph 5. 1.2. 1.1.
Thp removal of any outer insulation skin for the purposes of beach
teats la permitted, however, the removal of the insulation skin
shall not expose internal components to possible damage by handling,
or in any way reduce shielding. If the unit Is not sealed,
suitable provlaiona for drainage shall be incorporated to prevent
the accumulation of moisture.
Components - The power supply unit ohall contain only solid
state components. Vacuum tubes and moving parts except for
factory sot adjustments, are prohibited. In the RF transmitter-
amplifier unit or units, solid state components in proven,
conservatively designed circuits shall be used to the greatest
possible extent. All parts shall be chosen to provide high
reliability and consistent performance in system operation.
Tost Points - Care must be taken in providing electrical tost
points to ensure that the external loads (such as cable
capacitance or inadvertent shorts) introduced by the tooting
activities does not cause damage to the HF aootion or unite
under test. Electrical teat points available for uoo in
RF section testing shall be sufficient to isolate a fault to
a major component plug-in unit, Teot points alvill include
but are not limited to the following subparagraph requirements.
The RF section ehall have test polnto to monitor the input
oi/ipial waveform, and potential .
The high voltage power supply shall have test points' to monitor
the high voltage potential output*
»
Phyelool 3t»i ^IHaxienMi tevelbpo lidlto and Inatallattob
mounting facilities for the equipment shall be in accordance
with the Boeing Specification Control Drawing 10-20402. All
case protrusions shall be contained within the maximum
envelope liraite.
I
Pin i’Ai'i 0
ui 1 . _ . .
Tr'iTf) iiv ' _ . . .
aii^planH company
REVISED BY
OCH DATE
DCN I.TI/.
Si’LC'IFICATION NO.
A
DIO-20402’
RO
RACE ID
r • r 1 ' 7 4 n
i - /coo
fMOnCAIVOH OOCUMSNT PtA^t
wiglit of liie oqulpnent shall be the minisiusi con-
slstant with the requirements of this specification axid within
the Xlinltatlons of eoutid design* Weight economy is of prime
imporUnee in the doalgn of all flight articles* Ihe naximu,
weight entered on the Boeing specification, control drawing shl^
not be exoeeded* ^
•t
eCN OATI DCN LT*.
lXLO-20it(^
60CIN6 AlftPLANS COMPANY wattu m wm.
»>C l\Ut
' 3. 1.1.2
3.M,2,1
1
I
i 3. 1.1. 2. 2
Electrloul RequlCMientB
El4CirtcA^_.]te^rf«rtfao» Suppression - The equlpwent shall
neet the requiroiente or stl Uociaaont ©107-59-26171, The
equlpwsnt le defined ae Claes 1 per CW07-5:9-2617A; See
Drawing 10.»S!w02,
Dj^lec trie Strength - The equipaent shall be capable of wlth-
standlng the non-operative onrlronaontal conditions of eeotlon
3«1,1«3*1| «nd shall be capable of operation under the opera¬
tive environmental conditions of aeotlon 3, 1,1. 3, 2, without
faHuro or malfunotion.
3.3a.2.3
,1.1.2.)i
Electrical Connections - Connectors Into the equlpnent from
power eotirce , lapul sif?nal8 and antonna shall be located aa
shown, and shall be of the type apocifled| on BAC Drawing
10-201(02 • Connectors on plog*»ln components shall be Canncsi
type DA or DF. modified to include a moisture coal. Part '
nuBihera of modified connectors will bo specified at a later
date, RF oonnectors utlllaed within the assembly shall be
BAC approved.
Internal Wiring - Internal wiring shall consist of printed
circuits to tJio raarLaun possible extent and shall be securely
fastened to the aotmtlng structure. Any electrical wire usod
shall b© in acoordanco ^th an appropriate railitary specifica¬
tion and chnll bo Insulated with cold flow resistant dielectric.
f .*,0
E-
< 1
3. 1.1. 2. 6
Electronic Parts List - The Vendor must sulmlt to BAC for
a^roval a coimpleti list of the t^po and raanufact^irer of all
electronic oarts, BAC Docinnent D2-9129 io appllcablco
Owundlng - Single point croundlng external to the equlpraont
>lng •
package ' 10 to bo cmplpyGd for all clrcuito except those
oircuito of the RP section, Clrcuito within tho cqulpsiiont
package shall be isolated from oquipment cases and base aa
described below,
Transmitter-Power Amplifion A minimum DC Isolation of one
asgohm shall exist between case ground snd all modulation
signal Input tezmlnals (loads).
High Voltage Power Supply* A minimum isolation of one raogohra
shall exist between (l) Input terminals (leads) and case
ground, (2) output temlnals and case ground, and (3) Input
^rmlnals and output terminals.
Individual signal, power, and case grounding is required and
separate ground leads ahall bo provided throtigh connector^
airplane company
1>
.urr
«CVISHn BY
OCN 1>ATL' PCH LTR.
A.
HI
7
srncif-'iCATicN no.
D10*20b02
32 .
a. ...
I P'AGK
SPECIFICATION DOCUMENT PaGE
^ ! 3*1*1«2.6 pins execpt wh«r« signal and power leads must haws a oomnon
/ i (Cont'd) ground due to the haslo olroult design. The provisions of
i OM07-59-2617A paragraph 3. 2.9.1 apply.
I 3. 1.1. 2. 7 Bonding - The provision of QH07>39-26l7A. paraginphs 3*2.3 and
I 3.2.4 apply. Electrical bonding shall be provided between all
unit oasee and the unit mounting structure. A direct metal to
I metal contact with the two surfaces held together by positive
pressure is preferred. For the power supply unit, bonding
may be accomplished through one of the component connector
i pins. A bonding strap may be used on the RF units in lieu
of metal to metal contact.
I
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1
- 4 - -
PEVISFD ur
, R l'
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iGCN L 1 R J
ic
SPtCIf iCA TKJN NO.
DIO-20402
_
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‘ Nu AIKPt ANf: COMPANY
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1 ■ ■■■ 1 . ■ L
13
specificatkM document page
3.1. 1,3
3.1.1.3.1
i 3.1.1^3.1.1
!
