UNCLASSIFIED

AD NUMBER

ADB193852

NEW LIMITATION CHANGE

TOApproved for public release, distributionunlimited

FROMDistribution authorized to U.S. Gov't.agencies and their contractors; ForeignGovernment Information; SEP 1957. Otherrequests shall be referred to The BritishEmbassy, 3100 Massachusetts Avenue, NW,Washington, DC 20008.

AUTHORITY

DSTL, DSIR 23/27631, 8 Sep 2009

THIS PAGE IS UNCLASSIFIED

v'7 ~ AD-B193 85216

UNCLASSIFIED

V)l

DTD. 166 -TYPE AUSTENITIC,

Ii CHROMIUM -NICKEL STEEL SHEET:

AUG 0 31994

REPORT OF WORK CARRIED OUT BY BRISTOL A71RCRA1rYTTD7'

FOR MINISTRY OF SUPPLY

Mceslion for

lNTS CRA&IDTI TA

Uoftlo'flOd LIBRARY CORyDfst ltitoni JAN__21_1958

By lmtlt We

94-24388 AvalhtCoe L

=C.TI= T&IE REPI PENT IS WARNED V-1 0T ,A1lO(

CONTAiNED IN THI DOC X T iAY BESUBJECTlx TO PMYVATELX.OWNED AtGHTS.ISSUED

SEPTEMBER, 19S7BY

TECHNICAL INFORMATION AND LIBRARY', SERVICES

MINISTRY OF SUPPLY

'94 8 02 046-

4..Mm.12/57 IP S&T. Meo. 12/57JDD16-ipUSTENITI0C CNLOM-1lCKL STEEL SHRTn

ASUALOFRPERIES

00. INTROUCTICN

This report sumarizes the properties of the stabilised 18% chromiwz/80.nickel stainless steel sheet materials-chosen by Bristols for structuralapplications.' The major characteristics influencing this selection Werethe wreldablity (in particular to P7.448, a 12% chromium type steel) endthe high strength.

The material is basically Firth-Vickers steel PDp (wich conforms tospecification LT.166, recently superseded by S.520) modified by variousspecial Bristol requirements. The factors which have led to the formu-lation of these special requirements are outlined herein.

Messrs. Fairey Aviation Co. Ltd. have also onosen this material forstructural aipplications and, with their agreement, this report has beenextended to include comments on their experience.

Note: All results qvoted in this report have been obtained using materialsupplied by Pirth-Vickers (Steinless Steel) Ltd. Figures 1-11 arebased on results obtained by Bristols (or supplied to them byPirth-Vickprs) end Figure 12 is based on results obtained by

* Faio-eya.

01. COMIfCAL COMPOSI.TION

The material is of the 18% chromium 8% nickel stabilised austenitictype. The specified ohe. ical composition is given in Table I attached,together with those fcr the now obsolete DTD.i66 end icr 3.520 (thenearest equivalents in ntional specifications).

02. GRADES USED

02.01 Bly Bristol Aircrait Ltd.

Bristol speciifications have been prepared for 4 grades ci

D.166-type material, as follows:-

Applcaton peciic on Min. Spec. Properties CommentsNo. Be t, 1 ft

Purchase from BAC.A. 1038 - 42 58-68 15 Requires conver-Firth-Vickers jsion by User to

_____________1021, 22 cr 61

Aircraft use W' .A. 1021 27.0 48 64 6 JProperties~after heat

BAC.A. io6i - 45 60 6 treatment by

- -. - - User

Non-aircraft BC.102 - 4~2 56 15 Dloes not requireuse (e.g. models) ony - heat treatment

PDTD.166 and S.520 (ref. onl) _ 40-5O52-70.15j Not used

Thus BAC.A.l1021 covers the high grede aircraft material, endBA.A.1061 the material for use there modulus is less critical.The special requirements in these BAC.A. specifications aresummarised in Table 2 attached. F

UNCLASSIEDT

An iortant feet-=* to be noted is theessny or the special1

atosat .

