1
NBSIR 74-465

Shear and Tension-Bending Fatigue

Test IVIethods for Tlireaded

Airframe Fasteners

D.J. Chwirut, D. E. Marlowe, and J. S. Steel

Engineering Mechanics Section

Mechanics Division

Institute for Basic Standards

National Bureau of Standards

Washington, D. C. 20234

September 1974

Prepared for

Aero Structures Department

Naval Air Development Center

Department of the Navy

Warminster, Pennsylvania 18974

NBSIR 74-465

SHEAR AND TENSION-BENDING FATIGUE

TEST METHODS FOR THREADED

AIRFRAME FASTENERS

D.J. Chwirut, D. E. Marlowe, and J. S. Steel

Engineering Mechanics Section

Mechanics Division

Institute for Basic Standards

National Bureau of Standards

Washington, D. C. 20234

September 1974

Prepared for

Aero Structures Department

Naval Air Development Center

Department of the Navy

Warminster, Pennsylvania 18974

U. S. DEPARTMENT OF COMMERCE, Frederick B. Dent. Secretary

NATIONAL BUREAU OF STANDARDS, Richard W. Roberts. Director

CONTENTS

Page

1. INTRODUCTION .......... 1

2. PROGRAM 2 2.1 Single Shear Fatigue 2 2.2 Double Shear Fatigue ..... 2 2.3 Tension-Bending Fatigue .... 2

3. TEST METHOD DEVELOPMENT 2 3.1 Single Shear 2 a. Specimens 2 b. Test Equipment 2 c. Test Procedure 3

d. Test Results 3

3.2 Double Shear 4

a. Specimens ..... 4

b. Test Equipment ^

c. Test Procedure ....... 5 d. Test Results 6

3.3 Tension-Bending ..... 7 a. Specimens ....... 7 b. Test Equipment 7 c« Test Procedure ............ 8

d. Test Results 8

4. CONCLUSIONS ............. ..... 9

5. CLOSURE 10

i

SHEAR AND TENSION- BENDING FATIGUE TEST METHODS FOR

THREADED AIRFRAME FASTENERS

Daniel J. Chwlrut, Donald E. Marlowe, and James S. Steel*

ABSTRACT

Fatigue test methods for threaded airframe

fasteners loaded in other than direct tension are described. The types of loading considered are single shear, double shear, and tension-bending.

The test fixtures used in these tests are described. Results of tests on lots of fasteners

from different manufacturers indicate that

fasteners considered identical on the basis of

direct tension procurement tests exhibit different fatigue life characteristics when loaded

in shear and/or tension-bending. Thus the test

methods described herein may be of future value

as procurement tests for airframe fasteners.

Key words: Airframe fastener; double shear;

fatigue; single shear; tension-bending; test

methods.

1. INTRODUCTION

Current military procurement practices require only a limited amount

of fatigue testing to verify the quality of threaded airframe fasteners.

In the case of high strength tension bolts such as the 160,000 Ibf/in^

(11.0 X 10^ N/m^) and 180,000 Ibf/in^ (12.4 x 10^ N/m^) series, verification of fatigue resistance is based upon axial tension fatigue tests.

Under this type of loading, failures are expected in the threaded section

of the fastener.

In service, however, few fasteners experience simple tension. Most

experience a combination of loads including single shear, double shear,

and/or bending. Under these conditions fatigue failures have occurred

in the shoulders of fasteners from lots which passed the tension fatigue

acceptance tests. This suggests that the standard axial tension fatigue

test [1] is an inadequate measure of the fatigue resistance qualities of

fasteners in service.

The investigation reported herein was undertaken to establish standard fatigue test methods for airframe fasteners loaded in shear and

combinations of tension and bending. This work was performed at the

National Bureau of Standards under the sponsorship and with the financial

assistance of the United States Navy, Naval Air Development Center,

Warminster, Pennsylvania.

*Present address. Fire Technology Division,

1

NBS
2 . PROGRAM

Three different test conditions were investigated in this study.

They were designed to produce the type of failures which have occurred

in fasteners in service.

2.1 Single Shear Fatigue

The single shear test was designed to produce the type of failure

experienced by flush head fasteners when used in a single lap joint

configuration. The prying action imparted to the head of the fastener

causes a catastrophic failure at the fastener shoulder, i.e. complete

separation of the head from the shank of the fastener.

