TORAY T700GC-12K-31E/#2510 - National Institute for Aviation

Transcription

Advanced General
Aviation Transport
Experiments
A – Basis and B – Basis
Design Allowables
for
Epoxy – Based Prepreg
TORAY T700GC-12K-31E/#2510
Unidirectional Tape
[US Units]
AGATE-WP3.3-033051-132
November 2002
J. Tomblin, J. Sherraden, W. Seneviratne, K. S. Raju
National Institute for Aviation Research
Wichita State University
Wichita, KS 67260-0093
ii
TABLE OF CONTENTS
1.
INTRODUCTION.........................................................................................1
1.1.
Scope ..............................................................................................2
1.2.
Symbols Used ..................................................................................3
1.3.
Acronyms and Definitions ..................................................................4
1.4.
References.......................................................................................5
1.5.
Methodology.....................................................................................9
1.5.1.
Test Matrix..................................................................................9
1.5.2.
Environmental Conditioning .......................................................11
1.5.3.
Fluid Sensitivity Screening .........................................................11
1.5.4.
Normalization Procedures..........................................................13
1.5.5.
Statistical Analysis ....................................................................14
1.5.6.
Material Performance Envelope and Interpolation........................14
1.5.6.1.
Interpolation Example.............................................................16
2.
TORAY T700GC-12K-31E/#2510 PROCEDURES AND PREPREG
PROPERTIES ...................................................................................................18
2.1.
3.
GENERAL......................................................................................19
2.1.1.
Materials...................................................................................19
2.1.2.
Lay-up/Bagging .........................................................................19
2.1.3.
Cure.........................................................................................20
2.1.4.
Non-Destructive Inspection (NDI) ...............................................20
2.1.5.
Tabbing ....................................................................................23
2.1.6.
FAA Test Coupon Conformity and Test Witness ..........................23
2.1.6.1.
Test Coupon Conformity.........................................................23
2.1.6.2.
Test Witness .........................................................................24
2.2.
Prepreg Documentation by Prepreg Lot............................................25
2.3.
Data Documentation .......................................................................28
TORAY T700GC-12K-31E/#2510 LAMINA PROPERTIES ..........................30
3.1.
Test Results ...................................................................................31
iii
3.1.1.
Summary..................................................................................31
3.1.2.
Individual Test Summaries.........................................................32
3.1.2.1.
Tension, 1-axis ......................................................................33
3.1.2.2.
Tension, 2-axis ......................................................................34
3.1.2.3.
Compression, 1-axis ..............................................................35
3.1.2.4.
3.1.2.5.
Shear, 12 axis .......................................................................37
3.1.2.6.
Shear, 13 axis .......................................................................38
3.1.3.
Individual Test Charts................................................................39
3.1.3.1.
Tension, 1-axis ......................................................................40
3.1.3.2.
Tension, 2-axis ......................................................................41
3.1.3.3.
3.1.3.4.
3.1.3.5.
Shear, 12 axis .......................................................................44
3.1.3.6.
Shear, 13 axis .......................................................................45
3.2.
Raw Data .......................................................................................46
3.2.1.
Raw Data Spreadsheets and Scatter Charts ...............................47
3.2.2.
Fluid Sensitivity Raw Data Spreadsheets and Scatter Charts ..... 102
3.2.3.
Representative Shear Stress-Strain Curve ................................ 107
3.3. Statistical Results ............................................................................. 109
APPENDIX A. PHYSICAL AND MECHANICAL TEST PROCEDURES ............. 118
A.1. Physical Properties .......................................................................... 119
A.1.1. Uncured Resin Content ............................................................... 119
A.1.2. Uncured Volatile Content ............................................................ 119
A.1.3. Resin Gel Time .......................................................................... 119
A.1.4. Resin Flow ................................................................................. 119
A.1.5. Uncured Fiber Areal Weight ........................................................ 119
A.1.6. Infrared Spectroscopy................................................................. 119
A.1.7. High Performance Liquid Chromatography (HPLC) ....................... 120
A.1.8. Differential Scanning Calorimetry (DSC) ...................................... 120
A.1.9. Cured Neat Resin Density........................................................... 120
iv
A.1.10. Fiber Volume ............................................................................ 120
A.1.11. Resin Volume ........................................................................... 120
A.1.12. Void Content ............................................................................ 121
A.1.13. Cured Laminate Tg by DMA ...................................................... 121
A.2. TENSILE PROPERTIES................................................................... 121
A.2.1. 0° (Warp) and 90° (Fill) Tensile Properties ................................... 121
A.2.1.1. Tensile Calculations .............................................................. 122
A.2.1.1.1. Tensile Strength (Un-normalized) ..................................... 122
A.2.1.1.2. Tensile Strength (Normalized) .......................................... 123
A.2.1.1.3. Tensile Modulus of Elasticity (Un-normalized) ................... 123
A.2.1.1.4. Tensile Modulus of Elasticity (Normalized) ........................ 123
A.2.1.1.5. 0° (Warp) Tensile Poisson’s Ratio .................................... 123
A.3. COMPRESSIVE STRENGTH ........................................................... 124
A.3.1. 0° (Warp) and 90° (Fill) Compressive Strength Properties ............. 124
A.3.1.1. Compressive Strength Calculations ........................................ 125
A.3.1.1.1. Compressive Strength Calculation (Un-normalized) ........... 125
A.3.1.1.2. Compressive Strength Calculation (Normalized) ................ 125
A.4. COMPRESSIVE MODULUS ............................................................. 125
A.4.1. 0° (Warp) and 90° (Fill) Compression Modulus Properties ............. 125
A.4.1.1. Compression Modulus Calculations ........................................ 126
A.4.1.1.1. Compressive Modulus Calculation (Un-normalized) ........... 126
A.4.1.1.2. Compressive Modulus Calculation (Normalized) ................ 127
A.5. IN-PLANE (IOSIPESCU) SHEAR ...................................................... 127
A.5.1. In-plane (Iosipescu) Shear Strength Calculations .......................... 128
A.5.1.1. In-plane (Iosipescu) Shear, Ultimate Strength Calculation........ 128
A.5.1.2. In-plane (Iosipescu) Shear, Modulus Calculation..................... 128
A.6. SHORT BEAM SHEAR..................................................................... 128
A.6.1. Short Beam Shear Strength Calculations ..................................... 129
A.6.1.1. Short Beam Shear Strength Calculation.................................. 129
APPENDIX B. MOISTURE CONDITIONING HISTORY CHARTS...................... 130
APPENDIX C. PHYSICAL TEST RESULTS..................................................... 140
APPENDIX D. STATISTICAL ANALYSIS SUMMARY ...................................... 165
v
APPENDIX E. METHOD FOR TRANSFORMING VARIANCES OF TEST
SAMPLES (SUPPLEMENT TO DOT/FAA/AR-47/00) ........................................ 175
APPENDIX F. RAW TESTING SUMMARIES ................................................... 181
APPENDIX G. DATES OF PANEL MANUFACTURE AND COPY OF FAA
FORM 8130-3 ................................................................................................. 214
vi
1. INTRODUCTION
This material characterization program was performed to characterize the lamina
properties of Toray Composites (America), T700GC-12K-31E/#2510, 150 g/m2,
unidirectional tape, herein designated P707AG-15. The P707AG-15 prepreg
material system designation shall be used to refer the material in this report. The
material qualification was conducted under FAA project number TC1616SE-A
through Lancair Company that wanted to use the aforementioned material
prepreg system on their LC40 aircraft.
This report contains the test results obtained from the tests conducted for the
material qualification of P707AG-15 in accordance with FAA Document
DOT/FAA/AR-00/47: Material Qualification and Equivalency for Polymer Matrix
Composite Material Systems and Toray Composites (America), Inc. (TCA)
Material Process Specification, TCSPF-T-UD06, Revision 1 dated February 4,
2000. Toray Composites (America), Inc. (TCA), Integrated Technologies (Intec),
National Institute for Aviation Research (NIAR) and Rose Consulting performed
the testing on the unexposed and exposed prepreg materials for lamina baseline
test properties in accordance with ASTM test methods, SACMA test methods,
and TCA test work instructions.
Three batches of P707AG-15 and the corresponding mixed resins were tested
for baseline test properties. The data reported herein will be used to set material
acceptance criteria for future material production and material receipt. The Raw
Test Data, Inspection Records, Fabrication Records, Processing Records and all
other relevant documents of this report, TCQAL-T-1013, are archived at Toray
Composites (America), Inc., and it is available only upon request.
The physical and chemical tests were performed on the mixed resins, the
uncured prepreg materials and cured prepreg laminates. The mixed resins were
evaluated for cured neat resin density. The uncured prepreg samples were
evaluated for resin content, fiber areal weight, volatile content, gel time, flow, IR
(Infrared Spectroscopy), HPLC (High Performance Liquid Chromatography) and
DSC (Differential Scanning Calorimetry). The cured prepreg laminates were
tested for fiber volume, resin volume, void content, cured ply thickness and Tg
(glass transition temperature) by DMA (Dynamic Mechanical Analyzer).
TCA Test Laboratories performed all the physical and chemical tests on the
mixed resins, the uncured prepreg materials and cured prepreg laminates,
except for fiber volume, resin volume and void content that Intec performed and
cured laminate glass transition temperature, dry and wet conditions, that Rose
Consulting performed.
TCA Test Laboratories performed the fabrication of all the test panels and test
specimens, ultrasonic inspection, chemical and humidity conditioning, except for
0° and 90° Compressive Strength specimens that NIAR tabbed and machined.
1
Also, the TCA Test Laboratories performed the attachment of strain gauges and
mechanical testing, except for specimens tested at –65 °F (Dry) that Intec
performed. Moreover, TCA Test Laboratories performed the fluid sensitivity on
one qualification batch by testing in-plane (iosipescu) shear strength only.
All TCA and Intec test equipments were calibrated with standards traceable to
the NIST.
1.1.
Scope
The test methods and results described in this document are intended to provide
basic composite properties essential to most methods of analysis. These
properties are considered to provide the initial base of the “building block”
approach. Additional coupon level tests and sub-element tests may be required
to fully substantiate the full-scale design.
The test methods and results contained in this document are consistent with MILHDBK-17-1E,2D,3E - Military Handbook for Polymer Matrix Composites. All
material, specimens, fixtures and test results contained within this document
were traceable and conformed by the Federal Aviation Administration (FAA). It
should be noted that before application of the basis values presented in this
document to design, demonstration of the ability to consistently produce
equivalent material properties as that evaluated during this program should be
substantiated through an acceptable test program.
2
1.2.
Symbols Used
ν12tu
µε
E1c
E1t
E2c
E2t
F12su
F13su
F1cu
F1tu
F2cu
F2tu
G12s
major Poisson’s ratio, tension
micro-strain
compressive modulus, longitudinal
tensile modulus, longitudinal
compressive modulus, transverse
tensile modulus, transverse
in – plane shear strength
apparent interlaminar shear strength
compressive strength, longitudinal
tensile strength, longitudinal
compressive strength, transverse
tensile strength, transverse
in – plane shear modulus
Superscripts
c
cu
s
su
t
tu
compression
compression ultimate
shear
shear ultimate
tension
tension ultimate
Subscripts
1
2
12
13
1 – axis; longitudinal
(parallel to warp direction of reinforcement)
2 – axis; transverse
(parallel to fill direction of reinforcement)
in – plane shear
interlaminar shear (apparent)
3
1.3.
Acronyms and Definitions
A – Basis
AGATE
ASTM
B – Basis
C. V.
CTD
CPT
DMA
Dry
ETD
ETW
FAR
FAW
Gr/Ep
NASA
RTD
SACMA
SRM
Tg
tply
wet
95% lower confidence limit on the first population
percentile
Advanced General Aviation Transport Experiments
American Society for Testing and Materials
95% lower confidence limit on the tenth population
percentile
coefficient of variation
cold temperature dry
cured ply thickness
dynamic mechanical analysis
specimen tested with an “as fabricated” moisture
content
elevated temperature dry
elevated temperature wet
Federal Aviation Regulations
fiber areal weight
graphite/epoxy
National Aeronautics and Space Administration
room temperature dry
Suppliers of Advanced Composite Materials
Association
SACMA Recommended Method
glass transition temperature
cured ply thickness
specimen tested with an equilibrium moisture content
per section 1.5.2
4
1.4.
References
ASTM Standards
D 792-91
“Standard Test Method for Density and Specific Gravity of
Plastics by Displacement,” American Society for Testing and
Materials, Philadelphia, PA 1991.
D2344
“Standard Test Method for Apparent Interlaminar Shear
Strength of Parallel Fiber Composites by Short-Beam
Method,” American Society for Testing and Materials,
Philadelphia, PA.
D2734
“Standard Test Method for Void Content of Reinforced
Plastics,” American Society for Testing and Materials,
Philadelphia, PA 1994
D3039
“Standard Test Method for Tensile Properties of Polymeric
Matrix Composite Materials," American Society for Testing
and Materials, Philadelphia, PA 1995.
D3171-90
“Standard Test Method for Fiber Content of Resin-Matrix
Composites by Matrix Digestion,” American Society for
Testing and Materials, Philadelphia, PA 1990
D3530-90
“Standard Test Method for Volatiles Content of Epoxy Matrix
Prepreg” American Society for Testing and Materials,
Philadelphia, PA 1990
D3531-76
“Standard Test Method for Resin Flow of Carbon FiberEpoxy Prepreg,” American Society for Testing and
Materials, Philadelphia, PA.
D3532
“Standard Test Method for Gel Time of Carbon Fiber-Epoxy
Prepreg,” American Society for Testing and Materials,
Philadelphia, PA.
D4065-93
“Standard Practice for Determining and Reporting Dynamic
Mechanical Properties of Plastics,” American Society for
Testing and Materials, Philadelphia, PA 1993.
5
D4473
“ Standard Practice for Determining Cure Behavior of
Thermosetting Resins Using dynamic Mechanical
Procedures,” American Society for Testing and Materials,
Philadelphia, PA.
D5379-98
“Shear Properties of Composite Materials by the V-Notched
Beam Method,” American Society for Testing and Materials,
Philadelphia, PA 1998.
E168
“General Techniques of Infrared Quantitative Analysis,”
American Society for Testing and Materials, Philadelphia, PA
1992.
E1252
“Standard Practice for General Techniques for Qualitative
Infrared Analysis,” American Society for Testing and
Materials, Philadelphia, PA 1995.
E1356
“Glass Transition Termperature by Differential Scanning
Calorimetry or Differential Thermal Analysis,” American
Society for Testing and Materials, Philadelphia, PA 1995.
SACMA Standards
SRM-1R-94 “Compressive Properties of Oriented Fiber-Resin
Composites," Suppliers of Advanced Composite Materials
Association, 1994.
SRM-18R-94 “Glass Transition Temperature (Tg) Determination by DMA
of Oriented Fiber-Resin Composites," Suppliers of Advanced
Composite Materials Association, 1994.
SRM-19R-94 “Viscosity characteristics of Matrix Resins," Suppliers of
Advanced Composite Materials Association, 1994.
SRM-20R-94 “High Performance Liquid Chromatography of Thermoset
Resins," Suppliers of Advanced Composite Materials
Association, 1994.
SRM-22R-94 “Determining the Resin Flow of Preimpregnated “B” Staged
Material," Suppliers of Advanced Composite Materials
Association, 1994.
SRM-23R-94 “Determination of Resin Content and Fiber Areal Weight of
Thermoset Prepreg with Destructive Technique," Suppliers
of Advanced Composite Materials Association, 1994.
6
SRM-25R-94 “Onset Temperature and Peak Temperature for Composite
System Resins Using Differential Scanning Calorimetry
(DSC)," Suppliers of Advanced Composite Materials
Association, 1994.
Toray Documents
TCSPF-T-UD06
“Torayca Unidirectional Carbon Fiber Preimpregnated
with Epoxy Resin Prepreg Tape - 250°F Curing
System Material and Process Specification,” Revision
1, Toray Composites (America), Inc., Puyallup, WA,
February 4, 2000.
TCWIN-U-C002
“Fourier Transform Infrared Analysis," Toray
Composites (America), Inc., Puyallup, WA, 1998.
TCWIN-U-C003
“Differential Scanning Calorimetry," Toray Composites
(America), Inc., Puyallup, WA, 1998.
TCWIN-U-C004
“High Performance Liquid Chromatography," Toray
TCWIN-U-M003
“Lay-up/Vacuum Debulking,” Toray Composites
TCWIN-U-M006
“Autoclave Curing,” Toray Composites
Inc., Puyallup, WA, 1998.
TCWIN-U-M008
“Panel Tabbing,” Toray Composites (America), Inc.,
Puyallup, WA, 1998.
TCWIN-U-M101
“Tensile Specimen Machining," Toray Composites
TCWIN-U-M102
“Compression Specimen Machining," Toray
TCWIN-U-M103
“Compression Modulus Specimen Machining," Toray