7>.2.Z cr aieAeon c. t.Aec ste Ipefeto (it05) be e prsretoev

er :d*,s but in

or bycontne4u strt-roli; ereat odulugs) of

.jigr ~rperytn--ettsibberW Yat Lare foineng urtt 030lb

eelainrpoete r obpielll) hnsrprlen mstri-rlletnizsr;Cillais stverts rotetpur o~se ndset

No-Sngtlinistin fo-she -6'- siibeunles A thiinj quait4 iths0 modl to4"(eto 3" iwfs eing~ rodued for dOmntei

i wt d hbinto eive &picec

tiM4st6r thcetzeianeeri).o 2.ecial stress-stri carve is

atamlu6a yT oi s caess;6 ver lt an ech

no-eiabet~s oneing6A52 cifatosbeClosr -ticlosse olernces tedi era defe t sesd 'no al'

.?lte secifartonsably ov la. g Oiarion of outrop ing .

V Do6 atoifcaton prmis~kutiteitrierysin4ve-shlog-

iolingor y cntiaou 3tip*lifg;thes reldte-rlvant ~ft~,-~j~ngo~wardi osrer udinsfsio

- titenriaXrtor tstburpeso2;N-~kt -5--info-et aaja nesthsqatt

lwah t-01o 4 t '" i en poue o te

'ofher dventages of strip roflinghave - b& ristols. and,bya54i~to'oted hediada tags an herlighs-th~tefore

'As-a~giedmk excess thickness an steel gives threZtimes the excess

weireble. ti -luiita alloy, close'thicliness- control svr

For stri-olled BAC.A.O58, edge trmming (2" each aide) enables I 'ln~igue- ~ fr adut-250teult -cverng5 thicluaessiss, and'it can be

aeen,.that the d4esired-rage fe r -rmi~ sAtunrealistic if-smallpercen'afters trutmidg iaM bescopt

f (a)- Strend tns Achiivdj

'The -strength achieved, is primrilys a funitich of the amsutoZcold rvoh dAring eiolljig, although it can also be affected'by I

variaions n cheical ompo itin ithin the specified range. Therelation;between fl, ft end e,. is given-In ?Figure'3; the wider

(i)The variation in the-forms of stress-strata curves obtainable

(U),thewidr rage f dlivry dtesforthesheet-rolled materialact~l tesedandtheejpct~iontherefore of kreat'

va~atios~i'oheica 6opoiiionbetse4different specimens.

AsDD.16-tpt ateias ae~cld~orkdit would be expected '

tathi olb6cmdietoa arainof prepeities. -'As can ,f

be sen frm Fgur 4 his ' itio~d~s ocur(particularly withg me in , S anld cl andes

mared in~li 6-n 'f. t i imortnt o ntethat, contrary toalumni* aloys~t i~th~ongtudnajdirection-which is the

vv~ke~h~~etheni l c ongitudixsiaiting).-' (c), icowrsloer?;n s ;:::olat ( :;i e J adls

Fro ?iuro5 i~oi~bo sen tatlongitudinally-cr, is markedlylo'e tha il'______ adBar i d_ tr'aa r__,tesand compression Properties are simila&). (taseretnin ,

()Effectscf'Cold. ort 3

Preliminary 'tests on sheet-rolled material -show that transverseSI Earops to the level of longitudinal 3 with i% prestrilnoi core(less than 2%'i6t be -sufficien't), with a oorrcspondiirg increase inti; they also show that longiudinal c drois by some 3C5 isitli 2%

* piestrin or mere. These tests rere regarded as showing a considerableiaunichinger effect, and. th6 need to-imolode forming fectswhenconideri tg desijn strength.

(c) 'Effects ofg training Rate

it has been shown that variation of stradning rate within thei~ange'likely to be -enconintered'in normA, laboratory wrki does notLaffect test results. 1

Tes 5!ataat resntbut drips it,gPO6e fly rtin tj and ft haebe6btjanes, drops in ex r-nut pat-e I

-eat blahed-(d e t tng diffiulties),but are probably less than

Heairva~200C crup to 10, bouts gays snii rease-in tj, but

othr ron temlc~tuo.(rccvey') properties.

atr~~p roe eideceto..sgest teat thekprsof tearing

t~lhilpastreso s ain ' shge hnthe ator at-,'1.5 noiliaflyasase e notadaaaeaalb. Hesiper, considerablescatersas otainea * he tests (.55 to 2.22) so 1. 5 scold aparto2 e raitc r deig urposes.

