AMERICAN SOCIETY FOR TESTING MATERIALS

1916 RACB STHMT

PHILADELPHIA 3. PA.

1956

BEFEREnm
on

FHT1GUE
STP No. 9-H

This is a list of references to articles published in 1956 dealing with

fatigue of structures and materials, following the plan used in previous annual
lists from 1950 through 1955* References are generally so arranged that sheets
can be cut apart for filing according to any desired plan. Brief abstracts have
been included when these were readily available.
Comments and suggestions concerning the value and format of this list
would be appreciated. Correspondence should be addressed to
Dr. Horace J. Grover, Chairman
Survey Subcommittee III
ASTM Committee E-9
Battelle Memorial Institute
505 King Ave., Columbus 1, Ohio
Sponsored by ASTM Committee E-9 on Fatigue
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 STP9H-EB/Jan. 1956
ALEKSAHDROV, B.I. and N. P. ALLEN and P. G. FORREST
SHISHKOVA, A.P.
The Influence of Temperature on the Fatigue
The Effects of Various Types of Treatment of Metals
on the Fatigue Strength of E1434 Steel
(Russian) PAPER NO. 1 of Session 4 from "INTERNATION-
AL CONFERENCE ON FATIGUE OF METALS", VOL II,
METALLOVEDENIE: OBRABOTKA METALLOV, NO.8, INSTITUTION OF MECHANICAL ENGINEERS,
pp 20-27 (Aug. 1956) 16 p + 3 plates (1956)
Effect of Cu, mild steel, and-some tech-
nical creep-resisting allo^Sf^eti£^ie|Ui>der

ANONYMOUS Cont'd N. P. ALLEN and P. G:

Effect of Surface Finishing on Fatigue
Strength of Titanium Alloys fluctuating stresses at high temperature;
PRODUCT ENGINEERING, "DEVELOPMENTS TO correlation of creep strength and fatigue
WATCH", p 7 (January 1956) strength; influence of metallographic
structure and corrosion.
Tests for the University of Illinois
show correlation between hardness of sur-
face and its fatigue strength. Roughness
of surface is also a factor, but is less
important than fatigue strength.

A. A. R. RESEARCH STAFF A. A. R. RESEARCH STAFF

ENGINEERING DIVISION ENGINEERING DIVISION
Causes of Shelly Spots and Head Cracks 'Rail Failure Statistics, Covering:
in Rail: Methods of Their Prevention' (a) All Failures; (b) Transverse Fissures;
(c) Performance of Control-Cooled Rail
AMERICAN RAILWAY ENGINEERING ASSOCIATION
BULLETIN, VOL 57, NO. 528, pp 830-850 AMERICAN RAILWAY ENGINEERING ASSOCIATION
(February 1956) BULLETIN, VOL 57, NO. 528, pp 794-814
(February 1956)
This investigation was to determine
whether gage cover design improvements Rail failure statistics are presented-
on rail sections have assisted in pre-

Cont'd Causes of Shelly Spots... Cont'd Rail Failure Statistics...

venting onset of shelling failures. •types of failures include transverse
Emphasis was placed on following per- failures, web failures, detail fractures,
formance of various service installa- and others. Data were collected from
tions. It appears design improvements 62 railroads which constitutes 90 per
at the gage corner are helpful. The cent of all main-line tracks in the
studies also confirm that heat-treated United States and Canada.
or alloyed-steel rails can extend the
service life of track.

1
Copyright© 1956 by ASTM International www.astm.org
A. Ao R. RESEARCH STAFF ANONYMOUS
ENGINEERING DIVISION
Comet Fatigue-Test Progress
Service Tests of Solid and Manganese
Steel Insert Crossings Supported by Steel AEROPLANE, VOL 90, NO. 2326 p 182
T-Beams and Longitudinal Timbers; (February 17, 1956)
AMERICAN RAILWAY ENGINEERING ASSOCIATION Editorial on the failure of part of
BULLETIN, VOL 57, NO. 528, pp 689-696 the wing structure in the Comet 2 test
(February 1956) fuselage/wing combination in the fatigue-
testing tank at Hatfield on January 30,
Investigation was to develop inte- 19560. Criticizes disregard of importance
grally welded steel T-beam types of sup- of failure of wing test was primarily on

Cont!d Service Tests... Cont'd Comet Fatigue-Test Progress

ports for railroad crossings to improve
life of support. Included in the study fuselage. Points out that wing/fusel-
was an assessment of effect of sub- age combination is a single unit and a
structure. The service experience de- failure of the wing structure is no less
monstrated the T-beam supports to be adequate significant than a secondary failure in
for crossings. It was also shown that a the fuselage connected with basic fatigue
sub-structure constructed of timbers was test.
more beneficial than the steel sub-structure
in service performance.

ANONYMOUS ANONYMOUS
Failure by Fatigue Comet Fuselage Fatigue Tests
MACHINERY, VOL 89, NO. 2291, pp 12 ENGINEERING, VOL 181, NO. 4693, PP 18
(October 12, 1956)
and 19 (January 6, 1956)
This editorial claims that some de-
signers are still insufficiently aware of Article describes experimental setup
the dangers existing where conditions of devised to permit repeated cabin pressure
fatigue loading and stress concentration testing with superimposed steady flight
prevail simultaneously in metal parts or and gust loads on the Comet 2 airframe.
assemblieso The importance of surface fin- Apparatus consists of a tank 140 feet long,
ish and avoidance of notches by stream- 20 feet wide, 16 feet deep, with a water
lined shapes is emphasized. capacity of 290,000 gallons. The setup is

ANONYMOUS Contsd Comet Fuselage Fatigue Tests

Failure of 15CMW Turbo-Generator Low-Press- so arranged that fuselage differential
ure Turbine Spindle pressure can be obtained ranging from 0 to
ENGINEER, VOL 201, NO 5233, pp 502-505 8-t Ibs per sq. incho Vertical loads and
(1956) simulated inertia load for fuselage and
Description of No. 4 turbo-generator at cabin contents are applied by hydraulic
Ridgeland power station of Commonwealth jacks and a system of levers0 Vertical
Edison Company, near Chicago, which failed wing loads applied at the front and rear
during routing over-speed trip test. Re- spars with gust loads superimposed on
port of investigation of design, manufact- steady flight loads are imposed by a sys-
ure and metallurgy spindle which indicated tem of hydraulic jacks„ The water tank
that accident was caused by hydrogen flakes test is designed to simulate as closely
or thermal cracks developed during heat as possible loads met during representa-
treatment.
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ANONYMOUS ANONYMOUS

Fatigue Problems Metal Fatigue; A Bibliography of

Unpublished Reports
AIRCRAFT ENGINEERING, (July 1956)
VOL. XXVII, NO. 329, P 215
LIGHT METALS BULLETIN (ENGLAND)
ANONYMOUS VOL 18, NO. 2, p 54 (January 20, 1956)
The Aircraft Fatigue Problem
THE AEROPLANE, (September 21, 1956)

ANONYMOUS ANONYMOUS

Importance of the Surface Effect on Research and Apparatus Testing:

Fatigue Testing by Ultrasonics
the Initiation of Fatigue Cracks
(Swedish) AIRCRAFT ENGINEERING, VOL 28, NO. 332,
JERNKONTORETS ANNALER, VOL 140, NO.5 pp 368 (October 1956)
PP 360-372 (1956)
Fatigue testing by ultrasonics was
Fatigue experiments on three carbon• developed by Mullprd Ltd., Century House,
steels and one chromium-nickel steel Shoftesbury Ave., W.C.2. The fatigue
indicate a surface effect which appears testing of a material (not a finished
to contribute to the initiation of fatigue product) can be accomplished in a few
cracks.

ANONYMOUS Cont'd Research and Apparatus Testing:

Low-Temperature Fatigue Testing of
Copper hours. It is in the experimental stage
METALLURGIA, VOL 53, NO.319 pp 212-213, and will have to be compared with tests by
216 (May 1956) conventional methods.
Axial load fatigue tests under com- The specimen is designed to be longi-
pletely reverse stress made on pure copper tudinally resonant at approximately 20,000
at 4°, 20°, 90° and 293°K. Special mach- cps and stresses on the order of 33,000
ine with loud-speaker type drive - 225 psi can be produced. A traversing micro-
cps. scope is used to measure motion along the
specimen from which strain is calculated.

Con'td Low-Temperature Fatigue Testing. Contfd Research and Apparatus Testing

Results showed similar increases Artificial cooling is required to

in ultimate tensile strength and in prevent undue temperature rise in the
cyclic stress for a given life as tem- test piece„
perature was lowered. Very brief,
one table. Without cooling a specimen becomes
white hot and breaks in a few minutes.

3
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 BARBER, A, Do

ANONYMOUS International Conference on Fatigue in

Aircraft Structures
Shot Peening for Safety AIRCRAFT ENGINEERING, VOL 28, NO 326,
pp 130-133 (April 1956)
STEEL PROCESSING, VOL 42, pp 103-104,
110 (February 1956) Summaries of the papers presented
at Columbia University on January 30, 31
and February 1, 1956. (Complete papers
and edited discussion have been published
under title Fatigue in Aircraft Structures

ATKINSON, R. J. Cont'd International Conference on Fatigue

Fatigue Testing in Relation to Transport by Academic Press, Inc., 125 East 23d St.,
Aircraft New York, N.Y.)
PAPER from "FATIGUE IN AIRCRAFT STRUCTURES," Seventeen papers were presented dur-
ACADEMIC PRESS, pp 279-294 (1956) ing the 3-day conference; they fall into
one of three general categories: (l)
Examples of fatigue data on which design 5 papers on Physical Theories of Fatigue;
might be based, fatigue loading actions, (2; 6 papers on Prediction of Fatigue
and a scheme of testing geared to design Life and Strength; (3) 6 papers on
and early production stages are discussed. Prevention of Fatigue Failure.
9 ref.

BAILEY, R. W. BARDGETT, W. E.
Usefulness and Role of Repeated Strain Testing Lead Additions: Effect on Fatigue Pro-
as an Aid to Engineering Design and Practice perties of En 24 and En 26 Steels
PAPER NO. 14 of Section 2, from INTERNATION- IRON AND STEEL, VOL 29, PP 392-395
AL CONFERENCE ON FATIGUE OF METALS, VOL I, (August 1956)
INSTITUTION OF MECHANICAL ENGINEERS,
7 pages, (1956)
Typical cases illustrating value in
design and material selection.

BALDWIN, T. BARROIS, W.
Fatigue des Structures D'Avions
Significance of the Fatigue of Metals II. Endommagement par Fatigue et Rupture
to Railways des Pieces Entaillees (French)
PAPER NO. 4 of Session 9, INTERNATIONAL "DOCAERO", NOVEMBER 1956
CONFERENCE ON FATIGUE OF METALS, VOL II,
INSTITUTION OF MECHANICAL ENGINEERS, Study of fatigue in aircraft struct-
11 pages (1956) ures. Evaluation of S-N curves, notch
effects, influence of coatings, heat treat-
ment, mean stress, residual stresses

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BARRETT, A. J. BARROIS, W.

Summary of Discussions (Aircraft Design On the Fatigue of Composite Structural

Philosophy) Elements of Aircraft (French)

JOURNAL OF ROYAL AERO. SOC., VOL 60, METAUX CORROSION - INDUSTRIES (FRANCE)
NO. 545, PP 301-330 (May 1956) 30, NO. 364, PP 464-504 (December 1956)

Summary of the Society's All-Day The repetitive load acting during

Discussion on Aircraft Design Philosophy, flight on commercial and military aircraft
held on November 17, 1955. flying under various conditions, is analyz-
ed.
Following a discussion of the basic
phenomena of fatigue and its statistical

Cont'd Aircraft Design Philosophy Cont'd Fatigue of Composite Structural

Elements of Aircraft
Aspects covered were design require- implications, the results are applied to
ments, electronic and mechanical aids to the investigation of the fatigue endur-
flight safety, fatigue, aircraft inspect- ance of aircraft complex structural ele-
ability, operational damage, and design ments. It is said that there is no
methods. The discussion on fatigue valid criterion for damage calculation
dealt largely with the fail-safe concept and therefore it is not possible to re-
present the complex stresses occuring
under service conditions by some simpler

BARRETT, J 0 C., R. W. HUBER & Cont'd Fatigue of Composite Structural

I. R. LANE, JR. Elements of Aircraft
equivalent. Consequently, rigorous cal-
Arc-Welding Titanium culations of expected aircraft life are
not believed to be possible so far, but
BUREAU OF MINES REPORT OF INVESTIGATIONS by carrying on the work of fatigue test-
5178, pp 39-44 (JANUARY 1956) ing on the actual structural parts and
by continuous observation of their be-
Arc welded samples of unalloyed havior in service the accuracy of these
titanium made in a chamber of inert gas calculations will steadily improve.
such as helium with a stream of inert

Cont'd Arc-Welding Titanium Cont'd Fatigue of Composite Structural

Elements of Aircraft
gas issuing from the torch and, if poss-
ible, a trailing shield produced speci- The aircraft designers are reminded
mens which had bending fatigue strengths to keep an eye on vital and hidden struc-
comparable to that of the basic material, tural parts where a developing crack may
be passed undetected and thus, ultimately
may cause failure.

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BARWELL, F. T. and D. SCOTT BESRY, W. R.
Effect of Lubricant on Pitting Failure Spring Design: Part XXVII
(Corrosion Fatigue) of Ball Bearings
ENGINEERING (BRITISH PUBLICATION) MECHANICAL WORLD AND ENGINEERING RECORD
July 6, 1956 VOL 136, pp 512-617 (November 1956)
A four-ball testing machine was de- Fatigue Failure and recommendations
vised for comparing the effect of various for designing springs to withstand fluc-
types of lubricant on pitting failure uating or cyclic loading.
(corrosion fatigue). The results were (To be continued)
reasonably reproducible.

BA3TENAIRE, FRANCOIS BESUKLADOV, W.F., CHUVIKOVSKY, G.S.,

CHUBIKOVSKT, W.S. and E. M. SHEVANDIN
A Certain Property of the Statistical
Distribution of Life in Fatigue Re- Fatigue of Shipbuilding Steels and the
sistance Tests (French) Strength of Ship Structures
COMPTES RENDUS, VOL 243, No. 18 pp 1270- PAPER NO. 9 of Session 9, INTERNATIONAL
1273 (October 29, 1956) CONFERENCE ON FATIGUE OF METALS, VOL II,
INSTITUTION OF MECHANICAL ENGINEERS,
The mathmatical average or the var- 9 pages (1956)
iation observed in a sample are ex-
pressions with no statistical significance

BENE3, F. BETTEREXE, W. and A. W. FRANKLIN

Fatigue Limits of Screws (Czech.) Development of Nickel-Chromium Base
Alloys for High-Temperature Service:
STROJEffiNSTVI, VOL 6, NO.6, pp 388-394 II. Creep, Rupture, and Other Pro-
(June 1956) perties.
Influence of material and its proper- METAL TREATMENT AND DROP FORGING.
ties. Mechanical properties of bolts VOL 23, pp 385-389 (October 1956)
manufactured of various materials and
heat treated for uniform strength.

BENNETT, JOHN A. Cont'd Development of Nickel-Chromium,etc

The Distinction Between Initiation and
Propagation of a Fatigue Crack
Progressive improvement in nimonic
PAPER NO. 8 of Session 6, from INTER- alloys has resulted in increasing resis-
NATIONAL CONFERENCE ON FATIGUE OF METALS tance to creep and rupture at elevated
VOL II, INST. OF MECH. ENGINEERS, 5 p temperatures. Corresponding improvement
and 3 plates (1956) in fatigue strength and in short-time
Distinction may be difficult to make tensile and torsion properties is as-
when, the cracks are small, and any non- sociated with increasing creep resistance.
destructive method for identifying cracks
should be verified by metallographic ex-
amination of sections cut through the
questionable markings.
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BLATHERWICK, A. A. and B. J. LAZAN BOWMAN AND DOLAN
Resistance of Low-Alloy Steel Plates
Effect of Changing Cyclic Modulus on to Biaxial Fatigue
the Bending Fatigue Strength
WELDING JOURNAL, VOL 35, NO. 2,
pp 102-s - 108-s (February 1956)
AMERICAN SOCIETY FOR TESTING MATERIALS
ANNUAL MEETING, 1956 3/4 in» thick steel unnotched,
notched and welded plate specimens were
subjected to cyclic biaxial tension.
The studies were aimed primarily at or
above the yield point strain and fatigue

BOLLER, K. H. Cont'd Resistance of Low-Alloy Steel, etc,

Fatigue Properties of Various Glass- life of less than 5 x 105 cycles. Data
Fiber-Reinforced Plastic Laminates were plotted as strain range versus cycles
to failure.
FOREST PRODUCTS LAB., FOREST SERVICE, Low alloy steels with as-received
May 1956, WADC TR 55-389 yield strengths up to 123,000 psi were
compared with plain carbon steels commonly
Fatigue strength values are presented used in pressure vessels. The steels
for 6 standard and 4 heat-resistant resin having the highest static strength demon-
strated the greatest resistance to repeat-
ed loading, but their superiority to plain

Cont'd Fatigue Properties, etc... Cont'd Resistance to Low-Alloy Steel, etc.

carbon steels was not as large as indicat-
laminates reinforced with glass fibers. ed by a comparison of yield or tensile
strengths. The fatigue strengths of weld-
Fifty-three S-N curves, represent- ed specimens were comparable to those for
ing fatigue data between 1 thousand the unnotched plate but the data showed
and 10 Million cycles, show the effect more scatter. A small notch was suffic-
on fatigue strength of a notch, moisture, ient to reduce the allowable cyclic strain
fabrics, resins, mean stress levels, range by a factor of 1.25 or morea It was
angles to warp, and temperatures up to concluded that a pressure vessel built el-
500° Fo iminating obvious flaws or severe stress
raisers could be operated at stress levels
well in excess of current code limitations
without fear of fatigue failure.
BORE, C. L- BRAILEY AND DONNELLEY
The Presentation of Fatigue Data for
Fatigue-Life Calculations Plain-Bearing Fatigue Testing
ROYAL AERO. SOCIETY JOURNAL, VOL 60, COMMUNICATIONS AND ELECTRONICS, VOL 3,
PP 331-346 (May 1956) pp 16-18 (January 1956)
A simple and convenient "endurance Testing of engine-bearing systems
chart" for the presentation of basic using electronic and hydraulic techniques.
fatigue data which shows the effects of
mean stress, residual stress, and pre- Diagrams, photographs, graph.
tension, and displays several interest-
ing features of the data.
Tables, graphs, diagrams. 10 ref.
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 BROCK, G. W. and G* M» SINCLAIR
BREEN, Jo Eo and JOSEPH PL LANE
An Investigation of Fatigue and Character-
Effect of Dispersion of Alpha Phase on the istics of Leaded Alloy Steel
High-Temperature Fatigue Properties of DEPT. OF THEORETICAL AND APPLIED MECHANICS
Alpha-Beta Brass REPORT NO. 105, (Sponsored by BUREAU OF
ASM TRANSACTIONS, VOL 49, PREPRINT NO.39 ORDNANCE, DEPT OF THE NAVY, Contract No.
NOrd 16417), UNIV. OF ILLINOIS, Sept.1956
24 pages (1956)
An investigation was made to determine
A comparison at elevated temperature the influence of small amounts of lead on
of the tensile-fatigue and stress-rupture the tensile and fatigue properties of SAE
properties of a two-phase alloy as modi- 1018, 1045, 8620, 4140, and 4340 steel.^
fied by changes in dispersion. Statistical methods were used to determine
the mean fatigue limit and the mean fatigue

BRENNER, P. Cont'd Investigation of Fatigue...etc.

Static and Fatigue Properties of High= life. It was found that the lead had little
Strength Aluminum Alloys influence on the tensile properties, and the
ALUMINUM, VOL 32, NO 12, pp 756-768 mean fatigue limit on the leaded steel was
(December 1956) only significantly reduced at ultimate
strengths above 130,000 psi, the notch sen-
Dimensioning of highly stressed parts sitivity of the steel being little effected.
particularly those of aircraft and pass- At stresses above the endurance limit,
enger vehicles, must be based on informa- leaded SAE 1018 and 4140 tended to give
tion about fatigue as well as static mech- longer fatigue lives on smooth specimens,
anical properties. This has stimulated but no information is available on the
the author to carry out tests of the fat- other steels or on notched specimens.
igue behaviour of a series of high-

Cont'd Static and Fatigue Properties, etc BROOKS, P. D.

strength Al alloys of the types: AlCuMg, Structural Fatigue Research and Its
AlZnMg, AlZnMgCuo Endurance limits for Relation to Design
smooth specimens is about proportional
to the static tensile strengths. In the PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
notched state, the endurance limit seems ACADEMIC PRESS, p 207-232, 1956.
to be proportional to the tensile and Sequential steps in handling major
yield strengths up to tensile strengths fatigue requirements on complete design
of about 65, and to yield strengths of projects as applied to two typical air-
about 55 kg/sq mm (41 and 35 psi,approx)» craft, namely, medium-range transport,
When these values are exceeded, it re- and long-range interceptor. 11 ref.
mains constant or even falls slightly.

Cont'd Static and Fatigue Properties, etc. BtiHLER, HANS AND WALTER SCHREIBER
There seems no justification for the wide- Application of Statistical Methods for
spread view that a limitation of the yield- Analyzing Short-Lifetime Fatigue Strength
strength ratio has a favorable effect on (German)
the fatigue characteristics in the notched
state. The effect of compression, of struc- ARCHIV FflR DAS EISENH&FTENWESEN, VOL 27, NO.3,
tural deterioration through overheating, pp 201-209 (1956)
and primary precipitation of intermetallic The results of fatigue tests at
compounds on endurance limit have also been relatively high reversed stresses are
studied„ It is shown that the endurance analyzed by statistical method. The
limit of structural parts can be improved specimens were made from aluminum alloys,
not only by design measures, but also by cast iron, and steel,,
suitable heat treatment of the alloys„ Thirty-seven groups of 100 specimens
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BROOM, T., J. H, MOLINEUX AND BUNYAN, To W.
V 0 N0 WHITTAKER
Service Fatigue Failures in Marine
Structural Changes During the Fatigue of Machinery
Some Aluminum Alloys
PAPER NO. 6 of Session 9, INTERNATIONAL
JOURNAL OF INSTITUTE OF METALS (ENGLAND) CONFERENCE ON FATIGUE OF METALS, VOL II,
VOL 84, PART 10, pp 357-363 (June 1956) INSTITUTION OF MECHANICAL ENGINEERS,
12 pages (1956)
Possible structural changes occur-
ring during the fatigue of a number of
representative aluminum alloys are consid-
ered with reference to their likely effects

Cont?d Structural Changes During Fatigueeo, BURNS, ANNE

on fatigue Iife0 A comparison of fat- Fatigue Loadings in Flight: Loads in the
igue tests carried out at room tempera- Wing of a Varsity
ture and at liquid-air temperature pro-
vides direct evidence for the supposition AJR.C. TECHNICAL REPOT (18647), C.P. NO 285;
that the disappointingly poor room-tem- MINISTRY OF SUPPLY, AERONAUTICAL RESEARCH
perature fatigue properties of the high- COUNCIL, LONDON, ENGLAND (1956)
strength aluminum alloy D0T.D» 683 are
due to over-ageing during test. By Data are presented on the number of
similar tests, and by analogy with other load cycles of various magnitudes occurring
alloys, the relatively good fatigue proper- in the wing of a Varsity in normal ground
and flight conditions. The conditions

Ccnt'd Structural Changes During Fatigue., Contfd Fatigue Loadings in Flight:...

ties of the medium-strength aluminum-?^ include taxying, take-off, landing, and
magnesium alloy are shown to be associated flight in turbulence. The relative im-
with work-hardening and strain-ageing, portance of the loads in the different
The effect described can be understood conditions is illustrated by reference
in terms of obstacles to movement of dis- to the loads in a typical flight,
locations and the consequences of the mi- A relationship is determined between
gration of lattice sites produced by de- wing loads and accelerations in turbulence
formation « Fatigue tests have also been so that the test results can, if required,
carried out at room temperature and be related to gust data obtained operation-
liquid-air temperature on an alloy,S,AoP0, ally by means of the counting accelero-
meter0

Cont'd Structural Changes During Fatigue, CANTA, Go M.

