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UNCLASSIFIED
Refitoduced
by tkz
DEFENSE DOCUMENTATION CENTER
FOR
SCIENTIFIC AND TECHNICAL INFORMATION
CAMERON STATION, ALEXANDRIA, VIRGINIA
NOTICE: When government or other drawings, sped*
fi cat ions or other data are used for any purpose
other than in connection with a definitely related
government procurement operation, the U. S.
Government thereby incurs no responsibility, nor any
obligation whatsoever; 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 rights
or permission to manufacture, use or sell any
patented invention that may in any way be related
thereto.
G3-3.
i
lMJW//VCr/7/V
Best
Available
Copy
swxrrzjF *■+, wAS-jv/AfGTxrM
PREPARED bv Rick Urban _
CHECKED by R. Winnie 3-6-59
SUPERVISED by Wesley G. Frederick
3-9-59
APPROVED by James F. Blair 3-9-5
APPROVED BY N, Bryan 3-10-59
SECURITY
CLASSIFICATION T - , ,, ,
approved bv J > Elton Hall 3-16-5
SPECIFICATION DOCUMENT NUMBER 010-20403' ...
TITLE SPECIFICATION FOR AIRBORNE FK/FM TELEMETRY _
_ SYSTEMS _ _
MODEL(S) WS-133A REVISION _ tJL _ DATED_#J“3<> ~ 6.3
ISSUE NUMBER _ ISSUED TO. iff
For Supplemental Information See ruorv m
XXHJQcoaaoaKioaaxBxiiaxsKrHaBDixxjDacEEBDmE specification control drawing 1°-20^Q3 _ )
LIST OF ACTIVE PAGES
RAOE
REVISION
RAOE
REVISION
RAOE
REVISION
RAOE
REVISION
RAOE
REVISION
NUMBER
LETTER
NUMBER
LETTER
NUMBER
LETTER
NUMBER
LETTER
NUMBER
LETTER
REV LTR
REVISION
_ _ ' _ _ } _ _
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DDA'S, ETC-
title Paget Revised List of Active, Pages
Begs Rev. ei Added new revision page,
fog* 1* Paragraph 1.2.2 deleted
Bags Is Paragraph 1,2,1 Eliminated optional provisions
fbge 6: Paragraph 3«1*1»1*1 * added reference to BAG Drawing
10-20103.
Page 6; Paragraph 3*1*1*1*6 - Revised to include components,
ih^e 7; Section 3«1»1*1«9 completely rewritten to define test
po ints
Paragraph 3*1*1.1*10 - rewritten to require SCO
package
Page 7a t Mew page added (due to rewriting page 7 >
Page fit Paragraph 3.1*1. 2.1 - Rewritten to define wiring
specifically*
Pago 0: Paragraph 3.1*1* 2 ,6 Specified separate ground leads.
? d S
S * S l 8
> 9 > < uj
in ui y k x
a a I o y
t>\ w A
nil Ua| >
> | & <
ui ± > a* <
£ 1 1 uJ
u R < at «
ihga ?a i
Page fit
O ¥
\ fV'
* r C p
^ ip *
i i*i
S 'i
Paragraph 3.1*1. 2.1
Pago 0: Paragraph 3.1*1* 2 ,6 Specified separate ground leads.
Page 9* Paragraph 3*1*1»3«2.3 - Changed 95? to ICO?
fttge 13* Sections 3,1, 2.2.1 and 3,1.2. 2.2 completely rewritten
& 11 to define design and performance more completely
Page 13* paragraph 3.1.2.2.2.2 deleted
& 11 3.1.2, 2.1.2 deleted
Pag# ISfi Section 3*1*2*3 - deleted
P»g# 15 1 Paragraph 3.1. 2.1.1 • added sentence on effects of
short circuit.
Page I61 Paragrapha 3.1. 2.6.1. 3 3*1.2,64.3 defined
modulation and linearity
Page 17« Paragrapns 3*1. 2*6.2. 6 through 3*1*2,6.2.11 -
rewritten to more completely define RF ’ <1*.
tX-'-f. section.
Page 17a 1 Hew Jage added (dile to rewritting page 17)
Page 19» Table I Bivieed SCO input Impedances to read 10UK
minimum.
Revised input voltage Range to read * 2.5
volte.
Page 17a 1 Hew
Page 19* Tab;
f 1*8#
IS I
Reason for C hangar STL request (3-16-59)
Chang# , i '•*
Bitec tire « RAD miseilea 003* OO^ lol and on
\m AIRPLANE COMPANY
SEATTLE 14, WASHINGTON
fcMvz&Oj
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANCE WITH- REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION ANO TOOLING INFORMATION, RERUN OOA'S, ETC.
Page 8a,
Page 13,
Page 13,
Page 16,
Paragraph 3. 1.1. 2. 7, Changed to read "A bonding
strap ohall be used", etc., in lieru of "a bonding
strap my be used", etc.
Paragraph 3.1. 2. 2. 2, Replaced "3. 1.2. 4. 2.1" vith
"3 .1 .2 .1 .1 . 3" .
Paragraph 3.1. 2. 2. 2.1, Replaced "VT*" with '9^”
Paragraph 3-1-2.6.2 Deleted "and section 3. 1.2. 3. 1"
Reason for Change: Engineering error
Title Page 1; Deleted list of Active pages, added reference td
Title Page II for Active Page list, edded Reliability
Group Signature.
Title Page II: Added new Title Page with complete list of
Active Pages .
Page Rev b, c, d & e: Added nev revision pages.
Revised table of contents page "a" to list flight proof testa
fer 10-20A03-1 on page 24a in lieu of page 24.
Page c, Revised index page te include figure 7, 8^? and 10}
changed titles of figures 5 and 6. j
Page 1, Paragraph 1.2.2, added new paragraph for mixer J
* circuitry.
Page 1, Paragraph 1.2.3, changed to revV'subc’rrier mixer |
output" in lieu of "subcarrier mixer amplifier out-'
put" j
Pace 3, Paragraph 2.1.1, Deleted reference to MIL-E-B109P j
Page 4, Paragraph 2.1.3, Deleted reference to AF Bulletin
67B (cancelled)
Page 4, Paragraph 2.2, Added sentence "Where conflicting
requirenents exist", etc.
Page 4, Paragraph 2.2.1, deleted reference to Subcontractor)
Status Report Document DK-1Q11, added reference to
Work Statement Document 02-397"! •
Page 5, Paragraph 3>1*1*1*2.1, Critical Materials, deleted
all
Page 6, Paragraph deleted all after first sen¬
tence, added sentence "See paragraph 3 -l-l -3 -3",etcj
Page 7, Paragraph 3*1*1*1*6 (Cont'd) deleted from this page}
due to revision immediately above.
Page 7, Paragraph 3-1 *1*1 *7, Between 2nd and 3rd sentences
inserted new sentence "The subcarrier oscillator
section . . . .units" .
Page 8, Paragraph 3 .1.1 .2 .6, Re-written to detail grounding)
requirements .
Page 8a, New page added for paragraph 3. 1.1. 2. 7 and section
3. 1.1. 3 due to revision immediately above.
Page 10, Paragraph 3. 1.1. 5. Last sentence, changed "Mixer
Amplifier" to rend "Mixer".
Page 11, Paragraph Last sentence, deleted all
aftar "Vendor".
Page 11, Paragraph 3 .1.1 >5 *3# added new paragraph for Part
Number Changes.
Page Ua, Nev page added for paragraph 3-1 *2. 1.1. 4 due to nei
BOEING AIRPLANE COMPANY
SEATTLE 14, WASHINGTON
See Fiage Rev. f
1 _
MODEL
. . . . . . -j _
NO.
DIO-20403
PAGE
Rev.
b
8»c a 661 «-*!
REV LTR
REVISION
B
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHAHOE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DOA'S. ETC.
Paragraph 3.1. 2.1.1. If (Cent'dy deleted due to addi¬
Page
12#
Page
12,
Page
13,
Page
15,
Page
15,
Page
17#
Page
17#
Page
17,
Page
19,
l
Pag*
21#
Page
23,
Page
23,
Page
23a,
Page
23a,
Page
27,
Page
31,
Page
32#
Page
35,
Page
Page
38#
Page
39,
Page
M#
Page
Page
W.
Page
46,
Page
Page
Page
46,
O
£
w»
6
U
X
z
3
QC
»
<
Ui
Q£
¥
g
tion of new page 11a.
Paragraph 3 .1.2. 1.2. 4, Deleted "qualification"
Paragraph 3*1 -2 .2. 2.1, substituted "Upper limit" foil
"fj" and \lov*r limit" for "f2" .
Paragraph 3.1.2.2.2.11, Re-worded, far clarity.
Paragraph 3.1. 2. 3, Added new paragraph for mixer
section requirements.
Paragraphs 3-l*2.6.2.4 and 3.1. 2. 6. 2. 5 moved to pag4
16 due te revision of paragraph 3. 1.2. 6. 2. 2.
Paragraph 3.1. 2. 6. 2. 6, Included canter frequency tol¬
erance as part of stability requirement.
Paragraph 3*1 >2. 6. 2. 7, Defined center frequency.
Paragraph 4 .1.2. 2, Deleted "at no additional cost tq
the Buyer" .
Paragraph 4. 3.1. 3, Re-written to reference Figure 9
far vibration envelope requirements .
Paragraph 4.5 .1.4, Re-written to mere clearly define
the temperature-altitude teat.
Para. 4.5. 1.4.1 re -numbered to 4. 5. 1.4. 2 due to rev j
is ion Immediately above.
Rev page added new for 4. 5. 1.6 due to re-vriting
4.5.I.4.
Para. 4. 5. 1.6, Re-written to detail the interference
teats.
Para. 4.7.3, added new para, for Bvldenee of Accep
tance test.
Para. 6.1.1, External cooling provisions deleted;
para, re-written to more clearly describe condition!
during operating life.
Para. 6.2.1, changed "6.4.3" te read "D2-3971"
"Design proposal submitted” changed to read "design
proposal information submitted" .
Para. 6. 3. 10, Re -worded to more completely define
reliability.
Para. 6. 4. 3.1. 3, Proposal Revisions, deleted all.
Para. 6.4. 3.1. 5, Quotation Program Schedule, deleted
all.
Paragraphs 6.4.3 .2.1 to 6. 4. 3 .2. 5 inclusive which
required reliability program, outline drawings,
sshamatlcs, cutaway drawings and brochure deleted
Reference made to D2-3971 for list of specific sxhi-f
bits required.
Para. 6. 4. 4. 3, Installation and Maintenance 1 ns true
tisns requirements, deleted all.
Paragraph 6. 4. 4. 4, Production Drawings requirements
re-written.
Para. 6.6.1, Request for Quotation re-worded.
Para. 6.6.2, Deleted reference to para. 6.4.3 1°
lieu of D2-3971, Paragraph re- worded.
Para. 6.6.3, Deleted last sentence.
Para. 6.6.4, Fin Quotation, deleted all.
Para. 6.6.3, Purchase Order, re- worded.
See Page Rev.
BOEING AIRPLANE COMPANY
SEATTLE 24. WASHINGTON
MODEL NO.
D/0--ZQ4O3
PAGE
Rev.
- C
REVISION
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DDA'S, ETC.
i>z
1 *
a.) <
u at
S a
Page lt7# Para. 6*6.7* Deleted "subject te proprietary
restrictions stipulated by the Vendor", in (a) j
deleted "Detail" and added "per 6*U.b.iin, in (c).
Added "Program" and added (e) "Interference Control" $tc.
See Page Rev. f
Reason for Cha
«*
Clarification of Specification
Table o ? contents, changed page "2U" te "2iia"
Page c, Added Figure 10, Stock test spectrum
Page 1, Para. 1.2.3, Deleted "or as an alternate, the R.F. ampli¬
fication may be incorporated within the transmitter unit."
Page 2, Para. 1.2.6, Added first aentence "Each complete system
.... supply", and substituted "these" for "the above".'
Page 3, Para. 2.1.1, added reference to MIL-F-1U072 and M1L-E-
5U00C for grouping and usage of diasimilar metals.
Page i|, Para. 2.1. U, Deleted reference to MS335d6 for grouping]
and usage of dissimilar metals.
Page It, Para. 2.2.1, addeu reference to Finish Document D2-L051*
Page 6, Para. 3*1*1*1*2.3, Revised to require finishes in accord
with D2-L051, j.n lieu of "dictated by the metals used":
and subject to BAC approval.
Page 6, Para. 3.1*1. 1.2. It, New para, added requiring grouping ■
and usage of dissimilar metals in accord with M1L-F-
Ht072 and i.lL-E-SUOOC.
Page 6, Para. 3*l*l*l*b, Revised para, heading to read "Main¬
tainability" in lieu of "Maintenance Convenience"
added sentence "Maintainability shall be considered" etc.
Pa«.e 7, Para. 3*1.1. 1.9 added requirement for DC test receptacle.
Page 7, Para. 3*1*1*1*10, Moved to pate 7a to gain space. Alee
deleted 2nd sentence "Space provisions must be made :
within the envelope to replace the subcarrier oscillator
package with a package of ten subcarrier oscillators •
without change to the RF and hi,,h voltage power supply-
sections"
Page b, Para. 3*1. 1*2. 3, Changed to read "shall be ThC type in liei
of "shall be ThC King Electronics Type".
Page 6, Para. 3*1*1»2.6, Substituted "the RF chassis" for "case"
and "leads" for "terminals (leads) ". j
Page 10, Para. 3*1*1*3*2.6, Revised to read "IRQ db" in lieu !
of "156 db" replaced "between lpO cps to 300 cps for •
150 seconds "with "below 300 cps". Deleted last
sentence about acoustic noise effects being covered
by vibration and acceleration requirements of
3.1.1.3.2.2 and 3.1.1.3.2.5* j
Page 10, Para. 3*1*1*3.2.7, Deleted last aentence about angu- :
lar oscillation excitation being covered by vibration j
and acceleration requiremente of 3*1*1.3*2.2 and
3* 1*1. 3*2.5*
Page 10, Para. 3*1*1*U*1, changed to read "R.O minutes" in
lieu of "3*5" minutes.
MODEL
NO.
PAGE
DIO - ?.0 4oi
V.
J
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
BAC 1681 A-R7
a- 7000
O^AOdddY
REV LTR
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE. CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DOA'S, ETC.
a
>|sis
i 3i«
g'Sig
§ «
< Ui
tt £
o u
Page 10, Para. 3*1*1*1>, in last sentence deleted "mixer" and 1 See^Page "Rev.
added "two".
Page 11a, Para. 3*1*2. 1.1. 5, New para, added for transient *
potentials. ;
l|Page 13, Para. 3*1*2. 2. 1.1, changed to read "+5*0 volts" in !
lieu of "+2.5 volts" for Fi, "aero volte" in lieu of ;
"-2.5 volts" for fj "±0.0050 volts" in lieu of
“±0.0025 volts "for fj_ and f2. !
Page 13, Para. 3. 1*2. 2. 2.1, inserted phrase "when 0 times tne j
rated positive input voltage is applied, i.e.," and j
deleted negative voltage requirements. Also added ;
sentence requjring voltage limiters. j
Page Hi, Para. 3*1.2. 2. 2.3, Revised to read "0 or +5" in lieu !
of "±2.5". j
!,Page lit, Para. 3*1. 2. 2. 2.6, Revised to read "0 to +5" in lieu j
of ± 2.5" j
Page 15, Para. 3*1*2. ii. 1.2, Revised to read "l.uO%" in lieu t
of "0.0551". ;
Page lp, Para. 3*1*2. it. 2, added provisions for snort circuit ’
isolation.
Page 16, Para. 3*1*2. 3. 1*2, Revised to road "1.00%" in lieu j
of "0.05%“ and added sentence "The primary. . .onms" ;
Page 16, Para. 3*1.2. 3.2, added 2nd sentence "Hie nigh voltage ;
power supply. ...or circuit breakers".
Page 16, Para. 3.1. 2.6. 2. 2, Deleted requirement for reducing j
power output to 5 watts. j
Page 16, Para. 3*1.2. 6.2. It, Reviaed to specify antenna conducted
radiation & added radiation requirements in the I
receiver passbands, j
Page 22, Para, U.5»l, added "and shock".
Page 22, Para. It. 5*1.2, Revised to require simultaneous random
and sinusoidal vibrations per Figure 5 and 6 in lieu
of sinusoidal vibration followed by rancom vibration
per Figures 5 and 6,
Page 2U, Para. U.5.1.7, Rewritten to reference Figures 9 and l(j
and to more clearly define the reliability test.
Ifege 2i»a, fiew page added for para. It. 5. 2 due to rewriting of
para, U. 5*1.7.
Page 2ltn, Para. U.5.1.8, New para, added for otner environmen¬
tal testa auch as sand and uust, salt spray, etc.
Page 2i*a, Para. U.5.1.5, Added new para, for ohock lest.
rtige k9 Table 1, revised input voltage ran^e to read "0 to +3"
volts in lieu of "±2.3"; tolerance on input impedance
specified, ana preference for higher nr inal input
impedance stated.
P*ga 55, Figure 3, Optional provision for Regulator removed in
two places, power flow vector from regulator to mixer
removed in two places.
Page 56, Figure 1*, revised vibration envelope to read Q.li double
amplitude 5-16 cps, ± 5G 16-30 cps, ± 2U 50-300 cps in
lieu of ±UG 5-H* cps, ±5G 16-112 cps, ±1UG 160-600 cps^
Page 57, Figure 5, Addeu ".OOUU25 DA" and substituted "15. b
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
A AC 1681 »-F 2
MODEL
NO.
1
DI0-2O4O3
1
PAGE
R«av.
6AC l6il A-*2
a. 7000
REV LTR
I
3 l
REVISION
FOLLOW DESCRIPTION OP CHANCE WITH: REASON FOR CHANGE, CHANCE EFFECTIVE
INFORMATION, PRODUCTION ANO TOOLING INFORMATION, RERUN ODA'S. ETC.
Title Page I, added new change letter "E".
Title Page II, added change letters to revised pages list
Page Is, *P&ra» 2.2.1, deleted D2-47SL*
Rev. Page h, New page added for change "E" description.