I
I
I
3.1.1.3.1.2
3.1.1.3.1.3
t
I 3.1.l.3.1.1t
I
3.1.1.3.1.5
Bnvixvnmental Coadltioits
ll»».OpeWbtv» » Mill* oBi of thippl&g eontalnort Xt»'
•4ax{Muii of eailBfylng tho pexforMBso rtquirtaentB
of •octloQ 3.1.2.2 aftor being eubjeetod to tbe following envlroib.
aeatal conditions.
•
Ibnqponturo'Alti'^o • An aabiont preseuroHiltitude range of sea
level to lOfOOO feet ae encountered during air transport and elr r
teaperatore ranging fron a nininun of (•lt3*C} to a naxinin j
of plus l60*F (71*0), under unsheltered ground conditions. (This
flgoiB is based on a free air tenperatura of 125*7 increased by
35*F solar radiattre heating of a packing case #7 enelosure.) The
air tsMperature aeij change at rates up to 1.8*F\1«0*C} per second.
Vibration > Ooi^tlex vibration (including siimsolds and random
noise) of which the combined aajcliaui is represonted bj the
sinusoidal vibration envelope of Figure 3*
Humidity > Belative humidity to 100)K with conditions such that
condensation takes plaee in the fom of water or frost.
Shock - Slocks involved in free drips of up to 1 inch and
pivot dropa up to U inches. Cbrreaponding acceleration peaks
may be lOOg.
Sand and Duet • Sxpoaure to sand and dust as encountered in
desert ersss.
3.1.i.3«1.5.1 With the Technical Progrers Repprts required by D2«l4l23, the
vendor shall submit a report concerning the packaging of
I equipment to wlthstai^ this enviro»ental condition. Packaging
I Btiall be subject to BAC appmml.
! 3.1.1. 3.1.6 Salt Spray « Kxposure to salt sea atmosphere as encountered
in lisa coast areas* Paragraph 3.I.I.3. 1.5.1 is applicable.
3.1.1. 3.1.7 lUogus • Fhngus growth as ercountered in tropical clijaatea.
Paragraphs 3.1. 1*1. 2.2 and 3.1.1.3.1.5.1 sts applicable.
3. 1*1. 3. 2 Operative ConditioM • The equipment shall be capable of
satisllying the peorToraance requirements of section 3.1, 2. 2
while being subjected to the following envlronmeotal condltionsi
•*
3. 1.1. 3. 2,1 Tempereturv-Altitude - Ap ambient pressure-altitude change
from sea level to 200,000 feat altitude within 1*5 minutes
followed by a constant pressure-altitude of 200,000 feet for
3.5 minutes. Within one minute after missile launch, the
equipment will be subjected to 6oo*F thermsl radiation from
axtemsl coapartmsnt walls. The duration of the ^00* F thenaal
radiation will be about ^ alnutea* Biere will be provisions
tar ground cooling to an ambient compartment tempera turs of
*6S*f during tha prs-launeh period.
PREPAWEO 1
EJY 1
REVISED BY
OCN DATE
DCN i.TB.
SPECIEICATION NO.
TYPED BY !
.X/l-i'i.. .
El.
ra.0-20lt02
r
eSM
30EING AIRPLANE COMPANY
. .
page jUi
SPECIPICATIOH OOCOMEHT PAGE
i >
( A
3.XJ..3.2.2 .
3.1.1.3.2.3
3.1.1. 3.2.Ji
3.1.1. 3.2.5
3.1.1.3.2.6
3. 1.1. 3. 2. 7
3.I.I.4
3.I.I.4.I
PREPARED
BY
TYPED BY
Vibration - Cotqplex vibration ineluding sinusoids as represented
by the vibration envelope of Fi^pire. 4 and random noise as
represented by the vibration env^ope of Figure 5.
Hunidity - Relative humidity to lOOi^
0
Shock - Shocks caused by nissile engine ignition and eutoff .
Excitation of equipment due to ^ak is considered covered
in paragraph 3.1*1*3.2.2.
Acceleration - Sustained acceloration of 15g iraociTum In each
of 3 mutually p-iperidicular axes.
Acoustical Field - Sound pressure levels of 140 db RR5 (RE 0.0002j
d/cm^). overall (37 1/2 - 4800 cps) Random.
Ar.gular Oscillation - Maximum and rms excursions as follows
about each of three mutually peipientlicular axes.
Frequency Range
0.'; to 1 cps
1 te*3 cps
3 to 12 cps
Above 12 CT5S
Reliability
Maximum Excursion
RMS Fjccur^lon
1 degree 0,30 degree
0.5 degree 0,15 degree
0.1 degree 0,03 degree
Determined by local mounting conditions.
'Reliability shell be.e(aasitlbare«baa a desfigb £aetos><!onj;en
equal basis with other design criteria such as perforn^auace ,
weight, and cost. The reliability of the article shall be
such that when integrated into the system of which it Is a
part, it will perform its design function throughout its
required life.
Reliability Reguiremant - The reliability of each telemetry
system is defined as tiie probability of successful operation
for 30 minutes of grouiKi environmental conditions followed
Innedlately successful operation for 5 minutes while
being subjected to flight environmental conditions.
. • ;hOFING AIPPLANE COMPANY
K'f viiy BY N I'Ali
CSfi
. -(
; DIO-20402
i 15
‘PfCK I .4 r|r 'J:'..
•n 4047 4000 («At BAC 11741)
speariCATKM oochmimt f»M
3.1.1.5
>1 ■?
