UNCLASSIFIED

AD26"2 ,407AD20

ARMED SERVICES TECHNICAL INFORMATION AGENCYARLINGTON HALL STATIONARLINGTON 12, VIRGINIA

UNCLASSIFIED

NOTICE: When government or other drawings, speci-fications or other data are used for any purposeother than in connection with a definitely relatedgovernment procurement operation, the U. S.Government thereby incurs no responsibility, nor anyobligation whatsoeverj and the fact that the Govern-ment nay have formulated, furnished, or in any waysupplied, the said drawings, specifications, or otherdata is not to be regarded by implication or other-wise as in any manner licensing the holder or anyother person or corporation, or conveying any rightsor permission to manufacture, use or sell anypatented invention that may in any way be relatedthereto.

DMIC Report 156July 26, 1961

DESIGN INFORMATION ON AM-350c.

c-) 7.-'STAINLESS STEEL FOR AIRCRAFT AND MISSILES

DEFENSE METALS INFORMATION CENTER

Battelle Memorial Institute

Columbus 1, Ohio ,ASTIA

A SP T I A

71

DMIC Report 156

Juy 6 16

DESIGN INFORMATION ON AM-350 STAINLESS STEELFOR AIRCRAFT AND MISSILES

by

R. J. Favor, 0. L. Deel, and W. P. Achbach

to

OFFICE OF THE DIRECTOR OF DEFENSERESEARCH AND ENGINEERING

DEFENSE METALS INFORMATION CENTERBattelle Memorial Institute

Columbus 1, Ohio

ACKNOWLEDGMENTS

The authors wish to thank Mr. D. A. Shinn, Air Force Mem-ber, Federal Aircraft Design Criteria Committee, Structures Sub-committee (formerly the ANC-5 Panel), for perirission to publishthe design curves generated on Air Force Contract No. AF 33(616)-6410.

Most of the detailed information on specific alloys has comefrom material producers and published papers by producers, fabri-cators, and users of these alloys. References on this informationare included in the bibliography.

TABLE OF CONTENTS

Page

SUMMARY ................. ............. ............. .... .......... .

GENERAL COMMENTS ................... ................................ 3

MANUFACTURING CONSIDERATIONS ................................. 3

Heat Treatment a I Forming ..................... ........................ 3Forging .......................... ................................. . 4Welding .......................... .............................. .* . . 4Machining ............................ . ............................... 5Corrosion Resistance .............. ....... .......................... 5

BIBLIOGRAPHY ..................... ................................... 7

APPENDIX A

PROPOSED DESIGN-ALLOWABLE STRENGTHS FOR MIL-HDBK-5 ....... ......... A-i

APPENDIX B

SUPPORTING DATA FOR ROOM-TEMPERATURE ALLOWABLES AND ELEVATED-TEMPERATURE DESIGN CURVES ................ ....................... ... B-i

DESIGN INFORMATION ON AM-350 STAINLESS STEELFOR AIRCRAFT AND MISSILES

SUMMARY

The information contained in Appendixes A and B to this report waspresented at the Los Angeles meeting of the Structures Subcommittee(formerly ANC-5 Panel) of the Federal Aircraft Design Criteria Committee,November 15, 16, and 17, 1960.

Tentative room-temperature design-allowable strengths and elevated-temperature design curves for short-time ultimate tensile strength, tensileyield strength, compressive yield strength, ultimate shear strength, bearingultimate strength, and bearing yield strength are presented. These curvesare based on a number of published and unpublished reports and papers.Data are summarized in Appendix A in the format recommended for MIL-HDBK-5 (superseding ANC-5), Strength of Metal Aircraft Elements.Appendix B contains summary plots of substantiating data from whichdesign-allowable strengths were derived.

3

GENERAL COMMENTS

AM-350 is one of the semiaustenitic precipitation-hardenable stain-less steels. In the annealed condition it is soft and ductile and has manyof the desirable forming characteristics of.the austenitic stainless steels.

When hardened, it is strong and hard like the martensitic stainless steels.

The primary application for AM-350 is for parts and assembliesrequiring high strength and oxidation r~sistance up to 800 F. It is availablein sheet, strip, foil, welded tubing, billets, bars, forgings, and wire.

The AM-350 analysis is covered by the AMS and MIL specificationslisted on page A-3, Appendix A.

MANUFACTURING CONSIDERATIONS

Heat Treatment and Forming

In the annealed condition AM-350 is essentially austenitic (approxi-mately 5 to 15 per cent delta ferrite) and has forming characteristicssimilar to the AISI 300 series stainless steels. However, it does have ahigher rate of strain hardening. Hardened AM-350 is martensitic, but doesretain sufficient ductility to permit limited forming or straighteningoperations.

Condition H (see Table 1) is the most suitable for forming complexparts, and AM-350 is normally shipped from the mill in this condition.Cold forming with Condition H material will cause hardening by martensiteformation in addition to strain hardening in proportion to the amount ofdeformation. Hardening can be minimized by working at 300 F or above.