2.2 Double Shear Fatigue

Because of difficulties in the testing of fasteners in single shear,

the double shear test was designed. In this test, the prying action on

the head of the bolt causes failure initiation at the shoulder of the

fastener near one joint interface, but catastrophic failure cannot occur

since the shank can still carry the load at the other interface.

2.3 Tens ion-Bending Fatigue

The tension-bending test was designed to simulate the effects of

induced bending in nominally direct tension loading configurations.

Whereas fasteners loaded in direct tension should fail in the threads,

the introduction of some bending causes the head-to-shank fillet to

become the critical crack location and the fastener fails catastrophically

with the head separating from the shank.

3. TEST METHOD DEVELOPMENT

3.1 Single Shear

a. Specimens

Single shear fatigue testing was conducted using 0.25 in ^0.6 cm)

diameter, 85,000 Ibf/in (5.86 x 10^ N/m^) tensile strength 100 flush head

fasteners with steel washers and self locking nuts. These fasteners had

Phillips wrenching recesses.

b. Test Equipment

The testing program was conducted in two electrohydraulic fatigue

machines. The rated capacities of these machines are 10,000 Ibf (44,480 N)

and 50,000 Ibf (222,400 N)

.

The single shear test fixtures are shown in figures 1 and 2. Three

sets of fixtures were designed, with plate thicknesses as indicated in

figure 2. In each set, the thickness of plate A supporting the bolt head

is half the thickness of plate B. When load is applied to this eccentric

2
joint, most of the flexure occurs as bending of plate A and thus loads

the head of the bolt in a prying action. The total thickness of the two

plates was approximately equal to the fastener grip length.

Spaulding [2] has shown that the stress concentration in a flush

head fastener due to pinching by a countersunk plate is essentially

constant for ratios of plate thickness to countersink depth greater than

approximately 1.2. Since it is desirable to have this stress concentration constant for tests on all lengths of fasteners, a minimum thickness

of plate A of approximately 1.2 times the fastener head height is established. As previously mentioned, to insure the proper loading on the

bolt head, plate B should be twice as thick as plate A. Thus the shortest

fastener that can be tested must have a grip length of at least 3.6 times

the head height.

All plates were 3 in (7.6 cm) wide and 17.6 in (44.8 cm) long. This

length is the maximum compatible with the crosshead clearance of the

10,000 Ibf (44,480 N) capacity fatigue machine.

The 100° countersink was machined to a depth such that the head of

the fastener was flush with the surface of the shear plate. The plates

were AISI 4130 alloy steel hardened to about Rockwell C45.

c. Test Procedure

The test fastener, washer, nut, and fixtures were washed with acetone or were vapor degreased with trichloroethylene prior to testing.

This is necessary to remove any lubrication on the bolt which may cause

an increase in fastener fatigue life [3].

A nominal torque of 10 Ibf-in (1.1 N-m) was applied to the fastener

and nut before each test. This torque was large enough to draw the

plates together but was judged not large enough to increase the fatigue

life of the fasteners through preload as noted by Mordfin [4].

The maximum cyclic loads were taken as percentages of the single

shear static strength of test fasteners. Loads were generally in the

range of 40 to 90 percent of the static strength. The minimum cyclic

load was 10 percent of the maximum. All tests were conducted at 10 Hz.

Specimen failure, as indicated by the inability of the fastener to

sustain the test load, caused automatic machine shutdown.

d. Test Results

Tests on two different lengths of 0.25 in (0.6 cm) diameter, 100°

flush head fasteners indicated that the stress concentration factor in

the fastener caused by the countersunk shear plate was not essentially

constant as predicted, indicating that Spaulding's results [2] may not

be applicable to this particular loading configuration. Therefore, the

single shear fatigue life of such fasteners is not independent of

fastener length. For example, at one test load, all 8 of the longer

3
fasteners failed between 56,000 and 125,000 cycles of load, whereas 42 of

the 44 shorter fasteners had not failed after 150,000 cycles of load.