TCWIN-U-M111
“90 Degree Tensile Specimen Machining," Toray
7
(America),
TCWIN-U-M201
“Tensile Testing,” Toray
Composites (America),
Inc., Puyallup, WA, 1998.
TCWIN-U-M204
“Compressive Strength Testing," Toray Composites
TCWIN-U-M206
“Compressive Modulus Testing,” Toray Composites
TCWIN-U-M214
“Strain Gauge Attachment," Toray Composites
TCWIN-U-M215
“Laminate Density/Fiber Volume Testing," Toray
TCWIN-U-M216
“Strain Gauge Calibration," Toray Composites
TCWIN-U-P001
“Volatile Content," Toray Composites (America), Inc.,
Puyallup, WA, 1998.
TCWIN-U-P004
“Resin Content/Fiber Areal Weight," Toray
TCWIN-U-P007
“Gel Time," Toray Composites America), Inc.,
Puyallup, WA, 1998.
TCWIN-U-P008
“Flow," Toray Composites (America), Inc., Puyallup,
WA, 1998
Other Documents
FAA Document DOT/FAA/AR-00/47: Material Qualification and
Equivalency for Polymer Matrix Composite Material Systems, J.S.
Tomblin, Y.C. Ng and K.S. Raju, 2001.
MIL-HDBK-17 1E, 2D, 3E – Military Handbook for Polymer Matrix
Composites
8
1.5.
Methodology
1.5.1. Test Matrix
Testing was performed according to the test methods delineated in the test
matrix, with modifications as referenced in FAA Document DOT/FAA/AR-00/47:
Material Qualification and Equivalency for Polymer Matrix Composite Material
Systems. The test matrix for properties included in this document is listed on the
next page, with the following notation cited in each column:
#x#
where the first # represents the required number of prepreg batches, defined as:
Prepreg containing T700 12K graphite fibers from one mill roll, impregnated with
one batch of resin in one continuous manufacturing operation with traceability to
all components. The second # represents the required number of replicates per
prepreg batch. For example, “3 x 6” refers to three prepreg batches of material
and six specimens per prepreg batch for a total requirement of 18 test
specimens.
9
Table 1.5.1: Minimum Recommended Test Matrix and Standards Used for
Testing
TEST
0o (warp) Tension Strength
0o (warp) Tension Modulus,
Strength and Poisson’s Ratio
90o (fill) Tension Strength
90o (fill) Tension Modulus and
Strength
0o (warp) Compression
Strength
0o (warp) Compression
Modulus
90o (fill) Compression Strength
90o (fill) Compression Modulus
In-Plane Shear Strength
In-Plane Shear Modulus and
Strength
Short Beam Shear
Fiber Volume
Resin Volume
Void Content
Cured Neat Resin Density
Glass Transition Temperature
METHOD
ASTM D3039-95
ASTM D3039-95
ASTM D3039-95
ASTM D3039-95
SACMA SRM 1-94
SACMA SRM 1-94
SACMA SRM 1-94
SACMA SRM 1-94
ASTM D5379-93
ASTM D5379-93
ASTM D2344-89
ASTM D3171-90
ASTM D3171-90
ASTM D2734-94
--SACMA SRM 18-94
NO. OF REPLICATES PER
TEST CONDITION
CTD1
1x4
RTD2
3x4
ETW3
3x4
ETD4
3x4
1x2
3x2
3x2
3x2
1x4
3x4
3x4
3x4
1x2
3x2
3x2
3x2
1x6
3x6
3x6
3x6
1x2
3x2
3x2
3x2
1x6
1x2
1x4
3x6
3x2
3x4
3x6
3x2
3x4
3x6
3x2
3x4
1x2
3x2
3x2
3x2
1x6
3x6
3x6
3x6
One sample per panel
Supplied by manufacturer for
material
3 dry, 3 wet per prepreg batch
Notes :
1
2
3
4
CTD: One prepreg batch of material tested (test temperature = -65 ± 5o F,
moisture content = as fabricated, soak time at –65 was 5 min.)
RTD: Three prepreg batches of material tested (test temperature = 70 ±
10o F, moisture content = as fabricated)
ETW: Three prepreg batches of material tested (test temperature = 180 ±
5o F, moisture content = equilibrium per section 1.5.2, soak time at 180
was 2 min.)
ETD: Three prepreg batches of material tested (test temperature = 180 ±
5o F, moisture content = as fabricated, soak time at 180 was 2 min.)
10
1.5.2. Environmental Conditioning
All ‘wet’ conditioned samples were exposed to elevated temperature and
humidity conditions to establish moisture saturation of the material. Specimens
were exposed to 85 ± 5 % relative humidity and 145 ± 5 °F until an equilibrium
moisture weight gain of traveler, or witness coupons (1” x 1” x specimen
thickness) was achieved. ASTM D5229 and SACMA SRM 11 were used as
guidelines for environmental conditioning and moisture absorption.
Effective moisture equilibrium was achieved when the average moisture content
of the traveler specimen changed by less than 0.05% for two consecutive
readings within a span of 7 ± 0.5 days and was expressed by:
W i - W i - 1 < 0.0005
Wb
where
Wi = weight at current time
Wi-1 = weight at previous time
Wb = baseline weight prior to conditioning
It is common to see small fluctuations in an unfitted plot of the weight gain vs.
time curve. There were no fluctuations that made significant errors in results or
caused rejection in the moisture equilibrium criteria. Once the traveler coupons
passed the criteria for two consecutive readings, the samples were removed from
the environmental chamber and placed in a sealed bag with a moist paper or
cotton towel for a maximum of 14 days until mechanical testing. Strain gauged
specimens were removed from the controlled environment for a maximum of 2
hours for application of gages in ambient laboratory conditions.
1.5.3. Fluid Sensitivity Screening
Although epoxy-based materials historically have not been shown to be sensitive
to fluids other than water or moisture, the influence of some fluids other than
water or moisture on the mechanical properties were characterized. These fluids
fell into two exposure classifications. The first class was considered to be in
contact with the material for an extended period of time, and the second class
was considered to be wiped on and off (or evaporate) with relatively short
exposure times.
To assess the degree of sensitivity of fluids other than water or moisture, Table
1.5.2 shows the fluids which were used in this qualification plan.
11
Table 1.5.2: Fluid Types Used for Sensitivity Studies
Specification
Exposure
Classification
MIL-T-5624
Extended Period
MIL-H-5606G
Extended Period
Laboratory Grade
Extended Period
Fluid Type
Jet Fuel
(JP-4)
Hydraulic Fluid
(Tri-N-butyl phosphate ester)
Solvent
(Methyl Ethyl Ketone)
To assess the influence of various fluids types, a test method sensitive to matrix
degradation was used as an indicator of fluid sensitivity and compared to the
unexposed results at both room temperature dry and elevated temperature dry
conditions. Table 1.5.3 describes the fluid sensitivity-testing matrix with respect
to the fluids defined in Table 1.5.2. Engineering judgment and statistical tests
were used to assess the degree of material degradation. The results of this
screening are included following the data sheets in section 3.2.2.
Table 1.5.3: Material Qualification Program for Fluid Resistance
Fluid Type
Test
Method
Test
Temp.
(o F)
Exposure1
Number of
Replicates2
Jet Fuel JP-4
Hydraulic Fluid
Solvent (MEK)
ASTM D53793
ASTM D53793
ASTM D53793
180
180
Ambient
See note 4
See note 5
See note 5
5
5
5
Notes :
1
2
3
4
5
Soaking in fluid at ambient temperature (immersion).
Only a single batch of material is required.
Shear strength only.
Immersion duration = 500 hours ± 50 hours
Immersion duration = 60 to 90 minutes
12
1.5.4. Normalization Procedures
The normalization procedure attempts to reduce variability in fiber-dominated
material properties by adjusting raw test values to a specified fiber volume
content. Only the following properties were normalized:
•
•
0° (warp) & 90° (fill) Tensile Strength and Modulus
0° (warp) & 90° (fill) Compression Strength and Modulus
The normalization procedure was adopted from MIL-HDBK-17-1E, section
2.4.3.3. The procedure which was used to normalize the data is based on two
primary assumptions:
•
The relationship between fiber volume fraction and ultimate
laminate strength is linear over the entire range of fiber/resin ratios.
(It neglects the effects of resin starvation at high fiber contents.)
•
Fiber volume is not commonly measured for each test sample, so
this method accounts for the fiber volume variation between
individual test specimens by utilizing a relationship between fiber
volume fraction and laminate cured ply thickness. This relationship
is virtually linear in the 0.45 to 0.65 fiber volume fraction range.
Additional information is detailed in FAA Document DOT/FAA/AR-00/47: Material
Qualification and Equivalency for Polymer Matrix Composite Material Systems.
For all normalized data contained in this document, the test values are
normalized by cured ply thickness according to:
Normalized Value = Test Value ×
CPT specimen
CPT normalizing
where:
CPTspecimen =
Average Sample Thickness
# of plies
13
1.5.5. Statistical Analysis
When compared to metallic materials, fiber reinforced composite materials
exhibit a high degree of material property variability. This variability is due to
many factors, including but not limited to: raw material and prepreg manufacture,
material handling, part fabrication techniques, ply stacking sequence,
environmental conditions, and testing techniques. This inherent variability drives
up the cost of composite testing and tends to render smaller data sets than those
produced for metallic materials. This necessitates the usage of statistical
techniques for determining reasonable design allowables for composites.
The analyses and design allowable generation for both A and B basis values
were performed using the procedure detailed in section 5.3 of FAA Document
DOT/FAA/AR-00/47: Material Qualification and Equivalency for Polymer Matrix
Composite Material Systems.
1.5.6. Material Performance Envelope and Interpolation
Using the B-basis numbers, a material performance envelope may be generated
for the material system by plotting these values as a function of temperature.
Figure 1.5.1 shows an example material performance envelope using B-basis
values.
14
120
Actual Basis Value
Estimated Value
B-Basis Strength Values (ksi)
100
RTD
CTD
80
ETD
RTW
60
Material
Performance
Envelope
ETW
40
20
-100
-50
0
50
100
150
200
Temperature (o F)
Figure 1.5.1 Material performance envelope.
Since each specific aircraft application of the qualified material may have
different Material Operational Limits (MOL) than those tested in the material
qualification (which is usually the upper limit), some applications may require a
reduced MOL. In this case, simple linear interpolation may be used to obtain the
corresponding basis values at the new application MOL.
This interpolation may be accomplished using the following simple relationships
assuming TRTD < TMOL < TETD :
For the corresponding MOL “dry” basis value, the “interpolated” basis value using
the qualification data is
B MOL = BRTD −
(B RTD − B ETD )(TRTD − TMOL )
(TRTD − TETD )
15
where
BMOL = new application basis value interpolated to TMOL
BRTD = basis RTD strength value
BETD = basis ETD strength value
TRTD = RTD test temperature
TETD = ETD test temperature
TMOL = new application MOL temperature
For the corresponding MOL “wet” basis value, an estimated Room Temperature
Wet (RTW) value must be calculated. This may be accomplished by the simple
relation
BRTW = BRTD − ( BETD − BETW )
The “interpolated” wet basis value using the qualification data may then be
obtained by
BMOL = B RTW −
where:
(BRTW − BETW )(TRTW − TMOL )
(TRTW − TETW )
BMOL = new application basis value interpolated to TMOL
BRTW = estimated basis RTW strength value
BETW = basis ETW strength value
TRTW = RTW (i.e., RTD) test temperature
TETW = ETW test temperature
TMOL = new application MOL temperature
These equations may also be used for interpolated mean strengths as well as Abasis values with the appropriate substitutions. It should be noted that because
unforeseen material property drop-offs with respect to temperature and
environment can occur, extrapolation to a higher MOL should not be attempted
without additional testing and verification. In addition, the interpolation equations
shown above are practical for materials obeying typical mechanical behavior. In
most cases, some minimal amount of testing may also be required to verify the
interpolated values.
1.5.6.1.
Interpolation Example
This section provides an example of linear interpolations to a specific application
environment less than the tested upper material limit used in qualification.
16
Assuming a specific application environment of 150o F, Figure 1.5.2 depicts the
linear interpolation of the B-basis design allowable to this environment. Using
the above equations along with the nominal testing temperatures (see Table
1.5.1), the interpolated basis values at 150o F become
ETD
: BMOL = 75.106 ksi
ETW : BMOL = 59.746 ksi
120
Actual Basis Value
Estimated Value
100
CTD
B-Basis Strength Values (ksi)
RTD
80
ETD
RTW
60
ETW
40
20
-100
-50
0
50
100
150
200
Temperature (o F)
Figure 1.5.2 Example of 150o F interpolation for B-basis values.
17
2. TORAY T700GC-12K-31E/#2510 PROCEDURES AND PREPREG
PROPERTIES
18
2.1. GENERAL
All of the testing described in the report took place at Toray Composites
(America), Inc. in Tacoma, Washington, except for the following tests:
Test Laboratory
Integrated
Technologies
(Intec), Bothell, WA
National Institute
for Aviation
Research (NIAR),
Wichita, KS
Rose Consultant,
Half Moon Bay, CA
Test Property
acid digestions (fiber volume, resin volume, laminate
density and void content)
-65°F (Dry) mechanical tests (0° & 90° Tension, 0° & 90°
Comp. Modulus and In-plane Shear)
-65°F (Dry) mechanical tests (0° Tension)
180°F (Wet) mechanical tests (0° Comp. Strength)
cured laminate transition glass temperature, Tg
2.1.1. Materials
The T700GC-12K-31E/#2510, P707AG-15, Unidirectional Tape prepreg batches
were manufactured by the hot melt method of resin impregnation. Toray, Ehime
of Japan and Carbon Fibers America in Decatur, Alabama manufactured the
carbon fiber.
The resin mixing and impregnation were done by Toray
Composites (America), Inc. at the Frederickson, WA facilities.
This material qualification program characterized the physical, chemical and
mechanical properties of P707AG-15 prepreg material, namely; batches
AB991033, AB991034 and AB991035. The prepreg batches were manufactured
with two lots of carbon fibers and three batches of resin matrix. The P707AG-15
Unidirectional Tape batches were manufactured to nominal uncured resin
content of 35 % (by weight) and a fiber areal weight (FAW) of 150 grams per
square meter.
2.1.2. Lay-up/Bagging
TCA Test Laboratories manufactured all the mechanical test laminates by laying
up plies of the P707AG-15 prepreg material in the desired orientations, and by
vacuum bag cure. Both the ply orientation and vacuum bag assembly for cure
were in accordance with Advanced General Aviation Transport Experiments,
“Material Qualification Methodology for Epoxy-Based Prepreg Composite
Material System”, TCA Material Process Specification, TCSPF-T-UD06, Revision
1 dated February 4, 2000, and TCA work instructions, described in Figure 2-1.
19
The test laminates were vacuum debulked in accordance with TCA work
instructions, TCWIN-U-M003.
2.1.3. Cure
The test panels were cured in accordance with TCWIN-Q-M006 and per Figure
2-2. For the specimen selection methodology and batch traceability of each test
property, batch replicates were sampled from at least two different panels
covering at least two independent cycles per Figure 2-3. Test specimens were
selected from each individual test panel. The test specimens were extracted
from panel areas that were good, visually and based on non-destructive
inspection techniques.
2.1.4. Non-Destructive Inspection (NDI)
Laminates fabricated for mechanical testing were non-destructively inspected
using a Sonix/KrautKramer Branson Ultrasonic equipment at 5MHz pulse.
Metal dam*
Vacuum Sealant (one edge only)
(Tack tape)
Vacuum bag
Surface
breather
Pressure plate
1
Solid FEP (optional)
Edge dam
(3 sides tack
tape)
Edge breather
1
Glass yarn
Solid FEP (optional)
Laminate
Edge breather
Vacuum Sealant
(Tack tape)
Caul
plate
Figure 2-1. Vacuum Bagging Stack Sequence
1
The solid FEP may not be necessary when the caul plate is treated with a release agent, for example, Frekote
release agent.
20
Temp, °F
30
250
25
200
20
150
15
100
10
Temperature
50
Vacuum, in Hg
300
5
Vacuum
0
0
50
100
150
200
0
250
Time, minutes
Notes:
(1) Apply 22 inches Hg minimum vacuum to the vacuum bag assembly and
check for leak before beginning the cure cycle. The leak rate shall be less
than 2.0 inches Hg over 5 minutes.
(2) Apply the temperature ramp from ambient to 270 ± 10 °F at a rate of 3.0 ± 1.0
°F per minute.
(3) Maintain the cure temperature at 270 ± 10 °F for 120 ∼ 150 minutes.
(4) Cool down the temperature to 170 °F or lower at a rate of 4.5 ± 0.5 °F per
minute before removing the vacuum.
(5) Remove the bagged laminates from the autoclave and de-bag for inspection.
FIGURE 2-2. #2510 CURE CYCLE
21
FIGURE 2-3. SPECIMEN SELECTION METHODOLOGY AND BATCH TRACEABILITY
PER ENVIRONMENTAL CONDITION AND TEST METHOD
BATCH 1
Material Batch
LOAD
“A”
Autoclave Load
(Independent cure Process)
Panel
Manufacturing
BATCH 3
BATCH 2
LOAD
“A”
LOAD
“B”
LOAD
“A”
LOAD
“B”
LOAD
“B”
PANEL
“A1”
PANEL
“A2”
PANEL
“B1”
PANEL
“B2”
PANEL
“A1”
PANEL
“A2”
PANEL
“B1”
PANEL
“B2”
PANEL
“A1”
PANEL
“A2”
PANEL
“B1”
PANEL
“B2”
1
1
1
1
1
1
1
1
1
1
1
1
Typical Number of
Specimens (1)
(1) 6 specimens for Tension, Compression Strength, In-plane Shear and Interlaminar Shear
2 specimens for Compression Modulus
22
2.1.5. Tabbing
Tabs were used to ensure the accuracy of the tensile and compressive strength
specimens. Tabs were applied to the tension and compression strength specimens
in accordance with Section 3.1.4 of the AGATE “ Material Qualification Methodology
for Epoxy-Based Prepreg Composite Material System”, dated February 1999, with
the following exceptions;
1.) AF 163-2 film adhesive used to bond the tabs to the test specimens described
below was further cured by placing the test specimens in a temperature chamber at
180 °F for 24 hours. This was because the AF163 was not fully cured, initially, at
180°F for 5 hours. The 180°F cure temperature was selected because it was the
maximum temperature allowed by the AGATE methodology, described in section
3.1.4, since the cure temperature of the P707AG-15 was 270 ± 10°F
a.) 0° (warp) & 90° (fill) tension specimens for testing at -65°F (Dry), 75°F
(Dry), 180°F (Dry) and 180°F (Wet).
2.) Hysol EA9628 film adhesive used to bond the tabs to the specimens described
below was cured up to 260 °F for up to 120 minutes.
a.) 0° (warp) & 90° (fill) compressive strength tested -65°F (Dry), 75°F (Dry),
180°F (Dry) and 180°F (Wet).
The same material or strain compatible material tabs as the test coupon were used
for compressive strength specimens. Fiberglass tabs were used for tension
specimens. To retard the absorption of moisture into the tabs and bond lines of the
tension specimens tested at hot/wet condition, the tab section (including the edges)
were masked with a room-temperature curing “Plasti Dip” rubber coating prior to
humidity conditioning. The rubber coat was peeled off just before testing. The
National Institute for Aviation Research (NIAR) of Wichita State University bonded
the tabs and machined the 0° (warp) & 90° (fill) compressive strength specimens.
2.1.6. FAA Test Coupon Conformity and Test Witness
