UNCLASSIFIED436 16

AD

DEFENSE DOCUMENTATION CENTERFOR

SCIENTIFIC AND TECHNICAL INFORMATION

CAMERON STATION. ALEXANDRIA. VIRGINIA

UNCLASSIFIED

NOTICE,- When government or other drawings, speci-ficetions or other data ure used for any purposeother than in connection with a definitely relatedgovernment procuitment operation, the U. S.Government thereby incurs no responsibility. Dor anyobligation whatsoever; and the fact that the Govern-ment may have formlated, furnished, or in any -aysupplied the said dravings, specifications, or otherdata is not to be regarded by implication or other-vise as in any manner licensing the holder or anycther person or corporation, or conveying any rightscr permission to manufacture, use or sell anypatented invention that may in any way be relatedthezeto.

C-71

MCDONNEILL

ET ' 20 March 196.

REVISED

EVALUATION OF BRAZING ALLOYJ FOR n1LE

FABRICATIO11 OF INCONL 718

HO1;EYCOa SANDWICH PANEIZ

REPORT. A469 SFRIAL NO.

MCDONNELL

This report vas prepared under Contract NumberAF33(657)-11215 and BPSN: 63-6899-7381-738103.Additional information pertaining to any datacontained herein may be obtained from theDirectorate of Materials and Processes(ASRCE(-1), Aeronautical Systems Division,Air Force Systems Comnm.d, United StatesAir Force, Wright-Patterscon Air Force Base,Ohio, or McDonnell Aircraft Corporation,St. Louis, Missouri

INDEXO:E _.(N1-4)(I-i)(IV-a)(VI-b)

(W

1 2 J uly 1 96 ) -,_o,, S o Umgv,.go (A) 8-563"r)v ¶••

""(VI-O(() ) •-) - ,

IABORATORIz Structures

MVAIMATIOI OF BRAZING ALUOYS FOR THS FABRIC&TIJM OFICONS' 710 t'O)MU.•,K SANdcH PAMEL.

ASTRACT

A nickel base e Lrwti~ral alloy, Inconel 718, has been considered foruse in the fabrication of honeycomb structures capable of s aned opere-tion at elevated temperatures. Four gold-containing brass *11o72 wre &l-acted for comqatibility testing with Inconel 718 base metal.

From the results of thes tests Proeabrase 128 and Premsbraze 130braze alloys appeared to be suitable for honeycomb structure briaing withInconel 718 as base metal. No evidence was found to indicate that eitberof Utese braze alloys are susceptible to crevice corrosion. The Nicoro andIncuro 20 braze alloys wsre eliminated from testing because of inferiorwettability and flow characteristics.

Methodsj, Metallu~rgica2 Growp

t, o Manager trl'u~cture IAb Loorstory P"Cjeat A:Usor

i? ulv MCDONNELL12 July 15ý3. • • t ~ ~T?, LOUtIS, WII$OUNIq [ "

j ,,Ho fl (B )--17-63 1• ,:'

1 •INTRODUCTION

Dra~d honeycomb constructivn can be highly efficient in the productionof thin air"foll er control suarface panesl capable of withstanding the offsetsof high temperature operation. Inconol 718 has comes under considoratiom as abae mot~a alloy for this type of structure, but little data concerning the com-pAtiLv' lity of Inconol 718 and cossercial braze alloys is available. Your gold-containitng braze alloys were selected for study am possible Incconl 718 honey-comb brazing matarials.

Wottability, lap shear, crevice corronion, and edgewise corosionntests were conducted in a brass alloy evaluation Program by the McDmwnllSt-.ictauvo Laboratory during the period 12 June through 27 Mlovmber 1962.

2. MI•CRIMWION 0?• TSST ARTICLAS

2.1 Baos Metal

Annealed Inconel 718 shoot stock (0.012, 0.025, and O.O43-inch thick),and honoycoub core (O.OO2-inch ribbon and 0.25-in,;h call size) wx ro i-ntbadfor specimen fabrication.