3.1.I.5*2
3.1.I.5.3
Xd«aliifleatl«n of Fi<»dttet
■’f ■
Hm infaruttilM ap*elfi»d^'iitiftli ba p«rMiRsnUy Murk^d on tbo
ortXelOi uain^ Miorlala mBi/n pnoooMoo tbat will inouro
XoKibillt/ durlne tho osq^tod life of tko ortlelo and tteo
proprodttotioa toot* of oobtion U*0« Idootiflootlon aarkinf of
tha articio ataall coafoni to Jlll«»StD*130A« oxeopt that apacoa
for aarklng atock laiaborf rofdatratlod tau«bar» date of
nanafaoturoj contaaotor order nnkboTj. and wel^t na/ bo loft
blank* Ike vonuor'a part nuaber ahali coapletely Identify
the artiole ia the last 12 or loaa dlgita. In aceordanoo
with H1L-6ZD»13QA» the traQaalttox^^aiqilifler unit or unltOf
and tho power aupply unit ehall be identified by individual
part noi^ra*
Booiog I^rt Maabor « The Boeing apeclflcatlon control part
nuaibor ahali noi do pertnanetitly narked on the articio nor
ehall It be contained in any part of tha vondore part nuaber*
Tb facilitate BAG handling a separate and easily ranovable
tag or adhesive label bearing the BAG part nuaber shown on
tho epoeification control drawing ahali be affixed to tho
ertielo* A teg ehall not be attaehed through e aounting hole*
Serial Mual^ing • Articles manufactured la aecordence with this />
s^bi/ication ehall bear serial nuabers aaalgoed by tho vender*
The eerlal nuid>ering systen is the option of tha vendor*
Part luaber Chygea <• Artiolea which eiijial,etaly satisfy tha
rebulrei ents of iKis Bpoclficatlen ahalV be aaaignad a
specific vendor part nuiiher* Artieles which do neX ee^
pletely aatisfy the requirenents of this specif icatlan Shall
be differentiated froathoee tliat do, by a different vender
pert nuidaer* In eddltlon» different Boeing deah nuabent aey
be asalgoad to diatioguleh perto net coapletely aatisfying the
requireuente of this specification* After final approval of
the article by BAG* the part nuaber aealgnod by tha vendor
shall be positive inontifioation such that thif article swd/ar'
conponents aay bo procured by vondSr part nuaber alone Without
rafarenca to this specification* Obingas in the artiele^
ai3d/or ceaponents wnathor initlatad by BAC ar tho voixior» whiah
affaot functional* physical* or structural intorchangeobillty
shall always bo attended by a change in vendor's part naabar
to identify the new configuration* Iko Drawing's nuaber
roquireaents of specification niI^]>5026B shall govern changes in
the manufacturer 'o part numbers*
PREPARED
D Y
RBvitco a« 1 eo* ootc
kMtta.
TYPED BY
RUl.
m.0-20li02
LAH
G
[ BOEING airplane COMPANY
osac 1^
•AC m**
a«*Tpoo
SPECIFICATION DOCUMENT PAGE
3>1>2 D»tAllAd Requireaenta
3*1>2.1 RF Section Design Requirements
Ihe design of the R? section shall be adequate to obtain the required
performance stated in section 3>1>2.2 and the reliability require*
ments as stated in paragraph 3«1.1<U>1> and shall take into con¬
sideration possible degradation of performance due to production
variations, environmental conditions and aging.
3.1.2. 1.1 Cooling - Sie equipment nay be operated for as long as }6 consecu-
tive hoiirs on t^ bench at an ambient tenperature of 80°F with
external cooling such as a cold plate or blower If neobssary.
During the pre-launch period, ground cooling, facilities will be
available to maintain the equipment ambient temperature at approxi¬
mately 6^F. Ihese ground cooling facilities will supply 25 pounds
ol‘ air per minute at about to the instrumentation section and
will be available until 10 seconds before launch. Cooling air will
not oe ducted into any of the components. During flight, there
shall be no external cooling system for the equipment. The unit
shall therefore be assigned and protected as necessary to perform
within the limits specified while oeing subjected to tbe tempera¬
ture-altitude environmental conditions as described in paragraph
3*1. 1.3. 2.1.
3. 1.2. 1.2 Interdependence - Ihe design of the units shall be such that fall-
ures will be contained in the faulty unit and will not cause damage
in other units.
(a) Loss of power supply shall not damage the transskitter.
(b) Loss of exc-tation shall not result in power amplifier tube
failure.
3.1. 2. 1.3 Power Source - Ihe RF section shall operate from 28 t 2
volt D-C power system containing maximum electrical interference
components as sot forth in the test requirements of paragraph
'U.5.2.7. Paragraph 3.2.1. 2.1 is applicable. Ihe power system
negative lead will be grounded external to tbe unit. Maximum cur¬
rent drain shall not exceed li.U5 amp. Ihe RF section secondary
power supplies and converters shall be designed to provide against
the effects of accidental output shorts without damage to the con-^
verter. Fusee or circuits breakers will not beutllized in the
design. Ihe power source impedances will be as follows:
(a) Ground Power - 0.5 ohms or less, DC
0.2 ohms from 2 cycles to 10 la
0.2 ohms to 1.0 ohm linearly from 10 Be to 100 Be
Ground operation power will be supplied by a T.H. unit opera¬
ting from 60 cycle line power. Ihe T.R. unit output will be
26 T DC t 2 volts with maximum ripple limited to t IJ^ (paak
to peak).
PKf PABFn
■>Y
•Vn
s
hY
t /ll>* by I ' rj I
'■ R.U
- ^
'i C.SM
'1 INC, airplane company
F ' D10-20U02
_ li:: _ 17,
4. 1 ittas
SPECIFICATION DOCUMEIIT PAGE
^ 3*1«2.1.3 (cont)- (b) Airborne Power - The airborne PCM/FM prlmaiy power supply
ie a battery eontaininf: approx lira tely 20 oells. The load
on this power simply is approximately 14 arperes. The
Internal Irrpedance of the battery varies with both time and
load. The c;d.eul.' teu nominal initlBl'' internal impedance
of the battery with a 14A load is 0.73 ohms decreasing to
0.63 ohms between 2 and 3 minutes operation. Allowances
for cell variation, JO day stand time and temperature
variation will cause maximum and minimum Initial impedance
values of 0.‘' ohms and O.65 bhms.
3.i.-'.1.4 Adjustments - The equipment shall operate within the toler¬
ances specified i.erein during tlie entire operational life of
the equipment while being subjected to the environmental
conditioni specified without adjustment or tuning, with the
exception of the adjustments p..:r.ltted in section 'j.l.Z.Z.J.
Aliy adjustment controls utllicod by the vendor shall bo
positively locked nd sealed ; rior to deliver . Such adjust¬
ments (v;ith ■exception of those permitted in section 3»1«2.2.3)
sliall not be accessible without disassembly of the plug-in
C'-rny vnents. Signal inputs and ii'^ ut volb ge controls such
as switci'os or x-elayc s'nall net be utilized.
i
f
I
I
I
"S*0»7»00.j IWAS BAC 117ABI
SPECIFICATION DOCUMENT PAGE
3.1. 2.1.5
3.1. 2.1. 6
Ihe RF section transmitter sbsll be crystal stabilised.