'Toe results as' l3natudxueatfatigub -et-s bssi

1-I- Lnii at LEdurenca

____________ vero Aftr Poihigj210s l~i

Heat treatment of DM 166-type Mterials-in the range -4C/55O0Cprcepsan increase in mecha'nical streongth and. stiffnes sta

sbuttipde a less in ductiii. -The effect is3 due to-a

6, %eipiltentd ehafiom, and the ti atzent has been variously

12f treeipitaticn treatmaht,2~od1 R ~ul~ecovery treatment, or

The ecriutes" -sywes-'reutvingdescriptions a_ pan a n d the secend is taveurd-at

4 4Tha Aecpreveeenz -An 'moduli and strongth due to this type oftreatment As markced, and cay be _aeccepsesed' by soot redactien in

a -&lo~ian.info_atien is available. on the effects of tts following

(i) 59000 far I+ houre . moduli, and strensthr are Leprovea nearlyaseucsaalr (ii),, (Iii) ana_(v) treatmen ts, with increasedeogation,, suggesting that the tlmper softenn ag

'4nssg ati this~ teprsee

(ii) 50%- for-4 hours moduli and strengths are significantly

improved (see Figures 6 said 7) without reduction in elongation.

(ill) 52500 for 4 hours : although elongations terd to be slightlylower with this treatment thou with (i), the difference isnot sigutfiqnt, so that in Figures 6 and.7 this treatmenthas not been differentiated fras (ii).

(iv) 5000C : there as evidence that the maximum strength increase,accoopenied by the maximum reduction in elongation, occurs at50000, cnd that this teperature should be avoided..

(v) 4500C for 2 bours : moduli and proof strengths are improved asfor (ii) and (Iii), but ultimate strengths tend to be somewhathigher and elongations to be someehat lower (see Figures 6 and7), thsn for (ii) and (iii).

It may also be noted that the improvements in moduli andstrength wore, more marked in strip-rolled than in sheet-rolledmaterial and that the large reductions in elongation appear to beconfined to sheet-rolled material.

The relation between ti, ft and o% after "Moilus-Recovery" isshown in Figure 8, and omoared avth the As-delIvered properties(see Figure 3) there is again a general improvement in characteristics,particularly for strip-rolled material. It is p6ssible thatvariations in chemical composition rather than the rolling methodused, was responsible for the effects noted in this and the pr-eviousparagraph.

Properties in the As-delivered condition have been regarded bythis Company as inadequate for structural use, and "Modulus Recovery"has been required for all material both to achieve the higherstrongthsani stiffnesces end to achieve less directional andcompression/tension variations (see below). Experience to datesuggests that the final properties being achieved are satisfactory

"Modulus Recovery" must follow all forming operations otherthan distortion correction.

The colour of sheets after "'odulus Recovery" va:ies fromyelloz-brown to blue-brown, the blue trend increasing withincreasing "Modulus Recovery" tewperature and with lack of degreasing

(b) Effect on Directional Variations

Frot Figure 9 it can be seen that, although the material isstill significantly, directional, the variation is less marked thenin the As-delivered condition (Figure 4).

(c) Effect on Ccmoression/Tenaion Relationship

From Figure 10 it can be seen that the differences betweencompression and tension properties are much smaller then in theAs-delivered condition (Figure 5).

(d) Scatter of Frocerties within a Sheet

Extensive tests withina sheet ha.ve shown that the Coefficientsof Variation on tension and-compressiva moduli in the longituainal

and transverse directions vary from 1$ to 3%, so that individualtesting of sheets is a satisfactory mesno of control. The Coefficient 'iof Variation on DPN numbers varied from ij to 4%; the dirction orindentation affects DW values in the se sense as direction ofloading affects ft values.

L

I-6 -

- 6- 4."