The chemical composition of Inconel 718, in percent, is tabulated bsw

Ni - 50.o-55.0 C - 0.10 max.Cr - 17.0-21.0 Si - 0.75 max-•

CbT - 4.5- 5.75 Hn - 0.50 max.Mo - 2.8- 3.3 S - 0.03 Max-Al - 0.2- 1.0 Ou - 0.75 maex-Ti - 0.,3- 1.3 Fe - balance

2.2 Braze Alloys

The four. gold-containing braze alloys were in the foris of 0.001 or0.002 inch thick foils. Their chemical compositions aria tonporataro character-istlcs are liste1d belovi

_Pomab-ass 128 Promabras 130 Vicoro Incuro 20% An 2 2 35 2 0% 1. 22 is 3% o 62 78% cr 6% in 2melt Point 1785Y 17h0• 83• 17TF'1ow Point 1835? 174CF 1886F 1877FB

3, TXST PHOXXZM3.1 WttattliOy TmSt

t iSi•f Trconol n8 tact blanks, me apab o inch in are, wrn he *ef.cdfrof 0.i25 tinhethick opert m terial. S71eral om thede blanks wnre cleaned by

baemta#loyfrtbhtp of trutere tonwin liti.daa onernngth crn

g 12 July 1963 it.LCDONNELL PA&(

FINAL RDPORT

3.1 Wsttability Testa (Continued)

ufnir A - vapor d.eras•iwd per PS 120101Alkaline cleaned per PS 12030;Rinsed with tap water, and dried by forced air.

Prncedure B - Vapor degreased per PS 12010;Pickled in 30 percent Ho03 - 2 percent HF solution(1207) for ten minutes;Rinsed in tap water, and dried by fcrced sic.

Procedure C - Vapor dagreased per PS 12010;Liquid honed per PS 12045;Rinsed in tap water, and dried by forced air.

Procedure D - Vapor degreaved per PS 12010;Alkaline clea"ed per PS 12030;Pickled "'. 30 percent HNO3 - 2 percent HF solution(120Y) for ten minutes;Rirsed with tap water, and dried by forced air.

The specimens were handled with white gloves after cleaning and dur-ing layup for brazing. The braze alloys were cleaned with trichlorethylenei~mdiately before application. The braze alloy foils were cut into 0.25-inch squares which were stacked to a depth of 0.006 inch upon each Inconel718 wattab~lity test blank. Two specimens were prepared withi each braze alloytested for each combination of cleaning procedure and brazing tempersture.

The wettability specimens were brazed in a vacuum retort which wasevacuated to a pressure lower than one micron before heating. While thisvacuum was mintainod, the specimens were heated to brazing temperature witha graphite cloth heating element. After brazing, the spectmna were cooled tobelow 60OF under vacuum, and then air cooled to room temperature. Teot brazeswere conducted at the following temperatures:

Braze Alloy Test Tenperatures (OF)

Premabraze 128 2000, 2050Premabraze 130 1800w, 1900Nicoro 1875, 1925, 200CIncuro 20 1860, 1910, 2000

After measurement of the flow radius, the wettability speoimine woremounted for metallographic examination.

3.2 Lap Shear Test.

Inconol 718 shoot, 0.043 inch thick, was sheared into pieces 4.5 x 3inches in area for lap shear brazes. From the wettability test results,

V

12 Ju ) MCDONNELL

NIVOICO _____________ _

FINIL WLORT

3.2 Lap 3hear Tests (Continued)

ciewaii* proceduz-w D was az+-t.ed for the preparation o! the incoael 716

during this phase of the program. Also from the wettability teat results,the braze alloys selected for further evaluation were Premabras. 128 and 13C.