AM-350 can be fully hardened from Condition H by the double-aging(DA) heat treatment which is accomplished by first aging at about 1375 F andthen at about 850 F. The 1375 F age precipitates chromium carbides fromthe austenitic matrix and alters the composition of the austenite so that theaustenite transforms to martensite on cooling to room temperature. Thesecond age at 850 F tempers the martensite.

Another method of hardening AM-350 is by subzero cooling and tem-pering (SCT). AM-350 in Condition H responds only partially to the subzerocooling so that it is necessary to reanneal to Condition L (described in Table1) before subzero cooling and tempering. Sufficient ductility is retainedafter'the SCT treatment to allow limited formin6 operations. For example,AM-350 (SCT) sheet or strip can be bent 180 degrees over a 3T pin.

4

The designer should be aware that a dimensional growth of about0. 004 to 0. 005 in. /in. occurs when AM-350 is hardened.

A detailed discussion of heat treatment and the interaction of fabri-cating and heat-treating variables is presented in DMIC Report 111, "ThePhysical Metallurgy of Precipitation-Hardenable Stainless Steels", byLudwigson and Hall.

TABLE 1. CONDITIONS AND HEAT TREATMENTS OF AM-350

Condition Heat Treatment Purpose

H Solution treated at 1850 to 1975 F, Formabilityair cooled or water quenched

L Solution treated at 1710 F *25, air cooled Preparationor water quenched for hardening

DA Condition L or Condition H, plus 3 hours Hardeningat 1375 F *•5, air coold to 80 F max.,plus 3 hours at 850 F *25, air cooled

SCT Condition L plus 3 hours at -100 F plus Hardening3 hours at 850 to 1000 F, air cooled

Forging

AM-350 is readily forged. Forging temperatures above Z150 F shouldbe avoided because of the free ferrite which may be formed. Free ferritewill decrease heat-treating response.

Finishing temperatures should be in the range of 1 700 to 1800 F toprevent grain coarsening on subsequent solution treatment and to promotehomogeneous precipitation of carbides. For optimum properties, a con-ditioning treatment after forging is recommended.

Welding

AM-350 can be welded by all of the conventional methods used for thechromium-nickel stainless steels. As-welded AM-350 can be hardened by

the DA treatment without reannealing. For optimum properties, however,postweld reannealing is recommended.

To obtain proper response to the SCT treatment after welding, thealloy must be reannealed at 1710 F *25 prior to hardening.

For a detailed discussion on the welding of AM-350, DMIC Report 118,"Welding of High-Strength Steels for Aircraft and Missile Applications", byMishler, Monroe, and Rieppel, is recommended.

Machining

AM-350 has a very high rate of work hardening as well as a tendencyto be soft and gummy in the annealed condition. For best machinability,AM-350 should be in the equalized and overtempered condition. This con-dition is produced by heating to 1425 F, cooling to room temperature, andovertempering at 1000 to 1100 F. This gives a hardness of approximatelyRockwell C35, and the alloy then machines like low-alloy steels of similarhardness. Finishing operations may be performed in this condition ifproper allowances are made for growth which occurs upon reannealing andhardening. If extreme dimensional accuracy is required, finish machiningshould be done in the hardened condition. Machining recommendations asreported by Metcut Research Associates are presented in Table 2.

Thermal machining of AM-350 is currently under development.Nelson, Scott, and Gassner( 1 9 ) report that face-milling tests on induction-heated AM-350 (Bhn 380 or about Rockwell C41) have shown tool life at1000 F to be about 100 times normal. On the other hand, turning tests onAM-350 (Bhn 400) at various temperatures up to 900 F have shown only afive-time improvement in tool life.

Corrosion Resistance

AM-350 shows good corrosion-resisting properties in ordinary atmos-pheres and also in' a number of chemical environments. However, differentcorrosion behavior results from the two hardening treatments, SCT and DA.The greater precipitation of chromium carbides during the DA treatmentcauses some susceptibility to intergranular corrosion. For this reason, DAis less desirable than SOT where exposure to certain severe environments isexpected.

A literature survey and limited investigation on the susceptibility ofAM-350 to stress corrosion is reported in WADD Technical Note 60-95,"Stress Corrosion of Notched and Unnotched AM-350 Alloy", by Ault. Aultconcluded that "stress-raisers such as mechanically induced notches do nothave an appreciable effect on the susceptibility of the alloy to stress cor-rosion cracking. Rather the more important factor is local surface defectsor inhomogeneities in the material. It was also found that concentrationcell corrosion may be an important consideration for AM-350."

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BIBLIOGRAPHY

(1) Kurg, Ivo M., "Tensile Stress-Strain Properties of 17-7 PH andAM-350 Stainless-Steel Sheet at Elevated Temperatures", NACA TN4075, Langley Aeronautical Laboratory (September, 1957).

(2) Roberts, D. A., Roach, D. B., and Hall, A. M., "Physical andMechanical Properties of Nine Commercial Precipitation-HardenableStainless Steels", DMIC Report I12 (May,- 1959).

(3) Stein, Bland A., "Compressive Stress-Strain Properties of 17-7 PHand AM-350 Stainless-Steel Sheet at Elevated Temperatures", 'NACATN 4074, Langley Aeronautical Laboratory (August, 1.957).