Symposium on Testing Machines:
which does not undergo structural changes Ho Fatigue-Testing Machines (Dutch)
during fatigue,
METAALINSTITUUT T.N.O., NO. 45 >
Some principles affecting the 7 pages (October 1956)
development of new alloys of good fatigue
properties are discusseda
Characteristics of three types of
fatigue-testing machines are presented,

9
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CARPENTER, S, R. CAZAUD, R.
High-Flying Titanium
Prestressing Prevents Fatigue Failures
WESTERN MACHINERY AND STEEL WORLD, from Occurring«
VOL 47, pp ^8-73 (June 1956) FRANCE INDUSTRIES, NO. 15 (MARCH 1956)
The strength-weight properties of (ENGINEERING DIGEST, VOL 3, NO. 1,
titanium heat-treat considerations, fatigue pp 22-24, January 1957).
characteristics, and some shop-forming Hie principles of setting up residual
methods with reference to aircraft. stress patterns to offset the forces exper-
Tables, photograph, graphs. 13 ref. ienced under working condition are outlined.
These prestresses can be induced by

Cont'd Prestressing Prevents Fatigue, etc.

CASE, ROBERT Co
Interpreting Service Damage in Rolling- mechanical, heat or chemical treatments.
Type Bearings
Test results are shown for two alumin-
BUREAU OF SHIPS JOURNAL, VOL 5, pp 6-12 um alloys and a low-carbon steel. Super-
(October 1956) ficial hardening of steel is given special
Abuse before and during mounting; re- attention as the endurance limit can be
sults of improper mounting; inadequate lub- almost doubled by this treatment.
rication; wear from abrasives; corrosion;
seizure and smearing; passage of electric
current; fatigue.

CAZAUD, R. CHANG, ToS. and Kesler, C.E.

Fatigue Failure and Service Experience Static and Fatigue Strength in Shear of
With Particular Reference to the Shape Beams With Tensile Reinforcement
of the Part DEPT. OF THEORETICAL AND APPLIED MECHANICS
REPORT NOo 108, ENGINEERING EXPERIMENT
PAPER NOo 3 of Session 7, INTERNATIONAL STATION, UNIV. OF ILLINOIS, October 1956
CONFERENCE ON FATIGUE OF METALS,
INSTITUTION OF MECHANICAL ENGINEERS, Dimensional analysis is employed in de-
6 pages (1956) riving expressions for the initial crack-
ing load and the ultimate strength in shear
of simply supported reinforced concrete
beams with tension reinforcement only. These
expressions, which include size effect, are

CAZAUD, Ro Confd Static and Fatigue Strength in Shear *

Fatigue Strength of Machine Parts (French) converted into nomographs for ease of ap-
plication» This study of static strength
METAUX, CORROSION-INDUSTRIES, VOL 31 includes results from tests of 105 beams,
NO. 365, pp 1-17 (January 1956) 42 of which were tested by the authors.
Fatigue tests were made on 39 rein-
Discusses endurance limits of steels forced concrete beams with tension rein-
and alloys, influence of transformation forcement only. These beams were simply
conditions, the effect of size and shape, supported on a span of 60 in. and loaded
surface state, temperature, and corrosion. at the third points. Statistical studies
of the fatigue behavior with regard to
Graphs, tables, photographs. 23 ref. initial diagonal cracking and final failure
are included0
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10
CHILDS, J.K., LEMCCE, M.M. COATES, R. C. AND J. A. POPE
Fatigue Investigation on High Strength Steel Fatigue Testing of Compression-T^rpe
Coil Springs
SOUTHWEST RESEARCH INSTITUTE
July 1956, preprint. WADC TR 56-205 PAPER NO. 6 of Session 7, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL IH
A single heat of aircraft quality INSTITUTION OF MECHANICAL ENGINEERS (1956)
SAE 4340 steel, heat-treated to three high
strength levels, was tested by the Prot 15 P.
method in axial loading to determine the Spring-fatigue-testing machines. Ef-
variation in fatigue properties. In addi- fects of shot-peening, scragging, scrag-
tion Prot rotating beam tests were per- ging and peening, and mean stress.
formed at one of the strength levels0

Cont'd Fatigue Investigation, etc... COFFIN, JR., LoF.

Conventional S-N curves were determined Design Aspects of High-Temperature Fatigue
at this same strength level to provide with Particular Reference to Thermal Stresses
factors necessary to correct the Prot
method mean failure stresses to mean en- TRANSACTIONS OF THE ASME, VOL 78, NO.3,
durance limit values. PP 527-533,( April 1956)
A criterion for fatigue failure has
The endurance limit under completely been proposed, based on experiments carried
reversed axial stress increased with an out on test specimens subjected both to
increase in ultimate strength from 190,000 constrained thermal cycling and constant-
to 260,000 psi, but decreased when the temperature strain cycling.

Cont'd Fatigue Investigation, etc... Contfd Design Aspects of High-Temperature...

This criterion relates the number of
same material was heat-treated to 300,000 cycles to failure with the plastic strain
psi. change per cycle. The application of such
a criterion to design, where thermal-stress
Under high mean tensile stress, the fatigue is the principal factor, is dis-
300,000 psi material did have a fatigue cussed from fundamental and practical view-
strength superior to that of the 260,000 points. From such a criterion it is poss-
psi material. ible to predict the life of a certain mach-
ine part for a calculated thermal stress, or
conversely, the thermal stress permitted for
a certain limiting number of cycles of stress

CHODOROWSKI, W. T. COFFIN, LoF. AND J. H. READ

Fatigue Strength in Shear of an Alloy Steel A Study of the Strain Cycling and Fatigue
(With Particular Reference to the Effect Behaviour of a Cold-Worked Metal
of Mean Stress and Directional Properties) PAPER NO. 1 of Session 5, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II
PAPER NO. 6 of Session 2, INTERNATIONAL INSTITUTION OF MECHANICAL ENGINEERS(l956)
CONFERENCE ON FATIGUE OF METALS, VOL 1, 12 p
INSTITUTION OF MECHANICAL'ENGINEERS
12 p. 2 plates (1956) The strain softening of AISI-347
stainless steel is examined as a function
Tests under torsional fatigue of two of the more important variables
stresses on longitudinal oblique, and the degree of prior cold work and temper-
transverse specimens. ature.
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 COLB1AN, J. J. AND W« N0 FINDLEY COCMBS, AoGJi., F. SHERRATT, AND J.A. POPE
A Theory of the Non-Linear Influence of An Analysis of the Effects of Shot-Peening
Normal Stress on Fatigue Under Combined Upon the Fatigue Strength of Hardened and
Stresses Tempered Spring Steel
TECHNICAL REPORT NO. 4 (ENGINEERING MATER-
IALS RESEARCH LABORATORY, DIV. OF ENGIN- PAPER NO, 1 of Session 3, INTERNATIONAL
EERING, BROWN UNIV), November 1956 CONFERENCE ON FATIGUE OF METALS, VOL I,
INSTITUTION OF MECHANICAL ENGINEERS
In previous papers it has been sug- 10 p, 4 plates (1956)
gested that fatigue results from alternat-
ing shearing strees, and that the resist- Effects of shot velocity, energy,
ance of material to this action is influ- and size on fatigue life.

Contfd Theory of the Non-Linear Influence.. CORDIANO, COCHRAN, JR., AND WOLFE
enced t?y the normal stress acting on the Effect of Combustion-Resistant Hydraulic
critical shear plane. In an earlier Fluids on Bail-Bearing Fatigue Life
paper the influence of the normal stress
was considered to be linear» The present ASME TRANSACTIONS, VOL 78, pp 989-993
paper investigates the possibility that (July 1956) discussion, pp 994-996
the influence of the normal stress may be Phosphate ester, phosphate ester-base,
nonlinear. The possible effect of aniso- and water-glycol-base combustion-resistant
tropy is also considered. A nonlinear the- fluids and a petroleum oil were investi-
ory is developed and compared with other gated to determine relative effects when
used as flood lubricants, on the life of
angular-contact ball bearings.

Cont'd Theory of the Non-Linear Influence.. CORNILLION, J.

Some Remarks on the French Approach to
theories and with results of tests of the Problem of Fatigue
SAE 4340 steel at a hardness of Rockwell PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
C-25. ACADEMIC PRESS, pp 317-322
General outline of methods employed
including evaluation by cumulative damage
Dr<, Grover has a copy of this paper theory and fatigue tests.
9 ref.

CONN, HARRY CORTEN, Ho To AND T. J. DOLAN

Engineering for You and Me. II Strength, Cumulative Fatigue Damage
Fatigue, Failure in Fasteners PAPER NO. 2 of Session 3, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I,
MACHINEAND TOOL BLUE BOOK, VOL 51 INSTITUTION OF MECHANICAL ENGINEERS
P 105, 12 P (mARCH 1956) 14 Po (1956)
Mechanical, physical, and chemical A phenomenological hypothesis of
properties of metals; factors that cause fatigue damage, visualized as the nucle-
failures in dynamically stressed parts» ation of submicroscopic voids which de-
velop into cracks, is given in terms of
Tables, graphs, diagrams„ 3 ref„ the numbers of damage nuclei and the rate
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CORTEN, H.T., AND SINCLAIR, G.Mo CRAMER, R. E.
A Wire Fatigue Machine for Investigation Fourteenth Progress Report on Shelly
of the Influence of Complex Stress Histories Rail Studies at the Univ. of Illinois
AMERICAN RAILWAY ENGINEERING ASS'N
AS1M PREPRINT NO, 67, 1956 Annual Meeting BULLETIN, VOL 57, NO. 528, pp 850-857
A wire fatigue testing machine is des- February 1957
cribed that was designed especially for the
study of the effect of complex stress his- This investigation involved rolling
tories. The machine is based on the prin- road tests on high silicon rails and on
chrome vanadium rails.

Cont!d A Wire Fatigue Machine„*.. Cont'd 14th Progress Report-Shelly Rail....

ciple of a deflected rotating strut, and
the stress level may be changed rapidly
without inducing noticeable extraneous The results show the high silicon
vibration in the specimen„ The specimen rails to be in the range of 50 to 100 per
is driven from one end only. cent better than standard carbon steel
rails in resisting development of shelling
Results of constant stress amplitude failurese The chrome-vanadium alloy rail
tests at 6500 rpm on steel wire are present- appears to be more resistant.
ed and analyzed statistically0

COTTELL, GoA. CRAMER, R. E.

Lessons to be Learnt From Failures in Investigation of Failures in Control
Service Cooled Railroad Rails
PAPER NO. 1 of Session 7, INTERNATIONAL AMERICAN RAILWAY ENGINEERING ASS'N BULLETIN
CONFERENCE ON FATIGUE OF METALS, VOL III VOL 57, NO. 528, pp 787-793 (February 1956)
INSTITUTION OF MECHANICAL ENGINEERS Article summarizes the results of
9 PC 4 plates (1956) a study of 43 failed controlled cooled
railso Failures have been catagoried as
Causes, recognition and prevention of transverse fissures, detail fractures
corrosion fatigue and dry fatigue. from shelling, fractures from welded-
engine burns, and head and web separating
failures.

COX, H. L. CROSSLAND, B.
Effect of Large Hydrostatic Pressures
Stress Concentration in Relation to Fatigue on the Torsional Fatigue Strength of an
Alloy Steel
PAPER NO. 16 of Session 2, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I, PAPER NO. 8 of Session 2, INTERNATIONAL
INSTITUTION OF MECHANICAL ENGINEERS CONFERENCE ON FATIGUE OF METALS, VOL I
12 p, 12 plates (1956) INST. OF MECH. ENGINEERS, 14 p. (1956)
The present state of knowledge of Fluid pressure has no effect on
stress concentration in relation to needs the stress-strain curve except to increase
of designer. the strain to failure by about 80$ at
20 tons per sq. in. pressure.

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13
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CRUM, R.A. AND B. D'APPOLONIA DANFGRTH AND ANDERSON
Fatigue Damage Measured by Deflections of Vibratory Stress Measurements in Multi-
Rotating Beam Specimens stage Compressor Blading
SESA PROCEEDINGS, VOL XIV, NO.l PROCEEDINGS OF THE SESA, VOL 14 NO. 1
pp 71-82 (1956) (1956)
An apparatus constructed to measure
and continuously record the mid-span deflec- Strain-gage measurements have become
tion and the energy dissipated during cyclic indispensable in evaluation and development
loading of rotating beam specimens tested at of fatigue-resistant blading in modern
various speeds is described. multistage aircraft gas turbines.

Cont*d Fatigue Damage Measured by Deflections Contf d Vibratory Stress Measurements....

Section I describes significant develop-
Results are reported from tests made on ments made in the application, monitoring,
H-75A titanium alloy. and recording of blade-vibration data in
The material exhibited a pseudo-elastic multistage compressors.
behaviour at stresses above the static elas- Section II outlines essential points of
tic limit during the early stages,, The test formulation, illustrates by selected
deflection increased slowly until it equal- examples the wide variety of blade vibra-
led the plastic deflection as found under tion to be anticipated, and indicates the
static load, when it increased rapidly to manner in which blade-vibration observation
failure. The transition is regarded as can serve performance as well as structural
the threshold to severe damage„ improvements.

GUI-MINGS, H.N., F.B.STUIEN, AND DAVIES, R. B., J.T.MANN, AND D.S.KEMSLEI

V. C. SCHULTE
Hardness Changes During Fatigue Tests on
Relation to Inclusions to the Fatigue Copper
Properties of SAE 4340 Steel
PAPER NO. 9 of Session 6, INTERNATIONAL
ASM TRANSACTIONS, VOL 49, PREPRINT NO.23 CONFERENCE ON FATIGUE OF METALS, VOL II,
(1956) 36 p. INST.OF MECH.ENGINEERS, 8 p (1956)
Progressive hardness changes during
Fatigue test data. An explanation fatigue; hardness traverses along fract-
concerning the mechanism of fatigue. ured specimens; metallographic examination.

DAVIDENKOV, N.N. AND E.IoBELIAEVA DEMER, L. J.

Investigation of Impact Fatigue (Russian)
Bibliography of the Material Damping
METALLOVEDENIE I OBRABOTKA METALLOV Field
NO 11, pp 4-10 (November 1956)
WADC TECHNICAL REPORT NO. 56-180
Fatigue limit of 10^ cycles under (June 1956)
static and dynamic conditions of alter-
nating loads were determined for six
kinds of alloyed steel in different ther-
mal treatments.

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DEMMLER, AaW«, M.J.SINNOTT, AND Lo THCMASSEN DOLAN, THOMAS J*

Ihe Notched Fatigue Properties of Significance of Fatigue Data in Design

Some Titanium Alloys of Pressure Vessels

ASTM ANNUAL MEETING, 1956 WELDING JOURNAL, VOL 35, NO 5

pp 255s-260B (May 1956)
Considerations involved in design and
construction of full scale pressure ves-
sels for cyclic loading are reviewed. Sur-
face finish, environment, size effects,
defects, localized stress risers, metallur-

DIRKES, WoE, Contfd Significance of Fatigue Data...

A Method of Predicting the Effects of gical notches and statistical variability
Notches in Uniaxial Fatigue are considered. The danger of transfer-
ASME TRANSACTIONS, VOL 7S, N00 3 ring quantitatively the results of tests
pp 511-517, April 1956 on laboratory specimens is emphasized.
There is a limit to the increase in fatigue
This paper approaches the problem strength that may be expected by changing
of correlating notched and unnotched test to steels of higher static tensile strength
data from observations of how the mater- without careful attention to improvement of
ial may be considered to be affected under design details.
repeated stresses, A semigraphical

Cont'd A Method of Predicting the Effects., DONELY, PHILIP

method of extrapolating notched test The Measurement and Assessment of Re-
data is developed. Although the data peated Loads on Airplane Components
available do not conclusively prove the
observations reported herein, neither (Presented to the 3d Meeting of the
does presently available information refute Structures and Materials Panel of Advisory
the views presented„ Individual observa- Group for Aeronautical Research and Devel-
tions are gathered together to form a pic- opment, Langley Field, Virginia)
ture which is intended as an aid to de- April 12, 1956
signers in visualizing possible trends
even though complete test data are not a-
vailable.

DDC, JR., .E.H. DOREY, S.F. AND G. P. SMEDLEY

Aluminum Alloys for Elevated Temperature The Influence of Fillet Radius on the
Applications Fatigue Strengths of Large Steel Shafts
ASME PAPER 56-AV-8, ASME AVIATION PAPER NO. 3 of Session 3, INTERNATIONAL
CONFERENCE, March 1956 CONFERENCE ON FATIGUE OF METALS, VOL I
INST. OF MECH. ENGINEERS, 12 p (1956)
AERONAUTICAL ENGINEERING REVIEW
VOL 15, NO. 1 (January 1956) Results of full-scale torsional
fatigue tests.

15
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DRYDEN, H.L. AND TH. VON KARMAN Wo E. DUCKWORTH AND G. H. WALTER
Advances in Applied Mechanics Fatigue of Plain Bearings
VOL IV, 413 p (1956) ACADEMIC PRESS, PAPER NO.4 of Session 7, INTERNATIONAL
NEW YORK CONFERENCE ON FATIGUE OF METALS, VOL III
INST. OFMECH. ENGINEERS, 10 p (1956)
Theory and characteristics of boundary Mechanism of fatigue, determination of
layers, elastic and plastic phenonmena, fatigue strength; fatcors influencing fatigue
and fatigue properties of materials. strength*; relation between thickness and
strength of linings; stress analysis; in-
fluence of backing materials.

DUBININ, G.N. EVANS, E.B., Lo J. EBERT AND C. W. BRIGGS

Mechanical Properties of Steel After Fatigue Properties of Comparable Cast
Impregnating Its Surface With Chromium and Wrought Steels
(Russian) ASTM PREPRINT NO. 64, 1956 ANNUAL MEETING
VESTNIK MASHINOSTROENIIA, COL 36, NO.10 The fatigue properties of comparable
PP 56-58 (October 1956) cast and wrought steels in the 0.30 to
0.40# carbon range were determined on R.R,
Chromium plating steel increases its Moore (10,000 rpm) machines.
long-time strength from 40 to 50 times
and increases fatigue strength at high
temperatures.

DUBUC AND WELTER Cont!d Fatigue Properties, etc...

Investigation of Static and Fatigue Resist- A cast and wrought 1040 carbon steel,
ance of Model Pressure Vessels four low-alloy cast steels (1330, 4135>
WELDING JOURNAL, VOL 35 8630 and 8640) and four low-alloy wrought
pp 329s-337s (July 1956) steels (1340, 4140, 4340 and 8640) were
studied. The effects of steel composi-
As part of a program of pressure ves- tion and heat treatment, surface finish,
sel research model vessels (ID-12W; t = 3/4") directionality, and section size were in-
were subjected to pulsating hydraulic vestigated with unnotched and notched
pressure at room temperature „ Pressures specimens, and the results are presented
up to 9,300 psi, corresponding to unit in numerous tables and figures0

Cont'd Investigation of Resistance Cont'd Investigation of Resistance

stresses approaching the ultimate strength ASTM A-302 Grade B steel (a 50,000
of the material, were employed. The psi minimum yield point manganese-molyb-
weakest zones were found to be in the joint denum grade) withstood higher pressure
between the shell and head and in the regions than ASTM A-201, Grade A steel (30,000
of openings for attachment. Despite num- psi minimum yield point) but the latter
erous intentional and unintentional stress was less notch sensitive.
risers on the outer surface of the shell,
no fatigue failures occurred in this area.
Design details such as the shape of the
head were of major importance.

16
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EBNER, M.L, AND W. A. BACKOFEN FENNER, A. J., K. H. R. WRIGHT
and J. Y. MAM
Fatigue and Anisotropy in Copper
Fretting Corrosion and Its Influence
AMS TRANSACTIONS, VOL XLVIII, pp 372-383 on Fatigue Failure
(195?) (ASM-SLA Classification: Q7, Cu)
PAPER NO. 3 of Session k, INTERNATIONAL
Commercially pure copper rod was found CONFERENCE ON FATIGUE OF METALS, VOL,II
to exhibit a mechanical anisotropy under INST. OF MECH. ENGINEERS, 10 p (1950
fatigue loading which the authors explain
by postulating the presence of a fibrous Characteristics and mechanism of fret,
structure of crack-like flaws aligned ting; the fretting behavior of nonferrous
parallel to the axis of the wrought speci- surfaces; fretting corrosion and service
men. failures.

Cont'd Fatigue and Anisotropy in Copper FINDLEY, W. N.

Specimens prestrained in torsion in one Fatigue of Metals Under Combinations of
direction only prior to fatigue testing Stresses
in bending (a) failed after fewer stress
cycles at any stress level, (b) developed (Series Title: Basis research on fatigue
a helical, fibrous-appearing fracture failures under combined stress) (Lecture
rather than a fracture normal to the spec- delivered to Societe Royale Beige des In-
imen axis and (c) exhibited more rapid genieurs et des Industriels, Brussels,
crack propagation than specimens that Ju e 15, 1955) June 1956, 27 p. illus.
were twisted and untwisted prior to fatigue Brown University.
testing. U.S. Army Ordnance Corps, Office of
Ordnance Research, Cont;Da-10-020-OHB-3520
Project: 7B2-001 (13^3)

Cont'd Fatigue and Anisotropy in Copper FINDLEY, W. N.

On the basis of the S-N curves for copper Theories Relating to Fatigue of Materials
rod given the two prestressing treat- Under Combinations of Stress
ments studied, the authors suggest that U. S. Army Ordnance Corps, Office of
permanent damage from the generation of Ordnance Research, Contract: DA-19-020-
cracks comparable to the postulated ORD-3520, Project: 7B2-001 (13^3)
microcracks may have occurred after less Tech. Report No.2, June 195-' (Engineering
than the first 30 per cent of the ex- Materials Research Laboratory, Div. of
pected life. Eng., Brown University, Providence, R.I.

ERKER, A. FINDLEY, W.N., J. J. COLEMAN AND

B.C.HANLEY
Design of Screw Fastenings Subject to Theory for Combined Bending and Torsion
Repeated Stresses Fatigue with Data for SAE 43UO Steel
PAPER ITO. 3 of Session 3, INTERNATIONAL PAPER NO. 9 of Session 2, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, CONFERENCE ON FATIGUE OF METALS, VOL. I
INST. OF MECHANICAL ENGINEERS, INST. OF MECH. ENGINEERS, 10 p (19:'')
13 Pa- es (1956) Mathematical formulation of the effect
of a normal stress acting on the critical
shear plane. Comparisons with experiment-
al data.