(0, :ffects. of'Pretrain Prior to "adlug Recoverr *

Tests on-sateridl- given,3% tensile prestrain followed by a"Modulus Recovery" titatment havo shown that the neea to include

'fosming eff6cts when considering design str6ngths is not fullyelimnated by introduding "Modulus RSe'very";:

-

(i) longitudinal prestrain. Including the prestrain has littleeffect on the longitudinal tension or compression propertiesafter "iodules'Decsvery"

(ii) transverse prestrain. Including the prestrain has littleeffect on the transverse compression properties after "ModulusRecovery",, but the effect o the trnaverss tension propertiesis approiinately to double the increases in t1 and ft due to"Moduluz Recovery", apparently without impairing the elongation(compare Figure 1- vith Figures 3 and 8).

(f) Effects of Low Temoerature Treatment Prior to "Modulus Recovers"

There is some evidence to suggest that a low temporaturetreatnent at, ssy, -50o0 will increase the effect of a subsequent"Roulus Recovery" treatment, but it is not conclusive.

(g) Effect on Distortion

In thicker parts (16 swg., say) the distortion produced by"Modulus Recovery"'is small. In thinner parts (22 sieg., say),however, distortion is ,sufficient to require subsequent correctionif serious assembly stresses are to be avoided; the effect of thiscorrection on properties is removed by applying a zecond "ModulusRecovery'

treatmnt (this second treatment usually producs some

further distortion which thia-Compny would correct without further"Modulus Recovery", accepting aay resultant loss in property).

07. .PORMMg

- 07.01 At Bristol Aircraft Ltd.

Stretoh-forsing was originally selected on the basis of somesatisfactory operations on sheet-rolled material at the lower endof the VtD.i66 strength range. Uowever, despite extensivedevelopment trials, strtch-Coring of strip-rolled material andthe ma~ority of, sheet-rolled material subsequently provedLmpraotical;m this seems explicable in teens of the shapes of thestress-strain curves to failure (see Figure 2), the 'flat top't$oes not pezrittln8 atretch-foring.

Farnham rolli)g followed by wheeling has been used success-fully for for ing severe single curvatures (also including slightreflex double curvatures) aiid does not son to produce much changein properties. To avoid minor surface damage of the rolls vichsight later imprint on isft surfaces (of, e.g. aluminiu alloys)it has been found satisfactory to Farnham roll DTD.166-typematerials betven aleninium alloy sheets which protect the rollz.

Bond radii down to Zt have been produced by "rubber bolster"press fooming, and by using female rubber dies in brake pressforming, provided special care is exercised on tool design.Seeoion rolling down to 2t has also been successful but onl, sofar on,s laboratory scale and-has not yet been proved asaprodubtion process. Dimples can also be produced in the material,but again need special tool development.

~Ar!

Ie

.Whn DD. 6-tpe ateial ar- oke to hardnasses in"eX~eS of350/70 DN (a coud oqur in dimpling), stress-

corision troubles are thought to be liable to occur; to avoidthese possible troubles, a stress-relief ( ich is provided by theModulus Recover ' treatments) is considered to bc most advisable.

07.02 At Fairey Aviation Co. Ltd.

The use of matched tools en a power press has been foundnecessary for producing details such as I'angea ribs, but theSfiish is not zuitabole for subsequent spot Yielding. Normal

rubber prae forming techniques we re inadequate forfoorming theaterial, and hand foxming was not practicable in material thickerthat 20 hcg.

~08. ETZABILITY

P8.O1 Fuddle Volding

The "puddle welding" process has been developed by Bristolsfor welding through MD.166-typQ materials either into ITD.i66-typeor into .448.-type maerialz (see pare. 00 : Introduction). It isan arson-arc process using a tungsten electrode but not involvingpressure; there is full penetration of the upper sheet by theweld pool, and partial penetration of the lower sheet (it say beused also for welaing more than 2 sheets). The gap between thesheets at time of aflding must be restricted, as increased gapsresult in reduced streongt; gaps of no more than 0.002 incheshave been required by Bristols, and they necessitate both accuratefoirting before solding and stiff gigs with power-holding.Individual welds are used rather than continuous runs, to reducedistortions.