When load is applied to the single shear lap joint, the plates bend

due to the eccentricity of the joint configuration. In tests on the

longer fasteners, because the plates are thick, this bending was slight

and most of the load was transferred to the test fastener in shear of the

bolt shank and prying of the bolt head. In tests on the shorter fasteners, the thinner plates flexed considerably, and a larger portion of the

load was carried by the test fastener head in direct tension, which is

apparently not as critical a type of loading as the prying of the head

in shear. . —

Because of this fixture limitation, it was decided that a symmetric

double shear test configuration might yield a more consistent transfer of

load to the test fastener, and provide a test method which would be

independent of fastener length,

3.2 Double Shear

a. Specimens

The double shear test method was developed using 0,25 in (0,6 cm)

diameter, 85,000 Ibf/in^ (5.86 x 10^ N/m^), 100° flush head fastener with

steel washers and self locking nuts, and four sizes of 160,000-180,000

lbf/in2 (11.0 X 10 -12.4 x 10^ N/m^) series, 100° flush head fasteners

with steel washers and self locking nuts. Both types of fasteners tested

had Phillips wrenching recesses. A program to determine the ability of

the test method to distinguish between lots of fasteners from different

manufacturers was undertaken using three sizes of 160,000-180,000 Ibf/in^

(11,0 x 10^-12.4 x 10^ N/m^) series, 100* flush head fasteners obtained

from U, S. Navy supply depots.

b. Test Equipment

This testing program was conducted in the same two testing machines

described previously.

The double shear test fixtures are shown in the photograph in

figure 3 and schematically in figure 4. The side plates of the joint

are simulated by the small inserts as shown in figure 5.

Head angle measurements on test fasteners indicated that most fasteners have head angles a few minutes of arc less than the nominal 100 degrees.

In order to insure loading on the fastener head and precipitate shoulder

failures, a 98 - 99 degree countersink angle was used. Complete engineering drawings for these fixtures are given in Appendix A.

As mentioned earlier, failure of the shoulder in a double shear test

does not cause catastrophic failure of the test joint since the shank can still support the load. However, to decrease the scatter in fatigue life

4
data, it was decided to consider initiation of shoulder cracking as failure of the fastener. To detect this failure, a fatigue crack initiation detector was developed [5]. This device is shown installed on the

test fixtures in figure 3.

A dc linear variable differential transformer (DCDT) is mounted as shown in figure 3 with the armature secured to one test fixture and the

coil to the other fixture. The voltage output of the DCDT is thus

directly related to the relative positions of the two test fixtures, and

the output form and frequency approximate the waveform and frequency of

the mechanical forcing function (applied loads). A block diagram of the

equipment comprising the crack initiation detector is shown in figure 6.

The dc voltage supply powers the DCDT and provides the bias voltage to

the circuits of the peak amplifier. The voltage output of the peak

amplifier is proportional to the signal from the DCDT when the test

fastener is experiencing the maximum cyclic load. The peak amplifier

output is recorded on one axis of an X-Y recorder. A circuit diagram

for the peak amplifier detector circuit is shown in figure 7. It

should be noted that the first stage amplifier gain, and therefore the

total detector gain, is a function of operating frequency because of

the presence of capacitor CI. As a result, the fatigue test frequency

must remain constant for the duration of the test.

r The signal to the other axis of the X-Y recorder is proportional to

the number of load cycles applied to the specimen. The record for each

test is a plot of number of cycles versus change in relative position of

test fixtures at maximum load. As a fatigue crack is initiated and

propagates through the fastener, changes in the relative position of the

test fixtures of 0.00002 in (0.0005 mm) can be resolved. Experience

gained from approximately 550 tests using this system indicates that

changes of 0.0001 in (0.0025 mm) in fixture position correlated with

crack initiation in the fillet of the bolt.

c. Test Procedure

The test fastener, washer, nut and test fixtures were washed with

acetone prior to testing. The tightening torque was 5, 15, 75 and 205

Ibf-in for 0.190 (No. 10), 0.250, 0.375, and 0.500 in (0.5, 1.7, 8.5

and 23.1 N-m for 0.483, 0.635, 0.952, and 1.27 cm) diameter fasteners

respectively. For tests on fasteners longer than those for which the

fixtures were designed, a solid stainless steel spacer was inserted

between the washer and test fixtures.

The maximum cyclic loads were taken as percentages of the double

shear static strength of the specimen. Loads were generally in the

range of 40 to 70 percent of the static strength. For each test the

minimum cyclic load was 10 percent of the maximum. Cyclic speeds

ranged from 5 - 10 Hz.

