UNCLASSIFIED

Al 270 423

ARMED SERVICES TECHNICAL INFORMATION AGENCYARLINGTON HALL STATIONARLINGTON 12, VIRGINIA

UNCLASSIFIED

NOTICE: When government or other dravings, speci -fications or other data are used for any purposeother than in connection with a definitely relatedgovernment procurement operation, the U. S.Government -hereby incurs no responsibility, nor anyobligation whatsoever; and the fact that the Govern-ment may have formilated, 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.

If

IOWAI

NORTHOP CRPORTION NORAH DIISIO

UJ' NJ P9,

NORTiHROP AIRCRAFT, INC.

NORTIHROP DIVISION

REPORT NO. NOR-59-396

PROPERTIES AND HEAT TREATMENT OF AM 350 STEEL

15 July 1959

PREPARED BY

F. C'. Khlbafh

APPROVED BY

SH. D. Childers, SupervisorChemical-Metallurgical Utnt

L. F. Bernbach, ..;ýral fpervisorMaterials Research Laboratory

REVISIONS

CHG. NO. DATE ENGR. PAGES AFFECTED REMARKS

A I-2a-6i1 CH4M Complete Revision

fimm 00-5 (H.7.57)

FORM 90.7A ENGINEER PAGE

(in. It-Ri)

F. C. Kahlbaugh i"CHECKER NORTHROP AIRCRAFT, INC. REPORT NO.

NORTHROP DIVISION NOR-59-396DATE MODEL

15 July 1959

Rev. 28 November 1961

TABLE OF CONTENTS

Section Page

1 Introduction . . . . . . . . . . 12 Conclusions . . ...... .. .. . . .... . . . . . 13 Procedure . o . * . o • • . . e . ....... . . 14 Results .0 .. * e o a . e * . .* a . . • a • • 35 Discussion . . . . o o o. . . 0 * * * * . . . . . .. . 56 References .. .. .9 . . . . . . . . ... . . . . . . . . 6

Table

I Chemical Composition and Mechanical Properties of AM 350Steel Reported by Allegheny Ludlum Steel Corporation. . 7

II Variations on SCT-185 Heat Treatment . . . . . -- . . . 8III Room-temperature Tensile Properties of AM 350 Steel in

Ccnditi nss L-1710 and SCT-185 ... .......... 9IV Room-temperature Tensile Properties of AM 350 Steel

Subjected to Variations in SCT-185 Heat Treatment . . . 10V Elevated-temperature Tensile Properties of AM 350 Steel.. 12

VI Room-temperature Tensile Properties of AM 350 Steel AfterExposure to Elevated Temperatures .0. . .o ..*. . .e. 13

VII Room- and Elevated-temperature Compressive Propertiesof AM 350 Steel . o . .o. . .. . . . ... . . . . • • * 14

1 Effect of Annealing Temperature on Tensile Properties . . 152 Effect of Tempering Temperature on Tensile Properties . * 163 Hardness vs. Strength . . .. . . . . . . . . . . . .... 174 Variation of Tensile Properties with Test Temperature . . 185 Tensile Properties After Exposure to Elevated Temperatures

for 100 Hours , . . 196 Tensile Properties After Exposure t; E levated 0TemperatureS

for 500 Hours .0. .e # s . . . . . .e a o e * .e 207 Variation of Compressive Yield Strength with Test

Temperature ...... . . . • . . . . . . . . . • . . . 21

"FORM0 Il7A' ENGINEER 'PAGE(.1-57) PG

.- F. C,_Kahlbaugh___1CHECKER NORTHROP AIRCRAFT. INC. REPORT NO.

NORTHROP DIVISION noR- 9-c)6DATEODEL

15 July 1959Rev. 28 November 1961

1. INTRODUCTION

AM 350, one of the newer high strength corrosion resistaunt steels, issensitive to small variations in chemistry and heat treatment, and widevariations in its mechanical properties were encountered in material pro-duced prior to 1956. It was the object of this work to verify the producertsclaims that the material has been improved and will consistently meet themechanical properties called for in applicable specifications; to verifythe reconmnended heat treatment teanperatures, times, and tolerances; and toobtain room- and elevated-temperature test data for use in establishingdesign allowables.

2. CONCLUSIONS

2.1 All material tested met the requirements of Specifications NAI-1149and A14S 5548, although considerable variation in mechanical propertieswas found in sheets from different heats. The properties determinedfor different locations in individual sheets showed no significantvariation.

2.2 The recommended heat treatment tolerances are satisfactory for develop-ing the specification mndimurn properties. The "trigger" anneal treat-ment is the most critical for developing maxdmun properties, and amore extensive study of it should be undertaken.

2.3 The guaranteed and specification minima of 150 ksi yield strength,185 ksi ultimate strength, and 10 percent elongation are consideredsatisfactory bases for the establishment of room temperature designallowables.