(4) "AM-350 and AM-355, Alle~gheny Ludlum Precipitation HardeningStainless Steels", Allegheny Ludlum Steel Corporation Technical DataPublication (1959).

(5) "Design Data for Precipitation Hardening Stainless Steels", ProgressReport MMT 12-58-6, North American Aviation (December 15, 1958).

(6) Brisbane, Alton W., "Mechanical Properties of AM-350 and AM-355Stainless Steels", *WADC TR 58-672, Materials Laboratory, WrightAir Development Center (February, 1959).

(7). Tiktinsky, M., "Summary of High Strength Steel and Titanium AlloySheet Products", Report No. 12957, Lockheed Aircraft Corporation(March 28, 1958).

(8) "Engineering Properties Precipitation Hardening Alloys AM-350 andAM-355"; Technical Data Sheet, Allegheny Ludlum Steel Corporation(no date).

(9) "Effects of Stretching at Various Stages of Heat Treatment on Tensileand Compression Properties of Precipitation Hardening StainlessSteels", Report No. LPA.68-160, Part II, North American Aviation(April 17, 1959).

(10) Dedman, H. E., Wheelahan, E. J., and Kattus, J. R., "TensileProperties of Aircraft-Structural Metals at Various Rates of LoadingAfter Rapid Heating", WADC TR 58-440, Part I, Southern ResearchInstitute (November, 1958).

(11) "Evaluation of Precipitation-Hardenable, Martensitic Stainless Steel",North American Aviation, Inc. (September, 1957).

(12) Ludwigson, D. C., and Hall, A. M., "The Physical Metallurgy ofPrecipitation-Hardenable Stainless Steels", DMIC Report I 1I (April 20,

1959), OTS PB 151067.

9 and 10

(13) Mishler, H. W., Monroe, R. E., and Rieppel, P. J., "Welding ofHigh Strength Steels for Aircraft and Missile Applications", DMICReport 118 (October 12, 1959), OTS PB 151074.

(14) Fiorentino, R. J., Roach, D. B., and Hall, A. M., "Heat Treatmentof High-Strength Steels for Airframe Applications", DMIC Report 119(November 27, 1959), OTS PB 151076.

(15) Allegheny Ludlum Data Sheet 90-1758-R, "Elastic Constants of AM-350and AM-355".

(16) Allegheny Ludlum Data Sheet 125-71659-350, "Shear and BearingStrength of AM-350 at Room and Elevated Temperatures".

(17) Allegheny Ludlum Data Sheet 86-111457-350, "Room and ElevatedTemperature Tensile and Compressive Properties of Type AM-350".

(18) Allegheny LIidlum Memorandum, "AM-350 and AM-355 Cleaning".

(19) Nelson, W. D., Scott, J. A., and Gassner, R. H., "Trends in Aero-space Manufacturing", Metal Progr., 79 (4), 106 (April, 1961).

(20) Reinch, Wayne A., "Metals and Fabrication Methods for the B-70",Metal Progr., 79 (3), 70 (March, 1961).

(21) Ault, Robert T., "Stress Corrosion of Notched and Unnotched AM-350Alloy", WADD Materials Central, WADD TN 60-95 (May, 1960).

(22) Metcut Research Associates, "Machining AM-350, Solution Treatedand Aged to Bhn 444", Metal Progress Data Sheet, Metal Progr. 79(5), 96-B (May, 1961).

APPENDIX A

PROPOSED DESIGN-ALLOWABLE STRENGTHSFOR MIL-HDBK-5

Presented at the Z0th meeting Qf the ANC-5 Panel on"Strength of Metal Aircraft Elements", held in LosAngeles, November 15, 16, and 17, 1960. These data,subject to approval by the Panel, will constitute a re-vision to MIL-HDBK-5, dated March, 1959.

A-i

APPENDIX A

PROPOSED DESIGN-ALLOWABLE STRENGTHSFOR MIL-HDBK-5

Introduction

Design-allowable strengths for AM-350 stainless steel products in

various conditions have been proposed for amending the March, 1959, issueof MIL-HDBK-5, Strength of Metal Aircraft Elements. When approved,these data will provide guidance to designers concerned with airframe andmissile structures.

The following glossary of terms is supplied for those readers notfamiliar with MIL-HDBK-5:

Ftu - Guaranteed minimum room-temperature ultimate tensile

strength

UTS - Typical or average ultimate tensile strength

Fty - Guaranteed minimum roomr-temperature yield strdngthat 0. 2% offset

TYS - Typical or average tensile yield strength

Fty -- Minimum yield strength in compression at 0. 2% ofiset

CYS - Typical or average compressive yield strength

FPu - Minimum ultimate shear strength (may be pin shear, punchshear, or panel shear; refer to MIL-HDBK-5)

USS - Typical or average ultimate shear strength

Fbru- Minimum ultimate strength in bearing at a specified e/D ratio

UBS - Typical or average ultimate bearing strength

Fbry - Minimum yield strength in bearing at a specified e/D ratioand a specified hole elongation value

BYS - Typical or average bearing yield strength

L -- Longitudinal

S~A-2

T - Transverse

e/D - Ratio of edge distance to diameter of pin or fastener holeused to determine bearing strength

Is,. -- Per cent elongation in uniaxial tension, usually in 2 inches

E -- Modulus of elasticity in tension

EC -- Modulus of elasticity in compression

G - Modulus of rigidity

w - Density

C - Specific heat

K - Thermal conductivity

Coefficient of thermal expansion, mean.

