1301T-BEARING PROPERTIES Of
GLASS-FABRIC-BASE
PLASTIC LAMINATES
No. 1824
June 1951
INFORMATION REVIEWED
AND REAFFIRMED
1958
INFORMATION PEVIDNED
AND REAFFIRMED
1965,
FOREST PRODUCTS LABORATORY
MADISON 5. WISCONSIN
UNITED STATES DEPARTMENT OF AGRICULTURE
FOREST SERVICE
In Cooperation with the University of Wisconsin
BOLT-BEARING PROPERTIES OF
GLASS-FABRIC•. BASE PLASTIC LAMINATESBy
FRED WJEREN, Engineer
Forest Products Laboratoryra Forest Service
U. S. Department of Agriculture
•nn•••••n•
Summary
Thi s report presents the results of about 400 bolt-bearing tests of
three gla ss-fabric-base plastic laminates made with a polyester resin conforming to U S. Air Force Specification 12049. The laminates were either 1/4or 1/8- inch thick and wore tested at angles of 0°, 90°, and 45° to the warp
direct ion, at DA ratios of 1 and 4, and in both the dry and the wot Oonditions,
Incl uded are data on the bolt-bearing properties of the materials and on the
off oct of end or edge distancos,
The laminates worn roinforood with glass fabrics of widoly difforent
p roportios, so that some difference in bearing properties might bo expected.
Tho and and edge distances required to preclude failure to the and or lodge
of the specimen were substantially different for the throe laminates. However,
-This progross report is one of a series prepared and distributed by the
Forest Products Laboratory undor U. S. Navy, Bureau of Aeronautics
Ordor NAor. 01044 and U, S, Air Forco No. USAF-33038 (51-4066-E). Results
hero reported are preliminary and may be revised as additional data
b000me available.
2
-Maintained at Madison, Wis., in cooperation with the University of Wisconsin.
Report No. 1824
Agriculture-Madison
an end distance of 4D and edge . distance \ of 2-1/2D were large enough to prevent
such failures, regardless of the fabric used.
With adequate end edge distances, the stresses at proportional limit
and at maximum load were (1) highest at the low D/t ratio, (2) highest when
laminates were tested in the dry condition, and (3) about the same at 45° as
at 0° or 900.
Introduction
Various methods aro available for the joining of elements of glassfabric-base plastic laminates to each other or to other members of a strucutro.
Included in these methods is the use of bolts or rivets. It is important that
some information on the bolt-bearing strength of such laminates, along with
data on the effect of end and edge distance, be available to the designer.
This study was made at the Forest Products Laboratory in cooperation
with the ANC-17 Panel on Plastics, It includes tests of throe laminates, in
wet and dry condition, with various and and edge distance ratios, at D/t
ratios of 1 and 4.
Description of Material
Glass-fabric-base plastic laminate panels were made from each of three
fabrics: 112-114 plain weave, 181-114 satin weave, and 143-114 unidirectional
weave. Panels of 112-114 or 181-114 fabric were parallel-laminated and those
of 143-114 fabric were cross-laminated. The 1/8-inch-thick panels were 18 by
18 inches and the 1/4-inch-thick panels were 36 by 36 inches.
All panels were fabricated with resin 2, a laminating resin of the
polyester (alkydr.styrone) typo conforming with the requirements for Types I,
II, and III of U. S. Air Force Specification 12049. The rosin was catalyzed
Report No, 1824
-2-
by the addition of 0.8 percent benzoyl peroxide by weight. Each panel was
cured at a pressure of 14 pounds per square inch for 1 hour and 40 minutes
in a press at a platen temperature increasing from 220° to 250° F. Average
values of thickness, rosin content, specific gravity, and Barcol hardness,
and the number of plies of fabric for each panel are given in table 1.
Preparation of Specimens
Specimens were cut from the cured panels with a 1/8-inch emery wheel
rotated at 1,770 revolutions per minute on the arbor of a variable-speed
table saw. Each specimen was cut to . a- lengthof about 6 inches and of a
width dependent upon the edge distance desired. They were cut from the panel
either parallel to, perpendicular to, or at 45° to the warp of the fabric of
the top lamination.
An attempt was made to match dry and wet specimens wherever possible.
In general, the specimens were numbered consecutively, and odd-numbered ones
were conditioned for dry tests while the oven-numbered ones were conditioned
for wot tests. Each specimen may be identified from its number. For
example, for specimen 0-31-1:
0 = specimen tested at 0° to warp of
top lamination
31 = panel number
1 = specimen number
Tho holes wore drilled and roamed with care to provide uniform holes
with smooth surfaces. Each hole was drilled about 0.003 inch under size with
a twist drill rotated at about 300 revolutions per minute. The specimen was
placed over a wooden block so that, as the drill emerged, there would bo no
delamination of the fabric. The holes wore then carefully reamed to size so
Report No, 1824
-3-
that the pin used in test could be pushed through by hand.
Dry specimens were conditioned in an atmosphere at a temperature of 75° F.
and at a relative humidity of 50 percent for at least 1 month before testing.
Wet specimens were conditioned for at least 2 months at a temperature of
100° F. and at a relative humidity of near 100 percent.
Testing
Tensile loads wore applied to the bolt-bearing specimens as shown in
figures 1 and 2. The specimen was gripped with either (1) a pin-connoctod
clamp-on dovico (used with 1/4-inch laminates, fig. 1) or (2) a solf-alining
Tomplin grip (used with 1/8-inch laminates, fig. 2). The jig that supports
the loading pin was bolted to the movable head of the testing machine. It
is described in Forest Products Laboratory Report No. 1523-C, 3 and consists of
two side plates that house removable bushings reamed for various sizes of
pins or bolts. A projecting lug on the inner face of each bushing provides
support for the bolt in the gap between the plates and the specimen. These
lugs, however, do not interfere with lateral extrusion of the laminate under
the bolt hole. Either a 1/4-inch-diameter hardened-steel pin or a 1/2-inchdiameter aircraft bolt was used in each bearing test.
An initial load was placed on the specimen and the dial stem of a
dial gage, reading to 0,0001 inch, was placed in contact with the end of the
specimen. The load was applied at a head speed of about 0.03 inch per minute.
Load-deformation readings were taken at regular increments of load until the
maximum load was reached. For specimens that failed by crushing under the
bolt hole, the load usually held momentarily at the maximum, with accelerating
g
Bolt-bearing Strength of Wood and Modified Wood. Forest Products Laboratory
Report No. 1523,4. Nov. 1946,
Report No. 1824
deformation, and then failed suddenly. For specimens that failed otherwise,
failure was more rapid,
For the 0° and 90° specimens, there were four general types of failure
(fig. 3): (1) crushing under the bolt hole, (2) failure to end, (3) failure
to edge, and (4) failure toward edge. The first type of failure occurred when
edge and end distances were adequate, and was a crushing and delamination of
the material under the bolt, Failure to end was a result of inadequate and
distance, that resulted in a shearing or pulling out of the laminate at the
end of the specimen. Failure to edge was usually caused by inadequate width
(edge distance) of the specimen, which resulted in a tensile-type failure
across the not section. The fourth type of failure, which has been called a
failure-toward-edge type, was caused primarily by inadequate end distance.
This is discussed further under "Stress-concentration Effect" in the
"Analysis of Results." Instead of causing a shearing out to the end, as
expected, the concentrated tensile stresses at the edge of the hole induced a
failure perpendicular_ to the applied load. Once the failure started, a cleavage
type of failure occurred, in which the failure progressed outward toward the
edge of the specimen. In some tests the end element subsequently failed
parallel to the applied load, probably because of the bonding stresses induced
in it. If the failure toward the edge progressed far enough, it would appear
similar to the failure-to-edge typo, and thus it might be difficult to
differentiate between the third and fourth types of failures in some cases.
The 45° specimens failed by one of or by a combination of the first
three typos of failures mentioned in the preceding paragraph. Failure by
crushing under the bolt hole was about the same as with the 0° and 90° specimens. End failure sometimes followed the warp or fill direction'of the laminate
and at other times had tendency to shear out to the end. Failure to the edge
Report No. 1824
-5-
also followed the warp or fill direction or failed on an irregular line
perpendicular to the edge of the specimen,
Typical failures for both the 1/8-inch and 1/4-inch laminates are
shown in figure 3,
Presentation of Data
The average bolt-bearing prorertios for each of the three laminates
are given in table 2. Those valuos are based only on the specimens that
failed by crushing under the bolt; that is, the specimens that had adequate
and and edge distances. The number of tests reprosonts the number of spooimons of oach group that failed in this way. Bearing strength is defined in
Federal Spocification L-P-406a as the bearing stress at a deformation of
4 porcont of the hole diameter, whore stress is load divided by bearing area
(bearing area being diameter of hole times thickness of specimen). For tho
1/4-inch pin, this deformation is 0.01 inch, and the average values are given
in column 4. For tho 1/2-inch bolt, this doformation is 0.02 inch, and no
values of bearing strength aro given because all deformations at maximum
load are loss than this value. Deformation at proportional limit is read from
the straight line transposed through the origin of the load-deformation curve.
Thus, tho proportional limit stress divided by its deformation indicates the
slope of tho load-deformation curve. The doformation at maximum load is the
deformation road just before the specimen fails completely. Total deformation
after failure would bo much greater for the specimens that failed by crushing
under the bolt. Values from compression and tension tosts are from previous
tests of similar laminates. -4 5
4
-Mechanical Properties of Plastic Laminates. Forest Products Laboratory Report
No. 1820, February 1951.
echanical Properties of Cross-laminated and Composite Glass-fabric-base Plastic
Laminates. Forost Products Laboratory Report No. 1821. February 1951,
Report No. 1824
-6-
Results of individual bolt-bearing tests of 1/4-inch laminates are
given in tables 3, 4, and 5, and those of 1/8-inch laminates in tables 6,
7, and 8. End distance is the distance from the end of the specimen to the
circumference of the bearing hole, and edge distance is the distance from
the edge (side) of the specimen to the circumference of the bearing hold.
Values of bearing strength, and proportional limit and maximum load values
are as described in the preceding paragraph. The average tensile stress on
the net section is simply the maximum load divided by the net tensile area;
namely, thickness, multiplied by the width of the specimen minus the diameter
of the hole. The type of failure observed for each specimen is also given.
It will be noted that the specimens that failed by compression under the bolt
hole aro listed separately within each group of specimens. Table 2 presents
the average values from tests of these specimens.
Results of a few exploratory tests of 112-114 laminate of 1/8-inch
thickness are given in table 9, and are plotted in figure 4. These tests show
how the maximum bearing stress of this laminate varies with changes in end
distance and width of specimen.
The estimated minimum end and edge distance ratios required for each
group of specimens to assure failure under the bolt hole are given in table
10. Those values are based on the curves of figures 5 through 10.
Typical load-deformation curves for specimens that failed by crushing
under the bolt are shown in figures 11 and 12. It should be understood that
those are not average curves but are given merely to indicate load-deformation
tendencies.
The effect of end distance and edge distance on the maximum bearing
stress can be easily visualized by the curves of figures 5 through 10, For
Report No, 1824
-7-
each specimen, maximum stress in bearing is plotted againstthe end or edge
distance ratio. End distance ratio is the end distance divided by the diameter
of the bolt, and edge distance ratio is similarly defined. Values for plotting
.are taken from tables 3 through 8. For the specimens plotted for the enddistance-ratio relationship, the specimens were wide enough to nullify the
edge distance factor. Similarly, specimens used for edge distance tests had
an end, distance large enough to prevent end failure.
, In figures 5, 6, and 7, the horizontal broken line represents the
average maximum stress for those specimens that failed under the bolt hole.
Figures 8, 9, and 10 represent the results of tests of 1/8-inch laminates,
and it can be seen that the curves are based on less data than are the curves
for the 1/4-inch laminates. Each specimen that failedulder the bolt hole has
been, plotted both with respect to its and distance and its edge distance.