2.4 AM 350 does not have the high strength expected at elevated tempera-tures. Both PH 15-7 Mo and 17-7PH corrosion resistant steels in theRH 950 condition are stronger, the difference in tensile yield strengthbeing approximately 30 ksi at8OOF and 10 ksi at 900. F. The compressiveyield strength is much higher than its tensile yield strength, but stillnot as high as that of PH 15-7 Mo or 17-7PH. The difference in com-pressive and tensile yield strength of AM 350 persists to 1000 F.

2.5 AM 350 is not embrittled by exposure to tenperatures up to 900 F. Anincrease in mechanical properties, both strength and elongation, wasobserved after exposure to elevated temperatures for 100 and 500 hours.

3. PROCEDURE

3.1 Specimen Preparation

Three sheets of AM 350 corrosion resistant steel, each fran a differentheat, were purchased from Allegheny Ludlum Steel Corporation for testing

t'n N4 20- ?A I

(R. I. 59) ENGINEER PAGE

F. C. Kahibaugh NORTHROP CORPORATIONCHECKER NORAIR DIVISION REPORT NO.

NOR-59-396DATE 15 July 1959 ,oDIM

Rv-PA Nnvymhlr 1061,

in this program. The nominal dimensions of the sheets were 0.040 by 36by 120 inches. The material was supplied in the H-1900 condition.Certified chemical composition and mechanical properties reported bythe vendor are shown in Table I.

All specimens were taken with the length parallel to the rollingdirection of the sheet. Nine tensile specimens used to verify thereliability of the material were taken from the following locations ineach sheet: one from each corner, one from the center of each edge,and one from the center. Specimens for the remainder of the testswere taken at random locations.

Three tensile specimens from each sheet were heat treated to ConditionL-1710 (heat to 1710 F ± 5 for 30 minutes, air cool to room temperature)The remainder of the specimens, except those to be used for heattreatment verification, were heat treated to Condition SCT-185 asreconmnended (heat to 1710 F ± 5 for 30 minutes, air cool to roomtemperature; liquid cool to -100 to 110 F for 3 hours; heat to 850 F ± 5for 3 hours). Two tensile specimens from each sheet were heat treatedto Condition SCT-185 with one variation in the procedure, as shown inTable II. All specimens were mechanically descaled prior to testing.

3.2 Tensile Tests

Tensile tests were performed on a Baldwin-Lima-Hamilton 5000 poundcapacity testing machine and in accordance with Federal Test MethodStandard No. 3.51, Method 211.1, specimen F2. Specimens were 8 incheslong, with a 2 inch gage length 1/2 inch wide, and were loaded bymeans of 1/2 inch pins inserted through holes in the grip sections.Autographically recorded load-strain curves were used for calculationof yield strength and modulus of elasticity. The test equipment andfixtures are fully described in Report No. NAI-57-246 (Reference 1).

Twelve specimens from each sheet, three heat treated to ConditionL-1710 and nine to Condition SCT-185, were tested at room temperatureto verify reliability and uniformity of the material and establishconformance with the mechanical property requirements of SpecificationNAI-1149 and AMS 5548. The two specimens from each sheet that hadbeen subjected to each heat treatment variation were also tested atroom temperature.

Elevated temperature tensile tests were performed in triplicate at600 F, 800 F, 900 F, and 1000 F on specimens prepared from Sheets7 and 9. Sheet 7 was selected because it had the lowest room tempera-ture strength and Sheet 9 because of its marginal elongation. AfOrced-air, box-type furnace was used to heat the specimens, which weresoaked at temperature for 30 minutes prior to testing. The tempera-ture during soaking and testing was held to within ± 5 F of thatspecified." An extensometer modified for high temperature use was usedto record strain measurements.

(R. 1- 59) ENGINEER PAGE

F. C. r ahlbaugh NORTHROP CORPORATION 3CH•cECKER NORAIR DIVISION --.E--ORTNO.I - _ NOR-59-396

DATE 15 July 1959 MODELRev. 28 November 1961,

To determine the effects of elevated temperature exposure, two specimensfrom each sheet were tested at room temperature after being heated for100 hours and 500 hours in a forced-air electric furnace at 700 F, 800 F,and 900 F.

3.3 Compression Tests

Standard 1 by 3 inch compression specimens were tested in an NAA-typecompression fixture in which the specimen is supported in a verticalposition by steel leaves. The strain in the middle 2 inch section wasrecorded by means of a compressometer. The test equipment and fixturesare described in Reference 1. Load-strain curves were used for yieldstrength and modulus of elaoticity calculations.

Compression tests were performed on a Baldwin-Tate-Emory 120,000 poundcapacity testing machine at room temperature and at 600 F, 800 F, 900 F,and 1000 F on three specimens from each sheet. The forced-air, box-typefurnace was used in elevated temperature tests. Specimens were soaked for30 minutes, and the temperature was held within ± 5 F of that specifiedduring soaking and testing.