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FINDLGY, W. N. AND P.N.MATHER FISHER, W.A.P*
Modified Theories of Fatigue Failure Fatigue Aspects of Structural Design
Under Combined Stress
SESA PROCEEDINGS, VOL XIV, NO. 1 JOURNAL, ROYAL AERONAUTICAL SOCIETY
PP 35-46 (1956) VOL 60, NO 543, PP 198-202 (March 1956)
For ductile metals, a modified princi-
pal shear stress theory gives good agree-
ment with available data. For brittle
metals, and some notched steels, a modified
principal stress theory is besto

Contfd Modified Theories of Fatigue Failure.. FISHER, W.A.P. AND H. YECMANS

A proposed design expression, developed Investigation of the Fatigue of
to represent the fatigue failure of ductile Extruded Tubular Booms
(notched and unnotched) and brittle metals
under combined bending and torsion, is AERO. RESEARCH COUNCIL (GKEAT BRIT) (ARC CP 234]
also shown to be in good agreement with (1956^ 15 p, diagrams, photos, tabs.
the test data0 Three types of specimen made from alum-
While the above theories are applic- inum alloy DTD 364 were tested and the re-
able to combined bending and torsion only, sults compared. The types of specimen
modified expressions in terms of principal were; (a) extruded tube specimens lightly
stresses have been derived which are appli- machined on the outside - having transverse
cable to other states of combined stress. holes drilled through the tube (these

FINDLEY, W.No, W« Io MITCHELL, AND Contfd Investigation of Fatigue, etc....

Do D. STROHBECK
Effect of Range of Stress in Combined Bend- represented the critical section of the
ing and Torsion Fatigue Tests of 25S-T6 Viking replacement and Valetta spar boom),
Aluminum Alloy (b) plain extruded tube with the center
portion reduced to ensure failure in the
ASME TRANSACTIONS, VOL 78, NO. 7 test section, and (c) solid polished bar
PP 1481-1489,(October 1956) specimens made from the walls of the ex-
Fatigue-test data under bending, torsion, truded tubes. The results showed that
and combined bending and torsion are present- the fatigue strength of the plain tube,with
ed for mean stresses from zero to values the original extruded bore, was less than
which caused substantial yielding. half that of the polished bar. Fatigue
cracking started in every tube from an ob-
vious flaw on the inner surface.
Cont'd Effect of Range of Stress, etc... FORREST, P. G.
The mean normal stresses in the bending Influence of Plastic Deformation on Notch
and the torsion tests were corrected for Sensitivity in Fatigue
the effect of the nonlinear distribution
of stress resulting from yielding. The PAPER NO. 11 of Session 2, INTERNATIONAL
effect of stress relaxation at high mean CONFERENCE ON FATIGUE OF METALS, VOL I
stresses was investigated. The applica- INST. OF MECH. ENGINEERS, 15 p (1956)
bility of several theories of failure are The dynamic plastic strain per cycle
compared with these test dataa The in- varies during the course of a fatigue test
fluence of anLsotropy, mechanism of crack for most of the materials investigated.
formation, mean stress, and maximum stress Measurements afford no evidence that fail-
are discussed. ure by fatigue is inseparably associated
with plastic deformation.
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FORREST., P*G. FORSYTH, PoJ.E.
Fatigue in Metals The Mechanism of Fatigue in Aluminum
and Aluminum Alloys
PAPER FROM "CHEMICAL ENGINEERING PRACTICE",
VOL II, ACADEMIC PRESS, pp 176-208 (1956) PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADMIC PRESS, p 20-42, 1956
Characteristics of fatigue failures; test
methods and equipment; fatigue strength of Fatigue behavior was examined in super-
metals; influence of stress conditions, purity aluminum, Al J$ copper alloy, Al 10$
size, surface finish, and temperature; Zn and Al 7.5% Zn 2.5# Mg Alloys. Re-
corrosion fatigue. crystallization and aging was produced under
fatigue stresses at nominally room tempera-
ture and occurred mainly in localized re-
gions. 25 refs

FORREST, P.G0 FRANKS AND WOODING

The Measurement of Fatigue Damage in Some Dynamic Mechanical Properties of Heat-
Mild Steel Treated Low-Alloy Weld Deposit
ENGINEERING, VOL 182, pp 266-268 (Aug.31, 1956) 'WELDING JOURNAL, VOL 35, NO. 6,
Unnotched and notched test pieces of pp 291s-297s (June 1956)
mild steel were tested in a direct-stress Single-vee groove butt welds were
fatigue testing machine. For the stress prepared in 1" thick medium carbon steel
range investigated, no fatigue crack could plates using AWS E10015 electrodes. Ro-
be detected in unnotched test pieces until tating beam fatigue tests were conducted
within the last 2# of the fatigue life.

Cont*d The Measurement of Fatigue Damage... Cont'd Some Dynamic Mechanical Properties,etc
However, with specimens containing a notch on longitudinal (all-weld metal) and trans-
with Kt of 3«5> fatigue cracks could be verse unnotched specimens in the as-welded,
found after lo£ of the estimated fatigue stress-relieved, quenched and tempered
life. It was hoped that a frac0 stress (1050 F) and annealed conditions. The
at 196 C would be sensitive to small cracks, ratios of endurance limit to tensile strength
but icith unnotched specimens a fatigue crack varied from 0.59 to 0.69 corresponding to
0*3% caused an insignificant reduction in endurance limits from 48,000 psi for an-
frac. stress, which may be attributed to nealed material to 72,000 for stress re-
the ductility still present in mild steel lieved weldments.
when tested in static tension at 146 C.

FOHSYTH, P.J.E. FREUDENTHAL, A.M.

The Basic Mechanism of Fatigue and Its Cumulative Damage Under Random Loading
Dependence on the Initial State of a
Material PAPER NO.4 of Session 3, INTERNATIONAL
PAPER N00 5 of Session6, INTERNATIONAL CONFERENCE ON FATIGUE OF METALS, VOL I,
CONFERENCE ON FATIGUE OF METALS, VOL II, INST. OF MECH. ENGRS. 14 p (1956)
INST. OF MECH.ENGS, 5 p, 2 plates (1956)
Random fatigue-testing machine;
The microscopic changes or damage which tests on 2024 and 7075 Al alloys.
precede the formation of fatigue cracks
and the changes which occur in the small
volume of material at the tip of the crack
when propagating are illustrated in pure
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FREUDENTHAL, A.M. (Editor) FREUDENTHAL, A.M. AND R.A. HELLER
Accumulation of Fatigue Damage
Fatigue in Aircraft Structures
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADEMIC PRESS, INC., NEW YORK ACADEMIC PRESS, NEW YORK, pp 146-177(1956)
456 p,(1956)
Tape-programmed, random-load, rotating-
Proceedings of INTERNATIONAL CONFERENCE, beam fatigue testing machine is described.
held at Columbia University, Jan 30-31 Results are correlated from random testing
a.nd Feb 1, 1956. Conference sponsored machines with constant amplitude testing
jointly by Solid State Sciences Div., machines. Results of random fatigue tests
Air Res. and Dev> Command, U.S. Air Force on 2024 and 7075 aluminum alloys are tabu-
and Guggenheim Inst. of Flight Structures, lated. 14 ref.
Dept. of Civil Eng.Mechanics, Columbia
University.

fiont'd Fatigue in Aircraft Structures FREUDENTHAL AND WEINER

The Conference was devoted to three prin-
cipal aspects of fatigue in aircraft struc- On the Thermal Aspect of Fatigue
tures: physical mechanism of fatigue and JOURNAL OF APPLIED PHYSICS, VOL 27
fatigue theories, prediction of fatigue life pp 44-50 (January 1956)
and fatigue strength (testing and test in-
terpretation) and prevention of fatigue An attempt is made to explain the phe-
failure (actual design for fatigue). The nomenon of progressive deterioration of
subjects of the 19 papers range from a disr- the strength of metals and alloys due to
cussion of the fatigue nechanism on the the action of repeated-load cycles.
microscopic scale in terms of dislocations Diagrams, micrograph. 24 ref.
to the presentation and discussion of

Cont'd Fatigue in Aircraft Structures FRICKE, JR., W.G. AND M.S. HUNTER
methods used in the aircraft industry to Fatigue Crack Propagation in Aluminum
ensure adequate fatigue performance of Alloys
structural parts and specific details of
aircraft.
ASTM ANNUAL MEETING, (1956)

FREUDENTHAL, A.M. AND E.J. GUMBEL FRITH, P.H.

Distribution Functions for the Prediction
of Fatigue Life and Fatigue Strength Fatigue of Wrought High-Tensile Alloy Steels
PAPER NO. 5 of Session 3, INTERNATIONAL PAPER NO. 7 of Session 5, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I CONFERENCE ON FATIGUE OF METALS, VOL II,
INST.OF MECH. ENGRS. 12 p (1956) INST. OF MECH. ENGRS. 14 p (1956)
Fatigue theories and scatter of fatigue
strength and life; boundary conditions; dis- Includes 287 fatigue results for
tribution of fatigue life at constant stress various types or combinations of reversed
amplitude and fatigue strength at constant stress.
number of cycles; fatigue life vs fatigue
strength relations.
Dr. Grover has a copy. 20
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FROST, N.E. and C. E. PHILLIPS A. G. GARDNER
Studies in the Formation and Propagation The Influence of Design on Stress
of Cracks in Fatigue Specimens Concentration and Fatigue Failure
PAPER NO. 2 of Session 6, INTERNATIONAL MACHINERY (LONDON) VOL. 39,(Nov. 1956)
CONFERe^CE OK FATIGUE OF METALS, VOL. II, pp 1061-1066
IW3T. OF MECHANICAL ENGINEERS, 9 p, 4 plates
(1956) Determination of fatigue or endurance
The existence and formation of non-propaga- strength; causes and alleviation of stress
ting cracks in notched specimens subject to concentration; heat treatment stresses due
fatigue loading5 conditions necessary to form to design; effect of shape on cooling
non-propagating cracks and their effects on speed.
notch sensitivity;strength-reduction factors
of cracks; crack propagation.

tfRQST, N.E. and C. 3. PHILLIPS

GAROFALO, F. and R. ROSLOFFS
The Fatigue Strength of Specimens
Containing Cracks Statistical Analysis of Fatigue Data
THE CHARTERS HECHANICAL 1LNGINEBR, THE
JOURNAL OF THE INSTITUTION OF iiECHANICAL ASTM ANNUAL MEETING,(1956)
SNGIKESRS, VOL. Ill, NO. 3,(MARCH 1956)
page 155.

GASSNER, E.
GADD, £. R.
Effect of Variable Load and Cumulative
Damage on Fatigue in Vehicle and Airplane
Fatigue in Aero-Engines Structures: The Fatigue Strength of
PAP£R NO. 5 of Session 8, INTERNATIONAL Vehicle and Aircraft Components
CONFERlil\lCIi ON FATIGUE OF METALS, PAPER NO. 10 of Session 3, INTERNATIONAL
INSTITUTION OF MECHANICAL ENGINEERS CONFERENCE ON FATIGUE OF METALS, VOL. I,
16 pages (1956) INST. OF KECK. ENGINEERS, 8 pages (1956)

Results of practical-vehicle-running
and laboratory-program tests are compared

GARCIA-1-iARTIN, ZG3HIO GASSNER, 14.

Investigation of the Fatigue Strength Performance Fatigue Testing with Respect
of Butt-folded Joints in a tfeldable to Aircraft Design
l!
Lloydr:«Type Spanish Steel (Spanish) PAPER KRO-i "FATIGUE IN AIRCRAFT 3TRUCTtE.;i;S»
ACADEMIC P&233, pp. 17B-2Q6, 0-956)
1K3TITUTO mi HIEiiRQ Y DSL AC&tO,
VOL 9, MC. 46, pp 519-535 (May 1956) Survey of fatigue testing in the German
Aeronautical Research Institute, 193&-1945,
Study c.C ~oho fatigue strength, under and in the Laboratorjr for Performance Test-
clyn£--.-,ic beudin>: and traction forces, of the ing since the war, including wing load
base metal. Also the effect that the distributions, and service performance
butt-welded joint and extra thickness of
the vrGjcling bead have on this strength. tests. 8 ref.

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GA3SNER, I. E. GELA, LEPKOWSKI AND GADE
The Problem of Fatigue Strength in Aircraft How 7 Nonferrous Metals Perform at
Structures (German paper translated by Low Temperatures
Tiber Haas)
MATERIALS & METHODS, VOL 44, PP 116-102
AlitCilAFT ENGINEERING, VOL.28, NO.329 (September 1956)
PP 22F-234 (July 1956)
Tensile, fatigue, and impact proper-
Evaluation of allowable stresses for ties of BeCu, phosphor bronze, Ag solder,
kust loading of passenger transports as Mo, W, Ta, and Nilvar.
published, in the 1936 German Strength Re-
quirements BVF (Bauvorschriften fflr Flug-
zouge). Concluded that requirements are
now unconservative, principally due to

Contfd Problem of Fatigue Strength, etc. GIDDINGS, H.

to increased, flight speeds and high-strength Aircraft Fatigue
:-Y.aterials. BVF requirements assumes a JOURNAL ROYAL AERONAUTICAL SOCIETY (ENGLAND)
;.:v;vpie relation between static strength and
fiVii^ue strength of actual structures. VOL 60, KO. 545, PP 301-330 (May 1956)
Ii-xaraple of simplified beam of high-strength The article attempts to trace briefly
aluminum, designed to the BVF requirements, the development of aircraft fatigue over
fihown to havo a life of only 2400 hours by the past ten years and to present some of
tost; desired life of transport aircraft is the problems and the methods being used
;;(.-,CGO-5C,000 flight hours. In this range to solve them and to emphasize the very
ci' flight time, the life calculated by wide extent to which fatigue affects air-
cuiaulative-daiaage theory is stated to be craft design today.

Cont'd Problem of Fatigue Strength, etc. Cont'd Aircraft Fatigue

viiGonsorvative by a multiple. This is The widely varying nature of fatigue
;-tbributed to the disregard of loads below loads, met by an aircraft compared with nest
the fatigue limit, "although their contrib- machinery is one reason for the relative
utory effect in the occurence of fatigue difficulty of the aircraft problem. Host
failures was proved at an early stage (ref. fatigue loading conditions, as distinct from
D7L .toport FB 1461, August 30, 194l)n. fatigue stresses, are fundamental and the
Author proposes more tests of typical designer can do little or nothing about them,
c-.lrcraft structures and material.s under a In some cases, however, the operator can
inlfor:; frequency distribution law for reduce these loads. Internal stress can
^uoG leading. From these, new design arise from incorrect fit in a fabricated as-
ivies ciiii be established. sembly or in forging or heat tre£.t=:ient, :.xd
can quite easily amount to 10,000 Ibs/sq In

6ont!d Aircraft Fatigue

GAi'TO, F. in aluminum alloy parts. The effect as far
.fi
.aiHuonce of Iron and Silicon Contents on as fatigue is concerned is equivalent to
1-j-e i-Vti^ue Resistance of Ergal (Italian) that of raising the nean load, rhis is B,
factor the production engineer can do some-
^LLUwIittC, VOL 25, NO. 4, PP 175-186 thing about, by control of tolerances and
Mioril 1956); discussion p. 186. fits and by the use of correct heat treat-
T-c influence of different iron an-d ment temperatures and by the use of inter-
silicon contents on the fatigue resistance mediate stress relief treatments in machin-
i;io.er rot at ing-bending stress of Srgal-type ing operations. The .author discusses r-•>-•-
;••;'.loys v-as determined. More alloying de- craft fatigue from the point of view of
Ci'et.'ujs ':he resistance of fatigue. fatigue loading conditions, fatigue strengt!
J'.bles, graphs, diagrams, micrographs, and design, inspection and maintenance,
"•;:o'c,o._-<V:^h3 . 8 refs. and "fail safe" design.
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22 (Continued)
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Cont'd Aircraft Fatigue H. GIDDINGS GILBERT, G.N,J. and K0 B. PAIMER
He recommends that in designing for The Influence of Understressing on the
fatigue the designer should (l) carry out Fatigue Properties of Flake Graphite
an analytical study of the operating load- and Nodular Graphite Cast Irons
ing conditions of all primary components,
(2) give careful consideration to the BRITISH CAST IRON RESEARCH ASSOCIATION
choice of materials and stress level, using JOURNAL, VOL 6, pp 410-421 (Dec. 1956)
the S-N data most relevant to the particu-
lar application and carrying out tests
where suitable data are not already avail-
able, (3) simplify the design of structure
to the greatest possible extent, (4) by
careful design and choice of stresses and
materials ensure that crack propagation

Cont'd Aircraft Fatigue GILBERT, P. To

rates are low and that fatigue failures
will not be catastrophic, (5) carry,out Corrosion-Fatigue
extensive fatigue tests of all details where METALLURGICAL REVIEWS, VOL I, PART 3
fatigue damages is predicted as significant, PP 379-417 (1956) 169 ref.
(6) confirm by flight strain gage tests
the assumed fatigue loading data and also Historical review of corrosion fatigue as
strain gage or stress lacquer static test distinct from stress corrosion. Definition,
specimens so that all points of stress test methods, characteristics, effect of
concentration are obtained, (7) use counting environment, data for ferrous and nonferrous
accelero-meters and/or strain gage in ser- alloys, relationship to mircostructure, el-
vice and choose the operating conditions ectrochemical aspects, protection.

Cont!d Aircraft Fatigue GLOWACKI, ZYCMUNT

so that the best compromise between fat- The Effects of Wire Plasticity on the
igue' and other considerations is obtained, Fatigue Strength of Steel Wire Rope
and (8) ensure a high standard of main- (in Polish)
tenance and inspection so that ground hand- HUTNIK, VOL 23, NO 9, pp 336-339 (Sept. 1956)
ling damage is minimized and fatigue
and other flight damage detected and re- Annealing steel wire after the last draw-
paired while still safe. ing operation improves the mechanical pro-
perties of the wire and the rope made of it.

GIDDINGS, Ho GOHN, G.Rc, J. PC- GEURARD AND H. S. FRETNIK

The Extent of the Fatigue Problem in The Mechanical Properties of Wrought

Aircraft Design Phosphor Bronze Alloys
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADEMIC PRESS, pp 347-375 ASTM SPECIAL TECHNICAL PUBLICATION NO. 183
Review of types of fatigue loading January 1956
actions, strength and design of aircraft
components, and effect of operating, in-
spection and maintenance procedures on
fatigue life.

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GOODGER, A. Ho GaaOVEE, HORACE J.
Corrosion Fatigue Cracking Resulting from Allowance for Stress Concentration in Design
Wetting of Heated Metal Surfaces, with
to Prevent Fatigue
Special Reference to Steam Power Plant PAPER NO. 1 of Session 2, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I,
PAPER NO. 9 of Session 4 INTERNATIONAL INST. OF MECHANICAL ENGINEERS, 9 pages (1956)
CONFERENCE ON FATIGUE OF METALS, VOL II,
INST. OF MECHANICAL ENGINEERS, 9 pages Evidence for effective stress-concentra-
6 plates (1956) tion factors was derived from laboratory
tests on specimens with simple geometrical
Typical examples of cracking; conditions discontinuities under various load conditions
for cracking; mechanism of attack; effect
of temperature on endurance; detection and
remedial measures.

GOUGH, H. J. GROVER, H. J.
The Changing Nature of the Fatigue Problem How Shot Peening Improves Fatigue Strength
ENGINEER (LONDON) VOL 202, NO. 5251 SAE JOURNAL, VOL 64, PP 28-30 (August 1956)
PP 359-362 (1956)
Introductory address presented at Ways in which the method may be expect-
International Conference on the Fatigue of ed to influence fatigue strength. Surface
Metals, sponsored by Bffi and ASME. Reviews roughening of previously polished surfaces
state of knowledge in 1939 and general pic- lowers fatigue strength, while surface work-
ture presented by conferences held in hardening and residual stresses usually
Melbourne in 1946 and MIT in 1950. improve it.
53 ref.

GOULD, A. J. GROVER, GOEBDON, AND JACKSON

Corrosion Fatigue The Fatigue of Metals and Structures
PAPER NO. 2 of Session 4, INTERNATIONAL THAMES AND HUDSON (LONDON) 1956 399 pages
CONFERENCE ON FATIGUE OF METALS, VOL II This book is directed particularly to
INST. OF MECHANICAL ENGINEERS (1956) the designer or engineer with some know-
9 pages ledge of but limited practical experience
Testing; associated factors and in fatigue problems. It provides references
methods of reducing the severity of to published literature for more complete in-
attack. formation on the most important items. Iden-
tical to book published in 1954 by the U.S.
Government Printing Office, except for in-
clusion of a subject index.

GRAY GROVER, LA MOTTE

What You Can Do About Metal Fatigue Fatigue of Welded Joints Committee
STEEL, VOL 138, pp 68-72 (Jan. 16, 1956) WELDING RESEARCH COUNCIL YEARBOOK
PP 32-33 (1956)
Precautionary measures are given to Studies in progress at the University
prevent fatigue failure, reasons for of Illinois on evaluating and improving
metal fatigue are given, and pointers the behavior of welded members and con-
which may be used in fatigue testing. nections which are subjected to repeated
loads.
Graphs, photographs.
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_2i_
GROVES, WILSON T. GUMBELj Eo J.
Practical Aspects and Methods of Carbon A Method of Programming for the Statistical
Control in Heat Treatment Estimation of Fatigue Strength (German)
SCHWBIZ. ARCHIV ANGEW. WISS. TECHN.
INDUSTRIAL HEATING, VOL 23, pp 2060-2070 (SWITZERLAND) VOL 22, NO. 11, p 375 (Nov 1956)
(1956)
The opinion is voiced that statistics
Effect of surface carbon concentration on present the only reliable method of estimat-
wear and fatigue life; control of concentra- ing fatigue strength. For this purpose the
tion. probability of safe life is evaluated as a
function of the load. Safe life, in the pre-
sent case, is the term of survival of 10' or
rather 10° testing cycles. In the first

Cont'd Method of Programming Stat.Estimation

GUARD, R. W.
series of tests each of 49 specimens is
Metals at Elevated Temperatures subjected to 15 different loads. Result-
ing safe life probabilities within the range
PRODUCT ENGINEERING, VOL 27, pp 160-164 of 0,02 to 0.98 will indicate the minimum
(October 1956) endurance as a function of the load applied,
and also the minimum load at which the
Hot and cold behavior of metals com- specimens survive 10' or 10° cycles.
pared, using homologous temperature scale; Based on this information a second ser-
fatigue vs rupture stress as design criter- ies of tests, this time restricted to such
ion, predicting long-term properties from minimum loads and less, should be carried
short-term tests. out again with 49 specimens tested during
10? - 10^ cycles. The probability of safe

HAAS, T.
Cont'd Method of Programming Stat.Estimation
International Conference of Fatigue of Metals life is then estimated as (ng-nfs)/(ns+ l),
AIRCRAFT ENGINEERING, VOL 28, pp 431-433 where ng stands for the number of specimens
(December 1956) tested at load S, and njs is the number of
those specimens which have failed. In this
The author?s impression and criticisms latter series 6 different loads at least
of eleven papers, of direct aeronautical en- should be applied in such a way that the
gineering sigTiificance, presented in London. properties of the surviving specimens should
A follow-up conference of the ASME was held appear in an approximate order of magnitude
in New York from November 28 to 30. The of Oo02, 0.20/0.50, 0.80, 0.90 and 0.98.
complete papers and edited views from both Extrapolation to unity points to the value
London and N.Y. conferences will be published of fatigue strength.
in Proceedings of sponsoring organization.