The material traceability and test specimen conformity were performed for the cured
laminate mechanical test properties of the program. For the physical properties,
material traceability was verified by TCA inspection section only.
2.1.6.1.
Test Coupon Conformity
A conformity traveler accompanied each group of test specimens for cured lamina
mechanical properties. The conformity traveler recorded the materials and process
definition, completion and verification by inspection of each process, that included
lay-up, cure cycle, tabbing and final coupon dimensions. Mr. Wing C. Chin, FAA
Designated Airworthiness Representative (DAR) performed the test panel and
specimen conformity, and reviewed the completeness of traveler conformity records.
Finally, Mr. Wing C. Chin, FAA DAR prepared a statement of conformity, FAA 813023
3 tags for all the test panels and test specimens, prior to environmental conditioning
and testing of the test specimens. The conformity of all the test panels was
performed October 27, 2000. However, additional test panels for compressive
strength test were fabricated and conformed on November 15, 2000 and August 1,
2000 due to problems in the testing process, for example, tabbing and machining of
specimens.
The conformed compressive test panels were replacements for
previously fabricated test panels. The conformity of all the test specimens was
performed November 22, 1999. However, the additional test specimens for
compressive strength were fabricated and conformed 4/14/2000, to replace the test
specimens with out of mode failure, for example, tab failure due to adhesive failure
and end broom failure.
2.1.6.2.
Test Witness
Mr. Moto Ashizawa, FAA Designated Engineering Representative (DER) witnessed
all the cured lamina mechanical test property testing of at least one batch of the
prepreg material for the program. TCA personnel that were authorized to witness on
behalf of Mr. Moto Ashizawa, FAA DER witnessed the rest of the tests. The test
dates of the lamina mechanical test properties were described in the tables of test
results.
24
2.2. Prepreg Documentation by Prepreg Lot
Prepreg Documentation
Prepreg Manufacturer & Product ID: Toray Composites P707AG-15
Prepreg Batch or Lot #
Batch (Lot) ID as labeled on samples
Date of Manufacture
Expiration Date
Resin Content [%]
Reinforcement Areal Weight
& Test Method
Resin Flow
& Test Conditions
Gel Time
& Test Conditions
Volatile Content
Material Identification (weave, form, class, etc.): Carbon/Epoxy Unidirectional Tape
Impregnation Method: Hot Melt
AB991033
AB991034
AB991035
910-041
910-042
910-043
10/06/1999
10/06/1999
10/06/1999
10/06/2001
10/06/2001
10/06/2001
34.6%
35.0%
34.9%
149 g/m2
148 g/m2
149 g/m2
SACMA SRM 23R-94
SACMA SRM 23R-94
SACMA SRM 23R-94
17.4%
17.5%
17.7%
@ 250°F
@ 250°F
@ 250°F
6.2 minutes
6.0 minutes
6.2 minutes
@ 250°F
@ 250°F
@ 250°F
0.17%
0.15%
0.14%
Reinforcement Documentation
Fiber/Fabric Manufacturer & Product ID: Toray T700G-12K-31E
Precursor Type: PAN
Nominal Filament Count: 12K
Finish/Sizing Type and %: 31E (0.5%)
Nominal tow or yarn count/inch: n/a
Twist: Never twisted
Fabric Batch or Lot #
Date of Manufacture
Average Fiber Density per Lot
& Test Method
Matrix Documentation
Matrix Batch or Lot #
Date of Manufacture
Average Neat Resin Density by Lot
& Test Method
099024
02/1999
1.79 g/cc
TY-030B-02
A909092
09/1999
1.79 g/cc
TY-030B-02
A909092
09/1999
1.79 g/cc
TY-030B-02
Resin Manufacturer & Product ID: Toray Composites #2510
3-CCH
10/01/1999
1.267
ASTM D792
25
3-CCG
10/01/1999
1.267
ASTM D792
2-BFC
10/04/1999
1.266
ASTM D792
Prepreg Documentation
Prepreg Batch or Lot #
Batch (Lot) ID as labeled on samples
Date of Manufacture
Expiration Date
Resin Content [%]
Reinforcement Areal Weight
& Test Method
Resin Flow
& Test Conditions
Gel Time
& Test Conditions
Volatile Content
Reinforcement
Documentation
Fiber Batch or Lot #
Date of Manufacture
Average Fiber Density per Lot
& Test Method
Matrix Documentation
Matrix Batch or Lot #
Date of Manufacture
Average Neat Resin Density by Lot
& Test Method
Prepreg Manufacturer & Product ID: Toray Composites P707AG-15
Material Identification (weave, form, class, etc.): Carbon/Epoxy Unidirectional Tape
Impregnation Method: Hot Melt
AB010955
AB020234
AB020436
AB020552
A-1, B-2, A-3, B-4,
A-5, B-6, A-7, B-8,
A-9, B-10, A-11, B12
A-13, B-14, A-15, B16, A-17, B-18, A19, B-20, A-21, B22, A-23, B-24
A-25, B-26, A-27, B28, A-29, B-30, A31, B-32, A-33, B34, A-35, B-36
A-37, B-38, A-39, B40, A-41, B-42, A43, B-44, A-45, B46, A-47, B-48
09/27/2001
09/27/2003
35.4%
150 g/m2
SACMA SRM 23R-94
-
02/28/2002
02/28/2004
36.0%
148 g/m2
SACMA SRM 23R-94
-
04/18/2002
04/18/2004
35.7%
152 g/m2
SACMA SRM 23R-94
-
05/02/2002
05/02/2004
-
12 minutes
@ 250°F
0.17%
12 minutes
@ 250°F
0.17%
9.7 minutes
@ 250°F
0.15%
-
-
-
Fiber/Fabric Manufacturer & Product ID: Toray T700G-12K-31E
Precursor Type: PAN
Nominal Filament Count: 12K
Finish/Sizing Type and %: 31E (0.5%)
Nominal tow or yarn count/inch: n/a
Twist: Never twisted
A111034
A111034
03/2001
03/2001
1.80 g/cc
1.80 g/cc
TY-030B-02
TY-030B-02
A111092
09/2001
1.80 g/cc
TY-030B-02
A111034
03/2001
1.80 g/cc
TY-030B-02
Resin Manufacturer & Product ID: Toray Composites #2510
3-GPT, 3-GPU
2-COV, 2-COW
1-CTC
2-CRJ
9/23/2001, 9/24/2001
-
2/25/2002
-
4/10/2002
-
4/28/2002
-
26
Notes: (1)Test methods to determine resin content, reinforcement areal weight, resin flow, gel time, and volatile
content are defined in TORAY Material Specifications (see reference section). (2) These information and test results
were submitted to NIAR by TORAY Composites (AMERICA), Inc.
27
2.3. Data Documentation
MATERIAL IDENTIFICATION
R material identification
R material class
PREPREG ANALYSIS
R ply manufacturer
R date of manufacture
R material lot number
R
R
R
R
commercial designation
material form
reinforcement areal weight
reinforcement areal weight test method
resin content
REINFORCEMENT ANALYSIS
F
precursor type
R
R
manufacturer
R
date of manufacture
R
lot number
R
surface treatment (Y/N)
R
surface finish (sizing) identification
R
density (Average per lot)
density test method
R
nominal filament count
R
nominal tow or yarn count/inch
R
twist
R
fiber areal weight (when applicable)
fiber areal weight test method
MATRIX MATERIAL ANALYSIS
R
R
manufacturer
R
date of manufacture
R
lot number (R – not prepregged,
F – prepregged)
R
nominal density and test method
PROCESSING INFORMATION
F
part (panel) manufacturer
R
date of manufacture (date completed)
cure cycle (for each state)
R
process stage type
R
process time
R
process temperature
R
process pressure
R
other critical control parameters
T700GC-12K-31E/#2510 Unidirectional Tape
Carbon/Epoxy
Toray Composites (America), Inc
10/1999, 09/2001, 02/2002, 04/2002, 05/2002
AB991033, AB991034, AB991035, AB010955,
AB020234, AB020436, AB020552
P707AG-15
Unidirectional Tape Prepreg
144 – 156 g/m2
Solvent Extraction
32 – 38 %
PAN
T700GC-12K-31E
Torayca
02/1999, 09/1999, 03/2001, 09/2001
099024, A909092, A111034, A111092
Y
31E
1.79 g/cm3
JIS R 7601, TY-030B-02
12000/tow
N/A
No Twist
144 – 156 g/m2
SRM 23
#2510
10/1999, 09/2001, 02/2002, 04/2002
3-CCH, 3-CCG, 2-BFC, 3-GPT, 3-GPU, 2-COV,
2-COW, 1-CTC, 2-CRJ
1.267 g/cc
ASTM D792
original QT: 10/1999 – 7/2000
additional QT: 05/2002
Cure Cycle
120 +10/-0 minutes
270 ± 3 °F
none
minimum 22 inHg vacuum
28
LAMINA ANALYSIS
R
form (panel, tube, etc.)
R
ply count
R
R
F
R
R
R
Panel
8 – axial tensile; 18 – trans tensile; 8 – axial &
trans comp; 24 – IPS ; 18 – ILSS
lay-up code
(0°)8 – axial tensile; (90°)18 – trans tensile;
(0°)8 – axial comp; (90°)8 – trans comp;
(0°/90°)6S – IPS; (0°)18 – ILSS
fiber volume
54.4% Average
void content
2.1% Average
density
1.525 g/cc Average
glass transition temperature (wet, nominal) 262°F
glass transition temperature (dry, nominal) 297°F
glass transition temperature test method
DMA E’
SPECIMEN PREPARATION
R
specimen orientation
0°, 90°, 0°/90
F
tab adhesive curing temperature (nominal) up to 260°F
MECHANICAL TESTING
R
number of specimens
R
test procedure
(citing all deviations from standard
procedures including reporting
requirements)
R
date of applicable standard
R
date of testing
R
specimen thickness for each specimen
R
R
R
R
R
specimen conditioning method
conditioning temperature
conditioning humidity
conditioning time
conditioning environment (if not lab air)
R
R
R
F
R
R
R
R
fastener type (if any)
fastener torque-up conditions (if any)
test temperature
moisture content
soak time at test conditions
failure mode identification and location
all non-normalized (raw) data
method of calculating modulus
nominal ply thickness
nominal fiber density
nominal fiber areal weight
See data files
ASTM D 3039 (Tensile),
SACMA SRM 1 (Comp),
ASTM D 5379 (IPS),
ASTM D 2344 (ILSS)
1995(Ten), 1994(Comp), 1993(IPS), 1989(ILSS)
original QT: 11/1999 – 07/2000
additional QT: 05/2002 ~ 09/2002
nominal: 0.048”(0° Tens), 0.107”(90° Tens),
0.048”(Comp), 0.143” (IPS), 0.107” (ILSS)
DOT/FAA/AR-00/47 Section 3.2, Sept. 2000
145 ± 5°F
85 ± 5%
until saturation (6 to 8 weeks)
for fluid sensitivity: Jet Fuel, Hydraulic Fluid &
MEK (IPS only)
N/A
N/A
-65 ± 5°F, 75 ± 5°F, 180 ± 5°F
Dry : 0.1 - 0.7 % Wet : 1.1 - 2.2%
-65°F: 5 – 6 minutes 180°F: 2 – 3 minutes
Per specimen
Per specimen
1000 – 3000 microstrain (Tens)
1000 – 3000 microstrain (Comp)
2500 – 6500 microstrain (IPS)
0.0060 in.
1.79 g/cm3
150 g/m2
R – Required for all data
F – Required for fully-approved data
These requirements are current for MIL-HDBK-17-1E, which supercedes for any discrepancies.
29
3. TORAY T700GC-12K-31E/#2510 LAMINA PROPERTIES
30
3.1.
Test Results
3.1.1. Summary
MATERIAL:
T700GC-12K-31E/#2510, 150 g/m2, unidirectional tape
PREPREG:
Toray Composites P707AG-15
FIBER:
Toray T700GC-12K-31E
Tg (dry): 297 °F
PROCESSING:
T700 UNI/#2510
Summary
Tg (wet): 262 °F
RESIN:
Toray Composites #2510
T g METHOD:
DMA (SRM 18-94)
Vacuum bag cure (minimum22 in-Hg): 270 ± 3 °F for 120 +10/-0 minutes
Date of fiber manufacture
02/1999 – 09/2001
Date of testing
11/1999 – 09/2002
Date of resin manufacture
10/1999 - 04/2002
Date of data submittal
04/2002 – 07/2002
Date of prepreg manufacture
10/1999 - 05/2002
Date of analysis
07/2002 – 09/2002
Date of composite manufacture
10/1999 – 05/2002
LAMINA MECHANICAL PROPERTY SUMMARY
Data Reported as: Measured
(Normalized by CPT= 0.0060 in)
CTD
RTD
ETD
ETW
B-Basis
Mean
B-Basis
Mean
B-Basis
Mean
B-Basis
Mean
F1tu
(ksi)
210.579
(216.021)
240.912
(243.955)
272.894
(277.268)
314.387
(315.086)
276.967
(281.634)
319.079
(320.048)
282.985
(288.420)
326.012
(327.759)
E1t
(Msi)
---
18.422
(18.529)
---
18.104
(18.209)
---
17.710
(17.812)
---
17.636
(17.745)
---
0.350
---
0.309
---
0.309
---
0.323
ν 12tu
F2tu
(ksi)
6.389
7.683
6.207
7.086
5.488
6.415
3.291
3.757
E2t
(Msi)
---
1.313
---
1.219
---
1.083
---
0.920
F1cu
(ksi)
174.601
(175.305)
202.546
(202.546)
184.914
(185.786)
209.999
(210.272)
179.882
(180.730)
204.285
(204.549)
156.723
(154.388)
177.255
(174.041)
E1c
(Msi)
---
16.618
(16.512)
---
16.347
(16.284)
---
17.192
(17.188)
---
16.981
(16.916)
F2cu
(ksi)
36.594
40.964
26.149
28.814
19.443
21.425
15.324
16.886
E2c
(Msi)
---
2.043
---
1.471
---
1.231
---
1.153
21.546
23.136
21.106
22.443
17.501
18.610
12.988
13.811
F12su
(ksi)
G12s
(Msi)
---
0.757
---
0.613
---
0.509
---
0.453
(ksi)
---
---
11.142
12.489
---
---
---
---
F13su**
** Apparent interlaminar shear strength
31
3.1.2. Individual Test Summaries
32
3.1.2.1.
Tension, 1-axis
Tension, 1-axis
Material:
Toray - TCA T700G-12K-31E/#2510 Unidirectional Carbon
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.51 - 1.57 g/cc
Fiber volume:
53 - 60 %
Void content:
0 - 3.4 %
Ply thickness:
0.0059 - 0.0072 in
Ply range:
8 plies
Test method:
D3039-95
Normalized by:
0.0060 in. ply thickness
TCA T700G-12K-31E/#2510
Unidirectional Carbon
[0] 8
Modulus calculation:
linear fit from 1000 - 3000µε
CTD
RTD
ETD
Test Temperature [°F]
-65
75
180
180
Moisture Conditioning
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
Equilibrium at T, RH
ETW
Source code
Normalized
Measured
Normalized
Measured
Normalized
Measured
Normalized
Measured
Mean
243.955
240.912
315.086
314.387
320.048
319.079
327.759
326.012
Minimum
212.029
199.309
252.895
251.950
287.499
286.782
276.031
258.779
Maximum
276.014
274.782
350.861
347.387
352.099
352.982
355.054
354.906
7.626
8.568
7.634
7.558
5.504
5.791
6.838
8.228
C.V.(%)
tu
F1
B-value
216.021
210.579
277.268
272.894
281.634
276.967
288.420
282.985
(ksi)
A-value
196.621
189.513
252.493
245.713
256.470
249.380
262.649
254.798
E1
t
No. Specimens
30
18
18
No. Prepreg Lots
3
3
3
18
3
Mean
18.529
18.422
18.209
18.104
17.812
17.710
17.745
17.636
Minimum
18.002
18.133
17.786
17.651
17.415
17.253
17.065
17.130
Maximum
18.900
18.775
18.804
18.572
18.330
18.223
18.106
18.119
C.V.(%)
1.265
1.021
1.542
1.639
1.587
1.894
1.865
1.907
(Msi)
No. Specimens
16
12
12
No. Prepreg Lots
3
3
3
Mean
ν 12
t
0.350
0.309
12
3
0.309
0.323
No. Specimens
16
12
12
12
No. Prepreg Lots
3
3
3
3
33
3.1.2.2.
Tension, 2-axis
Tension, 2-axis
Material:
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.48 - 1.52 g/cc
Fiber volume:
50 - 55 %
Void content:
2.0 - 4.0 %
Ply thickness:
0.0058 - 0.0062 in
Ply range:
18 plies
Test method:
D3039-95
Normalized by:
N/A
TCA T700G-12K-31E/#2510
[0] 18
CTD
RTD
ETD
-65
75
180
180
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
Source code
Normalized
Measured
Normalized
Measured
Normalized
ETW
Measured
Normalized
Measured
Mean
7.683
7.086
6.415
3.757
Minimum
5.772
5.546
4.814
2.831
Maximum
9.190
8.656
7.370
4.683
C.V.(%)
15.137
8.394
8.880
8.492
F 2tu
B-value
6.389
6.207
5.488
3.291
(ksi)
A-value
5.689
5.541
4.900
2.938
No. Specimens
No. Prepreg Lots
E2 t
(Msi)
6
1
146
7
18
3
146
3
Mean
1.313
1.219
1.083
0.920
Minimum
1.260
1.164
1.052
0.880
Maximum
1.350
1.254
1.109
0.946
C.V.(%)
3.134
2.388
1.917
2.425
No. Specimens
No. Prepreg Lots
4
1
12
3
12
3
34
12
3
3.1.2.3.
Compression, 1-axis
Compression, 1-axis
Material:
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.46 - 1.54 g/cc
Fiber volume:
49 - 57 %
Void content:
0.5 - 5.5 %
Ply thickness:
0.0057 - 0.0061
Ply range:
8 plies
Test method:
SRM 1-94
Normalized by:
0.0060 in. ply thickness
TCA T700G-12K-31E/#2510
[0] 8
CTD
RTD
ETD
-65
75
180
180
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
ETW
Source code
Normalized
Measured
Normalized
Measured
Normalized
Measured
Normalized
Measured
Mean
202.546
202.546
210.272
209.999
204.549
204.285
174.041
177.255
Minimum
189.803
189.803
190.936
189.006
174.311
174.420
134.781
135.486
Maximum
213.689
213.689
234.916
236.592
222.711
224.300
192.097
197.022
C.V.(%)
4.842
4.842
5.906
6.151
6.066
6.317
8.145
8.273
F1
B-value
175.305
174.601
185.786
184.914
180.730
179.882
154.388
156.723
(ksi)
A-value
160.113
159.017
169.607
168.338
164.991
163.757
140.888
142.618
cu
E1c
No. Specimens
6
18
18
No. Prepreg Lots
1
3
3
25
3
Mean
16.512
16.618
16.284
16.347
17.188
17.192
16.916
16.981
Minimum
16.450
16.415
16.232
16.262
16.411
16.421
15.952
16.018
Maximum
16.575
16.820
16.399
16.490
19.543
19.761
18.411
18.419
C.V.(%)
0.536
1.722
0.372
0.638
6.840
7.443
5.391
4.924
(Msi)
No. Specimens
2
6
6
6
No. Prepreg Lots
1
3
3
3
35
3.1.2.4.
Compression, 2-axis
Compression, 2-axis
Material:
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.52 - 1.56 g/cc
Fiber volume:
52 - 58 %
Void content:
0 - 2.5 %
Ply thickness:
0.0059 - 0.0062 in
Ply range:
8 plies
Test method:
SRM 1-94
Normalized by:
N/A
TCA T700G-12K-31E/#2510
[0] 8
CTD
RTD
ETD
-65
75
180
180
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
ETW
Source code
Normalized
Measured
Normalized
Measured
Normalized
Measured
Normalized
Measured
Mean
40.964
28.814
21.425
16.886
Minimum
35.123
26.641
19.042
15.233
Maximum
43.986
31.121
23.472
18.490
C.V.(%)
8.777
4.732
5.046
5.055
F2
B-value
36.594
26.149
19.443
15.324
(ksi)
A-value
34.147
24.380
18.128
14.287
cu
E2c
No. Specimens
6
18
18
No. Prepreg Lots
1
3
3
18
3
Mean
2.043
1.471
1.231
1.153
Minimum
1.745
1.432
1.204
1.083
Maximum
2.341
1.594
1.254
1.213
C.V.(%)
20.623
4.289
1.833
4.239
(Msi)
No. Specimens
2
6
6
6
No. Prepreg Lots
1
3
3
3
36
3.1.2.5.
Shear, 12 axis
Shear, 12-axis
Material:
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.51 - 1.54 g/cc
Fiber volume:
54 - 59 %
Void content:
1.8 - 3.9 %
Ply thickness:
0.0058 - 0.0060 in
Ply range:
24 plies
Test method:
D5379-93
Normalized by:
N/A
TCA T700G-12K-31E/#2510
[0/90]6s
CTD
RTD
ETD
-65
75
180
180
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
ETW
Source code
Normalized
F12
su
(ksi)
G12s
Measured
Normalized
Measured
Normalized
Measured
Normalized
Measured
Mean
23.136
22.443
18.610
13.811
Minimum
22.758
21.020
17.752
12.767
Maximum
23.423
23.379
19.400
14.683
C.V.(%)
1.151
2.819
2.938
4.313
B-value
21.546
21.106
17.501
12.988
A-value
20.655
20.218
16.765
12.442
No. Specimens
6
18
18
No. Prepreg Lots
1
3
3
18
3
Mean
0.757
0.613
0.509
0.453
Minimum
0.743
0.526
0.486
0.426
Maximum
0.775
0.665
0.543
0.505
C.V.(%)
1.812
5.774
3.298
4.374
(Msi)
No. Specimens
4
12
12
12
No. Prepreg Lots
1
3
3
3
37
3.1.2.6.
Shear, 13 axis
Shear, 13-axis
Material:
Gr/Ep
Resin content:
32 - 38 wt%
Comp. density:
1.52 - 1.55 g/cc
Fiber volume:
54 - 58 %
Void content:
1.7 - 2.8 %
Ply thickness:
0.0058 - 0.0063 in
Ply range:
18 plies
Test method:
D2344-89
Normalized by:
N/A
TCA T700G-12K-31E/#2510
[0] 18
CTD
RTD
ETD
-65
75
180
180
dry
dry
dry
equilibrium
as fabricated
as fabricated
as fabricated
145 F, 85%
ETW
Source code
Normalized
F13
su
(ksi)
Measured
Normalized
Measured
Mean
12.489
Minimum
10.226
Maximum
15.029
C.V.(%)
7.368
B-value
11.142
A-value
10.103
No. Specimens
No. Prepreg Lots
Normalized
Measured
Normalized
Measured
170
7
NOTES: These values represent the apparent interlaminar shear properties and are to be used for quality control
purposes only. Do not use these values for interlaminar shear strength design values.
38
3.1.3. Individual Test Charts
39
3.1.3.1.
Tension, 1-axis
0° Tension -- Normalized Strength
TCA T700G-12K-31E/#2510 Unidirectional Carbon Tape
400
350
Strength (ksi)
300
250
200
150
100
Conditioning
X Dry
O Wet
50
0
-100
-50
0
50
100
150
200
Temperature (°F)
NOTE: The symbols represent the ‘pooled’ average of all tests, and the bars represent the upper and lower limit of
the data. The 180° dry and wet data has been staggered for clarity
40
3.1.3.2.
Tension, 2-axis
90° Tension -- Measured Strength
10
9
8
Strength (ksi)
7
6
5
4
3
Conditioning
2
X Dry
O Wet
1
0
-100
-50
0
50
100
150
200
Temperature (°F)
the data. The 180° dry and wet data has been staggered for clarity.
41
3.1.3.3.
Compression, 1-axis
0° Compression -- Normalized Strength
250
Strength (ksi)
200
150
100
Conditioning
50
0
-100
X Dry
O Wet
-50
0
50
100
150
200
Temperature (°F)
42
3.1.3.4.
Compression, 2-axis
90° Compression -- Measured Strength
50
45
40
Strength (ksi)
35
30
25
20
15
Conditioning
10
X Dry
O Wet
5
0
-100
-50
0
50
100
150
200
Temperature (°F)
43
3.1.3.5.
Shear, 12 axis
In-Plane Shear -- Measured Strength
30
Strength (ksi)
25
20
15
10
Conditioning
5
0
-100
X Dry
O Wet
-50
0
50
100
150
200
Temperature (°F)