3.4 Hardness Tests

Rockwell hardness was determined on tensile specimens used in estab-lishing specification conformance and verifying heat treatment procedures.Hardness was determined on a Wilson Hardness Tester, Model JR.

4. RESULTS

4.1 Room Temperature Tensile Properties

The room temperature tensile properties for both the L-1710 and SCT-185conditions are listed in Table III. All sheets met the requirements ofSpecification NAI-1149 for Condition L-1710, although Sheet 9 wasmarginal in ultimate strength and elongation. All sheets met specifi-cation requirements for the SCT-185 condition, having average propertiesof 204 ksi ultimate strength, 170 ksi yield strength, and elongationbetween 10.0 and 18.5 per cent. The total variation of the materialtested was 10 ksi for both yield and ultimate strength.

4.2 Effects of Heat Treatment Variations

Tensile properties of material subjected to variations in heat treatmentare given in Table IV. All heat treatments investigated producedacceptable properties. Figure 1 is a graph showing the effect of theannealing treatment, and Figure 2 shows the effect of the temperingtemperature.

R• 20-7A III PAGE

(R. 1 59 ENGINEER

F. C. Kahlbaugh NORTHROP CORPORATION ICHECKER NORAIR DIVISION ,REPORT NO.NOR-59-396

DATE 15 July 1959 MODEL

Rev. 28 November 1961,

Ultimate and yield strengths varied unpredictably with the annealingtemperature. Since each sheet reacted differently, a single temperaturecould not be found to produce the best properties in all three sheets.From the observed data it appears that temperatures near 1700 F producedthe most uniform results. Decreasing the annealing time from 30 to10 minutes caused only a slight loss in strength for the material tested,but for other heats a greater loss in strength might result.

After the 1710 F trigger anneal, the material must be directly subzerocooled to -100 F. Higher temperature, shorter time at temperature, anda delay between annealing and cooling all caused loss of strength.According to DMIC Report 111 (Reference 2), holding at -100 F for longerthan the recommended 3 hours results in higher strengths with reducedductility.

Tempering as recommended at 850 F for 3 hours produced the maximumhardening. Tempering at 900 F gave an increase of 3 per cent in elonga-tion, with an accompanying loss of 10 ksi in strength.

4.3 Hardness/Strength Correlation

Rockwell hardness measurements are included in Tables III and IV. Asatisfactory correlation between hardness and strength could not be found.As is true with other stainless steels, a plot of strength versus hard-ness gives a scatterband, as shown in Figure 3.

4.4 Elevated Temperature Tensile Properties

The results of elevated temperature tensile tests are presented inTable V and shown graphically in Figure 4. Yield and ultimate strengthdecreased gradually with increase in temperature up to 800 F, where theloss in yield strength became more rapid with further increase in tempera-ture. Yield strength decreased more rapidly than ultimate strength.Young's modulus decreased gradually with increasing temperature. Elonga-tion decreased to a minimum of 5 per cent at 600 F, then increased athigher temperatures. Sheet 9 showed another loss of elongation at 100 F,while the elongation of Sheet 7 continued to increase. The reason forthis behavior is unknown.

4.5 Effects of Elevated Temperature Exposures

Results of room temperature tensile tests after exposure to elevatedtemperatures are given in Table VI and presented graphically in Figures 5and 6. All strengths were above the specification minimum requirements.Except for Sheet 9, the tensile properties were increased or unchanged.Sheet 9 exhibited a small loss in ultimate strength when exposed to 800 Fand 900 F for 100 hours, but behaved similarly to the other sheets underall other exposure conditions. Elongation was slightly reduced for allsheets when specimens were exposed to 800 F for 500 hours, or to 900 Ffor 100 hours or 500 hours. All elongation measurements were above the10 per cent specification minimum, however.

0- 7A

59) ENGINEER PAGE

F. C. Kahlbaugh NORTHROP CORPORATION _CHECKER NORAIR DIVISION REPORT NO.

199NOR-5-9o'E15 July .1959 .D;Rev.28 November 1961,

4.6 Compressive Pnoperties

Results of room- and elevated-temperature compression tests are givenin Table VII and Figure 7. The compressive yield strength behaviorwith elevated temperature was similar to that of tensile yield strength,but 30 ksi higher. Compressive modulus of elasticity decreased slightlywith increasing temperature up to 800 F, where it began to decreaserapidly.

5. DISCUSSION

AM 350, a semiaustenitic steel, is austenitic at room temperature afterannealing at 1950 F. In this condition, the Ms is below -100 F. In order totransform the austenite to martensite, the Ms and Mf must be adjusted tohigher temperatures. The Ms and Mf are adjusted at a temperature which willprecipitate enough carbide to raise the Ms and Mf but leave enough carbonin the austenite to give reasonably strong martensite. Further increase instrength is obtained by a controlled precipitation of the constituents insolution in the martensite.