Deleted
3.1. 2.1.7
3.1. 2.1. 8
Center Freqaenqr - Ihe center frequency of the RF section
shall be in tbe 225 to 260 megacycles band.
Modulation • Deleted
0
3.1. 2.1.9 unit shall contain adequate filtering
al iis input, terminals to eliminate any fdedbaok ripple greater
than 1.00$ of the primary voltage to tM primary power source.
The current feedback ripple shall not exceed 1.00$ peak of
average load current drain throughout the ripple frequency
domain.
A
3.1.2.1.10
3.1.2.1.10.1
3.1.2.1,10.2
RFModutatlngSigni^ - Ihe transmitter unit of the RF section
shall be capAie of being frequency nodulated by a serial pulse
train from the function programmer (not port of this specif i«
cation). Ihe characteristics of the pulse train are as follows:
See Figure 13 for typical signal wave form.
Wave Form - The wave form will consist of non-return-to-zero
bits, where the positive level indicates the absence of a
pulse^ and the negative level indicates the presence of a pulse.
Pulse Frequency - Ihe nominal modulating frequency will be
172.8 kc i 1$. This assumes an alternate lEZ bit,
pattern of 3U5.6 kilo bits per second t 1$.
i
i
r
I
3.1.2.1.10.3 Pulse Amplitude • Ihe pulse amplitude will be two volts t 3$
with the positive voltage level at ground reference.
3.1.2.1.1U.U Rise and Fall Time - Ihe rise time and the fall time will be
ai27^J23 ioicro seconds when driving a 52 i 0.1$ ohm load.
3.1.2.1.11 te«lwidth - Side bands of the modulated RF carrier signal con» A
taining at least 99$ of the total output power shall be con- 0
talned within the Imc band. Any one side band outside the
above defined band may not exceed 0.25$ of the total outpwat i
power. !
3.1.2.1.12 lhansient Potenttals • Ihe design of the equipment shall be
such as to withstand voltage transients in the power system of
28 ± 12 volts for a maximum duration of 25 milliseconds.
("■iFPAPfP 1
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!
•^Of lNG AIRPLANE COMPANY _ i ; 19
A
< 40.; .0C(> IWAS BAC II74BI
SPEOFiCATtON DOCUMENT PACE
1^
3.1.2.2(J
3.1.2.2.1
3.1.2.2.2
3. 1.2. 2. 3
3.1.2.2.3.1
3. 1.2. 2. 4
3.1. 2.2. 5
RF S«etlon PcrfenMao* R*qulr«a*nta
With power duppllod la aoeordaneo vlth paragraph 3*1. 2.1. 5 aaA
input slgaala la aoeeri with aaetloa 3*1*2.1.10 tha RP atatl«i
ahall aatiafy tha following perforaaaeo requiroaoatat
Mft • Tha oqttipaaat total oparatiag Ufa ahall bo 300 houra.
fHainlyt thla Ufa will ba aeowaalatad »a tha baaeh la nomal
aablant onrlronaeat and aa inatallad la the aiasila in tha
lauaching rarataant* Tha aqulpaaat will oparata at all'tlBoa
during tha alaalla'a fll^t Ufa and will ba uaad to obtain
data £roa a tllb davoral alaataa 'prior ta flrat alaail* notion
until flight tamlnatloB.)
Oalatad
A
Power Output - Once adjusted to tha frequency spaoiflad in
paragraph 3*1*2*2.7( and whan operating into a load whose
Inpadanea lias on or within a VSWR cirela of 2*0 on a Solth
Chart noraaliaad to 30 ohas, tha power output shall ba a ainiaua
of 13 watts and ahall not axoaad IB watta without any
further adjustaent. Two serawdrivar typo adjustaents n»y ba
aaployad In the RP output circuit and they shall ba capable
of being positively looked. Any aaladjustaent during bench
operation shall not daaage tha transmitter. EaviMaBaantal
straasas aa defined by aaotioa 3*1*1*3 shallnot alter tuning
after adjustaent has bean made*
€
During ground operation and while operating into a load eanaing
a V3VR of 3sl« power output nay drop to a nlniaum of 1 watt*
The oanrler frequency shall remain with the specified stability ^
in paragraph 3*1*2, 2*6. Tha RP Section will not be damaged
while operating in the above oondition for a period of two hours.
Linearity - The power output shall ba constant within +0.3
db over the maximum transmitter deviation*
Spurious Radiation • With the exception of the edlocatad
missile receiver pasabasda« all spurious antenna conducted
signals shall ba at least €o db below tha unmodulated carrier
level. Spurious antenna conducted signals in the allocated
receiver pasabands shall ba at learnt 102 db below th* ummodu-
lated carrier level; the receiver passbanda are as follows t
403-420 no; 4. 9-3.7 Kmc. Should a filter be required to
satisfy the above requirement « the filter shall be fully
contained wit|iia a separate nodule to facilitate filter removal
and substitution.
3. 1.2. 2. 6 Stability - The awdulated carrier frequency shall be stable to
within + O.Oljt, including the center frequaaoy tolerance as
specified in paragraph 3*1. 2. 2.7.
PkEFAREP
BY
r— - \ — ; - rr
; r RtYIStO BY
OCN DATE
DCN L7R.
SPECIFICATION NO.
TY^ED BY
j
u ®
010-20402
_ i
A ^
BOEING AIRPLANE COMPANY
1! .
PAsr 40
flAC 11746
SPECIFICATION DOCUMENT PA<t£
t
5. 1.2. 2.7
3. 1.2.2. 8
Caatar rr*QU«ncy - Hi* canter frequency shall be within +
0,005% of the frequency specified* The center frequeBcy"’i8
specified in the reference letter, paragrafdi 2.2.5.
center frequency is defined as that assigned frequency to
which all references to deviation and aodulation are oade.)
Modulation Filter Charaeteristlce - The modulating filter
shall be a low pass filtejP with cut-off at approximately
250 kc and a "roll-off" of approximately 18 db/octave.