Analysis of Results
General
The method of test employed in this bolt-bearing study is considered
to bo satisfactory. Bonding of the bolt or pin is not considered to have
affected, the results Within the EA range tested. It will be noted from tho
load-deformation curves, figures 11 and 12, that, there is usually a lack of
straightness for the first 2 or 3 readings. Those readings, however, take
into account any nonelastic slip, and the curves are considered to be generally
typical of bolt-bearing curves of other materials.
In the subsequent discussion, the maximum bearing stress is frequently
mentioned. Unless it is otherwise stated, it should be taken to mean the
bearing stress at maximum load for those specimens that failed by crushing under
Report No. 1824
-8-
the bolt hole. In application of bearing values, it is assumed that structures
will be designed with adequate end and edge distances to prevent end or edge .
failures,
Federal Specification L...P-406a prescribes that the bearing strength
shall be reported for each bearing test, As mentioned previously, the
deformation at which the bearing strength should bo calculated was not reached
for the bearing specimens of 1/8—inch laminate with the 1/2—inch bolt. Thus
no values of bearing strength can be given for this D/t ratio, and no comparison
of bearing strengths can be made with those at other D/t ratios. It would
appear that the stress at proportional limit, as well as at maximum load, may
be a more practical value to report in a summation of results of bearing
tests of those materials.
Relation of Maximum Bearing Stress to Compressive
Strength
6
shown that the compressive strength of laminates
Previous studies —have
is greatly affected by the angle of loading, and that the strength at 45°
to the warp of the laminations may be less than one—half of the strength at
0° or 90°. On the other hand, it can be seen from table 2 that the maximum
bearing stress is about the same at 0°, 45°, and 90° loading. From these
limited data, it is not possible to establish any definite relationship between
maximum bearing stress, compressive strength, D/t ratio, and angle of loading.
Examination of the data in table 2, however, indicates that at 0° and 90°
the maximum bearing stress increases with an increase in the compressive strength.
There was a distinct difference between the compression failures and the
bearing failures, The compression specimens failed by a shear offset type of
-Directional Properties of Glass ,-fabric—base Plastic Laminates of Sizes that
St Not Buckle, Forest Products Laboratory Reports Nos. 1803 and 1803—A4
April 1949, and April 1950.
.9.
Report No. 1824
failure combined with some crushing of fibers. Bearing failures were simply
a
crushing and delamination of the laminate under the bolt, since the stressed
zone was retarded from failing in transverse shear. Except for the 1/8-inch
112-114 laminate, at 0° and 90° in the wet condition, all values of maximum
bearing stress are greater than the corresponding compressive strength.
In general, the proportional limit bearing stress of the 1/4-inch
laminates and the compressive strength are about the same at 0° and 90°
(table 2). No explanation is offered for this agreement, since a similar
relationship does not hold for the 1/8»inch laminate.
A few dry bearing tests under compressive loading wore previously
completed- of a 1/4-inch-thick 181-114, resin 2 laminate. In those tests, end
and edge distance ratios and notch sensitivity were not factors affecting the
bearing values. The results of those tests also indicated that bearing values
are not greatly affected by the angle of loading. However, the bearing
strength was a little lower, proportional limit stress about the same, and
stress at maximum load about 20 percent higher than comparable values under
tensile loading, Since the specimens under compressive loading all failed
by crushing under the bolt hole, the above comparison is limited to those
specimens under tensile loading that failed in the same way (table 2).
Effect of
DA Ratio on Bearing Properties
It was hoped that the results of this study would show
a
relationship
from which bearing properties could be predicted on the basis of tho D/t
ratio to be used, The D/t ratio, as mentioned before, is the diameter of
the bolt divided by the thickness of the laminate. However, tests at only
two pit ratios were completed; namely, at values of 1 and 4. A few tests
at a D/t ratio of 1/2 wore attempted, with a 1/4-inch laminate and 1/8-inch pin.
Report No. 1824
The results were unsatisfactory because, even though a nickel-chrome steel pin
treated to Rockwell C-43 hardness and having a tensile strength of more than
200,000 pounds per square inch was used, the pin failed in shear before
complete failure occurred in the laminate. There was also evidence of bending
of the pin. Thus, at this DA ratio, the pin may be expected to fail before
the laminate,
Examination of the average values in table 2, however, showsthat in
each case the stress at proportional limit and the maximum bearing stress
are greater at a D/t ratio of 1 than at a D/t ratio of 4. Although a straightline relationship probably does not exist between those ratios, reasonable
values of the bearing properties at D/t ratios between 1 and 4 can be estimated.
There is, however, danger in extrapolating outside of this range. At values
loss than 1, higher properties might be expected, except that as the length of
bolt or pin becomes longer with respect to a given diameter, a greater bonding
of the bolt or pin will occur that will tend to lower the average stresses,
At D/t ratios increasingly greater than 4, there will eventually bo a tendency
(especially if there is any lateral component of loading) for the laminate to
become unstable under the bolt. For most practical applications, however, the
use of combinations resulting in large D/t ratios appears unlikely.
The above relationships are discussed in terms of the D/t ratios. It
seems logical to assume that different thicknesses of laminate would have
similar properties in bolt-bearing as long as the D/t ratio was kept constant.
It would, however, be desirable to verify this with further tests as well as
to obtain additional data on the bearing properties of the laminates at
additional D/t ratios.
Report No. 1824
Edg e and End Distances; Conditioning
The laminates tested for this study were made of three glass fabrics
having entirely different properties, and represented the range of fabrics
now being used for aircraft laminates of this type. If edge and end distances
are selected that are adequate for all of these laminates, they should also
be adequate for any of the other glass-fabric-base plastic laminates presently
being used as aircraft laminates. The 112-114 laminate, made with a fine-weave
fabric, required the greatest end and edge distances in all cases.
Prom those data, which are summarized in table 10, the designer can
select the minimum end and edge distances required for a particular application. Caution should bo exercised in the application of those data, in the
realization that the values are based on tests of limited scope. Within the
range tested, however, it appears that an end distance of 4D and an edge
distance of 2..1/2D will be adequate for these laminates.
With two exceptions, the end rand edge distance ratios required at a
DA of 1 wore as groat as or greater than the corresponding values at a D/t
of 4. This applied to both dry and wet conditions. In general, adequate edge
and end distances required to assure failure under the bolt were less for the
wet condition than for the dry condition. For the 143-114 laminate, maximum
end and edge distance ratios were about the same in either condition„
Examination of the curves of figures 5 through 10 shows that the
maximum bearing stress of any of the laminates tested, at any edge or and
distance ratio, was loss in the wet condition than in the dry condition.
Stress-concentration Effect
A few exploratory tests were made of each laminato'before the main test
specimens were cut up so that some knowledge of the critical end and edge
Report No. 1824
-12-
It has been mentioned that some specimens, with inadequate end
distances, failed by shearing out to the end while others failed toward the
edge. Results of tests from previous work —4 —
5 show that the shear strengths
for these three laminates at 0° are not greatly different. It appears,
therefore, that the difference in the types of failure is attributable to
some othor factor.
Based on the limited end-distance tests of 0° and 90° specimens, it
can bo said that the 112-114 laminate was the most susceptible to failures
duo to concentrations of tensile stress and the 143-114 laminate was the
least susceptible. The ratio of tensile stress on the net section to the
tensile strength of the material, whore failure occurs to the edge, may also
be considered an indication of the notch sensitivity of the material.
Examination of these values likewise indicates that the 112-114 laminate is
the most sensitive and the 143-114 laminate the least sensitive to notches
at angles of 0° and 90°. At 45° the materials are not greatly different.
The average tensile stress on the not section at failure is given for
each specimen, tables 3 through 8 6 For 0° and 90° loadings, it is soon that
the tensile stresses developed are low compared to the tensile strength of
the laminate (table 2) regardless of the typo of failure, but at 45° loading
the tensile stresses approach the corresponding tensile strength. It is
apparent that laminates joined with bolts or rivets cannot be expected to develop
high efficiencies with respect to the tensile strength of the laminate.
Variation of Slope of Load-deformation Curves
Barring tho first two or three points on a load-deformation curve, it
is soon that the deformation varies linearly with the load up to the proportional
limit (figs. 11 and 12). The proportional limit itself, as with many other
Report No. 1824
-14-
materials, is difficult to establish exactly, and the values of proportional
limit stress may vary considerably within each group of specimens. If,
however, the stress at proportional limit is divided by the deformation
(read from an offset line through the origin), such a value can be used as a
guide to compare the initial slope of the load-deformation curve between
various specimens or groups of specimens. It is thus a measure of deformation
or elasticity of a particular material in bolt bearing.
Values of stress divided by deformation were computed for the average
of the values in table 2, They are not recorded, however, since such a term
has not a generally established engineering interpretation. It was of interest
to note that at a D/t ratio of 1, the slope was practically the same for both
dry and wet conditions within each group. This was not true at a D/t ratio of
4, where the stress-over-deformation value was, in all cases, lowest in the
wet condition. This indicates, of course, greater deformation for a given
stress when the laminate was wet. No reason is offered for this variation at
different D/t values.
Discussion of Tables
It was mentioned above that the values of table 2 are average values
from tests (where the specimens failed under the bolt hole), taken from
tables 3 through 8. For the 1/4-inch laminate, bearing strength is defined
as the stress at a deformation of 0.01 inch. Examination of tables 3, 4, and
5 shows that at the maximum load, the deformation is almost always greater than
this value, and thus bearing strength is somewhat lower. In a few instances,
however, the deformation at maximum load is less than 0.01 inch. For specimens
that failed by crushing under the bolt, it was mentioned that accelerating
deformation took place just after the maximum load was attained. Thus,
Report No, 1824
-15.
the bearing strength would be equal to the maximum stress in these
cases.
A further examination of tables 3 through 8 shows that in some enddistance tests the failure was actually to the edge (type-3C failure).
It was explained above that if the failure-toward-edge type (S) progressed
far enough, it might appear to be a failure-to-edge type. For these spociMons, thoreftwe, it should be understood : that failure was probably due to
inadequate end distance oven though the final failure was to tho edge.
Table 10 gives the estimated end and edge distance ratios required to
assure failure under the bolt hole. Those values are taken from figures
5 through 10. At a D/t ratio of 1, the tests cover a sufficient range to
provide well-established curves. Tho critical edge and end distances from
those curves, therefore, are considered reliable. At a D/t ratio of 4,
however, the test data are limited, and in some cases the curves must be
estimated. Further, the curves are generally drawn as two straight-line
segments, especially the curves expressing end distance ratios. Nevertheless,
a
study of the data, correlated with other curves that are well-
established, indicate that the minimum end and odge distance ratios given
for a D/t ratio , of 4 are reasonably correct,
Conclusions
An analysis of the results of bolt-bearing tests of three glass-fabricbase plastic laminates loads to the conclusions that follow. The tests were
limited in scope and number but, within limits, the results are believed to
be indicative of the bolt-bearing properties of similar laminates now being
used for aircraft. Except whore specifically mentioned, the conclusions are
Report No. 1824
-161-
based on those specimens having sufficient end and edge distances to preclude
failuro to the end or edge.
1. The stresses at proportional limit and at maximum load are about
the same for 45° loading as for 0 . or 90° loading.
2. The average stresses at proportional limit and at maximum load
are lower in the wet condition than in the dry condition.
3.
The stresses at proportional limit and at maximum load are
considerably greater at a D/t ratio of 1 than the corresponding values at
a D/t ratio of 4.
4, The maximum stress in bearing is lower in the wet condition than
in the dry condition, regardless . of the edge or end distance ratio.
5. There is considerable . variation in the end and edge distances
required to prevent failure to the . endand odge of the specimen. Tho end
and edge distances will vary with type of laminate, conditioning, angle of
loading, and D/t ratio. Within the range tested, it appears that an end
distance of 4D and an edge distance of g-1/•D . Will be adequate for all
laminates.
6, At 0° and 90° loading, the 112-114 laminate ap peared to be more
susceptible to stress concentrations than either of the other laminates,
and thus will require greater end and edge distances,
Report No, 1824
-17
Table 1.--Average values of thickness, resin content,
specific gravity, and Barcol hardness for
laminated panels
•.