5
Fatigue failure was defined as initiation of a crack at the fastener

shoulder, and was detected by the fatigue crack initiation detector.

This device was connected to the error detector interlock system of the

testing machine through a meter relay to shut down the machine shortly

after crack initiation.

d. Test Results

Using the 85,000 Ibf/in^ (5.86 x 10^ N/m^) series fasteners, a series

of double shear development tests were run to determine the optimum

combination of fixture variables for reproducing service failures. The

parameters considered and optimum values obtained are as follows:

Hardness of side plate material R 40-50

under fastener head ^

Countersink angle 98-99 degrees

Body hole size D + 0.010 inch (D + 0.025 cm)

minimum

Fastener orientation no effect

Web thickness (figure 5, £0.1 x D

dimension A)

These values are incorporated in the final design of the fixtures

as given in Appendix A. Fastener length had no effect on the fatigue

life of fasteners tested in these fixtures. Changes in test frequency,

within the range used, had no effect on results. Also during this

phase of the program, the fatigue crack initiation detector [5] was

deve loped.

An attempt to determine the ability of these test fixtures to

distinguish between fasteners of different quality was made using four

sizes of 160,000-180,000 Ibf/in^ (H.O x 10^-12.4 x 10^ N/m2) series

flush head fasteners. A complete set of reference sample data on a uniform set of fasteners obtained from one manufacturer was generated.

This included at least seven replicate tests at each load level. When

the test loads are normalized with respect to the fastener double shear

strength, the median fatigue life curves and limits of the 0«95 confidence interval on the median appear as in figure 8, It appears that,

when plotted on a normalized basis, the data from all sizes of a series

of fastener may be considered as belonging to the same population.

Two lots of this same type of fastener were obtained from stock

maintained by the U. S. Navy. These are identified as Stock Samples

Nos. 1 and 2.

Figure 9 shows results of at least seven tests at each of two load

levels on each of three sizes of fasteners taken from Stock Sample No. 1,

6
The 0.95 confidence interval for the median for the tests of 0.25 in

diameter fasteners from the reference sample, which is representative of

the data for other sizes (see figure 8), is also given for comparison.

Figure 10 shows similar results for tests on fasteners from Stock

Sample No. 2. The 0.95 confidence limits for the 0.25 in diameter

fasteners from the reference sample are also shown.

It was observed that the two stock samples of 0.25 in diameter

fasteners, although obtained from two different supply depots, had the same manufacturer's lot number on the labels on the shipping boxes.

Thus the two sets of stock sample data may not be independent and may

actually comprise only a single set of data.

The scatter of fatigue life values of fasteners tested as stock

samples is somewhat greater than that of fasteners tested in the

reference group. However, the median of each size generally falls within the 0.95 confidence interval, indicating that these lots were of

the same quality when loaded in double shear. No conclusions regarding

the ability of this method to distinguish fasteners of different quality

can be drawn from the results of these tests.

3.3 Tension-Bending

a. Specimens

The tension-bending test method was developed using 0«25 in (0»6 cm)

diameter, 125,000 Ibf/in^ (8.62 x 10^ N/m^) tensile strength hexagonal

head fasteners and 0.25 in (0.6 cm) diameter, 180,000 Ibf/in^ (12.4 x 10^

N/m ) tensile strength 12 point external wrenching fasteners with fatigue

test nuts. No washers were used for these tests. The ability of this

test method to distinguish between lots of fasteners from different

manufacturers was determined using 0,25 in (0,6 cm) diameter, 125,000

Ibf/in (8,62 x 10 N/m ) tensile strength hexagonal head fasteners

taken from U. S. Navy supply depots,

b. Test Equipment

This program was conducted in the same two testing machines

described previously.

The tension-bending test fixtures are shown in the photograph in

figure 11 and schematically in figure 12, These fixtures can apply

loads to the fastener in four constant (i,e,, independent of load)

ratios of bending stress to axial stress, in addition to direct tension.

The fixtures are similar to those described by Larson and Radzimovsky

[6], Complete engineering drawings for these fixtures are given in

Appendix B.