Additional definitions and nomenclature and derived relationships will'be found in MIL-HDBK-5.

A-3

ITEM 60-14. ATTACHMENT TO THE MINUTES OFTHE ANC-5 PANEL MEETING

Subject: Tentative Design Data on AM-350 Stainless Steel

2. 2. 4 AM-350 Stainless Steel

2. 2. 4. 0 Specifications, Comments, andRoom-Temperature Properties

Specifications. Material specifications for AM-350 stainless steelare presented in Table 2. 2. 4. 0(a).

TABLE 2. 2.4. 0(a). MATERIAL SPECIFICATIONS FORAM-350 STAINLESS STEEL

Alloy and Condition Specification Type of Product

AM-350 MIL-S-8840 Sheet and stripAM-350 AMS 55S4 Tubing, seamlessAM-350 (equalized and AMS 5745 Bars, forgings, and

overtempered) forging stock

Comments. The primary application of AM-350 is for parts requiringhigh strength and oxidation resistance up to 800 F. AM-350 is readilyforged, welded, and brazed. The designer should be aware that after aforming operation, it is usually necessary to reanneal AM-350 before thealloy can be hardened and also that a dimensional growth of approximately0. 004 to 0. 005 in. /in. occurs during the hardening treatment. AM-350 canbe hardened by subzero cooling and tempering (Condition SOT) or by doubleaging (Condition DA). The properties in the SCT condition are higher thanthose reported for the DA condition, but if the SCT method of hardening isselected it is necessary to precede it with a 1710 F annealing treatment incases where the material was previously annealed at 1850 to 1975 F (Con-dition H as supplied by the mill).

Room-Temperature Properties. The room-temperature properties ofAM-350 in the double-aged (DA) and in the subzero cooled and tempered(SCT) conditions are shown in Table 2. 2. 4. 0(b). The ultimate tensilestrength, tensile yield strength, and elongation values are taken from thematerial specifications. Other properties are derived from test data.

A-4

The elevated-temperature properties of AM-350 are presented in thefollowing sections:

Section Material Condition

2.2.4.1 DA

2.2.4.2. SCT

A-$

TABLE 2.2.4.0(b) DESIGN MECHANICAL AND PHYSICAL PROPERTIESOF AM-350 STAINLESS STEEL

Alloy AM-350

Sheet, strip, bars,; Sheet, strip, bars,Form ' forgings, and seamless and forgings

_tubing

Condition DA SCT

Basis Minimum specification values and typicalvalues adjusted to minimum

Mechanical PropertiesFtu, ksi 165 185

Fty, ksi 135 150

Fcy, ksi 148 170

Fsu, ks! 112 123Fbru ksi

(e/D = 1.5) 260 295

(e/D = 2.0) 345 372Fbry, ksi

(e/D = 1.5) 198 230(e/D z 2. 0) 230 260

e, per cent 1 0 (a) 1 0(a)

E, 106 psi 30.0

Ec, 106 psi -

G, 106 psi 1.

Physical Properties

W, lb/in. 3 Condition H 0.286Condition SCT 0. 282

C, Btv/(lb)(F) 0. 12 (32 to 212 F)

K, Btu/[hr)(ft2 )(F)/ft1 8.4 (at 100 F); 11. 7 (at 800 F)

a# 10-6 in.'/in. /F 6.3(70 to Z31 F); 7. 2(70 to 932 F)

(a) Per cent in 2 biches fog sheet, strip, and tubing; pas eeen in 4D for bars and forgings.

A-6

2. 2.4. 1 Double-Aged Condition (DA)

The double-aged condition is developed in AM-350 by starting withthe solution-treated condition (either Condition L or Condition H), aging at1375 F for 3 hours, air cooling to room temperature, and then a secondaging at 850 F for 3 hours and air cooling to room temperature.

Elevated-temperature data for the double-aged material are presentedin Figures 2.2.4. 1. 1(a) through 2.2.4. 1. 6(b).

A-7

100fExposre to 1/2 hr

I --

60T IIII

I TI.

T0UT

0 ~~~ ~ -0 40 60 80 -00 -20 140 -600

0

0 0 46'6080 001 4010

100

Tempeaturh FttrprtrFigu~~~~~~re' 2....() fet0 m Exposure up toe 1enshr

yiel stTn t -~ -f -A-- -35--stainless~~~ 1te ( Tube-I e

A-8

0 00 40 600 U00 I000 1201400 LIL1600Tempenture Fttrprtr

~1gue 2,.4.12(a) Ef~ot o tmExposure up to 1/ ho~esa

600

A-9

sIo

'II

0 20 40 600 800 1000 1200 1400 1600Temnperature, F

Figure 2.2.4.1,4. Etffect or' temper'ature on tbie tensile andGoampessivg modulus (S and L~c of Ulvf350stafinlss steel (doubl.~aed).