1
Panel : Number : Thickness : Resin i Specific : Barcol
No. :
of :
: content : gravity :hardness
:
: plies s
.
:
:
:
of
:
s
:
..
: fabric :
:
:
: Percent :
112-114 Laminate. Resin 2.
9
s
11
1
201
202
48
:
84
42
42
42
42
:
:
:
0.254
.128
.121
.122
.123
:
:
:
Parallel–laminated
43.9
44.1
42,3
42,7
43.0
:
t
1.69
1.69
1.73
1.72
1.72
s
69
s
70
66
65
64
s
s
181-' 114 Laminate. Resin 2. Parallel-laminated
24
31
i
t
23
12
:
:
.238
.119
:
$
36.0
33,9
3
:
1,79
1.81
:
70
70
143-114 Laminate. Resin 2. Cross–laminated
25
32
:
:
26
13
:
:
.240
.124
:
:
31.0
32.2
:
s
1,87
1.84
e
:
70
69
00 00 00
C-M
.. .. \00
.. ...
.. .. CC11
NH m0 0K\\
-7r1 nn NH
00 00 00
00 00 00
MN
HM
.. ..
.. ..
.. .. -d-M
ON 0 nm CU n
.4'...t -714", NH
00 00 00
Hi
0
4-1 4.2
03 CO
a)
0 +3
if\
--
oo oo oo
00
oo oo
MN
if\C- OM
•• ••
• •
mrr. t-.4. nn
....
oo oo coo
NN NH
”“
..”
00 00 00
141\40 ft
HO
C-\0
•
n •
N101
m.-1NN
NN NN
•
00
00
ooQ°\
oo
m.-1O°1
•• ••
•• •
00 00
oo
oo
nm
-4-reN
Is ••
• n
-1H
•• ••
•• ••
00 00
00 00
oo
on
• •
mn
Pr\N
oo ca
oo
\0m
• •
...16 N\0 -71n
ON rc) r- rim
-A-N /4-‘-t ..7N
0 0
42
HO
0 0
0 0
if ..\
m..
H CT
H
al
•••
00
oo
NH
•• n
00
oo
nn
n •
0_1-
om
-7N
00
00
KNO
HH
•• ••
WN
1C\1C\
HH
00
MH
MM
00
00
H
HH
00
OD \O
•• ••
•• ••
•• ••
•• ••
00
O 0
K\ \
00
00
HM
.. ..
00 0
H H
•• ••
00
00
00
re.N
NN
•• ••
NH
00
oo
Hn
• n
oo
oo
00
00
•
••••
ma\
--r^ r-w Om
nn -1-4nn
m 88
00 00
43d
. . 00 00
. 0
nn
--1-14-\ 'd
00 0
00 4J
C
NW\
00
00
,7'
O
ra
H
--1-
00 00 00
0 00 00
nal
N
NC- WW1 CO 0
HH
r-I
WH
••••
••••
•• ••
1.1
-1-
K1
•• ••
nm
00
00
wm
0 --1.11.\
HO HO
HH
00 00 00
CN
..
0 o
0
o,
o, o
1(10/
•• ••
N C-
0
40. a-3
00
0
te\
" .
•• ••
00 00
00 82
in...\C)...
... ...
N t--
al WI
NH NH
• •
00
N H \O -1-
cc\ 0 H C.-
CV NH
N
• • • •
** • '
0 00 00
co
Hi
H
H
n
n
-.
-
0
0
0 0
Nn -1
.-1'141 \ON
K'. 0.1
rel 0.1
\OM NH
K•N 01
l',• N
•• ••
0 0
0 0
0..
N..
HI -1NH
0
.. ..
'd
0
vi
io
0
L,
W
q
i
e
r-91
+2
r4
CO
X
o
.4U
-I1 HI
0
I
g
.,„7....-
H Hi +3
-P .r1
Z
/4 0
0 4-1
,1-1 +2
..
co
m
:::.
4-1s.o.
RA
Oa
..
g
.
H
H
0H
p.,
I
yi
11
01
p.
..p.
A
0.1
0
O HWt
H
1
k0
-I-
00k
H M4.m
"
kM
G) 4-1
roco-om
Moo
.4
Nn
-7 M
• • ' •
•"•
C0
0 0 00 0
0
ONO
0. ... %.0 LC \
00\ CH \ID N0
.. ..
.. ..
.. ..
H" -
•• ..
• "•
i
N 00 oo oo
,-1 00 00 00
H --...ri"... ....7-. ...\
... re)... CN
N M ,-4 Cv 0\ H
NN
1C6N
1.(101
•• • •
4.
a) a
+3Pi H
o
O
•• ' •
d 00
C) 0
la, -t,,PC.
..
M
+3
at
00
...1-0,
Hi 003
if\to, M\O
I-- H1\
HH
HI HI
i-I H
,9 00 0 0 00
41
-1 0
42
...
H K1-.7 ri1
MH
Wt^00
00
• •
O
4,7,,
oo
oo
-1-co
nreN
K1 K1
oo
0101
MH
WNW\
oo
oo
no
nrc\
M 00 \OM
lf\CO
88
0.1\0
00\0
rt-Nrcn
--
.
00 00 00
00 00 0
C--N NO 1-1-07
^ ft
00H 0CM
LC\M\
-7 rf1
•• ••
•• ••
••••
0 PC \
K1 0
H K1 0 ON
HH HH
HH
00 00 00
00
00 00
00
.4',1 NM NO
w n nal mm
NH
88
1.1-NN tr\01
**”
**”
QC- 1/40\0
mn con
oo
oo 00
oo oo
00
00
g
0
A.
d
H
-6
H
LC1 NO
•• ••
00
00
IC\ N
.
00
OQ
wn
wm
• n
MN WH
--1-n
0\ c0
K1 0\
HO
00
CN N
-.1HO
00
•• ••
00
00
• • • •
00
00
H ‘.0
\ON
WNW
oc\N
•• ••
nn NH
mn mn
oo
oo
oo oo
• • ••
00
00
\ON
ft I%
a)
14
NN
IC \
HH
00
0
0
0
•• ••
1.4
m
4-,
00
00
Mre),
0N
Kl
•• ••
c0
t00
00
00
00
tr\tc\
OM
00
00
WM
00
tc\
•• ••
ON t-- ON t--
00
00
\OM
MH
WNW\
00
8••°
M
•
00
00
M\D
OQ
00
H1/40
•• n
MH MH COM
WNW\ WNW\ re\N
•• ••
•• ••
if\
C10\ .
\
g
0
0 "-I
O +2
$-n
A3
•• 0
•• •• •• •• •• ••
O
I
H
O
W
ra
Ati
A3
0
0\
N-P
A3
A
3
43
;4 a)
A3
LC\
0
Pa 4-,
A
0
0\
3
A
3
1)•a +)
0
$40
0
$.1
A3
•
0 0
0 0
O
C340
+3 0
0
4,
n
rd
0
mn
.. ..
rf \
•
0
0
H
0
rd g
Table 7--Result, of bolt-bearing testa of parallel-lamlnated 112-114 laminate. Diameter of bolt and thickness of laminate were 1/4 inch
Ep,clment Width: End : Edge : leaning :
Proportional
MaXImum
:W.
:
: die- : di:- :strong-tn.-2:
limit
:. toad
:tante.1114nueR1
•
Xmfor- : 5treee : Defer- : lean,,
1 nation 1
: batten :
1
t 2
:
;
4
5
:
6
:
7
:
A
:
9
----------_. 2-
t•-- •
•
In
91.
In.
I.
4.
3
4.
1
1
iTanellelrailf.: Ape:einem : width: Ent : 5dgm : Bearing : ?rmportlsaml : Maximum
4. etrwoo: nre.1.
:
Er,
, dl.- : die- Istrenglala
19015:
load
lee net :
.
.
4tanoa-1:tanee31
:section: r Defer- 1 Etrese t Defer- : Barest:
.•
.
.
I
..
maticca :
: m%taen 1
t
.
.
-
•
1
1 :
, /D
: 11 :
12
1
13 : 14 : 15 :
:
18
i7
18
1
:
20
1
•. .
:
p.
.o.l.
...
P.a......:
III,:
in, ;
:
In. :
P...1. r
End distance teats
In.
;
P...1.:
In.
:
: Teel:lie:Peal1 itrOME : m,i
1 On east :
: anacticor
a
:
--.1
•
21
22
P-11.1.:
P.m.i.:
Edge distance test.
Dry, 9 . 0°
0-9-101 :
1.225: 0.15 a 0.49 1 22,980 : 5,890 : 5 : 0-9-1
103 : 1.232: .29
.49 a 0.24152
1 0.0054 r 31,130 : 7,920 : a .
3
105 : 1.04. .46
.49 •
.0097 : 02800: .0081 : 38,900 : 9,880 : :
5
107 : 1.234: .62
.49 : 43096 : .0058 : 28.350
.0105 I 44,880 :11,400 : 12 . 7
109 : 1.100: .73 a .42 • 57 2 210 ; ,0100 : 37,210 :i .0143
: 48,530 :14,270 1 8 :
17
111 : 1.255: .91
.49 : 36,960 : • .0142 : 50,040 :12,70o :
8 :
t
.
•
•
1
:
:
.
11
13 • 1.234: 1.05
1
.49 1 39,920 2 .0077 ; 31,620 , .0162 : 49,800 :12,650 : C : 13
a
t
15
.
•
;
.
i
:
21
.
:
•
I
:
:
.
:
23
,.
:
:
:..
•
1
25
.
..
:
a
•,
.•
:
r
..
:
::
:
i
27
10.757 t 1.00 : 0.25
37,430 : 0.0065 : 50,520 : 0.0122 : 42,330
20,870 : E
: .761 1 1.00 2 .26 : 35,820 : .0076 : 32,130 : .0128 ; 43,050 : 21,060 ; E
: .756 : 1.00 : .25 : 37,500 : .0090 ; 35,480 a .0117
41,450 , 20,480 : E
.746 a 1.00 : .25 : 38,150 : .0069 : 29,840 : .0115 42,900
21,620 2 E
:1.103 2 1.00 : .43
41,270 : .0086 a 36,510 ; .0151 1 51,900 ! 15,210 1 E
.
t
;
;
.
t
.
:
:1.105 : 1.00 ; .43 : 39,040 : .0080 : 33,470 : .0155 : 52,430 :15,330 a 0
:1.106 I 1.00 1 .43 : 38,270 : .0070 ; 29,920 ! .0157 : 51,500 :15,040 :
:1.103 : 1.00 : .43 : 37,010 : .0092 : 34,650 : .0182 : 51,810 1 15,180 : C
:1.486 : 1.00 1 .62 : 30,810 : .0092 : 29,030 I .0177 : 48,470 : 9,80o ;
:1.488 : 1.00 2 .62 : 31,260 : .0090 : 29,920 : .0192 : 50,790 : 10,260 a C
:1.489 ; 1.00 : .62 : 33,050 : .0108: 35,940 : .0165 . 48,750 : 9,840 : C
:1.488 : 1.00 : .62 . 33,730 : .0102 : 34,510 I .0167 : 49,570 a 10,010 :
•
.
.a
1
8
1
2
1
c
:
:
1
•
c
_
c
0,
90-9-101 : 1.248: .15 : .50 •
.po% : 22,640 : .0030 1 22,640 : 5,670 • t : 90-9-1
• .628 a 1.02
.19 .0073 : 31,010 : .0079 : 31,710 : 20,970 5 E
103 : 1.247: .31 . .50 .2048 : 28,460 • .0060 : 30,910 : 7,750 • 9 • 3
• .629 : 1.00 : .19 .0063 2 26,670 : .0081 a 30,750 2 20,280 : I
105 1 1.245: .46 : .50 8032 : 27,420 i .0075 i 37,820 : 9,5005 •• .625
: 1.00 I .19 : 25,300 : .0078
E ..0060
31,460 20,970 : 0
107 5 1.245: .62 : .50 t 41,950 : .0070 , 31,750 : .0104 : 42,620
:10,710 : 1 : 7
: .632 : 1.00 a .19 1 .0076 : 31,080 i .0082 : 31,870 : 20,860 : E
109 : 1.244: .75 : .50 I 44,880
.0:b : 28,020 : .0119 : 45,910 :11,550 . I :
:1.000 : 1.00 : .37 39,120 : .0084 e 34,540 t .0124 : 44,980 a 14,990 :
11
I
,
1
.