the data. The 180° dry and wet data has been staggered for clarity
44
3.1.3.6.
Shear, 13 axis
Apparent Interlaminar Shear -- Measured Strength
20
18
Strength (ksi)
16
14
12
10
8
6
Conditioning
4
X Dry
2
0
-100
-50
0
50
100
150
200
Temperature (°F)
45
3.2.
Raw Data
Specimen Naming Convention
Test coupons were identified using a ten-digit specimen code, with the significance of each digit delineated
below. A representative sample ID is shown for reference purposes.
A1 – 910-041 – 1-3
0° Tension
1st Character: Independent Cure Cycle
‘A’ designates a cure cycle that was
independently cured from ‘B’ cure cycle
2nd Character: Panel Number
Numeric order of the panel fabricated for each cure
cycle
3rd ~ 8th Character: Master Roll Number
Prepreg Master Roll number used to
fabricate the panel
9th ~ 10th Character: Sample Number
The samples cut from each panel,
increasing numerically.
Panel Type ID
Panels/specimens were also identified with
the test type
46
3.2.1. Raw Data Spreadsheets and Scatter Charts
47
0° Tension -- (RTD)
Strength & Modulus
normalizing t ply
[in]
0.0060
Specimen
Number
A1-910-041-1-3
A2-910-041-1-3
A1-910-041-1-8
B1-910-041-1-3
B2-910-041-1-3
B1-910-041-2-2
A1-910-042-1-1
A2-910-042-1-1
A1-910-042-1-6
B1-910-042-1-1
B2-910-042-1-1
B1-910-042-1-6
A1-910-043-1-1
A2-910-043-1-1
A1-910-043-1-6
B1-910-043-1-1
B2-910-043-1-1
B1-910-043-1-6
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Strength
[ksi]
320.938
335.891
321.176
320.317
303.504
328.201
293.401
347.387
298.001
251.950
300.751
332.368
275.407
320.986
320.083
318.659
330.703
339.244
Modulus
[Msi]
18.572
18.439
Poisson's
Ratio
0.330
0.300
18.304
18.025
0.305
0.305
18.165
18.307
0.315
0.310
17.869
18.046
0.305
0.305
17.889
17.651
0.335
0.300
18.312
17.664
0.305
0.290
Average
314.387
18.104
0.309
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
23.762
7.558
251.950
347.387
18
0.297
1.639
17.651
18.572
12
0.013
4.093
0.290
0.335
12
48
Avg. Specimen
Thickn. [in]
0.049
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
0.048
0.048
0.048
0.048
0.049
0.047
0.048
0.048
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. t ply
[in]
0.00608
0.00598
0.00598
0.00594
0.00601
0.00602
0.00602
0.00606
0.00592
0.00602
0.00603
0.00599
0.00605
0.00614
0.00591
0.00605
0.00604
0.00601
Averagenorm 0.00601
Standard Dev.norm
Coeff. of Var. [%]norm
Min.
Max.
Number of Spec.
0.0059
0.0061
Strengthnorm
[ksi]
324.950
334.491
320.038
317.314
304.136
329.090
294.501
350.861
293.780
252.895
302.004
332.022
277.817
328.342
315.082
321.513
332.977
339.739
Modulusnorm
[Msi]
18.804
18.362
315.086
18.209
24.054
7.634
252.895
350.861
18
0.281
1.542
17.786
18.804
12
18.133
18.062
18.233
18.490
17.936
18.121
18.045
18.055
18.476
17.786
Pooled Average = 315.086 [ksi]
Pooled Standard Deviation = 24.054 [ksi]
Pooled Coeff. of Variation = 7.634 [%]
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
100
200
300
400
0
600
500
0° Tensile Strength [ksi]
Pooled Average = 18.209 [Msi]
Pooled Standard Deviation = 0.281 [Msi]
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
5.0
10.0
15.0
20.0
25.0
0° Tensile Modulus [Msi]
49
30.0
35.0
40.0
Prepreg Lot #
ASAP Batch #
5
0° Tension -- (CTD)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-1
A2-910-041-1-1
A1-910-041-1-2
A1-910-041-1-10
A1-910-041-1-11
A1-910-041-1-12
A2-910-041-1-10
A2-910-041-1-11
A2-910-041-1-12
B1-910-041-1-1
B2-910-041-1-1
B1-910-041-1-2
B1-910-041-2-3
B1-910-041-2-4
B1-910-041-2-5
B2-910-041-2-3
B2-910-041-2-4
B2-910-041-2-5
A1-910-042-2-3
A1-910-042-2-2
A2-910-042-2-1
B1-910-042-2-4
B2-910-042-2-1
B2-910-042-2-3
A2-910-043-1-7
A2-910-043-1-8
A2-910-043-1-9
B1-910-043-2-1
B1-910-043-2-2
B2-910-043-2-1
Cure
Cycle
A
A
A
A
A
A
A
A
A
B
B
B
B
B
B
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Strength
[ksi]
261.807
241.216
232.898
245.723
226.813
214.697
229.803
199.309
244.840
230.072
243.892
235.368
221.947
254.174
274.782
242.153
228.176
265.373
270.271
271.333
218.048
268.148
265.452
218.048
231.648
217.989
266.167
210.451
246.373
250.386
Modulus
[Msi]
18.550
18.280
Poisson's
Ratio
0.330
0.310
18.230
18.410
0.310
0.320
18.317
18.377
18.166
18.582
18.775
18.331
18.133
18.382
18.391
18.713
18.469
18.638
0.338
0.380
0.396
0.395
0.388
0.334
0.358
0.365
0.343
0.396
0.330
0.310
Average
240.912
18.422
0.350
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
20.641
8.568
199.309
274.782
30
0.188
1.021
18.133
18.775
16
0.032
9.279
0.310
0.396
16
50
Avg. Specimen
Thickn. [in]
0.047
0.048
0.048
0.050
0.051
0.051
0.048
0.058
0.047
0.047
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.049
0.049
0.049
0.048
0.048
0.048
0.049
0.049
0.049
0.048
0.048
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Average norm
Standard Dev. norm
Min.
Max.
Number of Spec.
Avg. tply
[in]
0.00593
0.00596
0.00601
0.00625
0.00632
0.00634
0.00600
0.00719
0.00591
0.00593
0.00600
0.00594
0.00600
0.00598
0.00594
0.00602
0.00603
0.00604
0.00613
0.00609
0.00610
0.00599
0.00604
0.00603
0.00613
0.00611
0.00606
0.00605
0.00603
0.00600
Strength norm
[ksi]
258.534
239.709
233.383
255.859
238.720
226.863
229.707
238.963
241.167
227.197
243.892
232.917
221.947
253.485
272.206
243.010
229.364
267.142
276.014
275.177
221.545
267.869
267.222
219.184
236.523
221.985
268.995
212.029
247.656
250.386
Modulusnorm
[Msi]
18.318
18.166
0.00608
243.955
18.529
18.604
7.626
212.029
276.014
30
0.234
1.265
18.002
18.900
16
0.0059
0.0072
18.002
18.410
18.706
18.637
18.457
18.563
18.900
18.426
18.515
18.719
18.586
18.853
18.565
18.638
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
0
100
200
300
400
500
600
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
5.0
10.0
15.0
20.0
25.0
51
30.0
35.0
40.0
Prepreg Lot #
ASAP Batch #
5
0° Tension -- (ETW)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-5
A2-910-041-1-5
A1-910-041-1-6
B1-910-041-1-5
B2-910-041-1-5
B1-910-041-1-6
A1-910-042-1-3
A2-910-042-1-3
A1-910-042-1-4
B1-910-042-1-3
B2-910-042-1-3
B1-910-042-1-4
A1-910-043-1-3
A2-910-043-1-3
A1-910-043-1-4
B1-910-043-1-3
B2-910-043-1-3
B1-910-043-1-4
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Strength
[ksi]
276.821
328.770
258.779
317.673
315.286
333.209
343.381
344.898
319.021
354.906
346.624
353.010
330.748
302.319
354.243
322.992
311.882
353.655
Modulus
[Msi]
17.169
18.119
Poisson's
Ratio
0.340
0.340
17.687
17.883
0.320
0.275
17.448
17.130
0.304
0.335
17.693
17.313
0.331
0.321
18.050
17.573
0.346
0.353
17.544
18.017
0.312
0.298
Average
326.012
17.636
0.323
Averagenorm
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
26.826
8.228
258.779
354.906
18
0.336
1.907
17.130
18.119
12
0.023
7.015
0.275
0.353
12
Standard Dev. norm
52
Avg. Specimen
Thickn. [in]
0.051
0.047
0.051
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.049
0.048
0.048
0.048
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Coeff. of Var. [%] norm
Min.
Max.
Number of Spec.
Avg. t ply
[in]
0.00633
0.00592
0.00640
0.00597
0.00602
0.00594
0.00597
0.00598
0.00595
0.00600
0.00604
0.00602
0.00601
0.00616
0.00598
0.00605
0.00601
0.00598
Strengthnorm
[ksi]
291.931
324.318
276.031
316.019
316.139
329.877
341.736
343.605
316.230
355.054
349.151
354.334
331.437
310.192
352.989
325.684
312.531
352.403
Modulusnorm
[Msi]
18.106
17.874
0.00604
327.759
17.745
22.412
6.838
276.031
355.054
18
0.331
1.865
17.065
18.106
12
0.0059
0.0064
17.595
17.932
17.365
17.065
17.701
17.439
18.088
18.031
17.690
18.055
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
0
100
200
300
400
500
600
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
5.0
10.0
15.0
20.0
25.0
53
30.0
35.0
40.0
Prepreg Lot #
ASAP Batch #
5
0° Tension -- (ETD)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-4
A2-910-041-1-4
A2-910-041-1-9
B1-910-041-1-4
B2-910-041-1-4
B2-910-041-2-2
A1-910-042-1-2
A2-910-042-1-2
A2-910-042-1-6
B1-910-042-1-2
B2-910-042-1-2
B2-910-042-1-6
A1-910-043-1-2
A2-910-043-1-2
A2-910-043-1-6
B1-910-043-1-2
B2-910-043-1-2
B2-910-043-1-6
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Strength
[ksi]
307.781
328.131
289.866
307.698
331.673
322.023
286.782
330.190
343.825
352.982
305.839
309.174
344.723
307.413
318.972
317.114
304.698
334.545
Modulus
[Msi]
17.315
17.927
Poisson's
Ratio
0.310
0.305
17.588
17.973
0.295
0.315
18.016
18.223
0.325
0.310
18.153
17.379
0.330
0.305
17.591
17.463
0.315
0.290
17.253
17.644
0.325
0.285
Average
319.079
17.710
0.309
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
18.479
5.791
286.782
352.982
18
0.336
1.894
17.253
18.223
12
0.014
4.566
0.285
0.330
12
54
Avg. Specimen
Thickn. [in]
0.049
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
0.048
0.048
0.048
0.048
0.049
0.049
0.048
0.048
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. t ply
[in]
0.00618
0.00595
0.00599
0.00595
0.00601
0.00600
0.00602
0.00604
0.00591
0.00599
0.00603
0.00598
0.00603
0.00615
0.00610
0.00606
0.00604
0.00595
Strengthnorm
[ksi]
316.886
325.260
289.383
305.326
332.019
322.023
287.499
332.116
338.811
352.099
307.560
308.208
346.375
314.906
324.288
320.086
306.475
331.548
Modulusnorm
[Msi]
17.827
17.770
Averagenorm
Standard Dev. norm
0.00602
320.048
17.812
17.617
5.504
287.499
352.099
18
0.283
1.587
17.415
18.330
12
Min.
Max.
Number of Spec.
0.0059
0.0062
17.453
17.992
18.061
18.330
18.107
17.477
17.675
17.889
17.415
17.747
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
100
200
300
400
0
600
500
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
5.0
10.0
15.0
20.0
25.0
55
30.0
35.0
40.0
Prepreg Lot #
ASAP Batch #
5
Strength & Modulus
TCA T700G-12K-31E/#2510 Unidirectional Carbon
Specimen
Number
A1-910-041-1-3
A2-910-041-1-3
A1-910-041-1-8
B1-910-041-1-3
B2-910-041-1-3
B1-910-041-1-8
A1-910-042-1-1
A2-910-042-1-1
A1-910-042-1-8
B1-910-042-1-1
B2-910-042-1-1
B1-910-042-1-8
A1-910-043-1-1
A2-910-043-1-1
A1-910-043-1-6
B1-910-043-1-1
B2-910-043-1-1
B1-910-043-1-6
A-3-1
A-3-3
A-3-5
A-3-7
A-5-1
A-5-3
A-5-5
A-5-7
A-3-2
A-3-4
A-3-6
A-3-8
A-5-2
A-5-4
A-5-6
A-5-8
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
Strength
[ksi]
8.082
6.418
7.120
6.978
7.229
7.306
8.448
7.493
6.940
8.409
8.656
5.887
6.655
7.202
6.332
8.180
7.464
6.765
7.514
6.490
7.508
7.591
6.941
6.999
7.257
7.406
7.948
6.532
6.778
8.404
7.157
6.705
6.755
7.821
NOTE: This table is continued in next four pages.
56
Modulus
[Msi]
1.215
1.184
1.183
1.164
1.205
1.226
1.239
1.252
1.233
1.241
1.234
1.254
Avg. Specimen
Thickn. [in]
0.107
0.108
0.108
0.107
0.109
0.107
0.106
0.106
0.108
0.105
0.105
0.109
0.105
0.105
0.108
0.106
0.106
0.108
0.107
0.110
0.109
0.108
0.108
0.108
0.108
0.108
0.108
0.110
0.109
0.107
0.108
0.108
0.108
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00595
0.00599
0.00599
0.00596
0.00603
0.00595
0.00587
0.00591
0.00602
0.00583
0.00582
0.00603
0.00583
0.00586
0.00602
0.00587
0.00590
0.00599
0.00595
0.00611
0.00608
0.00598
0.00599
0.00602
0.00601
0.00602
0.00601
0.00609
0.00604
0.00592
0.00603
0.00602
0.00603
0.00595
Strength & Modulus
Specimen
Number
B-4-1
B-4-3
B-4-5
B-4-7
B-6-1
B-6-3
B-6-5
B-6-7
B-4-2
B-4-4
B-4-6
B-4-8
B-6-2
B-6-4
B-6-6
B-6-8
A-15-1
A-15-3
A-15-5
A-15-7
A-17-1
A-17-3
A-17-5
A-17-7
A-15-2
A-15-4
A-15-6
A-15-8
A-17-2
A-17-4
A-17-6
A-17-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
ASAP
Batch #
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
Strength
[ksi]
7.432
7.176
7.152
7.224
7.844
6.908
6.974
6.444
6.964
7.398
7.424
8.509
7.351
6.575
7.073
7.158
7.336
6.063
7.031
6.206
6.911
7.374
6.197
6.854
6.651
6.552
7.550
8.055
6.667
6.592
6.921
7.612
57
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.108
0.109
0.109
0.109
0.108
0.109
0.109
0.108
0.109
0.109
0.109
0.108
0.108
0.109
0.109
0.107
0.107
0.109
0.108
0.108
0.108
0.108
0.109
0.108
0.108
0.108
0.107
0.106
0.108
0.109
0.108
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00602
0.00607
0.00607
0.00605
0.00597
0.00603
0.00604
0.00601
0.00607
0.00607
0.00606
0.00598
0.00601
0.00604
0.00604
0.00593
0.00597
0.00603
0.00597
0.00599
0.00598
0.00602
0.00603
0.00601
0.00601
0.00601
0.00597
0.00589
0.00601
0.00603
0.00602
0.00593
Strength & Modulus
Specimen
Number
B-16-1
B-16-3
B-16-5
B-16-7
B-18-1
B-18-3
B-18-5
B-18-7
B-16-2
B-16-4
B-16-6
B-16-8
B-18-2
B-18-4
B-18-6
B-18-8
A-27-1
A-27-3
A-27-5
A-24-7
A-29-1
A-29-3
A-29-5
A-29-7
A-27-2
A-27-4
A-27-6
A-27-8
A-29-2
A-29-4
A-29-6
A-29-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
ASAP
Batch #
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
Strength
[ksi]
7.442
6.843
7.141
7.348
6.619
6.307
6.877
6.582
6.827
7.313
6.641
7.551
6.968
7.093
6.915
7.171
7.578
6.951
6.842
6.679
7.728
7.388
7.257
6.720
7.690
6.854
6.907
7.886
7.513
6.572
7.074
8.018
58
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.108
0.108
0.108
0.108
0.107
0.109
0.108
0.109
0.108
0.108
0.108
0.107
0.108
0.108
0.108
0.107
0.110
0.111
0.112
0.111
0.110
0.111
0.112
0.111
0.111
0.112
0.112
0.109
0.111
0.111
0.111
0.110
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00598
0.00602
0.00602
0.00600
0.00596
0.00603
0.00598
0.00604
0.00600
0.00602
0.00601
0.00594
0.00599
0.00602
0.00602
0.00597
0.00613
0.00619
0.00621
0.00617
0.00613
0.00619
0.00620
0.00617
0.00618
0.00621
0.00620
0.00604
0.00616
0.00619
0.00618
0.00609
Strength & Modulus
Specimen
Number
B-28-1
B-28-3
B-28-5
B-28-7
B-30-1
B-30-3
B-30-5
B-30-7
B-28-2
B-28-4
B-28-6
B-28-8
B-30-2
B-30-4
B-30-6
B-30-8
A-39-1
A-39-3
A-39-5
A-39-7
A-41-1
A-41-3
A-41-5
A-41-7
A-39-2
A-39-4
A-39-6
A-39-8
A-41-2
A-41-4
A-41-6
A-41-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
ASAP
Batch #
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
Strength
[ksi]
7.144
6.713
7.263
7.113
7.436
6.907
7.608
7.419
7.652
6.670
7.313
7.966
6.669
7.673
6.546
8.211
7.316
6.762
6.310
5.552
7.960
6.417
6.500
7.574
6.155
5.744
5.846
6.519
7.446
6.998
6.741
7.313
59
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.110
0.111
0.111
0.111
0.111
0.112
0.111
0.111
0.111
0.111
0.112
0.109
0.111
0.111
0.111
0.110
0.106
0.108
0.108
0.108
0.107
0.109
0.109
0.108
0.107
0.108
0.108
0.105
0.108
0.109
0.109
0.105
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00614
0.00618
0.00619
0.00617
0.00615
0.00620
0.00618
0.00616
0.00615
0.00619
0.00620
0.00608
0.00618
0.00619
0.00618
0.00610
0.00592
0.00602
0.00602
0.00601
0.00594
0.00606
0.00604
0.00602
0.00597
0.00603
0.00601
0.00584
0.00602
0.00606
0.00603
0.00585
Strength & Modulus
Specimen
Number
B-40-1
B-40-3
B-40-5
B-40-7
B-42-1
B-42-3
B-42-5
B-42-7
B-40-2
B-40-4
B-40-6
B-40-8
B-42-2
B-42-4
B-42-6
B-42-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
Prepreg
Lot #
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
ASAP
Batch #
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
7.583
7.200
6.815
7.330
6.939
6.516
5.546
6.876
6.716
5.905
6.274
7.878
6.751
6.913
7.173
7.865
Modulus
[Msi]
7.086
0.595
8.394
5.546
8.656
146
1.219
0.029
2.388
1.164
1.254
12
60
Avg. Specimen
Thickn. [in]
0.107
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.106
0.108
0.108
0.108
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00594
0.00600
0.00602
0.00600
0.00598
0.00601
0.00601
0.00599
0.00598
0.00602
0.00600
0.00592
0.00602
0.00602
0.00601
0.00595
Average
0.0060
Min.
Max.
0.0058
0.0062
Measured Strength
14
7
12
ASAP Batch #
6
5
8
4
6
3
4
2
2
1
0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
10
0
0
2
4
6
8
10
12
14
90° Tension Strength [ksi]
Measured Modulus
6
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
90° Tension Modulus [Msi]
61
2.0
2.5
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
Strength & Modulus
Specimen
Number
A1-910-041-1-1
A2-910-041-1-1
A1-910-041-1-2
B1-910-041-1-1
B2-910-041-1-1
B1-910-041-1-2
Cure
Cycle
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
ASAP
Batch #
1
1
1
2
2
2
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
9.190
8.502
7.712
7.653
7.272
5.772
Modulus
[Msi]
1.350
1.340
7.683
1.163
15.137
5.772
9.190
6
1.313
0.041
3.134
1.260
1.350
4
62
1.300
1.260
Avg. Specimen
Thickn. [in]
0.105
0.106
0.107
0.105
0.109
0.106
# Plies in
Laminate
18
18
18
18
18
18
Avg. tply
[in]
0.00583
0.00590
0.00592
0.00582
0.00603
0.00590
Average
0.0059
Min.
Max.
0.0058
0.0060
Measured Strength
6
3
ASAP Batch #
5
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
1
0
0
0
2
4
6
8
10
12
14
Measured Modulus
6
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
63
2.0
2.5
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
Strength & Modulus
Specimen
Number
A1-910-041-1-5
A2-910-041-1-5
A2-910-041-1-7
B1-910-041-1-5
B2-910-041-1-5
B2-910-041-1-7
A1-910-042-1-3
A2-910-042-1-3
A1-910-042-1-4
B1-910-042-1-3
B2-910-042-1-3
B1-910-042-1-4
A1-910-043-1-3
A2-910-043-1-3
A1-910-043-1-4
B1-910-043-1-4
B2-910-043-1-4
B1-910-043-1-5
A-7-3
A-7-5
A-7-7
A-9-1
A-9-3
A-9-5
A-9-7
A-9-8
A-11-2
A-11-4
A-11-6
A-11-8
A-11-3
A-11-5
A-11-7
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
Strength
[ksi]
3.873
3.949
4.010
3.706
3.654
3.806
3.790
3.655
3.823
3.866
3.457
3.720
3.717
3.738
3.824
3.553
3.451
3.298
3.464
3.523
3.637
4.153
3.963
3.815
4.079
4.455
3.439
3.852
3.818
3.834
3.562
3.940
3.680
64
Modulus
[Msi]
0.893
0.908
0.936
0.903
0.938
0.930
0.942
0.929
0.936
0.946
0.880
0.897
Avg. Specimen
Thickn. [in]
0.108
0.109
0.109
0.108
0.109
0.108
0.107
0.108
0.108
0.108
0.108
0.108
0.108
0.107
0.108
0.108
0.108
0.108
0.110
0.110
0.110
0.108
0.109
0.109
0.108
0.107
0.109
0.109
0.109
0.108
0.110
0.109
0.109
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00600
0.00605
0.00604
0.00600
0.00605
0.00600
0.00596
0.00598
0.00600
0.00600
0.00599
0.00603
0.00598
0.00594
0.00599
0.00598
0.00598
0.00598
0.00612
0.00608
0.00609
0.00601
0.00603
0.00604
0.00602
0.00595
0.00606
0.00607
0.00603
0.00598
0.00609
0.00606
0.00605
Strength & Modulus
Specimen
Number
B-8-1
B-8-3
B-8-5
B-8-7
B-10-1
B-10-3
B-10-5
B-10-7
B-8-2
B-8-4
B-8-6
B-8-8
B-10-2
B-10-4
B-10-6
B-10-8
A-19-1
A-19-3
A-19-5
A-19-7
A-21-1
A-21-3
A-21-5
A-21-7
A-19-2
A-19-4
A-19-6
A-19-8
A-21-2
A-21-4
A-21-6
A-21-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
ASAP
Batch #
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
Strength
[ksi]
4.683
4.286
4.086
4.013
4.047
3.529
3.566
3.669
4.597
4.122
4.479
4.462
4.203
3.554
3.564
3.777
3.991
3.357
3.402
3.990
3.961
3.243
3.697
3.679
4.077
3.572
3.816
4.095
3.655
3.647
3.498
3.690
65
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.108
0.108
0.109
0.109
0.108
0.109
0.109
0.109
0.108
0.108
0.109
0.107
0.108
0.109
0.109
0.106
0.107
0.109
0.110
0.107
0.107
0.108
0.108
0.108
0.108
0.110
0.108
0.106
0.108
0.108
0.108
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00599
0.00602
0.00604
0.00604
0.00598
0.00606
0.00607
0.00605
0.00600
0.00602
0.00606
0.00597
0.00602
0.00607
0.00607
0.00591
0.00592
0.00607
0.00610
0.00595
0.00597
0.00602
0.00602
0.00599
0.00600
0.00609
0.00603
0.00588
0.00599
0.00602
0.00602
0.00594
Strength & Modulus
Specimen
Number
B-19-1
B-19-3
B-19-5
B-19-7
B-21-1
B-21-3
B-21-5
B-21-7
B-19-2
B-19-4
B-19-6
B-19-8
B-21-2
B-21-4
B-21-6
B-21-8
A-31-1
A-31-3
A-31-5
A-31-7
A-33-1
A-33-3
A-33-5
A-33-7
A-31-2
A-31-4
A-31-6
A-31-8
A-33-2
A-33-4
A-33-6
A-33-8
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
ASAP
Batch #