Page 7a, Para. 3* 1.1. 2. 3, added Power Supply and Power
Amplifier Connector information. Paragraph
removed from Page 8 and added to Page 7a*
Page 8, Para. 3. 1.1. 2.3, removed paragraph from page 8
and added to page 7&*
Page 11, Para. 3*1*2. 1.1.3, added maximum ripple require¬
ment. Changed "DC battery power source" to "DC
power system".
Page 11a, Para. 3. 1.2. 1.1. 3, deleted "due to switching
auxiliary power supplies". Changed "40 volte"
transient potential to "28^12 volts"*
Page 11a, Para. 3*1*2. 1.1. 6, added new paragraph for
overvoltage and undervoltage protection.
Page 43a, ^Deleted page. Photographic coverage, Para.
6.4*6, no longer a requirement.
Reason for Change: Clarification of specification,
request, equipment is in accord.
Vendor
*To reduce scope of photography requirements.
Change Effective:
SA01 & on
SB01 ft on
SCOl ft on
SDQ1 & on
SEOl & on
SFOl & on
3G01 tr on
AB01 & on
AC01 thru AC-17
AD01 thru AD-13
AE01 thru AEQ4
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
e>C 1681 A-A2
MODEL
NO.
DK>-Z040^
— - a
PAGE
Rmv. h
?. 7fVin
REV LTR
REVISION
Sf
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IS
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3
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ft
2
ft
2
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8
a
Ml
8
8
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ft
<A
a
UJ
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s
a.
ft
<
a.
a
UJ
ft
UJ
<
a
mJ
UJ
ft
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANCE, CHANCE EFFECTIVE
INFORMATION, PRODUCT ION ANO TOOL INC INFORMATION. RERUN OOA'S, ETC.
P
Title Page 1, added ohange letter "F".
i
Title Page II, added change letter ”F* to list of active
00
1
page*.
N
N
*R
ns,
V
Rev. Page i, new page added for Rev. "F" description
M
o
*
Page 24, Paragraph 4. 5. 1.7 Replaced "Danonatration of aatie-
<?
J,
1
o
X
factory reliability will be completed when the
C K
‘i
j
r\i
1
J
i
isystemo have operated for 80 eyelet aaeh with no
LU
rQ
T
s
°i
discrepancy or 150 cycles each with a total of no
2
o
y
|T\
J
!
\
more than one discrepancy, or 205 cycles each with
o
<f
0
U
J
3
a total of no more than two diaerenanciee" with
*
in
ifl
V
"Demonstration of satisfactory reliability will be
<
t/>
o’
D
completed when one system has operated for 75
Ul
oc
X
l
\
ii
cycles with no discrepancy*' .
I
a:
s
Reaaon for change: Program cost reduction.
i
Change effective: SA01 & on, SB01 & on, SC01 * on, SDOl
& on, SE01 & on, SFOl & on, 3G01 A on, AB01 &
on, ACOl thru AC17, AD01 thru AD13, & AB01 thru
AB04.
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
MODEL
NO.
DIG-20403
PAGE
Rev. 1
BAC 1681 A-R2
a- 7000
REVISION
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE, CHANGE EFFECTIVF
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DDA'S, ETC.
a Jr . 1 1
* I *s> . O
> , uj xr.
Jl3 * 5
UJ ' UJ , U i Of ‘
Oi a s Cl
UJ ' UJ , U i Of 1
■“f'wul
Title Page, added change letter "0". j® <J> m
Title Page II, indicated revised pagee. V
Rev. Page j, description of Rev. 0 changes. ffi'
Page a, added ~2 and -3 to index. i— ‘Wi-Ti :
Page c, added -2 and -3 to figure index. <;UI ^?!
Pap 1, Paragraph 1.1 and 1.2, aided reforoocee to -2 and -3 -Sl> >. ‘ |
systems. <3^
Pare b, Paragraph 2.2.1, added D2-bS62 to Publications listing. ^ v<dr!-Tj
Pago 5, Paragraph 3.1, changed "10-20103" to "10-20h03 & -2". )<-
Page 17, Paragraph 3.2, changed "10-20U03-1" to "10-20b03-l & -3f. of^
Page 20, Paragraph b.3.1, cnanged "10-20U03 & 10-20b03-l" to ?!
"1020b03 , -1, -2, and -3'. J |
Page 21, Paragraph )|.3.2, same as change to Paragraph b.3.1. ! j ‘
Paragraph b.b.l, changed "10-20U03" to "10-20b03 & -2". j | ■
Paragraph )ub.2, changed "10-20b03-l" to '*10-2Cb03-l & i I
-3". ’
Page 2ba, Paragraph b.5.2, changed "10-20b03-l' to "10-?0b03-l, ; j j
-2 and -3”. j !
Pace 26, Paragraph b.o.2, changed "10-20b03 « 10-20U03-1" to
"LO-2OU03, -1, -2 and -3". Added functional test ! | j
document number, D?-bb6'd , ' !
Page 31, Paragraph 6.1, changed "10-20b03 and 10-20b03-l" to ! • ’I
"10-20b03, -1, -2 and -3". i ! j
Pageb?, T;.ble I, same change as Para-graph 6,1, | j j j
Page 55, Figure 3, changed "10-20bO3" to "10- 2 0b 03 or -2" and j | I
"10-201x03-1" to "10-20b03-l or -3". j i ;
CC O - ij >■
i Reason for Changes
PRR I5bii
| PRR 1561
PRR 1563
Effectivity s SWA 303 9, AD01 & ON, ACOb, AS01 & OH,
. ' 0 1 < ■
: i r ;
UJ ■ * i ' i
rv t -1 | ,J . _J
^ ! Cl 1 U- 1 a. |
^ * « j a I of i
STL request for removal of test connector i
duct cap chain.
Provi-ie for more no uitive mating of DPG !
connectors.
Provide for more positive mating of DSD
connectors.
ib
*
!
Ill;
i M
BOEING AIRPLANE COMPANY | ~— ---|N°‘
i WS-133A : D10-20U03
-U _ Li
PAGE
REV. j
REVISION
i
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN ODA’S, ETC.
Title Pag#, added change letter "H" and date.
Title Page II, indicated revised pages.
Rev. Page K, description of Rev. H changes.
Page 7a,
Page 8,
Page 8a,
Page 11,
Page 4, Paragraph 2.2.1, deleted "D2-2444" and added
"GM 07-59-2617A."
Paragraph 2.2.3, corrected "2-4446-8-316" to read
"2-4446-8-216."
Page 7a, Paragraph 3*1. 1.2.1, changed "D2-2444" to
"GM 07-59-2617A."
Page 8, Paragraph 3.1. 1.2.6, changed "D2-2444, paragraph
3. 2. 2.1" to "GM 07-59-2617A, paragraph 3.2.9."
Page 8a, Paragraph 3.1. 1.2.7, changed "D2-2444" to
"GM 07-59-2617A."
Page 11, Paragraph 3. 1.2. 1.1. 3, changed last sentence "The
maximum current shall not exceed 4.0 ampereB" to
"The maximum current shall not exceed 4.25 amperes
under all operating conditions except for 2:1 and
5:1 VSWR load conditions where a maximum current
of 4.5 amperes is allowable."
Page 17, Paragraph 3. 1.2.6. 2. 7, corrected "2-4446-8-316" to
read "2-4446-8-216."
Page 17a, Paragraph 3.2.1, corrected "2-4446-8-316" to read
"2-4446-8-216."
Page 23a, Paragraph 4. 5.1. 6, changed "D2-2444" to
"GM 07-59-2617A."
Page 47, Paragraph 6.6.7, changed "D2-2444" to "GM 07-59-
2617A."
Page 17,
Reason for Change:
(a) To increase maximum allowable system current per
BMC authorization (Letter 2-6311-4/6A dated 3-8-1 ) •
(b) BMD/BMC/STL direction to replace MIL-I-26600 with
Gm 07-59-2617A as specification for RFI testing of
WS-133A equipment (CCP 354).
uj.z'z fc SjO <£
1 a 1 a . < oj ^ a. _j
! ui ' •. j . a ' r ►_ o. uj
.ajl QluU < or
i O$0y
SS®?;
\%°.0C y
So q.4'
® ?! 1
1
Eff activity:
SA01 thru SG01, AB02, AB04, AB05, AB09, EWA 3019,
AD04 thru AD23, and AE01 thru AE06.
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
MODEL NO.
WS-133A
D10-2Q4Q3
1
i_X Li-
RKV. k
B»C 1681 A-R2
REVISION
//
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANCE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DDA’S, ETC.
Title Page, added change letter "H" and date.
Title Page II, indicated revised pages.
Rev. Page K, description of Rev. H changes.
Paragraph 2.2.1, deleted "D2-2444" and added
"GM 07-59-2617A."
Paragraph 2.2.3, corrected "2-4446-8-316" to read
"2-4446-8-216."
Paragraph 3.1. 1.2*1, changed "D2-2444" to
"GM 07-59-26 17A."
Paragraph 3.1.1.2.6, changed "D2-2444, paragraph
3. 2.2.1" to "GM 07-59-2617A, paragraph 3.2.9."
Paragraph 3. 1.1.2.' 7, changed "D2-2444" to
"GM 07-59-2617A."
Paragraph 3. 1.2. 1.1. 3, changed last sentence "The
maximum current shall not exceed 4.0 amperes" to
"The maximum current shall not exceed 4.25 amperes
under all operating conditions except for 2:1 and
5:1 VSWR load conditions where a maximum current
of 4.5 amperes is allowable."
Paragraph 3.1.2.6.2.7, corrected "2-4446-8-316" to
read "2-4446-8-216."
Page 17a, Paragraph 3.2.1, corrected "2-4446-8-316" to read
"2-4446-8-216."
Page 23a, Paragraph 4. 5. 1.6, changed "D2-2444" to
"GM 07-59-2617A."
Paragraph 6.6.7, changed "D2-2444" to "GM 07-59-
2617A."
Rev.
Page
Page
4,
Page
7a,
Page
8,
Page
8a,
Page
11*
Page
17,
Page
17a,
Page
23a,
Page
47,
Reason for Change:
(a) To increase maximum allowable system current per
BMC authorization (Letter 2-63H-4/6A dated 3-8-1).
(b) BMD/BHC/STL direction to replace MIL-I-26600 with
CM 07-59-2617A as specification for RFI testing of
WS-133A equipment (CCP 354).
Ef festivity :
SA01 thru SG01, AB02, AB04, AB05, AB09, EWA 3019,
AD04 thru AD23, and AE01 thru AE06.
ui 1 j . a 1 :
BOEING AIRPLANE COMPANY
SEATTLE 24, WASHINGTON
me 1631 A-R2
MODEL
WS-133A
K1
! \ I
I !
NO.
DIO-20403
I
REVISION
FOLLOW DESCRIPTION OF CHANCE WITH: REASON FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION. RERUN DDA'S, ETC.
Title Page I, added change letter ”J” and date.
Title Page II, indicated revised pages.
Page 1 (Rev.), description of changes.
Page 26, Paragraph 4.6*2 completely revised to include funct¬
ional test information for each dash number.
Reason for changes To clarify functional test requirements.
•N
Title Page I, added change letter "K" and date.
Title Page II, indicated revised pages. ^ ^
Rev. Page 1, description of changes. P A \ Vv-L. \ C V<_ f
Page b, added "6.7 Specification Waivers." / . -
Page 48a, 48b, 48c, new pages adding para. 6.7. /
Page 4, Added Boeing letter reference under 'correspondences
'msvM .gw*
Title Page I, added Revision Letter L
Title Page II, added Revision Letter L
Revision Page If described the Revision L changes
Page a, added -10 and -11 Speoification Numbers
Page o, added *10 and -11 Specification Number
Page 1, describe -10 and -11 systems
Page 5f added -10 Speoification Number
Page 17, added -11 Specification Number
Page 20, added -10 and -11 Specification Numbers
Page 21, added -10 and -11 Specification Numbers
Page 24a, describe the applicable preproduction Test Require¬
ments for -10 and -11 systems.
Page 26, added -10, *11, -12 and -13 Speolfioation Numbers
Page 31, added -10 and -11 Specification Numbers
Page 49, added -10 and -11 Speolfioation Numbers
Page 55. Added -10 and -11 Specification Numbers
Reason for change i To assign new part maabetra for ths
improved HP Sections.
M | Title Page I, added Revision Letter "K".
Title Page II, added Revision Letter "M".
Revision Page If described Revislor "M" change.
Page d, new pages added list of Material page.
Page 4a, new pages added Boeing corresoondence.
Page 48c, added para. 6.7.2.
Pages 48d and 48e, new pagees added para. 6.7.2.
I
Reason for Change: To show final approval statue of PV/JTH
Telemetry Equipment. Pen.^f-A/ <2 6 741
■" *‘i «<=- -f' • * ■' *- *
I <
U
BOEING AIRPLANE COMPANY
SEATTLE 2A, WASHINGTON
9»C 1681
MODEL
WS-133
NO.
D1O-2Q403
R.E.M- t-ii'iL ?Le>l l -Vi * Re \j \? 2 7 - ?
N (U
ro
1 + O
■ I'f s j
,C0 in v
! ‘ ti fl>, CD
til 5 a: 4i:
(£-3.
l M
am
m
Li
FOLLOW DESCRIPTION OF CHANGE WITH: REASON FOR CHANGE, CHANGE EFFECTIVE
INFORMATION, PRODUCTION AND TOOLING INFORMATION, RERUN DDA'S, ETC.
N Title Pffptjgg added Revision Letter "N"
Title Page ll , Revised list of active pages.
Revision Page m, described Revision N changes.
Page a, Para 3*1 revised to delete "4 -10".
Para 3.2 revised to delete "4 -11".
Added para. 3*3 "Design Requirements for 10-20403-10".
Added para. 3*4 "Design Requirements for 10-20403-11"-.
Page o, added Figures 11 and 12 to Index.
Page 1, corrected FM/FM telemetry system part number to
(10-20403-1, -2, -3, -10 and -ll).
Page 3* Added MIL-D-70327 to Specifications, Military.
Page 5, Deleted -10 from Section 3*1.
Pago 17, Deleted -11 from Section 3*2.
/ Page 17b, New Page, Design Requirements for 10-20403-10.
/ Page 17o, New Page, Design Requirements for 10-20403-10.4“! I
Page 24a, Deleted Paragraph 4*5* 3
Page 24b, New Page, Paragraph 4*5*3 Preproduction Tests
for 10-20403-10 & -11.
Page 26, Paragraph 4*6.2, Changed references from D2-4862
to applicable paragraphs of D2 -4862-1.
Page 63, New Page, added Figure 11.
Page 64, New Page, added Figure 12.
Reason for Changes To include revised vibration requirements
for -12 & -l3.~lTo separate 1S133A system (-2 & 3)
requirements from Y/S133B system (-10 & -ll)
requirements for' clarification of subsequent revisions.
Change Effectives All (WS133B)
o
s g o
> u) Z
III
O Ul
g a $
8 ® 0
iss
iO
THE BOEING COMPANY
SEATTLE 24, WASHINGTON
MODEL
REV
SPECIFICATION DOCUMENT PAGE
TABLE OP CONTENTS
1. SCOPE
2. APPLICABLE DOCUMENTS
3. REQUIREMENTS
3.1 DESIGN REQUIREMENTS FOR 10-20403 & -2
3.2 DESIGN REQUIREMENTS FOR 10-20403-1 & -3
3.3 DESIGN REQUIREMENTS FOR 10-20403-10
3.4 DESIGN REQUIREMENTS FOR 10-20403-11
4. QUALITY ASSURANCE PROVISION
4.1 CLASSIFICATION OF TESTS
4.2 TEST CONDITIONS . *'
4.3 ACCEPTANCE TEST REQUIREMENTS AND PROCEDURES
4.4 COMPONENT TESTS
4.5 PREPRODUCTION TEST REQUIREMENTS AND PROCEDURES
4.5.1 FLIGHT PROOF TESTS FOR 10-20403
4-5.2 FLIGHT PROOF TESTS FOR 10-20403-1, -2, & -3
4.5.3 FLIGHT PROOF TESTS FOR 10-20402-10 & -11
4.6 BAC RECEIVING INSPECTION AND FUNCTIONAL TESTS
4.6.1 RECEIVING INSPECTION
4.6.2 FUNCTIONAL TESTS
4.7 QUALITY CONTROL
5. PREPARATION FOR DELIVERY
5.1 DELIVERY TO BAC
5.2 DELIVERY TO OTHER THAN BAC
5.3 MARKING
PREPARE!)
BY
SPECIFICATION NO.
D10-20403
SPECIFICATION DOCUMENT PAGE
6. NOTES
6.3 INTENDED USE
6.2 APPROVALS AND CLEARANCES
6.3 DEFIKIIXORN AND ABBREVIATIONS
6.4 DATA REQ'JIi'EPENTS
6.5 CHANGES TO THE ARTICLE OR SPECIFICATION
6.6 SEQUENCE OF BAC VENDOR NEGOTIATIONS
6.7 SPECIFICATION V,TAIVERS
PAGE
31
31
32
34
37
44
46
4£&
BAC H74 B
\
SPECIFICATION DOCUMENT PAGE
' (
S’
V
Figure No.
1
2
3
>
5
6
7
8
9
10
11
12
FIGURE INDEX
Title
Qualification Discrepancy Report
Acceptance and Functional Test Summary
Block Diagram of System ( 10-20.1(03# " ’"l
■'-2* and —3, -10 and -ll)
Sinusoidal Vibration Envelope for
Equipment Non-Operative
Sinusoidal Vibration Design Envelope
for Equipment Operative
Random Vibration Design Envelope for
Equipment Operative
Sinusoidal Vibration Acceptance Test
Envelope for Equipment Operative
Shock Test Spectrum for Equipment In-
Operative
Sinusoidal Vibration Envelope, Simulated
Flight Environment
Random Vibration Envelope, Simulated
Flight Environment
Random Vibration Envelope for
Equipment Operative, -11 HF
Sections
Sinusoidal Vibration Envelope for
Equipment Operative, -ID, -1'. RF
"Sections
Page
50
$3
55
56
57
58
59
60
61
62
63
64
PREPAREO
BY
REVISED BY
OCN DATE
DCN LTR.
SPECIFICATION NO.
D10-20U03
TYPEO BY
A.H.
§-l-(e>0
G
E.&.D.
2-22-4*
L
BOEING AIRPLANE COMPANY
U.L.