13
: .995 : 1.00 a .37 : 37,430 : .0084 : 33,730 r .0148 : 47,710 1 16,010 : I
111 : 1.232: .91 : .49 : 39,060 : .0060 : 25,100 • .0148 : 49,180 :12,520 a C : 15
: .995 : 1.00 : .37 : 44,100 : .0064 : 28,920 I .0114 : 46,590 • 15,630 a E
113
1 1.233: 1.05 a .49 : 59,460 t .0068 1 28.020 : .0144 ; 47,700 :12,130 ; C
1
17
: .993 a 1.00 : -37 : 40,880 r .0085 : 33,73o a .0124 : 45,460 : 15,300 .
•
:
:
:
a
.
.
.
r
r
.
a
.
:
:
I
:
2
:
.
1
1
•
a
21
:1.359 : 1.00 : .55 1 32,700 : .0107 : 36,510 2 .0146 : 46,190 : 10,410 : C
•
•.
1.
:
.
:
.
.
.
1
a
23
.
:1,354
;
1.00
;
.55
a
35,420
;
.0103 : 36,360 1 .0160 . : 48,060 1. 10,880 : C
.
..
1
:
1
.•
:
/
25
:1.341
:
I
1.00
i .55 : 40,480 : .0071 I 28,57o : .0146 : 48,73o a 11,070 : 2
t
;
1
a
1
..
.•
:
:
27
:1.345 a 1.00 a .55 a 34,400 : .0094 s 33,600 : .0157 : 47,680 1 10,890 t C
1
1
.
.
1
1
;
I
:
,
I
a
.
Dry, G . 45°
45-9-101 1 1.242: .17 : .50 1 24,940 a .0030 1 10,980 1 .0128 2 28,390
1 7,160 : N,E : 45-9-1
103 : 1.235: .31 : .49 1 34,230 ; .0053 1 22,130 t .0184 : 41,030 :10,410 : E3
3
105 : 1.231: .47 a .49 ; 40.160 a .0052 : 23,620 ! .0190 : 50,790 :12,940 : C,N 1 11
1
a
;
2
-
•
:
1
13
107 : 1.249: .62 : .50 2 .0054 : 23,440 1 57,030 :14,270 : C
09 : 1.247: .76 : .50 2 39,2W : .0072 : 29,920 1 .0174 : 50,870 :12,750 : C 2 .21
1
111 : 1.239: .92 : .49 : 34.470 : .0091 1 31,620.a .0185 a 51,620 :13,050 i C : 23
1 .742 : 1.00 : .25 .0057 i 30,040 : .0079 : 36,36o a 18,440 : 8
: .747 : 1.00 r .25 : 30,590 t .0096 : 34,82o 1 17,520 : 8
1 .858 : 1.00 2 .30 : 37,000 1 .0068 1 26,090 : .0116 : 40,710 t 16,740 1 0
: .855 : 1.00 a .30 : 37,110 : .0084 : 32,130 r .0121 ; 42,090 : 17,390 a 8
.
.a
.
.
1
i
:1.251 : 1.00 : .50 : 35,340 : .0075 a 27,310 a .0187 a 51,410 ! 12,840 : C
:1.252 : 1.00 : .50 1 31,340 : .0117 : 37,250 : .0192 : 51,820 a 12,920 : C
Wet 0 . 0°
0-9-102 1 1.233: .16 2 .49 104 : 1.232: .30 a .49 106
:1.227; .45 a .49 •
1
.
.0042 : 19,370 ' 1,920 a N
.0060 : 27,050 • 6,890 : 2 •
.0066 : 29,800 : .0084 : 33,020 : 8,450 2 E :
.488
.12 •
• .645 : 1.01
.20 •
: .807 : 1.02 : .98
• 0-9-2
.
.
.
2
; •
•
4
6
:
108 : 1.228: .62 : .49 : 36,680 : .0060 : 25,300 : .0108 : 38,340 : 9,800 : C :
110 : 1.231: .73 : .49 : 35,390 : .0070 : 28,120 a .0120 : 39,450 1 :10,050 a C a 112 : 1.234: .91 a .49 : 32,760 1 .0074 : 26,770 : .0148 : 40,790 :10,360 : C t
114 a 1.235: 1.07 I .49 : 32,760 : .0075 : 26,770 : .0137 : 38,190 : 9,720 1 C :
,
a 1.00
.
;
1 .0736 : 13,280 : -0033 : 19,770 : 20,760 : E
.0030 a 1 8 ,180: .9)5.5 i 30,670 s 19,410 : E
y)050 : .0061 : 21,880 : .012f. : 37,340 2 16,760 : E
i
.
.
:
.
.
: .988 1 1.02
•
E 40,160 p
.37 •
21.100 : 1.03 : .42 : 34,882 / .0069 : 25,580 : .0152 : 40,310 :
:1.220 : 1.01 : AO 1 33,600 E .0060 : 23,550 : .0153 : 38,910 :
5 : 30,20o 1 .X197 : 28,460 : .0149 : 38,580 :
:1.332 : 1.01 : .,
8
10
12
14
2
13,600 : c
11,860 r C
10,020 a C
8,910 a c
i
Wet, 8 = 90°
1
90-9-102 : 1.246: .15 • .5o
.0036 : 19,600 • 4,920 1 I . 90-9-2 • .495 : .98
.12 a .0034 I 12,800 : .0058 : 19,920 2 20,330 f E
104 1 1.247: .51 • .50 • .0031 t 20,720 : .0052 : 25,420 • 6,370 1 C a 4
• .647 a .99 a .20 '
.0056 a 21,600 : .0090 : 27,520
:37:00
106 2 1.246: .47 1 .5o •
.0055 a 27,310 : .0082 : 31,810 : 7,980 : 5 : 6
: .812 1 .99 : .28 : 31,470 : .0054 a 22,310 a .0107 : 32,270 : 14,350 ; E
.
..
.
a
.
.
108 : 1.245: .62a .5o -
• .0060 : 26,770 '
35,280 : 8,870 : C :
•
8
: .988 : .99 1 .37 : 28,210 : .0060'. 19,120 a .0160 : 34,380 I
110 : 1.246: .75 : .50 : 33,770 : .0060: 23,35o : .0114 : 36,960 10
:1.100 : .98 1 .42 : 31,270 : .0058 a 19,840 i .0125 a 36,110 , 10,620 .: c
112 : 1.232: .92 a .49 : 53,670 : .0071 : 26,560 : .0134 : 38,050 :
9,280 :: CC::
: 9,690
12
:1.222 : 1.00 7 .49 : 31,410 : .0053 : 18,470 a .0126 1 36,220 : 9,320 : 2
114 : 1.232: 1.05 : .49 ; 32,710 : .0067 : 25,100 : .0125 ; 36,710 : 9,340 a c : 14
:1.327 : .98 a .54 : 29,270 : .0055 : 19,350 : .0127 a 34,270 : 7,950 ; c
a
a
.
Wet, 9 . 45°
45-9-102 : 1.243: .15 t .50 : 22,240 : .0040 1 12,000 2 .0140 : 24,800 : 6,240 1 N I 45-9-2
104 : 1.228: .29 a .49 1 26,670 : .0040 t 14,290 : .0200 I 33,020 : 8,440 1 N,C a
4
.
:
:
a
:
r
.
2
106 1 1.235: .45 : .49 : 30,780 : .0064 f 22,660 a .0172 a 39,530 :10,040 1 : C x
6
108 1 1,249: .61 : .30 1 33,200 : .,0030 a 19,530 a .0163 a 43,050 :10,770 i: C
110 : 1.251: .73 1 .50 : 31,540 : .0070 : 23,720 1 .0162 : 40,240 , :10,040 •: C a 10
112 : 1.234: .90 : .49 2 30,750 1 .0072 : 22,130 t .0170 : 39,840 :10,120 : C :
12
a
a
a
=Distance from end of specimen to circumference of bearing hole.
Distance from edge of specimen to circumference of bearing hole.
2Bearing stress at a deformation of 0.01 inch.
= cruehing under bolt hole;
Z M 86507 F
N
failure to end; E failure to edge; and
S
failure toward edge.
: .649 1 1.01 a .20 .0048 a 18,820 a .0065 a 23,450 : 14,690
1 .807 : 1.01 a .28 1 30,780 1 .0071 a 23,440 a .0112 :33,360 : 14,970
:
.
.
.
:
a
.982 : 1.00 a .37 1 29,800 : .0081 :24,310 a .0167 :39,140 :13,360
:1 : 21/6,
1:
; 1.01 i .42 : 30,200 : .0076 : 25,300 a .0177 a 41,030 a 12,120
: 1.02 1 .49 : 30,560 : .0054 : 18,250 : .0169 a 41,050 : 10,540
:1.330 : 1.02 1 .54 a 29,720 : .0058 1 18,970 : .0170 : 40,40o : 9,350
5
:8
a
a
C
IC
IC
Table 4.--Reeclts of bolt-bearing teete of parallel-laminated 181-114 laminate. Diameter of bolt and thickness of laminate were 1/4 inch
.
.
.
•
.
: Tens ile7Ye.11 Neal/cum
:
:/enelle..1711-: Specimen:Width : EMI : 2:12r , Bearing : ProportIonal
1
Maximo/
Specimen : gidth : End ; Edge : Bearing : ProportloM41 1Pad
limit
:
dl,- :mtrecgtkl:
Wo. ;
load
: etre.... Wei;
die- , dl.- :ctrangthl:
limit:
:-..---_- ..... , ...... --.--.....! Z.d,', l 't I
;
Itancol:t.ccuZ:
Z
um
filiti
:
:cancel:buccal':
t
•
. Defor- : Strom. : Defer- : Strum. . asellon:
.
.
.
:
:
.
.
: Defer- t Stream : Defer. : Strada :section:
•
1
.
: action :
: Motloo :
:
:
:
:
,
t
:
..
•
: matt= :
7 tratIon ;
:
:
No.
:
1
z
. dte-
:
2
•
:
:
4 :
3 :
:
:
.
5
.
:
•
t
6
.
:
7
:
8
;
9
,.! 10
.
121,
: P.m./. [ 1E.
1 P a 1
•
1 18 1
.
E2
• i' LP- 1. - :
!
: 14 : 15 :
•
•
•
:
1 13
15
•
a
.
1
17
,
IE,
:
.
:
18
1
:
•
•
I
P...I.:
19
:
:
In.
: P...1.; p.a.t.:
.
20
!
:
21
1 22
--......
. Edge distance tests
End distance tests
Dry, 0 . 0°
1 0.999 : 0.10 : 0.37 21,540 ; 7,190: N : 0-24-1
3
0.0044 : 27,000 : 0.0052 , 30,130 1 10,040: N •
: 1.000 • .22 • .38 5
.0054 . 30,130 1 .0078 : 36,490 : 12,130: N .
: 1.002 • .30 • .38 7
.0052 : 31,800 : .0098 : 42,850 : 14,2401 ii,c . : 1.002 • .39 • .38 •
11
0063:36,670: .0092 :48,330 ; 16,110: 0,N 1 1 1.000 : .50 • .38 a
a
.
.
;
i
;
.
I
13
31,540 0 .0120 : 50,460 : 16,820: C :
111 : 1,000 : .6o . .38 : 46,220 : .0061
15
113 1 .998 : .69 : .37 : 42,980 : .0080 t 36,360 t .0140 : 51,160 E 17,100: C : 17
.
;
21
:
:
•
.
-
t
:
••
••
23
•.
.
•
:
•
•
25
•
.
•.
•.
:
.•
:
•.
••
27
••
:
.•
.•
*
•.
0-24-101
103
105
107
109
1
1
.
a
:
.