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
Strength
[ksi]
4.055
3.493
3.428
3.323
3.545
3.575
3.425
3.305
3.505
3.185
3.371
4.010
3.705
3.393
3.497
3.814
3.910
3.467
3.630
3.491
4.111
3.822
3.713
4.278
3.698
3.247
3.906
3.765
3.850
4.282
4.079
4.362
66
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.107
0.109
0.109
0.108
0.107
0.108
0.108
0.108
0.109
0.109
0.109
0.106
0.108
0.109
0.108
0.107
0.111
0.111
0.111
0.111
0.112
0.111
0.111
0.111
0.111
0.112
0.111
0.110
0.112
0.111
0.111
0.110
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00594
0.00607
0.00607
0.00601
0.00596
0.00600
0.00601
0.00599
0.00603
0.00608
0.00603
0.00589
0.00598
0.00603
0.00601
0.00592
0.00616
0.00619
0.00619
0.00617
0.00620
0.00618
0.00617
0.00617
0.00617
0.00620
0.00619
0.00611
0.00622
0.00617
0.00617
0.00612
Strength & Modulus
Specimen
Number
B-32-1
B-32-3
B-32-5
B-32-7
B-34-1
B-34-3
B-34-5
B-34-7
B-36-1
B-36-3
B-36-5
B-36-7
B-36-2
B-36-4
B-36-6
B-36-8
A-43-1
A-43-3
A-43-5
A-43-7
A-45-1
A-45-3
A-45-5
A-45-7
A-43-2
A-43-4
A-43-6
A-43-8
A-45-2
A-45-4
A-45-6
A-45-8
A-47-2
Cure
Cycle
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
ASAP
Batch #
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
Strength
[ksi]
4.418
3.603
3.663
3.938
4.094
3.835
3.879
3.998
3.635
3.763
3.862
3.839
3.272
3.802
3.881
4.350
3.592
3.201
3.692
3.084
3.679
3.348
3.078
3.433
3.847
3.859
2.831
3.534
3.663
3.545
3.314
3.990
3.868
67
Modulus
[Msi]
Avg. Specimen
Thickn. [in]
0.110
0.112
0.112
0.110
0.110
0.111
0.111
0.111
0.110
0.111
0.111
0.111
0.111
0.111
0.111
0.109
0.108
0.107
0.108
0.109
0.108
0.108
0.109
0.108
0.108
0.107
0.109
0.107
0.108
0.108
0.109
0.107
0.108
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00609
0.00625
0.00622
0.00612
0.00610
0.00617
0.00618
0.00616
0.00612
0.00619
0.00615
0.00616
0.00617
0.00618
0.00614
0.00604
0.00597
0.00594
0.00599
0.00608
0.00598
0.00599
0.00606
0.00602
0.00598
0.00595
0.00606
0.00596
0.00598
0.00601
0.00605
0.00594
0.00602
.
Strength & Modulus
Specimen
Number
A-44-1
A-44-3
A-44-5
A-44-7
A-48-1
A-48-3
A-48-5
A-48-7
A-44-2
A-44-4
A-44-6
A-44-8
A-48-2
A-48-4
A-48-6
A-48-8
Cure
Cycle
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
Prepreg
Lot #
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
ASAP
Batch #
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
3.850
3.683
3.398
3.931
3.982
3.653
3.971
3.977
3.483
3.634
3.400
3.938
4.052
4.241
3.919
3.728
Modulus
[Msi]
3.757
0.319
8.492
2.831
4.683
146
0.920
0.022
2.425
0.880
0.946
12
68
Avg. Specimen
Thickn. [in]
0.107
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.107
0.108
0.109
0.108
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00596
0.00600
0.00601
0.00599
0.00599
0.00602
0.00602
0.00601
0.00598
0.00601
0.00602
0.00593
0.00601
0.00603
0.00602
0.00597
Average
0.0060
Min.
Max.
0.0059
0.0062
Measured Strength
14
7
12
ASAP Batch #
6
5
8
4
6
3
4
2
2
1
0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
10
0
0
2
4
6
8
10
12
14
Measured Modulus
6
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
69
2.0
2.5
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
Strength & Modulus
Specimen
Number
A2-910-041-1-4
A1-910-041-1-4
A2-910-041-1-8
B1-910-041-1-4
B2-910-041-1-4
B2-910-041-1-8
A1-910-042-1-2
A2-910-042-1-2
A2-910-042-1-6
B1-910-042-1-2
B2-910-042-1-2
B2-910-042-1-6
A1-910-043-1-2
A2-910-043-1-2
A2-910-043-1-6
B1-910-043-1-2
B2-910-043-1-2
B2-910-043-1-6
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
6.660
6.369
6.174
6.692
6.186
6.297
6.909
7.370
6.332
6.809
6.892
5.641
6.731
6.367
4.814
6.941
6.230
6.052
Modulus
[Msi]
1.054
1.079
6.415
0.570
8.880
4.814
7.370
18
1.083
0.021
1.917
1.052
1.109
12
70
1.055
1.052
1.070
1.090
1.095
1.109
1.104
1.107
1.093
1.088
Avg. Specimen
Thickn. [in]
0.108
0.108
0.109
0.108
0.108
0.108
0.107
0.107
0.108
0.107
0.107
0.109
0.107
0.107
0.109
0.106
0.107
0.107
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. t ply
[in]
0.00601
0.00600
0.00603
0.00600
0.00602
0.00599
0.00593
0.00595
0.00600
0.00592
0.00592
0.00608
0.00594
0.00593
0.00607
0.00590
0.00597
0.00597
Average
0.0060
Min.
Max.
0.0059
0.0061
Measured Strength
6
3
ASAP Batch #
5
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
1
0
0
0
2
4
6
8
10
12
14
Measured Modulus
6
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
71
2.0
2.5
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
0° Compression -- (RTD)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-11
A2-910-041-1-9
A2-910-041-1-10
A1-910-041-1-2
B1-910-041-1-11
B2-910-041-1-9
B2-910-041-1-10
B1-910-041-1-2
A1-910-042-1-7
A2-910-042-1-7
A2-910-042-1-8
A1-911-042-1-1
B1-910-042-1-7
B2-910-042-1-7
B2-910-042-1-8
B1-911-042-1-1
A1-910-043-1-7
A2-910-043-1-7
A2-910-043-1-8
A1-910-043-1-1
B1-910-043-1-7
B2-910-043-1-7
B2-910-043-1-8
B1-910-043-1-1
Cure
Cycle
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
194.240
205.157
210.430
Modulus
[Msi]
16.270
214.506
236.592
222.740
16.465
218.988
189.006
223.404
16.265
209.509
226.321
198.093
16.262
203.790
202.602
191.894
16.331
202.233
219.027
211.458
16.490
209.999
12.917
6.151
189.006
236.592
18
Avg. Specimen
Thickn. [in]
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00600
0.00600
0.00600
0.00601
0.00596
0.00596
0.00596
0.00592
0.00606
0.00606
0.00606
0.00599
0.00600
0.00600
0.00600
0.00600
0.00606
0.00606
0.00606
0.00603
0.00598
0.00598
0.00598
0.00592
Averagenorm 0.00600
16.347
0.104
0.638
16.262
16.490
6
Standard Dev.norm
Min.
Max.
Number of Spec.
72
0.0059
0.0061
Strengthnorm
[ksi]
194.160
205.072
210.342
Modulusnorm
[Msi]
16.297
212.986
234.916
221.163
16.232
221.223
190.936
225.684
16.248
209.378
226.180
197.969
16.273
205.786
204.586
193.773
16.399
201.601
218.342
210.797
16.256
210.272
12.419
5.906
190.936
234.916
18
16.284
0.061
0.372
16.232
16.399
6
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
50
100
150
200
250
300
350
0
400
0° Compression Strength [ksi]
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.0
5.0
10.0
15.0
0° Compression Modulus [Msi]
73
20.0
25.0
0
30.0
Prepreg Lot #
ASAP Batch #
5
0° Compression -- (CTD)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-1
A1-910-041-1-2
A1-910-041-1-3
A1-910-041-1-1
B1-910-041-1-3
B1-910-041-1-2
B1-910-041-1-4
B1-910-041-1-1
Cure
Cycle
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
ASAP
Batch #
1
1
1
1
2
2
2
2
Strength
[ksi]
213.689
212.689
206.089
Modulus
[Msi]
Average
202.546
16.618
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
9.808
4.842
189.803
213.689
6
0.286
1.722
16.415
16.820
2
16.415
189.803
194.780
198.225
16.820
Avg. Specimen
Thickn. [in]
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
# Plies in
Laminate
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00600
0.00600
0.00600
0.00601
0.00600
0.00600
0.00600
0.00591
Averagenorm 0.00599
Standard Dev. norm
Min.
Max.
Number of Spec.
74
0.0059
0.0060
Strengthnorm
[ksi]
213.689
212.689
206.089
Modulus norm
[Msi]
16.450
189.803
194.780
198.225
16.575
202.546
16.512
9.808
4.842
189.803
213.689
6
0.089
0.536
16.450
16.575
2
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
Prepeg Lot #
ASAP Batch #
5
2
1
1
0
0
0
50
100
150
200
250
300
350
400
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.0
5.0
10.0
15.0
20.0
75
25.0
0
30.0
Prepreg Lot #
ASAP Batch #
5
0° Compression -- (ETW)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-3
A1-910-041-1-4
A1-910-041-1-5
A6-910-041-1-8
A6-910-041-1-9
A6-910-041-1-11
A1-910-041-1-4
B6-910-041-1-7
B6-910-041-1-8
B6-910-041-1-11
B1-910-041-1-4
A1-910-042-1-1
A6-910-042-1-7
A6-910-042-1-10
A6-910-042-1-11
A1-910-042-1-3
B1-910-042-1-3
B6-910-042-1-8
B6-910-042-1-9
B6-910-042-1-11
B1-910-042-1-3
A6-910-043-1-7
A6-910-043-1-11
A6-910-043-1-12
A1-910-043-1-3
B1-910-043-1-1
B1-910-043-1-2
B6-910-043-1-7
B6-910-043-1-8
B6-910-043-1-9
B1-910-043-1-3
Cure
Cycle
A
A
A
A
A
A
A
B
B
B
B
A
A
A
A
A
B
B
B
B
B
A
A
A
A
B
B
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
1
1
1
2
2
2
2
3
3
3
3
3
4
4
4
4
4
5
5
5
5
6
6
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
166.126
165.717
163.971
135.486
157.780
158.226
Modulus
[Msi]
16.018
197.022
186.760
185.834
16.730
183.135
187.865
194.633
192.444
16.813
183.548
190.575
173.790
156.764
16.500
185.209
184.304
183.242
18.419
187.640
179.306
180.176
182.419
169.411
17.405
177.255
14.664
8.273
135.486
197.022
25
Avg. Specimen
Thickn. [in]
0.045
0.047
0.046
0.048
0.047
0.048
0.048
0.047
0.047
0.047
0.048
0.047
0.046
0.046
0.047
0.047
0.049
0.047
0.047
0.048
0.048
0.048
0.048
0.048
0.048
0.046
0.048
0.047
0.048
0.048
0.049
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00566
0.00588
0.00575
0.00597
0.00593
0.00594
0.00598
0.00585
0.00587
0.00592
0.00599
0.00585
0.00581
0.00580
0.00583
0.00585
0.00609
0.00584
0.00589
0.00599
0.00598
0.00601
0.00596
0.00594
0.00600
0.00571
0.00602
0.00590
0.00594
0.00599
0.00607
Averagenorm 0.00591
16.981
0.836
4.924
16.018
18.419
6
Standard Dev.norm
Min.
Max.
Number of Spec.
76
0.0057
0.0061
Strength norm
[ksi]
156.782
162.264
157.139
134.781
155.808
156.743
Modulusnorm
[Msi]
15.952
192.097
182.675
183.318
16.689
178.671
181.799
188.145
186.831
16.403
186.301
185.414
170.531
156.437
16.448
185.402
182.960
181.524
18.411
178.531
179.941
177.173
180.519
169.234
17.594
174.041
14.175
8.145
134.781
192.097
25
16.916
0.912
5.391
15.952
18.411
6
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
0
50
100
150
200
250
300
350
400
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0
0.0
5.0
10.0
15.0
20.0
77
25.0
30.0
Prepreg Lot #
ASAP Batch #
5
0° Compression -- (ETD)
Strength & Modulus
normalizing tply
[in]
0.0060
Specimen
Number
A1-910-041-1-13
A1-910-041-1-14
A2-910-041-1-11
A1-910-041-1-3
B1-910-041-1-13
B1-910-041-1-14
B2-910-041-1-11
B1-910-041-1-3
A1-910-042-1-8
A1-910-042-1-9
A2-910-042-1-9
A1-910-042-1-2
B1-910-042-1-8
B1-910-042-1-9
B2-910-042-1-9
B1-910-042-1-2
A1-910-043-1-8
A1-910-043-1-9
A2-910-043-1-9
A1-910-043-1-2
B1-910-043-1-8
B1-910-043-1-9
B2-910-043-1-9
B1-910-043-1-2
Cure
Cycle
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
199.343
200.422
212.675
Modulus
[Msi]
16.421
221.975
224.300
209.123
17.045
199.666
216.765
199.746
16.840
174.420
211.499
202.470
16.522
203.761
198.465
177.499
16.562
203.923
208.422
212.660
19.761
204.285
12.904
6.317
174.420
224.300
18
Avg. Specimen
Thickn. [in]
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.049
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.047
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00600
0.00600
0.00600
0.00600
0.00596
0.00596
0.00596
0.00596
0.00606
0.00606
0.00606
0.00606
0.00600
0.00600
0.00600
0.00601
0.00606
0.00606
0.00606
0.00604
0.00598
0.00598
0.00598
0.00593
Averagenorm 0.00601
17.192
1.280
7.443
16.421
19.761
6
Standard Dev.norm
Min.
Max.
Number of Spec.
78
0.0059
0.0061
Strengthnorm
[ksi]
199.260
200.339
212.587
Modulusnorm
[Msi]
16.411
220.403
222.711
207.641
16.931
201.704
218.978
201.785
17.015
174.311
211.367
202.343
16.556
205.756
200.409
179.237
16.673
203.286
207.771
211.996
19.543
204.549
12.408
6.066
174.311
222.711
18
17.188
1.176
6.840
16.411
19.543
6
Normalized Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
Prepeg Lot #
ASAP Batch #
5
1
1
0
0
0
50
100
150
200
250
300
350
400
Normalized Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.0
5.0
10.0
15.0
79
20.0
25.0
0
30.0
Prepreg Lot #
ASAP Batch #
5
Strength & Modulus
Specimen
Number
A1-910-041-1-9
A1-910-041-1-10
A2-910-041-1-11
A1-910-041-1-2
B1-910-041-1-9
B1-910-041-1-10
B2-910-041-1-11
B1-910-041-1-2
A1-910-042-1-7
A1-910-042-1-8
A2-910-042-1-7
A1-910-042-1-1
B1-910-042-1-7
B1-910-042-1-8
B2-910-042-1-7
B1-910-042-1-1
A1-910-043-1-7
A1-910-043-1-8
A2-910-043-1-7
A1-910-043-1-1
B1-910-043-1-7
B1-910-043-1-8
B2-910-043-1-7
B1-910-043-1-1
Cure
Cycle
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
27.701
28.209
28.730
Modulus
[Msi]
1.442
29.415
29.335
28.586
1.594
30.813
31.121
28.455
1.433
27.757
26.641
30.749
1.482
29.038
27.161
30.595
1.432
28.042
26.956
29.345
1.440
28.814
1.364
4.732
26.641
31.121
18
80
1.471
0.063
4.289
1.432
1.594
6
Avg. Specimen
Thickn. [in]
0.047
0.047
0.047
0.047
0.048
0.048
0.048
0.048
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.048
0.049
0.049
0.049
0.048
0.049
0.049
0.049
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00594
0.00594
0.00594
0.00593
0.00600
0.00600
0.00600
0.00600
0.00617
0.00617
0.00617
0.00607
0.00609
0.00609
0.00609
0.00603
0.00610
0.00610
0.00610
0.00598
0.00610
0.00610
0.00610
0.00604
Average
0.0061
Min.
Max.
0.0059
0.0062
Measured Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
5
1
0
0
0
10
20
30
40
50
60
Measured Modulus
6
3
ASAP Batch #
5
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
81
2.0
2.5
3.0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
Strength & Modulus
Specimen
Number
A1-910-041-1-7
A2-910-041-1-7
A2-910-041-1-8
A1-910-041-1-1
B1-910-041-1-7
B2-910-041-1-7
B2-910-041-1-8
B1-910-041-1-1
Cure
Cycle
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
ASAP
Batch #
1
1
1
1
2
2
2
2
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
42.691
43.545
42.527
Modulus
[Msi]
1.745
43.986
37.913
35.123
2.341
40.964
3.595
8.777
35.123
43.986
6
82
2.043
0.421
20.623
1.745
2.341
2
Avg. Specimen
Thickn. [in]
0.047
0.047
0.047
0.047
0.048
0.048
0.048
0.048
# Plies in
Laminate
8
8
8
8
8
8
8
8
Avg. t ply
[in]
0.00594
0.00594
0.00594
0.00591
0.00600
0.00600
0.00600
0.00596
Average
0.0060
Min.
Max.
0.0059
0.0060
Measured Strength
6
3
ASAP Batch #
5
4
2
3
2
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
1
1
0
0
0
10
20
30
40
50
60
Measured Modulus
6
3
ASAP Batch #
5
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
83
2.0
2.5
3.0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
Strength & Modulus
Specimen
Number
A1-910-041-1-2
A1-910-041-1-3
A2-910-041-1-1
A1-910-041-1-4
B1-910-041-1-2
B1-910-041-1-1
B1-910-041-1-3
B1-910-041-1-4
A1-910-042-1-1
A1-910-042-1-3
A2-910-042-1-2
A1-910-042-1-3
B1-910-042-1-1
B1-910-042-1-3
B2-910-042-1-1
B1-910-042-1-3
A1-910-043-1-1
A1-910-043-1-2
A2-910-043-1-1
A1-910-043-1-3
B1-910-043-1-1
B1-910-043-1-2
B2-910-043-1-1
B1-910-043-1-3
Cure
Cycle
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
16.060
17.264
16.742
Modulus
[Msi]
1.192
17.931
17.517
18.490
1.116
17.045
15.233
16.690
1.139
16.174
16.573
18.064
1.083
16.379
15.677
17.791
1.171
16.631
16.644
17.044
1.213
16.886
0.854
5.055
15.233
18.490
18
84
1.153
0.049
4.239
1.083
1.213
6
Avg. Specimen
Thickn. [in]
0.048
0.048
0.048
0.047
0.048
0.048
0.048
0.048
0.048
0.048
0.048
0.049
0.048
0.048
0.048
0.049
0.048
0.048
0.048
0.049
0.048
0.048
0.048
0.049
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00600
0.00600
0.00600
0.00593
0.00600
0.00600
0.00600
0.00603
0.00600
0.00600
0.00600
0.00617
0.00600
0.00600
0.00600
0.00609
0.00600
0.00600
0.00594
0.00613
0.00600
0.00600
0.00600
0.00609
Average
0.0060
Min.
Max.
0.0059
0.0062
Measured Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
5
1
0
0
0
10
20
30
40
50
60
Measured Modulus
6
3
ASAP Batch #
5
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
85
2.0
2.5
3.0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
Strength & Modulus
Specimen
Number
A1-910-041-1-11
A2-910-041-1-13
A2-910-041-1-14
A1-910-041-1-3
B1-910-041-1-11
B2-910-041-1-13
B2-910-041-1-14
B1-910-041-1-3
A1-910-042-1-9
A2-910-042-1-8
A2-910-042-1-9
A1-910-042-1-2
B1-910-042-1-9
B2-910-042-1-8
B2-910-042-1-14
B1-910-042-1-6
A1-910-043-1-9
A2-910-043-1-8
A2-910-043-1-9
A1-910-043-1-2
B1-910-043-1-9
B2-910-043-1-8
B2-910-043-1-14
B1-910-043-1-2
Cure
Cycle
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
A
A
A
A
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
2
2
2
2
3
3
3
3
4
4
4
4
5
5
5
5
6
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
20.454
21.865
20.491
Modulus
[Msi]
1.254
21.709
23.015
23.472
1.204
22.253
21.188
19.042
1.254
21.564
21.966
20.653
1.223
20.366
22.295
21.371
1.208
20.276
21.518
22.149
1.245
21.425
1.081
5.046
19.042
23.472
18
86
1.231
0.023
1.833
1.204
1.254
6
Avg. Specimen
Thickn. [in]
0.047
0.047
0.047
0.048
0.048
0.048
0.048
0.048
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
0.049
# Plies in
Laminate
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
Avg. tply
[in]
0.00594
0.00594
0.00594
0.00604
0.00600
0.00600
0.00600
0.00595
0.00617
0.00617
0.00617
0.00611
0.00609
0.00609
0.00609
0.00609
0.00610
0.00610
0.00610
0.00608
0.00610
0.00610
0.00610
0.00608
Average
0.0061
Min.
Max.
0.0059
0.0062
Measured Strength
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
5
1
0
0
0
10
20
30
40
50
60
Measured Modulus
6
3
ASAP Batch #
5
4
2
3
2
1
1
0
0
0.0
0.5
1.0
1.5
87
2.0
2.5
3.0
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
In-Plane Shear -- (RTD)
Strength & Modulus
Specimen
Number
A1-910-041-1-32
A1-910-041-1-33
A1-910-041-1-5
B1-910-041-1-32
B1-910-041-1-33
B1-910-041-1-5
A1-910-042-1-11
A1-910-042-1-12
A1-910-042-1-1
B1-910-042-1-11
B1-910-042-1-12
B1-910-042-1-1
A1-910-043-1-11
A1-910-043-1-12
A1-910-043-1-1
B1-910-043-1-11
B1-910-043-1-12
B1-910-043-1-1
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
21.586
22.240
21.721
21.903
22.484
22.550
22.542
22.856
23.379
22.012
23.141
22.563
22.460
21.020
23.164
22.191
23.214
22.952
Modulus
[Msi]
0.625
0.638
22.443
0.633
2.819
21.020
23.379
18
0.613
0.035
5.774
0.526
0.665
12
88
0.613
0.615
0.646
0.639
0.605
0.593
0.593
0.526
0.602
0.665
Avg. Specimen
Thickn. [in]
0.143
0.143
0.144
0.143
0.143
0.142
0.144
0.141
0.141
0.144
0.141
0.140
0.144
0.144
0.143
0.144
0.142
0.140
# Plies in
Laminate
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
Avg. t ply
[in]
0.00596
0.00595
0.00601
0.00598
0.00596
0.00593
0.00599
0.00590
0.00588
0.00600
0.00586
0.00585
0.00599
0.00601
0.00597
0.00599
0.00593
0.00584
Average
0.0059
Min.
Max.
0.0058
0.0060
Measured Strength
6
Prepreg Lot #
4
2
3
2
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
1
1
0
0
0
5
10
15
20
25
30
35
40
45
50
In-Plane Shear Strength [ksi]
Measured Modulus
6
ASAP Batch #
5
3
4
2
3
2
1
1
0
0.00
0
0.20
0.40
0.60
In-Plane Shear Modulus [Msi]
89
0.80
1.00
1.20
Prepreg Lot #
ASAP Batch #
Prepreg Lot #
In-Plane Shear -- (CTD)
Strength & Modulus
Specimen
Number
A1-910-041-1-1
A1-910-041-1-2
A1-910-041-1-3
B1-910-041-1-1
B1-910-041-1-2
B1-910-041-1-3
Cure
Cycle
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
ASAP
Batch #
1
1
1
2
2
2
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
23.318
22.758
23.134
22.877
23.305
23.423
Modulus
[Msi]
0.775
0.743
23.136
0.266
1.151
22.758
23.423
6
0.757
0.014
1.812
0.743
0.775
4
90
0.760
0.751
Avg. Specimen
Thickn. [in]
0.142
0.143
0.144
0.142
0.142
0.142
# Plies in
Laminate
24
24
24
24
24
24
Avg. tply
[in]
0.00592
0.00596
0.00599
0.00590
0.00591
0.00591
Average
0.0059
Min.
Max.
0.0059
0.0060
Measured Strength
6
Prepreg Lot #
4
2
3
2
1
Prepreg Lot #
ASAP Batch #
3
ASAP Batch #
5
1
0
0
0
5
10
15
20
25
30
35
40
45
50
Measured Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.00
0
0.20
0.40
0.60
91
0.80
1.00
1.20
Prepreg Lot #
ASAP Batch #
5
In-Plane Shear -- (ETW)
Strength & Modulus
Specimen
Number
A1-910-041-1-13