-f-3 o-6>3
N
PAOe C
B -
i
I
B i
i
G>
B. i
Q>
B
N
rt
I,
SYM IV
^ For Approvals and Clearances, see D2-4858.
Final anoroval Is granted to these units. The
^ vendor Is United Electrodynamics Incorporated,
Pasadena, California} Vendor code number OflOll.
10-20403-13
10-20403-12
>
10-20403-11
>
10-20403-10
(*>
in-20403-9
p ^ Vendor P/N
t-' 12966-3
10-20403-8
Vendor P/N
~ 12967-1
10-20403-7
L^. Vendor P/N
^ 12Q66-2
10-20403-6
f-s^ Vendor P/N
F* 12966-1
10-20403-5
1 ^ Vendor P/N
12967
10-20403-4
L^ Vendor P/N
~ 12966-0
10-20403-3
! _ Vendor P/N
12R1Q-3 .
'
10-20403-2
i Vendor P/N
F" 12819-2
10-20403-1
I Vendor P/N
12819-1
.
10-20403-0
L^. Vendor P/N
^ 12819
REQD
PART OR IDENTIFYING
NUMBER
NOMENCLATURE
DESCRIPTION
MATERIAL
MATERIAL SPEC
WT
LIST OF MATERIAL
Airborne FM/FM
Telemetry System
CODE
IDENT NO _
81205 *
SIZE
A
D10-20403
SCALE
AF 04(647)-289 SH a
U 3 4J16 OOOO-RtV. 12/61
2
4*
SYM IV
^ For Approvals and Clearances, see 02-4858.
Final approval Is *r ant, ad to these units. The
^ vendor is United Electrodynamics Incorporated,
Pasadena, California; Vendor code number 08011.
10-20403-13
10-20403-12
>
10-20403-11
10-20403-10
>
10-20403-9
["^ Vendor P/N
L-' 12966-3
10-20403-8
K, Vendor P/N
” 12967-1
10-2O4O3-7
L^. Vendor P/N
^ 12966-2
10-20403-6
r>. Vendor P/N
F* 12966-1
10-20403-5
I . Vendor P/N
12967
10-20403-4
[ ^ Vendor P/N
~ 12966-0
10-20403-3
| _ Vendor P/N
■" 12R19-3
10-20403-2
[ Vendor P/N
F” 12819-2
10-20403-1
I _ Vendor P/N
F* 12819-1
10-20403-0
Vendor P/N
^ 1,2819
REQD
PART OR IDENTIFYING
NUMBER
NOMENCLATURE
or
DESCRIPTION
MATERIAL
MATERIAL SPEC
WT
LIST OF MATERIAL
Airborne FH/FM
Telemetry System
CODE
IDENT NO
81205 *
SIZE
A
010-20403
SCALE
AF 04(647)-289 SM d
I
t H
U 3 4316 O000**ev. 12/61
i
SPECIFICATION DOCUMENT PAGE
«»
I
4 *-
1.
1.1
1.2
1.2.1
1.2.2
1.2.3
1.2.4
SCOPS
SYSTBi FUNCTION
This specification outlines the characteristics and performance
requirements of airborne FM/FM telemetry systems (10-20403. -1* -2,
-3, -10 and -ll) for use in research and development flight
tests of an intercontinental ballistic missile.
SYSTEM COMPONENTS
The systems specified herein shall consist of the following
major components as shown in block diagram, Figure 3* Systems
10-20403 and -1 are physically Interchangeable. They differ
electrically only in transmitter center frequency.
Systems -2 and -3 are electrically interchangeable with systems
10-20403 and -1 respectively. Physical differences are as
noted on Specification Control Drawing, 10-20403*
Systems -10 and -11 are eleotrically and mechanically inter¬
changeable with the -2 and -3 but are improved through incorpora¬
tion of higher rated tubes and related oircuit changes.
Subcarrier Oscillators
The subcarrier oscillators shall convert the output signals
from transducers and signal conditioners into frequency modu¬
lated IRIG subcarriers.
Mixer
The mixer circuitry shall accept the ‘modulated subcarrier
oscillator output signals, mix these signals, and provide a
single modulating input signal for the RF Section transmitter.
RF Section
The RF Section shall consist of an RF transmitter unit and RF
amplifier unit. The RF Section shall be suitable to accept the
subcarrier mixer output voltage and produce a frequency modu¬
lated RF signal which will in turn be fed to an antenna triplexer.
(Not part of this speoifioation).
D.’C. Regulator ,
A D.C. regulator shall provide all power required for the
suboarrier oscillator units.
PREPARE0
BY
REVISED BY
DCN DATE
DCN LTR.
. SPECIFICATION NO.
TYPEO DY
EB'b
2-21-icZ
L
L10-20403
R.L.L,
4*3o.U3
N
BOEING AIRPLANE COMPANY
•
PAGE 1
L
ii
SPECIFICATION DOCUMENT PAGE
The high voltage power supply shall furnish all the power
required for the If seotion*
•I'M-*
Sadi a caplets system shall include two component aounting
structures - One for the SCO section, Sizer oirouitry and
D.O. Regulator and the other for the H.f . aeotlon and High
Voltage Power Supply. The ooapoaent aounting atrueturoa
shall provide all of the physical support required for
these ooaponente, shall contain all inter-ooeponent eleotrioal
wiring, and shall provide heat elnka aa required.
PREPARED
BY
BOEING AIRPLANE COMPANY
DCN DATE j
DCN LT(f.!
SreClEICAllON NO.
7* k-s:t .
©10-20403
SPECIFICATION OOCUMENT PAGE
2.
2.1
2.1.1
2.1.2
APPLICABLE DOCUMENTS
GOVERNMENT DOCUMENTS
The following government documents of the exact issue noted,
together with the noted revisions thereto constitute a part
of this specification, but only to the extent defined herein.
In those cases where the document listed is not dated, the
issue in effect on the date of invitation for bids, shall
form a part of this specification. Where conflicting require-|
ments exist, the requirements of this specification shall
govern.
Specification - Military
MIL-D-5028B
MIL-E-5UOOC
MIL-D-5U80C
MIL-T-91U7
MIL-E-005272B
MIL-F-1U072
MIL-D-70327
Standards
MIL- STD-12 A
MIL- STD-28
MIL- STD-1 2? B
MIL-STD-130A
MIL-STD-LL2
"Drawing and Data Lists, Preparation of Manu¬
facturers", dated 20 August 1956.
"Electronic Equipment, Aircraft, General
Specification for", dated 15 July 1958.
"Data, Engineering and Technical (Reproductiorj
Thereof)", dated 29 September 19 5U.
"Test Reports, Preparation of", dated 13 July
1953.
"Environmental Testing, Aeronautical and
Associated Equipment, General Specification
for", dated 5 June, 1957 J with Notice 2 dated
June 21, 1957.
"Finishes for Ground Signal Equipment",
dated 15 May 1955.
"Drawings, Engineering and Associated Liets",
dated 16 March 1959*
Abbreviations for Use on Drawings" dated 11
March 1952.
"Approved Method for Assignment of Lrawing
Titles", dated 2 June 1958.
"Marking for Shipment and Storage" dated 10
April 1957 with Change Notice - 1 dated 6 '
January 1958.
"Identification Marking of U.S. Military
Property" dated 8 September 1958.
"Telemetry Standards for Missiles and Air¬
craft" dated 26 September 1958.
PREPARED
OY
REVISED BY
0O> PATE
»CM LTR.
SPECIPICATION NO.
TYPED DY
R. U
4-17-5^
B
D10-20U03
R.l.l.
4 -30-fc!
N
BOEING AIRPLANE COMPANY
PACK 3
SPECIFICATION UOCUMEH1 PAGE
ft
I
2.1.3
Public at Iona
1
<
ANA Bulletin 143d
"Specification and Standards, Use of", dated 19
August 1954. !
ANA Bulletin 405
"Storage Life - Aeronautical Article", dated !
September 21, 1951, including Amendment 3 dated i
July 20, 1956.
2.1.4
Deleted.
2.2
1
NONGOVERNMENT DOCUMENTS
j
The following non-government documents, cf the exact issues shown,
form a part of this specification to the extent specified herein. In
those cases where the document is not dated, the latest issue in effect
on the date of invitation for bids shall form a part of this specifica¬
tion. One copy each of the documents listed below and marked with an
asterisk is to be furnished with each copy of this specification being - j
sent to a vendor. Vlhere conflicting requirements exist, the require¬
ments of the specification shall govern. ;
2.2.1
Publications
GM 07-59-2617A
STL Document "Electro Interference Control Require¬
ments for Minuteman (WS-133A)."
*D2-3971
Boeing Document "Work Statement for Airborne FM/FM
Telemetry Systems."
*02-4051
Boeing Document "Protective Finish Performance
Document for Model V.'S-133A." j
*05-2288
Boeing Document "Approved Standard Electronic
Components."
*05-2300
Boeing Document "Packaging Requirements.”
D2-4862
Boeing Document "Functional Test Procedures,
10-20403 Airborne FM/FM Telemetry System."
2.2.2
Drawings
*10-20403
Boeing Drawing, Specification for Airborne ?H/TH
Telemetry Systems.
2.2.3
Correspondence
Boeing Materiel Letter to United ElectroDynamics ,
2-4446-8-216 dated July 30, 1959. (Confidential)
Boeing letter 2-6432-10-41, Nor. 17, 1961, RFI j R
waiver request for the PCM/FM and Tti/M RF sections j
PREPARED
BY J . . _ ......
, ! j IHlAI'ON i/, j
Rt VISED L*Y £. * 1 . ■ • T ‘ : ,* ( !
TYPED !!Y !
AH - (r K D10-2Q403 1
|
; t : ;
BOEING AIRPLANE COMPANY
'! . * . 4
fci A C n 74 H
SPECIFICATION DOCUMENT PACE
2.2.3 (Cont.) Correspondence
Boeing Materiel TV/X to United Electrodynamics
2-4437-1-6229, dated 10-5-62.
Boeing memos 2-6425-01-78 an*4 -82 dated 10-16-62;
10-20403-7, -8, -9 Workmanship Deviations.
i
PREPARED
BY
M 1 . i Mfft' nf\
RE V ' 0 BY , f-1." : ID r I r.-
TYPEO_ fiY
JR 3~/¥’l IA ^0-20403
r- •- J
4a
BOEING AIRPLANE COMPANY
BAC. 11 74 B
I
SPECIFICATION DOCUMENT PAGE
T .
4* '
r
X
3.
3.1
3.1.1
3. 1.1.1.
3.1.1.1.1
3.1.1. 1.1.1
3.1.1. 1*1.2
3.1.1.1.2
3*1. 1.1. 2.1
REQUIREMENTS
DESIGN REQUIREMENTS FOR 10-201*03, and^-2. -5 )
* ■ - * t
The requirements set forth herein describe an airborne F>|/FM
telemetry system. ‘
General Requirements
Physical Requirements
Selection of Specification and Standards - Specifications
and standards for necessary commodities and services not
specified herein shall be selected in accordance with ANA
Bulletin 11*3, except as provided in paragrapns 3*1. 1.1. 1.1
and 3. 1.1.1* 1.2. The requirements of MIL-STD-1*1*2 apply to
the extent specified herein as requirements of this speci¬
fication.
Commercial 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, commercial
utility parts like screws, bolts, nuts, cotter pins, etc.
having suitable properties may be used provided:
(a) They can be replaced by the standard parts (MS or AN)
without alteration.
(b) The corresponding standard part numbers are referenced in
the parts list and, on the vendor's drawings.
Standard Parts - With the exception in paragraph 3.1.1. 1.1.1, MS
and AN standard parts shall be used where they suit the purpose.
They shall be identified on the drawings by their part numbers.
Materials and Processes - All materials and processes used
shall be in accordance with government material and process
specifications wherever applicable. Where the vendor finds it
necessary or desirable to use materials or processes not
covered by government specifications, they shall be entirely
suitable for the purpose. The use of lightweight materials,
weight and space saving designs is a major consideration and
their use sliall be investigated and exploited to the greatest
possible extent. . '
Deleted
PREPARED
BY
REVISED BY
DCN DATE
DCN LTR.
SPECIFICATION NO.
DIO- 201*03
TYPEO BY
eb.d.
L
Z.LX.
4-30*43
N
BOEING AIRPLANE COMPANY
^ -
PAoe S*
L
ii
SPECIFICATION DOCUMENT PAGE
J
V
!
i
3. 1.1. 1.2. 2 Fungus-Proof Materials - Materials that are nutrients for
fungi shall not be used where it is practical to avoid them.
Where used, they shall be treated with a fungicidal agent
acceptable to BAC. i
3. 1.1. 1.2.3 Finishes - Surfaces shall meet the applicable finish require- | 0
ments specified in D2-4051.
3.1.1. 1.2.4
3. 1.1. 1.3
3. 1.1. 1.4
3. 1.1. 1.5
3. 1.1.1. 6
Similar and Dissimilar Metals - Similar and dissimilar metals : g,
shall be grouped in accordance with MIL-F-14072. The usage :
of dissimilar metals shall be in accordance with MIL-&-5400C .
Produclbillty - The design shall allow the use of such methods j
and processes as will result in maximum production with a
minimum expenditure of manhours and materials, commensurate
with the quality requirements unique to the individual model 1
or type. j
Maintainability - Maintainability shall be considered aa a g>
design factor along with other major design parameters. The
design shall provide for simple and rapid installation or {
rmnoval of components (listed in section 1.2) from the compo¬
nent mounting structure, Boeing Drawing 10-20403, without die- ;
turbing or damaging interconnecting wiring and connectors, and
without special tools or equipment. If a box type structure |
is utilized, the cover shall be removed without special tools •
and with a maximum of 10 bolts or screws. Any gaskets utilized !
with the cover shall be secured to the cover to prevent loss i
of, or damage to, the gasket upon removal of the covwr. ;
i
Workmanship - The equipment shall be fabricated and finished !
in a thoroughly workmanlike manner. Particular attention
shall be given to freedom from defects of solder joints, I
connectors, conductors, insulation and printed circuits; I
proper wiring supports, circuit arrangement and conductor I
spacing; and cleanliness during and after assembly. Attention j
shall also be given to freedom from blemishes, defects, burrs, i
and sharp edges, accuracy of dimensions; radii of fillets and
working of parts. BAC Document D5-2300 is applicable as noted
above . D
Inter changeability - Articles and/or components manufactured ! g,
in accordance with this specification shall be functionally,
physically, and structurally interchangeable. See paragraph
3.1. 1.5.3 for part number changes for non-inter changeable
articles. !
PREPARED
BY
TYPED BY
J. REV!SfD_p;
Jj _ ft U
BOEING AIRPLANE COMPANY
L-CfJ DA M DO '
3-ST-S-4 A
w- n Eri B
j/r/s-3 ' D
CIFICATON Nr*.
010-201*03
r''‘ i 6
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BAC n 7* B
li
SPECIFICATION OOCUM6NT PAGE
I
3. 1.1. 1.7
3.1.1.1.&
Construct ion - The construction of the system shall be adequate
to obtain the required performance and reliability under the
conditions of tnis specification. Modular construction shall
be used to the greatest extent possible, and each major component
as listed in section 1.2, shall be a plug-in type unit. In
addition, the subcarrier oscillator section shall include 5
individual plug-in type subc-rrier oscillator units. The design
shall be such that any of the subcarrier oscillator units can
be removed and replaced in the subcarrier oscillator section
while the section is installed on the mounting structure. The
entire subcarrier oscillator section in turn shall be designed
such that it can be removed from and replaced on the component
mounting structure without affecting the other major components.
The component mounting structure may be utilized to serve as a
heat sink and/or function as an RF shield. The major components
and sub-compenents shall be identified by individual part number
as specified in paragraph 3.1. 1.5*
b
Components - With the exception of the RF section, the system
shall contain only solic state components. Vacuum tubes and
moving parts except for factory set adjustments, are
proonibited. In the RF section, solid state components in
proven, conservatively designed circuits shall be used to the
greatest possible extent. All partssnall be chosen to
provide high reliability ana consistent performance in system
operation.
3.1.1. 1.9
3.1.1. 1.9.1
3.1.1.1.9.2
Test Points - Care must be taken in providing electrical test
points to ensure that external loads (such as cable
capacitance or inadvertent ahorta) introduced by the testing
activities does not cause damage to the aystem or components under
test. Electrical teat points available for use in system testing
shall be sufficient to isolate a f..ult to a major component plug¬
in unit. Test points monitoring DC functions of the RF package
shall appear at a receptacle mounted on the RF package. Aa snown
on specification control drawing 1Q-2QU03, this receptacle shall
be located on the same surface as the RF ceax connector. Test
points stiall include but are not limited to the followingi
£>;
Each subcarrier oscillator sliall have test points to monitor
the output signal.
Summing network output shall be provided at test points.
3.1.1.1.9.3 Voltage regulator output shall be made available at test points.
3.1.1. 1.9. 1* High voltage power supply output snail be made available at test
points.
3.1.1.1.1U Physical Size - Envelope limits ana installation mounting
facilities for the system shall be in accordance with the
Boeing Specification Control urawin„ 10-2uU03.
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SPECIFICATION DOCUMENT PAGE
3.1.1.1.11 Weight - The weight of the system components shall be the minimum
consistent with the requirements of the specification and within
the limitations of sound design practices. It shall not exceed
the value specified on the Boeing Specification Control Drawing
10-20403.
3. 1.1. 2 Electrical Requirements
3.1. 1.2.1 Electrical Interference Suppression - The system shall meet the
requirements of STL Document GM 07-59-2617A. The systems are
defined as Class I per GM 07-59-2617A.
3. 1.1. 2. 2 Dielectric Strength - The system shall be capable of withstanding
the non-operative environmental conditions of section 3. 1.1, 3.1,
and shall be capable of operation under the operative environ¬
mental conditions of section 3. 1.1. 3. 2, without failure or mal¬
function.
3. 1.1. 2. 3 Electrical Connectors - Connectors into the telemetry package from
power source, transducers and antenna shall be located as shown,
and shall be of the type specified, on BAC Drawing 10-20403.
Connectors on the plug-in components except the power supply and
' RF power amplifier shall be Cannon type DAD or DED. The power
supply and RF power amplifier power connectors shall be Cannon DE
or DA type within a pressure sealed cavity using a vulcanized
compression gasket 3eal at the interfaces. RF connectors utilized
within the assembly shall be type TWC or TM.