The 1950 F anneal is used to give a soft, easily formed material. Temperatureshigher than 1950 F give larger grains and increased amounts of delta ferrite,both being detrimental to strength. The delta ferrite is soft and ductileand is not affected by subsequent heat treating operations. Therefore, largeamounts of delta ferrite result in lower strengths. Large grain size tendsto cause uneven distribution of carbides precipitated during subsequenttreatments, which may result in lower strength and corrosion resistance.Annealing at lower temperatures gives uneven distribution of carbides andless stress relief than annealing at 1950 F. Lower annealing temperaturesmay also result in less stable austenite, giving lower formability.

The amount of delta ferrite formed in AM 350 is partially dependent onchemical composition and annealing temperature. Different heats of materialannealed at 1950 F may have varying amounts of delta ferrite formed (5 to15 per cent ) owing to slight variations in chemical' composition, which is onepossible cause for variation in strength between different heats o.f material.

To harden AM 350, the austenite composition must be adjusted to raise the Msand Mf temperatures. Heating to 1710 F for short times raises the M. to justabove room temperature and the Mf to -100 F. When AM 350 is heated to 1710 F,carbides are precipitated from the austenite into the austenite-delta-ferriteinterfaces. The austenite retains approximately 0.05 per cent carbon at thistemperature. Variations in the balance of other alloying elements may resultin a change of the Ms and Mf temperatures. It is possible, then, to obtainfull transformation of austenite at -100 F in one heat of material but onlypartial transformation in another, resulting in larger quantities of retained

I

F 2R . 0- 7O A I II_,,,_ _ _(,- 59) ENGINEER PAGE

F. C. Kahlbaugli NORTHROP CORPORATION 6CHECKER NORAIR DIVISION Fi'eoR'r No.

DT MODELNOR-59-3

'R•ev. iý iolvm 9e~r91961,

austenite. Greater amounts of retained austenite decrease the yield strengthprimarily. As shown in Figure 1, the same annealing temperature is not idealfor all heats of AM 350. The "trigger" anneal is the most critical operationin heat treating AM 350 and determines to a great extent the strength of thefully heat treated material. Variation of chemistry is not the only causeof variation in the mechanical properties of AM 350.. Certified reportsfrom the vendor show a variation of 15 ksi tensile strength in two sheetspurchasr from the same heat; as only one of these sheets was tested in thisprogram, no explanation can be given for the variation.

Following the "trigger" anneal, cooling to -100 F for 3 hours completes theaustenite-to-martensite transformation. Loss of strength is caused by delay-ing the subzero treatment or by cooling to a temperature above -100 F. Cool-ing to-100 F is necessary for complete transformation, and any temperatureabove this will give increased amounts of retained austenite. Delaying thesubzero treatment may result in austenite stabilization, i.e., the austenite-to-martensite transformation becomes sluggish, giving more retained austenite.Holding for longer time at -100 F is reported to give higher strength butlower ductility, because of further austenite transformation (Reference 2).Three hours is chosen as giving the best combination of strength and ductility.

The increase in strength with exposure to elevated temperatures, particularlyto 800 F for 500 hours, is not fully understood but is thought to be due toprecipitation of a hardening phase, possibly a chromium-rich ferrite. Theincrease in elongation after exposure at 700 F is also unexplained, althoughcertainly some stress relief is taking place.

6. REFERENCES

1. McCarthy, W. H., "Short Time Elevated Temperature Mechanical Propertiesof 6A1-4V Titanium Alloy Sheet," Report No. NAI-57-246, 21 February 1957.

2. Ludwigzon, D. C., and Hall, A. M., "The Physical Metallurgy of Precipita-tion-hardenable Stainless Steels," DMIC Report 111, April 20, 1959.

S.. .. .. . . .. ... . .. .i

FORM 2O-7A I N RA(R. 11-17) ENGINEER PAGE

F. C. Kahlbaugh 7CHECKER NORTHROP AIRCRAFT, INC. REPORT NO.

NORTHROP DIVISION NOI•-59-396DATE - MODEL

15 July 1959

Rev. 28 November 1961

TABLE I. CH1,,aCAL COMPOSITION A1JD I-MiCHANICAL PROPERTIES OF AM 350 STEELREPORTED BY ALLEGI =, LUDIUM STEEL CORPORATION

Sheet 3 Sheet 7 Sheet 9Requirement Heat 35201p Heat 79277 Heat 79650

Composition AMS 5548Carbon, % 0.08 - 0.12 0.094 0.091 0.089Manganese, % 0.50 - 1.25 1.02 0.76 0.76Phosphorous, % 0.040 max 0.022 0.020 0.018Sulfur, % 0.030 maox 0.013 0.022 0.017Silicon, % 0.50 max 0.37 0.22 0.24Chromium, % 16.0 - 17.0 16.78 16.78 16.37Nickel, % 4.0 - 5.0 4.45 4.53 4.11Molybdenum, % 2.5 - 3.25 2.95 2.93 2.73Nitrogen, % 0.07 - 0.13 0.10 0.12 0.090