A-10

200

00

I I f

A-li

200

L LI f I I 10-- -

I SIrI I, I OOI I rLI" l.

10.

A-12

6. 2.4.2 Subzero-Cooled and Tempered Condition (SOT)

The SCT condition is developed in AM-350 by starting with a solutiontreatment at 1710 F (Condition L) and then subcritically transforming at-100 r followed by aging at 850 to 1000 F.

levated-temperature data for the SCT material are presented inFigures 2. 2.4. 2. 1(a) through 2.2. 4.2. 6(b).

A- 13

100 .. . .. ..

Ev Stnt Ex ofureupmtotso

* Ii. so0

.. .. .. .

90

0 200 400 600 .800 1000 1200 1400 1600

Temperature, FFigure 2.2.4..2.1(a). Ef~ect of' temperature oni the teUmtsie

tenilel arength (Ptu~) of AM-350stainless steel (3SCT).

A- 14

IIF-

0 200 400 600 800 1000 1200 1400 1600

Temperature,, F

Figure 2.2.4.2.2(a). Effect of temperature on the compressiveyield strength (" I) of AM-350- stae-Wesosteel (SCT).

100+111IIT IA- 'llStrength at emperature

I I4IF

T TI T IT I

0 20 400 600 800 000 200 14001I0TempTraturIT

60 ur T....() EI eo of Ieprtr oT t Imtsha tef F)ofAI3O tilsste1 FCT)r

100

Tempeature FtV~~i~re2..4..3a) Zteo. emeratUre onth utiat

Ii. T110

T --,-

0 200 400 600 800 1000 1200 1400 1600

Temperature, FFigure 2.2.4.2.3(a). Effect~ of temperature on the betiarte

yeaied strength (Fbi,.) of AM-350stailress steel (SG~)

A- 16

40

20. 00 600 OW01000 1201400 1600

Temperature,F

CoWrObsive modulus (I n OOfA-5SV&AJA1881 stool (S CT).

A- 17

200

160, O

l i l 1 1 * i 1 'r 1 1 4 0 -

.0 -in 0.0 In./in

Figure~~~~~~~~A .22.()*lpIca esl teeszancre oAM35 stInlu te ST tro

el1te1emeatrs

A-Is

I1lol201 11

00I

Jill[n I.0 ItsIn

For AM- 1 tils 1t. (# T at rooII m II

anlt elvaedllraur

i s II I l

APPENDIX B

SUPPORTING DATA FORROOM-TEMPERATURE ALLOWABLES AND

ELEVATED-TEMPERATURE DESIGN CURVES

I 7

SUPPORTING DATA FOR* ROOM-T EMPIEATURE MM"HN RMA~lo-PROPERTY

-D3IM N ALLOWABLES FOR A51-350 (DAt

Source

AMS w 165 ket

Fty n 135 kel

Compressive Yield

NACA TN 4074, CYS = 164 kait (average of L and T tests)4075

UTS a 182 kaL

F tu 165 kst (guaranteed minimnum)

F Y x F 163 CYS . tta18.x 165 a149 kst

Ratio of *.I49 a. ,0.90* Ftu 165

Allegheny Ludluzm CYS r. L74.5 kst

UTS w 195. 5 ksi

r,,, a 165. 0 ksi (guaranteed minimum)

CYS 174.5

UTS 195. 5

Ratio of fc..Y -14?7 0.84Ftu 165

Att. 60-14 Ratio of Fcy = 148 g 0. 897Ftu 165

Ultimate Shear

Allegheny ILudlura USS a 12Z.2 kst (average of 4 tests)

UTS a 179. 1 ksi

B-2

rttt a 165 ksl (guaranteed minimurn)

uss xT Ft 1226 2 x 165 112.5 ksi

Ratio of LF----u at 1 2... _5 z 0. 6 85

Att. 60-1.4 atio of w 112 = 0.068Ftu 165

Ultimate Bearing (e/D a 1.5)

WADC TR 58-672 BtJS = 276. 1 ksi (average of L and T tests, heat 25417)

UTS = 179.7 ksi (average of L and T tests, heat 25417)

tu != 165 ksi (guaranteed rninimum)

rbru BUS 6.1 x 165 = 254 ke!u�• x 179.77lx 254

Ratio of . -. - = 1.54S165Ftu

WADC TR 58-67Z BUS = 258. 0 ksi (1 transverse test)

UTS = 159. 9 ks[ (does not mneet spea.)

F'tu 165 ksl (guaranteed minimum)

_Fbru BUxtu x . 258 x 165 * 266 ksiS-U'T ý 159.9

Ratio of Fbru =Z66 =1.61•Ftu 165

Allegheny Ludlum BUS = 285.5 kel

UTS = 179.1 ksi

F = 165 ksi (guaranteed minimum)tu

BUS 285.5Fbr =-Tx x 165 =262 ksi

UTS tu 179.1

Ratio of Fbru 262 = 1.59Ftu 165

B-3

*Atto 60-14 Ratio of.!a uŽ.6 * 1. 575Ftu L65

Ultimate Beating (eJD - Z. 0)

WADC .XR 58-672 BUS * 362. 5 kas (average of L and T test)

UTS * 179.7 kel (average of L and T test)

Ftu = 165 ksi (guaranteed minimum)

BUS 362.5Fbru =B x Ftu-3.x 165 = 333 ksiu UTS 179.7

Ratio of Fbru - 333 = Z. 02Ftu r

WADC TR 58-672 BUS = 344. 0 ksi (average of L and T tests)

UTS = 159.9 ksi (does not meet spec.)