The lap shear panel parts were cleanec immediately beforc layup andwere handled with white gloves during layup. A 0.002-inch thick brass alloyroil strip was placed between two h.5 x 8-inch Inconel 718 pieces to form asingle panel measuring approximatelJy 9 x 8 inches in area. A 3t overlap andthe minimum possible clrarance were maintained furrL layup and brazing.

The vacuum brazing procedure followed was similar to that of thewettability teat, specimens, except that the time at temperature was shortenedto three minutes. The Premabraze 128 lap shear panels were brazed at 2050F,and the Premabraze 130 panels at 19001. All lap shear specimen panels werecooled in the retort, under vacuum, to below 60OF before air cooling to rooatemperature.

After cooling, the specimens were aged by heating at 1325? foreight hours, then furnace cooling at lOOF/hr to 1150F, holding at this temp-erature for eight hours, followed by air cooling to room temperature.

The lap shear panels were friction sawed into 0.75-inch stripswith the brazed joint perpendicular to the long axis and deburred to producespecimens as shown in Figure 1 on page 15.

Lap shear specimens brazed with Premabraze 128 and 130 were testedat room temperature and at IOOOF in a 60,000-pound Baldwin universal testingmachine. 1oad was applied at a rate of 3000 ib/min until failure. The speci-mens tested at 10(x)O were heated to temperature in one minute with quartzradiant lamp ba ":s, held at temperature for five minutes, and tested.

Three specimens joinec with each braze alloy were exposed to a 20percent salt spray solution at 95F for 100 hours per Federal Test MethodStandard 151a, Method 811.1. Three additior-l specimens joined with eachalloy were submerged in aerated water at room temperature for 100 hours.After the exposure periods, the specimens were tested under tenaica AL roomtemperature to deterine whether any damage hav been sustained from crevicecorrosion.

3.3 Honeycomb lrazing Testa

Inconel 716 face akins and cores were prepared for brazing two boney-comb specimeres with Premabraze 128 as braze alloy, and two with Premabrare 130.The face skins, measuring 3.5 x 2.3 inches in length and width, were shearedfrom a 0.012-inch thick sheet, and the matching cores were cut from 0.63-inchmaterial having a 0.002-inch foil thickness.

-. .-

A19 MCDONNELLVA! V 12 JulY 1963 ST. Louis. IOUP, PAGE,

NIVISetP

FINAL RLPORT

3.3 Honticcmb ,Brazing 'rests (Continucd)

Mhe coroft And face !4k"n were cleaned accordi.-i to Proceruhr- Ddescribed in section 3.1. The braze alloys were cleaned with trichlorethylene.The parts were handled with white Cloves during layup. A single sheet of0.002-inch thick bratze alloy was JAid between each farte skin and the core,and the specimens sealea into vacuum envelopes for brazing.

After placing the brazing envelope and specimen in the retort, theonvelope anr retort were both evacuated to a pressure of less than one micron.With this vacuum maijitained upon the envelope, the retort was back filled toprovide a differential pressure of approximately two psi on the envelope.Brazing was conducted at 205OF with Premnbraze 128, and at 190OF with Pro-mebraze 130 alloy. In each case, the specimens were held for three minutesnt brazing temperature and cooled to below 30OF in the envelope under vacuum.

The honeycomb specimens were heat treated similarly to the lap shearspecimens, except that they were left in the brazing envelope and a contin-uous flow of argon gas was maintained throughout the aging cycle.

After heat treatment, the honeycomb edgewise compression specimenswere machined to three inches in length and two inches in width. The two-inch ends were ground to a parallelism within 0.001 inch/inch.

With parallel loading plates clamped lightly to the specimen ends,compressive testing was conducted in a 60,000-pound Baldwin universal testingmachine. Each specimen was loaded to failure at a rate of 1500 lb/min. Onespecimen brazed with each filler alloy was tested at room temperature and oneof each at lOOOF. The elevated temperature test specimenn were heated withquartz radiant lamp banks and held at temperature for fifteen minutes priorto testing. The edgewise compression test setup is shown in Figure 14 onpage 26.