Condition H-1900 AMS 5548Yield strength, ksi 75.0 max 73.6 67.7 49.8Ultimate strength, ksi 180.0 max 151.8 146.3 169.9Elongation in 2 in., % 20.0 min 47.0 44.0 28.5Rockwell hardness B 95 - 100 B 93 - 96 B 93 B 95Cold bend, 180' 2T OK OK OK

Condition L-1750 N-AI-1149Yield strength, ksi 120 max 43.0 44.-4 66.3Ultimate strength, ksi 200 max 166.9 186.4 197.7Elongation in 2 in., % 8.0 min 15.0 13.0 9.0Rockwell hardness - C 39.5 C 39.5 C 42.5

Condition SCT-185 AMS 5548Yield strength, ksi 150.0 min 180.8 167.7 175.9Ultimate strength, ksi 185.0 min 200.8 204.6 214.6Elongation in 2 in., %0 10.0 min 12.0 10.0 11.0Rockwell hardness C 38 - 48 - C 47 C 47

FORM 20O-7A -(R. 11 -a?) ENGINEER PAGE

F. C.* Kahlbaur,,h 8_______ZHECKER NORTHROP AIRCRAFT, INC. REPORT NO.

JuY1 -NORTHROP DIVISION Joil-59-.396

DATE15 JulODEL

-Rev.8 -Novmer 1961

Lr\H0+1 0

0)

0 ~ +1 +1 +1 +1 +1"Zi cti (j cd cd wd co_

co ca co U) oU U) U a U o toU) 1 to

Z4-

01U) rX4 0 (

0 HHr 0U ~ U U ' ' ' 0 .U) ý L

Id 0 d Id I~d 4' 1 0 10' cr3 d cr3 cr31

0000\ 0

01,

00

H0 00 0q 01 c tr

t) N~U 0r -i1

4-) '0 c- v- LC- L- 4') 4' Y ct - 1- -U) H H H o ) ) U U) U1) U) Uf) U)

0

ribm 0 N P4 0. :1 11: 101 cy U) HAcoU)-

FC.KhbuhNORTHROP CORPORATION 9CHECK. I ame

NORAIR DIVISION NOR-59-396'1rl Ju.Y 1959 WAWL

0n4 N N N N 3.0 0'00

0.

H 0 to a 1 K 0If001 p1

14 N HH cH HH11 cHH0Ht

4'0,1 c-rý '0H - r- c- r- c I,

4-9 .0 >.q M9 r_,,'00 0 00 0

0 4-4

4 o H4HHHHHH4

00

H 0'

00 HHH 0 - HHHHHO 0ý

VA) If HC00t 000 004 -H

Ho C;O 0 0,c,On -W.4 .,j to'0to'lot , ,c\G \a -

g q(nI. t -N'0'0 \0,,00 \HO'0

z 4 0 0U) tX -A\ 0000 -to0 0N-r\O0'. 0 *~ Cv0 0 0

H,-H li Air- H ,., t. HA 11 -4t

0 0A ý\OOOO0) 4) 9 .

m4) 4' c;?,a 0 \ .0.0±' 0 ' ar .- o r- L0'H0

93 0 O0\N t Ic 0 *-Na~'HN-.-0s0- 4' .- 44

r0. 0h 10H0HHH _*,o I

4'

4 : 04 ~ %01101 0 4()04NONR ONC 0I~ NN4N N N N N

00 r--0 t-o)U)0 I-0r-00 00,

0 44 ...

'0 N 0'0m't0'084ý

F. C. Kahlbaugh NORTHROP CORPORATION 1C4U~I OMAIR DIVISIOII No.'

DA Tr 15 Ju3.Y 1959 Milev. 28 TNovember 1.961

N) 0 l). Wý C\U 0 9U.. tAA 0'cc 4) 04 wvoo.0 41%s010 10 u'.Wl c'- t- El-V--c'- '0t-'o U'o 'S W'o'0-A II

M)A HO0Q wH4 NC'-O 0 H r'c'- t~- m 0 r'-,00 %a )r.4. 40.O

0 NN 04 NN 1N N NiN NC'J NN l 1 s qN " JN N N N cyN ( N N NN0H

4) HI .ek 01 M\0 oro HO 7\0 000 HO'a,0 N HH 00 0 m,-'.N 0 Da.r. w~ N HH HHH H Hi H H -H HHH HH H HHH H Hc/3 I

N- 1 00 000 00-0 00CJ0 H 444 C>.' 0 0O00 ~000 C-

4) 00 t r -t 000 W" (3, 0 0W 00-4' OW.tNf N010' w' '0 N1 t l4) t. . . . . . . . . .* oi

F' '\'. 9 '- -0 C'-w C'.- 9 9 -C"- 4 9\l 'O ' .41rý '0 Ucl' 0..