PREPARED
BY
TYPED BY
I T Uir '• A MON NO.
REVISED ft Y | PCN pATf fo-'N l ’K.j
AH H D1O-204Q3
BOFING AIRPLANE COMPANY
SPECIFICATION DOCUMENT PACE
3. 1.1.2. 4 Internal Wiring - Internal wiring shall consist of printed cir-
cuits and shall be securely fastened to the mounting structure.
Any electrical wire used shall be in accordance with an appropriate
military specification and shall be insulated with cold flow re¬
sistant dielectric.
3. 1.1. 2. 5 Electric Parts List - The Vendor mist submit to BAC for approval a
complete list of the type and manufacturer of all electronic parts.
BAC Document D5-2288 is applicable whenever design permitB.
3. 1.1. 2. 6 Grounding - The provisions of GM 07-59-2617A, paragraph 3*2.9* are
applicable. Single point grounding external to the equipment
package will be employed for all circuits except those of the RF
section; thus, circuits within the equipment package shall be
isolated from equipment cases and base as described below:
(a) Transmitter-RF Amplifier: A minimum DC isolation of one
megohm shall exist between the RF chassis ground and all
signal input leads. DC isolation shall be provided by a
transformer external to the transmitter.
(b) High Voltage Power Supply: A minimum isolation of one 1
megohm shall exist between (1) input terminals (leads) and j
case ground, (2) output terminals and case ground, and (3)
input terminals and output terminals. j
(c) Sub-Carrier Oscillators: A minimum isolation of one megohm
from 0 to 500 cpa between case ground and any point on the j
signal circuit shall be provided. A minimum DC isolation of i
one megohm shall exist between input power terminals (leads) j
and case ground. Separate signal and power ground leads shall >
be provided, through connector pins. Isolation between |
signal circuit and power circuit within the unit is not a
requirement . I
j
(d) Regulator: A minimum DC isolation of one megohm shall exist '
between case ground and all input and output terminals (leads). j
(e) All Units: To prevent the formation of "power loops" (low ]
resistance loops formed by power distribution leads and signal |
return leads), balanced circuit design shall be utilized. j
PREPARED
BY
REVISED BY
j ' A T 1 0 N NO.
or* da n Jcv:n i
'6-rVC^ H i p10_2C>403
; 1
TYPFD BY
AH
_
DOPING AIRPLANE COMPANY
T ’ , -,r 8
■ ■ ■ J - 1 -
,i1 40 47 SO 00 (WAS BAC 1174B)
SPECIFICATION DOCUMENT PACE
3. 1.1. 2.7 Bonding - The provisions of QM 07-59-2617A, paragraph 3.2.3 apply.
filectrical bonding shall be provided between all component caaes
and component mounting structure. A direct metal to metal contact
with the two surfaces held together by positive pressure is pre¬
ferred. Except for the RF Section, bonding may be accomplished
through one of the component connector pins. A bonding strap
shall be used on the RF section in lieu of metal to metal contact.
3. 1.1.3
Environmental Conditions
3. 1.1. 3.1 Non-Operative Conditions - The FM/FM telemetry system shall be
capable of satisfying the performance requirements of section
3. 1.2. 1.2 after being subjected to the following environmental
conditions.
3. 1.1. 3*1.1 Temperature-Altitude - An ambient pressure-altitude range of sea
level to 50,000 feet as ercountered during air transport and air
temperatures ranging from a minimum of -80°F (-62°C) to a maxi mum
of plus 160°F (71°Cj, under unsheltered ground conditions. (This
figure is based on a free air temperature of 125°F increased by
35°F selar radiative heating of a packing casg or enclosure.) The
air tengxsrature may change at ra*.es up to 1.8°F (l.0°C) per second.
PREPARED
BY
^REVISED BY DON n*T( b N LT-.'.
AH 5-ra-ti H !
( If I A MON
DIO-20403
DOPING AIRPLANE COMPANY
111 4047 9000 (WAS SAC H7««)
SPECIFICATION DOCUMENT PAGE
3.1.1.3.1.2 Vibration - Complex vibration (Including sinusoids and random
no lea) of which the combined maxima la represented by the
sinusoidal vibration envelope of Figure U.
3. 1.1. 3.1.3 Humidity • Relative humidity to 100$ with conditions such that
condensation takes place in the form of water or frost*
3.1.1.3.1.U 8hock - Shocks involved In free drops of up, to 1 inch and
pivot drops up to U inches as encountered in shipment.
Corresponding acceleration peaks may be lOOg.
3«1»1«3*1*5 Sand and Oust - Exposure to sand and dust as encountered in
desert areas.
3.1.1. 3.1.6 Salt Spray - Exposure to salt spray atmospnere as encountered
in sea coast areas.
3*1.1. 3*1.7 Fungus - Fungus growth ac encountered In tropical climates.
3.1.1.3.2 Operative Conditions - The Fh/FM telemetry system shall be
capable of satisfying the performance requirements of section
3. 1.2. 1.2 while being subjected to the following environmental
conditional
3.1.1. 3.2.1 Temperature-Altitude - An ambient pressure-altitude change from
sea level to 200,000 feet altitude within 1.3 minutes followed
by a constant pressure-altitude of 200,000 feet for 3 minutes.
There will be provisions for ground cooling to an ambient
compartment temperature of ♦ 65* F during the pre-launch period.
Within one minute after missile launch, the equipment will be
aubjeoted to 700* F thermal radiation from external compartment
walls. The duration of the 700 *T thermal radiation will be
about 3 minutes.
3*1. 1.3*2. 2 Vibration • Complex vibration including Simwoids as represented
by the vibration envelope of Figure 5 and random noise as
represented by the vibration envelope of Figure 6.
3. 1.1. 3.2. 3 Humidity - Relative humidity to 100$.
3*1.1. 3*2.U Shock • Shocks caused by missile engine ignition and cutoff.
Excitation of equipment due to shock is considered covered
in paragraph 3.I.I.3.2.2.
3.1.1. 3*2. 5 Acceleration - Sustained acceleration of 3$g maximum ia
each of 3 mutually perpendicular axes.
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SPECIFICATION DOCUMENT PAGE
'•« l
< J
3 .1.1 .3 .2 .6 Acoustical Field - Sound pressure levels of 140 4b (RE 0.0002 d/cur2
principally below 300 cps.
3*1 .1-3 *2.7 Angular Oscillation * Maximum and me excursions as follows abeut
each of three mutually perpendicular axes.
3 .1.1.4
3- 1.1.4. 1
3.1 .1.5
3-1.1. 5.1
frequency Range
0.5 to 1 cps
1 to 3 cps
3 to 12 cps
above 12 cps
Reliability
Maximum Excursion
RMS Excursion
1 degree 0.3 degree
0-3 degree 0.15 degree
0.1 degree 0.03 degree
Determined by local mounting conditions .
Reliability shall be considered as a design facter on an equal
basis with other design criteria such as performance, weight,
and cost, The reliability of the article shall be such that
when integrated into the system of which it is a pert, it will
perform its design function throughout its required life.
Reliability Requirement - The reliability of each telemetry
system is defined as the probability of successful operation
for 30 minutes at ground environmental conditions and successful
operation for 4.0 minutes while subjected to flight environ¬
mental conditions. A reliability of 0.990 is required for the
telemetry system ■
Identification of Product
The Information specified shall be permanently marked on the
article, using materials and/er processes that will insure
legibility during the expected life of the article and the
preproduetion tests of seetieo 4.0. Identification marking of
the article shall conform to XIL-8TO-13QA, except that spaces
for marking stock number, registration number, date of manu¬
facture, contractor order number, and weight may be left blank.
The vender's part number shall completely identify the article
in the last 12 or less digits. In accordance with MH-8TD-13QA,
the following major components and sub -c components, shall he
identified by individual part numbers: RF Amplifier, each
HF Transmitter of a particular frequency. High Voltage Power
Supply, Voltage Regulator, each sub carrier oscillator of a
particular frequency and the two component mounting structures .
Boeing Part Buhber - The Boeing specification control part
numSer" snail not bo permanently marked on the article oere
shall it be contained in any pert of the vendors part nusfear.
E>
PREPARED
BY j
TYPED BY |
1
1 ‘ 1 1
_
J
BOEING AIRPLANE COMPANY
REVISED BY j L'O n*_TE fc.-N t.Tii.’
e H , B !
r
SPECIFICATION NO.
D10- 20403
-4 —
t
/*
BAC 1174B
SPECIFICATION DOCUMENT PAGE
3.1.1. 5.1
(Cont'd)
3.1. 1.5. 2
3.1. 1.5.3
I
3.1.2
3.1. 2.1
3.1. 2.1.1
3.1. 2.1.1. 1
3.1. 2. 1.1. 2
3* 1*2. 1.1. 3
TP facilitate BAC handling, a separate and easily removable
tag or adhesive label bearing the BAC part amber shown n
the specification control drawing shall be affixed to the
article. A tag shall net be attached through a Mounting hole.
Serial Munberlug - Articles manufactured in accordance with
this specification shall bear serial numbers assigned by the
vendor. The serial numbering system is the option of the
vendor.
’4
Part Number Changes - Articles which completely satisfy the
retirements ei1 this specification shall be assigned a specific
vendor part number. Articles which do not completely satisfy
the requirements of this specification shall be differentiated
from those tint do, by a different vendor part number. In
addition, different Boeing dash numbers may be assigned to
distinguish parts not completely satisfying the requirements of
this specification. After final approval of the article by
BAC, the part number assigned by the vendor shall be positive
identification such that the article may be procured by vendor
part lumber alone without reference to thia specification.
Changes in the article, whether initiated by BAC or the vendor,
vjhich affect functional, physical, or structural interchange¬
ability sharl always be attended by a change in vendor's part
number to identify the new configuration. The drawing number
requirements of MIL-D-5028B shall govern changes in the manu¬
facturer's part number.
Detailed Requirements
System Requirements
Design Requirements - Ihe design ef the airborne FH/JW tele¬
metry system "shall be adequate to obtain the required perfor¬
mance stated in auction 3«1«2«1*2 and the reliability require¬
ments as stated in paragraph 3.1.1.U.1, and shall take into
consideration possible degradation of performance due to oro-
riuction variations, environmental conditions and aging.
Component Interdependence - As a design objective, the design
of the various units shall be such that failures will be con¬
tained in the faulty unit and will not cause damage in other
units or prevent operation of un-related units, i.e. loos of
a power supply should not damage the transmitter, or failure
of an SCO should not affect operation of the ether 300 'a.
System Input Signals - The individual channel input voltages
and input im .edances are listed In Table I of this specification.]
Power Souroe - The telemetry system shall operate from a
28 l 2 volt DC power system including a maximum ripple of
1.0 volt peak-to -peak. The maximum current shall not exceed
4.25 amperes under all operating conditions except for 2:1 and
5:1 VSWh Load conditions where a maximum current of 4.5 amperes
is allowable.
PREPARED
BY
TYPED BY
BOEING AIRPLANE COMPANY
REVISED fiv
a ou
AH
I-
PCN DATE |OCN LTR,
6- 17-Sf
-4
3-19- &o
3-13-Wl
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SPECIFICATION NO.
D10-20403
PAGE \\
E
H
SAC I >74 B
SPECIFICATION DOCUMENT PACE
3.1.2.1.1.U Adjustments - Ihe system shall operate within the telerences
specified herein during the entire operational life of the
equipment while being subjected to the eaefere mental conditions
specified without adjustment or tuning. Any adjustment
oontrols utilised by the vendor shall be positively locked
and sealed prior to delivery. Such adjustments with the
exception of the RF tuning. control, ahall not be accessible
without diaasseably of the plug-in components. The RF tuning
control shall be acceaeible for adjustment after assembly of
the unit; however, the control oust be positively sealed prior
to delivery. Signal inputs and input voltage controls such ae
switches or relays shall not be utilized.
3. 1.2. 1.1. 5 fransieat Potentials - The design shell be such that the
equipment will not be dam god when subjected to transient
potentials of 26 t 12 volte for a maximum duration of 25
aillieaeonds at a repetition rate net greater than one
pulse per hour.
3.1.2. 1.1. 6 Overvoltage and Undervoltage Protection - The ground power
supply will be autenatically shut down within 50 milliseconds
should the voltage exceed the limits of 1*0 and 16 v< Its.
Protection of the telemetry equipment from hi$i voltages
exceeding UO volte during the 50 millisecond period Bhould
be considered as a design objective.
CPEPARIO
“V -
BOEING AIRPLANE COMPANY
SPECIFICATION NO.
IJiVi'All BY ; l.'CN £>A T F lOC.N LTR.
o 4? 6 U j3 f7-C.Y| C D10-20U03
][ a .JH 3-i9~C 0 E
pA GF H Q
SPECIFICATION DOCUMCHT PAM
3.1. 2. 1.2
3.1.2. 1*2.1
3.1.2. 1.2.2
3.1.2.1.2.3
3. 1.2.1. 2. U
3.1. 2. 1.2. 5
3.1. 2.1.2. 6
3.1. 2. 1.2.7
3.1.2.2
Performance Requirements
The integrated system shall be operated te previde assurance
that the detailed performance requirements ef the major
components ars satisfied.
The integrated system operation shall bo performed on the bench
under controlled conditions with calibrated reoeivsr* recorder
and necessary test equipment.
The system shall be subjected to applicable voltages and fre¬
quencies which shall be recorded for comparison of input end
output transmiaeien accuracies.
The perfermancs results obtained as per paragraph 3. 1.2. 1.2.3
shall be used as a standard for comparison purposes with
system parforuanss while being subjected to flight proof
end aceeptance testing.
The Integrated system performance procedure and results shall
require BAC approval before aceeptance as a standard.
Life - The system Vital operating life shall be 500 hours.
Mainly* this life will be accumulated on the bench in normal
ambient environment and as installed in the minelle in the
launching revetment. The system will operate at all times
during the missile's flight life and will bo used to obtain
data from a time several minutes prior to first missile motion
until flight termination.
Cooling - The system may be operated for an indefinite period
on the bench at an ambient temperature ef 60*F without
external cooling. During the pre-launch period* there will
bo ground-cooling provisions whicn will maintain the
telemetry system ambient temperature at approximately 65*F.
These ground cooling provisions will bo available until
10 seconds bofere launch. During flight* there shall bo
no external cooling system or equipment for the telemetry
systems described by this specification. The telemetry
systems snail therefore be designed and protected as
necessary te perform within the limits specified in the
following paragraphs while being subjected te the tempera¬
ture-altitude environmental conditions as daaoribsd in
paragraph 3*1*1. 3. 2.1.
Suboarrlor Oscillator Requirements
PR F PAR tP
BY
BOEING AIRPLANE COMPANY
REVKCD SV DO* Mil
(2.U. U-H-59 &
ICATION NO.
DIO- 20 1*03
Imoc 12.
FAC 117.H
4
SPECIFICATION DOCUMENT PAGE
3.1.2.2.1 Design Requirements - The subcarrier oscillator center
frequencies and bandwidth* shall be per IRIQ standards as
defined by MlL-STD4*b2. The specific SOD center frequencies
are listed in Tfcble 1.
3«1.2. 2.1.1 Abbreviations - The following abbreviations are used in
this document to descrioe suocarrier oscillator requirements.
VF2
IRIO center frequency
1R1G upper band edc.e
IRIG lower band edge
IR1Q bandwidth
Subcarrier Oscillator Center Frequency
Subcarrier frequency with + 5.0 volts uC t
0.1$ (i 0.0050 volts DC) applied to the
modulator input.
Subcarrier frequency with zero volts DC ±
0.005Q Volts DC applied to the modulator input.
3.1. 2. 2.1. 2
f2-fx
Deleted.
Intelligence Subcarrier Bandwidtu
3*1. 2. 2.1.3 Frequency modulation of the subcarrier sine wave output shall
be proportional to the input signal amplitude with decreasing
frequency caused by an increasing positive signal.
3.1.2. 2.2 Performance Requirements - With power being supplied vo the
system in accordance with section 3. 1.2. 1.1. 3 and the input
signals in accordance with paragraph 3.1*2. 1.1. 2, and SCO's
■hall satisfy the following performance requirements 1
3. 1.2. 2. 2.1 The SCO's shall each include an output filter which provides
a minimum of 2u db attenuation at adjacent band edges. Voltage
limiters as required shall ~e included to protect the SCO's
from damage when up to b times the rated positive input voltage
is appxied.
Pi-lt’AtJf 0
BOEING AIRPLANE COMPANY
M •* . : M.N 1ATC jDCN LTH.'
SPECIFICATION Nv
C i D10-20L03
: -
jp*GE
SPECIFICATION DOCUMENT PAGE
3.1. 2.2. 2. 2
3.1. 2.2. 2.3
3.1. 2.2. 2.1*
3.1.2. 2.2.5
3. 1.2. 2. 2. 6
3.1. 2. 2. 2.7
3.1. 2.2. 2. 8
3. 1.2. 2. 2.9
PREPARtn
BY
TYPEO BY
Deleted
Modulation Sensitivity - A 0 or +5 volt signal into each SCO
shall modulate the SCO at least 90$ but not more than 92$
of 1R1G full scale deviation.
Frequency Response - Die frequency response of each SCO
shall be flat within t 2.5$ (0.25 db) for a modulation
index of 5 or greater.
Deviation Linearity - Die deviation linearity of each SCO
shall be within 1$ ( of bandwidth) of the best straight line
(least squared method).
Stability - The stability of each SCO shall be such that
with the modulation sensitivity as specified in paragraph
3«1.2. 2. 2. 3, the operating environment in accordance with
section 3*1. 1*3.2 and the voltage never exceeding 0 to + 5
volta, it snail be impossible to deviate the SCO outside the
1RIQ bandwidth during the system operating life. Zero drift
versus temperature shall be less tiian ± 2$ of bandwidth and
sensitivity change versus temperature shall be less than
t 1$ of bandwidth (32*F to 150* F)
When any SCO is deviated from fg to f-^ by a corresponding
input voltage (at any frequency^from zero to the highest
allowable input frequency for that SCO nominal frequency).
the output voltage of the SCO over the band of fg-
not vary by more chan a total of 25$.
f, shall
Variations of system input voltage from 26 to 30 volts shall
not produce an output frequency chan, e exceeding ± 1$ of
f1"f2*
The distortion products that lie within the frequency band
of any other SCO intelligence band shall be less than 1$ of
the rated output of the SCO in that band. The input of both
eubcarrier oecillators shall be grounded only when this
test is performed.
i \ 1 -f-.i tiV ,M N DA n p- N l. T
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: IS-I7-591 C ; D10-20L03
BOEING AIRPLANE COMPANY
1 —
I
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B At: 11 74 B
SPECIFICATION DOCUMENT PAGE
V»
X
>1
3.1.2.2.2.10
Each SOD shall Mat linearity anf frequency stability require¬
ments over a range of source impedance from 0 to 10,000 ohms.