A1-910-041-1-12
A1-910-041-1-11
B1-910-041-1-10
B1-910-041-1-12
B1-910-041-1-11
A1-910-042-1-5
A1-910-042-1-6
A1-910-042-1-7
B1-910-042-1-5
B1-910-042-1-6
B1-910-042-1-7
A1-910-056-1-8
A1-910-056-1-9
A1-910-056-1-7
B1-910-043-1-5
B1-910-043-1-6
B1-910-056-1-7
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
14.337
14.339
13.522
14.683
14.005
14.289
13.309
12.767
12.865
13.298
13.026
13.381
13.942
13.822
14.504
14.335
13.825
14.351
Modulus
[Msi]
0.505
0.471
13.811
0.596
4.313
12.767
14.683
18
0.453
0.020
4.374
0.426
0.505
12
92
0.456
0.443
0.443
0.426
0.440
0.445
0.451
0.446
0.458
0.447
Avg. Specimen
Thickn. [in]
0.143
0.142
0.144
0.143
0.142
0.142
0.143
0.143
0.144
0.144
0.145
0.144
0.144
0.145
0.144
0.144
0.144
0.144
# Plies in
Laminate
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
Avg. t ply
[in]
0.00594
0.00591
0.00600
0.00595
0.00593
0.00592
0.00597
0.00598
0.00600
0.00602
0.00603
0.00600
0.00602
0.00603
0.00600
0.00598
0.00599
0.00600
Average
0.0060
Min.
Max.
0.0059
0.0060
Measured Strength
6
ASAP Batch #
3
Prepreg Lot #
Prepreg Lot #
ASAP Batch #
5
4
2
3
2
1
1
0
0
0
5
10
15
20
25
30
35
40
45
50
Measured Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.00
0
0.20
0.40
0.60
93
0.80
1.00
1.20
Prepreg Lot #
ASAP Batch #
5
In-Plane Shear -- (ETD)
Strength & Modulus
Specimen
Number
A1-910-041-1-29
A1-910-041-1-30
A1-910-041-1-7
B1-910-041-1-29
B1-910-041-1-30
B1-910-041-1-7
A1-910-042-1-13
A1-910-042-1-15
A1-910-042-1-3
B1-910-042-1-13
B1-910-042-1-14
B1-910-042-1-3
A1-910-043-1-13
A1-910-043-1-14
A1-910-043-1-3
B1-910-043-1-13
B1-910-043-1-14
B1-910-043-1-3
Cure
Cycle
A
A
A
B
B
B
A
A
A
B
B
B
A
A
A
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
ASAP
Batch #
1
1
1
2
2
2
3
3
3
4
4
4
5
5
5
6
6
6
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Strength
[ksi]
17.885
17.992
18.094
18.157
18.503
19.104
19.052
17.989
19.096
19.122
19.400
19.217
18.404
18.305
18.713
17.752
19.178
19.022
Modulus
[Msi]
0.512
0.507
18.610
0.547
2.938
17.752
19.400
18
0.509
0.017
3.298
0.486
0.543
12
94
0.493
0.498
0.525
0.497
0.520
0.522
0.486
0.491
0.512
0.543
Avg. Specimen
Thickn. [in]
0.143
0.144
0.144
0.143
0.144
0.143
0.142
0.143
0.142
0.141
0.142
0.142
0.144
0.145
0.145
0.140
0.141
0.142
# Plies in
Laminate
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
24
Avg. t ply
[in]
0.00598
0.00598
0.00602
0.00597
0.00598
0.00595
0.00592
0.00596
0.00593
0.00588
0.00593
0.00594
0.00601
0.00603
0.00603
0.00584
0.00588
0.00593
Average
0.0060
Min.
Max.
0.0058
0.0060
Measured Strength
6
ASAP Batch #
3
Prepreg Lot #
Prepreg Lot #
ASAP Batch #
5
4
2
3
2
1
1
0
0
0
5
10
15
20
25
30
Measured Modulus
6
ASAP Batch #
3
Prepreg Lot #
4
2
3
2
1
1
0
0.00
0
0.10
0.20
0.30
0.40
0.50
0.60
95
0.70
0.80
0.90
1.00
Prepreg Lot #
ASAP Batch #
5
Apparent Interlaminar Shear -- (RTD)
Strength
Specimen
Number
A1-910-041-1-1
A1-910-041-1-2
A1-910-041-1-3
A1-910-041-1-4
A1-910-041-1-5
A1-910-041-1-6
B1-910-041-1-1
B1-910-041-1-2
B1-910-041-1-3
B1-910-041-1-4
B1-910-041-1-5
B1-910-041-1-6
A1-910-042-1-1
A1-910-042-1-2
A1-910-042-1-3
A1-910-042-1-4
A1-910-042-1-5
A1-910-042-1-6
B1-910-042-1-1
B1-910-042-1-2
B1-910-042-1-3
B1-910-042-1-4
B1-910-042-1-5
B1-910-042-1-6
A1-910-043-1-1
A1-910-043-1-2
A1-910-043-1-3
A1-910-043-1-4
A1-910-043-1-5
A1-910-043-1-6
B1-910-043-1-1
B1-910-043-1-2
B1-910-043-1-3
B1-910-043-1-4
B1-910-043-1-5
B1-910-043-1-6
Cure
Cycle
A
A
A
A
A
A
B
B
B
B
B
B
A
A
A
A
A
A
B
B
B
B
B
B
A
A
A
A
A
A
B
B
B
B
B
B
Prepreg
Lot #
1
1
1
1
1
1
1
1
1
1
1
1
2
2
2
2
2
2
2
2
2
2
2
2
3
3
3
3
3
3
3
3
3
3
3
3
ASAP
Batch #
1
1
1
1
1
1
2
2
2
2
2
2
3
3
3
3
3
3
4
4
4
4
4
4
5
5
5
5
5
5
6
6
6
6
6
6
96
Strength
[ksi]
13.230
13.488
13.544
13.724
12.634
13.075
12.601
13.712
13.419
13.323
12.938
11.862
13.552
14.116
13.651
12.855
12.655
12.247
14.727
14.206
15.029
13.983
14.477
14.183
13.898
13.880
14.191
13.636
13.438
13.558
13.740
13.785
13.495
13.201
13.230
12.915
Avg. Specimen
Thickn. [in]
0.106
0.106
0.107
0.105
0.107
0.105
0.105
0.105
0.104
0.104
0.105
0.106
0.109
0.109
0.110
0.109
0.109
0.108
0.109
0.109
0.107
0.107
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.108
0.107
0.109
0.108
0.107
0.108
0.108
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00591
0.00588
0.00593
0.00584
0.00592
0.00585
0.00584
0.00585
0.00579
0.00580
0.00584
0.00588
0.00606
0.00604
0.00609
0.00607
0.00608
0.00602
0.00603
0.00604
0.00594
0.00593
0.00599
0.00598
0.00601
0.00599
0.00603
0.00600
0.00600
0.00603
0.00593
0.00603
0.00600
0.00592
0.00602
0.00598
Strength
Specimen
Number
A-1-1-1
A-1-1-3
A-1-1-5
A-1-4-7
A-1-4-9
A-1-4-11
A-1-8-13
A-1-8-15
A-1-1-2
A-1-1-4
A-1-1-6
A-1-4-8
A-1-4-10
A-1-4-12
A-1-8-14
A-1-8-16
B-2-1-1
B-2-1-3
B-2-1-5
B-2-4-7
B-2-4-9
B-2-4-11
B-2-8-13
B-2-8-15
B-2-1-2
B-2-1-4
B-2-1-6
B-2-4-8
B-2-4-10
B-2-4-12
B-2-8-14
B-2-8-16
B-2-8-18
Cure
Cycle
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
Prepreg
Lot #
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
4
ASAP
Batch #
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
8
97
Strength
[ksi]
12.990
12.129
12.027
13.428
13.009
12.130
12.570
13.160
12.877
11.984
12.022
13.144
12.828
11.704
12.860
12.134
13.834
13.279
13.357
13.728
12.787
13.153
12.219
11.170
12.527
12.102
12.494
12.524
12.182
13.335
11.560
11.171
11.512
Avg. Specimen
Thickn. [in]
0.107
0.108
0.108
0.108
0.108
0.109
0.108
0.109
0.107
0.108
0.109
0.107
0.109
0.109
0.108
0.108
0.108
0.109
0.109
0.108
0.109
0.109
0.107
0.108
0.109
0.109
0.109
0.108
0.109
0.109
0.108
0.108
0.108
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00595
0.00597
0.00602
0.00600
0.00598
0.00604
0.00598
0.00604
0.00593
0.00599
0.00603
0.00594
0.00603
0.00606
0.00599
0.00603
0.00600
0.00605
0.00607
0.00598
0.00603
0.00603
0.00597
0.00601
0.00603
0.00606
0.00603
0.00601
0.00603
0.00603
0.00599
0.00601
0.00601
Strength
Specimen
Number
A-13-2-1
A-13-2-3
A-13-2-5
A-13-5-7
A-13-5-9
A-13-5-11
A-13-7-13
A-13-7-15
A-13-2-2
A-13-2-4
A-13-2-6
A-13-5-8
A-13-5-10
A-13-5-12
A-13-7-14
A-13-7-16
A-13-7-18
B-14-2-1
B-14-2-3
B-14-2-5
B-14-5-7
B-14-5-9
B-14-5-11
B-14-7-13
B-14-7-15
B-14-2-2
B-14-2-4
B-14-2-6
B-14-5-8
B-14-5-10
B-14-5-12
B-14-7-14
B-14-7-16
Cure
Cycle
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
Prepreg
Lot #
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
5
ASAP
Batch #
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
10
98
Strength
[ksi]
11.857
13.369
12.084
12.942
13.518
12.349
13.508
12.945
12.173
12.892
12.472
12.597
11.676
11.371
12.364
11.624
10.835
13.918
13.165
12.735
12.741
12.250
12.836
11.445
11.948
12.345
12.737
13.068
12.676
11.600
12.042
11.942
11.910
Avg. Specimen
Thickn. [in]
0.108
0.107
0.108
0.107
0.107
0.109
0.107
0.108
0.107
0.107
0.109
0.107
0.108
0.109
0.107
0.108
0.109
0.107
0.107
0.107
0.107
0.108
0.107
0.108
0.108
0.107
0.107
0.108
0.107
0.108
0.108
0.108
0.108
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00600
0.00592
0.00601
0.00596
0.00596
0.00603
0.00596
0.00600
0.00597
0.00596
0.00604
0.00593
0.00601
0.00606
0.00594
0.00599
0.00604
0.00593
0.00594
0.00595
0.00596
0.00599
0.00597
0.00601
0.00601
0.00595
0.00595
0.00597
0.00596
0.00600
0.00599
0.00599
0.00601
Strength
Specimen
Number
A-25-3-1
A-25-3-3
A-25-3-5
A-25-6-7
A-25-6-9
A-25-6-11
A-25-8-13
A-25-8-15
A-25-3-2
A-25-3-4
A-25-3-6
A-25-6-8
A-25-6-10
A-25-6-12
A-25-8-14
A-25-8-16
A-25-8-18
B-26-3-1
B-26-3-3
B-26-3-5
B-26-6-7
B-26-6-9
B-26-6-11
B-26-8-13
B-26-8-15
B-26-3-2
B-26-3-4
B-26-3-6
B-26-6-8
B-26-6-10
B-26-6-12
B-26-8-14
B-26-8-16
B-26-8-18
Cure
Cycle
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
Prepreg
Lot #
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
6
ASAP
Batch #
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
12
99
Strength
[ksi]
12.692
13.627
11.661
13.055
12.992
12.210
12.211
12.532
12.619
13.211
11.241
11.691
11.537
12.261
10.934
11.351
11.752
13.360
12.664
12.876
12.490
12.825
12.282
12.075
11.539
12.111
11.661
11.575
12.238
12.325
12.122
10.901
10.456
11.010
Avg. Specimen
Thickn. [in]
0.111
0.110
0.111
0.111
0.110
0.111
0.110
0.110
0.111
0.111
0.112
0.110
0.111
0.111
0.110
0.110
0.111
0.111
0.111
0.112
0.111
0.111
0.112
0.112
0.112
0.111
0.111
0.111
0.111
0.111
0.112
0.112
0.112
0.113
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00617
0.00611
0.00619
0.00615
0.00613
0.00618
0.00613
0.00612
0.00614
0.00615
0.00620
0.00614
0.00619
0.00616
0.00613
0.00613
0.00615
0.00616
0.00615
0.00619
0.00617
0.00618
0.00620
0.00621
0.00621
0.00619
0.00616
0.00618
0.00619
0.00619
0.00623
0.00622
0.00624
0.00625
Strength
Specimen
Number
A-37-1-1
A-37-1-3
A-37-1-5
A-37-3-7
A-37-3-9
A-37-3-11
A-37-8-13
A-37-8-15
A-37-1-2
A-37-1-4
A-37-1-6
A-37-3-8
A-37-3-10
A-37-3-12
A-37-8-14
A-37-8-16
A-37-8-18
B-38-1-1
B-38-1-3
B-38-1-5
B-38-3-7
B-38-3-9
B-38-3-11
B-38-8-13
B-38-8-15
B-38-1-2
B-38-1-4
B-38-1-6
B-38-3-8
B-38-3-10
B-38-3-12
B-38-8-14
B-38-8-16
B-38-8-18
Cure
Cycle
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
A
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
B
Prepreg
Lot #
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
ASAP
Batch #
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
13
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
14
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
100
Strength
[ksi]
12.206
12.710
11.852
12.385
11.653
12.512
11.693
11.297
12.287
12.218
11.669
12.719
11.811
12.139
10.509
11.289
10.916
12.500
11.521
11.115
13.077
13.392
12.375
11.367
11.078
11.709
11.368
11.839
12.703
11.767
11.750
10.226
10.557
10.763
12.489
0.920
7.368
10.226
15.029
170
Avg. Specimen
Thickn. [in]
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.107
0.108
0.108
0.109
0.108
0.108
0.108
0.107
0.107
0.108
0.109
0.109
0.107
0.108
0.108
0.107
0.107
0.108
# Plies in
Laminate
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
18
Avg. tply
[in]
0.00596
0.00594
0.00593
0.00596
0.00593
0.00593
0.00595
0.00594
0.00593
0.00593
0.00596
0.00592
0.00594
0.00594
0.00595
0.00594
0.00596
0.00601
0.00600
0.00604
0.00599
0.00598
0.00602
0.00593
0.00595
0.00600
0.00605
0.00603
0.00597
0.00602
0.00602
0.00596
0.00595
0.00599
Average
0.0060
Min.
Max.
0.0058
0.0063
Measured Strength
14
Prepreg Lot #
6
10
5
8
4
6
3
4
2
2
1
0
0
0
5
10
15
ILSS Strength [ksi]
101
20
25
Prepreg Lot #
ASAP Batch #
7
ASAP Batch #
12
3.2.2. Fluid Sensitivity Raw Data Spreadsheets and Scatter Charts
102
In-Plane Shear -- (MEK - RTD)
Strength
Specimen
Number
A1-910-041-1-23
A1-910-041-1-24
B1-910-041-1-23
B1-910-041-1-24
B1-910-041-1-25
Batch
Number
1
1
2
2
2
Strength
[ksi]
22.492
22.173
22.531
22.805
22.262
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Avg. Specimen
Thickn. [in]
0.140
0.141
0.142
0.142
0.142
22.453
0.248
1.106
22.173
22.805
5
# Plies in
Laminate
24
24
24
24
24
Avg. t ply
[in]
0.00585
0.00589
0.00592
0.00593
0.00593
0.0059
Min.
Max.
0.0058
0.0059
In-Plane Shear -- (MEK - RTD)
Measured Strength
Batch #
3
2
1
0
0
5
10
15
20
25
103
30
35
40
In-Plane Shear -- (JP-4 JET FUEL - ETD)
Strength
Specimen
Number
A1-910-041-1-15
A1-910-041-1-16
B1-910-041-1-15
B1-910-041-1-16
B1-910-041-1-17
Batch
Number
1
1
2
2
2
Strength
[ksi]
18.184
17.774
18.070
18.256
18.698
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Avg. Specimen
Thickn. [in]
0.144
0.144
0.143
0.143
0.143
18.196
0.335
1.843
17.774
18.698
5
# Plies in
Laminate
24
24
24
24
24
Avg. t ply
[in]
0.00599
0.00601
0.00594
0.00596
0.00597
0.0060
Min.
Max.
0.0059
0.0060
Pooled Coeff. of Variation = 1.843[%]
In-Plane Shear -- (JP-4 JET FUEL - ETD)
Measured Strength
Batch #
3
2
1
0
0
5
10
15
20
25
104
30
35
40
In-Plane Shear -- (Hydraulic Fluid - ETD)
Strength
Specimen
Number
A1-910-041-1-19
A1-910-041-1-20
A1-910-041-1-21
B1-910-041-1-19
B1-910-041-1-20
Batch
Number
1
1
1
2
2
Strength
[ksi]
17.692
17.936
18.042
18.359
18.559
Average
Standard Dev.
Coeff. of Var. [%]
Min.
Max.
Number of Spec.
Avg. Specimen
Thickn. [in]
0.145
0.145
0.144
0.144
0.144
18.118
0.344
1.898
17.692
18.559
5
# Plies in
Laminate
24
24
24
24
24
Avg. t ply
[in]
0.00602
0.00603
0.00601
0.00598
0.00599
0.0060
Min.
Max.
0.0060
0.0060
In-Plane Shear -- (Hydraulic Fluid - ETD)
Measured Strength
Batch #
3
2
1
0
0
5
10
15
20
25
105
30
35
40
Fluid Sensitivity Comparison:
Average In-Plane Shear Strength
with Fluid (ksi)
Same Environment In-Plane Shear
Strength without Fluid (ksi)
Worst Case Environment In-Plane
Shear Strength (ksi)
MEK (RTD)
(RTD)
(ETW)
22.453
22.443
13.811
The RTD average in-plane shear strength was not reduced after exposure to MEK. However, it remained 63%
higher than water exposure in ETW condition.
with Fluid (ksi)
JP-4 JET FUEL (ETD)
(ETD)
(ETW)
18.196
18.610
13.811
The ETD average in-plane shear strength was reduced 2% after exposure to JP-4 Jet Fuel. However it remained
32% higher than water exposure in ETW conditions.
with Fluid (ksi)
HYDRAULIC FLUID (ETD)
(ETD)
(ETW)
18.118
18.610
13.811
The ETD average in-plane shear strength was reduced 3% after exposure to hydraulic fluid. However it remained
31% higher than water exposure in ETW conditions.
106
3.2.3. Representative Shear Stress-Strain Curve
The following stress-strain curve is representative of the TORAY T700-12K31E/#2510 Unidirectional Tape prepreg system. The tension and compression
stress-strain curves are not presented in graphical form. If strain design allowables
from these tests are required, simple one-dimensional linear stress-strain
relationships may be used to obtain corresponding strain design values. This
process should approximate tensile and compressive strain behavior relatively well
but may produce extremely conservative strain values in shear due to the nonlinear
behavior. A more realistic approach for shear strain design allowables is to use a
maximum strain value of 5% (reference MIL-HDBK-17-1E, section 5.7.6). If a
nonlinear analysis of the material’s shear behavior is required, the curve-fit of the
shear stress-strain curve may be used. The representative shear stress-strain curve
was obtained by taking the average of all the sample shear curves and determining
the best-fit line through the data. The actual data points are also presented on the
chart to demonstrate material variability.
107
Shear Stress vs. Shear Strain, RTD
20000
18000
Strain Data Points
Best Curve Fit Output
16000
Shear Stress [psi]
14000
12000
10000
8000
y0.5 = a + bx0.5ln x
r2 = 0.99935929
a = -15.451144
b = -196.23019
6000
4000
2000
0
0
0.02
0.04
0.06
Shear Strain [in/in]
108
0.08
0.1
0.12
3.3. Statistical Results
109
DISTRIBUTION OF DATA & NORMAL CURVES
Toray
DISTRIBUTION OF DATA AT INDIVIDUAL TEST
CONDITIONS
1.2
DISTRIBUTION OF POOLED DATA
1
CTD
RTD
ETD
ETW
0.9
NONE
NORMAL CURVE
1.0
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
Probability of Survival
0.8
0.6
0.6
0.5
0.4
0.4
0.3
0.2
POOLED DATA
0.2
0.1
NORMAL
CURVE
+ 10%
0
0.0
0
100
200
300
0.5
400
0.6- 10% 0.7
0.8
0.9
1
Normalized Data
0° Tension - Measured Strength
110
1.1
1.2
1.3
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
NORMAL CURVE
1.0
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.6
0.5
0.4
0.4
0.3
0.2
POOLED DATA
0.2
0.1
NORMAL
CURVE
+ 10%
0
0.0
0
100
200
300
0.5
400
0.6- 10% 0.7
0.8
0.9
1
Normalized Data
0° Tension - Normalized Strength
111
1.1
1.2
1.3
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
1.0
NORMAL CURVE
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.4
0.6
0.5
0.4
0.3
0.2
0.2
POOLED DATA
0.0
-10
-5
0.1
0
5
10
15
20
NORMAL
CURVE
25
+ 10%
0
0.5
-0.2
0.7
- 10%
0.9
1.1
Normalized Data
112
1.3
1.5
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
NORMAL CURVE
1.0
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.6
0.5
0.4
0.4
0.3
0.2
POOLED DATA
0.2
0.1
NORMAL
CURVE
+ 10%
0
0.0
0
50
100
150
200
250
0.5
300
0.6
- 10%
0.7
0.8
0.9
Normalized Data
0° Compression - Measured Strength
113
1
1.1
1.2
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
NORMAL CURVE
1.0
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.6
0.5
0.4
0.4
0.3
0.2
POOLED DATA
0.2
0.1
NORMAL
CURVE
+ 10%
0
0.0
0
50
100
150
200
250
0.5
300
0.6
- 10%
0.7
0.8
0.9
Normalized Data
0° Compression - Normalized Strength
114
1
1.1
1.2
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
1.0
NORMAL CURVE
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.4
0.6
0.5
0.4
0.3
0.2
0.2
POOLED DATA
0.0
0.1
0
10
20
30
40
50
NORMAL
CURVE
60
+ 10%
0
0.5
-0.2
0.6
- 10%
0.7
0.8
0.9
Normalized Data
115
1
1.1
1.2
Toray
CONDITIONS
1.2
1
CTD
RTD
ETD
ETW
0.9
NONE
1.0
NORMAL CURVE
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.4
0.6
0.5
0.4
0.3
0.2
0.2
POOLED DATA
0.0
0.1
0
10
20
30
NORMAL
CURVE
40
+ 10%
0
0.5
-0.2
0.6
- 10%
0.7
0.8
0.9
Normalized Data
In-Plane Shear
116
1
1.1
1.2
Toray
CONDITIONS
1.2
1
RTD
NONE
NONE
NONE
0.9
NONE
1.0
NORMAL CURVE
NORMAL CURVE
0.8
NORMAL CURVE
NORMAL CURVE
NORMAL CURVE
0.7
0.8
0.6
0.4
0.6
0.5
0.4
0.3
0.2
0.2
POOLED DATA
0.0
0.1
0
5
10
15
20
25
NORMAL
CURVE
30
+ 10%
0
0.5
-0.2
0.6- 10% 0.7
0.8
0.9
1
Normalized Data
Apparent Interlaminar Shear
117
1.1
1.2
1.3
APPENDIX A. PHYSICAL AND MECHANICAL TEST PROCEDURES
118
A.1. Physical Properties
A.1.1. Uncured Resin Content
Three (100 mm X 100 mm) uncured samples were taken across the width of the
prepreg ply sheet, from the start and end of the batch. These samples were tested
for resin weight percentage in accordance with TCWIN-Q-P004, using N-Methyl
Pyrrolidone (NMP) solvent to extract the resin matrix, and SACMA SRM 23-94,
Method A.
A.1.2. Uncured Volatile Content
The volatile content weight fraction was determined in accordance with TCWIN-QP001 that meets the intent of ASTM D3530. Three (100 mm X 100 mm) uncured
samples were taken across the width of the prepreg ply sheet, from the start and
end of the batch.
A.1.3. Resin Gel Time
Three (6 mm X 6 mm) uncured samples were taken across the width of the prepreg
ply sheet, from the start and end of the prepreg material batch. The gel time property
was performed in accordance with ASTM D3532 and TCWIN-U-P007.
A.1.4. Resin Flow
The resin flow property was determined in accordance with SACMA SRM 22-94 and
TCWIN-U-P008.
A.1.5. Uncured Fiber Areal Weight
The surface areas of resin content samples tested in accordance with 2.2.1 were
precisely measured in accordance with TCWIN-Q-P004 and SACMA SRM 23R-94.
The fiber areal weight (g/m2) was calculated by dividing the mass of the resin free
fibrous residue by the measured surface area.
A.1.6. Infrared Spectroscopy
The infrared spectroscopy signature tests were performed in accordance with
TCWIN-U-C002 that meets the intent of ASTM D1252 and ASTM D168.
119
A.1.7. High Performance Liquid Chromatography (HPLC)
HPLC signature tests were performed in accordance with TCWIN-U-C004 and
SACMA SRM 20R-94.
A.1.8. Differential Scanning Calorimetry (DSC)
DSC was performed to provide thermal property, specifically onset and peak
temperature, data for prepreg material. The DSC tests were conducted in
accordance with SACMA SRM 25R-94 and TCWIN-U-C003.
A.1.9. Cured Neat Resin Density
Testing the specimens in accordance with ASTM
M215 determined the cured neat resin density.
follows:
 W1
ρ Re sin = ρ L 
 W1 − W2
where:
D792 Method A and TCWIN-UThe density was calculated as