Dry,
• 0.0051 : 33,200 . 0.0053 1 34,020 : 32,590 : E
: 0.511 : 0.75 : 0.13
.0067 29,310 • .0076 i 35,170 : 34,620 : E
t .504 : .75 ; .13 .0079 . 32 1 620 : .0077 : 34,850 : 33,770 : E
.508 : .75 : .13 • .0069 1 32,480 1 .0069 : 35,380 : 34,290 : E
.508 : .75 : .13
: .698: .75: .22 :38,670 : .0094 r 39,000 : .0135149,790127,7901 E
a
:
t
1:
.
1
.
: .696 : 73: .22 : 37,770 , .0104 : 39,480 : .0163 : 49,270 : 27,620 : C
: .698 : .75 : .22 : 42,250 : .0090 : 39,830 : .0143 : 51,600 : 28,800 : C
: .692 : .75 : .22 : 39,740 : .0078 : 33,620 : .0146 . 50,690 : 28,670 : c
•
47,750 : 18,90o : c
, .881 : .75 ; .32 •
: .880 : .75 1 .51 : 55,600 1 .0099 : 34,480: .0148 : 47,500 : 18,850 : C
( 2 ; ;;;:it .1 .0141 : 49,350 : 19,770 : c
: .874 : .75 s .31 : 37,58o ! : 4
• 49,780 : 19,82o : c
, .878 : .75 ; .31 •
0 - 90°
• .0045 : 20,080 : .0072 : 31,300 : 29,980 7
.511 : .75 : .13
90-24-101: 1.000 • .10 • .38 • 1 .0030 : 20,570 .... 6,860: N • 90-24-1 .0953 : 22,780 .0081 7 31,980 : 30,060 .
.516 : .75 : .13 3
.38 •
1
103: 1.003 •
.0055 : 27,980 : 9,290: 2 '
.0074 1 32,130 : .0076 ; 32,120 : 30,300
.515
:
.75
:
.13
,
5
.0060
:
33.470
!
.0069
:
35,730
105: 1.002 • .32 • .38
•
i 32,220 : 30,400
-
7
:
.515
:
.75
E
.13
107: 1.003 : .40 : .38 : 40,000 : .0061 : 32,0787 1 .0105 . 41,010 • 13,620: N,C :
49,780 : 27,550 :
17 1 .702 : .75 : .23 : 41,240 : .0070 : 33,780 : .0135
1 .0085 : 44,440 : 14,730: C,N :
109: 1.004 : .51 : .38 . t ::
1
.
1
.
1
.
:
1
.
.
I
.
:I
11
:
.697
1
.75
:
.22
:
39,820
:
.0088
:
37,170
:
.0140
;
49,470
: 27,680 :
111: 1.001 1 .60 i .38 : 42,920 : .0074 4 35,000 1 .0119 1 46,750 : 15,560: C :
13 : .701 : .75 . .23 : 40,090 : .0064 : 29,200 • .0157 1 48,500 : 26,880
113: 1.005 : .71 : .38 : 43,350 : .0074 : 33,470 : .0134 : 47,620 .15
: 15,760:
C
:
: .7011 .75 : .23 : 43,360 : .0070 : 32,740 : .0127 : 48,410 : 26,850 :
.
21 1 .874 : .75 : .31 : 40,000 : .0080 : 35,400 7 .0128 : 49,030 : 19,640 r
..
..
•
•.
.•
:
.•
:
:
..
23 , .879 2 .75 : .31 : 33,780 : .0102 : 39,110 : .0132 : 44,890 : 17,850 :
•
.•
2
2
.•
.
;
:
:
.75 : .32 : 42,310 : .0084 : 37,330 .0160 : 49,780 : 19,72o :
25 : .881
.
•
•
.
:
1
1
.
•
.
:
.
.75 : .32 : 41,430 : .0086 : 37,500 : .0140 : 49,370 : 19,530
•
27 11
:
.882
•
•.
.•
.
:
.•
:
:
x
11,880:
N
:
1
f
Dry, 0 -
45*
.0059 : 29,200 : .0079 : 31,060 : 20,280
45-24-1 t .633 t .75 : .19 .0030 1 10,390 • .0080 • 21,560 - 7,11021
45-24-101: 1.004 1 .10 x .38 .0076 :30,360 : .0085 : 32,050 : 20,710 3 1 .637 : .75 : .19 103: 1.003 ; .15 1 -38 : 25,780 : .0037 I 12,070 : .0137 1 30,780 1. 1! 250: 18.8 : E
.75
:
.29
:
32,410
:
.0078
7 29,460 : .0164 : 47,500 : 20,540 11
:
.828
79o.
2,1
:
,
.30 : .38 : 31,360 : .0052 : 18,640 : .0158 : 41,530 : 15
1051 1.003
.75 1 .29 : 38,840 : .0059 : 30,360 : .0126 : 46,070 : 19,930
13 : .828
.35 s .38 : 36,690 : .0074 : 28,100 : .0146 : 44,210 : 14.600: 0 ,N 1
107: 1.007
.
1
1
.
:
1
.
.38 : 36,330 : .0040 : 16,330 , .0170 : 45,550 : 15,120: 0,0
109: 1.003 1 .39
21 : 1.015 : .75 1 .38 1 37,440 : .0072 1 29,960 : .0212 : 52,070 : 17,020
,
,
;
.
.
.
•
23 : 1.016 : _75 : .38 . 36,730 : .0077 : 30,090 : .0182 : 46,810 : 15,280 111: 1.003 1 .49 : .38 : 41,470 : .0050 : 24,490 : .0184 : 51,350 : 17,050: C :
N
•
11
R
0
i
:
i
1
c
.11
....2
.0048 : 18,180 : .0077 : 26,230 : 31,990 : R
.455 • .74 : .10 .0024 • 16,530 r .0030 : 16,530 : 5,350: N 1 0-3.-2
0-24-102 • .997 • .10 ' .37 '
-
: .0056 : 26,200 1 .0096 : 32,490 1 31,730 : 2
.75: .13 t
7,920:
.0027 : 23,870 1 .0042 . 23,870 :
104 : 1.003 : .22 • .38 .
I
.
•
.
:
/
.0046 : 29,790 ; .0050 : 29,790 : 9,8903
106 : 1.003 : .32: .38 : .561 : .74 r .16: 32,350 : .0052 : 22,610 : .0118 : 33,740 : 27,120 :
6
i
•
.0099 : 33,170 r 11,050:
108 : 1.002 • .42 • .38 •
.75 E .i9 : 32,330 : .0055 : 22,410 : .0140 : 35,090 : 22,500 E C
54
.640
:
.0060
:
29,880
1
.0093
:
37,340
:
22,4201
110 : 1.002 : .5G 2 .38 . .70e ; .73 E .23 : 30,750 : .0050 : 22,910 : .0105 : 31,100 : 17,200 :
10
I
.
1
1
•
1112
2
r .747: .76 : .25 : 30,480 : .0062 : 22,910 : .0110 : 31,450 : 15,820 :
: 1.005 : .61 t .38 : 37,930 : .0036 : 16,530 r .0096 . 37,930 • 12,560:
1114
4
: .807 : .77 : .28 : 32,000 : .0050 : 26,090 1 .0105 1 32,520 1 14,600 : 2
: 1.004 : .71 1 .38 : 37,530 : .0066 : 27,980 1 .0100 : 37,530 : 12,7.40:
Wet. 0 . 90'
11
C
:
C
r
.73 : .10 1 .0058 : 21,370 : .0066 1 23,590 : 28,490 : 2
.457
5,50.01 0 1 90-2a-2 .0031 : 16,560 : .2233. 16,360 90-24-102: 1.003 : .10 : .38 .0037 : 14,590 : .0083 : 28,240 : 27,360 : K
.76 . .13 1 4 ; .508
2,5001 i •
.0032 : 22,570 . .0037 : 22,570
104: 1.002 i .22 : .38 :
:
;
:
:
•
•
1.0
:
:
8,990
:
.0052
:
26,920
:
.0044
:
25
320
,
06: 1.002 : .30 : .38 1
30,040
:
.0068
: 24,030 : .0102 : 30,470 1 23,730 1 0
;
.16
1
6
:
.571
.
77
9,7581
0,2
.
.0052 : 25,210 1 .0073 1 29,330 : 108: 1.002 : .39 1 .38 8 : .640 : . 77 I .19 1 31,210 . .0062: 25,000 : .0093 . 31,210 : 20,000 7 C
.0058 : 25,830 . .0094 1 31,250 : 10,370: 0,17 : 110: 1.003 i .49 1 .38 10 , .700 : .77 : .22 29,830 : .0054 ,. 20,870 : .0102 : 30,000 , 16,660 ; C
.
.
.
.
.
1
T
12 1 .746 .76 : .25 : 28,260 t .0060 1 21,740 : .0098 1 28,260 : 14,250 : 0
112: 1.003 . .61 : .38 : 31,580 : .0056 : 25,000 -.0113. 32,580 1 10,820: C .
14 : .809 . .78 : .28 : 31,090 t .0043 1 18,340 : .0094 a 31,090 : 13,910 ; C
114, 1.002 : .69 r .38 : 33,220 : .0056 : 25,100 : .0100 : 33,220 . 11,050: C , 1
''91!"11:.0020 1 9,320 1 .0051 : 19,920 . 13,490 : 8
45-24-102: 1.003 : .10 : .38 , 14,17o : .0015 : 4,350 : .0109 : 14,170 : 10011, N : 45-24-2 : .619 : .76 : .18 .0041 , 15,130 1 .0088 : 27,390 : 14,390 : 1
4 : . 726
. 77 • .24 1 104: 1.006 . .21 : .38 1 22,980 1 .0025 : 9,360 1 .0124 : 24,430 1 8,0801 N : 6
:
.857
:
.75
:
.30
:
30,290
i
.0058
: 20,080 . .0131 : 34,480 1 14,200 : 1
106: 1.002 . .26 ; .38 : 27,510 1 .0036 1 13,500 : .0138 : 31,050 1 10,500:11,0 1 .
.
:
•
1
1.
•
•
108: 1.005 . .34 . .38 : 31,460 : .0036 : 14,630 : .0150 : 34,230 : 11,500:0,1 : .985 : .75 : .37 i 31,630 : .0032 : 13,390 1 .0156 : 36,820 1 12,520 : C
8
1
110: 1.004 : .40 1 .38 : 28,820 7 .0078 : 25,310 . .0162 I 36,730 1 38,180:0,E :
,820
:
11,100 : C
37
:
.0040
:
15,970
1
.0126
:
10
:
1.102
:
.75
:
.43
:
38,50
0
.
.
11
t1
1
:
z
.
12 : 1.160 : .73 : .45 : 3e,890 : .0050 : 20,000 I .0143 1 37,500 1 10,300 : C
112: 1.002 : .50 : .38 I 30,770 : .0061 : 22,670 : .0190 : 37,570 12,500: C 1
e
-Distance from end of specimen to clrcumference of bearing hole.
D istance from edge of specimen to circumference of bearing hole.
Bearing etrees at a deformation of 0.01 inch.
crushing under bolt hole; N - failure to end; E failure to edge; and 8 - failure toward edge.
Z M 865o8 F
Table 5.--Results of bolt-
tests of croes-leminated 1 -114 laminate. DinMeter of bolt and tbicknem of laminate were 1/4 inch
Xenia=
:Tonsi1e:Talk.
: T.,,..ii.:lail: Specin=a : Width : End : Edge T 1k...r1nk: Proportional :
Specimen: Width : Han : Edge : 13sarlt Proportional : Maximum
load
: etreem : urel
limit
wt ,.... : um.:
No. :
: die. : di.- .Str.ngthAl
No. :
I Me- : die- :streagth2:
Limit
bond
-. _-...: on not
:
:temcal:tenceI:
•
:tarnal:tnnOeg :
.
en net :
•
1
: Defer- 1 atrium : /mfor- 1 8tres. . •14:C•AnIE
: Defer- : &ma im : Date,- s . 05rons -motion:
.
.
: antic: :
:
1 nation:
:
:
:'
r
nation :
. nation :
--: .
.