(£
V
'T'V
AAr It74 H
2-7.^
SPECIFICATION DOCUMENT PAGE
i )
3.1. 2.2.9
3.1.2.2.10
I
^dulAtion Input S»a»ltlvlty • Tte RP Motion shall haT« a
aaVialtoa sanaiiimy of 4A«KQn;fO •.^lOf^voat (p«ak). Tha RF
Motion shall ba aodulatad by a sarlal UK pulsa tnia of
"onM" and "Saras*' f fad to the nodulatlng flltary with a "one"
being raprasentad by a -2 volt (paak^to^peak) signal and a
"saro" rfepraeantad bylt zero voltf ^ "ana" shall cauaa an RF
cazTlar deviation of lUO kc ^ the highaz' frequency direction
(lUO kc above tha carrier canter frequency) and a "zero"
shall cause an RP carrier deviation of lUO kc in the \ower
frequency direction (ihO kc below tha casrrier canter freq*
uancy). Tha deviation shall not exceed i lUO kc when rood-
ulatad by pulses having asg^litude tolerances specified in
paragraph 3*1.2.1.10.3.
Prljsary Power Tariatlon » The IlF section shall meet the
peri^orMnee requiraaenis specified in this section
during eystan input voltage variations between 26 to 30
volts dc.
4
s»
f;
PREPARFO
BY
U_-- - -1 - -1
1 * ■ T
1 TfEViSKO 14'' ! Di>' HATE
t)CN tTR.
SPECIFICATION NO.
TYPED hY
. i .
k
D10-20U02
_ _ . . i .
. 1
‘ _ 1
_ _
: BOEING AIRPLAhlF COMPANY
^ 6
PAor -
iJAC. 1174 8
2 >7-000 j
SPECIFICATION DOCUMENT PAGE
5.1.3
5.1.3.1
3.1.5.1.1
mUlBBOniB V SMTIOI (10-20402-90)
All Of am ftnorol pbgrslool roquiromoata opoolflod la Bootioao
5.1.1.1 aM applieablo with tho oxooptloa of poMcrajiii 5«1*1*1*9.2.
3.1.3.1.2 nootrloal Bocaigiaito
ill of Aho goaonl olootriool roqiiiraaonto opooifiod la
■ootlono 5.1.1.2 OM applloablo.
5.I.5.I.3
All of tho goaoral onrlroaioatal ooaAltioao of ■ootiOBS
3.1.1. 3 aro applloablo with tho OKOoptioa of paxagrapha
3.1.1. 3.2.2.
3.1. 3.1. 3.1 Tlteatioa - Ooaqitlax wibratloaa laoladlng raaioa rlbxatlon
aa daaarlbad bgr tho anwalopa of Tiguxo 24 and aiaaaoldal
Tlhratloa aa daaorlbad bgr tha anwolopo of Tlgura 4 apply.
3.I.3.I.4 HaliabUlty
Tha raliability raqaironanta of 3.1.1.4 apply.
3.1. 3.1. 3 Idantifloatloa of Pxadiffit
All of tha idaatifioatioa roqulraaenta of 3.1.1.5 apply
azeapt paragr^ 3.1. 1.3* 3.
•3. 1.3. 1.3.1 Part Mbar Ohaagaa - Artlolaa idiloh oonplataly aatlafy the
rafoiivaenta of ttila apaoifloation ahall ba aaalgaad a
apaolflo Toador part noabar. Artlolaa ihloh do aot oonplataly
aatlafy tha raqalranaata of thla apaoifloation ahall ba
dlffaraatlatad fros thoaa that dOf by a dlffarant waador
part BBnbar. In aAdltlon« dlffarant Boaias daah Bnd>ara
■ay aot ba awaiffiad to dlatlngulah parta aot OMqplataly
aatlafyii^ tha raqnlaaaanta of thla apaoifloation. After
final appvowal of tha artlola by Boai^. tha part aaibar aaaignad
by tha raaftor ahall ba poaltlwa Idantifloatloa aooh that tha
artlola aol/or ooa^aaata nay ba proonrad by Tondor part
■ai(hir aloao wltbout rafaraaoa to thla qpaelfloatlan. Ghangaa
la tha artloloy and/or ooapowanta idMthar laltlatad by Boalng
or tha wandort thloh affaat foaotloaalf phyaioal, or
atzuotural latarohaagaablllty ahall alwaya ba attaadad by
a ohaaga la Taadar*a part nwibar to Idantlfy tha aaw aaaflguratloa.
PREPARtn 1
REVISED BY
1 1 SPECIFICATION Nf'.
DCN PATE PCN 1 T_^
BY I
TYPED BY i
1
R. L- L
S'- 3- 63^ P i B10.20402
I
[ _ .
BOEING AIRPLANE COMPANY
1 1 22a
SPECIFICATION DOCUMENT PACE
A
(CoatlauAd)
Vaw dra«iQg8» r«q:airli)g mw drawing nunbant ahall b« drawn
in aooordanoe with 1CIL-S»70527«
M.9.2 Datail BnguirwnwitB
All of tha datail raquirananta of Boetiona 3<1«2 are applieahle*
PREPAPFD ;
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1 ;
' S''tCinCA[ION NO,
1
PEyISEJ by
DON OATC jCCN ' Tr<
'
BY j
TYPfD f'.Y !
i
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; R. 1-
1 1
1 910-20402
1
BOEING AIRPLANE COMPANY j
i !
.A ,■■■ ' , ■
.ACT 22^
BAG 1174 n
7.-1 *0:
iPECiFICAflOH UuCUmFNT page
(
I 3.2
t
i 3.2.1
3. 2. 1.1
3. 2. 1.1.1
3.2.1. 1.1.1
3. 2. 1.1. 1.2
3.2.1. 1.2
DESIGN REQUIREMENTS - MULTIPLEXER PRQORAJiiMER
ANP rooiercAUPB - ^ -
Th« r«qttir«m«iita sat forth hiroin doscrlbo tho doaign ra* i G
quiramanta far Multiplaxar Pragrammar >
(10-20402-41) for an airbarno PCM/FM talamatry ayatam. j
pacific daah numbara ara aaaignad to tha Logic Carda in
aactian 3.8. |
Ganaral Raquiramanta ^
Phyaical Raquiramanta ' 0
Salaction of ft>acification and Stantorda • Spacificationa and
atandarda for nacaaaary commo^haa and aarvicaa not apaci- , G
fiad harain ahall ba aalactad in accordanca with ANA BuUatin
143, axcapt aa provided in paragrapha 3. 2. 1. 1. 1. 1 and 3. 2. 1. 1.-
1.2.