KANSTOCK, R.F. HANSTOCK, R.F.

Cn the Effects Preceding Fatigue Failure of The Reactions of High-Strength Aluminum
High-Strength Aluminum Alloys Alloys to Alternating Stresses
PAPER from FATIGUE IN AIRCRAFT STRUCTURES, PAPER NO. 2 of Session 5, INTERNATIONAL
ACADEMIC PRESS, pp 62-82,(1956) CONFERENCE ON FATIGUE OF METALS, VOL II
Resonance method of testing was em- INST. MECH. ENGINEERS, 9 p, 2 plates (1956)
ployed. Variation of hysteresis with stress, The fatigue process; dynamic properties
critical stress and comparison of the ef- of Al alloys; nature of the changes in hy-
fects of temperature and cyclic stress steresis induced by prolonged cyclic stress-
are discussed, 6 refe es; differences between the effects of
thermal treatment and cyclic stressing;
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25
HARA,JSABURO HARDY, A.'A.
An Investigation of the Corrosion Fatigue of What to do About Sucker-Rod Failures
Marine Propeller Shafts
WORLD OIL, VOL 1^2, pp 129-132 (Feb 1956)
PAPER NO* 3 of Session k, INTERNATIONAL
CONFERENCE ON FATIGUE OF METAIS, VOL II, Improved field techniques and thread
INST. MECH. ENGINEERS, 6 pages 6 plates. design resulting in close fit of the threaded
(1956) connections should minimize fatigue failures.
Table, diagrams, photograph. 6 ref.
Fatigue strength of small steel specimens
subjected to sea-water corrosion; process
of origination and growth of cracks; com-
parison "between appearance of failure in
small specimens and actual propeller shafts.
HANSEL HARTMAN, A., AND W. KIAASSEN
Mechanical Properties of Butt Joints Brazed The Fatigue Strength at Fluctuating Tension
with BAg-1, BAg-3 and BCu Filler Metals( of Single-Lap Joints of Clas 2^3-T and
75S-T Aluminum Alloys with Two Rows of ITS
WELDING JOURNAL, VOL 35, No. U, (April 1956) Rivets (in English)
pp 211s - 2l6s
The room temperature impact, tensile and NATIONAAL LUCHTVAARTIABORATORIUM,
fatigue properties of brazed butt joints RAPPORT NLL-TNM 2011 (July 1956)
are presented. Unnotched rotating canti-
lever fatigue specimens with the brazed Fatigue Strength of the 2^S-T alelad
joint transverse to the specimen axis were sheet was superior.
employed. S^N curves are given. The en-

.Cont'd Mechanical Properties of Butt Joints HARTMANN, E. C.

durance limit established for joints brazed Effect of Unintentional Stress Raisers on
with BAg-1 (U5$ Ag, 2U$ Cfl, 16$ Zn, 15$ Cu) the Fatigue Strength of Structural Components
is 11,000 psi, 9,000 psi for joints prepared
with BAg-3 (50$ Ag, 16$ Cd, 15$ Zn,15$ Cu, PAPER NO, 13 of Session 2, INTERNATIONAL
3$ Ni) and 1^,000 psi for joints prepared with CONFERENCE ON FATIGUE OF METALS, VOL I,
BCu (99,9$ Cu). INST, MECH, ENGINEERS. (1956) 8 pages
Some evidence is given that ^he fatigue The final effect of many unintentional
values for BAg-1 are higher for 0.0015 inch discontinuities on the fatigue strength of
joint clearance than for 0.0025 inch joint finished parts is found to be entirely
clearance. The base metal used was a hard- negligible.
enable ferritic steel of the 2^$ Ni, ^$ Mo
variety.
HARDRATH, HERBERT F., HERBERT A, LEYBOLD, HARVEY AND TURNER
CHAS, B. LANDERS AND LOUIS W. HAUSCHILD
Correlation of Hydrogen Content to Tensile
Fatigue-crack Propagation in Aluminum- and Fatigue Properties in Heliarc-Welded
Alloy Box Beams
A-110AT Titanium Alloy Sheet
NACA TN 3856 (Aug. 1956) 33 p. diags,photo.
Eighteen box-beam specimens constructed ac- CONVAIR, REPORT NO. 56-189 7 pages
cording to four designs were subjected to (April 1956)
fatigue tests to study fatigue-crack propa- . No exact correlation could be found.
gation and accompanying stress redistribution, Tables, diagram, photographs.
At least two specimens of each design were
constructed from each of the aluminum alloys
202U-T3 and 70T5-T6.
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26
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HEAD, A. Ko HENKE, R. Wo
The Propagation of Fatigue Cracks Resistance of Materials of Mechanical
Corrosion
JOURNAL OF APPLIED MECHANICS (Sept. 1956) PRODUCT ENGINEERING, pp 194-197 (Jan.1956)
pp 407-410
also, TRANSc ASME, VOL 23, N0.3 (Sept. 1956) A brief review of the causes of stress
corrosion, corrosion fatigue, impingement,
erosion, and fretting, followed by guides
to the choice of the most resistant mater-
ials and possible remedies in design.

HEAD, A. Ko AND F. H. HOOKE HEYWOOD, R. B.

Fatigue of Metals Under Random Loads Correlated Fatigue Data for Aircraft
Structural Joints
NATURE, VOL 177, pp 1176-77
(June 23, 1956) AERONAUTICAL RESEARCH COUNCIL (GREAT
BRITAIN), ARC CP 227, 1956

HEAD, A.K. AND F. H. HOOKE HEYWOOD, R.B.

The Influence of Pre-Loading on the Fatigue
Random Noise Fatigue Testing Life of Aircraft Components and Structures
PAPER NO. 9 of Session 3, INTERNATIONAL AERO. RESEARCH COUNCIL ((SEAT BRITAIN)
CONFERENCE ON FATIGUE OF METALS, 1956, 27 p, diagrs, photos (ARC CP 232)
INST. MECHANICAL ENGINEERS (1956) Tests on aircraft components and struc-
5 pages tures are described which show that preload-
ing can have a marked influence on fatigue
behavior. Tensile pre-loading may increase
the life - in one instance a hundredfold

HMPEL, H. Cont'd Influence of Pre-Loading

Metallographic Observations on the Fatigue improvement was obtained - and compressive
of Steels preloading may reduce the life.
The effect is attributed to residual
PAPER NO. 7, Session 6, INTERNATIONAL stresses and to load redistributions in-
CONFERENCE ON FATIGUE OF METALS, VOL II duced by preloading.
INSTo MECHANICAL ENGINEERS (1956)
7 pages, 15 plates
Formation of slip markings and propa-
gation of cracks at room temperature;
formation of twin crystals at low temperature,
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 HOLT
HEYWOOD, R. Bo
Aluminum and Aluminum Alloys for
The Strength of Lugs in Fatigue Pressure Vessels
WELDING JOURNAL, VOL 35, NO 6
RAE TECHNICAL NOTE NO. STRUCTURES 182, pp 308s-312s (June 1956)
January 1956, 34 pages This condensed version of an interpretive
report prepared for the Welding Research Coun-
cil Pressure Welding Research Committee in-
cludes a comparison of direct-stress fatigue
test results for arc-welded butt joints in
3/8" thick 3003-F, 6061-T6 and 5154-H34
aluminum alloy plate.

HIORNS, F. J. HOOKE, F. Ho and P. S. LANGFORD

Some Aspects of the Problem of Fatigue Australian Work on Aircraft Fatigue and
Life Evaluation
BRITISH COAL UTILIZATION RESEARCH ASSOC- AIRCRAFT ENGINEERING, VOL 28, NO 334,
IATION, MONTHLY BULLETIN, VOL 20 pp 408-414 (December 1956)
pp 153-160 (April 1956)
An historical review of Australian re-
Factors influencing the fatigue strength search in structural fatigue and life as-
of materials; propagation of fatigue cracks; sessment of aircraft. Fatigue failures
the nature of fatigue process; fatigue in on operational aircraft are reviewed and
brittle materials.
the research programs initiated to invest i-
Table, 35 ref.

HOFFMAN, C.A. Contfd Australian Work on Aircraft Fatigue

Strengths and Failure Characteristics of
AMS 5534A (S-816) Alloy in Direct Tensile gate these failures are discussed.
Fatigue at Elevated Temperatures Results of wing fatigue testing of
Boomerang and Mustang fighter planes are
ASIM PREPRINT NO 68, 1956 ANNUAL MEETING discussed as are the results of flight
Tension fatigue tests were carried out load investigations using V-g recorders
on AMS 5534 A alloy at temperatures of 1200, and statistical or counting instruments.
1500 and 1600 F. Three mean stress levels Methods of general life assessment
were used at each temperature to give lives for all civil aircraft are reviewed.
of about 10, 100, and 1000 hr at zero cyclic 4 diagrs, 12 photos, 15 ref.
stress. For each condition, cyclic tensile
stresses were superimposed up to a maximum

Cont?d Strength and Failure Characteristics

HORGER, 0. Jo
of about 98$ of the mean stress. The nature
of the fracture was examined. Fatigue of Large Shafts by Fretting
Increasing cyclic stress reduced the time Corrosion
to failure under all conditions investigated, PAPER NO 4, of Session 4, INTERNATIONAL
the reductions being greater at 1200F than CONFERENCE ON FATIGUE OF METALS, VOL II,
at 1500 and 1600F; at the same time the ap- INST. MECHANICAL ENGINEERS, (1956)
pearance of the failure changed from that of 11 pages, 2 plates
stress-rupture to that of fatigue. Fatigue Fatigue resistance of press-fitted assem-
fracture was transgranular throughout, but blies was comparatively less influenced by
stress-rupture fracture was intergranular type of steel, tensile properties, or wheth-
at 1500 and 1600 F. er the shafts were normalized and tempered
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cal quenching to obtain favorable residual
further reproductions authorized.
thermal compressive stresses on the surface,
HOSHINO, J. HIIER, W. S. and F8 H. L3TON
Some Studies on the Pitting of Marine Materials-Property-Design Criteria for
Reduction Gears Metalss Part 3. Fatigue Evaluation of
Magnesium Alloys
PAPER NO. 7 of Session 9, INTERNATIONAL WRIGHT AIR DEVELOPMENT CENTER REPORT
CONFERENCE ON FATIGUE OF METALS, VOL II, 55-150 (June 1956)
INST. MECHANICAL ENGINEERS (1956)
6 pages WADC Rechnical Report 55-150 indicated
that the ANC-5 document shows discrepancies
in fatigue data for various magnesium al-
loys as obtained ;in rotating bending, plate-
bending, and axial-loading fatigue tests.

HUNTER, M. S. and W G. FRICKE, JR. Cont!d Materials-Property-Design Criteria

A study was made of three magnesium alloys
Fatigue Crack Propagation in Aluminum FS-la (AZ31A-0, J-l (AZ61A-F), and 0-1
Alloys (AZ80A-F) under conditions of completely
reversed stress for the three kinds of
ASTM PAPER, 1956 loading.,
Results suggest that the discrepancies
noted in ANC-5 data between rotating beam
fatigue data and data from the other two
types of test are real. Certain other in-
consistencies in the data suggest that afc-

Cont'd Materials-Property-Design Criteria

HYIER, W.S., Eo D. ABRAHAM and H»J.CKOVER
ditional fatigue studies should be made
Fatigue-Crack Propagation in Severely to provide more reliable information.
Notched Bars A review of methods presenting fatigue
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS data in ANC-5 was made. It is suggested
TN 3685, June 1956, 31 p, diags, photos, tabs that a more consistent method of presenta-
tion be followed for the various alloy
Fatigue tests were made in rotating bending systems for which fatigue data are reported,
on severely notched bars machined from 2024-
T4 aluminum-alloy extruded round rods. Two
sizes of specimens were studied, 1/4 inch-
diameter and 2 inch-diameter specimens.

Cont'd Fatigue Crack Propagation IVANOV and SAVUKOV

Effect of Electrospark Hardening on
The smaller specimens were notched Wear-Resistance and Fatigue Strength
with a V-groove and had notch severities (Russian)
Kj. of 5*2. The larger specimens also
contained V-grooves with notch severities MBTALLOVDENIE I OBRABOTKA METALLOV
of 5.2 and 13.9» NO 6, pp 52-56 (Dec. 1956)
Effect of electrode material, el-
ectrospark methods, and previous heat
treatment on wear and fatigue strength
of steel* Photograph, table, diagrams,
graphs. 3 ref.
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HYLER, W.S. and W0 F« SIMMONS INESON, E«, JoCLAYTON-CAVE and R.J.TAYLOR
Factors Influencing the Notch Fatigue Variation in Fatigue Properties Over Individ-
Strengthening of N-155 Alloy at Elevated ual Casts of Steels Part I0 Investigation
Temperatures of a Cast Steel to BS-970 Specification
En 100
TRANS. OF A2ME, VOL 78, NO.2 (Feb, 1956)
PP 339-349 IRON AND STEEL INSTITUTE JOURNAL, VOL 184
pp 178-185 (October 1956)
Data are given to illustrate the effect
of stress raisers on the elevated-tempera- A carefully designed experiment was con-
ture fatigue behavior of N-155 Alloy, These ducted to determine the differences in
data were obtained on specimens notched fatigue properties in rods rolled from
with V grooves having various root radii material in five different positions in a

Cont'd Factors Influencing Notch Fatigue Cont'd Variation in Fatigue Properties

and various notch severities0 The experi- cast, using 500 rotating-beam fatigue
mental program was in direct-stress fatigue, specimenso Factors such as composition,
and covered a range of alternating stress grain size, hardenability, and inclusion
to mean stress from A - 0«,0 to A -OO count were studied for possible correla-
at temperatures of 1200 to 1500 F. tion with the results.
The effect of surface finish also was Analysis of the fatigue-test results
studied to a limited extent, A metallo- showed that the differences were associated
graphic study of fractured surfaces was with differences in hardness and tensile
carried out. strength.

ILLG, WALTER INSTITUTION OF MECHANICAL ENGINEERS

International Conference on Fatigue of
Fatigue Tests on Notched and Unnotched Metals VOL I-IH.
Sheet Specimens of 2024-T3 and 7075-T6
Aluminum Alloys and of SAE 4130 Steel with PAPERS INDIVIDUALLY PAGED. 1956
Special Consideration of the Life Range INSTo MECH0 ENGINEERS, LONDON, ENGLAND
from 2 to 10,000 cycles Papers dealing with stress distribution;
effects of temperature, frequency, and en-
NACA TN 3866 (Dec0 1956) 40 pages vironment; metallurgical aspects of fatigue;
diagrs, photo, tabs. basic mechanisms, and engineering and in-
Fatigue tests were performed on notched dustrial significance of fatigue. Perti-
and unnotched fatigue specimens made of nent papers are individually abstracted.
2024-T3 and 7075-T6 aluminum alloys and of
SAE 4130 steel0 The notched specimens had
:Cont'd Fatigue Tests on Notched and, etc. JACKSON, JoS.
Hydrogen Occlusion and Its Effect on the
theoretical stress-concentration factors of Fatigue Properties of Plain Carbon
2.0 and 4«0 and the mean loads were 0 and 20 Spring Steels
or 50 ksi. It was found that repeated ap-
plications of stresses in the vicinity PAPER NO. 8 Session 5, INTERNATIONAL
of the ultimate strength on notched and un- CONFERENCE ON FATIGUE OF METALS, VOL II
notched specimens produced failures in a INSTo MECHo ENGINEERS, 8 pages (1956)
much smaller number of cycles than might be Conditions of steel which tend to
inferred from previously published data» lower the ductility are more prone to the
Ratios of fatigue strengths of unnotched damaging effects of H occlusion„ Occluded
specimens to those of notched specimens H has very little effect on the fatigue lim-
are given. it of cold-worked spring steels but can
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authorized.
fatigue limit.
 JACQUET, PJU JENSEN, R.S.
Observations on the Microstructure of a Fourteenth Progress Report of the
Brass Containing 6? per cent of Copper Rolling-Load Tests of Joint Bars
Subjected to Alternating Bending Stresses
AMERICAN RAILWAY ENGINEERING ASSOCIATION
PAPER NO* 9, of Session 5, INTERNATIONAL BULLETIN, VOL 57, NO 528, pp 818-829
CONFERENCE ON FATIGUE OF METALS, VOL II (February 1956)
INST. MECHo ENGINEERS, 6 pages, 7 plates
(1956) Rolling-road fatigue tests were made
Miscroscope reveals the crystallographic on 36-inch head-free joint bars and on
lattice of grains of alpha-brass which ap- Rajo compromise joint Type 106A, head free.
pear on the surface and also under the deep- These joint bars contain easements ground
er layers, under the effect of alternating on the top surfaces of the bars well be-

Cont'd Observations on Microstructure,etc Confd Fourteenth Progress Report, etc.

stresseso yond the area of contact of bar rail.

Results of the program suggest the
The cracks are the direct conse- ground easements were adequate to eliminate
quences of these disorders, and develop completely gouging of the bars by rail ends,
further on subsequent annealing. It was believed that this would increase
rail life in service.

JENSEN, HoT. KATTUS and DOTSOK -

The Elements of a Helicopter Fatigue
Substantiation Program Mechanical Properties of Medium-
Carbon Boron Steels
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADEMIC PRESS, pp 233-254 (1956) METAL PROGRESS, VOL.69, PP 68-72 (April 1956)
Basic facilities used in the test pro- Tensile, fatigue, impact, and notched-
gram are strain-gage flight test aircraft, tensile properties of tempered medium-
tie down test aircraft, fatigue laboratory carbon boron steels are equivalent to those
and the rotor-whirl stand. of other low-alloy steels tempered to the
4 ref „ same hardness levels.
Graphs, table.

JOHNSTONE, Wo¥. and A. Oo PAYNE KAUFMAN, ALBERT and ANDRE J. MEYER, JR.
Aircraft Structural Fatigue Research Investigation of the Effect of Impact
in Australia Damage on Fatigue Strength of Jet-Engine
Compressor Rotor Blades
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADEMIC PRESS, pp 427-448 NACA TN 3275, June 1956, 25 p.
The most serious damage was nicks at
Review of fatigue research by the Struc- blade edges. The farther the damage was
tures Division of the Aeronautical Re- from the maximum-vibratory-stress section
search Laboratories and summary of present of the airfoil and from the edges, the
status. less detrimental it was.
47 ref„
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KELLER, W.M. and G. H. MAGEE KaiSLEY, D.So
Effects of Cyclic Stress and Frequency on
Fatigue in Railroad Equipment Deformation Markings in Fatigued Copper

PAPER NO. 1 of Session 9, INTERNATIONAL JOURNAL OF INSTITUTE OF METALS, VOL 85,

CONFERENCE ON FATIGUE OF METALS, VOL II, pp 153-157 (1956-57).
INSTo MECH. ENGINEERS, 5 pages (1956) Fatigue deformation markings (Striations)
produced by cyclic stressing may be revealed
both on the surface and in the interior of
copper specimens by suitable etching. Frac-
tured rotating-cantilever specimens tested
at stresses ranging from +. 10,000 to +. 25,000
lb./in2, and frequencies "of 21 and 6000 c/m,
were sectioned and examined by optical and

KMSLEY, DoSo Cont'd Effects of Cyclic Stress, etc.

The Fatigue of Rock-Drill Rods electron microscopy after polishing and
MINE AND QUARRY ENGINEERING, VOL 22, etching.
PP 386-389 (September 1956) Striations were most numerous and dis-
tinct at low stresses and low frequency
Concludes that the majority of steel and under these conditions they occurred
rock drill rod fatigue failures are due in practically all crystals. At high stress-
to corrosion fatigue, rather than dry es and high frequency, Striations were much
fatigue or to a purely mechanical stress less numerous and definite, appearing in
distribution„ only an estimated one crystal in 500.
Evidence is given that the Striations

KENNEDY, A 0 Jo Sont'd Effects of Cyclic Stress, etc.

are in fact slip traces, whose character-
Effect of Fatigue Stresses on Creep istics change from slip packets of approxi-
and Recovery mately 1000 A. interlamellar spacing at
PAPER NO. 10 of Session 4, INTERNATIONAL low stress to substantially single lines
CONFERENCE ON FATIGUE OF METALS, VOL II at high stress. Hardness results suggest
INST. MECH. ENGINEERS 9 pages (1956) that Striations are not regions of intense
localized work-hardening, The persistent
Creep of Pb under static stress slip bands obtained by Wadsworth and Thomp-
with superimposed fatigue stresses. son, when present, appeared to be associa-
Effect of a fatigue vibration on ted with striations0
the recovery properties of work-hardened
metals.

KENNEDY, A.J. and R.F. SLADE Cont'd Effects of Cyclic Stress, etc.
An Automatic Electromechanical Stress- An explanation of the main observations
ing Unit for Creep and Fatigue Testing is given in terms of interaction between
JOURNAL OF SCIENTIFIC INSTRUMENTS, dislocations. It is concluded that local-
VOL 33, pp 409-410,'(November 1956) ized deformation most truly characteristic
of cyclic stressing occurs only in low-
Stress is imposed by means of a mech- stress, long-life specimens, and that as
anical spring, so that inertia effects, the stress increases deformation becomes
particularly when loading is repetitive, less localized and exhibits similar feat-
are negligible., The same system may be ures to those produced by unidirectional
used to conduct creep recovery or stress- stress.
relaxation tests.
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KENNEDY, A.-J. KEPERT, J.Lo and A.O.PAYNE
Metal Fatigue in Theory and Design Interim Report on Fatigue Characteristics
of Typical Metal Wing
NATURE, VOL 178, NO. 4540 (Nov. 3, 1956)
pp 957-959 NACA TM 1397, March 1956, BO pages
diagrs, photos, tabs.
General observations on the Interna-
tional Conference on the Fatigue of Metals Constant amplitude fatigue tests of
sponsored by the Inst. of Mechanical En- seventy-two P-51D-Mustang wings are reported,
gineers in co-operation with the American The tests were performed by a vibra-
Society of Engineers, held in London, tional loading system and by an hydraulic
Sept. 10-14, 1956. It is concluded that loading device for conditions with and
more rigorous distinctions must be drawn without varying amounts of pre-load.

Cont'd Metal Fatigue in Theory and Design Cont'd Interim Report on Fatigue, etc.
between fatigue and other parallel processes
There is a real need for statistical The results indicate that: (a) the
theory. Engineering design needs to be frequency of occurrence of fatigue at any
supplemented by a different approach in- one location is related to the range of
volving new methods, which recognize the loads applied, (b) the rate of propa-
fatigue as one of several interacting gation of visible cracks is more or less
processes causing failure. constant for a large portion of the life
of the specimen, (c) the fatigue strength
of the structure is similar to that of
notched material having a theoretical
stress concentration.