3.1.2.2.2.11
Feed Through - The input information signal frequency compo¬
nents appearing at the output of the SCO shall be at least
I4O db below the sub-carrier oscillator output signal.
3.1. 2.3
Mixer Requirements
The mixer circuitry shall contain passive elements only, and
ahall perform its function by means of a simple resistor Mt*
work. The network Bhall feature a common mixing resistor
being fed by the oubcarrier oscillator signals thru a scries
of resistors.
3.1. 2. h
D.C. Regulator Requirements
3.1.2.U.1
Design Requirements -
3.1. 2. lj. 1.1
Primary Power - Primary power available for the DC regulator
unit will be as specified in paragraph 3.1.2. 1.1. 3.
3.1.2.14*1.2
Feedback Sipple - The regulator unit shall contain adequate
filtering at its input terminals to eliminate any feedback
ripple greater than 1.00£ to the primary power source.
3.1.2.U.2
Performance Be quire meats - With power eupplied in accordance
with paragraph 3.1. 2.1.1. 3 the dc regulator shall supply the
necessary voltages with proper regulation for satisfactory
performance of the low voltage circuits. Should a short cir¬
cuit occur across the power terminals within an SCO, the effects
of the short circuit shall not be reflected at the output
terminals feeding the other SCO's. The use of fuses or circuit
breakers to provide this protection i* prohibited.
3.1. 2.5
High Voltage Power 9upply Requirements
3. 1.2. 5.1
Design Requirements -
PREPARED
_ BY
TYPED BY
— - - -
1 f] | 1 1 SPf.CIFICAI|ON NO.
, .1 Rf .ISU> 1 V 1 DCN r*ATC jlK.N LTR.J
MKS \,0/c/s 2' 0 | DIO-20I4O3
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BOEING AIRPLANE COMPANY jj i 15
9AC 11 74 H
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3.1. 2. 5.1.1
3*1.2. 5.1. 2
3. 1.2. 3*2
3*1. 2.6
3*1.2. 6* 1
3* 1*2. 6*1. X
SPECIFICATION OOCUMENT PAGE
Primary Power - Primary power available for this unit will be as
specified in paragraph 3*1*2. 1.1. 3*
Feedback Ripple - The unit shall contain adequate filtering at its
input terminals to eliminate any feedback ripple rcater than
1.00$ to the primary power source. The primary power source
impedance, including cabling to tne unit sha.il e a minimum of 1.1
ohms.
Performance Requirements - With power supplied in accordance with
paragraph j. 1.2. 1.1. 3 '{lie high volta, e power supply siaul supply
all power necessary for satisfactory performance of the RF Section
The high voltage power supply shall provide protection against
the effects of accidental output shorts without the use of fuses
or circuit breakers.
RF Section Requirements
Design Requirements - The RF Section transmitter shall be
crystal stabilized.
Dele tad.
C
Center Frequency • The center frequency of the RF section shall be
in the 223 to 26u megacycles bunu.
3. 1.2. 6. 1.3 Modulation - Modulation snail be. true FM and shall be linear to
1% of the best straight line (least squares actnoo) over the
transmitter ueviation.
3*1.2. 6. 2
3.1.2.A.2.1
3. 1.2. 6,2. 2
3. 1.2. 6.2. 3
Performance Requirements - With power supplied to the system in
accordance wifn 'sec tion j. i .2.5.2 and the input signals in
accoruance with parujpruph 3.X.2.6.2.U, the RF section shall
satisfy the following performance requirements!
VSWR - Over the frequency range specif led in para raph 3.1. 2.6, 1.2
the RF section shall work into a load whose impedance lies on or
within a VSWR circle of 2.0 on a Steith Chart normalized to 50 ohms
C
Pbwer Output - The power output of the RF section shall be a
minimum of 13 watts, and shaxl not exceed 17 watts.
Linearity - The power output shall be constant within £ 0.5 db
over the maximum transmitter deviation.
C
3.1.2.6.2.U Spurious Radiation * With the exception of the allocated missile
receiver passbands, all spurious antenna conducted signals shall
be at least 60 ab down from the carrier level. Spurious antenna
conducted signals in the allocated receiver passbands shall be at
least 102 db down from the carrier level; the receiver passbands
are as follows! ItOS-ltfO me; h>9 - 5*1 Kmc.
3, 1.2. 6. 2. 5 Distortion- The RF section shall not distort the subcarrier
oacillator voltages by more than 1%. This means that not more
IR f» f PARED T
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D10-20U03
3GEING AIRPLANE COMPANY
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SPECIFICATION DOCUMENT PAGE
3. 1.2. 6.2. 5 (Cont'd)
than 1$ additional noisa shall be measured relative to the
amplitude of the output voltage of the SCO that normally
occupies that band. This measurement must be made with all
SC0*s operating and inputs grounded.
3.1. 2. 6. 2. 6 Stability - The carrier frequency shall be stable to within
t 0.01% (including the center frequency tolerance of paragraph
3.1. 2. 6. 2. 7) under all environmental operating conditions.
3.1. 2. 6.2. 7
3.1. 2. 6.2. 8
i
3.1. 2.6. 2 .9
3.1.2.6.2.10
3.1.2.6.2.11
3.2
Center Frequency - The center frequency shall be within ± 0.005$
of the frequency specified. The center frequency is designated C
in BAC letter to United Electrodynamics, Inc., reference 2-UUU6-
8-2L6 dated July 30, 1?5 ?• (Die center frequency is defined to H
be the frequency of the crystal excited oscillator section of
the transmitter).
Transmitter Deviation - Ihe output voltage of each subcarrier
oscillator at band center after mixing shall be as required to
deviate the transmitter within the following limits:
C
SCO
10.5 kc
+
i+ ±
1 kc
1U.5 kc
±
6 ±
1 kc
22 kc
+
11 ±
1 kc
UO kc
+
27 t
3 kc
70 kc
±
6k ±
7 kc
±~
Tcnr
l3 kc
No more than 10$ peak to peak amplitude modulation of any sub¬
carrier voltage may ue caused by the RF section, in addition
to amplitude modulation due to the SCO itself. This shall be
measured by observing the subcarrier signal at the output of
an FM receiver (Mems-Clarke lliul-A or equivalent) when the RF
section is modulated by a single SCO whose output voltage is
adjusted in accordance with paragraph 3.1*2. 6. 2. 8 and whose
frequency is deviated between F^ and F2. Amplitude modulation
caused in the receiver may be deducted.
Loss of Excitation shall not result in power amplifier tube
failure.
The BF Section shall meet the requirements of section 3*1. 2. 6 ,
during system input voltage variations between 26 to 30 volts dc.
DESIGN REQUIREMENTS FOR 10-20U03-1, -and -3.-11
The requirements set forth herein describe an airborne FJ(/FM
telemetry system.
L
N
PREPARED
BY
REVISED BY
DCN DATE
DCN LTR.
SPECIFICATION NO.
D10-20U03
TYPEO BY
— *r
2-za*f*
L.
L.
4-30
N
BOEING AIRPLANE COMPANY
t.
PACE \"7'
4
SPECIFICATION DOCUMENT PAGE
3.2.1
All design requirements for FM/FM telemetry system 10-201*03
as specified in section 3*1 are applicable, with the exception
of the transmitter center frequency which is specified in
Boeing letter to United Electrodynamics reference 2-4446-8-216
dated July 30, 1959. (Confidential)
I
- -
V.
PREPARED
er
TYPED HY
_ ■[ RE VISE D ; Di > l'jA T f. DCN l:
' oYYj t~n sf'~d
Sf'E CIF'IC AT I' N rjri.
BOEING AIRPLANE COMPANY
AN
■no h
Dio-20403
17»
C
H
SAC 1 174 B
SPECIFICATION DOCUMENT PAGE
3.3.
DESIGN REQUIREMENTS FOR 10-20403-10
The requirements set forth herein describe an airborne F 10V
telemetry system.
*
3.3.1
General Reauirements
3.3.1.1
Fhysioal Requirements
The physical requirements for this system are the same as
stated in section 3. 1.1.1 except for paragraphs 3. 1.1. 1.6
and 3* 1.1. 1.9. 4*
3.3.1.1.1
Interchangeability - Articles and/or components manufactured
in acoordanoe with this specification shall be functionally,
physically and structurally interchangeable. See paragraph
3. 3. 1.5.1 for cart number changes for non-interohawreabla
articles. •
3. 3.1.2
Electrical Requirements
The electrioal requirements for this system shall be the same
as stated in section 3«1>1*2.
(
3.3.1.3
Environmental Conditions
The environmental conditions are to conform to the requirements
of section 3.1.1. 3 except for paragraph 3.1.1. 3.2^2.
3.3.1.3.1
Vibration - Cqmplex vibration inoluding sinusoids as represented
by the vibration envelope of Figure 5 and random noise as
represented by the vibration envelope of Figure 6 shall apply
to 10-20403-8 SCO package.
3.3.1. 3.2
Vibration - The random noise vibration envelope of Figure 11
and the sinusoidal vibration envelope of Figure 12 shall apply
to the EF Section 10-20403-12.
3.3.1.4
Reliability
The reliability requirements of section 3. 1.1.4 shall apply.
3.3.1.5
Identification of Product
The identification of produot requirements of section 3. 1.1. 5
shall apply except for paragraph 3.1.1. 5. 3*
PREPARED
BY
REVISED BY
DC* DATE
DCN LTR.
SPECIFICATION NO.
D10-20403
TYPEO BY
N
| BOEING AIRPLANE COMPANY
• ‘
PACE 17b
SPECIFICATION DOCUMENT PACE
3« 3*1. 5.1 Part Number Changes - Articles which completely satisfy the
requirements of this specification shall he assigned a specific
vendor part number. Articles which do not completely satisfy
the requirements of this specification shall be differentiated
from those that do, by a different vendor part number. In
addition, different Boeing dash numbers may be assigned to
distinguish parts not completely satisfying the requirements of
this specification. After final approval of the article by
The Boeing Company, the part number assigned by the vendor
shall be positive identification such that the article may be
procured by vendor part number alone without reference to this
specification. Changes in the article, whether initiated by
The Boeing Company or the vendor, which affect functional,
physical, or structural interchangeability shall always be
attended by a ohdhge in vendor1 3 part number to identify the
new configuration. New drawings, requiring new drawing
numbers, shall be drawn in accordance with MIL-D-70327.
3-3.2
Detailed Requirements
All of the Detailed Requirements of section 3.1.2 shall apply.
DESIGN REQUIREMENTS FOR 10-20403-11
The requirements set forth herein describe an airborne FM/FM
telemetry system.
3.4.1
All design requirements for FM/FM telemetry system 10-20403-10,
as specified in section 3*3 axe applicable, with the exception
of the transmitter center frequency which is specified in
Booing letter to United Electrolynamios reference 2-4446-8-216,
dated July 30, 1959*
PREPARED
OY
REVISED BY I DCN DATE PCN LTR.I
SPECIFICATION NO.
D10-20403
BOEING AIRPLANE COMPANY
I
SPECIFICATION DOCUMENT PAGE
►
UoO
iwl
U.L.1
lul.1.1
lul.1.2
lwl.1.3
amuraECE PB07I33DHB
CLASSIFICATION OF TB3T8
The inspection and tart lag of tho equipment procured
under this apeeifieation dull bo classified as
indicated la paragraphs U.1.1, U.1.2, and U.1.3.
ACCEPTANCE (VENDOR FUNCTIONAL) TESTS
Aooeptanee testa are those tests vhioh shall be aooonpliahod
by the Vender on eqnlfsat submitted for aeosptanse under
oontrast. Aooeptanoe testing is generally divided between
"Individual Testa" and "Sampling Tests". "Oonpeneni
Tests" nay also be included as a type of an Aooeptanoe Test.
SEVERITY OF TESTS - Aooeptanoe tests shall not have
detrimental effects on the operational life of the
equipment but shall assure that each production article
is the equal of that whioh successfully passed the pre-
production tests.
; -m
TEST PHOCEHJHS The Vendor shall provide the Buyer with
a detailed description, in dooms nt form, of the proposed
aeoeptanoe test prooedure and equipment sufficiently early
for BAC potent and approval prior to the scheduled start
of aooeptanoe testing. Tha approval of the prooedure and
equipment by BAC does not relieve the Vendor of the
responsibility to assure that the teste adequately prove
ooaplianoe with the specification requirements. Changes
to the prooedure may be made only after BAC approval.
RECORDS - Adequate inape etion and test reoords of all
amopptanoe testing shall be kept by the Vendor eo that
failure and reliability studies may be conducted utilis¬
ing these reoords as a reference. A reproducible form
as shown in Figure 2 and, supplied by the Bqyar or the
Vendor using the BAC format, shall be completed for each
article tested. The reproductible shall be submitted te
the Btqrer and a oopy included with each article tested.
r
MVtUOtr
DCH tATI
OCN ITI.
D10-20lg)3
ttmo it
BOEING AIRPLANE COMPANY iutturw*.
Mil U
BA<W-3977-(1wO)
t-roM
SPECIFICATION DOCUMENT PAGE
U.1.2
U. 1.2.1
U.1.2. 2
U.l.2.3
U.1.2.U
It. 1.2.5
Preproductlon (flight Proof) Teats
Flight proofing tests are intended to evaluate reliability and
performance accuracy of developmental equipment prior to flight
testing of similar equipment.
Test Procedure
The Vendor shall provide the Buyer with a description of
the proposed test procedure and equipment sufficiently
early for BAC comment and approval prior to the scheduled
start of flight proof testing* The approval of the
procedure and equipment by BAC does not relieve the Vendor
of the responsibility to assure that the tests, when per*
formed, adequately prove compliance with all requirements
of the specification*
Changes Necessary to Complete Tests
All changes made necessary by the failure of a unit to pass
the complete flight proof test shall be incorporated at the
Vendor's place of business on all future units shipped to
BAC.
Proof Required of Tests
The Vendor shall test the unit in such a manner as to conclu¬
sively prove to the extent specified under paragraph U.5
that the requirements of the applicable paragraph of
Section 3*0 have been met.
Records
Adequate records of all flight proof testing shall be kept
by the Vendor to support failure and reliability studies
and results presented in the test reports of paragraph
6.U.U*2*
Discrepanc ies
The required procedures when discrepancies occur during
testing are described in paragraph 6.U*5*
rr
imswiY
BCN OAT*
OCN IT*
TTKO n
re. a*.
fc-17-Sl
&
D1U-20U03
•OEING AIRPLANE COMPANY
MATTU H WM.
*ASI IS
E>i
BAC 117*1
>-7M0
SPECIFICATION DOCUMENT PAGE
U.1.3
U.2
4-2.1
J».3
U.3.1
4. 3*1.1
BAG Receiving Inspection and Functional teat;
Receiving inspection and functional testa are ptrformed
by tbs buyer to insure that articles are satisfactory
before their incorporation in an end product.
NUTS;
The BAC inspection and functional test requirements
included in this specification are primarily intended for
the use of BAG personnel. Although they may be
useful to the Vendor as a guide, they shall not be
considered as establishing the quality limits on design
requirements of the article.
TEST CONDITIONS
Atmospheric Conditions
Unless otnerwise specified, all tests required by this
specification snail be made at an atmospheric pressure of 2ti
to 32 inches of mercury, a temperature of 75* F plus or
minus 1Q*F, and a relative humidity of tiO% or less. Where
tests are made with atmospheric pressure or temperature sub¬
stantially different from the above values, proper allowance
shall be made for any cnange in Instrument readings.
ACCEPTANCE TEST REQUIREMENTS AND PROCEDURES
NOTE;
Reference should be made to paragraph U.1,1 for general
deacrlption of acceptance tests.
Individual Tests for 10-2uU03.»lf «dtG and -11
The following tests shall be performed by the vendor on each
system snipped and shall be applied to each system as whole.
Examination of Product
The system snail be examined for satisfactory compliance
with the weight, dimensional, nameplate, finish and
workmanship requirements.
PREPARED
IT
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KN MTI
1
KN IT*
lUCTOSTOBTSBr —
vine ®y
AH
9-7-60
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D10-20U03
E£l>
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L
BOEING AIRPLANE COMPANY mattu m wn.
NAM 20
«>C 117.®
>-noo
V
I
4 ~
SPECIFICATION DOCUMENT PAGE
i
4.3.1.2
4.3. 1.3
4.3.2
4*4
4.4.1
4.4.2
4.5
Performance
The equipment shall be operated for at least ten operating
cycles, under room conditions and self imposed environment.
An operating cycle shall consist of activating and varying
each information channel through its complete operating range.
The equipment shall operate without failure or malfunction
throughout this test. The test shall include at least three
start-ups.
Vibration
With the system operating in accordance with section 3. 1.2. 1.2
the system shall be vibrated in accordance with Figure 7 in
each of three coordinate directions. The duration of vibra¬
tion shall be one sweep at 1 octave/minute (approximately 8
minutes in each direction) . The vibration shall be applied
and measured at the attachment points of the equipment to
structure. The system shall perform without failure or mal¬
function. Upon completion of the above vibration tests, the
system shall be subjected to one cycle of operation a8 des¬
cribed in paragraph 4. 3. 1.2, and the system operation within
the performance limits defined, shall be verified.
Sampling Testa for 10-20403, -1. -2.-3* -10 and -11
Not applicable.
COMPONENT TESTS
Component Testing for 10-20401 '.and -10 j L
Mot applicable. j
Component Testing for 10-20403 -L. -fr and -11 ' L.
Not applicable. \
!
PREPRDDUCTION TEST REQUIREMENTS AND PROCEDURES j
NOTE: |
Reference should be made to paragraph 4.1.2 for* general i
description of preproduction tests. i
PREPARED
b r
" " T
i
REVISED E i
1 * 1
| DC.N . :
^ lp!'Liri'> rr)u r
TYPED BY
1
ft. u-
fc-17-SI
B 1 DIO-20403
. ..