H0 N N N NNcjN NNC' NNN 0101N NNN cQ JNdN NNN NNN

c.-

9:11k-: I c- :1 -H '.. 0W!. 00 00'( W"W" 00 t\0 tt!4) 9 I4'.n4ý - r

U 4' W) w'0 m".4 r- 01 w 4 z t'- r'- - H NH to901 NNN 0\ a, a-Y O'00 000 0o\ O a 000 R ( 010.0 000 0'W 0.01(7 wwt

H N NNN' H HH NN H HH NNN HHH H H.4 H HH-

w \7 - p p t\ 10\Q.)'- If\'J~- t^'.' W'. r -CY\O r- W\10. E-0 W LA Hr-. Ct-.0rý 0 -%d '0 \0 0 t'-Ct 10,010 %10.0.0 " LW'.w\ \0.10.0 w\10 `^. LA W ,W.'

0

-t 444 , 444 444 444 444 444 44 4 t4 4

0

C)' 0 NN" C-NC' N NN N NN NN-N NN C-iNNc NNN NNN

4ý 0 9 w\0ON 0 0 u" W'.4'0 4'4"A ON W'.M\W' 04' o 00 ^W'NPL. 4) -0 .9: O' -H4)C- .''C .00 .. "' . .U 0 .. 0 'A a N HHH irir- -HH H HHH H NH HNl N rNHH HHH NN01 N N

04 00 000 0\00 01 GO'Oa' 0 O' Y'O 000 0.0.0 0101071 010.0'

ciN N NNN HiN N HHH HH4rlH NNN r HHH H H H HHHl -

4) N 0 0 -*.4Io .0.0. to H 00- 0 I- C".4 -t'01 V N HýY" N cl-VW4. -H C. . . '.0.0 . W'W. . \'W .'W.' 4'IA ' W'.U\W

M 02r4(1 o - 01 WI b , r4 0 00 0 4 1b; 4. 4 0 4.0~~t

00

W ~~~ x o bD h D b . o h.0 ) C 044 - 4 ) -

44 4)03 t

40 0%- 02to ,q $4 H- H- H- H1 HC. C.. HO .0.10). C4'j to to m) to cu H 0 H1-4 H ̀ 4 34)

t) 4) 0) to t) . I 0

4ý t 124('n) 0 -r 4- E01) 0C)D )4) 4p43 434) %464D)

p. C.. , to m 4.4)4 W)W\ 0 0 : C

toH H H H1 H\ H. a%- 01

- -C-

I-) (H C. F1 C.

F. C. Kahlbaugh NORTHROP CORPORATION 11'"w.NORAIR DIVISION NOR-59- 96

".l" 15 July 1959 ______________________fl~ev.2

8 November 1961

04 ý00V-0 CO ý0 W\1 00 T0 0~

C ~ z 4-d- -4 4 -t -t- .t**t4 4 -t--

0 NN NCJ NN N NN 01C'

bfl

i C 0'to 0 'to 000 00,1 0 04-

'A 00' cy 0 -1k. . . . . . . . . . .. . . . . . . .

04 Ni 1- H H4 HHH HHH NNNH

.44 U) 0 (% 0 c a a%2 Do-" to to '0 -

oO 0 0 '0,00 'o H,0 10 10

VU 00' r...-. L."'1 000 41'0 t

co0 C'NN JN 'CN J(I N N4)H

00 c .4) o0 bwN C!H OH C!H HHHn

HH) 1-H HH H H HH

0 HHH HH HHH HHH HH

0- a\ -, -- 0---- t-----.--

0.

m u) AWd'01' 10 41"1' 440

WOC t- r-* 4 c- 0\00 -4-t4 c:-~- -t*-~

lo 0 NN NNN ('oN c.- N NNrNco "

F-4 ~ 0 4V 000 00 N0\'1'c~ V ~jNN 04 04

ik CO to c- C' c-4 000,a\C \ , 0t ()-,-'

4,.m O.~0 ( '-NV 6.06 aO a\0 a \ t 'oH1c\a0 HH4H ` HH1 - I 4H H HH HHH1-

0 ) r_ HNC. HNH H~f HN HNC1.- -

4) a

b,0 bD b 4o b

P.ý ac .4 r.4 m 4 H

00

-lot E- N.4 K K

4) Q)

W\- LeN 0 0

N' C'- 0 uto. to' c7\ cp\ F

(mSPAGE

F. C. Kahlbaugh NORTHROP CORPORATION ýCNECCK(. NORAIR DIVI31ON NOeW me.

S15 July 1959 OWL

0 (v 14N NNN N;= N" N N NNN

0000~ W\O^ 00 0 0 -4 0 0000totoT

'000'N O-I HN r- t V\0 10 W10 1

00o, 0\ ,a vwtoto 10'-O'00 NNNN-IqHH H H , -4H .- HH HH-

0 4Cv 11NH to 'O CCN4 4O'