I-
19 : 20 : 21 : 22
:
1
17 :
:2 : 3 :4: 5
: 6
:
18
17
: 8
: 9
: 13 : 14115 : 16
10 ;11: 12
.
.
.---.... .
. in. : In. 1 Im, : P.S.1. : It. In. . P.11.1.: In, Pet, P.s.1.:
: y..: :. : In. . P.a.t. r P.M-1..i
: I. : In. . In. : P.m.i. :
1
Edge ail:ranee trate
End distance taste
Dry, 0 = 0°
26,450 1 34,620 :
r
i
: 0.441 1.00 1 0.10 0-25-101 : 1.005 t 0.12 : 0.38 • 7 7 0.0030 : 21,620 : 7,16o : N ' 0-25-1
. 2.10154 :26,750,37,3607
103 : 1.006 . .22 • .38 • .0058 : 30,300 ; 10,020 : 2 .
3
0.0059 ; 27.350 : .0059 :28,030 : 38,090 :
: :t;?,
1:,..
D° ',. '23 105 7 1.004 . .30C .38 •
- 0.004-8 • 25,6L0 : .0075 : 37,35o 10 , 3 9 0 : 2 -
.0100 : 44,030 , 14,6107 : N.0
: 20.510
: .o064 : 3o,000 : 39,680
1.00 1 -09
• .439 ,.0046
107 : 1.004 : .39 : .38 : 44,030 :
11 . .553 C 1.00 1 .15 :
.
.
.0092 . 54• 4. 50 : -0099 1 42,020 . 34,670 :
:
,
:
109 : 1.003 : .50 : .38 : 44,430 : .0062 : 32,340 : .0108 : 46,470 : 15,430 1 C ,
13 . .550 1.00 : .15 : 39,660 : .0076 : 32,070 . .0113 : 42,780 : 35,650
15 : .547 1.00 : .15 : 39,150 f .0090 . 38,300 : .0120 : 44,68o : 37,610 r
111 : 1.007 : .63 : .38 : 44,94-0 : .0070 : 54,040 : .0128 : 49,790 ; 16,440 : c :
.0078 : 30,640 : .0139 : 44,680 : 35,690 :
113 : 1.011 : .70 : .38 : 45,420 1 .0072 : 35,590 : .0133 : 52,800 t /7,350 : C :
17 : .563 1.00 : .16 : 35,40o
•.
21 . .872 1.00 : .31 : 34,960 : .0084 : 50,250 :
t
•
i
•
1
:
T
23 . .865 1.00 . .31 : 39,490 : .0091 : 35,599 t .0140 : 45741g : 3210:;7I
•.
:
.
g1 :
:
25 : .863 : 1.00 : .31 : 35,320 : .0104 : 37,450 i .0I59 : 49,870 : 20,330
;
.
i
i
:
.
:
27 . .863 : 1.00 : .31 : 33,900 : .0114 : 38,989 ; .0166 : 50,510 :,20,600
•.
1
:
.
C
C
C
Dry, 0 = 90°
.0452 : 26,450 : .0064 : 31,160 r 42,100 1 2
.435 : 1.00 f. .09 90-25-101: 1.001 : .10 : .38 .0035 . 19,670 • 6,550 : N . 90-25-1
3 , .439 : 1.00 : .09 : 30,950 : _0091 C 31,540 . .0106 , 32,120 : 42,480 : E
103: 1.003 : .21 : .38 .0057 : 28,920 : 9,600 4 2 :
- .0056 : 24,070 : .0083 : 29,880 : 39,940 : 2
.0068 : 35,80o • 11,86o - 2 105: 1.004 : .30 : .38 •0055 : 26.450 1 .0068 : 32,070 : 42,420 : 2
7
.1419 : 1.gg : .09
09 '
107: 1.003 f .41 : .38 .0080 : 42,020 : .0081 : 44,710 • 14,850 : 2
11' .552 : 1.00 1 .15 : 37,510 : .0080 : 34,020 : .0135 : 46,970 t 38,880 : E
:
.
:
:
.•
:
17: .558 : 1.00 : .15 : 35,850 : .0060 : 24,900 1 .0165 : 46,560 : 37,790 : r
•
•
109: 1.003
. 48,690 . 16,16o : C:
.38 -
:
.
C
:
.
C
:
111: 1.005 : .62 : .38 : 45,900 : .0082 : 37,610 : .0120 : 50,170 . 16,610 : C :
13 : .548 1 1.00 : .15 : 95,340 : .0106 : 37,190 : .0135 t 45,540 : 38,200.: C
113: 1.004 : .72 : .38 : 42,560 . .0062', 30,770 : .0140 : 50,850 : 16,870 : C t 15 : .550 : 1.00 : .15 : 30,410 : .0091. : 36,360 . .0192 : 49,670 :41,400 : C
.
.
.
:
:
.
.
.
C.
C
, 48,800 : 19,800 : c
‘866 1 1.00 ! .31
:
21
.
i
.'
:
:
..
1
:
23 : .867 ; 1.00 : .31 : 34,140 : .0107 i 36,459 r .0155 : 49,040 1 19,850 : 0
1
25 : .869 ; 1.00 : .31 : 35,980 : .0:597 [ 36,820 : .0145 : 47,360 : 19,120 : c
*
.•
:
1
.•
:
:
.
.868 : 1.00 : .31 : 39.360 : .04.66 : 35.250 : .0154 , 47,230 1 19,100 : C
1
:
4
:
7
s
:
:27
Dry, 0 - 45°
0065 : 26,390 : .0052 : 26,390 : 17,880 r I
45-25-101: 1.003 : .10 : .38 •
6,72o , 2 ' 45-25-1 • .619 , 1.00 : .18 .0016: 6,690: .0090 : 20,250
29,500 : 20,04o : 2
3 : .618 : .99 : .18 103t 1.004 : .23 : .38 : 10,670 : .0037 : 15,000 : .0156 : 35,500 11,780 1 N:
11 : .as7 : 1.00 : .31 : 35,00o . .0095 : 33,330 : .0157 : 47,000 : 19,040 : E
105: 1.000 : .30 : .38 : 33,519 : .0033 : 18,110 i .0157 : 42,550 : 14,200 , N : 13 : .866 : 1.00 . .31 : 34,670 : .0092 : 33,330 r .0143 : 44,670 : 18,130 : 0
:
.
.
.4
1
.
.
.
.
.
-
i
.
•
.0060 :26,450: .0144 : 48,930 : 16 :6220
107: 1.002 : .40 : .38 :39,6-(0
70 . . C ,
:
21 : 1.117 1 1.00 . .43 : 33,900 : .0104 : 35,590 . .0171 : 52,030 :, 15,000 : C
109: 1.001 . .49 : .38 : 41,740 : .0066 : 28,100 . .0138 : 49,920 : 23 : 1.108 : 1.00 . .43 : 33,200 : .0108 . 36,510 : .0164 : 46,890 :0-3,660 : C
111: 999' .61 : .37 : 42,070 : .0053 : 24,900 2 .0145 . 50,210 : 16,76o , C : 7
:
C
:
.
1
.• :
- o°
Wet
.0054 : 18,410 : .0068 : 20,330 : 33,450 : 2
.402 • .99 : .08 0-25-102 : 1.002 :
.38 5,490 : 8 : 0-25-2
16,510
4• .0066
: 24,070
. .0075 : 26,390 : 32,500 : E
.453 • .99
: .10 •
104 : 1.001 : .21 : .38 .0034 : 22,550
2,500 , 2 .
.0044 : 19,-090 m .0084 : 29,540 : 28.780 : E,C
6
.507 : 1.00 : .13 106 : 1.003 : .29 • .38 •
.0042 : 26,380 • .0054 • 27,320
9,070: N:
:
..
..
:
.
.-
108 ; 1 003 : .39 : .38 .0077
:
9,790 : 2 :
29,450 :
,
:
8 : .675 1 1.00 : .21 : 31,670 1 .0048 : 19,170 : .0102 : 31,920 . 18,770 : c
.
•
:
C
.
10 : .646 : .99 : .20 : 30,380 : .0059 : 21,100 : .0112 : 32,660 : 20,620 : C
110 ; 1.004 : .50 : .38 : 31,950 : .0058 : 28,810 : .0070 : 31,950 :
112 : 1.004 : .61 : .38 : 32,970 : .0038 a 18,410 : .01C9 : 32,970 t i
12 : .705 : 1.00 : .23 : 32,940 : .0068 : 25,210 : .0100 : 32,940 1 18,100 : C
14 : .752 : .99 : .25 : 30, 360 : ..0061 : 21,760 f .0110 : 32,220 : 16,050 : C
114 : 1.001 ; .70 : .38 : 53,140 •
• .0089 : 33,140
0)(.1iE '''.
1
Wet, 0 . 90'
.0040 : 15,900 : .0059 : 23,010 : 36,100 : E
90-25-102: 1.002 : .09 • .38•
.0025 : 15,450 : 5,140 : 2 • 90-25-2 • .401 : 1.01 : .08 .
.
.
.,
:
.•
.
:
•.
104: 1.002
.22 • .38 •
.0051 : 22,010 : 7,320 : N :
4 : .453 1 .99 :: .10 : 29,790 : .0052 : 21,760 , .0080 : 29,790 0 36,680 r c
106: 1.004
.30: .38 • .0038 . 23,430 : .0053 : 26,95o 1 8940: N :
6 : .5o6 : 1.01 : .13 : 30,340 : .0036 1 18,490 : .0081 : 30,340 : 29,620 : C
108: 1.004
.39 • .38 •
.0054 : 25,320 : .0071 : 29,450 1 9,770 : 71,0 :
8 : .675 : 1.00 : .21 : 31,210 : .0046 : 23,430 : '.0082 : 31,210 4 18,350 : C
.
. .
:
.
.
10 : .643 1 1.00 : .20 : 32,450 : .:0051 : 25,730 : .0103 : 32,780 : 20,850 : C
110: 1.004 : .49 : .38 . 32,340 : .0052 . 27,230 : .0080 : 32,340 : 10720: CC
12
: .698 : 1.00 : .22 : 30,460 : .0058 : 22,410 ; .0091 : 30,460 ; 17,000 : c
112: 1.004 : .62 . .38 : 33,190 •
.0108 : 34,210 1 11,340 : C :
14 : .747 : 1.00 : .25 : 31,200 : .0056 : 21,580 : .0095 : 31,20o 4 15,700 1 C
114: 1.004
.7o : .38 : 33,390 . .0054 : 20,340 : .02_10 : 33,900 : 11,2 5o : 0 :
7
:
sittLL-125:
.0030 : 12,660 : .0049'. 19,160 : 12,840 : 2
45-25-102: 1.006 : .10 : .38 : 14,810 : .0018 : 6,580 : .0100 : 14,810 : 4,90. , 2 : 45-25-2 : .623 1 1.01 : .19 .0049 : 17,650 1 :0075 : 25,380 : 13,270 r 2
4: .728 : 1.01 : .24 •
104: 1.005
.20: .38 •
.0036 : 11,570 1 .0096 : 23,040 : 7630: NC
6 : .862 : 1.00 : .31 : 30,340 : .0074 : 24,370 4 .0120 : 32,690 : 13,350 : E,C
106: .993 : .30 . .37 : 25,930 : .0045 : 14,810 : .0184 : 30,950 1 10,410 : C ,N :
.
.
.
.
.
:
.
:
108: 1.000 : .41 : .38 : 30,790 . .0054 : 18,260 : .0140 :
35,930.
11,980
: c d, :
8 . .990 : 1.01 : .37 : 29,410 : .0066 : 21,850 . .0135 . 34,450 :1 11, 650 : C
.
.
.
.
:
:
:
10 . 1.098 : 1.02 . .42 s 30,000 : .0048 : 15,970 1 .0145 : 35,46o : 1 10,450 : C
110: 1.000
.51: .38 : 29,520 : .0066 !
: 24,190
:
.0139
: :34,520
11,510
: c ,N .