I .emabraze 128 and Premabraze 130 wettability data is tabulated inTables 1 and 2 on pages 8 and 9. Photographs of all Prematraze 128 andPremabraze 130 wettability specimens are shown in Figures 2 through 5 onpages 16 through 19, with representative specimens of Nicoro and Incuro 20shown in Figures 6 and 7 on pages 20 and 21. Typioal base metal-braze alloyinterfaces of Prembraze 128 and Premabraze 130 are shown in Figures 8 a&d 9on page 22.

Shear strength data for -ro-braze 128 zxd Premabraze 130, cootemperature and 1OOOF, is presented in Tables 3 and 4 on pages 10 and 1-

12 Jul 1963 .MCDONNELL

FINAL REPORT

4. TEST REkSULTS %i .... NU. )

braze 130, altAr crevice corrosion taste, are tabulated in Tables 5 and 6

on pages 12 and 13.

Edgewise compresouion test data obtained by testing honeysoeb specimensbrazed with Premabraze 128 and with Premabraze 130 braze alloys is presentedin Table 7 on page lb. Photographs of all failed compression apecimns artshown in Figures 10 and 11, on pages 2j and 2h. Photomicrogfaphs of typicalhoneycomb-to-sk1r, brazed Joints are prese;:t-d Ln Figures 12 and 13 on page 25.

5. LISCIJSSION OF TEST RESULTS

The limited quantity of golc-containing braze alloys available forthe wettabillty testa did not permit the formation of a measurable contactangle. Therefore, a standard wettability rating could not be computed. Brasealloy selection for further testing was, therefore, baned upon the measuredflow radius. kxtremely poor flow characteristics were exhibited by Nicoroand Incuro 20 alloys, regardless of surface preparation or brazing tempera-ture (cee Figures 6 and 7 on pages 20 and 2]). Further evaluation of thesetwo alloys was not conducted.

Both Premabraze filler alloys showed good flow characteriatL", part-icularly upon Inconel 718 surfaces prepared by cleanine procedures B or D, asdescribed in Section 3.1. Cleaning procedure D), requiring vapor degreasing.alkaline cleaning, HNO3 - HF pickling, tap water rinsing, and forced air dry-ing was selected for tIe preparation of Inconel 718 for brazing lap shear andhoneycomb specimens.

Evaluation of the lap shear test data in Tables 3 and h on pages 10and 11, revealed that Joints brazed with Premabraze 128 failed at higheraverage shear stresses thar. die those brazed with Premabraze 130 (50,900 psiversus 46 ,200 psi) when tested at room temperature. In Uasts cond-.cted at1000F, however, Premabraze 130 Joints failed at an average shear stress of32,500 psi and Premabraze 126 Joints at 31,300 psi average.

The lap shear specimens subjected to salt spray and aerated waterexposure before room tempernture shear tests failed generally at shear at-resseehigher than those developed by untrposea specimens. This probably was :auaedby variation in overlap or joint clearance.

Higher failing edgewise compression strtesos were exhibited by thehoneycomb specimenn brazed with Prerabraze 128 when tested at room tempera-ture and at I0001. A comparison of the test results is tabulated on thefollovLng page.

2JJY 63 7CDONNLL

flNAL Rk.ORT

5. LISCUSSION OF TLST RISULTS (CONTI)MED

Rraze Alloy Vailing ge.• ise. CozEr~eeinn Stress (psi)

I.T. 1000

Prembraze 128 167,6oo 142,300Prembraze 130 156,500 131,300

Visual examination of the brszed honeycomb specimena indicated thatPremabra:e 128 tenda to £orm larger fillets than does Preabrasze 130.

6. CONCLUSION

Both Premabraze 128 and Premabraze 130 appoarea suitable for brazingInconel 718. No evidence that either of these braze alloys applied to Li-conel 718 is susceptible to crevics corrosion appeared in these test restlts.Although the ftchanical properties of structures brazed with Presabraze 128were nearly alwaye higher than those of similar specimens brazed with Prema-braze 130, the lower brazing temperature of Premabraze 130 may be preferablebecause of the thermal effects on the inconel 718 base metal.