For alinement of the testing machine and measurement of bending

strains induced in test fasteners by the tension-bending fixtures, a

7
hexagonal head fastener with four resistance strain gages mounted at the

midlength of the shank was used. This device is shown in Figure 13.

c. Test Procedure

Prior to testing, the bending strain measurement device was used to

aline the testing machine. This procedure was used to minimize undesirable bending strains. Bending strain measurements taken periodically

during the test program indicate that for fasteners tested in direct

tension^ the bending stress caused by machine misalinement did not exceed

ten percent of the axial stress.

The amount of bending strain induced in the specimens by the tensionbending fixtures was measured using the bending strain measurement device.

The first three knife-edge positions of the tension-bending fixtures

produced ratios of maximum bending stress to axial stress of 1.7. 3.2.

and 5.4 in the two types of 0.25 in (0.6 cm) diameter fasteners tested.

The test specimen and fixtures were washed with acetone prior to

each test. When the specimen was inserted in the test fixtures, care

was taken to leave two unengaged threads between the top nut surface

and the fastener runout thread so as not to superimpose the stress con- centrations at these locations. No washers were used.

The maximum cyclic loads were taken as percentages of the static

direct tension breaking load for that series of fastener. Loads were generally in the range of 20 to 70 percent of the static strength. The

minimum cyclic load was 10 percent of the maximum applied load. Test

frequencies were between 2 and 10 Hz.

All tests resulted in the catastrophic failure of the fastener,

either in the threads or at the head-to-shank fillet. Failure caused

automatic machine shut-down and terminated the test.

d. Test Results

The development of the tension-bending fixtures was accomplished

using a^uniform set of 0.25 in (0.6 cm) diameter, 125,000 Ibf/in^ (8.62 x

10 N/m ) tensile strength hexagonal head fasteners obtained from one manufacturer. These fixtures can apply loads in constant ratios of

bending stress to axial stress and can duplicate service failures, i.e.,

thread failures in direct tension and shoulder failures with induced

bending. Another series of tests was run using 0.25 in (0.6 cm)

diameter, 180,000 Ibf/in^ (12.4 x 10^ N/m^ ) tensile strength, 12-point

external wrenching fasteners. These also yielded the desired mode of

failure. Because of time limitations, no study on the effect of varying

fixture dimensions on failure mode was made.

The ability of these fixtures to distinguish between fasteners of

different quality was demonstrated using the hexagonal head fasteners.

A complete set of reference sample data on a set of fasteners obtained

from one manufacturer was generated. This included at least five

8
replicate tests at each load level and each bending stress-to-axial

stress ratio. In addition, three lots of hexagonal head fasteners of

unknown origin were obtained at random from stocks of replacement fasteners maintained by the U. S, Navy. These lots were identified as stock

samples N, P, and Q,

The results of tests performed on fasteners from stock sample N are shown in figure 14, At least three tests were performed at each of three

load levels at each bending stress-to-axial stress ratio. The curves

shown are the median fatigue life curves for the control sample. At each

load level and bending stress-to-axial stress ratio, the median lifetime

failure point is indicated along with the range of fatigue lives for all

fasteners tested at that load level and bending stress-to-axial stress

ratio.

The results from similar tests performed on fasteners taken from

stock samples P and Q are shown in figures 15 and 16, respectively.

The data for the stock sample fasteners loaded in direct tension

generally fall on or near the median curve for the control sample. The

fatigue lives of the stock sample fasteners loaded with induced bending

stresses are generally somewhat shorter than the fatigue lives for the

control sample fasteners tested under similar loading conditions. Thus

it seems that the stock fasteners, although considered acceptable on the

basis of direct tension fatigue tests, were inferior to the control

sample when loaded in tension-bending fatigue,

4, CONCLUSIONS

Based on the tests conducted during this program, the following

conclusions may be drawn:

1, A single shear lap joint should not be used for the

determination of shear properties of flush head

fasteners. The variations in fixture geometry

necessary to accommodate fasteners of different

lengths cause significantly different test results

in nominally identical fasteners,

2, The double shear test fixtures described herein

can consistently reproduce the shear-type head

failures incurred in service in 100 degree flush

head fasteners. This method has been verified

using two type of fasteners obtained from one manufacturer and two samples of one type taken

from Navy stock,

3, The tension-bending fixtures described herein can

produce constant ratios of bending stress to axial

stress in hexagonal head fasteners. Failure

caused by direct tension fatigue, which occur in

9
the threads, can be distinguished from failures

caused by bending fatigue, which occur at the

head-to-shank fillet.