KENNEDY, N0G. KIENLIN, M 0 VON

Fatigue of Curved Surfaces in Contact Determination of Fatigue Strength of
Under Repeated Load Cycles Components of Internal Combustion Engines
Subject to Mechanical Stress, with Prac-
PAPER NO. 7 of Session 3, INTERNATIONAL tical Examples (German)
CONFERENCE ON FATIGUE OF METALS, VOL I,
INST, MECH. ENGINEERS, (1956) MOTORTECHNISCHE ZTS, (STUTTGART)
10 pages, 4 plates VOL 17, p 33 (February 1956)
Tests suggest that damage to the sur-
face of curved elastic pairs in contact
under cyclic loading stems from surface
conditions at the boundary of the area
of contacto
KILBRIDE, E. and Co E. PHILIPS
KHEIRALLA, A0A.
Researches on Fatigue of Metals at
A New Theory of Fatigue Mechanical Engineering Research Laboratory
INST* OF ENGINEERS AND SHIPBUILDERS -
NATURWISSENSCHAFTEN, VOL 43, NO. 14 SCOTLAND TRANSACTIONS, VOL 99, PART 3
(July 1956) pp 173-192 (1955-56).
see also, TRANS ASME, VOL 23, NO, 3
P 473 (September 1956) Review of recent research on pin
joints, screw threads, effect of size of
specimen^ propagation of fatigue cracks
and low endurance fatigue*
Graphs, diagrams, micrographs, photo-
graph, table. 9 refo
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KOCHANOVSKA, CERMAK, AND HOLY KUBRYAVTSEV AND BALABANOV
Fatigue Strength of Steel Plates
Contribution to the Study of the Altera- With Welded Straps (Russian)
tions in Steel Structures caused by
Fatigue (French) SVAROCHNOE PROIZVODSTVO, NO. 6, pp 1-5
(June 1956)
REVUE DE METALLURGY, VOL 53, NO, 9, Results of fatigue tests show that their
pp 701-702 (September 1956) strength is considerably lower than that of
plates without straps. High annealing of
plates with straps improves their fatigue
strengtho Normalizing of such plates
improves their strength still further,
DiagrSj tables, photos, micrographs.
4 ref.

KONISHI, ICHIRO AND MASANOBU SHINOZUKA KUBRYAVTSEV,I8V. and N.M.SAWINA

Effects of the Material of Surrounding Parts
Scatter of Fatigue Life of Structural Steel on the Fatigue Strength of Axles and Shafts
and Its Influence on Safety of Structure
(Japanese) (Russian)
VESTNEC MASHINOSTROENIIA, VOL 36, NO. 7
MEMOIRS OF THE FACULTY CF ENGINEERING, pp 10-14 (July 1956)
KYOTO UNIVERSITY, VOL 16, NO. 2, A study of the decrease in fatigue
PP 73-83 (April 1956) strength of axles and shafts where they
are in contact with fixed parts, such as
Frequency distribution was inter- the inner races of roller bearings.
preted by the theory of the stochastic
process.

KRAICHIK, M.M., L.M.SHKOLNIK AND KUDRYAVTSEV, I.V. and N.M.SAWINA

B.A.MEISNER
Increasing the Contact Fatigue Strength
A Method of Making Bending Fatigue Tests of Steel Plates by Surface Cold Working
on Welded Structures (Russian) (Russian)
ZAVODSKAIA LOBARATORIIA, VOL 22 METALLOVEDENIE I OBRABOTKA METALLOV, NO.9
pp 1472-1479 (December 1956) pp 31-41 (September 1956)
Shows that the character of the stress
in bending tests can have an influence A study of the fatigue strength in
on the measure strength of welded I-beams. contact zones of steel plates (50-mm thick)
and of improving this strength by cold
working.

KUDRYAVTSEV, I4V0 KUDRYAVTSEV, I.V. and N.M. SAWBfA

The Influence of Internal Stresses on Investigation of Fatigue Strength of
the Fatigue Endurance of Steel Joints Obtained by Electro-Slag Welding
of Large Sections (Russian)
PAPER WO. 12 of Session 39 INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS (1956) SVAROCHNOE PROIZVODSTVO, NO. 11
INST. MECHo ENGINEERS, 11 pages. pp 1-6 (November 1956)
Experimental investigation of
fatigue of joints after various heat
treatments.
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KUHN, PAUL LANE, P.H.R.

Fatigue Engineering in Aircraft Fatigue Tests on Seamless Mild-Steel

Pipe Bends
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
ACADEMIC PRESS, pp 295-316 PAPER NO. 3 of Session 9, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL III,
A review of design problems involving INST. MECH. ENGINEERS, 10 pages, 2 plates,
fatigue under constant-amplitude loading (1956)
and under variable-amplitude loading.
26 refo Specimens were subjected to pulsa-
ting internal pressure and to alternating
external loading in the plane of the bend.

LANDERS, CHARLES B., and HERBERT F.HARDRATH LARDGE, H.E.

Results of Axial-load Fatigue Tests on Thermal Fatigue Testing of Sheet Metal

Electropolished 2024-T3 and 7075-T6 PAPER from SHMPOSIUM ON METALLIC MATERIALS
Aluminum-Alloy-Sheet Specimens with FOR SERVICE AT TEMPERATURES ABOVE 1600 F,
Central Holes
AMERICAN SOCIETY FOR TESTING MATERIALS,
NACA TN 3631 (March 1956) 74 pages, pp 146-159; discussion pp 160-163 (1956)
diagrs, tabs0 also, SHEET METAL INDUSTRIES. VOL 33,
NO.349, pp 299-306 (May 1956)
Results are presented of axial-load
A test was devised based on heating
a specimen with a central hole to 1650 F
i
Cont«d Results of Axial-Load Fatigue Tests
Contfd Thermal Fatigue Testing, etc.
fatigue tests at stress ratios of 0 and
-1.0 on electropolished 2024-T3 (24S-T3) and and then cooling it rapidly in a blast
7075-T6 (75S-T6) aluminum-alloy-sheet spec- of cold air. The thermal cycle was
imens with central holes. The specimen based on the temperature curve of a
widths and hole diameters were varied in flame tube on an engine during accel-
order to provide data suitable for a study erating and decelerating conditions.
of notch-aize effect. The data are com- Micrographs, photos, graphs,
pared with previously published results of tables, diagrs.
tests on unnotched electro-polished speci-
mens and on unpolished specimens contain-
ing central holes.

LANE, PoH0R< LAUTERBURG, B.

Fatigue Tests on End Closures for Model Effect of Pores in Welded Butt Joints
Headers (German)
BRITISH WELDING JOURNAL, VOL 3 OERLIKON SCHWEISSMITTEILUNGEN, VOL 14,
pp 200-205 (May 1956) NO. 25, pp 5-19 (August 1956)
Pulsating-pressure fatigue tests on a Static and fatigue strength; brittle
number of designs for end closures for fracture; preparation of experiemtnal
6-ineh-diameter mild-steel pipe. specimens; method of testing.
Photos, graph, tables, diagrs, 3 ref.
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LASSITER, I.W., R. W. HESS and H.H.HUBBARD LEGG, KeL»C.
An Experimental Study of the Response of The Choice of Material for Airframes
Simple Panels to Intense Acoustic Loading AIRCRAFT ENGINEERING (ENGLAND) VOL 28
NO.331, pp 304-312 (September 1956)
JOURNAL OF AERONAUTICAL SCIENCES, VOL 24,
NO. 1, pp 19-24, 80 (January 195?) Some of the major factors influencing
the choice of materials for the use in
Stress levels calculated by the power the construction of airframes are analyzed„
spectrum procedure are compared with Strength, stiffness, high temperature,
measured stress levels, for flat panels creep, fatigue, machining, corrosion, weld-
exposed to high-intensity noise levels of ing and nuclear properties of four groups
both discrete and random nature. of common or likely future airframe engin-

Contvd Experimental Study of the Response, etc. Cont'd Choice of Material for Airframes
eering materials such as light alloys,
Discussion is presented on the steels, titaniums, and plastics, are dis-
effect of high noise intensity on fatigue cussedo The growth of speed and weight
life and rate of fatigue-crack progression. in present day aircraft has raised serious
problems in material technology, design
and production, and an attempt is made to
sketch possible future developments which
may help to materialize such projects as
rocket flight and nuclear aircraft pro-
pulsion o

LAUTERBURG, B. LEIRIS, H. DE

The Effect of Artificial Porosity on The Fatigue Testing of Components, A

the Fatigue Strength of Arc Weld Metal Means of Revealing the Danger Point in
Pieces or Structures
WELDING RESEARCH ABROAD, VOL 2, NO.3, PAPER NO. 5, of Session 2, INTERNATIONAL
pp 46-47 (July 1956) CONFERENCE ON FATIGUE OF METALS, VOL I,
INST. MECH. ENGINEERS, 6 pages (1956)
Three examples illustrate effectiveness
of method under varied conditions.

LAZAN, B.J. LESSELLS, J.M. and R.F. BRODRICK

Damping and Resonant Fatigue Behavior of Shot-Peening as Protection of Surface-
Materials Damaged Propeller-Blade Materials
PAPER NO. 2 of Session 2, INTERNATIONAL PAPER NO. 1, of Session 8, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I, CONFERENCE ON FATIGUE OF METALS, VOL II,
INST. MECH. ENGINEERS, 14 pages (1956) INST. MECH. ENGINEERS, 13 pages (1956)
The general role of material damping
in minimizing near-resonant fatigue stress
is analyzed by developing criteria based
on material properties and stress distrib-
ution
Copyright for
by ASTMevaluating
Int'l (all rights reserved);the
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29 16:12:20 EST 2015
strength ofby parts.
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LEVY, JOHN C. LIEBIEIN, J. and M. ZELEN
Cumulative Damage in Fatigue: A Method
of Investigation Economical in Specimens Statistical Investigation of the Fatigue-
Life of Deep-Groove Ball Bearings
ENGINEERING (BRITISH PUBLICATION) . VOL 179,
»Jf663- (June 10, 1955). JOURNAL OF RESEARCH, NATIONAL BUREAU OF
STANDARDS, VOL 57, pp 273-316 (Nov.1956)
Uses a method of treating fatigue data
which is thought to be how the assumption Fatigue-test data, involving nearly
is made that scatter is the result of 5000 bearings from several manufacturers,
local conditions pre-existing within each were analyzed to determine the parameters
particular specimen* in the equations relating life to load.

Cont*d Cumulative Damage in Fatigue Contrd Statistical Investigation, etc.

The statistical procedures used in the
investigation are described. They in-
The idea being a specimen that shows volve the use of order statistics for
an unusually long or short lifetime at a censored data and analysis on the basis
given stress will also show a similarly of the extreme value distribution.
long or short lifetime at a different The results from all bearing types
stress level. A one-to-one correspondence and all manufacturers are consistent with
is assumed between. a value of 3 for the slope of the load vs
life curve.

LID3TRCM, LEONARD C., AND BENJAMIN J. LAZAN UN, HUA, and ALPHONSE A. KIRSCH (MIT)
An Exploratory Study on High-Stress Low-
Effect of Fatigue Stress History on Cycle Fatigue of 2024 Aluminum Alloy in
Elasticity Properties and Stress Dis- Axial Loading.
tribution Under Rotating Bend WRIGHT AIR DEVELOPMENT CENTER, TN 56-317,
(August 1956)
WADC REPORT 56-122, 48 pages (Aug. 1956)
A review of the literature relating
to high-stress low-cycle fatigue was made,
Suitable configurations of 2024 aluminum

Contfd Exploratory Study of High-Stress, etc

LIPSITT, H.A. and G. T. HORNE
alloy fatigue specimens in axial loading
were determined. Proper techniques and
Final Report - Investigation of the Funda- necessary measuring devices were developed
mentals of Fatigue in Metals for fatigue testing of these specimens.
Various approaches to the experimental
NAGA CONTRACT NAW-6407, METALS RESEARCH study of the problem were examined by a
LABORATORY, CARNEGIE INSTITUTE OF TECH- number of tests of round specimens0 Based
NOLOGT, PITTSBURGH, PA.(January 1956) on the test results obtained thus far,
some summary remarks were made as reference
and suggestions for future work.

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LIPPSITT, HJU and G.T. HORNE LIU, Hotf., H.ToCORTEN, and G.M.SINCLAIR
The Behaviour of Single Crystals of Iron Fretting Fatigue Strength of Titanium
Under Fatigue Loading Alloy RC 130B
PAPER NO. 1 of Session 6, INTERNATIONA^ DEPT, OF THEORETICAL AND APPLIED MECHANICS
CONFERENCE ON FATIGUE OF METALS, VOL II, REPORT NO. 107 (SPONSORED BY GENERAL EL-
INST. MECH.ENGINEERS, 9 p, 2 plates (1956) ECTRIC COMPANY, CONTRACT CODE NO. 46 22 60
333) UNIVERSITY OF ILLINOIS, URBANA, ILL.
The range of stresses which will cause (September 1956)
fatigue failure in less tha 2 x 10' cycles An investigation was made to determine
in single crystals of nominally pure Fe test- the influence of a number of variables on
ed in axial tension-compression is very narrow the fretting fatigue strength of RC 130 B
Deformation characteristics are similar to Titanium alloy0 The variables studied in-
those in static tension, except that cross cluded different gripping materials, hard-
slip is more prevalent in fatigue. ness of the gripping materials, gripping

LISSNER, 0. Cont'd Fretting Fatigue Strength, etc.

pressure, surface preparation of specimens,
Importance of the Surface Effect on the dry lubricants, metallic coatings and spec-
Initiation of Fatigue Cracks. ial screen gripping shims,
An analysis of experimental results
JERNKONTORETS ANNAIER (SWEDEN) VOL 140, suggests that the primary mechanism respon-
NO. 5, PP 360-372 sible for fretting fatigue damage is the
(Abstracts in THE ENGINEER, VOL 202, NO.5244 repeated frictional shear stress on the
p. 121 (1956) and ENGINEER'S DIGEST, VOL 17, asperities or surface "high spots" which
N0.7, p 299 (1956) are in contact. The frictional force is
The fatigue experiments described in influenced by cold welding or alloying

Cont'd Importance of Surface Effect, etc. Coht!d Fretting Fatigue Strength, etc.
this paper were carried out on three carbon tendency and by surface roughness.
steel and on one quenched and tempered Cr- Based on prevention of fatigue crack
Ni steel. A surface effect wag noted, which initiation by this mechanism, a mathemati-
appears to contribute to the initiation cal expression is proposed which relates
of fatigue cracking. These fatigue tests the fretting fatigue strength to the
fatigue limit of the specimen material,
were interrupted after a period of corres- the hardness of the gripping material and
ponding to half the average life of a test the coefficient of friction.
piece at the stress spplied; a very thin
surface layer was then removed by turning,
and the fatigue test was continued. In
every case a considerable increase in the

Cont'd Importance of Surface Effect, etc. LCMAS, ToW., J.ONWARD, J.R.RAIT and
time to rupture was obtained. In the carbon E,W.COLBECK
steels, ageing was found to contribute to The Influence of Frequency of Vibration
some extent to the effect obtained. On the on the Endurance Limit of Ferrous Alloys
other hand, the greatest increase in the at Speeds up to 150,000 cycles per Minute
time to rupture was noted with the Cr-Ni Using a Pneumatic Resonance System.
steel, which showed no ageing during the PAPER NO. 7 of Session 4, INTERNATIONAL
interval between the fatigue-test periodss CONFERENCE ON FATIGUE OF METALS, VOL II,
The results obtained support a theory by INST,MECH.ENGINEERS, 13 pages (1956)
Schaub, in which the mechanism of fatigue in-
volves not only a certain plastic deforma- There is a definite influence of fre-
tion but also chemical reactions, especially quency on the endurance limit of a wide
between oxygen
Copyright by ASTM in reserved);
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29 16:12:20 2015 in range of materials when tested in resonance,
the surfaceby zone of the metal.
Downloaded/printed The pneumatic technique appears to be very
sensitive
38reproductions
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LUNDBERG, BO K.Oo LOVE, R.J.
Some Proposal for Evaluating Fatigue Fatigue in Automobiles
Properties of Airplane Structures
PAPER from INTERNATIONAL CONFERENCE ON
Presented-at SECOND EUROPEAN AERONAUTICAL FATIGUE OF METALS, VOL III, (1956)
CONFESS, THE HAGUE, Sept. 25-29, 1956, INST. MECH. ENGINEERS, 13 pages, 2 plates
instituted by AICMA, Aug. 1956, 89 pages
(English text)* AERONAUTICAL RESEARCH Fatigue investigations on gears,
INSTITUTE OF SWEDEN. FFA TECH NOTE, HE 634, crankshafts, and splines for axles.
Accelerated testing of complete vehicles.

LUNDBERG AND EGGWERTZ LOW, A.C.

The Relationship Between Load Spectra Short-Endurance Fatigue
and Fatigue Life PAPER NO. 15 of Session 2, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I,
FFA REPORT 6?, THE AERONAUTICAL RESEARCH INST. MECH. ENGINEERS, $ pages (1956)
INSTITUTE OF SWEDEN, 32 pages (March 1956)
For the five widely differing materials
A study of available data on accelerations tested with tensile strengths varying from
experienced by fighter planes indicates that 21 to 57 tons per sq. inch, but all with
the load spectrum for this category can be good ductility, fatigue life in reverse
approximated by a straight line in a semilog bending was found to depend solely on the
plot (sa vs. log H)0 For transport air- degree of strain, for maximum fiber strains
planes, the same approximation has earlier between 1 0.4 and ± 5#.

Cont'd Relationship Between Load Spectra,etc LTLE, JOHN P., JR.

been adopted. The important parameter of
straight-line spectra is the slope, the Aluminum Powder Metallurgy Products
possible variation of which is analyzed6
Using the cumulative-damage theory, the MATERIALS AND METHODS, VOL 43, NO. 4
influence of this slope on the damage-in- p 106 (April 1956)
tensity curve and fatigue life of the ele-
ment is investigatedo
Two methods have been developed for
the correction or evaluation of fatigue
lifetimes obtained by use of cumulative-
damage theory or program testing. One

Cont'd Relationship Between Load Spectra, et LYON, F.H. and H. J. (210VER

Some Suggestions for Research in
of the methods deals with the influence of Diaphragm Technology
the cut-off top of a load spectrum, while
the other takes into account a variation AMERICAN SOCIETY OF MECH. ENGINEERS
in stress level, implying also a change of New York, 12 pages (1956)
the mean stress and thus altered constants A number of suggestions for research have
in the S-N equation., appeared in recent literature, and others
In view of results obtained, an adoption have been advanced to the ASME Diaphragm
of straight-line spectra for program testing Subcommittee. These have been collected and
would yield "program-test properties'1 or discussed in this paper from the design view-
"spectrum properties'^ for materials or com- point. Extension of work on pressure-deflec-
ponents, which would be of about the same tion response, anelastic effects, temperature
basic nature
Copyright by ASTM asInt'l S-N properties.
(all rights reserved); Tue Dec 29 16:12:20 EST 2015 behavior, and fatigue to diaphragms is dis-
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further reproductions and suggest possible ap-
authorized.
roaches to certain problems.
MC GAMMON, R.D. and H.MoROSENEERG MC KEOWN, J 0
Hie Cold Work Introduced During the A Rapid Method of Estimating the Fatigue
Fatigue of Copper Limit or Endurance limit of Metals in
Reverse Bending
PHILOSOPHICAL MAGAZINE, VOL I, NO. 10
SER. 8, pp 964-966 (October 1956) METALLURGIA. VOL 54, pp 151-156, 158
(Sept, 1956)
Evidence supporting view that energy Use of the Prot method as a sorting
stored in a fatigue metal is released at process was studied in Wohler type machines
a different temperature and at a different at 3000 rpm. Specimens were spring-loaded,
rate from that stored in a metal strained the spring being extended at a constant rate,
in tension. Materials tested were lead and lead
alloys, copper and copper alloys, plain car-

MC CLINTOCK, F.A. Cont'd Rapid Method of Estimating Fatigue,etc

The Growth of Fatigue Cracks Under Plastic bon and alloy steels, aluminum alloys and
Torsion magnesium alloys; a few tests were made on
notched and unnotched titanium alloy,Til50A.
PAPER NO. 6 of Session 6, INTERNATIONAL The results showed considerable promise,
CONFERENCE ON FATIGUE OF METALS, VOL II, except for materials which are unstable in
INST. MECH. ENGINEERS, 7 p, 2 plates (1956) the conventional fatigue test (some alumin-
um alloys). Relationship between the en-
durance limit and the dynamic breaking
stress in general was linear over a fairly
Theoretical analysis and experiments wide range of strength values.
with an Al alloy. :

MC EVILY, ARTHUR J.,JR., WALTER ILLG and MC KEOWN, J.

HERBERT F. HARDRATH
Static Strength of Aluminum-Alloy Specimens Fatigue Properties of Some Non-Ferrous
Containing Fatigue Cracks Metals Excluding Light Alloys
NACA TN 3816, (October 1956) 54 pages, PAPER NO. 3 Session 5, INTERNAITONAL
diagrs., photos, tabs. CONFERENCE ON FATIGUE OF METALS, VOL II,
INST. MECH. ENGINEERS, 9 pages (1956)
Seven configurations of specimens made
of 2024 and 7075 aluminum-alloys in both Lead and its alloys; copper and its
rolled and extruded form were subjected to alloys; metal for slSeve bearings, coated
repeated axial loads until fatigue cracks metals.
of various lengths were formed. The spec-

MC KINNELL, W.P.JR., F.H. BECK and

Cont'd Static Strength of Aluminum-Alloy, etc M.G.FONTANA
imens were then subjected to static tests Corrosion-Fatigue Testing in Highly
to determine the residual static strength* Corrosive Media
Small cracks resulted in disproportionately
large reductions of static strength, the NEWS IN ENGINEERING, OHIO STATE UNIVERSITY,
reduction being greater for 7075 than for VOL 28, pp 28-32 (Nov. 1956)
2024 aluminumOalloyo A simple method of Reverse-bending fatigue-testing machine
analysis which predicts the observed re- was selected for conversion to corrosion-
sults was developed and described. fatigue testing. For the fuming nitric
acid corrosion-fatigue tests, titanium
and stainless steel were the materials
Copyright by ASTM Int'l (all rights reserved); Tue Dec 29 16:12:20 EST 2015 whose properties were investigated.
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MABIE, H.Ho and MoS.GJESDAHL MARTIN, J.W.C, and G. C. SMITH
A Fatigue Testing Machine for Reversed A Preliminary Study of the Fatigue of
Bending and Steady Torque Metals in Liquid Metal Environments
SOCIETY EXPERIMENTAL STRESS ANALYSIS METALLURGIA, VOL 54, NO.325 (Nov0 1956)
PROCEEDINGS, VOL VIX, NO. 1 (1956) pp 227-232,238
pp 83-88 Wohler and Haigh-Robertson fatigue tests
A fatigue testing machine constructed to were carried out on two brasses, and copper-
tin and copper-cadmium wire at room tempera-
test 1-in, diameter shafts in reversed bend- ture to study the effect of a coating of
ing, with or without a steady torque, is mercury* Push-pull tests were made on
described. mild steel in contact with liquid tin at
300C, and on 18/8 stainless in contact with

Cont*d Fatigue Testing Machine, etc. Cont'd Preliminary Study of Fatigue, etc.
liquid sodium at 300C» The liquid metal was
Tests were made at a few cyclic contained within the specimen.
stress levels and one torque level on The brasses showed a reduction in life
round shafts with keyways, triangular at all stresses, but the effect of amalgam-
shafts with rounded corners, and square ation on the Cu-Sn and Cu-Cd wires was neg-
shafts with rounded corners, prepared ligible. Liquid tin reduced the endurance
from normalized SAE 1045 steel. of mild steel at all stresses, whereas liq-
The results are presented. uid sodium had no marked effect in the few
tests made on stainless steel. In all
cases the deleterious effect was a minimum
in the region of the fatigue limit.