Nicoro and Incuro 20 braze test result3 inoicated that thede allo-ysare uneuitable for vacuum brazing Inconel 718.

S. -

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T TA LE: 0P M R Ar ' . 28 W..ETTeAVLIT V CAT i

BRA ZE TIMC AT wgrrTEO FLOW/SPECIMEN 3tiRFACE TEMP. rE MP AREA fi Aoius

NUM83EP COVVITIO? J J ,,

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3 B 0196 0.125r

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I 0207 0131

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11i A 2050 15 0 16 r 0.105

12 A 0.176 0.112

13 8 0.20.9 0. 133

14 8 0.232 0.14 6

15 C 0.075 0.0_30

I6 C I 0.09r 0.050

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APA01,11, ',? jfA4AZE ALLLY AFTE07 %1.Ov LESS. RADW._ OF (±RA.7E

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22 4 0 C)19 -0048

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25 C0 -0,125

26G C- 0 -0-125

27 1)P 0.013 -0,060

26 P '0.012 -0,065

'I1 A '.900 15 0,1107 0,060

32 A j0.146 0"0 9

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3ý4 80.134 0.081

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370. 130 0L084

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TYPICAL OF IMAINISO wP~lMu (OThU TUIN LIQUID J#.w&)1860?O AND 1910?

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OBJECTIVE ~mm Fum v w wit m wU oA mummMIAM " ua~iut Mm us muu WAUTI"

Tro obtain informuatilon nooded for the voluction orabaIneZ~l alloy for ~arc~;tioA'rr sisLtanh~nc-yan't!) pansflfll -?r.1, .ncr-i'l 71". honnyceosb coremshoot And ha? mat"'rialse Snltjction dill U.) unsod ont~he rosilts or vetta!i4lit.j 1si~ts, uhoar a~ronj'th ofbr'azou jointa, ro1gixtance to crqvico c'orroalon andodr~owibo com russi n Lunts of' sample pimnul r., ,-aimvns#Siloar and con;'rfinn.l tLi osts vill be conu mltnl (Atroomn ton-inratire and 1000 F&

2.0 JUSTIVICA;U':

In thn dosijgn or tmlperatur0ro& mt'vnt U.Jiln airfoil5'actiflos 1, maximnim w'ruct-ural ',ff1ýliciny cum bnroalized by utlliztno: brniz'n: r.vrc .;: r~struztlor.

('C Lhe more offici~vvt structural matwx~ialz for thisc.plicat.i'n, and, at t~ho prosont t~,rvar:: Iittlninformwrmni~ !: ova: i at I a on !h4, ao Latnl I It of

as foV'.nqrs

3-1 .itt~atil.tz Iast~n - lut'.triat, rv~vn W.

LItIoes or o:-n:idat^t 1'razln.- alloys -,,ll be 1

~ ~ra~.n! . .rflt.ret. !;n~eu~a1o :o~viodt; to .prflt tixtunt onl -x:'a

cr-Ya .i; ~rni9 ir .. ýr.i !ltuwi.mn, 'A1vhd%~ 1 Inclydnis a:; :,irt 71'

REFEREMES C1 1INCU)SURES c

' A"' a~"" S

-' ¶'r iq:.;-q - LAp shear cpeaimens will bo propared using only those1.. t1Toys uihich havoý- adoquato wett~ability als detoftilned in

~i Lvio. The brazins, Lrwmperaturo and .z1oaning tr#ýntm~nt 1411~ALbo be lindMted to the r.-,n catirfactory temp;orflturn anct crat.n-nt.an datro-irl:d in 3.1.

j, Crevice C-"ron ion Tests - Lap shoar test. specimens, prepared an in!Ts=* iTa beuseUi thin Invost~iention to determine theeffect. o a.lt sp~ray( and n- r1-1.';d wateor ur: cosisstmieo to crevicecorrecic *of brazod joints.