4, The tension-bending method described herein can

distinguish between fasteners which are nominally

identical when loaded in direct tension fatigue,

but which exhibit different fatigue behavior when

loaded in combinations of bending and tension.

Note, however, that this conclusion is based on

a limited number of tests of one size of one type

fastener.

5. CLOSURE

Test fixtures capable of consistently reproducing service-type

failures for shear and tension-bending loading have been developed.

However, these methods have been used on relatively small samples of a few types of fasteners. In order to fully verify the validity of these

test methods to discriminate between fasteners of different quality, it

is necessary to test fasteners from lots whose quality is previously

known. To accomplish this, the relative quality of nominally identical

fasteners purchased from different manufacturers should be determined

through careful documentation of service failures. Fatigue-life curves

should then be developed for these fasteners using the test methods

described in this report. The validity of the test method can then be

judged by comparison of the laboratory data with the service failure

data.

10
6. REFERENCES

Anon, Tension Fatigue Test Procedure for Aeronautical Fasteners.

National Aircraft Standard 1069 (1959), Aerospace Industries, Assn.

of America, Washington, D. C.

Spaulding, E. H., Detail Design for Fatigue in Aircraft Wing

Structures, Metal Fatigue, G. Sines, ed, McGraw-Hill Book Co., N. Y.

(1959).

Viglione, J., The Effect of Nut Design on the Fatigue Life of

Internal Wrenching Bolts, U. S. Naval Air Engineering Center,

Report No. NAEC-AML-1 91 0, (1964).

Mordfin, L., Some Problems of Fatigue of Bolts and Bolted Joints in

Aircraft Applications, NBS Tech. Note 136 (1962).

Marlowe, D. E., and Steel, J. S., A Fatigue Crack Initiation

Detector, J. Matls, JMLSA, 1_, 1 (March 1972).

Larson, D. S. and Radzimovsky, E. I., The Strength of Bolted

Assemblies Subjected to Combined Dynamic Loads. Presented at

Society of Automotive Engineers Mid-Year Meeting, Detroit, Michigan

(June 6-10, 1966).

Figure 1

- Laboratory setup for single shear fatigue testing

Plate Thicknesses for Three

Fastener Lengths

A

1 T 16

18

B i

3

8

J4

Figure 2- Full section of single shear test fixture near specimen dimensions are in inches ( 1 in = 2. 54 cm ; .



I I

Figure4 - Schematic of double shear fatigue test fixture. Length

dimensions are in inches (l in = 2 54 cm).



zo

OHou

COOOOH

X<

LUZ)O 3UUO Xu<3o z < — Ll_ o u OH Z LU

ECTRO OUNT

LU

U

OHTE AY

LU —J

:§ RE c

0)E3

LUg

VOLT/ 9

LU

ulU

ND

U-1

itr < MP! < Q

LU

Q- < u

0) a>Eo

D)OQ

_o

CQ

0)o
;

!

I







-i,

I

- i

.


1 r 1 1

1 ^—1

J

1

1

1

1 1 1_ _ _

1

Head- restraining screw

-Collar

Knife edge

• Test specimen

oading fixture

Nut

Figure 12 Schematic of tension - bending fatigue test fixtures.

0.5 L

4 Strain gages, 90 apart,

alined with specimen axis

AN 4-22 fastener

Figure 13 - Bending measurement device used with tension -bending test fixtures.

o

UJu>-u

iqi 'avoi

a>

0)> Q.Eo

(D

O)D

**- c

O) ow c

T3 u. C o

0) -Q1 c 0) O >

COC 3

<J

C

C 0 o

"D TO

(UE 1 . w3

O) u.
...

"v

9"

\i
ftD

>

u.o [HT

mge

o ii Li

w

Median o o o a

oc

Bending

Stress

1

Axial

Stress

<0.1 1.7 3.2 5.4

o

cn o

CO o O

8

O

o

CO «

•O _l O*"* U>-u

o

o

o

3

HI 'avoi
'•-(
co

o

-ao

3

*qi "a vol

APPENDIX Al

Double Shear Fatigue Test Fixtures for 0.190 (No, 10) and

0,250-in Flush Head Threaded Airframe Fasteners

Detailed drawings for the fixtures used for the tests described in

this paper are given in figures Al to A7.