4. .4- .0' .~ .0N4ýr .4t-1ý -' 4 H0,

0n a\C*Jo(, ' HHH HH-4H .-t -HHHo -tH

o 0N 0 0'N (I V r4riHH 0 loC

00 H 144 r- ,

0 4 -\ Wg HffwC.N *tp -olo~ 04

1'- H

0 N H N H H 04.4

r... .NNN .t ý 9 ( \ 00 0'p, _____ __ __ __ () 04. 0rI00 to1 4-

04.4

0 U) to 0\ 01\O = pN '00 C-0 c- 1061N 1 00c00 - r cr- W\.V., 0--- . . .

__ __ -ý CO 1ý lý I

00

4.

caP

ý4-

CkCIIPAW

F. C. Kahlbauph NORTHROP CORPORATION"Ec~cam op"? 4?MORAIR DIVISION NORI-59-3 96

@)Tcl1 July 1959-Rev .28 November 1961

1 0 0O 0~sO Cr %(1wr 000 000 0000 mm N NN N NN mmc mp'm menmc

0D 0 Wux 000 %ot0o o ow, 000 )rsvt,0

Wj ". N "H HH HHH HH-iH .-I -H -q -iHr

4)

E-. ~ ~ ~ ~ 1 H0 HNt .41 'lD NO0 , -4H -t H ww .. H 1 000 000HHH 700

NNN NNN NN N04N N HH.qri-1 N lNN

4.) u) 0~ o 'o r- 44ts IOW o '0 e -t'0 1 H HH ,--qr- HH HH HH H 4r -1HH

'0 00O C mKWWM C 0''CI 000 (7%'0.% 0'1H7\r-O0 M NN N NN N NN ý,r N NN N

bo

) 0 C) 0.. .0.. . . . . .

NC'\' H0O 6~ N -t11L'

C40

a)O o0~ NNN N0 I H H H H H H

C.. o . N4 '1N '0N' H O. H4JO 14 - AH1 f1

Co0 NrMN NNN "NN NNN M.NN N fN

0 0 N CoN Co0w '(\00 loo 'N CoO N 0 uo~

3 CA N HHH1 - H NH HHrlH H HHý HH14H HH H

.t w\H -z cn\7CoO 0\0 tCo4\0 \0O(71N

Iz . H H-4H HHiIH HHýiH H H H 000 H H H04NNN NNN c N NlN N NN c NNN1o N N N

P -4 r- N O N C '0-aCo 4 '\w\-t- to No' w, v\ v

I-044 r- -t* r-r-NN C rNN toto v NNýr-C- r- -Nr11 0 -4H H HH - ril HHH4 HH H HHl H H H-4H

bf 8 b 0 0 0

t. 0 0 8.00

0 H W'\ H W\ H Co\

0. 0 o 0 0 0 o

0 0 0 0 0 00 0 0 0 0 0

FORM 3O.7A ENGINEER PAGE(ft. 11"17)

F. C. Kahlbaugh 14.....CHECKER NORTHROP AIRCRAFT. INC. REPORT NO.

NORTHROP DIVISION NOR-59-396DATE MODEL

_ 15 July 1959_Rev. 28 November 1961

TABLE VII. ROOM- AND ELEVATED-TEMPERATURE COMPRESSIVEPROPERTIES OF AM 350 STEEL

Sheet 3 Sheet 7 Sheet 9

Fcy E Fcy E Fcy ETest Test 0.2% 0.2% 0.2%

Temperature No. Offset Offset 6 Offsetksi lO6 psi ksi 10 psi ksi 106 psi

Room Al 189.3 30.1 199.9 30.6 199.9 31.7A2 196.3 29.3 198.3 29.2 207.3 32.4A3 202.1 30.2 191.0 ^1.3 201.4 31.."Avg 195.9 29.9 196.4 30.4 202.9 31.7

60OF V1 160.0 26.3 162.8 26.3 173.5 28.1V2 162.5 27.5 164.0 27.9 172.9 29.0V3 168.4 27.5 160.3 28.2 170.2 29.2Avg 163.6 27.1 162.4 27.5 172.2 28.8

80OF Wi 146.1 31.9 149.5 30.L; 159.3 30.1W2 148.2 29.6 151.4 21.7 155.7 32.6W3 144.4 31.0 i48.1 27.2 150.1 29.6Avg 146.2 30.8 149.7 26.4 155.0 30.8

90OF Xl 129.5 22.9 134.4 26.3 147.1 27.1X2 134.6 23.5 135.3 26.8 143.7 25.6X3 129.0 24.0 136.0 25.1 145.0 24.0Avg 131.0 23.5 135.2 26.1 145.3 25.6