"Pudle welds" have shown good sheer strength and consistencyand tensieon strengths of the same order. There appears to beconsiderable energy absorption at failure, when the weld nugget isgenerally pulled cut from a shoet. heat treatment after weldinghas not been considored necessary.

Inspection of welds by radiography is often difficult, due to:-

(i) accessibility problems, snd

(ii) difficulties of interpretation - e.g. cracks can be detectedbut inadequate penetration is nAt shoe up.

It has been foun", however, that visual examinatton of theback of the wold provides an excellent moans of identifying badwelds (the back of the weld shoas coloured zones produced byoxide fis oZ varying thickness); a reweld procedure has beendeveloped to permit repair.

On batch of shest-rollex cDll66-typo terial i a found toexhibit abuoral waeling characteristics; tests on severalhundred other sheet-rolled and strip-rolled batches have notreproduced this condition (neither have batches specialy ther anufactured to check extrenes of' chemical composition).' However,

i all material is now checked cn receipt to ensure non, el weldingcharncteristics.

=802 spot Velding

Test data have been obtained by Paireys on the spot wecldingof oththe"D~erProperty Level Materi (DTD.i66) =n4 then

| ~~~~"Higher'Prorty Level llatcrlaV, FS.8) Although the...]

interpretation of the results is, as they emfhasise, complicatedby variations in the welding process, the following conclusionshave been drawn:-

(a) Although Ps/t of about 35,000 lb./in. was obtained wItith171.166, only 20,000/25,000 lb./n. was obtained vth PSTS3183.

(b) Tension strengths were slightly higher than shear strengths.

(0) The presence of a spot weld reduced the static proof andultimate strengths or the basic sheet materials by up to I%,and the endurance limit at 1O x 10

6 cycles by sore 10% to

(d) Shear tests in fatimAe p (i ± j) wroduced failure at 10 x 106cycles vhen P = 9% mean static failing load in Mx0.166 and15% n-an static failins load in PZIS.183.

(e) More linited evidence suggests that tension tests in fatigueP (i ± 1) produced failure at 10 x 10 cycles when P wasabout 2% to 24 of the mean static failing load.

0o. OORcOSIO MaSST'nm

At worst only slight local pitting was fonud by Fareys when samplesof D2D.166 material were exposed for 150 days either to local industrialatmosphere or to tlic-daily intermittent salt spray corrosion conditions.

10. CO05wsri

Although lrther information is still required for all the implica-tions of the use of WTD.166-type sneet zaterials ror aircraft structuraluses to be fuliy evaluated, present data suggest that these materials mayhave considerable advantages for certain types of application.

L -- L

i TABME i

Content: %; lment DTD.S6.B S,520 Ons FiS.183f BAC.A.1038

Min. la x. Lin. Yax. Min. Nax.

Carbon 0 . 25 o.1 6 O .15

rri= i2.00 - j 6.0 20.0 17.0 19.0,ickel 6.0 20.0 7.0 12.0 7.0 10.0

Silicon 0.20 - 0.20 - 0.20 1.0

Yansanesc - 1.00 - 1.0 - 1.0

Sulphur - 0.05 0.045 - 0.045

phosphous - 0.05 - 0.0545 - 0.05

'itanitn optionat - 5 X C" - 5 x C -

Niobium optional - 10 x Cm - - -

Tungsten optional - optional - - -enU optnal - oton - -

I n otul optional

Copper optional - optional - - -

Vanadium optional . optional - - -

j In S.520 the titsnium and niabiun additions are alternatives.

.otes 1. It has been suggosted by Firtn-Vickers that wnganese contents- of all TID.1 46-type zatorials Ssould be increased from 1% to 2%

max, It is considered that thin chsnge (tnich could permit areduction In nioxel content) should not cause much change inmechanical properties, other than inoreaain3 the tl/ft ratio inthe heavily cold--,ored acondition. iritols, however, resistedthe proposal 1or opecial applications because of the volume ofcheek toestin involved. Another user also resisted the proposalbecause, in applications where contact with hydrogen peroxidenight oceur, the hireer monganese content might be unacceptable.