DESCRIPTION

Base Plate

Top Side Plate

V2-13 Screw

Space

Retainer

Insert Blade

Lower Side Plate

Fig. Al-Double Shear Fixtures (lO and X'tn fasteners) , Assembly
-.4
Thread 1*14 to fit

10 Kip Fatigue Machine

C hamfer 45° x

Part No.l

Base Plate

Material : 0-2 Tool Steel Rc 60

2 Required

Fig. A 2
f f

•v.. -t

r,


.001 For No. 10 Fastener, A= 0.190 .qqq

1 .OOl

For J

in. Fastener, A = 0-250 -000

Port No. 4

Spacer

Material: 0-2 Tool Steel

Rc 60

1 Required for each size fastener

Part No. 5

Retainer

Material*. 2024—T4 Aluminum Alloy

2 Required

Fig. A4
r ,"1
0024-

3250 1*- ^ 5 _ 16 Part No. 6

Inserts

Material • A IS I 4340 Steel

Rc 45-50

1 Each Required for

each size fastener

Fig. A

5
X,.

i

-
z

y Drill

32y> <'32

Fastener Size A B No. 10

k

0190 -000

0"•^^^ 250

-nnn

0.188 tggo

0.24 9 1^00

Pait No 7

Blade

Material • 0-2 Tool Steel

Rc 60

Grind Flat and Parallel after Heat Treating

1 Required for each size fastener

Fig. A

6
. i. ...

i 1

I
Fig. A

7
-J,

.1 4

... L ;
APPENDIX A2

Double Shear Fatigue Test Fixtures for 0.375-, and 0.500-in

Flush Head Threaded Airframe Fasteners

Detailed drawings for the fixtures used for the tests described in

this paper are given in figures A8 to A17,

PART NO. DtSCR IPT ION

1 Base Plate oZ Top oide Plate o

v5 ^2 I0UNL.-2 Screw

^4 opacer

5 Retainer

6 Insert 7 Blade

8 Lower Side Plate

Fig. A8 - Double Shear Fixtures (

^6 and ^2 in fasteners), Assembly


r

. vs.

Si:
1.5000 D

+.0005

-.0000

Thread 2-12

0.250

•±.002

Part No. 2a

Top Side Plate

Material: 0-2 Tool Steel

1 Required

Fig. AlO
J- - /

-4
Thread 2-12

4

3.000

±.002

I i

^0.250

±002

ni 71

1

16

^

<32

1.000

±.005

1 " II' I /

' 1

' ' /

' ; '

/

^-i 1 "

"

1 '--f ijj 1 -jj

;

1 ! 1 1.5000 D

4.0005 —

H

-.0000

2 Holes

i-13 UNC

Drill -|

Part No, 2b

Top Side Plate

Material: 0-2 Tool Steel

1 Required

Fig. All
. . 5-.

.J i.:,L:

V. :-

''1' --yvt
Chamfer

Thread 2-12

Part No 1 (b)

Stud

Material: AISI 1015 Steel, Cold Drawn

2 Required

Drill

3r- -r^^* — .- *.005

For "g Fasteners,!: 0.375 .qqq

For 1 Fasteners, T= 0.500 tJJJ

Part No. 4

Spacer

Material : 0-2 Tool Steel

1 Required for Each Size Fastener

Fig. A12
- v

I

! i

1
I

0.250 ±.002

Fastener A B C D

3

8 0.375 JL

8 0.040 0.394

12

0.500 12 0050 0.525

Tolera nee

+.002

-000 t005 +.005

Part No 6

Insert Material : AISI 4340 Steel

Rc 45-50

1 Each Required for Each

Size Fastener

Fig. A14
-•x

/V ..X. . V,

. ) f . / \ \ \
Part No. 7

Blade

Material • 0-2 Tool Steel

Rc 60

Gfind Flat and Parallel After Heat Treating

1 Required for Each Size Fastener

Fig. A 15
i



1
APPENDIX B

Tension-Bending Fatigue Test Fixtures for 0.250-in

Protruding Head Threaded Airframe Fasteners

Detailed drawings for the fixtures used for the tests described in

this paper are given in figures Bl to B6.

L,

0.

0.