ρResin = Resin density, g/cc
ρL = density of ethanol or water, g/cc
W1 = weight of sample in air
W2 = weight of sample in ethanol or water
A.1.10. Fiber Volume
The fiber volume of each mechanical test laminate was determined in accordance
with ASTM D3171-90. The calculation was performed in accordance with the
following equation;
W 
VF = ρ C *  CF 
 ρF 
where:
VF = calculated fiber volume, %
ρC = laminate density, g/cc (same method as 2.2.9)
WCF = weight of fibrous carbon fiber residue of acid digestion, g
ρF = nominal carbon fiber density, g/cc = 1.79 for T700G
A.1.11. Resin Volume
The resin volume of each mechanical test laminate was determined in accordance
following equation;
120
where:
 100 − WCF 

VF = ρ C * 
ρR


VF = calculated fiber volume, %(v)
ρR = nominal cured neat resin density, g/cc = 1.267
A.1.12. Void Content
The void content of each mechanical test laminate was determined in accordance
following equation;

 100 − WCF WCF 

VV = 100 −  ρ C * 
+
ρR
ρ F 


where:
VV = Void content, %(v)
ρF = nominal carbon fiber density, g/cc = 1.79 for T700G
ρR = nominal cured neat resin density, g/cc = 1.267
A.1.13. Cured Laminate Tg by DMA
The dry and wet Tg by DMA was determined on three specimens per batch in
accordance with SACMA SRM 18R-94. The wet Tg specimens were conditioned in
accordance with method described in paragraph 2.1.7.1. The resultant wet Tg data
reflected the plasticization of resin matrix due to moisture absorption that is
anticipated for any operational environment.
A.2. TENSILE PROPERTIES
Note:
The following descriptions below apply to both 0° (Warp) and 90° (Fill)
Tensile specimens unless otherwise specified.
A.2.1. 0° (Warp) and 90° (Fill) Tensile Properties
The 0° (warp) and 90° (fill) tensile tests were conducted in accordance with ASTM
D3039 and TCWIN-U-M201. Six test specimens, 4 for tensile strength & modulus
and 2 for tensile strength only, were tested for each test condition. Test specimens
121
from one batch were tested at -65°F (Dry). Test specimens from three batches were
tested at 75°F (Dry), 180°F (Dry) and 180°F (Wet).
Twelve plies were used to fabricate the initial test panels, for zero-degree (warp)12
and ninety-degree (fill) 12 ply orientations. The panels were tabbed in accordance
with para. 2.1.5. The zero-degree and ninety-degree test specimens were wet cut to
9.0 inches nominal length and 1.00 inch nominal width in accordance with TCWINQ-M101.
The widths of the test specimens were measured with digital ¼” diameter flat anvil
and spindle micrometer. The thickness of the specimens were measured with digital
¼” diameter hemispherical anvil and spindle micrometer. The measurements were
recorded onto TCFOR-Q-033. The width and thickness measurements were
entered into the test frame computer along with the material type, batch number, test
condition and specimen identification.
The 0° (warp) tensile test specimens were strain gauged with CEA-06-125UT-120
biaxial strain gage, except the –65 °F test specimens that were strain gauge with
CEA-06-125UT-350 biaxial strain gage by Intec. The 90° (fill) tensile test specimens
were strain gauged with C-960401-A axial strain gage, except the –65 °F test
specimens that were strain gauge with CEA-06-125UW-350 axial strain gage by
Intec. Instron 4505 load frame, operated in stroke control mode, was used to apply
loading to the specimens at a crosshead rate of 0.05 inch/minute. For 0° (warp)
tensile specimens, the loads, crosshead displacements, longitudinal strains and
transverse strains were recorded throughout each test using a calibrated,
computerized data assimilation system. For 90° (fill) tensile specimens, the loads,
crosshead displacements and transverse strains only were recorded throughout
each test using a calibrated, computerized data assimilation system.
A.2.1.1. Tensile Calculations
The ultimate tensile strengths, moduli and the poisson’s ratio (zero-degree only)
were calculated by transferring the raw data recorded, for example, ultimate loads,
from the Instron computer into a Microsoft Excel spreadsheet program, in
accordance with the following equations:
A.2.1.1.1. Tensile Strength (Un-normalized)
The un-normalized tensile strength was calculated using the following equation:
σ ULT =
P
 1,000 psi 
b*d *

 ksi 
122
where:
σ ULT = the ultimate tensile stress (ksi)
P = the maximum load, (lb.)
b = the averaged measured width of the specimen (inch)
d = the averaged measured thickness of the specimen (inch)
A.2.1.1.2. Tensile Strength (Normalized)
The normalized tensile strength was calculated using the following equation:
σ ULT =
CPT specimen
P
x
 1,000 psi  CPTbatchaverage
b * d *

 ksi 
A.2.1.1.3. Tensile Modulus of Elasticity (Un-normalized)
The un-normalized longitudinal tensile modulus of elasticity was calculated using the
following equation:
P0.3% − P0.1%
E11T =
 1,000,000 psi 
b * d * (ε 0.3% − ε 0.1% )* 

msi


where: E11T = the tensile modulus of elasticity (msi)
b = the averaged measured width of the specimen (inch)
d = the averaged measured thickness of the specimen (inch)
P0.3% = the applied load at 3000 microstrain (kips)
P0.1% = the applied load at 1000 microstrain (kips)
ε0.3% = 0.3% measured longitudinal strain = 3000 microinches/inch (µin/in)
ε0.1% = 0.1% measured longitudinal strain = 1000 microinches/inch (µin/in)
A.2.1.1.4. Tensile Modulus of Elasticity (Normalized)
The normalized longitudinal tensile modulus of elasticity was calculated using the
following equation:
CPTspecimen
P0.3% − P0.1%
x
E11T =
 1,000,000 psi  CPTbatchaverage
b * d * (ε 0.3% − ε 0.1% ) * 

msi


A.2.1.1.5. 0° (Warp) Tensile Poisson’s Ratio
The poisson’s ratio (ν12) of 0° (warp) tensile specimen was calculated as follows:
123
υ12 =
where:
εY 2 − εY1
0.002
υ12 = major Poisson’s ratio
εY1 = transverse strain at stress 1, inch/inch
εY2 = transverse strain at stress 2, inch/inch
0.002 = the longitudinal strain range (εX2-εX1)=0.003–0.001 in/in
A.3. COMPRESSIVE STRENGTH
Note: The following description apply to both 0° (Warp) and 90° (Fill) Compressive
Strength specimens unless otherwise specified.
A.3.1. 0° (Warp) and 90° (Fill) Compressive Strength Properties
The 0° (warp) and 90° (fill) compressive strength tests were conducted in
accordance with SACMA SRM 1R-94 and TCWIN-U-M204. Six compressive
strength specimens were tested for each test condition. Test specimens from one
batch were tested at -65°F (Dry). Test specimens from three batches were tested at
75°F (Dry), 180°F (Dry) and 180°F (Wet).
Twelve plies were used to fabricate the initial test panels, for zero-degree (warp)12
and ninety-degree (fill) 12 ply orientations. The panels were tabbed in accordance
with para. 2.1.5. The test specimens were wet cut, to nominal length of 3.18 inches
and a nominal width of 0.50 inch. The test specimens were machined at NIAR,
Wichita State University in accordance with SACMA SRM 1-94.
The widths of the specimens were measured with digital ¼” diameter flat anvil and
spindle micrometer. The thickness of the specimens used in calculations was the
average of measurements on untabbed test panel with digital ¼” diameter
hemispherical anvil and spindle micrometer. The measurements were recorded
onto TCFOR-Q-033. The width and thickness measurements were entered into the
test frame computer along with the material type, batch number, test condition and
specimen identification.
A modified ASTM D695 anti-buckling fixture was used to augment specimen stability
during the compressive tests. Instron 4510 load frame, operated in stroke control
mode, was used to apply loading to the specimens at 0.05 inch/minute crosshead
rate. The loads and displacements were recorded throughout each test using a
calibrated, computerized data assimilation system.
124
A.3.1.1. Compressive Strength Calculations
The ultimate compressive strengths were calculated by transferring the raw data
recorded, for example, ultimate loads, from the Instron 4510 into a Microsoft Excel
spreadsheet program, in accordance with the following equations:
A.3.1.1.1. Compressive Strength Calculation (Un-normalized)
The un-normalized 0° (warp) & 90° (fill) ultimate compressive strengths were
calculated in accordance with the following formula:
F=
where:
P
b* t
F = the ultimate compressive strength (ksi)
P = the ultimate compressive load (klb. or kips)
b = the averaged measured specimen width (inch)
t = the average thickness measured on untabbed compression panel
A.3.1.1.2. Compressive Strength Calculation (Normalized)
The 0° (warp) & 90° (fill) compressive strengths were normalized in accordance with
the following formula:
F=
CPTspecimen
P
x
b * t CPTbatchaverage
A.4. COMPRESSIVE MODULUS
Note: The following description apply to both 0° (Warp) and 90° (Fill) Compressive
Modulus specimens unless otherwise specified.
A.4.1. 0° (Warp) and 90° (Fill) Compression Modulus Properties
The 0° (warp) and 90° (fill) compressive modulus tests were conducted in
accordance with SACMA SRM 1R-94 and TCWIN-U-M206. Two test specimens
were tested for each test condition. Test specimens from one batch were tested at 65°F (Dry). Test specimens from three batches were tested at 75°F (Dry), 180°F
(Dry) and 180°F (Wet).
125
Fourteen plies were used to fabricate the initial test panels, for zero-degree (warp)14
and ninety-degree (fill) 14 ply orientations. The test specimens were wet cut, to
nominal length of 3.18 inches and a nominal width of 0.50 inch, in accordance with
TCWIN-Q-M103.
The widths of the test specimens were measured with digital ¼” diameter flat anvil
and spindle micrometer. The thickness of the specimens were measured with digital
¼” diameter hemispherical anvil and spindle micrometer. The measurements were
recorded onto TCFOR-Q-033. The width and thickness measurements were
entered into the test frame computer along with the material type, batch number, test
condition and specimen identification.
A modified ASTM D695 anti-buckling fixture was used to augment specimen stability
during the compressive tests. Instron 4510 load frame, operated in stroke control
mode, was used to apply the loads. The crosshead displacement rate for each test
was 0.05 in/min (1.27 mm/min) and the strains were measured with a FAE-12S-12S6EL-2 uni-axial strain gauge, except for the –65°F test specimens that were strain
gauged with CEA-06-125UW-350 uni-axial strain gauge and tested by Intec. The
loads and strains were recorded throughout each test using computerized data
assimilation system.
A.4.1.1. Compression Modulus Calculations
The compression moduli were calculated by transferring the raw data recorded, for
example, longitudinal strains, from the Instron 4510 into a Microsoft Excel
spreadsheet program, in accordance with the following equations:
A.4.1.1.1. Compressive Modulus Calculation (Un-normalized)
The un-normalized 0° (warp) & 90° (fill) compressive modulus was calculated as
follows:
E=
where:
b * d * (ε 0.3%
P0.3% − P0.1%
 1,000,000 psi 
− ε 0 .1 % ) * 

msi


E = compressive modulus (msi)
P0.3% = applied load at 3000 microstrain, (lb.)
P0.1% = applied load at 1000 microstrain, (lb.)
b = averaged measured specimen width, (inch)
d = averaged measured specimen thickness, (inch)
ε0.3% = 0.3% measured strain = 3000 microinches/inch (µin/in)
ε0.1% = 0.1% measured strain = 1000 microinches/inch (µin/in)
126
A.4.1.1.2. Compressive Modulus Calculation (Normalized)
The 0° (warp) & 90° (fill) compressive modulus normalization was calculated as
follows:
E=
b * d * (ε 0.3%
CPTspecimen
P0.3% − P0.1%
x
 1,000,000 psi  CPTbatchaverage
− ε 0 .1 % ) * 