Commercial Parta - Commercial parta having auitabla propar-
tiaa may ba uaad where, on tha data of tha invitation for bida, G
there ara no auitabla standard parta. In any caaa, commercial
utility parts like screws, bolts, nuts, cottar pins, ate. having
suitable properties may ba used provided:
(a) They can ba replaced by tha standard parts (MS or AN)
without alteration.
(b) Tha corresponding standard part numbers ara rafarancad i
in tha parts list and, on tha Vendor's drawings.
Standard Parta • With tha exception in paragraph 3. 2. 1. 1. 1. 1, ' C
MS and AN Standard parts ahaU ba used where they suit tha
purpose. They shall ba identified on the drawings by their
part numbers.
Materials and Procassaa - All materials and processea used G
sbali be In accordanca with government material and process
specifications wharavar applicable. Where tha vendor finds it
necessary or desirable to use materials or processes not cov¬
ered by government spadifications, they shall ba entirely suit- '
able for the purpose. The use of lightweight materials, weight
and space saving designs is a major consideration and their use
shall ba investigated and exploited to the grbatast possible ex¬
tant.
I /i/^
< A if./
^ DIO -20402
K
23
A n
^'.c. 1 Fungus-prooi' Miitcri/jlo ~ Materials thut are nutrients for
fungi shall not bo uood where it is practical to avoid them.
Wliere used, Uiey shall bo treated with a fungicidal agent
acceptable to DAC.
. i .2.2 FJjilahoo - durfaces ahull meet tho applicable finish require¬
ments spocii'iod in U2-l40i)l«
;.2.i.i.2.3 Sijailar and Dissimilar Metals - Similar and dissimilar metals
shall be grouped in accoxxiancB with MlL-l’-lh072. The usage of
dissimilar metals shall be in accordance with MIL-E-SUOOC.
3.2.1.L.3 Producibillty - Hie design shall allow the use of such methods
and processes as will result in maximum production with a
minimum expenditure of manhours and materials 1 confmehsurate
with the quality rciiuirenents unique to the individual model
or typo.
3.2. 1 . 1 Ji Maintainability - MaintAinablllty shall be considered as a
donij-n factor alon/; with otbfr major design parameters. Ihe
design shall provide for and rapid installation or
removal of the unit with- f^imurn of special tof ls or
tanuling equipment. The shall Also provide for simple
installation or removal o^'^iOdKiles from the unit without dis¬
turbing or damaging intartfeblkhting wiring and connectors.
Covers shall bo faatonimi'iaW the minimum number of screws
or bolts necessary to oOi^bliy '♦it.h tho physical stress require¬
ments of this spuclficatlvjpi-*
3.2.i.i.3 Workmanship - Hie 0quip«mfct‘'’»hall be fabricated and finished
in a Uuiroughly workraanll^- l^nner. Particular attention
sluill bo given to frstdoM'fW* defects of solder Joints,
coriiiec. tors , conductors, iiUteJUrtion and jji’intcd circuits] proper
wirang supports, circuit ajTlmgomont and conductor spacing}
and cleanliness during and after assembly. Attention shall
also bo given to freodoM blemishes, defects, burrs, and
sharp edges, a* curacy of dinett^ens} radii of fillets and
working of parts. BAG Doctwtent 152-76 b 7 Is applicable.
3. 2. 1.1. 6 Intorchangoubility - Articles and/or components manul’ac turid
SPECIFICATION DOCUMENT PAGE
3. 2. 1.1. 6 (Cont*d)
in aooordanec %rlth thla apaolflcatlon shall be funotlonally,
physically, and structurally interchangeable. See paragraph
3.2.1. 3* 3 for part nuaber changes for non-interehan/i;eable
articles. See Drawing 10-20^02,
3. 2. 1.1. 7 Construction - The construction of the equipment shall be
adequate to obtain the required perfomanoe and reliability.
Construction of the sub-units shall be nodular to the greatest
possible extent. The use of printed circuit cards to contain
the Progranmer switching logic shall be exploited in the
interests of maximun flexibility.
3. 2. 1.1. 8 Components • The unit shall contain only solid state compo¬
nents. Vacuum tubes, moving parts and adjustable components
are prohibited. All parts shall be chosen to provide high
reliability and consistent performance.
3.2. 1.1. 9 Teat Pointf - Where printed circuit cards are employed,
extension cards shall be provided as special teat equipment.
The extension cards shall serve to bring out beyond the case
perimeter, the exposed clrouit points of the case which are
normally inaccessible. The extension cards shall accormodate
plug-in modules, which will be checked out during dynamic
testing. If all logic circuitry is accessible by extension
cards, test points are not required.
PREPAREn !
BY
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ccN OATt !of:M 1 rn.'
TYPED BY
'■ ' r ^
^ ! DIO-20402
- . 1
. ' 1
. . . . i -
BOEING AIRPLANE COMPANY
■
SPECIFICATION DOCUMENT PACE
5.2.1.1.10
5.2.1.1.11
5. 2.1. 2
5.2.1. 2.1
5. 2. 1.2. 2
5. 2. 1.2.5
5.2.U2.4
Physical Si«« • Maxi mm anvelope llaits and Installation
nountinir faollitlea tor the squlpnent shall ba In aeoordanoe
with Boslng Spsolfloatlon Control Drawing 10-20402.
Vslgfat > Ths weight of the equipment shall be the mlnimuB
oonaistent with the requirements of this speolflcatlon and
within the limitations of sound design. Weight eoonon^ Is
of prime importance in the design of all flight ortiolss.
The maxioniB wei^^ht entered on the Boeing speoifloatlon
oontrol drawing shall not be exceeded.
Electrical Requirements
ELectrioal Interference Suppression - Ths equipment shall
meet the requirements of STL Document CM07o59>26l7A. The
equli»ient is defined as Class I par (a!07>59-’26l7A. See
Dmwlng 10-20402.
Dialeotrlo Strength • The equipment shall be capable of
withstanding the non-operative environmental conditions of
seotion 5. 2. 1.5.1. and shall be capable of operation under
the operative environmental conditions of seotion 5. 2. 1.5. 2.
without system data or functional degradation within speo¬
lflcatlon limits due to dieleotric degradation, failure, or
malfunction.