12 : 1.160 : 1.00 : .45 : 28,950 : .0088 : 25,940 : .0164 1 37,150 : 10,200 : C
112: 1.002 . .61 : .38 : 3:4040 : .0063 : 95,483 : .0126 : 34,660 i 11,520 : N o N :
=Distance from end of specimen to circumference of bearing hole.
2Distance from edge of specimen to circumference of bearing hole.
hearing stress at a deformation of 0.01 inch.
4
^C - crushing under bolt hole; N - failure to end; E - failure to edge; and 8 • failure toward edge.
Z M 86509 F
N
P4
fa
U
0
" • -•
A5
.1 E
. 4.5
V
0'
r.
04
Fdi W M
O o oN
O o Io.-
.4
r
NI .NI we;
CIN
e1
0
teN
C.3
03
W 6G
aa
0.N1
HI
O
t
H
02
44
9, 4,
IN
1 Nd
eln
491
a
H
0
0
-I
,0
••
• , ••
O
t-- r-
-4' CC) 0 .,'
ri
I .I r-I
..
•
0
.•
..
..
..
01 01
.. .. .. ..
;n-n .-3
't7=-2
8. 8. 8.
0 HI HI
0 0 0
iK§Ng
•
47 111\i; -17
.-I
07-1 I-I I-1
•• •• •• •• ••
ri
g
n
4518
•• •• •• •• ••
0 0 0
O 0 0 0
01 .-I CU
PO
CO "00 1C\
g
0
3
14 -1
8-1
r-I 1 ri
0
0
A 1.
i
7 -1 7
El
H WS LIN
:`,.'
S
2FIR
0 0 0
•.
•• •• •• ••
IAN
01 18
p
.-i
.4
1
41
4
.21
N-1 1 1 4 1
• • • • • • • • • • • •
84-01
.54'
2
ot.--*
P8
. 1 N 01
0:1
2
4
-
.1
0 IC\ 11 N
C1
ro
•• C.) C.)
4 .4 .4
11
a)
00
CO 03
o ?dm
A.
CD
rr)
.21
.• .• •. .•
t- ti
t.21 .21 4
8 ti ne
8 P°
`..0
N
.21
88
8
Iri o 0 \
1- 0- 0-
Cr-I
•• • • •• • •
N
. 2 2
H
.1 N-1
e-1
a,
2
•• •• •• ••
4 .4
•• • • • • .•
NNN
.4 4 ..4
•• •• •• •• •• .•
2 Al
VD 0
4 1 erl
0
1,1•11t1
t•-
1
,o
0.1
Ill HI 0 cA
O
..........
5 .:
..3e.
a
ED
••••
l0
•• ••
0
8§
11-).
1/40
nnn
101
'0
8 4O
8 30'..i: 01
WI
UN
.,n
0 0
NUN
K1
01 01
k)
.• •• .• .•
0
4-
g
5
▪
‘.0
O
. 8 . 0. 8.
O
44
8 8o
o
t-
Sc"
44
Rid
.
LA 0
O
5
.0
4 A9
1-1
...1
a
P.
al
O
•
§
r=con
44
8
8 8
8
0
10
-
01 0\
0
03'
o;
HI 01 g
1,11CI
M
0 C.) U
•• • • • • • • • •
0 0
11-l4
4 rE
4q
1,0
A A
Pa
0
0
•
°
a:
g
H
••
N
II
' R
H 1
1 1
1,r‘
nu,
I-7 4. 4
1
UN
-7
a'
-t
P. 1
C.) C.)
A' ,0
'o
''
CU
0
I
r-I 01
.4
.7F 01 01
CO
• - C; c;3. •2;_.; 8 Ar
, .-1
1
Ct
a.
@
i
43 U0
r-1
•
0] 0 0 0
II
1
co
u„.
.--iCa 0 0 0
.
88 .R8
g
.4 888
ON ON -711•1N
CO CO CD
410 NN
s° -1;
1/4040 00.330:1
VC\
-11(1'
•• •• •• .• ••
a
ym
.4
8
ro
NO
••
8
Pn
0 0 \0
w 01
SO.4"
40 M1
-0
CU 1',1
• • •• • • •• • • ••
Cn1
I,"\ \
•• • .• .• • •
".4"-;
•7:
4.
r
10,05010.
,8
\1 "
'24 '721
§Elk
•
N^ sus
4
.-1'
tl
1/40 leN
szl
R.0
•
:?4‘,9\
• • • • •• •
CO -7 CV 0 0
O 00
•
• 0•
000
So
0
00
o o o
o
'
Kn 01 r-1
i
0 CO
lel
UN
•
00
0.‘
1-1 1-1
0 0 0
8•
3 ' 9.
0•4
0
•0
44
•
XI
°,0 5ta 5
yW
•
4
000
- .... .. ... ..
.. .. ••
r.1
2P N P
ON Ch 0, ChCO
H ri ri H
.4 .4 4 .4 .4
n-•/1
H 01 09 1/40 C.-
C-. C-.. C-
In 0
8 4.4 .-i .4
•• •• •• •• •• ••
,e 2 8
NN 8 8 8
HI
0
g
10
.
,0
°'
c‘l
O
r-1 IC \
el
4-1
rn
.4 4 4
.4
•• .• .. .. ,
r.
01 HI
••
.-I
CO CO 0 \ CO 0\
r-I .-1 ri H
121 4 14 .4 121
.4 .4 .4 4
•• •• ,• .• ••
.i .'"AN
W5
••CON
•cg
•
lt1 OS 01 C
.-
..4 .•4
.. .. .. .. ..
'11:Z r x
PIE' Pie-
8Z 282
0/
01
01 01
•• •• •• •• ••
cn 1
.1 .-. .c.
SIM
&
8
..-1 •• •• •• ••
.-1 A 4
.. .. .. .. .. ..
ai ai 4 4 (4
.. ..
As •••1 .. 111,1
e@l Os
it: II, u",
• • • • •• • • • •
N
oi
•• •• •• ••
4-
4,
3 o'I
2
#
5.1)
Jr,
0
1 ,9
1
II
W
0
W
000
0
0c0C0,-1\0 -3n
Cu‘On
IN H
00
n
0
0
HH
n
000 0
M
88
HN
0
W
O
HW
0
4.
Ha) 03
V H0
a) 0 4.)
0 4-$.,1 g
E-1 a) 0 a)
al
00
nNn c0
Nnn n
O
H
al
10-000
1 M 0'CO'N
0
.. .. .. .. ..
000
0
NnN
Ont.--1M
NO
,; HtNNal
HI
3
i
II3
0-'4
.0
k-,1
3, 0
0H
H
m0
O
D.
4)
.. .. .. .. . ..
W
Ckla
j1
1
4
4.3
O
H
07
---..-,
..-
41 44
I
O
4 .
PI
1
CnI
H
a
0
g
m
.41
g
,c1
H
O
+5
-I
H
0a) 0Z
CD
rHI
LO
.. .. ..
I
H
M
000\
Nn
n
\O
0
,-i
-4
o
QO 0H
wc0
it\
H
cOM
0CU
H
‘0
•
-.
000
OC-0
N NH
\D0N
000
O
H\O
H\Oo
2
`RWA
wW0
00
\On
v0-.3
22
00
0
CV
H \
nc0
n
HN
n
M n.30
t--\0t.-
‘2\C'D
00
H8
00 0
0
nnOl
0n 000
n Mn
M
0'D
In
N H r-I
H
00 0,
888
8
2 co
n-3
0
HH
s.,On
n
nC--\.0
0-3N 00
H-3
n
n
R
'.00
21
-3n-3
N
00
000
00 ...3nn
000
00 0
0
o00
00 00
000 0
0
• • •
0
----0.1cN
0)
N
NC--
cOHN0
Hn \el
nnn
H HC-0
Hn \O
Hnn
... .n
0
.. .. .. .. ..
cu0 000H
CU
H0CuC)
Cu LC\
i,'W ‘tki
WW 1'.
. . 0 H
HH H
H 444
HH (1
,21.-1.-I H
.. .. .. ..
.. .. .. ..
-1-1C.- -1-N -1-r-SE Wor,\R
tN CVLC\ trN
F1.1 PI
.A
,c
. . .
.
HH
..-14.4
H H
0 HI H H
0'
.. - - 6n
001 .. .. -- .. - n
0H
cico...9 -1 N-3
ast- Hn ..... Hn n
4 Hn1
1
4 4
0 H
n
K.0 nI
43 e-,I
. 14-N
., -3
4.)m
_1-
O
.. .. - .. 4.0
ns
k 0
ci, un-a
• C) C.) ^ C.) 0
- C-3 0
W W W C-)
W IM
1/40
1
CO
0
O
4-,
HI
gn
„
A4
•
H
LP.
H
N li
.
3I
In
On
0 C-) C.)
I
I
H
4-4H
-,I-H
0
H
rid,
ri1
ri
..
..
..
..
..
..
opH
0H CO 4. 00
0 0 80
OR 00
00
000
.4 A
H03030 g0 4.
H
CUNO
pc,
w0
4,a-.11
@teN incl.
'0O
-1_1- 8
0,...
.. ..
..
CrN
g
Li
0
ONO
\
O
n 1MI.4---1
4.0 4-, g 0 H
\003s CU
H
ri H
H
HHH
E-10)0a)
0
H .
.. .. ..
010
w
11
0
H
01 R.
,-,+.
HCD
4-,0
9
-91
.0
g
00
co
4.)
ca
O
4-3
,5
0
4.f4
00
O
0 4.>
H
H-'
I
8.HI
40
0
0
.-14.)O
A,
4_,,
pC4R
ri_,
O
N,••43
II
IR
1
N
a)
HI
EA
4-1
-0
..)
rd
r'il
C)
CA
H
a)
4.)
0
CWO
00 00
n8
"ANNN aL Tck;
0MONM
nn
HnON
g
K000
.,,,...4 w
0
000
. . . 0
2c0
reN
.L-4.4\1
H oo
o
9
-
.. ..
0
t"-
s.0
s.O.H...7
s.0
N CV N H
0N8
L7-IN
HN NN
0
0
00
000
00
%. 0 H -1-0
0 2R
11-\
lfl re \
0 00
8
NN
HIn OWN
01 1--1
'.0 0M
C.-
N
000
00 0 00
0
.. .. .. .. ..
0
00H
n ...3n
CV 0 Pr\
141
\Onn
NN n
O
0
ql
CQ
\000
Nain ti
n•
nc00
Mr\
CU
4-ref0, '
0
p. 1 0g
.
-,.
.0
1
i
rd 0)
0
01.41g
+,
,0
0
47
ill
.0Hm .,1 .
W'±3,1; 4.)g
a)
W
2
0
0
.. .. -
a)
co
H
0
44
00 44 404 04 eti,
82
GO
4,
0 ,-i
ii-i 4-)
A'
CV
N
M
C.-
n
nt,,r-I
1
les
.-1
H
M%
0
0
00
00
0
0 00
00
sc., sgsci.
AA
AA
N uD\D
NN
\O
c0
C-01
1C% \Or-
%ow
NO
N- CY%
M
n
NN
H
N-00
rnnn
HHH
H
H
n n-3
N- C-C.-1 .4 4
CO CO
CO
C.-- MM
MM
44 44
.....
.. .. .
g-jAR
1I
-4
PilI
ir\
-1.
,.0 -i•
t
H
tr.\
0
0/ 4'H
t-- t-.4 4.4
N
N
rMi
0
x'44
m
••
CA
000
w 0
••
A.4., ...I2
0
EA 0 0
on, o 0
08
N
0,
PA
CO m 0-0
U.
OS'
0
ta
0
o o o o
H o o al n
n.0 H \ID %0 CH
... ... ...
\D ‘.0 ON H 0
CM In In-1- .,-.7
CO
H
O
FT1 0
CY
14-N
CU 0 en CO 0\
N r-1 rA
re\
n o o
n.0 a\ al
0\ In ON
o
0 o 0 n
CIN In CV 0 t--
r-- CU 0 N-1/4.0
N-l0 H H K\ -4-
K1 0 c)n cd 0.
CU
In 01 N N
...I.
re,
In
S
O
0
0
H
0 0 0
H ON VD
CO CO
ON
... ...
al
\.o 0..