Ftu = 165 ksi (guaranteed minimum)

W. US xF a344 x 165355ksibru UTS tu 159.9

Ratio of Fbru - 355 - 2. 15Ftu 165

Att. 60-14 Ratio of Fbru L.5 = 2. 09Ftu 165

Bearing Yield (e/D = 1. 5)

WADC TR 58-672 BYS = 212. 7-ksi (average of L and T tests)

UTS = 179. 7 ksi (average of L and T tests)

Ftu = 165 ks! (guaranteed minimum)BYS 212.7

Fbr7 =B x "2 x 165 = 196 ksiUTS Ft 179.7

Ratio of Fbr-. = 196 = 1.19Ftu 165

B-4

WADC TR 58-672 BYS a 197. 2 ksi

UTS w 159.9 kui (does not meet spee.)

rtu 0 165" kst (guaranteed minimum)

BYS 197.2Fbry =-' x Ftu =a- x 165 uZ 03 ket

bry US tu 159.9

Ratio of0 jr = 203 1.23

F tu 165

AUegheny Ludlum BYS = 215. 8 ksi

UTS = 179. 1 ksi

Ftt = 165 ksi (guaranteed minimum)BYS 15 8.

r bry a -xP xF a. ;c 165 a 198 ksiUTS tu 179.1

Ratio of Fbry a 19._ 1.20Ftu 165

Att. 60-14 Ratio of I. = =198 1. 20

Ftu 165

Bearing Yield (e/D = 2. 0)

WADC TR 58-672 BYS 252. 0 ksi (average of L and T tests)

UTS = 179.7 ksi (average of L and T tests)

Ftu .165 ksi (guaranteed minimum)

BYS 252.0F -r Sx FtZ -x 165 =Z3lksiFbryUTS tu= 179.7

Ratio of b•y .Fi -- 1.40Ftu 165

WADC TR 58-672 BYS = 222. 7 ksi (average of L and T tests)

UTS = 159. 9 ksi (does not meet spec.)

B-6

Ftu a 165 ks1 (guaranteed rnimuum)

Frbrya BW'S X Jtu a 9.5 ?3 16 w Z30 kstUTS 159.9

Ratio of f a 3 a 1. 39.Ftu 165

Att. 60-14 Ratio of =230 a 1.395Ft 165

SUPPORTING DATA FORROOM-TEMPERATURE MECHANICAL-PROPERTY

DESIGN ALLOWAB LES F•R AM-350 (SOT)

Source

AMS Ftu 185 ksi

Ft7= 150 ksi

Compressive Yield

Allegheny Ludlum CYS = 193. 6 ksi (average of 3 heats)

UTS = 208.4 ksi (average of 3 heats)

Ftu = 185 ksi (guaranteed minimum)

CYS 193.6Fc = UTS -tu .4 x 185 = 171.5 ksi

Ratio of !7 = 171.5 = 0.93Ftu 185

NAA, MPDS Ratio of Fcy 164 = 0. 89-t 185F tu

Att. 60-14 Ratio of Fc7=170 = 0.92

Ftu 185

B-6

Ultimate Shear

Allegheny Ludlum USS * 137. 7 kul

UTS 2 208.3 ksi

Ftu 185 ks| (guaranteed minimumn)

USS 137.7Fs u XS Ftu UZ08. 3- X 185 =1ZZ ksi

Ratio of - su -- u. 0.66185

NAA USS = 140 kit(BTL 30468)

UTS -1l0ksi

Ftu = 185 kst (guaranteed minimum)

USS 140F ="- x F 1-4 x 185'= 133. Sksi

su UTS tu 1

F 123.5Ratio of s__U =---- .6Ft 185

Att. 60-14 Ratio of- - 0.66Ftu 185

Ultirnate Bearing (e/D : 1.5)

WAJD TR 58-67Z BUS = 304. 7.ksi (average of L and T tests, Z heats)

UTS = 193.4 ksl (average of L and T tests, 2 heats)

Ftu - 185 ksi (guaranteed mainimum)

BUS 304.7F.bru = UTS x Ftu = 1-93.4 x 185 = 292 ksi

ofFbru 292

Ratio of =- = 1.58Ftu 185

Allegheny Ludlum BUS = 348. 9 ksi

B-7

UTS = 208.3 ksi

Ftu - 185 ksi (guaranteed minimum)

BUS 348.9Fbru = '3 x 185 310 ksi

Fbru 310

Ratio of -3 1.67Ftu 185

Att. 60-14 Ratio of F u 9_5 z 1.59Ftu 185

Ultimate Bearing (e/D s 2. 0)