MANN, J«Yo
MASI, O.and A. ERRA
The Effect of Stress Concentrations on the
Fatigue Resistance of a Duralumin-iype The Reduction in Fatigue Strength of
Aluminum Alloy Weld Metal by Defects

ROYAL AERONAUTICAL SOCIETY JOURNAL, WELDING RESEARCH ABROAD, VOL 2, NO. 1

VOL 60, pp 681-685 (October 1956) PP 33-36 (January 1956)

Fatigue curves were established under

a wide range of theoretical stress-concen-
tration factors. Notch sensitivity is
assessed.

MARIN, JOSEPH MASON, W. Po

Interpretation of Fatigue Strengths Internal Friction and Fatigue in Metals
for Combined Stresses at Large Strain Amplitude

PAPER NO. 12 of Session 2, INTERNATIONAL ACOUSTICAL SOCIETY OF A1ERICA JOURNAL,

CONFERENCE ON FATIGUE OF METALS, VOL I, VOL 28, pp 1207-1218 (November 1956)
INST. MECHo ENGINEERS, 13 pages (1956)
Experimental determinations, using
Development of theory for predicting a barium titanate transducer coupled
fatigue strength of materials under combin- with an exponential horn.
ed states of stress*
Comparisons with test data.
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 MOTT, K.P.
MATTSON, R.L,
Fracture in Metals
Fatigue, Residual Stresses, and Surface JOURNAL IRON AND STEEL INSTITUTE, VOL 183,
Cold Working p 233 (July 1956)
PAPER NOo 5 of Session 1, INTERNATIONAL Discusses ductile fracture, brittle frac-
CONFERENCE ON FATIGUE OF METALS, VOL HI ture (especially in ferrous metals), and
INST. MECHo ENGINEERS (1956) fatigue in terms of dislocation theory0 Pro-
13 pages, 2 plates poses that the three stages of hardening ob-
served in plastic deformation of single
Experimental data illustrate the crystals also occur in cyclic straining0 The
importance of these problems. manner in which a slip line develops into a
crack is not yet clear.

MOHR, E. MURDOCH, JOHN ¥„

Recent Results from Investigation of The Behavior of Plain Concrete Subjected to
the "True Elastic Limit" Repeated Flexural Loading
ALUMINUM VOL 32, NO 4, PP 202-204 DEPT. OF THEORETICAL AND APPLIED MECHANICS
(April 1956) REPORT N0ol04, MASTER'S THESIS, UNIVERSITY
OF ILLINOIS (August 1956)
Extensive comparative studies have
shown that the bending-tensile strength This investigation reports the results
obtained from tests involving combination of tests of 220 plain concrete beams sub-
of static with cyclic stressing must be close jected to repeated flexural loading. Series
to the fatigue strength, although it has not of tests were made to determine the effects
yet been possible to prove that the former of the following variables on the behavior

Cont'd Recent Results from Investigation,etc Cont'd Behavior of Plain Concrete, etc.
under repeated loadings:
is identical with the "true" or fatigue (l) Range of stress, (2) Consistency of the
(or "dynamic") elastic limit., From the plots concrete mix, (3) Intermittent rest periods
of the number of repeated bends against the introduced into the loading pattern, (4)
tensile stress, information can be obtained Increased moisture content in the specimen.
for working out the bend-tensile strengths
which (as results from various aluminum It was found that plain concrete exhibits
alloys show) agree surprisingly well with no endurance limit when subjected to loads
the values of the fatigue strength0 This is which produce no reversals of stress. Fati-
true not only of tests on flat test bars but gue limits at ten million repetitions of
also for notched (drilled) bars and for stress were determined for each of the sev-
tests at high temperatures. eral ranges of stress investigated. The
fatigue limit was found to be affected by

MORRISON, JoLJ»., B. CROSSLAND and Cont'd Behavior of Plain Concrete, etc.

JoS.Co PARRY the range of stress but it was not influenced
by the consistency of the concrete mix,
Fatigue Under Triaxial Stresss Development Intermittent rest periods appear to be bene-
of a Testing Machine and Preliminary ficial, while an increased moisture content,
Results when present in specimens which have not
been extensively aged, adversely affects the
THE CHARTERED MECHANICAL ENGINEER, JOURNAL fatigue limit. The results of this in-
OF INST. MECHANICAL ENGINEERS, VOL 3, vestigation are in good agreement with those
NO.3, Page 153 (March 1956) of previous investigations insofar as valid
comparisons may be madec The need for ad-
ditional tests is, however, apparent;this
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42 investigation affords no conclusive data
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from which the mechanism of failure may be
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defined, nor does it describe the behavior of
plain concrete subjected to flexural loads.
 MflLLER-BUSSE, A. NAMBIAH, E.K.N.
The Behavior of a Welded Aluminum Alloy Fractures in Service
of the Al-Zn-Mg T^pe (German) TISCO, VOL 3, PP 153-162 (July 1956)
ALUMINUM, VOL 36, NO. 6, pp 333-339
(June 1956) Simple overload and fatigue fractures;
sources of stress-raisers; effect of
Data on static and fatigue strengths show temperature on fracture; influence of
that considerable use of the alloy for weld- corrosion; an example of service failure
ed structures in the future can be pre- investigation.
dicted.
Photographs, micrographs, graphs,tables.

MURPHT, SODERBERG AND ROSSHEIM NATIONAL BUREAU OF STANDARDS

Considerations Affecting Future Pressure- Motion Pictures of Metal Fatigue

Vessel Codes
NATIONAL BUREAU OF STANDARDS TECHNICAL
WELDING JOURNAL, VOL 35, NO 12,(Dec.1956) NEWS BULLETIN, VOL. 40, p 153 (Nov. 1956)
pp 5B2s-596s A small torsion fatigue machine was mount-
ed on the stage of a microscope. By inter-
Code requirements are presently associated rupting the light with a shutter on the shaft
with extremely ductile materials and safety of the machine, it was possible to take
factors ample to limit consideration to sim- 16 mm motion pictures of the microscopic
ple stress formulas. Impact and fatigue features of the surface during the fatigue
process.

Cont'd Considerations Affecting Future, etc, NAVROTSKII, D.I.

Impact Tests of Welded Joints (Russian)
tests could well be justified for vessels SVAROCHNOE PROIZVODSTVO, N0.6 (June 1956)
where the full potential of the materials PP 14-17
is to be approached. The work of the Methods and results of impact tests of
Pressure Vessel Research Committee, Weld- welded specimens for determining the critical
ing Research Council on fatigue resistance brittleness and yield points, relative elon-
of current and rejected ferrous materials gation, and relative reduction in area.
is summarized. Tensile and bending impact strength of
welded joints is found to be not lower than
that of the base metal. Diagrs, graphs,
tables, photos. 3 ref.

MUVDI, B.B., G. SACHS and E.P.KLIER NEWMAN, R.P.

The Influence of Weld Faults on Fatigue
Design Properties of High-Strength Steels Strength With Reference to Butt Joints
in the Presence of Stress Concentrations in Pipe Lines
and Hydrogen Embrittlement
INST. MARINE ENGINEERS, TRANS., VOL 68
WADC TECHNICAL REPORT 55-13, Supplement 1, pp 153-172 (June 1956)
WRIGHT AIR DEVELOPMENT CENTER, AIR RESEARCH The root zone of welds, with and without
AND DEVELOPMENT COMMAND (February 1956) backing rings, exercises a predominant in-
fluence on fatigue behavior. Except in the
case of lack of penetration defects, show
no significant effect on fatigue strength.
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NEWMAN, R.P. and G. COATES NOREMARK, G.E., Z^SHDDIEY, and
J.E.STALDffiYER
Fatigue Tests on Thin-Gage Box-Section Beams Fatigue and Static Properties of Welded
Joints in Low Alloy Structural Steels,Part II,
PAPER NO. 2 of Session 9, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II CIVIL ENGINEERING STUDIES, STRUCTURAL RE-
INST.MECH.ENGINEERS, 9 pages (1956) SEARCH SERIES N0.114, UNIV. OF ILLINOIS,
URBANA, ILL. (Jan. 13, 1956)
The purpose of the tests included Part I
of the present investigation was to deter-
mine the fatigue and static properties of
but It-welded joints in A-242 steel and to
compare, quantitatively, these results with
those obtained from similar joints in A-7

NICHOLS, R.W* Cont'd Fatigue and Static Properties, etc.

The Mechanical Properties of Carbon- steel. Tests were performed on three low
Steel Wire at Low-Temperatures alloy steels having appreciably different
chemical compositions to determine the uni-
IRON AND STEEL INSTITUTE JOURNAL, VOL 182, formity of the results. The report in-
PP 337-347 (April 1956) cludes the results of tests of four types
of specimens; plain plate specimens, longi-
Tensile, impact, fatigue, and high- tudinal fillet-welded joints, and transverse
strain reversed bend tests were made at and longitudinal butt-welded joints.
temperatures ranging from 20° to -60°C All of the fatigue specimens were tested
on 0.5# and 0.755? C wire in the annealed, on a zero-tension stress cycle of such a
as-drawn, and electro-galvanized cbnditions, magnitude that failure generally occurred

Cont'd Fatigue and Static Properties, etc.

Cont'd Mechanical Properties of Carbon, etc.
between 100,000 and 2,000,000 cycles.
The fatigue limit, determined on Haigh- When subjected to repeated loadings,
Robertson machines, increased with decreasing the low-alloy joints (welded with low hy-
temperature except for the electro-galvan- drogen electrodes) were found to be about
ized materials, which showed decreased 15 per cent stronger than similar joints
fatigue strengths at low temperatures. In of A-7 steel prepared with E6010 electrodes.
reversed-bending tests around formers, the However, when compared to joints in A-7
endurance of all materials decreased with steel prepared6 with E7016 electrodes, the
decreasing temperatures, the deterioration advantage of the A-242 joints was less than
being greatest for the electro-galvanized 10 per cent for the butt-welded joints.
wires.

NISHIHARA, TOSHIO and TOSHIRO IAMADA NOTHING, F.W.

Fatigue Strength of Metals Under Alter-
nating Stresses of Varying Amplitude Corrosion, Cracking, and Erosion on the
Outer Surface of Copper-Alloy Tubing
KYOTO UNIVERSITY, MEMOIRS OF FACULTY OF (German)
ENGINEERING, VOL 18, NO. 3, PP 172-208
(July 1956) METALL, VOL 10. NOS 21-22, pp 1033-1038
(November 1956)
Formulas for predicting fatigue life and
fatigue limit. Testing machines and their Stress corrosion; cracking and cor-
use on unnotched and notched specimens of rosion. Corrosion fatigue and erosion.
low-carbon and high-carbon steels, and of
duralumin.
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NORTHCOTT,L. and H.G.BARON OGDEN, H.R., F.C. HOLDEN and R,I.JAFEEE
The Craze Cracking of Metals Mechanical Properties of Ti-Cr-Mo Alloys
as Affected by Grain Size and Grain Shape
JOURNAL HON AND..-STEEL INS3XTUIE, VOLa84 TRANSACTIONS ASM, VOL XLVIII, pp 627-656
PP 385 (December 1956) (1956) (ASM-SLA CLASSIFICATION: Q GENERAL
M27, N3, Ti)
"Craze Cracking" (also called "thermal
fatigue" and "heat checking") is a form Changes in grain size and grain shape
of surface failure produced by repeated in an alpha, a metastable beta, and an alpha-
thermal stresses. An experimental method beta alloy of titanium alloyed with chromium
for producing craze cracking was developed; and molybdenum appear to leave the fatigue
the narrow face of a wedge-shaped specimen

Cont'd Craze Cracking of Metals Contfd Mechanical Properties of Ti-Cr-Mo

was heated intermittently by induction,
while the heavy section was continuously endurance limit unaffected. Varying the
water-cooled. Results of tests on carbon alloy content within the range studied
steels, heated to 700-1000 C, are shown (Ti-7.5 Cr -7.5 Mo and Ti-2.5 Cr-2.5 Mo)
and are discussed on the basis of the seems to have but little effect upon the
stress and strain changes occurring dur- fatigue properties although the tensile
ing thermal cycling. strength is markedly affected.

O'CONNOR, H.C. and J.L.M.MORRISON OLSEN, GERNER A.

The Effect of Mean Stress on the Push-Pull Strength of Materials
Fatigue Properties of an Alloy Steel
SECOND ED., PRENTICE-HALL, NEW JERSET
PAPER NO. 3 of Session 2, INTERNATIONAL 444 P. (1956)
CONFERENCE ON FATIGUE METALS, VOL I,
INST. MECH. ENGINEERS, 10 pages (1956) Principles of mechanics, including center
of gravity, moments of inertia, streaa and
The limiting safe range of stress was in- strain; riveted and welded .joints; torsion;
vestigated for mean stresses varying from design and deflection of indeterminate beams;
30 tons per dq in compression to 37-i tons fatigue strength.
per sq in tension. There is a linear re-
lation between the safe range of stress and
the mean stress for all ranges of stress in
which the lower static yield is not exceeded .
ODING, I.A. and V.S. IVANOVA ORLOV AND CHULOSHNIKOV
Fatigue of Metals Under Contact Friction Torsion Testing of Spot Welds (Russian)
PAPER NO. 11 of Session 4, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II, SVAROCHNOE PROIZVODSTVO, NO.6,
INST.MECH.ENGINEERS, 8 pages (1956) pp 20-21 (1956)
Reduction in fatigue limit in conditions Equipment and procedures involved
of contact friction can be explained by the and the results of spot-weld tests on
process of electric erosion that proceeds a number of materials.
under the action of a theremoelectric cur- Diagram, photographs, graph, table.
rent produced as a result of friction, and
which pulsates in magnitude because of a
variation in the resistance of the contact.
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OZELL, A.M.1 AND E. ARDAMAN PARRY, J.S.C.
Fatigue Tests of Pre-Tensioned Pre- Further Results of Fatigue Under
Stressed Beams Triaxial Stress
PAPER NO. 7 of Session 2, INTERNATIONAL
JOURNAL AMERICAN CONCRETE INSTITUTE, VOL 28 CONFERENCE ON FATIGUE OF METALS, VOL I,
NO. 4, PP 413-424 (October 1956) INST. MECH. ENGINEERS, 8 pages (1956)
Fatigue tests were conducted to determine The low critical shear stress previous-
the behavior of pretensioned concrete beams ly found for the catigue limit for unpro-
prestressed with 7/16 inch seven-wire tected cylinders subjected to repeated in-
strands. Eight beams (6H x 8" x 20'), ternal pressures appears little affected
with a center load, were tested to obtain by wide variation of triaxial tensile stress
some solutions to the following questions: or fluid pressure.

Contfd Fatigue Tests of Pre-Tensioned,etc.

Cont'd Further Results of Fatigue, etc.
Is the use of 7A6 inch sev^n-wire strand
feasible from the standpoint of repetitive
loads? Does a beam pretensioned with Strength can be raised by honing the
7/16 inch strand fail in fatigue because of bore after heat-treatment or by protecting
bond failure in the concrete or by breaking the bore from the fluid by a thin film of
in the strand? What is the magnitude of rubber.
changes in the load-deflection character-
istics influenced by fatigue damage? What
amounts of permanent set does a beam undergo
when subjected to repetitive loads?

Cont'd Fatigue Tests of Pre-Tensioned,etc.

PAINE, A.O.
Pilot test results answer all the above
questions, and further indicated that no A Note on the Fatigue of Wings
shear cracks were developed near the sup-
ports during the fatigue tests. It was JOURNAL AERONAUTICAL SOCIETY, VOL 23,
possible to draw a load versus failure- NO.8, p 747, (READER'S FORUM) (Aug 1956)
cycle diagram from the test data.
12 figures, 3 ref.

PARANJOE, V.Go PETERMANW,.HANS J.

Theories of Fracture A Fatigue Evaluation of a Wing Main Spar
TISCO, VOL 3, PP 144-152 (July 1956) to Fuselage Attachment Fitting for a
Various types of fractures; divergence Light Bomber
between theoretical and observed strengths;
theories of brittle and ductile fractures; AIRFORCE INST.OF TECH., WRIGHT-PATTERSON
brittle fracture in normally ductile mater- AFB, THESIS (Aug. 1956) 36 pages incl.
ials; fatigue and intercrystalline failures; illus., tables (REPORT NO. GAE 56-20)
effect of structural heterogeneity on in-
itiation and propagation of fracture.
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PAYNE, A.O. PERSON, N.Lo and B.J.LAZAN
An Investigation into the Fatigue Characteris The Effect of Static Mean Stress on the
tics of a Typical 24S-T Aluminum Alloy Wing Dumping Properties of Materials

PAPER NO. 3 of Session 8, INTERNATIONAL ASTW PREPRINT NO. 85, 1956 ANNUAL MEETING
CONFERENCE ON FATIGUE OF METALS, VOL II, A rotating cantilever machine was modi-
INST.MECH.ENGINEERS, 11 pages (1956) fied for mean stress work by converting it
also AIRCRAFT ENGINEERING ( ENGLAND) VOL 28 for bending vibration decay tests. Tests
NO.334, PP 431-432 (December 1956) were carried out on SIE 1020 Steel, 2024-T4
altiminum alloy, J-l magnesium, annealed
An interim report is presented concern- BC-55 titanium, S-816 alloy, glass laminate,
ing results obtained by the testing to and type 403 alloy. The mayiffmTn stress ap-
failure of ninety-one P-51-D Mustang fighter plied was kept beldw the cyclic stress

Cont'd Investigation into Fatigue, etc. Cont'd Effect of Static Mean Stress, etc.
wings at various mean and associated alter- sensitivity limit.
nating load levels. It was demonstrated With the exception of type 403 alloy,
that the Mustang wing, which was to be re- the change in damping versus alternating
presentative of the loading of a civil trans- stress relationship was less than 30% due
aircraft, had, contrary to the results ob- to the superimposed mean stress. For the
tained on small specimens, a longer life magneto-mechanical alloy 403 > the specific
under random loading than obtained by ap- damping energy decreased 90#, at +, 10,000
plying the linear cumulative damage rule. psi, when the mean stress was increased
The paucity of information so far from 0 to 40,000 psi.
made available does not enable a final

Cont'd Investigation into Fatigue, etc.

PETERS, ROGER W. and NORRIS F. DOW
conclusion to be drawn as to the reason Failure Characteristics of Pressurized
of the discrepancy; the lives of the Stiffened Cylinders
small specimens lying on the unsafe side NACA TN 3851 (December 1956) 18 pages
and those of the full-scale specimens diagrs, photos, tabs.
lying on the safe side, relative to the
linear cumulative rule. Stiffened cylinders of 2024 and 7075
aluminum alloys, representative of fusel-
age construction, were tested under internal
pressure and cyclic torsion. Fatigue cracks
which developed in the skin resulted in
both gradual and explosive types of failure.

PETERSON, R.E. Contfd Failure Characteristics, etc.

A Method of Estimating the Fatigue Strength The types of failure depended upon
of Small Ellipsoidal Cavities the hoop stress and the structural con-
figuration, and particularly upon the ratio
PAPER NO. 4 of Session 2, INTERNATIONAL of area in rings to associated skin area.
CONFERENCE ON FATIGUE OF METALS, VOL I The tests indicated that the 7075
INST, MECH. ENGINEERS, 10 pages (1956) alloy is somewhat more prone to the explosive
type of failure.
Methematical analysis for prolate and
oblate ellipsoids and inclusions$ appli-
cation to rotor problems.
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PHILLIPS, C.E, PLEINES, E.W.
Fatigue Cracks as Stress Raisers and Their The Engineering Properties of Synthetic
Response to Cyclic Loading Resin Adhesives and the Strength of the
Bond They Produce with Aluminum, According
PAPER from FATIGUE IN AIRCRAFT STRUCTURES, to Recent Foreign Information (German)
ACADMIC PRESS, PP 104-125 (1956)
ALUMINUM (BUDAPEST) VOL 32, NO. 5
Observations of crack growth of un- pp 257-265 (1956)
notched and V-notch specimens of a mild Previous parts of this paper (Aluminum
steel, a heat treated nickel-chromium steel, 1 and 3, 1956) described the physical and
and a l$> copper-aluminum alloy. technical principles of bonding and the
13 ref. mechanical properties of bonded aluminum-
aluminum joints, bond strength specifications
in the USA and Great Britain, temperature

PHILLIPS, C.E. Cont'd Engineering Properties of Synthetic,etc

Research on Fatigue of Metals at Mechanical effects and the strengths of complete
Engineering Research Laboratory, East Kilbride bonded structures. The present, conclud-
ing, part deals with the following: the
INST. ENGINEERS & SHIPBUILDERS IN SCOTLAND, strength of bonded light-metal joints under
TRANSACTION, VOL 99, PART 3, PP 173-192 static and cyclic stressing, and the be-
(1955-56) havior of bonded aircraft components under
cyclic stressing, It is noteworthy that
Review of recent reserach on pin joints, in static strength tests, large bonded
screw threads, effect of size of specimen, structures behaved better than the revitted
propagation of fatigue cracks, and low- ones.
endurance fatigue studies. 9 ref.
Graphs, diagrs,photo,microgrs, table.

PLATEAU, HENRY, AND CRUSSARD PROKHOROV, N.N.

Morphological Study of Rupture Surfaces The Strength of Metals Welded During
With the Electron Microscope (French) the Process of Crystallization (Russian)
REVUE UNIVERSELLE DES MINES, VOL 12,NO.10 SVAJROCHNOE PROIZVODSTVO, NO.6, (June 1956)
SERIES 9, pp 543-554 (October 1956) PP 5-11
Classical rupture types (ductile, inter- Discusses existing hypotheses and sug-
granular, cleavage) and fatigue ruptures gests an original one regarding the strength
were examined by the carbon replica tech- of metals.
nique. Described methods of testing the strength
of these metals.
Graph, diagrams, 19 ref.

POPE, J.A. and C.W. BARSON PUCHNER, 0.

Strength-Reduction Factors for Small Quench- Effect of Flame-Straightening on the
ing Cracks and for Decarburized Steel Fatigue Limit of Edged C-Profiles (Czech)
PAPER NO. 10 of Session 6, INTERNATIONAL ZVARANIE, VOL 5, NO.4, pp 104-106
CONFERENCE ON FATIGUE OF METALS, VOL II, (April 1956)
INST. MECH. ENGINEERS, 8 p, 2 plates(l956)
Flame straightening of parts of auto-
Heavy decarburization is more detri- mobiDe frames is tested to see whether the
mental to the fatigue strength of the Si-Mn fatigue limit of the high tensile steels
steel tested than the small quenching is adversely affected.
cracks induced,, Overstrain has no bene-
ficial effect upon the quenching cracks.
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RAITHBY, K.D and JENNIFER LONGSON EEGIER, ARTHUR A.
Some Fatigue Characteristics of Two-Spar Noise, Vibration and Aircraft Structures
Light-Alloy Structures (Meteor 4 Tailplane) AERONAUTICAL ENGINEERING REVIEW, VOL 15
AERONAUTICAL RESEARCH COUNCIL (CffiEAT NO. 8 (August 1956)
BRITAIN) RAE STRUCTURES 195 (Jan. 1956)32 p. General consideration of the problems
Results are given for fatigue tests on associated with noises in respect to vibra-
6l Meteor tailplanes, treated as representa- tion and fatigue damage of aircraft struc-
tive small-scale wing systems and tested tures. Discusses response of systems to
under a variety of loading conditions. various types pf inputs: (l) discrete fre-
The object of the investigation was to quency, e.g. propellers; (2) random frequency,
study the fatigue characteristics of a e.g.jets; (3) impulsive frequency, e.g. gun
typical aircraft structure, in particular blasts.
the effects of mean load and alternating

Contfd Some Fatigue Characteristics, etc. Cont'd Noise, Vibration and Aircraft, etc.
load on the endurance. The effects of pre- Discusses near field characteristics
loading, periodic overloading, and low of various noise sources, vibration modes
temperature were also investigated. En- and fatigue. Emphasis is on concepts and
durance curves are given for different orders of magnitude. Points out need for
mean loads; the results indicate that, for great deal more information on the fatigue
a given alternating load, the endurance of skin structure and its supports when
is roughly inversely proportional to mean subjected to the type of loading imposed
load. Substantial improvements in endur- by noise.
ance may be obtained by preloading and by
periodic overloading. The endurance at low

Cont'd Some Fatigue Characteristics, etc, RET, WILLIAM K.