J4 &.I A..~ Cesozzor Testa - The information obtained in 3.1, 3.23 0 illbe ued s abasis for selecting tho most suitable

braz . gj niloy or allo-,', bra~nj,* tomporetsires and cloaninr- treat-;-t-n t rahricatinr adrovrilso cmsprnoudon toot rpealmens for final

I ~ I i.o~1 71q shoot, NON1 Inch thIk.9

;~.2 lnn'-rzl 718 shoot.. 0.1,10 inchý LVeke

h 1.3 Inconil 718 honeycomb cnore, 0.75 to 1.00 # 003 thick Y 3-1215w L-1.2,"

3/16 :square cell 0.002 inch ribbon, perforated.

~ 1 1`ornivlra-ze 12,", 0.9)Ob in. foil.

h., J P.. ronabrri:'a 130, 1':-I i foil.

% 1,.3 *'!oro (Auj, Cu, *3), ).kYJ15 in. foil.

q-141*j :nL --o' 20 (Auj, TIn), '0.flYAl in. roil.

5.] icottabi 1.1 Cy ocimnon

5.102 Shcar 0.0L0 in. nCn1 1'. shfot. in hOP anncenlo-d ec-n-':WA'. Pioces 1-0 x 1.125 in. ernpare 16 piecoc for ovr~ft;.-

ti- of nac bra.7ir~r niliov.

5-142 ;loan h~ npoclrtann as followst

":;i.4) o *,.qPor dos,:r-arw -or ;ýAC ';121.

5-15 ndnutoo arci iirie.

: irn' k f.ric-loyoro.1,ucric acid ~iT

I- ii . ýonr Ife;~ Lc r.m*wiv oider,.

*I oL.2 Liquid hiuirv' -er ::Z P'.... 1201m5m.

lp!..' Lir ,-.r :.. 12050 for inco-1's1 X ma-l;I

X.1.6 Ail..4r cl-annlnr ha-fs1' till -,AL.9 !'4th clean white -loves:n 1.1 1.ra'/I m- I n -t.o aL

.J.7 i-lar(?' -rt1Inv allo Oic c"rLor of* noah zprc~z'ftn Jr.:nj;, therrnfed'Ir,, dnst!rlhni-I in T.;. 513-296o

522 Shrmr _jp~'ic nnna

5*.2@1 Shoar 6 pimaCr. h,56 x mi In* of~ O&OjO in. annoa;,LJ Inionl 71.1s!-nct mvr.I~'ial for vnvut:afio~r' .f 'rxh selt~ctou 'r:.,zinr alloy*

.-,.P oP C `,!-a r.1 "aO n. Qv- n tim :..o] e~tii. 4 rn Orm:

#-Iv- i bn;-'n. is -

I. arr. brainv',r I in joints n~3 ~nIoa-:1 brimirt, z'1,- -vvL£:-:afvd amd ý,rttzeo

F-feclog. 30z ino n. J.7' in mnoialloi .

71:v.-'r, -z1 .r; r. 'e t.-!i ner.J*aim

PAK 30

5.*dj Assemntle comproncion specimen cotmponents with brazing:alloy material in a suitable brazin, 1'ixtu-s in pr-!,aratinnfor bra21ng.

6,0 b•'1 AZG *Pi-.X!,:,.rf

6.1 rra?.o all toot specimens in vacuum. (Kininwi pressure. avallaI;c)o

6.2 •rnzin1 - Lteiloraturn•e for wetti.bility tests shall be as sh;,-n , :eJe.lime at tomperature shall be 15 minut-es. ool to root. teernotature.

Promahraze 128, (1900 and 1950 F.)

rrarnLrazo 130, (1800 Anrd Id50 F.)

'licoro (Au, Cu, 11)(10'75 and 1925 F.)