H CU
PC\
•
rT4
rI
i;:t 8
0
N- OD 0 In In
in 0\ as as 0
0
.--1
0 00000 0
0
H
AA
0
H
4 El
0
A
0
,-1
0 0
,
Le
N,8
0 8 8 8 8
.3‘. 8
0 0
In 0\
H
rl
CU
In
0 0 0 0 0
0 0 0 0 0
. . .
LIN
0
....,
• In In 0
,e,
0 1 H
0 0 0
•
0 0 0 0 0
Ln .1) IC\ K \
4n.0
ON H co
^ H^ \.0
CU
• HI ai N CU
PI
R.
H
2
OD H ,
CU In
HH
0 0
I"- ON
H
CU
N CU
C.-
H
CV rr-N
0 0
0.0
000 0
0
0H
8
0
.(21
000
00
0
0
0
0 0
IC\
8
0
rd
$
cD
•n•-9
DO •0
n1.
;1
-1.$
•„,,
g
+.3
4-$
rH
e."
.rr
aO
A
td 0
0
rH
P.
4-'
ri
O
H
W
N-00
H N K.\. re.
. te\.
0
H
N U\ N
HN OHIn
00 000
• ••
• • •
rl rA rA rl H
N[ 0
8 N
HNC
• • •
0 H rA H rl
CO tr \ ON
0'. LC \ a.
H H
-N n
rA rA H
8
Hqq
4,
.$1
CO
4
0
*LC\
H 0. ON N- N- -I.ON rA
In
u
H H
H
I .
II
CV
CM
IC1
CD
rn
CD
I
4
in
0
-.1.40
CO,
H 00 tHH .*
H CU In re. 1"-N
N u-. C-
N
N rAN0IN
O 000 o
• • •
1-1 ri H H
H
01
H
H H H
ts- 0 N 1.P. in
CO 0 H 9 at
H rl H r-I
0 N
o u-n
.. .. .. ..
..
@ 4,?, (0 , :.1
al
In
1
0
li;
PI)
ZZZ 00
0 0
T c.... Z
0
00o
in 00cy
• -A- re.
oo
on
N-
0 0 0
Lc,
--1-
11
CID
0N
H
CU
)4-.
I
4-3
O
I*
.. .. .. ..
Lc.
14. 0
0
^ c-)
C.1
mgC
H 0 .3. q
rt
0 0 n-n
1-. 0 0
17
.wTh
0 0 0 0
EA
0
Pi
••0
CO
4,
8
ILI
N 0 N
,,-., al -I'
8 rsZ
.
0 0
H H N\ .0 OD CO . In N
H H •CUN
HH
-I. v
H In in CT CT'
HI r-I H
H 1-1
0 0 0 0 0
H , 0
H CO LC\ • H H
cciHH . CC"; r-1
N N-1 rel
rf
0 0 -
CU 0
O n.
CV 0
-I- --I-
0 0 0 0
0 0
C.- 001.1/4.0
0 0
0
in
\0 ON K1 C.-- CU
in 0
ON N PC \ 03' CO.14. r-r
HNN NN
In rn
0
11-n
t-
rn-n
tl
V.
8
1 •!7-1
0
A
I.$
O
A
E4-
/-1
0
N
-I- in
--7 , C71 H
H 0 0 0 0 0
.
0
•• •• •• ,•• •• ••
0 0 0
0 0
N1 CU 0
ON CU
0.1 -7 CO
--ILC\
HN
N 01: N N
0
41
4-1
Ly
A
0
LOm I.1
q
W 'p
.
• " Nl Pr\
0 Q 0. 0
9 9
0
0
0
LC \ 0
HH
0CI
0 CU
.4 K\
O
O
0 0
L"--
Ls- PC,
N
0.
0
IC\ 4 Pr; NCO
-4' -1-..4-
4-41 K1
II-\
441
8 00°
H H
0 0
0 0
CU In
H
0N
N CU
0 0
in -I'
ON
\O
H H
03
K1 LC\
‘.0
8▪
8
80
.-$1 H
n.0 10
K\ K\ IC\ L.- t-
.4.' .0.4-
IC\ PC\
H H
\0
\D.
C- IC\ H
CO 0
•
N CC- CU
8
•
•
0
0
0
- •• •• - •• ••
I
-V
\ID C- t•- ^
-7 U\ Lrl CO 0
• • •-
,• •
O
NCO
H1;11
0
n Lt-N
•
421 n21
t- C- -7 -7
\
NN
H H H r-1 H
H
in
t-n
I
.1:, -..1. CU
coI
Lc-NH K1
IC\
.--1 H
PC\ IC1
•
CU N
rA rl H H
PC\ OrN tC\
01
Pe \
I
CO 0
C.- NC\
CU
K.\
1
U\
-1-
I
CU -
re \
i\
o
-7 \D
ri 4-1
ON
ON
r-I H H
•
CU
FC \
-1.
rcn
Table 9.--Results of exploratory bolt-beexing
tests of 112-114 laminate of ,j8inch thickness, tested with 1 2inch pin
..
:
Specimen : Width i
No,
•.
:
(1)
.:
:
End : Maximum
stress
: distance :
:
:
(3)
:
1 /-12.. :
..12.4.
:.
(2)
(4)
P.s,i,
:
16,960
:
0-48-2x : 1
•. 1-1/2
0-48-1x : 1-1/8 : 1-1/2 :
22,020
0-48- 6x : 1-3/8 :
1/2
5x : 1-3/8 :
3/4
4x : 1-3/8 : 1
17x : 1-3/8 : 1-1/4
18x : 1-.3/8 : 1-1/2
19x : 1-3/8 : 1-3/4
26,950
28,760
29,660
0-48-3x :
7/0 : 1-1/2
:
:
:
•.
I
0-11- lx : 1-3/4 : ;
2x 1 1-3/4 : 1-1/4
3x : 1-3/4 : 1-1/2 0-48-20x : 2-1/4 :
1/2 :
3/4
21x : 2-1/4 :
22x : 2-1/4 : 1
llx : 2-1/4 : 1-1/4 :
12x : 2-1/4 : 1-1/2 :
13x : 2-1/4 : 1-3/4
:
25,450
29,020
29,190
30,080
29,920
32,400
33,750
23,410
29,350
32,720
35,200
36,720
37,130
0-48-26x : 2-3/4 :
23,580
1/2 :
27x : 2-3/4 :
3/4
29,680
.
28x : 2-3/4 : 1
34,110
:.
14x : 2•3/4 : 1-1/4
•.
37,210
15x : 2-3/4 : 1-1/2 : 35,540
16x : 2-3/4 : 1-3/4 : 138,850
23x : 3
1 1-1/4
:
36,800
24x : 3
•. 1-1/2
. ,37,520
25x : 3
: 1-3/4
: .138,640
.Specimens failed under hole. Other specimens failed to edge,
Table 10,--Estimated minimum end and ed ge distance ratios required
to assure failure under the bolt hole, based on boltbearing tests of three laminates
.
Angle 1 Condition : 1/4-inch bearing
of
1
11/t = 1
:
;
loading :
:
End
: Edge
1
:
: 1/8»inch bearing
DA = 4
:
:
Edgo
s
: End
3 distance : distance : distanco : distanco
: ratio
: ratio
1 ratio
1 ratio
3
Dogroosi
s;
112-114 Laminate, Rosin 2
0
90
Dry
Wet
:
45
3
3.8
2,6
Dry
Wot
s
3,5
2.4
Dry
Wet
1
2.1
1,8
:
:
:
2.2
:
•
1,7
1.3
:
3
12.9
1.7
1.8
145
:
:
2.2
1,2
:
:
2.1
.5
1.7
1,5
s
1.6
:
1.3
-a.5
:
1.0
1.8
1,4
:
:
.9
.5
1,4
1.0
:
:
1.1
1.0
1.7
1,6
:
.6
.5
1
-1.6
11.6
:
s
1.1
1.1
1
1
181..114 Laminate, Rosin 2,
0
4
:
90
I
45
:
Dry
Wet
1
Dry
Wot
Dry
Wot
:
:
2.1
1.8
1
:
.8
.5
S
:
2,3
:
:
,9
.5
:
:
:
1,3
1.3
:
:
1,8
1,6
143-114 Laminate, Rosin 2
45
Dry
Wot
1.9
1.9
:
.7
:
t
3
.6
:
Dry
Wot
:
S
1.6
1.5
:
•
1.3
1.4
:
-Estimate based on limited data. See figures 8 and 10.
Figure 1.--Test set-up for bolt-bearing
tests of 1/4-Pinch laminates.
M 86182 F
Report No. 1824
Figure 2.--Test set-up for bolt-bearing
tests of 1/8-inch laminates.
M 86181 F
Report No. 1824
Figure 3.--Typical failures of glass-fabricbase plastic laminates tested in bolt bearing.
M 86183 F
Report No. 1824
-0
111, 1
4{
-
k ''-
9 0°
4 '1
•I
FA / LURE TOWARD EDGE
FA/ LURE TO EDGE
a
CRUSHING UNDER HOLE
E3 M B6180 I,
PA/U/RE TO END
,g
4-,
•
b0
cd
r-I
I
al
H
H
4-4
0
al
4+'
a)0
co
a)
U H
a)
a)
Pi H
oo H
cd
0
cd
;-1
-P
oo
4-)
rcl
O
4
4-1
rcl
4-)
-P
rd
Q)
c12
-4-'
ri
0
rin
g
q-1
0
C'
H
4-,
al
-.
P4
at
I
I
-4a)
F-1
••
4
2
a)
c.)
C..)
•H
g
4
4.)
a)
Z
-1-1
al
I
---...
• -I
0
rd
rci
0
a:
0
-,-.
co
a)
bD
0
03
,0
0
•-1
I
c0
----..
H
,
a)
4-)
0
0
•r-4
1-1
1
H
-0
4-,
•,-I
Go
0
H
-1-)
cd
g
9-1
0
r.T4
H
0 \
.-.1.
g
U
4
N-1
PT•4
Report No, 1824
4
'"
I-1
Z
Figure 5.--Effect of end and edge distance on the
ultimate stress in bolt bearing of parallellaminated 112-114 laminate. Diameter of bolt and
thickness of material were both 1/4 inch. Laminate
tested in dry and in wet condition.
M 86492 F
Report No. 1824
Figure 6.--Effect of end and edge distance on the ultimate
stress in bolt bearing of parallel-laminated 181-114
laminate. Diameter of bolt and thickness of material
were both 1/4 inch. Laminate tested in dry and in wet
condition.
M 86493 F
Report No. 1824
Figure 7.--Effect of end and edge distance on the ultimate stress
in bolt bearing of cross-laminated 143-114 laminate. Diameter
of bolt and thickness of material were both 1/4 inch. Laminate
tested in dry and in wet condition.
zm 86494 F
Report No. 1824
Figure 8.--Effect of end and edge distance on the ultimate
stress in bolt bearing of parallel-laminated 112-114
laminate. One-eighth-inch-thick laminate tested with
1/2-inch-diameter bolt. Laminate tested in dry and in
wet condition.
ZM 86495 F
Report No. 1824
Figure 9.--Effect of end and edge distance on the
ultimate stress in bolt bearing of parallellaminated 181-114 laminate. One-eighth-inch-thick
laminate tested with 1/2-inch-diameter bolt.
Laminate tested in dry and in wet condition.
zm 86496 F
Report No. 1824
Figure 10.--Effect of end and edge distance on
the ultimate stress in bolt bearing of crosslaminated
143-114
laminate. One-eighth-inch-
thick laminate tested with 1/2-inch-diameter
bolt, Laminate tested in dry and in wet
condition.
ZM
86497
F
Report No. 1824
;•4
•
co
a)
4
4-3
to
P.0
$4
H
0
O
N
do
4-)
H
0
O
c1-1
di
rd
0
r d
4-)
cti
QC
O
0
H -H
cri
H
•H
4-)
E-I
0
-P
r—i
H
4 4
0
C.)
0 0
=,—I
aa)
-4H
Report No, 1824
Report No . 1824