Eleotrical Connections - Connectors into the equipment from
power source and input signals shall be located as shown
and shall be of the type specified on BAC Drawing 10-20402.
Internal Wiring - Internal wiring shall consist of printed
circuits to the maximum possible extent and shall be securely
fastened to the mounting structure. Any electrical wire used
shall be in accordance with an appropriate mllitn.xy speolfioa-
tlon and shall be insulated with oold flow resistant dlelectrio.
‘ ;
PREPAREn I
_ _ BY _ ^ _
TYPED »Y j
14
BOEING AIRPLANE COMPANY
!• f.'f/ir.L-T . ['' N 11# 1 1 ILiiM
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srt I IF U ATION u' .
DlO-20402
,,r 26
Me 1 1 74 B
K
SPECIFICATION DOCUMENT PACE
3.2.1.?. 5
3.2.1.2.6
3. 2. 1.2. 7
3. 2. 1.3
Kleotronlc Parta List - Th« Vendor Bust submit to BAG for
approval a oonplete list of the typ* and manufacturer of
all elflotronic parts. BAG Document D2-9129 is applicable.
Grounding - Single point groiuiding external to the equipment
package is to be employed for all olroults. Circuits within
the equipment package shall be Isolated from equipment case
and base as follows t
A minimum isolation of one megohm at dc between case ground
and any connector pin (except shield pins) or internal cir¬
cuitry shall be provided.
Case grounding is required and separate signal and power
ground leads shall be provided. Casa grounding shall be
brought out through a pin in eaoh oonneotor. The Multiplexer
System Grounding method is shown in Figure 20,
Bonding - The provisions of GM07-59-?6l7A, paragraphs 3.2.3
and 3.2.^ apply. A direct metal to metsl contact with the
two surfaces held together by positive pressure is preferred.
Environmental Conditions
3. 2. 1.3.1 Won-Cneratlve Conditions - '/nile out of shipping container, |
the equipment shall be capable of satisfying the performance j
requijrements of section 3.?.?.? after being subjected to the i
following environmental conditions.
5.2. 1.3. 1.1 Tempera txire-Altitude- An ambient pressure-altitude range of
sea level to 20,000 feet as encountered during air transport
and air terpernture ranging from a minimum of -45*F, (-^3**C) j
to a maximum of plus IbO'P (71 “c), under unsheltered ground 1
oonditiens. (This figure is based on a free air temperature I
of 125"? increased by 55°? solar radiative heating of a ;
paoking case or enclosure.) The air temperature may change at I
rates up to 1.8"F (l.O'C) per second, ]
I
I
PREPARED i
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TYPED IIY_|
i
•: I SPt. ; jri 'ATPN rjr
j. >-*ev?sr^ ■'> ' j(.K rj li^.'
J- , w ^ ! D10-20i*02
iu
' BOEING AIRPLANE COMPANY
JL
3AC 1*74 fl
SPEaPICATION DOCUMENT PAGE
S. 2.1.). 1.2
3. 2. 1.3. 1.3
3. 2. 1.3. 1.4
3. 2. 1.3. 1.5
3. 2. 1.3. 1.5.1
3. 2. 1.3. 1.4
3. 2. 1.3.1. 7
3. 2. 1.3. 2
3. 2. 1.3. 2.1
3. 2. 1.3. 2.2-
VtbMUiMi • C«ai9l«K vIbimtiM (hthUitog plaAMiiU *a4 vaatwn
MiM) W «ki«k tlM «4MablM4 miudabum !• rOfarvMatod by tii*
■tawDliit vflmtiM •< Vlftor* 3.
HuMiilky - RpIMItp haaliftty to 1M% wllk c— 4itl— that
qaadanaati— takaa flaca Im Ika farm af watar ar Iraat .
Sbaak • Aaakq larahrad la fraa dvapa af up to 1 iach mad.
ftfdt drapa to 4 ladiaa. Cavraapandlag acealaratlau paaka
mayba llOg.
Saad and Itost • Expasura to aand and duat as aaaauakasad la
daaait araas.
With tha Tacbalaal Pragraaa Raparb rafulaad by D2«^jiU|* tha
aaadar aball aubaalt a rapavt caasaralag toa packaglag a|
agu^sMat to urtthstaad Ibis aarlrsaaqaatol aaadltlaaa . ^akag*
lag aball ba subjaat to BAC appraaal.
Salt Spray • Sapaaura to salt saa atsaaspbara as abcanndarad
la aaa asaat araaa . Paragraph 3.2 . 1 . 3 . 1 .5 . 1 Is appHaabls .
Faagus • Puagus grawtb as aacauatarad la trapUal altaaatoa .
Paragraph 3.2. 1.1. 1.2 aad 3. 2. 1.3. 1.5.1 art appUcabla.
OparatlTa Caadltlyia - Tha sfuipmaat Shalllha capabto af
aatlsiff^ tka parlaniMasa rafuiramaats af aactiaa 3.2. 2. 2
uddla balag subjactad to tha fallawlag aarlraamaatal aaadlHana;
Tampa ratara^AUltoda > Aa aaablaat prasfura-aititoda thaaga
fram saa laral ta 200,040 fast altttuda udtola 1.5 mlaatos
follawad by a eaastaad parasaura^altttada af 200,000 faat far
2.5mia«tas. WHbia aaa aoiaato aftar aaissUa lascach, tha
ayilfBasst will ba subjaetod to 400*r toarmal radlsttaa fram
axtaraal eampartoaaat walla. Tha duratlaa aftka 400^ ttMnnal
radlatlaa will ba abaut 3 sslautoa . Thara will ba prarislaaa
far grauad caallag to aa ambiaat caaaparlmaat tamparatura of
445^ duriag tha pra-lauaeh parlad.
Yibratlaa > Caa^laac rlbratlaa ladudlag alausalds as
saatod by tha Mbrstlaa aaralapa af Flgura 4 aad raadam
as raprasaatod^ toa ribratiaB omTslapa af Flgara 5 .
S
naiaa
3. 2. 1.3. 2. 3 Kumidifey * RalatlTS hamldity to 100%.
PREPAREO
By
TYPED BY
30EING AIRPLANE COMPANY
REVISED BY
H
Z' H
DCN DATE bCN I TP;
...i
SPECIF ICAIION 110.