AH
e-7-"&o
G
i 30EING AIRPLANE COMPANY
t ££>
2-22
- 21 _
BA C H 74 B
I
SPECIFICATION DOCUMENT PACE
4a
4.5.1
4. 5.1.1
4. 5. 1.2
4. 5-1.3
Prep reduction (Flight Proof) Teats for 10-2040}
The following taste shall ba applied to tha system as a whole
and with tha exception of the teats described by paragraph 4.5.1 .7,
are applicable to one set of equipment. The sovirensmntal tests
say ba performed in any manner except that tha mechanical tests
(vibration, acceleration and Block) shall precede the climatic
tests (temperature, altitude and humidity).
e
Examination of Product
Oha procedures of paragraph 4. 3. 1.1 are applicable.
Vibration
While operating in accordance with section 3. 1.2. 1.2, the
system shall be vibrated in each of three coordinate axes in |
accordance with the vibration envelopes of Figures 5 and 6. 1 B
The sinusoidal and random vibrations shall be applied aimul- i
taneously and measured at the /points of mounting of the equip*
ment to structure. Duration of applied vibration shall be
15 minutes in each axis. During the above vibration, the
equipment shall operate without failure or malfunction and
within performance limits specified in section 3. 1.2. 1.2.
Acceleration
While energized, the equipment shall be centrifuged for a
minimum of 3 minutes in each direction along 3 mutually
coordinate axes at an acceleration of 15g< The performance
of section 3«1 .2.1.2 shall be conducted as practicable.
Ho failure, malfunction or performance outside the limits
specified in section 3 >1.2.1 .2 shall occur. Upon completion
of each centrifuge test, the equipment shall meet the per¬
formance limits specified in section 3. 1.2. 1.2.
>
!
!
PREPARED
BY
1
_ I
t
REVISED BY i DCN DA Tl t>CN lIk.
1 SPECIFICATION MO.
TYPED BY
'"I
e. h. fc-io-s? b
D10-20403
l
1
1 -
BOEING AIRPLANE COMPANY
1
p*oi 2. 2. J
BAC 1174B
SPECIFICATION DOCUMENT PAGE
f 1*.5»1.U
U.5.1.U.1
l*.5.l.l*.2
Ibmperature-Altitude
With the equipment non-operative, the systen shall be subjected!
to a test chamber pressure corresponding to an altitude of
£0,000 feet simultaneous!/ with a tarapurature of -00* F for 0
heur a. The chamber pressure shall then be restored to ambient,
and one temperature raised to 32* F and maintained at 32* F i
until the temperature of the equipment stabilizes* While j
operating, the equipment a.utll Uion be thermally irrsdiated
by an enclosure simulating compartment walls, me enclosure |
snail be as follows: ;
(a) 'ihe walls and top of the test chamber snail have an
amiss ivity of .25 - .05*
(b) All sides of the test article shall be located no further
than 2.5 inches from tne corresponding radiating test ;
chamber walla.
(c) Ihe article snail be eitner suspended or thermally insulated
at tne attachment points of tho test chamber to prevent ths !
article from utilizing tne test chamber for a heat sink. j
(d) Provisions snail be made to neat four walls of tne test
chamber to 700* F ± £0*F within one minute from stabilized '
ambient and to maintain the ?0o° F ± £0*F wall ur.ip.rature i
for tnree minutes. |
|
During the first minute of this portion of the test, the
pressure stall be reduced from sea level to 90,000 feet i
altitude. At the same time, the wail temperature of the
enclosure shall be increased to 700 'Ft £0*F. me 90,000 feet
altitude and tho 700*F wall temperature condition shall be ,
maintained for tnree minutos. Jha equipment snail perform
during and after the test with no failure, malfunction or
out-of-tolerance performance degradation. |
Altitude - While operating under a self-imposed ambient tempera-; g>
ture, the system snail be subjected to a reduction in test j
ohamber pressure from that of sea level to 200,000 feet. The j
reduction in pressure shall occur within 1.5 minutes and the j
200,000 feet altitude condition shall be maintained for 2.5 ■
minutes. The equipment shall perform with no failure, malfunc- :
tion or out-of-tolerance performance degradation.
U.5.1.5
PREPARED
BY
TYPED f!Y
Humidity
While non-oporative, the system stall be subjected to 100 cycles
of temperature variation at a relative humidity of 95$. Bach
cycles stall consist of a test chamber temperature of 120*F(U9*C)
for one nour, followed b., a test chamber temperature of 110* F
(1*3*0) for one hou’. Upon completion of the 100 cycles the
chamber temperature shall than belowered to 60*F (27*C) within
one hour with the relative humidity maintained at 95$. The !
system stall then be operated, under these conditions in accor¬
dance with section 3. 1.2. 1.2. Ihe system shall perform without j
failure or malfunction and within the limits specified in I
section 3*1. 2.1. 2. _ _ j
i REVISED 3<_ . PCI- PA r i
z.vl c.-n-s-'j
'J-t '*IFk>Ti,,)N TKV
Dlc-20h03
BOEING AIRPLANE COMPANY
r
23
0AC H74B
SPECIFICATION DOCUMENT PAGE
4. 5.1.6
Interference
With the exception of paragraph 4.3 .4.4 of STL Document CM 07-59-2617A,
the procedures and tests of GM 07-59-261 7A are applicable. The testa
required by section 4.3.1 of GM 07-59-2617A are applicable to all power
and signal leads (properly loaded).
H
I
|
I
i
1 _ _ 1
PREPARED
BY
! - ( i *■ . 'A 1 1 O'. U |
REVISED BY : TCN DA T f !D' N t ff?.; j
TYPED BY
_ AH '3-IB-4I H i D10-20403 !
~~ 1 ' !
DOPING AIRPLANE COMPANY j
pa .• 23a i
SPECIFICATION DOCUMENT PAGE
4. 5. 1.7 Reliability Tests
The reliability test shall consist of operation of 10-20403
systems, while being subjected to simulated ground environment
and simulated flight environment cycles. Each cycle shall con¬
sist of 30 minutes operation at sea level pressure and 65°F
ambient temperature, followed immediately by four minutes of
operation under simulated flight environment. Plight vibration
conditions shall be simulated by simultaneous sinusoidal and
random vibration, from 5 cycles to 2000 cycles at levels indi- !
cated by Figures 9 and 10. Sinusoidal sweep from 5 cycles to j
2000 cycles shall be completed every fifth test cycle. Simu¬
lated flight environment shall be accomplished by vibrating j
the systems while simultaneously exposing the systems to temp- j
erature-altitude conditions. The temperature-altitude Simula- <
tion shall be as follows: The systems shall be installed in
an enclosure, simulating missile compartment walls, (internal i
surface emissivity “ 0.25), with the outer surface of the I
units comprising the systems no more than 2.5 inches from one j
radiating surface of the enclosure. During the first minute of j
simulated flight conditions, the pressure shall be reduced from j
sea level to 90,000 feet altitude. At the same time the simu¬
lated compartment wall temperature shall be increased to 700°F.
The 90,000 feet altitude and 700°F wall temperature conditions ■
shall be maintained for three minutes.
Demonstration of satisfactory reliability will be completed when
one system has operated for 75 cycles with no discrepancy. J
Between cycles the equipment shall be turned off and cooled to
initial conditions. The vibration axes shall be rotated to one
of the mutually perpendicular axes every 25 cycles.
Scheduled maintenance or adjustments may be performed between
cycles.
1 - - - - -
-
f
l
TYPED f|Y
acrf " 4 v D10-204°3
1
1 1 . . r ~ • 1
h
BOEING AIRPLANE COMPANY
- - li - . . p* ■■ 24
8*1. 1 1 7« 8
I
I
I
I
SPECIFICATION DOCUMENT PAGE
— i B>
I ^
4. 5. 1.8
4.5.1.9
4.5.2
4.5:3
Other Environmental Tests
In lieu of the environmental tests specified below, vendor
certification that all materials, processes, components and
systems can withstand the environmental stresses of these
tests, will be acceptable. Components, materials, ..processes
and systems which cannot be certified by the Vendor shall be
subjected to the following environmental. tests per MIL-E-005272B.
!a) Sand and Dust (Procedure i) . v
b) Salt Spray (Procedure i)
c; Fungus (Procedure i)
»
Shock
While non-operative, the equipment shall be subjected to two
shock machine shocks in each direction of each axis in which
the equipment will be subject to shock inputs from shipment
and handling. The shock machine shall produce a shock spectrum
within a minus 10 percent to a plus 50 percent of the spectrum
shown in Figure 8 . Upon completion of the tests, the equipment
shall be operated and its performance noted. The equipment
shall show no failure, malfunction, or out-of-tolerance perform¬
ance.
Preproduction (Flight Proof) Tests for 10-20 403-l> & ~3 •
Demonstration of satisfactory compliance by the 10-20403 system
with the flight proof tests of section 4*5.1 will be adequate
flight proof evidence for the -01, -2,; andr-3i systems.
DELETED
G
I &
\u
v
PREPARED
BY
I REVISED BY
DCN DATE
DCN LTR.
SPECIFICATION NO.
TYPEO BY
L
D10-20403
R,L,l.
N
BOEING AIRPLANE COMPANY
PACE 24^
SPECIFICATION DOCUMENT PAGE
4.5.3
4.5. 3.1
4. 5. 3*2
4.5. 3* 3
Preproduction (Flight Proof') Test for 10-20403-10 & -11
Paragraphs 4.5.1, applies with exception of paragraphs 4. 5*1*2
and 4* 5* 1*7*
Vibration
\7hile operating in accordance with section 3*1*2. 1.1* the
-12 HP Section shall be vibrated in each of three coordinate
axes in accordance with the vibration envelopes of Figures
11 and 12. The sinusoidal and random noise vibration shall
be applied simultaneously and measured at the points of
mounting of the Equipment to the structure. Duration of
applied vibration shall be one sweep at l/2 ootave per minute
(about 17 minutes in each coordinate axes) . During the
above vibration, the equipment shall operate without failure
or malfunction and within the performance limits specified
in section 3*1*2. 1.2.
\
Vibration
Y/hile operating in accordance with section 3*1*2. 1.2, the
-8 SCO Section shall be vibrated in each of three coordinate
axes in accordance with the vibration envelopes of Figures 5
and 6. The sinusoidal and random vibrations Bhall be applied
simultaneously and measured at the points of mounting of the
equipment to structure. Duration of applied vibration 3hall be
15 minutes in each axis. During. the above vibration, the
equipment shall operate without failure or malfunction and
within performance limits specified in section 3.1. 2. 1.2.
PREPARED
BY
TYPED BY
REVISED BY
R,L.k
DCN DATE DCN LTR.
4-30*13 N
SPECIFICATION NO.
DIO-20403
PACE 24b _
BOEING AIRPLANE COMPANY
tPECtflCATtON DOCUMENT PA6E
U.6
BAG RECEIVING INSPECTION AND FUNCTIONAL TESTS
MOTEi
Referenoe should be made to paragraph U.1.3 for
general description of BAC testing.
U.6.1
RECEIVING INSPECTION
The Quality Control Department will inspect all artiolee
received for specification conformance aa indicated below.
U.6. 1,1
PACKAGING AND PACKAGE IDENTIFICATION - For oonpUanoo
with Section 5.0.
U. 6.1.2
IDENTIFICATION MARKING - For compliance with applicable
paragraph of Section 3.0.
U. 6.1.3
CONSTRUCTION - Compliance with the requirement! of the
specifioation regarding outline and mounting provisions
and obvious defects or damage.
U.6.1.U
WORKMANSHIP - General quality of workmanship as required
by Section 3.0.
U. 6.1.5
GENERAL TESTING - BAC reserves the right to teat the
artidee in accordance with any of the requirements of
this specification. Inspection may be conducted by either
of the following methods with the ri^it reserved to inter¬
change methods (a) and (b) as warranted by the percentage
of failures.
(a) Individual (lOOf) Inspection.
(b ) Sampling Inspection.
U. 6.1.6
REJECTED ARTICLES OR LOTS - Articles uni/ or lots not
accepted by BAC Inspection may be resubmitted for oomplete
inspection after the Vendor has given the artiolee a
remedial treatment which will satisfy BAC Inspection
that artiolee meet the requirements of this specification.
Before resubmission, full particulars concerning previous
rejections and the action taken to oorreet original
defeats shall be furnished BAC Inspection. Reworked
artiolee and/or lots shall be submitted for acceptance
separately from newly produced items.
PREPARED
•t
itvitte ST
OCN DATI
OCN IT*
— IfKITCirasrHB’ -
D10-20U03
rr.so IY
BOEING AIRPLANE COMPANY mattu k wn.
PASS ^
BAC-X-3977-(U.6)
a-rooo
SPECIFICATION DOCUMENT PAGE
4.6.2 ACCEPTANCE FUNCTIONAL TESTS
4. 6.2.1 Functional test of the 10-20403. -1> -2, -3, -10, and -11
FM/FM Telemetry Systems shall be in accordance with D2 -4862-1.
4. 6. 2. 2 Functional tests of the -4, -6, -7, -9, -12, and -13 EF
Packages shall be in accordance with D2 -4862-1, paragraphs
6.3.2, 6.4.2, 6.4.3, 6.3, 6.6, 6.7, 6.8, 6.10, and 6.12.
4. 6.2. 3 Functional tests of the -5 and -8 VCO Packages shall be in
accordance with D2-4862-1, paragraphs 6. 3.1, 6.4.2, 6.4.3,
6.9, 6.10, and^.l^.
OAC 1174 B
2
SPSOnCAHON DOCUMENT PASS
rv
A*
U*7
U.7.1
U.7.2
4*7*3
QUALITY CONTROL
PRODUCTION CONTROL
The Vendor shall be responsible for the constancy of
production and shall guarantee that all production units
shall be at least the equal of the unit or units offered
for preproduotion tests. Sufficient control of all
materials, components, and sub-assemblies shall be exer¬
cised to assure that the articles, when completed, shall
be uniform and meet the requirements of the specification.
INSPECTION
The work under this specification shall at all times be
open for inspection to authorized representatives of the
Buyer and the Government. Records, facilities, supplies,
and servioes required for this inspection shall be
furnished by the Vendor. The inspectors may require
replacement of items which are defective or wlueh do not
otherwise meet specification requirements. An inspection
system acceptable to BAC and to the Government shall be
maintained by the Vendor, Records of all inspection
work by the Vendor shall be available to authorized
Buyer and Government personnel.
EVIDENCE OF ACCEPTANCE IE ST
All items that have successfully passed the acceptance test
snail be so identified 0/ the application of a test acceptance
stamp*
NUUK
•»
UV'MMr
IWMtl
KHVT*
fHBHgimig —
DKWOlgOJ
rmtn
ft.u.
L-n-sn
&
IpOflNO AIRPLANE COMPANY mattu r wm.
»*m 27
3-2
3 7000
SPECIFICATION DOCUMENT PAGE
5.1.1
5.1.2
5.1.3
PREPARATION FOR DKLT/ETg
KOTEi
Unless otherwise specified in the purchase order,
packaging, packing, and marking for shipment to
BAC shall bo in accordance with paragraphs 5*1 end
5.3, as applicable. Articles for shipment to other
than BAC shall bo in accordance with paragraphs 5*2
and 5.3. when so specified in the purchase order,
DELIVERY TO BAC
UNIT PACKAQINQ
Individual containers shall be so constructed as to
allow removal of ports for inspection purposes without
destroying the container or labels affixed thoreon. If
a paper wrapping is used for the unit, acid free paper
shall bo used. When possible, tho container shall afford
equal protection to the unit therein after the container
has boon opened, the unit remov'd, inspected, and replaced,
and tho container rosealed without tho use of special tool*.
Packaging of all units chipped to II AC shall provide suffi¬
cient protection to on cure delivery of the units to BAC
without damage and in a condition capable of mooting the
requiromcnt3 of this procurement spocif ication .
INTERMEDIATE PACKAGING
Where si7.o or other considerations result in more than
one unit boing packaged within a shipping carton, the
units shall be individually packaged within tho shipping
carton. 1hi3 requirement is mandatory in order to provide
suitable protection and positive identification, during
storage and handling after removal of tho individual units
from the major shipping carton. Any deviation from tho
above required individual packaging requirement must in
all easos bo approved by BAC prior to shipment of the parts
frexn the Vendor's factory.
SPECIAL DJSTRUCTI0I13
If tho articlo requires special attention during receiving
inspection, installation, and operation, tho Vendor shall
attach a removable instruction tag to oach articlo. If
non-obvious characteristics require an article to bo given
special handling, the Vendor shall notify BAC and also
attach a removable instruction tag to each articlo.
tt
rtn 0 rr
«vmo r» i ock wu l gcwirg.
DI0-ac*4-0^
[BOEING AIRPLANE COMPANY ICATTIE 14 WN.jj
BAC-X-3977- (5.0)
1 lt.rn
SPECIFICATION DOCUMENT PAGE
NOTKi
If the Vendor hag Packaging Team Authority, for the
itera(s) covered by this specification, preservation
and packaging shall bo in accordance therewith i
otherwise, the Vendor will be furnished detailed
preservation and packaging instructions in accord¬
ance with the Boeing Packaging Team Authority*
The above information applies to danestio shipments
whore limited and extended storage are involved and
for overseas shipments.
For domestic shipments intended for ismediate use,
sea paragraph 5« 1*
MOMID
IT
KN MTI | BCN LTD
Ql©-£0405
{BOEING AIRPLANE COMPANY
BAC-X-39
1-15-59
tWttU H WH
SPECIFICATION DOCUMENT PAGE
>
5.3 MS
5.3*1 MARKING TEXT
All containers, including individual packages and outer
cartons, shall be narked with the following information
in the order Hated i
(a) Vendor Part Number
(b) Nomenclature
(c) Quantity
(d) Buyer's Purchase Order Number
(e) Vendor's Name and AddLross
(f) Vendor's Trade Mark (Optional)
(g) Oats Packod
(h) Retest or Re inspection Date (if applicable)
(i) Dse Before (Da to) (if applicable)
(j) Serial Number (if applicable)
NOTE:
Reinspection and "use before" date markings shall
be in accordance with ANA Bulletin 405.