25

z T

^ ^ I I

I

' J LHi)

.1 I

I

I ._j

I

I J

I

I

I

PART NO- DESCRIPTION

1 Test Specimen

2 Nut

3 Knife Edge

4 Collar

5 Retainer

6 6-32 Screw

7 Base Plate

8 Spacer

9 Top Load Plate

10 Botiom Load Plate

11 1-13 Screw

~1

) (

Fig. Bl - Tension - Bend ing Fixtures, Assembly


•-5 "V

\

>;

... ..,

J- /

J\ •4

4

-17.:;

1

1

A
1

1 -ff

Part No. 5

Retainer

Material: Cold Rolled Steel

1 Required

Fig. B3
0

;--rIf. :

'

....jy.,.. ,.,,„.,; .„ \...\ -

""'^1"

4. ....J I -V

.-1

'

... .....
0)

COoZ

I o

u

o

-a

a;

CM

O)

0)

~oO

7

00 _^

6 o z - -z

•t- -I •-On

O Q. ^ Q- CO <

o

00

inu

OH -a

0)3

D0) Of
i
i

1.6

9_ 16

3

1—

r

'

I 4

^ 3

Drill and Tap

1-13 UNC

Part No. 9

Top Load Plate

Material: AISI 4340 Steel

Rc 41-43

1 Required

1

16

~3"

I

•

4 J

Ref

Drill and Tap

j-13 UNC

Part No. 10

Botto m Load Plate

Material: AISI 4340 Steel

Rc 41-43

1 Required

Fig. B6
-jv> -'V i... 71-

•'.tv1

/ M " / ....

-4 - - ...
NBS-114A (REV. 7-73)

U.S. DEPT. OF COMM.

RIRI 1 Or^ P A PM 1 r° DATA

SHEET

1. PUBLICATION OR REPORT NO.

NBSIR 74-465

2. Gov't Accession

IN O.

3. Recipient's Accession No.

4. TITLE AND SUBTITLE

Shear and Tension-Bending Fatigue Test Methods for

Threaded Airframe Fasteners

5. Publication Date

6. Performing Organization Code

7. AUTHOR(S)

Daniel J. Chwirut, Donald E. Marlowe, and James S. Steel

8. Performing Organ. Report No. NBSIR 74-465

9. PERFORMING ORGANIZATION NAME AND ADDRESS

NATIONAL BUREAU OF STANDARDS

DEPARTMENT OF COMMERCE

WASHINGTON, D.C. 20234

10. Project/Task/Work Unit No. 2130448

11. Contract/Grant No. NADC Proj ect Order No

.

PO-8-0033

12. Sponsoring Organization Name and Complete Address (Street, City, State, ZIP)

Aero Structures Department

Naval Air Development Center

Department of the Navy

Warminster^ Pennsylvania 18974

13. Type of Report & Period

Covered

Final

14. Sponsoring Agency Code

15. SUPPLEMENTARY NOTES

16. ABSTRACT (A 200-word or less factual summary of most significant information. If document includes a significant

bibliography or literature survey, mention it here.)

Fatigue test methods for threaded airframe fasteners loaded in other than direct tension

are described. The types of loading considered are single shear, double shear, and

tension-bending. The test fixtures used in these tests are described. Results of tests

on lots of fasteners from different manufacturers indicate that fasteners considered

identical on the basis of direct tension procurement tests exhibit different fatigue

life characteristics when loaded in shear and/or tension-bending. Thus the test methods

described herein may be of future value as procurement tests for airframe fasteners.

17. KEY WORDS (six to twelve entries; alphabetical order; capitalize only the first letter of the first key word unless a proper name; separated by semicolons)

Airframe fastener; double shear; fatigue; single shear; tension-bending; test methods

18. AVAILABILITY [^Unlimited 19. SECURITY CLASS

(THIS REPORT)

21. NO. OF PAGES

! For Official Distribution. Do Not Release to NTIS

UNCL ASSIFIED

1

' Order From Sup. of Doc, U.S. Government Printing

Washington, D.C. 20402. SD Cat. No. C13

Office 20. SECURITY CLASS

(THIS PAGE)

22. Price

1 ! Order From National Technical Information Service

Springfield, Virginia 22151

(NTIS)

UNCLASSIFIED

USCOMM-DC 29042-P74