2. So far as is knoen, niobiu has only recently ocen u.edextensively in this country instead of titaniwc for AtabilisingDD.66-typo m.tcri*,I againmt eld dccay. Loicer, Firth-Vickers

are intondinS to use niobium instead o' titaniuz in the future

for gI ral annufacture because e the improvement in surface•:inis ,hidi woul2 result; it is expected that thas would not

# result in any chanes in boajo nac.anical properties, but theresponse of niobium-otabillscd material to '!odulus Recovery" isnot kno;m. It is belioved that attempts in the U.Z.A. se yearsago to u~e niobium instead of titanium led to some for of troublebut no direct evidence has been found.

4 j

I ABIR *1

SPBOIAL PE221P11-:S V BAC.A. SFCIPICATION3 POR

DTD. I St-lIPS KVA7RUO,

Aplcto 1 Specification ~ §f4Fcial Rocuirenenta

Purchase f Arom' C. . 1038 1. Chemcial cao=eition restrcted oYirthl-rickets selected ranulooturens' r wge.

Only strip-rolled; sheet rollingr rohibit ca.

13. Clos cIloneso tolerance control.

F4. High rechanical proerties.5. Flongation values to be obtained for

I alerus 12 ow,. end thinpiec.

6. Blank matrial required with eac

"parcel" for subsequent testing by user.

Aircraft use BA.A. 1021 1. Conversion iron .C.. 1038 only.

2. .,dditlos thicnes tolerance control.3.lato), , equLs "Kodulu Rcecovery' heat

treatment (one of two types to be

sele"ced) after ma3or forming but beforeassembly; ooienu f ,r checki 3propertie, fcer scat treatment extracted

• lon~tuizsafly.

4 . B, requir-.ont after "Nodulus R,%covcry".

5. Li'j;r t1 and f, requIrement3 afterI "Eodulus recovery" (t/f t = aircraft

proof/ultirate ratio).

6. 6 elongation rcquircment aftor "ModulusRecovery".

7. ruddle-wldability daonstrated by shearand nrlsing teats.

B... 1061 1.11 requireaents of BA.- 1021 except '41'

Non-aircraft use EC..I02 M2 1. Conversion from BA...036 only.(e.2. :od )

2. Pulale-weldability demonstration byshiar an prising tests

K.4276

L~.. __ _ ___4171

Z -H. WI.N~

0~ THICKNE55 VAATION5 AQI&D IN BACA 1038 ~CL Na-Ar MA "' ~ * ',AAO At f CM

ALL RESULTS AM M'UG SMP-MM.EO iSWXM 2A-6"WCC

+3 ATiMtE 'O

t2 SHEE

0 oa 04 oo6_______U~ssIN

A 0A EWE

*i4ao -**EMM

_________ ___ __ ______ ____ __ E 1______________________________ (84a___ _____ _________________ ___________

FIG. No

2-. YPICAL TE6SAJCR OFJLE

I ~ FO0OTD 166-TYPE MATEIA15 -IN TENSIONCODToN A5*,Fl-U%)DeEcnoN. LirxGITuONAL

''I-AU. QMVFS AREPOF TlIG INM

ui

LU

- 60

ko t-ROLLM-

Al.L a~ev" WE

.20

mi

1. ____________________0__

a 10 20

FIG. No.'

- > TENSION'-PZOMZRTIES OF DO16-PE MTEZA-U'L

do

600

La 9- 6o 70

Mi

LI~ 60 b 700 6o 70ft

z

10D

MA 2

0 0t~~ ~ do 701o60

MOM~ WH6M LWS AME X)0ftE Wf "MU~dA~ Aft ONW~

o0 Q MnMDXD r 0 INODI -0M T

r.4 p'or V:SMSV AN l~biI.Wlft MK"-

z

"FIG. No.

z.~> DIRECTI&4AL VAZLATIOM OF M45ENANCMPE6

'PROPERilES OF. DID.166-IYPE&MTERIALSCao-.A5 ]DUVeReb

LONE0 ______

o s1RhP0U.ED

Tti~K

LA

S11 .24 CT,*

26ao 20 O 5 6o0C.