Elevated-Temperature Fatigue Properties
of Two Titanium Alloys
temperature is higher than at room tem-
perature. NACA RESEARCH MEMORANDUM 56B07,
28 pages (April 1956)
Test results are presented in tabular
form and as curves of stress versus cycles
to failure for each test temperature.
Tables, photograph, graphs, diagram.
1 ref.

RATNER, S.I. RICHARDS, D.G.

Destruction by Repeated Loading (Russian) Structural Testing of Aircraft Propellers
DOKLADY AKADEMII NAUK SSSR^ VOL 106 SOCIETY FOR EXPERIMENTAL STRESS ANALYSIS
N0.2, (Jan. 11, 1956) pp 246-249 PROCEEDINGS, VOL 13, NO.2, pp 49-56 (1956)
Two conditions exist in a material Procedure involves vibration stress
during loadings decrease of fracture surveys conducted on the airplane in
resistance and increase in resistance question, laboratory fatigue tests, and
to plastic deformation. service sampling.
Table, graphs. 2 ref.

49
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HOIG, MARIO PUJOL ROSS, S.T., R.P.SERNKA and W.E0JCMINY
Variation in the Properties of Spring Some Relationships Between Endurance Limit
Steels as a Function of Their Heat Treat- and Torsional Properties of Steel
ment and Surfaces Finish (Spanish)
TRANSACTIONS ASM, VOL XLVIII, pp 119-148
INSTITUTO DEL HEERRO Y DEL ACCERO, VOL 9, (1956) (ASM-SLA CLASSIFICATION?Q7,01,AY)
N0.43, PP 183-197 (February 1956)
discussion pp 197-198 Data are presented to show that, up to
Types of steel for springs, with the certain ranges of Rockwell ttCn hardness,
appropriate heat treatments. Experimental there is a linear relationship between the
study of a carbon spring steel; physical torsional yield strength or the endurance
properties, tests, heat treatment (classical limit and hardness for six medium-carbon
and isothermal), surface treatments. low-alloy, hardened-and-tempered steels
(SAE 2340, 4052, 4063, 4140,4340, and 5150)
These data also show there is apparently a

Cont'd Variation in Properties of Spring,etc, Contfd Some Relationships Between Endurance-

Relation of type of heat and surface constant difference in the hardness at which
treatments to fatigue behavior. Treatment the optimum endurance limit is obtained and
resulting in bainitic structure. Advantages that at which the optimum yield strength is
of polishing and phosphatizing. obtained in the tempered steels investigated,
Tables, diagrams ^photographs, micro- On this basis, it is stated that "the rela-
graphs , graph s. jf ,4^ re f. tively inexpensive torsion tests can indi-
cate the hardness to which medium carbon,
low alloy steels should be tempered to
obtain maximum fatigue properties."
(In evaluating the authors1 findings,

ROONEY, ROB1ST J. Cont!d Some Relationships Between Ehdurance-

Fatigue Life of 2024-T4 Aluminum Alloy it should be remembered that the results
at Low Stresses apply only to polished or super-finished
specimens and that the linearity between
MATERIALS LABORATORY, WRIGHT AIR DEVELOP- the endurance limit and tensile strength
MENT CENTER, WPAFB, OHIO, WADC-TN-56-433 or hardness disappears as the surface fin-
(October 1956) 4 pages including illus. ish becomes more irregular, such as when
notches or scale are present in the surface
under strain.)

ROONEY, R0J. RUDKBJ

Fatigue Properties of Fusion Butt-Welded Welding in the Shipbuilding Industry
High Strength Aluminum Alloys BRITISH WELDING JOURNAL, VOL 3,
pp 22-24 (January 1956)
REPORT ON FATIGUE PROPERTIES OF AIRCRAFT
STRUCTURAL MATERIALS, WADC TN-56-264, Research on butt-welding processes,
(June 1956) 14 pages, illus. tables. fillet welding by visible-arc machines,
and the brittle-fractures problem is
urgently needed. Labor scarcity, need
for modernization, and fatigue failures
present further problems.
50
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RUSSELL, J.E. AND D.V.WALKER RYDER, EJU AND GoC.BARNES
Some Preliminary Fatigue Results on a A Rapid Fatigue Test for Rolling Contact
Steel of Up to BOO V.P.NoHardness Using Materials
Notched and Unnotched Specimens ASTM BULLETIN, VOL.54, PP 63-64 (Oct. 1956)
PAPER NO 6 of Session 5, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II, A simple test rig is described for
INST. MECHoENGINEERS, 5 pages (1956) obtaining data on the fatigue characteris-
There is no confirmation of the theory tics of call bearings for jet engine appli-
that low fatigue ratios for very high tensile cations, A single ball held in a bronze
steel are due to lower tempering temperature. cage is placed between two drums, one of
No significant improvement in fatigue pro- which is driven while the other coasts.
perties is noted for C contents above 0,5#. The load on the ball can be controlled,
Tendency of notch susceptibility to fall

Contfd Preliminary Fatigue Results, etc. Cont'd Rapid Fatigue Test for Rolling Contact
and two ground flats on its poles confine
with increasing hardness above 400 V.P.N. the loading to an equator; the speed is
is confirmed. about 133*000 stress cycles/min» on the ball.
Oil can be supplied to the ball with or with-
out heat.
Results are presented from tests on
balls of SAE 52100 steel under progressive
loading conditions, and show some superior-
ity for vacuum melt steel.

RYBAI1CO,F.P., G.V.MIROUUBOV AND N.N.SIUTKIN SACK, G., B.BJTOVDI AND E.P.KLIER

The Effects of Frequency and Amplitude Design Properties of High-Strength Steels
of Alternating Cyclic Torsion on the in the Presence of Stress-Concentration
Maximum Plasticity of Metals and Certain
Alloys (Russian)
WADC TECHNICAL REPORT 55-103,
FIZIKA METALLOV I METALLOVEDENIE, VOL 3, SYRACUSE UNIVERSITY (January 1956)
N0.2, pp 341-348 (l$56)
Maximum plasticity of copper, lead,
tin, brass zinc, aluminum and its zinc
alloys decreases with the amplitude of
the deformation.

Contfd Effects of Frequency and Amplitude SCHAAL, A.

X-Ray Study of Behavior of Steels Under
Increasing the frequency of the cycles Repeated Cyclic Steels (German)
increases the plasticity of the metals,
while in the alloys it depends on the (HENRY BRUTCHER-TRANSACTION 3102) (1956)
relationship of the components. 30 pages

51
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SAFEE, WESLEI W, SCHIJVE, Jo
The Fatigue Strength of Riveted Joints
Tests Probe Limits of Controlled Shot and Lugs
Peening NACA TM 1395s 54 pages, diagrs, tables
IRON AGE, VOL 177, NO, 1, pp 76-79 (August 1956)5 Translation of DE VERMOEI-
(March 1, 1956) INGSSTERKTE VAN KLINKVERBINDINGEN EN
PENGATVERBINDINGEN, NATIONAAL LUCHVAART-
Shot peening can make an important LABORATORUM, RAPPORT M 1952, May 1954.
contribution to improving the fatigue Ihis report deals with a number of
life of metals. It can also provide a tests on riveted joints and lugs for the
surface finish which reduces the chance primary purpose of comparing the several
of part failureo But shot peening isn't types of riveted joints and to study the
infallible. It can be misapplied. effect of various factors on the fatigue
strength of lugs.

Cont'd Tests Probe Limits of Controlled,etc. Cont*d Fatigue Strength of Riveted, etc.
Knowing the "do's11 and "don'ts11 helps A check was made to ascertain whether or
make your shot peening operation more not an estimate of the fatigue life at a
effective, more profitable. certain loading could be made from the
There appears to be no direct re- dimensions of the joint and the fatigue
lation between arc height (Alraen test data of the unnotched material. Recom-
strip) and fatigue life. A maximum of mendations are made on the proportioning
50 psi air pressure is adequate for all of joints to obtain better fatigue be-
but the smallest shot. havior .

SCHIJVE, J. SCHLIECHER, R.L.

Fatigue-Crack Propagation in Light Practical Aspects of Fatigue in Aircraft
Alloys (in English) Structures
PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
NATIONAAL LUCHTVAARTLABORATORIUM. ACADEMIC PRESS, pp 376-426
RAPPORT NLL-TNM 2010, (July 1956)
27 pages, 16 plates Unit and component fatigue tests,
case histories, and an outlien of good
Theoretical consideration. The design practices.
consequences of a fatigue crack in an 12 refo
aircraft structure„

SCHWARTZ, CHARLES M.
SCHIJVE, J.
Fatigue Failures
General Survey of the Fatigue Phenomenon SAE JOURNAL, VOL 64, p 49 (June 1956)
(Dutch)
Fatigue failures appear to be related
INGENIEUR, «S-GRAVc, VOL 68 to "mistakes" in the crystal structure of
p W91, (July 1956) a ductile metal. The relationship between
fatigue failures and imperfections in the
crystal might be deducted from correlation
of X-Ray measurements of atoms dislocated
by microstresses from their ideal position
in the crystal lattice with fatigue data.

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SEBISTY, JoJ.,AND JoO.EDWARDS SERENSEN, S.W.
On the Endurance of Cast Iron and Steel
Some Metallographic Observations on the Under Repeated Loading of Varying Amplitude
Fatigue Failure of Bare and Clad Aluminum-
Copper-Magnesium Alloy Sheet PAPER N00 11 of Session 3, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL I,
JOURNAL INST. OF METALS (ENGLAND) PART 8 INSTo MECHo ENGINEERS, 9 pages (1956)
pp 291-297 (April 1956)
Fatigue Curves were statistically
The distribution of fatigue cracks in treated taking into account the large scat-
clad and bare aluminum-copper-magnesium al- tering of test data, and correlation equa-
loy sheet specimens of various thicknesses tions between the stress amplitude and
was determined by examination of appropriate number of cycles were determined8
metallographic sections. The specimens
were stressed in fully reversed plain bend-

Contfd Metallographic Observations, etc.. SKANLEY, F.R.

2
ing at 22,000-50,000 lb/in for various num- On the Mechanism of Fatigue - A Discussion
bers of cycles up to and including fracture. of a Paper by Thompson, Wadsworth and Louat
It was found that the form and extent AIRCRAFT ENGINEERING (ENGLAND) VOL 29
of crack damage in the clad material was in- N0.335, PP H-12 (January 1957)
fluenced by the thickness of the specimen,
the stress and the number of cycles. In Discussion of a paper by Thompson,
some instances, the crack formations were Wadsworth and Louat, which appeared in
so characteristic that a reasonable estimate PHILOSOPHICAL MAGAZINE (February 1956).
of the fatigue history of a specimen could be
made by microscopic examination.

Contfd Metallographic Observations, etc... SHASHIN, M. YA.

Study of Fatigue Strength of Shot-Peened
With the bare material, however, Specimens Under Stresses Exceeding the
fatigue damage was found to be highly local- Fatigue Limit
ized, since the first cracks to appear
tended to be preferentially propagated HENRY BRUTCHER TRANSLATION N0.3145, 5 pages
(From VESTNIK MASHINOSTROENIYA, VOL. 32
to failure without the formation of addi- NO. 9,(1952) pp 57-60. Henry Brutcher,
tional cracks. In this case, microscopic Altadena, California (1956)
examination was of little value in assess- S-N curves representing non-strain-
ing the fatigue history. hardened specimens and specimens strain
Other phenomena associated with hardened at different speeds of the stream
fatigue failure were investigated, but and for different times. Optimum depth
these were not found to give so complete
of strain hardeningc

Cont'd Metallographic Observations, etc... SHHEIDER, BIALOBZHESKII, ZAGRITSENKO,

AND SEREBRENNIKOV
a picture of the progress of fatigue as Variation in the Fatigue Limits of Alum-
did metallographic examination* inum Alloys Under the Influence of
Anodic Oxidation (Russian)
METALLOVEDENIE I OBRABOTKA METALLOV, N0.4
pp 14-20 (April 1956)
Chromic-acid anodizing increases endur-
ance and strength,, Investigation on the
effect of sulfuric acid anodizing on fatigue
limits, and effect of oxide coating thick-
ness and polishing.
53 Tables, graphs, micrographs, diagrs.
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SHERMAN, E.G. AND H.D*KESSLER SIEBEL, E. AND M. GAIER
Investigation of the Heat Treatability Investigation of the Surface-Structure
of the 6% Aluminum-/i# Vanadium Titanium- Effect on Vibrational Fatigue Limit of
Base Alloy Metal Parts (German)
TRANSACTIONS ASM, VOL XLVIII, pp 657-676
(1956) (ASM-SLA CLASSIFICATION: J GENERAL, VDI ZEITSCHRIFT, VOL 98, N0.30
Q GENERAL, T.) pp 1715-1723 (October 1956)
The Ti-6 A1-4V alloy developed by the Effect of roughness depth and stress
Armour Research Foundation under govern- distribution for various materials. Sug-
ment sponsorship, illustrates the improve- gestion for consideration of the routine ss
ment in the endurance strength which can degree in strength calculation.
be realized from the use of duplex heat

Contfd Investigation of Heat Treatability.. SIGWART, H.

treatments. Endurance ratios greater Influence of Residual Stresses on the
than 0*55 were obtained in the heat treat- Fatigue Limit
ments evaluated by the authors. (This PAPER NO.6 of Session 3, INTERNATIONAL
material is being used in large quanti- CONFERENCE ON FATIGUE OF METALS, VOL I
ties in ordnance, airframe, and air- INST.MECH.ENGINEERS, 12 pages (1956)
craft engines.) Nature of residual stresses including
stresses due to local plastic deformation,
unequal heating, and unequal stress dis-
tribution. Some examples of residual
stresses. Effect of stresses on fatigue
properties.

SHISHKBf, MAKURIN AND MANILOVA SLAGG, J.H.

A Study of T-Connections Under Action Correspondence - An Unusual Fatigue Failure
of a Variable Load (Russian) METALLURGIA, VOL 54, No.325
SVAROCHNOE PROIZVODSTVO, NO.6, pp 11-13 p 260 (November 1956)
(June 1956)
In welded T-connections, the tensile Letter to the editor regarding article
strength of the joint can be made equal to by E. Wood, Metallurgia, June 1956. At-
that of the base metal even if the butted tributes failure of hammer head to trans-
ends have not been fused completely. In- verse crack formed during production or
vestigates the permissible extent of non- heat treatment of hammer head.
fusion in the joints as well as the effect
of an eccentricity in welded parts on the
strength of the connection„ Diagrs,table
_Photos. 6 ref.
SHKOL'NIK, L.M. SMITH, PARDUE AND VIGNESS
Effect of Arsenic on the Fatigue Strength
on Rails (Russian) The Mechanical Properties of Certain Steels
METALLOVDENIE I OBRABOTKA METALLOV, NO. 2 as Indicated by Axial Pynamic-Load Tests
pp 14-21 (February 1956)
SOCIETI FOR EXPERIMENTAL STRESS ANALYSIS,
Chemical composition, mechanical propertie PROCEEDINGS, VOL 13, NO.2, pp 183-197
and service life,(number of cycles before (1956)
fracture), of rails in fatigue tests. Co-
efficients of correlation characterizing The influence of strain rate on the
the effect of As, C, Mn, and P on service shape of the stress-strain curves for
life (before fracture) of rails. several steel materials was investigated.
Graphs, tables, photographs, diagram.
4 ref,
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SNIDEBMAN, A, STAUMEYER, J*E., G.E*NCRBMARK, W.H.MUNSE
The Concept of Strength from Goodman Diagrams AND N.MoNEWMARK
SESA PROCEEDINGS, VOL XIV, N0.1, (1956) Fatigue Strength of Welds in Low-Alloy
pp 145-154 Structural Steel
The usefulness of the modified Goodman CIVIL ENGINEERING STUDIES, STRUCTURAL
Diagram for the estimation of strength for RESEARCH SERIES NO. 122, (Reprinted from
designs involving cyclic loading is discussed. THE WELDING JOURNAL) UNIVERSITY OF ILLINOIS,
In particular, cases are considered where URBANA, ILL, (June 1956)5 see also
the preload is not constant and the fluctu- WEEDING JOURNAL, VOL 35, pp 298s-30?s
ating stress, whether constant or varying, (June 1956)
is additional to the preload stress. The Fatigue tests have been conducted on
concept of "actual stress lines" is devel- full-scale butt welds and fillet welds in
oped, and its application described. No low-alloy steel plates with the stress ap-
specific numerical examples are given.

Cont'd Fatigue Strength of Welds....

SOETE, W0
plied either parallel to or perpendicular
Is Low-Temperature Stress Relief Necessary? to the direction of welding. Several dif-
ferent steels meeting the ASTM designation:
WELDING RESEARCH ABROAD, NO.3, VOL 2, A 242 were used in this investigation to
P 4043 (July 1956) study the uniformity of results of differ-
ent steels meeting this specification.
The fatigue strengths of steels meet-
ing the requirements of ASTM designation
A 242 do not differ appreciably in spite
of the comparatively wide variations in
their chemical compositions.

SPAULDING, E.H, Cont'd Fatigue Strength of Welds....

Observations on the Design of Fatigue-Re- Fqrther, the presence pf the weld in
sistant and "Fail Safe" Aircraft the steel reduced the magnitude of the
variations between the average fatigue
PAPER NOo 2 Session S, INTERNATIONAL strengths of the different alloy steels.
CONFERENCE ON FATIGUE OF METALS, VOL II A comparison of the fatigue strengths
INST.MECH.ENGINEERS, 15 pages (1956) of joints in the low-alloy steels with the
also AIRCRAFT ENGINEERING (ENGLAND) VOL 28, fatigue strengths of similar joints prepared
N0.334, p 432 (December 1956) from A-7 steel with E7016 electrodes is
Accounts of service, comparative struc- also included in the paper.
tural weight analyses to show the advantages
of the type of design advocated, the use of

STBACHOTA, A.
Cont'd Observations in the Design, etc... Stepwise Flame Hardening of Gears (Czech)
STROJIRENSKA VYROBA, VOL 1, N0.4
programme-loading and failure dynamics are pp 21-26 (April 1956)
among the topics discussed. Many examples New Czech instrument has heating tip
of good detail design, and several pictures that fits down along each individual gear
to illustrate fail-safety of aircraft are tooth. The advantage is a very even depth
given. of hardening for crest and through each
tooth, while the core of the tooth still
remains tough. Method results in better
fatigue limits and less brittleness. Design
and operation features. Diagrs, photos,
microgrs, graphs. 15 ref.
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STARKER W.L., S.M. MARCO AND R.R.GATTS STRAUBE, E.
Statistical Evaluation of Variation in Influence of Microstructure of the Fatigue
Endurance Limit Among Several Heats of Strength of Wrought Aluminum Alloys (German)
Propeller Type Steel ALUMINUM, VOL 32, N0.8 (August 1956)
THE OHIO STATE UNIV. RESEARCH FOUNDATION, pp 476-479
(August 1956) WADC TR 55-483. Practical examples are adduced, showing
Samples from three heats of SAE 4330, the effect of microstructure and homogeneity
five heats of SAE 4340, and four heats of on the fatigue strength of heat-treatable
SAE 4350 aircraft quality steel were sub- aluminum alloys. The experiments which are
jected to Prot-type rotating bending en- reported have shown that it is advisable
durance tests. All specimens were heat to investigate by X-ray and ultrasonic scan-
treated to approximately Rockwell C 43 ning the microstructure and homogeneity of
hardness.

Cont!d Statistical Evaluation, etc,.. Cont'd Influence of Microstructure, etc...

Separate estimates of the arithmetic semifinished parts, particularly for
average and the standard deviation of the aircraft, which are subjected to consider-
endurance limit were determined for each able load cycling in service, prior to
heat from specimens selected parallel to incorporation into the finished structure.
the direction of mill rolling and from
specimens selected perpendicular to that
direction. An evaluation was made of
the extent of agreement between the data
obtained and a normal frequency distribu-
tion of the endurance limits of individ-
ual specimens. On the basis of normal

Gont'd Statistical Evaluation, etc.,, STUBBINGTON, C.A. AND P.J.E. FORSITH

distribution, confidence limits of 95$ Some Microscopical Observations on the
probability were established for each Effect of Fatigue and Corrosion Fatigue
estimate of average endurance limit. Stresses on DTD 683
The effects of various parameters on the ROYAL AIRCRAFT ESTABLISHMENT, TECHNICAL
average and on the standard deviation of NOTE NO.MET 211, (U.S.NACA REPORT NO.
specimen endurance limits were studied. N 38244 (February 1956)
These parameters included the carbon
content, anistropy, nonmetallic inclusion It has been found that DTD 683 shows
count, hardness, tensile strength, type of transcrystalline failure and slip band
fatigue fracture, and origin of heat. exulation when subjected to cyclic stress
Additional endurance tests were performed except under conditions of corrosion fat-
to compare the results of Prot-type tests igue when some intercrystalline cracking
with conventional endurance tests. has been observed.
Contfd Microscopical Observation, etc...
SVESHNIKOV, D.A. AND G.P.MASLENNIKOV
The tendency to produce intercrystalline
Machine for Fatigue Testing of Coiled corrosion fatigue failure was found to be
Cylindrical Springs and Wire (Russian) greatest in certain conditions of heat
treatment* Some observations have also
ZAVODSKAIA LABORATORIIA, VOL 22, NO.10 been made on the microstructure of DTD 683
pp 1245-1247 (October 1956) after various heat treatments and sugges-
tions are made for modification of exist-
Design and operation of the apparatus ing heat treatments to obtain improved
and interpretation of results. corrosion fatigue properties.

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 STOLEN, F.B., H.N.CUHMINGS AND W.C.SCHULTE TEMES, C.L.
Relation of Inclusions to the Fatigue Pro- Automatic Frequency-Control System for a
perties of High-Strength Steels High-Frequency Resonant-Type Fatigue
Testing Machine
PAPER NO. 4 of Session 5, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II PROCEEDINGS OF SESA, VOL 14, NO. 1 (1956)
INST.MECH. ENGINEERS, 8 pages (1956) An automatic frequency-control and
amplitude-control systen is described for
Fatigue life and strength of high-strength a machine used to fatigue test cantilever
steels, heat-treated to a given ultimate specimens at their resonant frequencies;
tensile strength, depend largely on the size the controller enables testing over a
and location of inclusions. resonant-frequency range of 500 to 2000

TAYLOR, J. Cont'd Automatic Frequency-Control, etc.