INAA BUS = 410 ksi(BTL 30468)

UTS = 210 ksi

F = 185 kel (guaranteed minlmurrm)tu

BUS 410F ru = ý- -x Ftu =4--.1 185 361 kls

Fbru 361Ratio of - - 1.95Ftu 185

Fbru 380

NAA (MPDS) Ratio of - 380 2. 05Ftu 185

WADC TR 58-672 BUS = 392. lksi (average of L and T tests, 2 beats)

UTS = 193.4 ksi (average of L and T tests, Z heats)

F = 185 kst (guaranteed minimum)tu

BUS 392.1Fbru =•--x u- x185 = 375

Fbr 375

Ratio of -u -3 2.02Ftu 185

Att. 60-14 Ratio of Fbru - 372 2. 01Ftu 185

B-8

Bearing Yield (e/D a 1. 5)

WADC TR 58-672 BYS z 237. 2 kei (average of L and T tests, 2 heats)

UTS = 193.4 ksi (average of L and T tests, Z heats)

Ftu = 185 ksi (guaranteed minimrnm)

BYS 237.2

bry UT-S - Ftu 19-3.4

Ratio of Fbry % 227 1.23Ftu 185

Allegheny Ludlum BYS = 272. 0 ksl

UTS = 208.5 ksi

F = 185 ksl (guaranteed minimum)

BYS 272FbI=-T- X u- I? 2 x185 =241 ksa

F 24Ratio of ' br-y = 1. 30

Ftl 185

Att. 60-14 Ratio of Fbry w 230 = 1. 24Ftu 185

-Bearing Yield (e/D = 2. 0)

WADC TR 58-672 BYS = 227. 6 ksi (average of L and T tests, 2 heats)

UTS = 193.4 ksi (average of L and T tests, Z heats)

F ) 189 ket (guaranteed wInimum)tu

BYS 277.6Fbr zr[ x Fttc 1 9 3 Zx 185 265 ksl

Fbry 265

Ratio ofFtu- 18 43

B-9

NAA BYS * 290 ksi(BTL 30468)

UTS =2i0ksi

"Ftu = 185 kei (guaranteed minimum)

BYS 290F =I'• x F - x 185 256 ksi

bry US tu 210

Fbr 256Ratio of - _ 2 = 1.38

Ftu 185

NAA (MPDS) Ratio of Tbr =- = 1.38F 185

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Fbr 260Att. 60-14 Ratio of F----r = - = 1. 40

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Columbus 1. Ohio

Copies of the technical repom listed below amy be obtained fomn DMIC at no om by Government apgeb ad byGovemmem contract, subcoetracto. and their supplieus. Others may obtain copies from die 0ffc of Tedmical 9esylcs,Department of Commercs, Wasdbllngso 25, D. C. See P0 numbers and prices In pareabnm.

DMICSNumber Title

40D Department of Defense Titanium Sheet-lolling Program - Uniform Testing Procedure for Shea Materials,September 12, 1958 (PB 121640 $1.25)

441 Department of Defeme Titanium Sheet-lolling Program - Thermal Stability of the Titalnum sbeet.4oUlas-Program Alloys, November 25, 1958 (Ps 141061 $1.26)

46F Department of Defense Titanium Sheet -. lling Program Status Report No. 4. March 20. 1059 (pN 151065 $2.25)46G Department of Defense Titanium Sheet-Rolling Program - Time-Ternperature-Traiformation Diagrams of

the Titanium Sheet-solling Program Alloys, October 19, 1959 (13 151075 2.296)40H Department of Defense Titanium Sheet-Rolling Program, Status Report No. 5, June 1. 1960 (Ps 161087 82.00)481 Statistical Analysis of Tensile Properties of Heat-Treated TI-4A1-8Mo-1V Sheet, September 16. 1960

(PB 151095 $1.26)106 Beryllium for Structural Applications, August 15, 1968 (N9 121648 $8. 00)107 Tensile Properties of Titanium Alloys at Low Temperature. January 15. 1959 (PN 15106281.25)108 Welding and Brazing of Molybdenum, March 1, 1959 (P3 151068 $1.25)109 Coatings for Protecting Molybdenum From Oxidation at Elevated Temperature. March 6, 1959 (3I 151064

$1.25)110 The All-Beta Titanium Alloy (TI-18V-ICr-3A1), April 17. 1969 (P3 151066 88.00)111 The Physical Metallurgy of Precipitatlon-Hardenable Stainless Stela, April 90, 1950 (3S 15107 $29. 00)112 Physical and Mechanical Properties of Nine Commercial Preolpitation-Hardenable Stainless Stels,

May 1. 1959(3s 151068 88.25)118 Properties of Certain Cold -Rolled Austenitic Stainless Sheet Steels, May 15, 1969 (3S 151069 $1.78)114 Ductile-Brittle Transition in the Refractory Metals, June 26, 1959 (PB 151070 2.00)115 The Fabrication of Tungsten. August 14. 1950 (P3 151071 81.75)1161 Design Information on 6Q-Mo-V Alloy Stels (H-11 and 5Cr-Mo-V Aircraft Steel) for Aircraft and Missiles