- 20 (Au, Gu, In) (I60M and 1910 F.)

zo7.o i1,T THAT,•:r•,

After brazing;, retain all specimens nr. the brazing: envelope at heat Lt.1325"F., hold for P. houra, furnace cool at 100 V./Aw. to 1150 F., hold at1150 F. for e, hours and air cool. Circulate pure dry argon thra.-h theenvelope dur'ny heat treatment.

•i,0 S.;ci:E£F:, r:I';J.AIM'?i!

8.1 Shear Socimtn. - .ut shear tnnolu in stri;,:i and r•zhln, ted.specimens to the g,:orotr. shnrin in r'gures I and 2 for recw to prrr.-tWre and elevated temperature spocimns resiectively. PTepare atotal of 12 room temperature sp'ecItena ana 6 elevate ter.i,-,.ratu,-ospocions for ouch alloy.

8.2 "do 'Comprossion Specimens - Hachino edges of all speci,-r.?n Inaccordance with Paragraph 7.*2i of AIC iteport :Noe A*CC-17. :Inishrddimensions shall be 2.00 x 3.00 in. x brazed thickness.

?,0 Iettabillt 'f"ts - ax&wrline all sDecimens usirn" the? neqt:o. •escrtlbd

9.2 Sharnts - Test isx 4pocixons in tonsion at roo, Lev erw:v;rek#5I n@/min,) and Dix ht 1000 F. docord loa• at fadlr;, .itntshear stress at fa.lure and location or failure.

/.3 Crevice Corrosion Tests - Mx"oSe three la:, shiar s-ecrn- to a20,; sodium chloride solution 1er l'ed. Test, :.0thod :. ;d, %o. 351&,XAnthow '11*l for Ib hours and Joao in tenicn to .a;lur- a:

(Continued)

taiperature. In addition, expose three lap shear specimens toMO0 'nours in a standard controlled huniddty onivirotnent and test at

room temperaturo. Hecord load at ftaluroe joint shear stress atfn~luro and location of failure.

9.4 d ee Capression los - Conduct teats at roem temperature and atXO )-F. in accordance wiLh the procedure described !.• Pararaph 7o2.2

* ATC Roport flo. AK•1C-]7. Record load at failure, facinr stress'ii1sari and node of fniluw-.

10.1 The follovin,* Information is rnquired for all tastsL

10A.3] UDtalled clonnJng ,roceduroo.

10.1.2 Jetailed brazing- procedures. (temporature, tilie attemperature, or.)

*%." 3 !joteqilnd heat Lrentlrug proceduros*

1.07. *w"ttabiliLy Tests

:.0 l•l Wetting index values.

"0.2*2 ilhotomacroi•rapho and :hotomicrograophs or nll spalinsos.

10,303 Joint ihnar 're8 t failure.

;ý-.342 :1asn 1z&4-L1 Stress "L falviro

f,.~ L,, ocato.r 1•- failure.

](1, 1.1 Test tcmnerature

i;.:'J.. Loadinz ratoe

..1: rcvce Corrosion Tooto

10,L.) Comp~loan description of ynv~r-nh,2n'.Al onditionse.

101' ? Aauo mo tol stross nt failur'.

I Jo 4 Location of fai lure.

l',,4,5 Loading rn•e.

1Ozb.6 Phooieicrorranho oý Mny indicbtions or evidence of ce-iee

corrosion&

If PO#1

10.5 1d&* CovrwopLon Tests

lo.,.1 Load at failure.

1;.5.2 Facing stress at ralusire.

10*503 Mode of failure*

10.54. Test tw.pnrature.

10.4.5 Loading rate.

10,5.6 Diagramwatic And/or :-.hoto-raphkc dencription or tentnot-up.

10.•5.7 Photomicrot.raphs of t::pical honnycoNi tn skin brazidjoints and any unuauAl conditions observedt

10.5.8 Photographs of failed specimens.

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