DlO-20402
ii
"1 .ft«0 (WAS KAO I1TA«I
SPECIFICATION DOCUMENT PAGE
S.2.1.S.Z.4
3. 2. 1.3. 2. 5
3. 2. 1.3. 2. 4
3. 2. 1.3. 2. 7
3. 2. 1.4
3. 2. 1.4.1
SbAck - fkotk* c«m«4 Vf miasUt aagiM IgaHUn mad ntafC.
Excttatl«B •£ dM» t« ahadk i« eonaW«r«4 eovatad fai
pMAlrafli 3.2. 1.3. 2. 2.
Accalantian • SuttalMd accal«a«tlan of ISg maxlmtna in
•ack •£ 1 moSaallT parpaadicwlar axes .
Acaaatltal Fiald - Sawad praaaara lavals el 140 db RMS
(RE 0.0002 d/em*) artrall (37 1/2 - 4000 cpa) Raaddm.
Angalaa OaelUatiea - Maximain oad rma axeuvaiaaa aa
Helleaa abaut eadi of three aiutually perfeadlcalar axaa.
rregaeacy Raage Maximum Excaraiaa RMS Eacmaaian
0.5 te 1 cpa
1 to 3 cpa
3 ta 12 cpt
abere 12 cpa
ReliaMlity
ReliaMUty ahall be considered at a dasifn factor ea aa equal
basia wUb other deaign criteria tudi as ferfermaace , weight •
and cost. The reliability el the article shall be such that
udMa integrated iate tiie system of which it it a part, it will
perform its design fuactioa threu^oot Its required ^e.
Rellabil^ Ryutremeat - The reliability ef each Muhi^xer
system is ieratod aa the prebabiltty ef successful eperatiea
for 30 misutas ef ground earirsamsntal cenditioxo foUewed
immediately by successful eperatiOB for 4 minutes while
being subjected te flight earirsnmeatal csndItiaBUi.
A Multiplexer System ia defined as coaaisting of ttie fellewiag
cemplete and eperatienal uaStS!
(a) One Multiplexor Programmer and aaaociated leglc cards
(b) One Multiplexer and associated Ihgic cards
(e) Two Central Boxes and associated logic cards
(d) Six Auxiliary Bsxos and associated logic cards
A reliability of .994 shall be required for ea<di MuUlplexer
V/Vwine
prepared
BY
1
PEVIStD rtY
DC^- ;iATt
TrPFD BY
^ /V
•
30FING AIRPLANE COMPANY
1 degree 0.30 degree
0.5 degree 0.15 degree
0,1 degree 0.03 degree
Determiaed by local mounting conditiens .
^CN l.T9,^
t ^
"I sFToFTI'ArttiN :io.
DlO-20402
«’hGF
2P
Ul 4a«T *000 (WA» MAC 1 1?**)
3 0 2 . 1 . 5
Idsntifieation of Product
The Inforxxiation ■peeiflod ihall be pormanontly marked on
the article I uelng materials and/or proceeees that will insure
legibility during the expected life of the article and the pre*
produetlen tests ef seetien 4.0. Identiflcatien marking of the
article shall conform to MlL-STD-130Af except that spaces
for marking ' - . . registration number , date
of manufacture, eentracter order number, and weight may !
be left blank. The vendor's part number shall completely
identify the article in the last 12 or less digits. |
3 . 2 . 1 . 5 . 1 Boeing Part Number - The Beeizxg specification control |
pert number shall not be permanently marked on the article |
nor shall it bs contained la any part of the vendors part |
number . j
I
To facilitate BAG handling a separate and easily removable |
tag or adhesive label bearing the BAG part number shown,
on the specification control drawing shall be affixed to the i
article , A tag shall not be attached throu^ a mounting hole ,
i
I
3 . 2 . 1 . 5 . 2 Serial Numbering - Articles manufactursd in accordance with 1
this specification shall boar sorial numbers assigned by the j
vendor. The serial numbering system is the option of the i
vendor . I
I
I
3. 2. 1.5. 3 Part Niunber Changes » Articles which completely satisfy j
the requiremsnts cd this specification shall be assigned a |
specific vendor part numbor. Articles which do not com> I
pletely satisfy the requirements of this specification shall \
be differentiated frem those that do, by a different vendor I
part number. In additien, different Bbeing dash numbers
may be assignedte distinguish parts net completely satisfy¬
ing the requirements of this specification. After final appro¬
val ef the article by BAG, the part number assigned by the
vendor shall be positive identification such that the article
and/or components may be procured by vendor part number i
alone without rtforenco to this spoclfleatlen. Changes in
the article, and/er components whetiter initiated by BAG
or the vendor, uhich affect functlssialp physical, or structural
interchangeability shall always be attended by a change in
vendor 's part number to identify the new coxiflguration . The
drawing number requirements of Specification M1L-D-5028B j
SPECIFICATION DOCUMENT PAGE
5. 2,1. 5*4 Supplementary Identifloatlon - A "Unit Code" or "Card Code", as
applicable, shall be affixed to the article to supplement the
part number when its electrical and mechanical configuration have
been verified to be in aocordeuioe with the requirements of a
specific test program as defined in the applicable Program Control
I Drawing. A "PCM/FU Airborne Telemetry Program Control Drawing.
' Test Program will be prepared by Boeing to define the specific
complement of logic cards and the matrix programming of eeich system
purchased under this specification. The Program Control Drawing
effeotivlty for all systems is tabulated in Boeing drawing 21-30000.
"PCM^M Airborne Telemetry Program Control Drawing,"
3. 2. 1.3. 4*1 Unit Code - A "Unit Code" will be stamped on a metal cal and
affixed to the space provided on the nameplate of the Multiplexer
Programmer, Multiplexer, Control Boxes, and Auxiliary Boxes vdien
their logic card complements have bean verified to be in accordance
with the requirements of the applicable Program Control Drawing.
3. 2. 1.3. 4*2 Card Code - A "Card Coda" will be stamped on the connector shell
of the 16 Channel Matrix Cards when the installation of diodes
and Jumper wires has been verified to be in accordance with the
programmiaj requirements of the applicable Program Control Drawing.
3.2.2 Detailed Hegulrements
3.2. 2.1
Multiplexer Programmer Design Requirements
In addition to providing regulated power to the multiplexer units,
the Multiplexor Programmer shall direct the operation of the multi¬
plexer xmits by
…[truncated]