100OF Zl 97.4 17.4 110.0 17.7 115.5 19.0Z2 107.7 17.5 112.0 19.4 122.7 20.0Z3 104.9 17.4 119.3 18.3 126.9 20.0Avg 103.3 17.4 114.1 18.5 121.7 19.7

Foltm 20.663

(R.a.57) ENGINEER PG

F. C. Kahlbcuiaph AICAT N.RPR O15LCMLGKER NORTHROPAICATIN.RPTNODATE _ __ __ _ __ _ NORTHROP DIVISION M DN OU1-59-396

OAh15 July 1959 - Figure 1. Effect of Annealing Temiperature F~L-LRev,28 November 1961 on Tensile Properties__________

Sheet 3

225---4 Sheet 7-- S'heet 9

Ultimate

200 -t---

175 ---

S150- Yield4-3

125

Elongation100 - - 25

75 15~0.9-4-,-5 - 10 r

50 1S 70 7012-0

Annealing Temperature, F

FORm 20.-63(R.8.57) ENGINEER PAGE

F. C. Kahlbaugh 16C•ECCKER NORTHROP AIRCRAFT. INC. REPORT NO.

NORTHROP DIVISION iNOR-59-396DATE 15 JUIy iJýi9- Figure 2. Effect of TWrperng Tamperature MorEL

Rev.28 November 1961 on Tensile Properties

Q Sheet 3225-- [- Sheet 7

- Sheet 9

Ultimate

200- EJ

175 ---

S150-

Yield

0

125 -

Elongation 25

100-- 20

S--15 0

75 -

5--

50-- I I I825 850 875 900 925 950

Tempering Temperature, F

o63E1) 40GINIEER PAOE

F. C. Kahlbaurlh 17iCHECKER NORTHROP AIRCRAFT, INC. REPORT NO.

NORTHROP DIVISION ,OR-59-3q76_15 Ju~ly1959 Figure 3- 115 July 1959 Hardness vs. Strength

Rev. 28 November 1961

220

210--

2.90 "

1..

180 --

I 9

170

170-! I I I ! -t-, ,-42 43 4, 45 46 47 48 49

B A ardnn8s, ac

Best Availabl Copy

F O R M Z 0 .6 6 3 ,,,,,_ __,,_,_ _ _ _ __1(R. S. 57) ENGINEER PAGE

F. C.- Kahlbawth 18CHECKER NORTHROP AIRCRAFT., INC. REPORT 4o.

NOTHROP DIVISION roR-59-396DATE 15 July 1959 Figure 4. Variation of Tensile Properties MOOELRev.28 November 19611 pith Test Temperature _

Sheet 7

225 -- A Sheet 9

Ultimate200

ElN

175IdI

N,

S150 N

PYieldN N K

H 25

100 20

Elongation H

75 1- 1 o0

5

50 I I 0 t I I -00 200 400 600 800 1000

Test Temperature, F

N 1R 20.63(R . 0. 57 ) E N G IN E ERF. C. Kahlbaurh

PAGECHECKE a NORTHROP AIRCRAFT, INC. REPORT NO.NORTHROP DIVISION 110-19- 96DATE 15 July 1959 'Figure 5. Tensile Properties After Exposure MO-ELRev.28 November 1961 to Elevated Temiperatures for 100 Hours

0 Sheet 32 2 5 - -- [ S h e e t 7225

Sheet 9

Ultimate

200 - L ---- --- -------------------- --

noo175-

Yield.150

4),

Ej125

Elongation 25

100 20

----

15El---- -A.-

4-,75 4- 10

550 I I

0 200 400 600 800 1000

Exposure Temperature, F

FoRm 20.663(R.8.57) ENGINEER

F0.Kahlba~uh PAGE

C14ECKER NORTHROP AIRCRAFT, INC. 20OR N

1120. A l5 J l 19 9F igure 6. T e n s.... i .... Le Pr op ertie s A fter E:,ýposu M DERev.28 November 1961 to MlvtdOeDraEL fr50 or

QSheet 3225 Ultimate -0A Sheet 9

Shet-

200

Yield

*4150-

ct43

125-5

Elongation 2100_20

15

-S10 OZH

50550 200 400 600 800 1000

EXqosure Temperature. F

FoRM 20.463 .

(R. .857) ENGINEER

F. C. Kahlbauwh 21CHECKER ' NORTHROP AIRCRAFT. INC. REPORT NO.NORTHROP DIVISION TOR-59-396

OATE 15 July 1959 Figoure 7, Variation of Co.ppressive Yield MODELRet,28 NQvembber 1961 Strength with Test Temperature

Q Sheet 3225-- ----- ] Sheet 7

-- /N Sheet 9

200--

175--

150--

*r-I

~125-

ILII

100--

75--

50o I I I I I I .0 200 400 600 800 1000

Test Temperature, F