50*2 BAC SPECIFICATION NUMBER
The BAC specification number shall not appear on the
individual packages or on the outer shipping carton
unless specified on the purchase order.
5.3.3 SPECIAL MARKING INSTRUCTIONS
When so specified in the purchase order, units shall
have individual and intermediate packages and shipping
containers marked in accordance with MIL-STD-129 .
umu r
PCM DATS
ocMim
TVIIU It
D 10-20403
BOEING AIRPLANE COMPANY
SIATTlI M WH.
PASS
kc-x^977^(5.3)
MW
SPECIFICATION DOCUMENT PAGE
V
6.
6.1.1
6.1.2
HOTBS
INTXHDED U8S
The airborne FJt/PM telemetry systems (10-20403, -1, -2, -3, -10
and -11) described herein will be used to oolleot, prooees
and transmit data measurements euoh as vibration, temperature,
etc., of a ballistic adaeile.
The 300 hour operating life will be accumulated largely
during test and ehsokout operation on the bench and during
various stages of aiasile assembly. When operating on bench
testa the equipment be ua-inelosed and subjeot to normal
laboratory environment. When installed in the niselle
compartment, forced ventilation will be provided during pre-
1 aimoh only. The final and most oritioal operatiwr cycle
will consist of approximately 30 minutee operation at
ground environment followed by operation during approximately
3 l/2 minutes under oondltlone as deeeribed in J. 1.1. 5*2.
The equipment will not be reoovered.
The equipment must be able to survive normal handling and
shipping including air transport in un-heated, un-preasurized
aircraft. Extended storage la not anticipated.
z_
I
i
I
j
i
I
j
i
PREPARED
—
j 1 SP F CIF If ATIQN NO.
BY
1 REVISED BY
PCN OAT t bc.t LtK.!
TYPED BY
■ El U Z-Z2 oi L '
_ . ..
| 110-20403
BOEING AIRPLANE COMPANY
|PA7,F 51
live
1 7
SPECIFICATION DOCUMENT PAGE
f
6.2
6.2.1
6.2.2
6.2.3
APPROVALS AND CERTIFICATIONS
All approvals and certifications will be recorded in the
approval block of the specification drawing. Where deviations
from the specification design requirements have been granted
to the Vendor, the specification shall be either revised to
reflect the necessary deviations anu the original requirements
issued under a different specification dash number, or revised
by adding an appropriate note to the approval column on the
specification urawing indicating that deviations have been
grafted.
Design Proposal Approval
Assignment of this approval means that the Vendor's
design proposal information submitted in compliance with
D2-3W1 has been approved by the Engineering Department.
It does not indicate approval or acceptance of the Vendor's
detail dealt, n or manufactured article.
Final Approval
Assignment of tnis approval to the Vendor's article means
thati
(a) Ihe required preproduction exhibits, submitted in
accordance with 6.i|.L, nave been approved.
(b) Customer approval has been granted or was not
required.
(c) The article is approved for .installation, operation,
and delivery to Boeing's customer.
e>
i
j
I
I
j
I
Tentative Approval
Assignment of this approval to the Vendor's article j
means tnati
I
(a) The required preproduction exhibits, submitted
in accordance wutn 6.U.L, have been approved.
(b) Customer approval is required and is pending.
i
(c) The article is approved for installation and
operation. I
j
_ . . 1
PREPARED
GY
i i : brtCiPiCA riot. f-o.
1 RE 'J -if ' DCN Da 7 L t»Cn * » *-*
TYPEO BY
1
' £ *u- fc-n-S'? » D10-20U03
_
BOEING AIRPLANE COMPANY j; 31. !
SPECIFICATION DOCUMENT PAGE
(
>
NOTSt
Final approval and tentative approval are only
^type approvals" arxi do not relieve the Vendor of
the responsibility to assure that each article com¬
plies with all specification requirements*
6.2. U Flight Certification
Assignment of this certification to the Vendor's article
means that:
(a) The required preproduction exhibits iiave not
yet been approved.
(b) There are no operational limitations.
(c) The article is cleared for installation on
a limited number of missiles.
6.2.5 Limited Certification
Assignment of this certification to the Vendor's article
means that :
(a) The required preproduction exhibits have not
been approved.
( b ) There are definite operational limitations.
(c) The article is cleared for ground testing and
installation on a limited number of missiles.
IT
uvitit r
OCN DAT|
OCN LTD.
D1 0-201:03
TWO IT
BOEING AIRPLANE COMPANY hattu h wm.
PAM ^ ^
SiC U7H8
il
SPECIFICATION DOCUMENT PAGE
HiPii AdTiUiS ADD ADBIdVlAIlOhS
Abbreviations appearing in this specification coc ament
are in accordance with jhl_- STD-12 A.
6.3.1
6.3.2
6.3.3
Specification Document
The specification document which contains all tnc require¬
ments of the article except these shown on the- specification
control drawing.
Specification Contrcl Drawing
A supplemental drawin0 w.dch contains the genei: 1 c utline
ana other pnyaicul requirements- of the article and upon
widen the approval states is recorded.
toe inn Procurement Sp e c 11' ic a tien
The specification document and the supplementary specification
control drawing.
6. j.b
6.3.5
6.3.6
buyer
The Materiel Department of ti:c booing Airplane Company or its
designated represet. ta tiva.
Vendor
The manufacturer and/or manufacturer' 3 a.^ont supplying or
quoting on the specification article.
System Components
6.3.7
Any piece of equipment which constitutes a component part
of tne overall system.
Articles: Unit: Assembly: Part: System:
All refer to tho equipment defined by the procurement
specification.
PRI.AHSD
IT _
MVIW rr 1 OCN BATI I PCM IT»
BOEING AIRPLANE COMPANY ssattli wn.
:ir;ciTioN no.
Dld-2U)|03
17000
SPECIFICATION DOCUMENT PAOC
6.3.6 Booing Airplane Company
Booing Airplane Company, or a subcontracted company which
has bean granted design responsibility and responsibility
for the maintenance of procurement specifications.
6.3.9 End-Product
The overall article defined by the procurement specif ieation
including dash numbered components, if any) nowever,
if a specification covers a number of articles which, though
related, are functionally independent of each other and are
net intended for use as an integrated assembly, each of the
articles shall be considered as an end-product.
6*3.1° Reliability
For the purposes of tnis specification, reliability is
defined as the probability of succeaaful completion of
operation during the period immediately preceding flight, and
during flight.
6.3.11 Discrepancy
Any condition whore the equipment fails to operate or where
operation is out of the limits of the specification when
the equipment is subjected to the operational and environ¬
mental conditions of the specification.
6.3.12 Channel
Am electrical transmission circuit which is required to convey
the magnitude of a data measurement from a single data Bource.
6.3.13 FM/FH
Denotes frequency modulation of the subcarriers by the sources
of intelligence and frequency modulation of the RF carrier
signal by the subcarriers.
6.3.1U RF - Radio Frequency
6*3*15 1B1Q • Inter-Range Instrumentation Group
6.3.16 SCO - Subcarrier Oee ilia ter
6.3*17 VSWR • Voltage Standing Wave Ratio
PPf PAREP
BY
REVItCO ev
0O» MTC
tot tie.
IRiCIFICATION NO.
TYPE!. BY
fc.U.
fc-n-SO
&
010-201*03
BOEING AIRPLANE COMPANY
p»«i 3 S’
BAC U 74 fl
?- - 7000
SPECIFICATION DOCUMENT PAGE
6.3.18
Individual Tests
6.3.19
Acceptance tests waich are performed on uvery ite« shipped
(100 percent inspection).
6.3.20
Acceptance tests waich are performed on a lot basis
(less than 100 percent inspection).
Component ibsts
Pxeproduction tests which are performed on the individual
"black boxes" or subassemblies of a system rather tnar. on
tne complete system.
BOEING AIRPLANE COMPANY mattu h wn
MvttIO rr OCN DAT I | DCN IT«
i MiiXMPEEM
D10-2uii03
7
SPECULATION DOCUMENT PAGE
DATA REQUIREMENTS
6.U.1
Correspondence Initiated by Vendor
6.4.1. 1
Correspondence Identification
All correspondence, drawings, design information, and other
related material concerning this specification shall be
identified by this specification number. For example:
REFERENCE: 10-XXXX-X (Part number and dash number)
BOEING SPECIFICATION CONTROL PART NUMBER
6.4.1. 2
This identification may be hand-lettered on each piece of
data and need not appear on the Vendor’s original.
Addressing
6.U.1.3
All information and communications transmitted from the
Vendor to the hiyer shall be directed to the attention of
the appropriate personnel within the particular purchasing
department which nas requested proposals and/or placed
purchase orders.
(quantities required
All communications snail be furnished in the following
quantities:
(a) All correspondence (except preproduction test
data)
3 copies
6.4.2
(b) Drawin s, sketches, wiring drawings
(c) Preproduction test data
3 copies or
1 reproducible
5 copies
(d) Preproduction Discrepancy Reports and
Acceptance Test Summaries ....... 1 reproducible
Classification of Data
6.U.2.1
Government Security
Vendors shall not mark drawings and data with suci. classifica¬
tions as "Confidential" or "Secret", unless such classification
is mandatory by authority of applicable United otatee
Government security regulations*
rr
viwo rr l pcm mw l pcn an
BOEING AIRPLANE COMPANY ihtukwn
D10-2t)l»03
37 '
lit U7»l
iwoo
SPECIFICATION DOCUMENT PAGE
6.U.3
6.U.3.1
6.U.3.1.1
6.U.3.1.2
6.U.3.1.3
6.U-3.1.U
Exhibits Required in Vendor's Design Proposal
General Requirements
Part Mumbar - A specific part number snail be assigned each
article tor wuicn a design proposal is submitted. The 3 AC
specification control part number shall not bo adopted as a
Vendor's part number. ™
NOlEi
The specification control part number of the article
may be the name as the SPECIFICATION CONTROL DRAWING
number without any dash number suffix (e.g., 10-00000)}
however, the specification control part number article
may sometimes consist of tne SPECIFICATION CuiJTkOL
DRAWING number followed by a dash number (e.fa., lu-00000-2)
Exceptions or Deviations - Die Venuor shall include a list of
exceptions or deviations taken to the apeciflcation and the
reason for these exceptions.
Deleted
Qualification by Similarity - When the article described in
this specification is similar to an article previously
raaiaifactured by the Vendor ana used by BAC, and is con¬
structed of identical materials and/or components and
processes, certi'’ d test reports of such similar articles
and certification >.nat the same or improved construction
is used may be submitted with the Vendor's design proposal.
BAC reserves the ri^ht to reject all or any
part of such data anu require the testing as specified.
Acceptance of the data will depend on adequate evidence tliat
the specified article will pass the same tests as the article
covered by the reports.
Deleted
PRfPAREP ]
BY
■ — - - - 1
Rf.viStO
TYPHO 13 Y
i
L _
[
: f?.U.
1
I
1
; •
BOEING AIRPLANE COMPANY
r_ 1 ■ * r f 1 .<
i-n-59 e>
D10-20U03
38
HOC IU(8
SPECIFICATION DOCUMENT PAGE
4
t
I -
I
6.U.3* 2
6.U.3.2.1
6.U.3.2.2
6.U3. 2.3
6,1i.3. 2. It
6.U.3.2.3
- - - |
I
i
Specific Exhibits Required
The celler shall furnish to the Buyer, with hie bid submittal, j FEB
the specific exhibits required in the statement of work '!
document L2-3971.
Deleted
Deleted
Deleted
Deleted
Deleted
B
a
i
PREPARED
BY
TYPED BY
fttvi-.eo ;iv i .• i ■« ri [/■■ _
u-n-s^ &
BOEING AIRPLANE COMPANY
- f
s”f ;iF T r -j ‘/r,.
DIO-201103
3 9
BAC 1174 B
SPECIFICATION DOCUMENT PAGE
V
6.4.4
6. 4.4.1
6. 4. 4.2
DATA REQUIRED FOR TENTATIVE AND/OR FINAL APPROVAL
PREPRODUCTION ARTICLES - Ths articles which successfully
passed the preproduotion teats.
TEST REPORTS - Tost reports which are certified by the
signature of an officer or official of the Vendor’s company
or subcontracted testing laboratory, and which follows the
format of MIL-T-9107 , excopt as noted below shall be sub¬
mitted in accordance with paragraph 6.4.
(a) The Vendor shall submit to the Buyer either individual
test reports or a collective report of the results
obtained from subjecting the specified article to the
proproduction tests listed in Section 4.0. Unless the
vm&ti wtfta testing is unusually complicated, a single
collective report is preferred.
In order to expedite the approval of the article, it
is requested that intorim reports in triplicate be
submitted to the Buyer throughout the preproduction
testing, these will be used X'or an initial review
only and need not be In the final formal report fora.
(b) Test reports from Vendor's and/or their subcontractors
shall include a detailed and qualifying description of
the test procedures and a detailed summary of the teat
results. The reports shall also include a complete
description of the test machines and/or instruments
and shall include reproductions of all laboratory test
data sheets dated and identified on all equipments sub¬
mitted to tests. Graphic, tabular and
photographic presentations shall be used to completely
illustrate the way the tost was conducted and to verify
the results obtained from the tost. Those exhibits
shall be submitted to the Buyer so that he oan deter¬
mine that the article being tested doo3 meet the speci¬
fication and that the testing agencies' conclusions are
supported by adequate data.
(c) Tost reports shall clearly identify the relation of
the data to the requirement it is intended to satisfy.
(d) When revised tost report material is submitted, it shall
be so marked as to clearly distinguish it fren previously
submitted material. This provision is necessary as an
aid to librarians or other non- technical personnel who
must keep filed copies of to3t reports up to date.
PMFAftSO
•t
REVISED n
DCN DATE
DC* ITS
WC1FICA7ION NO.
TYMD |Y
DIO-S0405
BOEING AIRPLANE COMPANY
SEATTLE H WM
RASE 40
DACpX-1977- ( 6.4,4)
■4'“ -4^ J
17000
•1
SPECIFICATION DOCUMENT PAGE
I
I
6.I4.U. 2 (Cont'd) The use of revision system similar to that employed in
Boeing Procurement specification document* is encour-
ated liMotela the nature of each change is explained on
a “Revision" page, and an index of effective pages
reflects the current effectivity of eacr. page. j
(e) Beginning with the date of the initiation of actual .
flight proof testing, a complete test log must be kept
of all maintenance, calibration, modification, testing, j
design changes, etc., relative to or performed on each j
of the test parts, This log is to form a part of tha j
flight proof test reports and must be available to the I
Buyer at any time. All discrepancies occurring rauBt be I
entered together with all pertinent information concern* j
1 ing the failures. Cross references shall be made to the
Detail Discrepancy Report required by paragraph 6.U.5 |
of tills specification. j
(f ) During the test, data shall be recorded of the critical j
performance parameters of tne equipment, particularly I
those which provide indication of impending failure or
unacceptable shift of calibration. Due to the serious !
consequences of extended delays to a procurement program, ;
the Vendor snould be urged to take as muen pertinent data :
as possible over ana above the specification requirements.
Such data might assist in rapidly determining the cause of '
any impending failure and might enable analysis and
correction witn minimum delay.
j
(g) Ho tests conducted prior to the time indicated on the
Vendor' e test schedule will be allowed as evidence of
flight proof unless specifically authorized by the Buyer. 1
6*U.it*3
Deleted
i e>
6.U.U.1*
Production Drawings
f
The supplier shall furnish the data listed below. Tnis data
is necessary in order to meet contract requirements and sltall
be kept up-to-date concurrently with changes to the part or
parts.
i
: £>
PREPARED
BY
_
RfcrflSb." 6 v ( 1M> :-ATt
TYPED BY
i1 s -u. t-n-srf
- — — ii - - • 1 — -
BOEING AIRPLANE COMPANY
SPECIFICATION mo.
D10-20U03
r 41
SAC II7.B
SPECIFICATION DOCUMENT PA6E
4
< -
6.U.U.1* (Cont'd) Original delivery of the below aha 11 be made not later
than 15 days subsequent to completion of the individual
design or not later than 90 days befbre delivery of the
first article, whichever occurs first.
Forward with letter of transmittal to
Boeing Airplane Company
Seattle Division
P. 0. Box 3866
Materiel Department
Seattle 2ii> Washington
(a ) One Vandyke or autopositive (autopositive preferred)
copy of each assembly and detail drawing applicable
to the part or parts specified on the purchase order.
(1) Bach assembly and detail drawing shall be
prepared in accordance with the requirements
of the latest issue of MIL-D-502D in effect
At date of suppliers quotation. Drawing
nomenclature shall be in accordance with
MID-SZD-2U.
(2) Vandykes or autopositives shall be prepared
in accordance with Specification MIL-D-5U80.
(b) Show applicable Government contract number and
Boeing purchase order number in lAtter of
transmittal.
6.U«U*5 Acceptance Test Procedures
A description in document form of acceptance test procedures
and equipment for the approval of the Engineering Department.
MfiFARSO
•Y
MVIWt It
PCX BAT*
DCN IT*
manmss k&. —
D10-20it03
TYMD |Y
BOEINQ A
JRPLANE COMPANY sum* k wm
8 * C U7<*8
SPECIFICATION DOCUMENT PAGE
6.1i.5
6.U.5.1
6. R. 5.1.1
6.R. 5.1.2
6.U.5.2
DISCREPANCIES
DISCREPANCY PROCEDURE - Should any discrepancy occur during
the preproduction testing, the test shall be stopped. An
analysis snail be made of the cause of the discrepancy
and cnan^es proposed as necessary to correct the cifficulty.
'Die failure shall be entered in the test log of paragraph
6.R.R.2(e) together witn an analysis of the cause of fail¬
ure and the course of action planned to eliminate the
difficulty. The Vendor shall forward immediately to the
buyer the Preproduction Discrepancy Report (See paragraph
6.R.5.2J.
Design Changes Unnecessary - In the event that the Vendor
determines that no design change is necessary, full justi¬
fication for sue;, action snail be forwarded at once to tne
Buyer. The Vendor may continue the test; however, he bears
full responsibility for so doing until Booing approval is
given of the Vendor's decision. The Buyer w 11 forward
comments to the Vendor witn in 15 days after receipt of the
Preproduction discrepancy Report. If BAC disapproves tlie
Vendor's course of action, a mutually acceptable solution
must be agreed upon.