Fatigue Loading Actions on Transport Aircraft cycles per second and maintains constant
PAPER NO.4 of Session 8, INTERNATIONAL stress amplitude during the progressive
CONFERENCE ON FATIGUE OF METALS, VOL II decrease in resonant frequency resulting
INST. MECH. ENGINEERS, 10 pages (1956) from fatigue.
also AIRCRAFT ENGINEERING (ENGLAND) VQL 28, The machine holds the stress ampli-
NO.334, P 432 (December 1956) tude within about 1$, and a rate of drop
of over 5.5 cycles/second/second has been
Paper presented at the International followed satisfactorily.
Conference on Fatigue of Metals, London
(England) 1956. The fatigue loading effect
of gust, mechanical and aerodynamic vibra-
Cont'd Fatigue Loading Actions...
THOMPSON, N.
tions, jet noise, ground roughness and air
turbulence were measured; the procedures and Experiments .Relating to the Basic Mechanism
the instruments used were discussed. of Fatigue
It is demonstrated that the gust spectrum
is much more severe in climb and descent PAPER NO. 3 of Session 6, INTEENATIONAL
than in cruise. The permissible levels of CONFERENCE ON FATIGUE OF METALS, VOL II,
mechanical vibrations and aerodynamic buf- INSTJ*ECH.ENGINEERS,6 pages,4 plates (1956)
feting are dealt with empirically; only Stages in the development of a fatigue
preliminary results are avilable for jet crack in a single crystal of copper and
noise. Some work has been done on the fat- in polycrystalline nickel.
igue effect of ground loads.

TEED, P.L. (see also Litherland-Teed, P.) THOMPSON, N.

The Aircraft Fatigue Problem Experiments Relating to the Origin
AEROPLANE, VOL 91, NO.2351 pp.464-465 of Fatigue Cracks
(September 21, 1956) PAPER from FATIGUE IN AIRCRAFT STRUCTURES,
Introductory remarks to and comments ACADEMIC PRESS, pp 43-61 (1956)
on the papers presented at the joint con- Summary of results of investigations
ference on the fatigue of metals held in of copper and of aluminum on the basic
London, September 10-14, 1956 by the Insti- mechanism of fatigue. Similarities in
tution of Mechanical Engineers and The crack formation and crack propagation in
American Society of Mechanical Engineers. the two metals.
8 ref.

57
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THOMPSON, WADSWORTH AND LOUAT TOHBEY, M.N. AND G.B.GOHN
The Origin of Fatigue Fracture in Copper Statistical Treatment of Fatigue Data
PHILOSOPHICAL MAGAZINE, VOL I, SERIES 8, (Digest of "A Study of Statistical Treat-
NO.2, pp 113-126 (February 1956) ments of Fatigue Data11)
ASTM PREPRINT N0.70, 25 pages(l956), and
Polycrystal and single crystal speci- METAL PROGRESS, VOL 70, pp 140 and 142
mens were tested in pushpull at 1000 cps. (October 1956)
It was shown that the fatigue crack start-
ed in a slip band inside a single grain. Data on more than 1000 specimens; a study
An electropolishing technique showed of statistical treatments rather than a
changes in the character of the slip band study of fatigue.
after 5 per cent of the life had expired. The results of reversed-bending fatigue
Diag, graph, table* 10 ref. tests on two lots of commercial Grade A
(5% tin) phosphor-bronze strip are presented,

TIPLER, H.R, AND P.G.PORREST Cont*d Statistical Treatment of Fatigue, etc

The Fatigue Behavior of Iron With Inter- with 48 values being given for each deflec-
granular Weakness tion level. The machine used was a special
PAPER NO.10 of Session 5, INTERNATIONAL 24-specimen sheet-metal fatigue setup of the
CONFERENCE ON FATIGUE OF METALS, VOL II, fixed deflection type. Tests were run at
INST.MECH.ENGINEERS, 5 pages (1956) 80 to 85 F and at a speed of 2000 cpm.
The distribution of cycle life were
Tests reveal an unusual type of fitted by log-N, extreme value, and log-
fatigue failure in iron having exception- log-N distributions, showing that the type
ally weak grain boundaries. of distribution depends on the deflection
level. The use of response curves is sug-
gested.

TURNER, F. TSOBKALLO,S.O.
Aspects of Fatigue Design of Aircraft Experimental Determination of the Properties
Structures of Incomplete Elasticity of Spring Materials
(Russian)
PAPER from FATIGUE IN AIRCRAFT STRUCTURES, FIZIKA METALLOV I METALLOVEDENIE, VOL 2
ACADEMIC PRESS, pp 323-346. NO.l, pp 149-159 (1956)
Statistical approach is emphasized Present-day methods of measuring elastic
in design problems relative to fatigue fatigue and elastic limit. Relation of de-
and static failure. formation to time in testing for elastic
17 ref. fatigue. Role of intermediate loads.
Graphs, Diagrams. 26 ref.

UNKSOV, E.P. UZHBC, G.V.

Fatigue Endurance of Large Parts With Elec- Mechanical Aspect of Size Effect on
tric-Slag Welds Fatigue of Metals
PAPER NO. 8 of Session 9, INTERNATIONAL PAPER NO.17 of Session 2, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL III CONFERENCE ON FATIGUE OF METALS, VOL I
INST.MECH.ENGINEERS, 8 pages, 4 plates (1956) INST.MECH.ENGINEERS, 6 pages (1956)
Fatigue endurance of welded joint with- Discontinuity of the material itself
out heat treatment and with reinforcement is not likely to decisively affect the
left intact is lower than that of unwelded fatigue strength under a size increase.
samples. Heat treatment increased endur-
ance by 30 to 35#. Mechanical treatment
with no reinforcement was extremely favor-
able.
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VALLURI, S.R. VIDAL, G, F.GIRARD AND P.LANUSSE
Some Observations on the Relationship An Apparatus for Testing Metals to
Between Fatigue and Internal Friction Failure Under an Alternating High-Frequency
Stress (French)
NACA TN 3755 (September 1956) 42 pages
C.R.ACADEMIE SCIENCE (PARIS) VOL 242 No.8
Results are presented of an investiga- pp986-988 (February 20, 1956)
tion made to determine the internal friction
and fatigue strength of commercially pure The specimen is mounted on a large im-
1100 aluminum under repeated stressing in mobile mass, being connected to this by a
torsion at various temperatures and stress metal tube. A strain gage is attached to
levels in an effort to find if there exists the tube, and the output drives the top
any correlation between internal friction of the specimen electromagnetically. The
and fatigue characteristics. whole system is therefore resonant at the fun
Diagrs., photos.,. tabs. damental frequency of the specimen;this is
about 6 kc/s for the specimena used.
VARGA, ISTVAN VITOVEC AND LAZAN
Fatigue Tests of Aluminum Allovs and Creep, Rupture, and Notch-Sensitivity
Their Welded Joints (Hungarian; Properties of S-816 Alloy up to 1650 F
Under Fatigue and Static Stress
fcOHASZATO LAPOK, VOL 11. NO.8, PAPER from SYMPOSIUM ON METALLIC MATERIALS
PP 377-380 (August 1956) FOR SERVICE AT TEMPERATURES ABOVE 1600 F.
AMERICAN SOCIETY FOR TESTING MATERIALS
Factors effecting fatigue. Conclusions pp 69-88; discussion p 89 (1956)
concerning optimum welding materials.
Roles of creep and fatigae as design
factors. Relation of notch sensitivity

VIDAL, GEORGES Cont*d Creep, Rupture and Notch-Sensitivity

Hot Fatigue Resistance of Titanium Alloys to loading conditions, with particular

to Repeated Tensile Stress (French) reference to temperature and ratio of
alternating-to-mean stress.
REVUE DE METALLURGY, VOL 53, N0.10, Micrographs, graphs. 11 ref.
PP 767-774 (October 1956)
The resistance to hot fatigue with
repeated tensile stress between 68 F and
932 F for Cr-Fe-Ti, Cr-Al-Ti, and Fe-Al-Ti
alloys.

WADE, A.R. AND PoCSOOTEHUIS

WALKER, P.B.
Very-High-Speed Fatigue Testing
Aircraft Fatigue From the General
PAPER NO.5 of Session 4, INTERNATIONAL Engineering Standpoint
CONFERENCE ON FATIGUE OF METALS, VOL II
INST. MECHo ENGINEERS, 11 pages (1956) PAIER NO. 6 of Session 8, INTERNATIONAL
Choice of type of high-speed machine; CONFERENCE ON FATIGUE OF METALS, VOL II
calculation of stress, fatigue tests. INST. MECH. ENGINEERS, 7 pages (1956)

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WADSWQRTH, N.J
WALKER, P.B.
Some Observations on Corrosion and the
Fatigue Testing of Aircraft in Water Tanks Aircraft Strength Testing (Aircraft
Design Philosophy)
RAE (GREAT BRITAIN) (August 1956) 10 pages
(RAE TN MET. 2246) JOURNAL OF THE ROYAL AERONAUTICAL
SOCIETY (May 1956) pp 301-330
The corrosive effects of water upon
fatigue life of pressure cabins when tested
in water, and corresponding effects in
service are reviewed. It is concluded
that fatigue life is reduced by mild forms
of corrosion in both cases.

Cont'd Observations on Corrosion, etc. WAIXER, P.B.

It is suggested that until more is known Plastic Pressure Cabins
auxiliary tests should be made during all AIRCRAFT ENGINEERING, VOL 28, NO.331
tank tests of airplanes, and that all parts PP 322-324 (September 1956)
of the tank should be painted. It is con- This paper brings out the technical
sidered that, while local corrosive effects issues involved in the substitution of
in the tank may have to be tolerated, reinforced plastics for aluminum alloys
measures should be taken to prevent cor- in the pressure cabins of aircraft. The
rosion on an extended scale. conclusion is development of plastics for
Diagrams. this purpose is not likely to be profit-
able. Plastics owe their strength mainly

WADSWORJH, N.J. Cont'd Plastic Pressure Cabins

to embedded fibres requiring plastic bond-
The Fatigue Strength of Aluminum Alloy Sheet ing material which adds weight without con-
to Specification DTD 546, Using Specimens tributing to strength. Since fibres can
of Two Different Sizes carry stress in only one direction, complex
stress fields require two sets of fibres
RAE TECHNICAL NOTE MET. 237 (April 1956) laid at right angles. One set does not
assist the other in carrying the load.
The effect of specimen size on the fat- While it is true that plastics are now being
igue strength of specimens cut from 16 made which are, for all practical purposes,
gage Alclad DTD 546 sheet was investigated completely isotropic, a three dimensional
at an endurance of HP cycles. system does not exist* Plastics do have
Specimens 1 inch and 0.3 in. wide with the advantage of higher compressive strength

Cont'd Plastic Pressure Cabins

Cont'd Fatigue Strength of Aluminum Alloy...
and structural stability but do not meet
stiffness requirements. The thickness
and without a central hole (giving an el- necessary is insufficient to eliminate string-
astic stress concentration factor of 2.44) ers and does not give a covering any lighter
were tested in a Haigh machine0 The than aluminum alloy. Plastics are less
strength reduction factor due to the hole suited than aluminum and steel to deal with
was 1.8 in the large specimens and 1.48 in stress raisers and insufficient testing has
the smalleo There was little or no dif- been done to prove conclusively that they
ference in the strength of the plain spec- have better fatigue and creep properties.
imens. They have, for small structural components
the special advantages of transparency,
heat insulation and noise suppression.
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WALKER, P*B. WALTER, G.H.
Pressure Cabin Fatigue Fatigue in Plain Bearings
AIRCRAFT ENGINEERING, VOL 28
pp 11-19, (January 1956) INTERNATIONAL CONFERENCE ON FATIGUE OF
METALS, SPONSORED BY THE INST* MECH.
Abbreviated version of the author's ENGINEERS in cooperation with the ASME
lecture, "Fatigue of Aircraft Pressure Cabins1*, PAPER No. 4 of Session 7 (September 1956)
presented in Los Angeles in June 1955. How-
ever, certain parts have been revised and
brought up to date» It is a survey of the
problem and test methods.
Fatigue tests undertaken on a complete
aircraft as part of the Comet accident in-

Cont'd Pressure Cabin Fatigue WARD, R.G.

Vestigation to determine fatigue life of A Comparison of the Fatigue Properties
pressurized cabin. Theory presented of of the High-Strength Aluminum-Copper-Zinc
stress patterns in the skin of a pressure Alloys with the Aluminum-Copper Duralumin
vessel with various-shaped apertures. The Type Alloys
type of aircraft loading contributing most to
fatigue damage of the fuselage are considered ROYAL ACADEMY, ENGINEERING (GREAT BRITAIN)
to be: (a) cabin pressure, (b) transfer of (REA TN MET 244, 2? pages (April 1956)
load from undercarriage to wing and vice- Using data from British and American
versa, and (c) gust loading on wing. sources for round specimens in reversed
A Comet fuselage was tested at RAE in bending, an attempt is made to compare the
a water tank from which extended the wings. fatigue properties of the complex zinc-

Cont'd Pressure Cabin Fatigue Cont'd Comparison of Fatigue Properties, etc

Cabin pressure was applied by pumping more bearing aluminum alloys as typified by DTD
water into the water-filled fuselage; the 363, DTD 683, and 75S, and the simple alum-
wing lift and gust cycles were applied each inum-copper alloys such as DTD 150, DTD 364,
"flight" by hydraulic jacks until a fatigue and 14S. Under all conditions of testing
failure occurred at a window corner. The the performance of the high-strength alloys,
fuselage was repaired to permit additional if judged by the ratio of alternating stress/
testing. UTS, is inferior to that of the older alum-
Details are presented on the Comet test inum-copper alloys, and it is emphasized
installation and on the new larger tank that designing to static-strength require-
used for testing the Britannia. ments would result in a lower fatigue life
8 diagrams, 23 photographs,, for structures of the high-strength alloys.
Diagrs., tabs.

WALLACE, W.P. AND R»H. WALLACE WATKINSON, J.F.

Zirconium Fatigue Tests The Influence of Some Surfaces Factors
on the Torsional Fatigue Strength of
LIGHT METAL AGE, VOL 14, pp 24-25 Spring Steels
February 1956 PAPER NO.5 of Session 5, INTERNATIONAL
CONFERENCE ON FATIGUE OF METALS, VOL II,
Rotating beam fatigue tests on Zircaloy INST. MECH. ENGINEERS, 16 pages (1956)
2 and flexure fatigue tests on sheet crystal 4 Plates
bar Zr. ^ Snof-peening improves the fatigue
Graphs, diagram, micrographs. strength of quenched and tempered spring
steel in both the polished and the heat-
treated conditions. Decarburization re-
duces the residual stresses present after
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HECK, R. WELLINGER, K. AND P. GIMMEL
The Fatigue Problem in Welded Construction The Effect of Heat Treatment Notches
and Shape of Specimen on the Fatigue
PAPER NO. 5 of Session 9, INTERNATIONAL Strength of Butt *Welds in Pipe Steels
CONFERENCE ON FATIGUE OF METALS, VOL III,
INSTo MECH* ENGINEERS, 11 p, 4 plates (1956) WELDING RESEARCH ABROAD, NO. 3, VOL 2,
Some general considerations; fatigue in PP 36-39, (July 1956)
welds and joints; metallurgical aspects and
welding processes; residual stresses, ser-
vice experience and failures.

WEIBULL, W. WELLS, E.W.

Effect of Crack Length and Stress Amplitude Fatigue Loadings in flight Loads in the
on Growth of Fatigue Cracks Fuselage and Nose Undercarriage of a
Varsity.
FFA REPORT 65, THE AERONAUTICAL RESEARCH
INSTITUTE OF SWEDEN (February 1956)(English) ARC TECHNICAL REPORT 18671, C.P. NO. 287,
MINISTRY OF SUPPLY, AERONAUTICAL RESEARCH
The growth rate was strongly influenced COUNCIL, LONDON, ENGLAND (1956)
by small variations in the mean stress am-
plitude of an interval. For the tested Flight tests have been made on a Varsity
specimens the rate of growth seemed com- to obtain data on the fatigue loads in the
pletely independent of the crack length. fuselage and the nose undercarriage.

WEIBULL, W. Cont!d Fatigue Loading in Flight Loads, etc.

Scatter of Fatigue Life and Fatigue Strength The data are tabulated in terms of the
in Aircraft Structural Materials and Parts number of load ranges of a given magnitude
PAPER from FATIGJJE IN AIRCRAFT STRUCTURES, occurring during various ground and flight
ACADEMIC PRESS, pp 126-145 (1956) conditions*- An estimate is made of the loads
in a typical operational training flight to
Fatigue properties are described by show the relative importance of the various
S-N curves. Procedure for converting conditions<, A relationship is established
life distribution into strength distribution between the fuselage loads and the accelera-
is discussed. tions at the aircraft e.g. when flying in
7 ref. turbulence; this enables the results from
the flight tests to be linked to operational
data obtained on gusts.

WEIBULL, W. WERREN, FRED

Fatigue of Sandwich Constructions for Air-
Static Strength and>Fatigue Properties of craft. Aluminum Facing and Aluminum
Unnotched Circular 75S-rT Specimens Subject- Honeycomb Core Sandwich Material Tested
ed to Repeated Tensile Loading in Shear
FFA MEDD 68, 29 pages (June 1956) U.S. DEPARTMENT OF AGRICULTURE, FOREST
PRODUCTS LABORATORY, REPORT NO. 1559-H,
p. 11 (March 1956)
Determination of Shear Strength in the
direction of different axes.

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WERREN, FRED WIENE, P.E.
Supplement to Fatigue Tests of Glass-Fabric- Effect of Annealing (650°C) on Bending
Base Laminates Subjected to Axial Loading Fatigue of Large Welded Test Pieces
U.S. DEFT. OF AGRICULTURE, FOREST PRODUCTS WELDING JOURNAL, VOL 35, PP 26ls-264s
LABORATORY, REPORT NO. 1823-B, 26 p (Aug.1956) (May 1956)
Direct-stress tests at 0, 15, 30 and 45 Danish experiments on reversed bending
degrees to the warp direction. Stress fatigue of 1-meter-long double-fillet T-
was applied at a frequency of 900 cycles welds in approximately ln-thick carbon steel
per minute at zero mean stress on both un- plates are reported. Annealing at 650°C
notched and notched specimens. (1200°F) resulted in a 20# increase in en-
durance limit.

WEVER, F. Contfd Effect of Annealing etc...

Fatigue Properties of Steel at High Three possible reasons for the improvement
Temperatures are listed:
PAPER NO. 6 of Session 4, INTERNATIONAL 1. Relief of residual stress.
CONFERENCE ON FATIGUE OF METALS, VOL II, 2. Tempering of hardened areas in
INST. MECH. ENGINEERS, 7 P, 2 plates (1956) the transition zone.
Fatigue strength and mean stress; stress 3. Removal of hydrogen.
fracture times for static and alternating
loading; notch effect and surface hardening;
metallographical investigations.

WHALEY, RICHARD E, M.J.MC GUIGAN, JR., WIENE, P.E.

AND D.F.BRIAN Full-Scale Fatigue Tests of Diesel Engine
Fatigue-Crack-Propagation and Residual- Elements
Static-Strength Results on Full-Scale INST. OF MARINE ENGINEERS, TRANSACTION,
Transport-Airplane Wings VOL 68, pp 39-46; discussion pp 47-59
(March 1956)
NACA TN 3857, 57 pages (December 1956)
Rotary-bending tests; springs; cast iron;
Results are presented of fatigue-crack notch sharpness; tension-compression tests;
propagation during fatigue tests on the crankshafts; piston rods; shrunk joints;
wings of F-46 airplanes. Results are also welded elements.
presented of the residual static strength Photographs, graphs, diagrams, tables,
of these wings after fatigue test. micrographs. 3 ref.

WILLIAMS, L.S.
Contfd Fatigue-Crack-Propagation, etc.
Stress-Endurance of Sintered Alumina
The propagation curves along with an BRITISH CERAMIC SOCIETY TRANSACTIONS, VOL 55,
explanation of the crack growth are pp 287-312 (May 1956)
presented for each wing. Curves also
show the trends that occur with changing Fabrication of test-pieces; design
load levels. The loss in static strength and operation of high-temperature centrif-
is also shown and is compared with the cal- ugally-loaded cantilever fatigue machine;
culated strength and the results of small correlation between fatigue, delayed frac-
specimen tests0 ture, and bend strengths.
Diagrs0, photos„, tabs. Photographs, micrographs, tables,
diagram. 16 ref.

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WOOD, E. WOODWARD, A.R., K.W.GUNN AND G. FORREST
An Unusual Fatigue Failure The Effect of Mean Stress on the Fatigue
of Aluminum Alloys
METALLURGIA, VOL 53
pp 278-279 (Oune 1956) PAPER no. 10 of Session 2, INTERNAITONAL
CONFERENCE ON FATIGUE OF METALS, VOL I,
A short note on the fatigue failure of a INST. MECH. ENGINEERS, 14 pages (1956)
3 lb. 0.55$ carbon steel, ball-peen hammer Fatigue properties of seven alloys;
after 5 yrs service. Fracture occurred stress-mean stress diagrams; application
3/4 in. from the selectively hardened face, of several theories to behavior of the
and was caused by general overheating of alloys tested.
the hammer stamping, and local burning.

WOOD, E. YAMANOUCHI, HIROSHI AND TASKESHI INUKAI

Fatigue of Carbon Steel by Ultrasonic Flaw-
Correspondence - An Unusual Fatigue Failure Detection Method (in English)
METALLURGIA, VOL 54, NO.325 CASTINGS RESEARCH LABORATORY REPORT NO. 7
p. 260 (November 1956) WASEDA UNIVERSITY, pp 55-53 (1956)
The values of the ultrasonic attenua-
Reply to Slagg's letter regarding tion constant in mild steel under fatigue
Wood's article (Metallurgia, June 1956) test vary with repeated stress intensity
and stress cycle. These values increase
in proportion to stress cycle, but a tran-
sition point exists on the curve.

WOOD, W.A. ZAITSEV, AJt.

Failure of Metals Under Cyclic Strain Methods for the Analysis of Fatigue Cracks
PAPER NO. 4 of Session 6, INTERNATIONAL (Russian)
CONFERENCE ON FATIGUE OF METALS, VOL II, ZAVODSKAIA LABORATORJIA, VOL 22, NO. 4
INST. MECH. ENGINEERS, 6 pages (1956) pp 472-478 (March 1956)
An interpretation of the fatigue Survey of methods; nature, structure,
.property is based on study of the struc- and causes of11fatigue cracking, including
tural changes peculiar to fatigue. "brittle slip , zone differences, and micro-
cracks .
Micrographs, photographs. 6 ref.

WOOD, W.A.
Mechanism on Fatigue
PAPER from FATIGUE JN AIRCRAFT STRUCTURES
ACADEMIC PRESS, pp 1-19 (1956)
Observations of fatigue deformation
were interpreted as proceeding from fine
slip as opposed to coarse slip and that
pure fatigue may impose considerable plastic
strain without, progressive strain hardening.
Tests on copper in alternating torsion,
showed that a total of non-hardening plas-
tic strain could be imposed in fatigue that
would be impractical in static deformation.
18 ref.
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