(Revised), September 80, 1960 (PB 151072-R 81. 50)117 Titanium Alloys for High -Temperature Use Strengthened by Fibers or Dispersed Particles, August 81, 1989

(P3 1510738 $9.00)118 Welding of High-Strength Steels for Aircraft and Missile Applications, October 12, 1959 (3 151074 $2.25)119 Heat Treatment of High-Strength Steels for Aircraft Applications. November 27, 1959 (PS 15107 $9. 50)120 A Review of Certain Ferrous Castings Applications in Aircraft and MIssiles, December 18, 1959 (3B 151077

81.50)121 Methods for Conducting Short-Time Tensile, Creep, and Creep-Rupture Tests Under Conditions of Rapid

Heating, December 20. 1959 (P3 151078 $1.25)122 The Welding of Titanium and Titanium Alloys, December 81, 1959 (PB 151079 81.75)128 Oxidation Behavior and Protective Coatings for Columbium and Columblum-Bae Alloys, January 15, 1960

(PB 151080 $9.25)124 Current Tests for Evaluating Fracture Toughness of Sheet Metals at High Strength Levels, January 28, 1960

(PS 151081 $9. 00)125 Physical and Mechanical Properties of Columblum and Columbium-Base Alloys, February 22, 1960

(P0 151082 $1.75)126 Structural Damage in Thermally Cycled Reni 41 and Astroloy Sheea Materials, February 29, 1960

(PO 151088 $0.75)127 Physical and Mechanical Properties of Tungsten and Tungsten-Base Alloys, Match 15, 1960 (PS 151084 81.75)128 A Summary of Comparative Properties of Air-Melted and Vacuum-Melted Steels and Superalloys,

March 28, 1960 (PB 151086 $2. 75)129 Physical Properties of Some Nickel-Bease Alloys, May 20. 1960 (39 151086 $9. 75)180 Selected Short-Time Tensile and Creep Data Obtained Under Conditions of Rapid Heating. June 17, 1960

(P 151088 $9.25)181 New Developments in the Welding of Metals, June 24, 1960 (13 151089 $1.25)132 Design Information on Nickel-Base Alloys for Aircraft and Misiles. July 20, 1960 (3S 151090 $8.00)188 Tantalum and Tantalum Alloys. July 25. 1960 (3S 151091 85.00)184 Strain Aging of Refractory Metals, August 12. 1960 (PB 151092 81.75)185 Desin Information on PH 15-7 Mo Stainless Steel for Aircraft and Missiles, August 22. 1960 (3S 151098 81.25)

DUIC

i" Tm ffecM t of Alloying Ilemeuts In Titanium, Volmm A. Constition, September 11, 110(13 151094 $3;40)

186 The Iffect of Alloying 1lemoets In Titanium, Volume S. ehyscdal And 01mmin0 Prepres, DeoematonAd Tranformation Chracs taics, May 29, 1961

187 Daip Information on 17-7 PH Stainless Steels for Aircraft and Minsla, Soptember a. 1O0(P3 1510 1.00)

in6 Availability and Mechanical Properties of Hlgh-Stroth Steel Extusions. October 96, 196(13 I156 $1. 11D18i Melting and Cuting of the Refractory Metels Molybdenum. Columblum. Tantalum, a Toogas.

November 11, 1980 (PS 151008 $1.00)140 Physical sad Meaahlcal Propetis CoQmmrcial Molybdennm-S AlloyS. Novembet80. 1960( B 151099 $8.00)141 Tltanum-Alloy Fexgngs, necomber 19, 1960 (PS 161100 $2.25)142 Enviroamental Factors Influencing Metals Applications in Space Vehicles, December 97. 160(U1311110181.95)148 HIh-Strength-tool Forgins. January 5. 1961 (PB 151102 $1.75)144 S'ess-Cormion Cracking - A Nontechnical Inuroduction to the Problem, January 6, 1961 (11 151108 $0. 7)145 Deugn Information an Titanium Alloys for Aircraft and Missiles, January 10, 1961146 Manual for Beryllium Prospectors, January 18, 1961 (P9 161105 $1.00)147 The Factors influencing the Fracture Characteristics of High-Strength Steel. February 6. 1901(PB 151106 $1.95)148 Review of Current Data o•n the Tensile Properties of Metals at Very Low Temperatures, February 14. 1961

(PB 151107 $9.00)149 Brazing for High Temperature Service. February 21. 1961 (PB 151108 $1.00)150 A Review of Sending Methods for Stainless Steel Tubing, March 2. 1981 (PS 151109 $1.50)151 Invironmental and Metallurgical Factors of Stress-Cofrosion Cracking in High-Strength Steels, April 14, 1961159 Binary and Ternary Phase Diagrams of Columblum. Molybdenum. Tantalum, and Tungsten, April 28, 1961158 Physical Metallurgy of Nickel-Base Superaloys, May 5. 1961154 Evolution of Ultrahigh-Strength. Hardenable Steels for Solid-Propellant Rocket-Motor Cases, May 25, 1961155 Oxidation of Tungsten. July 17. 1961.

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