Design Changes Required - Should the Vendor elect to make
desi n civ-rges as a result of a failure, descriptive infor¬
mation must be forwarded immediately to the Buyer. This
data shall include a doscr iption of how the change was
developed, the nature of the change itself, justification
tnat the change will provide adequate design margin to
preclude recurrence of similar failures, and eviuence tnat
the change will not cause detrimental interaction w th other
portions of tne equipment under test, resulting in other
failures at a later date. Redesigned equipment items .nay
be required for examination at boejn,. The tuyer shall
forward comments to tne Vendor within 10 days, if Boeing
disapproves, a mutually acceptable c.ange must be agreed
upon. The Vendor may incorporate the redesign in prepro¬
duction test parts and begin the test, but he must not
release the change for manufacturing use on items to be
delivered under contract to Boeing until receipt of the
Buyer's approval.
DISCREPANCY hmORTS - A detailed report snail be made by
the Vendor on each discrepancy occurring during preproduction
tests. The report shall include details relating
to the failure and corrective action taken to enable Boeing
to fully evaluate the problem. Photographs shall be included
wherever they contribute to the understanding. The report
shall also include a reproducible copy of a completed "Pre-
production Discrepancy Report" form, see Figure 1, for each
discrepancy occurring during the test. Discrepancy Report form
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SPECIFICATION DOCUMENT PAGE
CHANGES TO 1HE ARTICLE OR SPECIFICATION
6.5.1
SAC Changas
6. 5*1.1
8h angea to the procurement specification may be initiated
by the Boeing Airplane Company to revise, add or delete
requirements. All Vendors affected will be notified of
such changes as soon as possible. All changes will be
confirmed in a subsequent revision of the specification.
Orally - Stated Changes
6.5.1. 2
6.5«1«3
Any orally stated change or intention to change the require,
raents of the procurement specification is unofficial.
Official Changes
All changes to the procurement specification will be
accomplished by revision of the SPECIFICATION CONTROL
DRAWING and/or SPECIFICATION DOC GHENT.
Interim Notice of specification Change
In instances where a specification must be changed immediately,
the change may be authorised by a letter or telegram of inten¬
tion from the Boeing Materiel Department. In this case, the
letter or telegram of intention will be followed by a substan¬
tiating revision to the specification.
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D1 0-204*03
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EOEIN6 AIRPLANE COMPANY wnuHt
SPECIFICATION DOCUMENT PAGE
6.5.2
6. 5.2.1
6. 5.2.2
6.5. 2. 3
Vendor Changes
Specification Chary.es
Changes to the procurement specification may be requested
by the Vendor or others concerned and, if approved, will
be confirmed in a subsequent revision of the specification.
Changes After Design Proposal Approval
After 'uiC design proposal approval has been granted, it shall
be necessary to obtain written approval of 2AC prior to the
incorporation of any change affecting physical, functional,
or structural interchan0eability or weignt.
Changes After Tentative and/or Pinal Approval
After tentative and/or final approval have been granted, it
shall be necessary to obtain written approval of EAC prior to
the incorporation of any change whatsoever. When a change has
been approved, revised drawings and data snail be sent to
BAC. Uevision letters or numbers and dates shall be used to
indicate the revision status of each original drawing or data
sneet. Where part number, changes are not required, serial
number effeotivity rau3t be noted for all changes.
Additional or repoat flight proof testing may be required
at the discretion of the .ngineering Department.
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6.6
6.6.1
6.6.2
6.6.3
6.6.1*
6.6.5
V
sequence of bac- vendor negotiations
REQUEST FOR QUOTATION
The Vendor will receive a copy of the procurement ; B
specification as part of the bidder's package ana an |
invitation to submit a design proposal. This may include ;
a request for estimate of cost and delivery schedules.
DESIGN PROPOSAL SUBMITTAL
i
The Vendor's design proposal shall be prepared in : e>
accordance with D2-3971 and shall be sent at the time of i
bid submittal to the Buyer who will route it to the |
Engineering Department. j
DPA ISSUANCE i
i
!
Upon evidence that the proposed article will meet specification g,
requirements the Vendor will be notified that Design Proposal !
Approval has been assigned.
Deleted
PURCHASE ORDER
After DPA has been issued, the Buyer may issue the purchase B
order. I
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SPECIFICATION DOCUMENT PAGE
r
■(' ) 6.6.6
6.6.7
Pinal is ing Design
The Vendor may then prooeed with efforts toward final
design configuration ana manufacture. In addition, the
Vendor ehaJ.1 prepare a preproduction test plan and submit
to tiie Buyer who will route the data to the Engineering
Department for approval. This plan shall Include a test
schedule per a form provided by the Buyer. When the Vendor
receives approval of his test plan, he may prooeed with
preproauction testing.
Critical Design Review
h critical design review shall be accomplished by BAC
Buginceriiit, on the equipment at the time the production
configuration iu established ana prxor to the start of
flight proof tasting. This siiall be a detail analysis
of each part of the equipment with respect to its adequacy
to fulfill its function. Jhe Ifenaor shall make available
to BAC sufficient data necessary to perform tills review.
Design data to be furnished will include but not be
restricted tot
(a) Production drawings per 6. h A.
(b) Circuit diagrams
(c) Detail reliability Program
(d) Detailed numerical reliability analysis in which the
potential operational reliability figure of the equip¬
ment is calculated, -oi explanation of the basis for
selection of the reliability figures f . r the individual
parts shall be included.
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(e) Tic interference Control flan in accoru with and within i&
tae time specified per paiagraph 3«U of GM 07-59-2617A. H
The above data shall -a fur isl.ed or. a keep-up-to-dr te basis.
Notification of jesting
The vendor shall notify Boeing at least three days prior
to conducting any tests in wnich data is to be used for
flight proof purposes. (At tuls time the Vendor must
supply a revised test schedule.) The buyer will notify
the vendor if Boeing witnesses are required at any or all
such tests.
6.6.9
Submittal of Test Data
The Vendor siiall send preproduction data to the Buyer who
will in turn route it to the Engineering Department.
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6.6.10
If the preproduction date indicates that the article will
meet all specification requirements! either tentative or
final approval will be assigned.
6.6.11
Ordinarily, an article must be assigned tentative or
final approval before it can be installed on production
assemblies. Purchase orders will stipulate that
no articles shall be shipped before approval has been
received. The Buyer, however, may apply for limited
or flight (operational) certification and then authorise
limited shipment to sustain production until approval
is assigned. This application for certification must be
accompanied by the data required under paragraph 6.U.U.5*
Notification of Approval
The Vendor will be notified of a certification or approval
issued to his article by means of a letter signed by tne
Buyer and followed up with a revised copy of tne speci¬
fication Control Drawing, titven it is urgent to release the
manufactured article for snipment to the Buyer, advance
notice of certification or approval may be telephoned, or
telegraphed to the Venaor by the Buyer.
6.6.12
srov&l of Acceptance Test Procedure
The Vendor's Acceptance Test Procedure, as required by
paragraph 6.i*«U«5 must be approved by the Engineering
Department prior to the shipment of the Vendor's articles.
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SPECIFICATION DOCUMENT PAGE
6.7
6.7.1
6.7. 1.1
6. 7.1.2
6.7. 1.3
SPECIFICATION WAIVERS
A waiver is granted from the requirement# of paragraph
3. 1.1. 2.1 to allow the out-of-tolerance conditions
specified below. (Ref. 2-6432-10-41 dated 11-17-61).
GM 07-59-2617A, Figure 1 (A.l)
Broadband Conducted Interference
RFI Condition >
320 Ke - 1 db out
425 Kc - 3.5 db out
CM 07-59-2617A, Figure 1 (A. 2)
Broadband Conducted Interference
RFI Condition t
1.5 Me
- 2 db
1.94 Me
- 2 db
12.0 Me
- 1 db
20.5 Me
- 2 db
out (*28 v. line)
out (-28 ▼. line;
out (Signal lines)
out (Signal lines)
GK 07-59-2617A, Figure 1 (B.2)
CW Radiated Interference
RFI Conditions
1.66 Kmc (7th Hannonic)-4.8 db out
1.89 Kmc (8th Harmonic) -2. 8 db out
6.7.1.4 CM 07-59-2617A, Figure 1 (C.2)
Transmitter Keydown
RFI Condition:
206 Me
214 Me
227 Me
229. 5Mc
245 Me
710 Me
1.42 Kmc
1.66 Kate
1.89 Kmc
2.12 Kmc
2.35 Kmc
3.30 Kmc
- 37 db out
- 7 db out
- 26 db out
- 27 db out
- 13 db out
- 2 db out
- 13 db out
- 52 db out
- 37 db out
- 20 db out
- 27 db out
- 14 db out
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SPECIFICATION DOCUMENT PAGE
| 6. 7. 1.5 GM 07-59-2617A, Figure 1 (C.2)
Antenna Conducted Keydown
; RFI Condition;
195.5 He
-
30 db out 1
216.5 Me
-
19 db out !
218.0 Me
-
23 db out !
235.5 Me
-
19 db out '
•
45C.0 Me
-
11 db out
676.0 Me
-
25 db out j
1.13 Kmc
-
9 db out !
1.36 Kme
-
5 db out |
1.57 Kme
37 db out 1
1.80 Kme
-
37 db out !
2.03 Kme
-
17 db out ;
2.25 Kmc
-
29 db out
2.93 Kme
-
1 db out
6.7. 1.6
GM 07-59-2617A
Figure 1 (C.?)
6. 7. 1.6.1
Transmitter Crossmodulation
Transmitter No
. 1 3$ amplitude modulation and tranemitter
No, 3 normal modulation-
RFI Condition:
195.5 Me
_
30 db out
200.4 Me
-
32 db out
218.0 Me
-
13 db out
220.5 Me
-
23 db out
223.0 Me
*
11 db out
6. 7. 1.6. 2
Transmitter Croaamodulation
Transmitter No
1 normal modulation and transmitter
No. 3 305C amplitude modulation.
RFI Condition:
195.5 Me
30 db out
201.0 Me
-
34 db out
217.0 Me
-
18 db out
221.0 Me
-
32 db out
223.0 Me
-
18 db out
236,5 Me
-
36 db out
680,0 Mo
-
3 db out
689.0 Mo
-
2 db out
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6.7. 1,6. 3
6.7.I.6 .4
6.7.8
Braamitter Croaomodulaticm
Snummittor Bo. 2 30 £ amplitude modulation aid tranttittar Bo. 3
normal modulation.
WlPoomtuai
201.0 Me
m
26 db out
206.0 Mb
m
38 db out
211.0 Me
m
12 db out
223.2 Me
m
17 4b eat
225*4 Me
m
9 4b e*
226.0 lfc
m
29 db out
229.0 Mb
m
22 4b out
235.8 lfc
m
30 db out
238.2 Me
m
32 Ab out
a4l.O Me
m
6 4b out
ttaaamlttear
Cromoaoduli
Braaanittar Bo. 2 aonaal modulation and tranomittar Bo. 3 30jt amplitude
modulation.
201.0 Me
806.0 Me
210.0 Ms
223.0 Me
223.0 Me
226.0 He
229*0 lfc
2kl.Q Me
38 db out
38 4b out
UfllMt
18 4b out
23 4b out
29 4b out
17 4b out
2 4b out
Gbeaoto» UP. A. Itched beard* obeli be par
* *. J*l69
B. Babazaal Connectors obeli bo
Hoatiftoi in accordance with
VD dsaadago.
C. Shielded wire inotal Lotion
obeli be par USD drawingo.
ttMQii, Bub- A. MtoboA board# obeli bo por
ftick* USD Spec. 1*169.
The following weabaamthlp derlatleme ore created from the
Of paragraph 3*1*1. 1*5 (Bef. 2-6425-01*76 dated 10-16-6?, 2-^25-01-82
dated 10-16-62 end SBX 2-4437*1*6229 dated 10-5-62).
Applicable Mara.
tr grflgft _
Para. 3-3.1
Jfcra. 3*a.
Pbra. 4.6.6
Tara. 3*3*1
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SPECIFICATION DOCUMENT PAGE
MU* hit.
B. attorns! connectors ahull ba Bare. 3*21
identified in accordance vlth
4.6.3
C. famine sf lull, auk as
lead length and shram MUf
on csnpanevts, shall ha yar
UED drawings.
D. Wiring shall ba par UD
drawings.
flubaarriar A. Btchat boards Ball ba yar
Oscillator USD Spec. J-l6f.
Kara. 4.8.2
fara 3.3.1
B. Faming of leads, aoab aa load Bara. 4.6.3
length, atraae relief, and distance
ftp aa ceapopant ta kaaft, Shall ba
par UED drawings*
G. Deviation to soalloyeA, Staged Para. 4.4.3
toawrtnals shall ba yar OB warfc-
asaShip standards monel, para. 3.3.
0. Malm* paA 4
par ORB dravlnga.
•hall ba Pare 3.8.4
Bagu- A. Btehad boards tell ba par USD Para. 3*3.1
later (FB-19) Spec. J-060.
B. Poncing at leads, nob as lead
length, stress relief, sad distance
fra csngpanaet te bead, Shall ba par
UBD Aravinas.
. 4,6.3
Pare. 4.4.3
9. Minin* pad dlanatsr shall be par Bmps. 3*8*4
UBD drawings.
Bwar Amplifier A. Bxtaraal conseetara tell b« Ana. 3.21
(BA'Il) identified in accordance vlth USD
C* Deviation ta soallapsA, Masai
tarslnal, terminals Shall be par
BSD vostaaoshlp sUpfbuiS annual,
pars. 3.3.
B. flhialdai wire lasts llatlac shall Pars. 4.8.6
ba par UBD Aravinas.
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CHAilML UIPUT DATA
?M/M XELEMBZUY Sy3'iM 10-20li03, -1, -2» -3, -10 & -11
L
Channel
12 (10.5 kc)
13 (Hi. 5 kc)
A (22.0 kc)
C (iiO.O kc)
X 170.0 kc)
Input Voltage Range
0 to ♦ 5 volt*
0 to ♦ 5 volts
0 to ♦ 5 volts
0 to ♦ 5 volts
0 to + 5 volte
SCO Input lapcdance*
et leest 100K ohms (±10$)
*t leest 100K ohms (±10$)
at least lOOK ohms (±10$)
et leest lOOK ohms (±10$)
et least lOOK ohms (±10$)
• A nominal input impedance greater than 100K ohms is preferred
end shall be considered as e design objective. Any nominal
input impedance attained greater than 100K ohas shell be stable
t« within ± 10$ of that nominal input impedance.
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SPECIFICATION DOCUMENT PAGE
FREFRUflJ C TlOfi DISCitEPANCY REPORT INSTRUCTIONS FOR FIGURE 1
This form shall be used to report the details of every
discrepancy, malfunction or failure observed on any item,
parts, material or assembly during preproduction testing*
Photographs shall be included whenever they contribute to
the understanding.
The form will be originated by the observer of the discrepancy,
malfunction, or failure. It must be complete and accurate
as possible.
The form will be reviewed for completeness in the area in
which it is originated. After completion, the form will be
routed as indicated at the bottom of the form.
1. Serial number of the report.
2. Date discrepancy was detected.
3. Cross reference to vendor report on same discrepancy*
R. Name of observer originating report.
5. Name of person who checks report for completeness
and approves.
6. Number of preproduction test paragraph being run when
discrepancy occurred.
7. Total running time (hour's and minutes) accumulated at time
discrepancy occured for test being run as indicated in
item 6.
U. Ibtal preproduction test time (hours) accumulated for all
test paragraphs completed prior to this discrepancy.
9. Name of loe.ng witness w/io observed this discrepancy.
1U. This ulock to be completed only for those preproduction teat
paragraphs wnich call for more than one operating mods.
11. Number of toeing purchase order which buys the item being
qualified.
12. Maine of vendor and the city in which the item is being
qualified.
13. tome of part as given in the title of the toeing procure¬
ment specification document.
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FIGURE, lb
111* Number of the Boeing Procur^«>nt'%pecification D rewing
with dash numbers at applicable.
15. Nans of the Vendor assembly which ip discrepant.
16. Assembly number of the Vendor assembly which is
discrepant.
17. Serial number of the Vendor assembly which is die*
c repant.
18. Name of the specific part in the Vendor assembly which
is discrepant.
19. Part number of the specific part in the Vendor aeaembly
which is discrepant.
20. Location or reference designator for the specific part
in the Vendor assembly which is discrepant.
21. A specific narrative description of background symptoms,
environment, actual test values read, operator's comments,
and cause of discrepancy if known.
22. Narrative analysis of discrepancy which is made to
determine corrective action to be taken.
23. Narrative account of corrective action taken to correct
discrepancy and prevent recurrence,
2U-30 For Boeing use only.
31. Routing instructions.
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FIGURE So.
ACCEPTANCE OK JUNCTIONAL TEST SUMMARY INSTRUCTIONS FOR FIGURE 2.
This form shall be used to report the completion of each
test reference or functional test paragraph by number and
date in chronological order. All test references shall be
listed whether discrepancies occurred or not and shall
include operating time and cycles.
The details of every discrepancy, malfunction, or failure
observed on any item, part, material, or assembly occurring
during functional testing shall be reported in proper
order. Photographs shall be included whenever they con¬
tribute to the understanding.
1. Name of manufacturer or vendor of item reported on.
2. Name of equipment or item as given in the title of the
Boeing Procurement Specification Document.
3- Assembly or part number of the vendor item being
reported on.
lj. Serial number of the vendor item being reported on.
5. Number of the Boeing Procurement Specification Document
and revision date.
6. Number of the test reference or functional test para¬
graph and the date on which it was completed.
7. List names of functional tests completed opposite each
number and state actual test values read. If no
discrepancies occurred during test, so indicate. If
discrepancies did occur summarise them opposite the
appropriate test number* Each summary shall include cause,
if known, and action taken. Apy failed oarts shall be
completely identified.
8. Operating time and cycles accumulated shall ba listed
for each test reference number.
9. Routing instructions.
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optional units, function may pEftFORwep >n other com pon ent
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REVISED
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DATE
SINUSOIDAL V1&RAT10N
ENVELOPE FOR EQUIPMENT
WON - OPERKTIVE
SPEC.
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PAGE 50
DOUBLE. AMPLITUDE IMCMEB
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REVISED
DATE
sinusoidal vibration -DESIGN
$ TEST* ENVECOPe for
EQUIPMENT OPERATIVE
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