* 0, E IO4

SIRW1

7 3111 26$

x +/

2.6 2m 4O ~ 0 50 6o

30o

/ 20

60

R +

+

50 60. 7~ 20* 1 3

woTO. uwINs. DZwkS IN 1ivw0L CIAPI4 AR INNCI OIOC~

L4 POW#4 ROWROIt ~MM QRP1L$ fMO A SW6rX

-~ ---------a FIG. No: ~

zRELION BEtWEEN COMPRE%6lON,& TEN510N,

MME50, -DffAATEI5

Co~om4. -As. D-uOeew

E&F,:iobww ts./os/#i

Losd, LANG

A -A/

i:'

24 + b 2 0

0 2 z6 ze30 hO 3

z 4,0 60

2s

UJ 26 A

26 28 30lo AO 3

MM W4EM I.NES-ARE MW" N TM G AI~ R W

.j EAC o RSW -mfa=fRATl

zI

'd FI. a

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A~ i-

w 26Y

u-C2' 2 82 0 4

- 2 Eo'aw ,T N/I

IM 26

30

70

600

*OM UNSWW* 04 MA 0WWMM'

3CZ 7P.

_ _-

FIG. No. 7

4 ~ ~' EFFECTS OF 'MODUW5 M'QE~ HEAT -~TMENTL~ ON RM.J5! PMOP2TIE5 OF -DTD.166-TYPE MATERAL5

4, A Z~5/4e.

~ 70 70

Y/4

-. 29' 30 32 50 Ao 50 60A

0

ffi E,'Bw1

+ tC TomsAm

70Mi

V Vg60

0~ ~ 0

x 28~ 50 -u

0-0

A 30

2.6 28 ~ 0 x. 0 d

00-3

6o 070 7 01z. mjt/mssbAW KTWMa""A-CN.fImob-

J.. 20"m ew TI SDO O I/RENMWRM O ML

- -FIG. No. 8

7A16 MO~t I -- D.Ijl~t~ MATItdIM5

~~ ~514EET-3~L

-A T Aom /ZW

70 aC 5O/ R

60" 60E

0+

usX

6' 70 80

10

705 u0 ?0 a

010

1.15027 10 PNICI1 I

M~i~V~tT ~4T~ 4 I i~JM.~~r ~uI

FIG. No.

0OG IN0~2w

J9 +WEE.O UD16j MTERW,5'

Co*tmo .mMb wRov kT-.~m

60

~g 28 0

a-x x

2 28 1?-,2 40 30 60 70'

uJ'

0'

U 6

2. 4-0 26 2 1 ~ L k ~ 5 0 7

U0

MI .0 60 7 0 o Rz2

LN WA Wr *SSA4 W 1WW~e OEAC PO I OVE&MMFMeWM5 I A 90

PFIG. Nob

PKOP&TM5 OF;DM.66-jNPE-MATERKA5

,o A5arc/zv.

~~0e t.L&TONS/N2

IL' e, / T,*~

04 26 40

ccoI

ins I /I

24 ,26 28 40 50 69

LUY4 70

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Defense Technical Information Center (DTIC)8725 John J. Kingman Road, Suit 0944Fort Belvoir, VA 22060-6218U.S.A.

AD#: ADB193852

Date of Search: 8 Sep 2009

Record Summary: DSIR 23/27631Title: DTD 166 Type Austenitic Chromium - Nickel Steel Sheet: A Summary of PropertiesAvailability Open Document, Open Description, Normal Closure before FOI Act: 30 yearsFormer reference (Department) S&T Memo 12/57Held by: The National Archives, Kew

This document is now available at the National Archives, Kew, Surrey, UnitedKingdom.

DTIC has checked the National Archives Catalogue website(http://www.nationalarchives.gov.uk) and found the document is available andreleasable to the public.

Access to UK public records is governed by statute, namely the PublicRecords Act, 1958, and the Public Records Act, 1967.The document has been released under the 30 year rule.(The vast majority of records selected for permanent preservation are madeavailable to the public when they are 30 years old. This is commonly referredto as the 30 year rule and was established by the Public Records Act of1967).

This document may be treated as UNLIMITED.