msi


A.5. IN-PLANE (IOSIPESCU) SHEAR
The in-plane (iosipescu) shear tests were conducted in accordance with ASTM
D5379-93 and D5379-98 for new calculation ranges.
Six test specimens, 4 for
shear strength & modulus and 2 for shear strength only, were tested for each test
condition. Test specimens from one batch were tested at -65°F (Dry). Test
specimens from three batches were tested at 75°F (Dry), 180°F (Dry) and 180°F
(Wet).
Sixteen plies were used to fabricate the initial test panels, in the (Warp/Fill) 4S ply
stacking sequence. The test specimens were wet cut, to nominal length of 3.0
inches and to nominal width of 0.75 inch. The specimen width is further machined to
symmetrical centrally located v-notched width of 0.45 inch, in accordance with ASTM
D5379-93.
The symmetrical centrally notched widths of the test specimens were measured with
digital needlepoint and spindle micrometer. The thickness of the specimens were
measured with digital ¼” diameter hemispherical anvil and spindle micrometer. The
measurements were recorded onto TCFOR-Q-033. The width and thickness
measurements were entered into the test frame computer along with the material
type, batch number, test condition and specimen identification.
The test specimens were inserted into the v-notched beam test fixture, with the
notch located along the line-of-action of loading by means of an alignment tool that
referenced the fixture. The notches influence the shear strain along the loading
direction, as the two halves of the fixture were compressed by the load frame while
monitoring load.
Instron 4505 load frame, operated in stroke control mode, was used to apply the
loads. The crosshead displacement rate for each test was 0.05 in/min (1.27
mm/min). The strains were measured with a EA-06-125-TW-120 rosette strain
gauge, except the -65°F test specimens that were strain gauged with EA-06-062TV350 and tested by Intec. The loads and strains were recorded throughout each test
using computerized data assimilation system.
127
A.5.1. In-plane (Iosipescu) Shear Strength Calculations
The strains were measured using the bonded strain gauge. The shear cord modulus
was calculated in accordance with ASTM D5379-98, at 6500 microstrain and 2500
microstrain. The ultimate in-plane (iosipescu) shear strength and moduli were
calculated by transferring the raw data recorded, for example, ultimate loads,
measured strains, from the instron computer into a Microsoft Excel spreadsheet, in
accordance with the following equations:
A.5.1.1. In-plane (Iosipescu) Shear, Ultimate Strength Calculation
τ Ult . =
where:
P
 1,000 psi 
b*d *

 ksi 
τUlt. = the ultimate in-plane shear strength, ksi
P = the ultimate load, lbs.
b = the measured specimen width, in the symmetrical
centrally located notch, inch
d = the average measured specimen thickness, inch
A.5.1.2. In-plane (Iosipescu) Shear, Modulus Calculation
G12 =
where:
P0.65% − P0.25%
1,000,000 psi 
b * d * (γ 0.65% − γ 0.25% ) * 

msi


G12 = shear chord modulus of elasticity (Msi)
P0.65% = applied load at 6500 microstrain (lbs.)
P0.25% = applied load at 2500 microstrain (lbs.)
b = the measured specimen width, in the symmetrical
centrally located notch (inch)
d = the average measured specimen thickness (inch)
γ0.65% = ε+45+ε-45= shear strain at 6500 microstrain
γ0.25% = ε+45+ε-45= shear strain at 2500 microstrain
A.6. SHORT BEAM SHEAR
The short beam shear tests were conducted in accordance with ASTM 2344-89.
Six test specimens from three batches were tested at 75°F (Dry) only.
128
Twelve plies were used to fabricate the initial test panels, in the zero-degree ply
stacking sequence, (warp)12. The test specimens were wet cut, to nominal length of
6*average thickness, in inches and to nominal width of 0.25 inch.
Instron 4505 load frame, operated in stroke control mode, was used to apply the
loads. The crosshead displacement rate for each test was 0.05 in/min (1.27
mm/min). The loads and displacements were recorded throughout each test using
computerized data assimilation system.
A.6.1. Short Beam Shear Strength Calculations
The short beam shear strengths were calculated by transferring the raw data
recorded from the Instron 4505 computer into Microsoft Excel spreadsheet program,
in accordance with the following equation:
A.6.1.1. Short Beam Shear Strength Calculation
F=
where:
3* P
1,000 psi 
4 * b * t * 

 ksi 
F. = the short beam shear strength (ksi)
P = the ultimate load (lbs.)
b = the measured specimen width (inch)
t = the measured specimen thickness (inch)
129
APPENDIX B. MOISTURE CONDITIONING HISTORY CHARTS
130
Traveler #1
Traveler #2
1.00
0.50
1.50
1.00
0.50
0.00
0.00
2
4
6
Time, days
8
2
1/2
4
6
Time, days
8
1.00
0.50
0.00
Time, days
6
1/2
8
4
6
Time, days
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #8
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
131
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #7
0.00
4
2
1/2
% Weight Gain
% Weight Gain
1.50
1.50
0.00
0
2.00
2
0.50
Traveler #6
2.00
0
1.00
0.00
0
Traveler #5
1.50
% Weight Gain
0
2.00
% Weight Gain
% Weight Gain
% Weight Gain
1.50
Traveler #4
2.00
% Weight Gain
2.00
2.00
% Weight Gain
Traveler #3
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #9M
Traveler #11M
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
Time, days
6
8
1/2
4
6
8
1/2
1.00
0.50
0.00
Time, days
1/2
8
4
6
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #12S
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
132
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #11S
0.00
6
2
Time, days
% Weight Gain
1.50
1.50
0.00
0
2.00
4
0.50
Traveler #10S
% Weight Gain
% Weight Gain
2
Time, days
2.00
2
1.00
0.00
0
Traveler #9S
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #15M
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #13M
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #13S
Traveler #14S
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
Time, days
6
8
4
6
Time, days
8
1.00
0.50
0.00
Time, days
1/2
8
4
Time, days
6
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #20
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
133
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #19
0.00
6
2
1/2
% Weight Gain
1.50
1.50
0.00
0
2.00
4
0.50
Traveler #18
% Weight Gain
% Weight Gain
2
1/2
2.00
2
1.00
0.00
0
Traveler #17
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #16S
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #15S
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #21
Traveler #22
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
6
Time, days
8
2
1/2
4
6
Time, days
8
1.00
0.50
0.00
Time, days
6
1/2
8
4
6
Time, days
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #28
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
134
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #27
0.00
4
2
1/2
% Weight Gain
% Weight Gain
1.50
1.50
0.00
0
2.00
2
0.50
Traveler #26
2.00
0
1.00
0.00
0
Traveler #25
1.50
% Weight Gain
0
2.00
% Weight Gain
% Weight Gain
% Weight Gain
1.50
Traveler #24
2.00
% Weight Gain
2.00
2.00
% Weight Gain
Traveler #23
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #29M
Traveler #31M
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
Time, days
6
8
1/2
4
6
8
1/2
1.00
0.50
0.00
Time, days
1/2
8
4
6
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #32S
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
135
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #31S
0.00
6
2
Time, days
% Weight Gain
1.50
1.50
0.00
0
2.00
4
0.50
Traveler #30S
% Weight Gain
% Weight Gain
2
Time, days
2.00
2
1.00
0.00
0
Traveler #29S
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #35M
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #33M
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #33S
Traveler #34S
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
6
Time, days
8
4
6
Time, days
8
0
1.00
0.50
Time, days
6
1/2
8
2
4
6
0
8
1.50
1.00
0.50
4
Time, days
6
8
1.50
1.00
0.50
8
1.50
1.00
0.50
0.00
2
4
Time, days
136
6
1/2
2.00
0
1/2
4
Traveler #40
0.00
2
2
Time, days
2.00
0
0.50
Traveler #39
0.00
0.00
1.00
Time, days 1/2
% Weight Gain
1.50
1.50
0.00
1/2
2.00
4
0.50
Traveler #38
% Weight Gain
% Weight Gain
2
1/2
2.00
2
1.00
0.00
0
Traveler #37
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #36S
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #35S
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #41
Traveler #42
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
6
Time, days
8
2
1/2
4
6
Time, days
8
1.00
0.50
0.00
Time, days
6
1/2
8
4
6
Time, days
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #48
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
137
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #47
0.00
4
2
1/2
% Weight Gain
% Weight Gain
1.50
1.50
0.00
0
2.00
2
0.50
Traveler #46
2.00
0
1.00
0.00
0
Traveler #45
1.50
% Weight Gain
0
2.00
% Weight Gain
% Weight Gain
% Weight Gain
1.50
Traveler #44
2.00
% Weight Gain
2.00
2.00
% Weight Gain
Traveler #43
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #49M
Traveler #51M
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
Time, days
6
8
1/2
4
6
8
1.00
0.50
0.00
Time, days
1/2
8
4
Time, days
6
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #52S
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
138
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #51S
0.00
6
2
1/2
% Weight Gain
1.50
1.50
0.00
0
2.00
4
0.50
Traveler #50S
% Weight Gain
% Weight Gain
2
Time, days
2.00
2
1.00
0.00
0
Traveler #49S
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #35M
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #53M
6
1/2
8
0
2
4
Time, days
6
1/2
8
Traveler #53S
Traveler #54S
1.00
0.50
0.00
1.50
1.00
0.50
0.00
2
4
6
Time, days
8
4
6
Time, days
8
1/2
1.00
0.50
0.00
Time, days
1/2
8
4
6
1.50
1.00
0.50
0
1/2
4
Time, days
6
8
6
8
1/2
Traveler #60
1.50
1.00
0.50
1.50
1.00
0.50
0.00
2
4
Time, days
139
4
2.00
0
1/2
2
Time, days
0.00
2
0.50
8
2.00
0
1.00
Traveler #59
0.00
6
2
Time, days
% Weight Gain
1.50
1.50
0.00
0
2.00
4
0.50
Traveler #58
% Weight Gain
% Weight Gain
2
1/2
2.00
2
1.00
0.00
0
Traveler #57
0
1.50
% Weight Gain
0
2.00
% Weight Gain
1.50
Traveler #56S
2.00
% Weight Gain
2.00
% Weight Gain
% Weight Gain
2.00
Traveler #55S
6
1/2
8
0
2
4
Time, days
6
1/2
8
APPENDIX C. PHYSICAL TEST RESULTS
140
Summary of Chemical and Physical Tests - Uncured
Material Properties
Material Batch
Uncured
Resin
Content
(%)
Physical
Fiber Prepreg
Areal Volatile
Gel
Resin
Weight Content
Time
Flow
2
(g/m )
(%)
(minutes) (%)
Chemical
IR
P1
AB991033
AB991034
AB991035
Grand Average
Requirement
34.6
35.0
34.9
34.8
35 ± 3
148
0.17
149
0.15
149
0.14
149
0.15
150 ± 6 2.0 max
6.2
6.0
6.2
6.1
5 - 25
HPLC
(% Area)
P2 P3 P4
17.4 scan 9.8 8.5 5.8 61.5
17.5
on
9.9 8.6 5.8 61.6
17.7
file 10.0 8.9 6.1 60.9
17.5
9.9 8.7 5.9 61.3
10 min
TBD
P5
14.3
14.2
14.1
14.2
DSC
(°F)
Onset Peak
280
327
281
327
281
329
281
328
TBD TBD
Summary of Chemical and Physical Tests - Cured
Material Properties
Material Batch
Resin
Density
(g/cc)
AB991033
1.267
AB991034
1.267
AB991035
1.266
Grand Average
1.267
Requirement 1.26 ± 0.03
Glass Transition
Temperature
by DMA
(°F)
Dry
Wet
294
300
298
297
TBD
260
265
261
262
TBD *
* FAA Recommended Hot/Wet Tg: 230°F, Based on Maximum Operation Temperature of 180°F + 50°F
141
Material Properties, Batch AB991033
Batch No./
Panel ID
Test
Type
Cured
Laminate Fiber Resin
Void
Ply
Density Volume Volume Content Thickness
(g/cc) (%vol) (%vol) (%vol)
(in.)
Autoclave
Cure
Run
ID
-
AB991033
A1-910-041 0° Tens
A2-910-041 0° Tens
B1-910-041 0° Tens
B2-910-041 0° Tens
A1-910-041 90° Tens
A2-910-041 90° Tens
1.533
1.515
1.531
1.542
1.497
1.480
58.7
55.7
55.6
53.4
52.4
49.6
38.1
40.8
42.2
46.2
44.2
46.7
3.25
3.42
2.13
0.35
3.45
3.71
0.0061
0.0060
0.0060
0.0060
0.0060
0.0060
99-631
99-558
99-559
99-559
99-560
99-560
B1-910-041 90° Tens
1.505
53.0
44.0
3.05
0.0060
99-559
B2-910-041 90° Tens
A1-910-041 0° Comp
A2-910-041 0°Comp
B1-910-041 0°Comp
B2-910-041 0°Comp
A1-910-041 90°Comp
A2-910-041 90°Comp
B1-910-041 90°Comp
B2-910-041 90°Comp
A1-910-041
IPS
B1-910-041
IPS
A1-910-041
ILSS
B1-910-041
ILSS
Average
Standard Deviation
COV, %
Requirement
1.493
1.501
1.469
1.509
1.504
1.525
1.545
1.549
1.539
1.511
1.527
1.537
1.532
1.517
0.022
1.47
TBD
52.7
52.4
49.9
51.8
49.1
53.4
55.6
55.5
56.0
56.0
58.8
58.4
55.9
54.2
2.9
5.34
TBD
43.4
44.5
45.4
45.9
49.3
45.0
43.4
43.9
42.4
40.1
37.4
38.8
42.0
43.2
3.0
7.03
TBD
3.92
3.13
4.67
2.25
1.55
1.64
1.01
0.67
1.63
3.86
3.74
2.78
2.13
2.62
1.20
45.82
TBD
0.0060
0.0060
0.0060
0.0060
0.0060
0.0059
0.0059
0.0060
0.0060
0.0060
0.0059
0.0059
0.0058
0.0060
0.0001
0.98
TBD
99-559
99-564
99-569
99-563
99-568
99-564
99-564
99-563
99-572
99-560
99-563
99-558
99-559
-
142
Batch No./
Panel ID
Test
Type
Cured
Laminate Fiber Resin
Void
Ply
(g/cc) (%vol) (%vol) (%vol)
(in.)
Autoclave
Cure
Run
ID
-
AB991034
A1-910-042 0° Tens
A2-910-042 0° Tens
B1-910-042 0° Tens
B2-910-042 0° Tens
A1-910-042 90° Tens
A2-910-042 90° Tens
1.557
1.571
1.563
1.541
1.504
1.509
57.5
60.3
57.6
56.4
51.2
51.9
41.7
38.8
42.0
41.9
46.3
45.8
0.82
0.88
0.39
1.67
2.47
2.32
0.0060
0.0060
0.0060
0.0060
0.0060
0.0060
99-569
99-569
99-566
99-566
99-569
99-571
B1-910-042 90° Tens
1.510
53.5
43.5
2.93
0.0060
99-566
B2-910-042 90° Tens
A1-910-042 0° Comp
A2-910-042 0°Comp
B1-910-042 0°Comp
B2-910-042 0°Comp
A1-910-042 90°Comp
A2-910-042 90°Comp
B1-910-042 90°Comp
B2-910-042 90°Comp
A1-910-042
IPS
B1-910-042
IPS
A1-910-042
ILSS
B1-910-042
ILSS
Average
Standard Deviation
COV, %
Requirement
1.519
1.461
1.475
1.499
1.512
1.552
1.536
1.557
1.552
1.516
1.537
1.527
1.536
1.527
0.029
1.91
TBD
55.4
49.4
53.2
50.1
48.7
57.0
51.6
53.9
53.8
55.1
56.0
54.5
55.6
54.1
3.0
5.57
TBD
41.6
45.6
41.2
47.5
50.5
41.9
48.3
46.7
46.5
41.7
42.2
43.5
42.7
44.0
3.0
6.74
TBD
3.00
5.07
5.55
2.38
0.78
1.05
0.09
0.00
0.00
3.13
1.80
1.98
1.73
1.90
1.54
80.86
TBD
0.0060
0.0061
0.0061
0.0060
0.0060
0.0062
0.0062
0.0061
0.0061
0.0059
0.0060
0.0061
0.0060
0.0060
0.0001
1.03
TBD
99-570
99-569
99-571
99-568
99-568
99-569
99-581
99-566
99-568
99-571
99-568
99-571
99-566
-
143
Batch No./
Panel ID
Test
Type
Cured
Laminate Fiber
Resin
Void
Ply
(g/cc)
(%vol) (%vol) (%vol)
(in.)
Autoclave
Cure
Run
ID
-
AB991035
A1-910-043 0° Tens
A2-910-043 0° Tens
B1-910-043 0° Tens
B2-910-043 0° Tens
A1-910-043 90° Tens
A2-910-043 90° Tens
1.563
1.551
1.543
1.529
1.512
1.517
60.0
55.5
52.7
53.4
53.0
52.8
38.6
44.0
47.4
45.2
44.4
45.2
1.41
0.51
0.00
1.35
2.57
2.04
0.0060
0.0061
0.0060
0.0060
0.0060
0.0060
99-583
99-583
99-582
99-582
99-581
99-581
B1-910-043 90° Tens
1.505
52.6
44.4
2.98
0.0060
99-572
B2-910-043 90° Tens
A1-910-043 0° Comp
A2-910-043 0°Comp
B1-910-043 0°Comp
B2-910-043 0°Comp
A1-910-043 90°Comp
A2-910-043 90°Comp
B1-910-043 90°Comp
B2-910-043 90°Comp
A1-910-043
IPS
B1-910-043
IPS
A1-910-043
ILSS
B1-910-043
ILSS
Average
Standard Deviation
COV, %
Requirement
1.504
1.514
1.530
1.541
1.512
1.547
1.527
1.555
1.559
1.532
1.517
1.538
1.542
1.532
0.018
1.19
TBD
53.2
52.7
51.7
56.9
53.4
54.3
55.8
56.4
58.3
57.1
54.0
56.9
56.6
54.9
2.3
4.15
TBD
43.6
45.1
47.8
41.3
43.8
45.3
41.7
43.0
40.7
40.2
43.3
41.1
41.7
43.4
2.4
5.47
TBD
3.27
2.25
0.54
1.86
2.76
0.35
2.51
0.53
1.04
2.65
2.61
2.09
1.69
1.75
0.98
56.22
TBD
0.0060
0.0061
0.0061
0.0060
0.0060
0.0061
0.0061
0.0061
0.0061
0.0060
0.0060
0.0060
0.0060
0.0060
0.0001
0.90
TBD
99-572
99-583
99-583
99-582
99-582
99-583
99-583
99-584
99-584
99-581
99-582
99-581
99-572
-
144
145
146
147
148
149
150
151
152
153
154
155
156
157
158
159
160
161
162
163
164
APPENDIX D. STATISTICAL ANALYSIS SUMMARY
165
COMPANY
Toray
MATERIAL
PROPERTY
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
30
18
18
18
No. of Batches
4
6
6
6
Mean
240.912
314.387
319.079
326.012
Std.dev
20.641
23.762
18.479
26.826
% Co. Variation
8.568
7.558
5.791
8.228
Minimum
199.309
251.950
286.782
258.779
Maximum
274.782
347.387
352.982
354.906
Kb
1.652
1.732
1.732
1.732
Ka
2.799
2.866
2.866
2.866
Equal C.V. Basis Values
B-Basis Value
210.579
272.894
276.967
282.985
A-Basis Value
189.513
245.713
249.380
254.798
Anderson Darling Test for Normality
O.S.L
Normality is
0.304
0.052
0.483
0.086
Acceptable
Acceptable
Acceptable
Acceptable
O.S.L for pooled data is
0.2329
Normality is Acceptable
Check for Normality based on Normal Scores
r
2
Normality is
0.988
0.943
0.987
0.945
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9891
r for pooled data is
k-sample Anderson Darling Test ( ADK < ADC for batches from same population)
ADK
1.167
0.842
0.494
1.292
ADC
1.764
1.501
1.501
1.501
YES
YES
YES
YES
SAME POPULATION
N/A
Equality of Coeff. of Variations: Pooled Data ( F CALCULATED < FCRITICAL for equality )
α LEVEL
0.05
1.20
0.025
0.01
F CALCULATED
F
2.879
3.447
4.203
CRITICAL
COMMENTS
166
COMPANY
Toray
MATERIAL
PROPERTY
0° Tension - Normalized Strength
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
30
18
18
18
No. of Batches
4
6
6
6
Mean
243.955
315.086
320.048
327.759
Std.dev
18.604
24.054
17.617
22.412
% Co. Variation
7.626
7.634
5.504
6.838
Minimum
212.029
252.895
287.499
276.031
Maximum
276.014
350.861
352.099
355.054
Kb
1.652
1.732
1.732
1.732
Ka
2.799
2.866
2.866
2.866
B-Basis Value
216.021
277.268
281.634
288.420
A-Basis Value
196.621
252.493
256.470
262.649
O.S.L
Normality is
0.162
0.143
0.695
0.249
Acceptable
Acceptable
Acceptable
Acceptable
0.6438
r
2
Normality is
0.983
0.955
0.990
0.967
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9948
ADK
1.237
0.917
0.610
1.498
ADC
1.764
1.501
1.501
1.501
YES
YES
YES
YES
SAME POPULATION
N/A
α LEVEL
0.05
0.78
0.025
0.01
F CALCULATED
F
2.879
3.447
4.203
CRITICAL
COMMENTS
167
COMPANY
Toray
MATERIAL
PROPERTY
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
146
18
146
No. of Batches
2
14
6
14
7.683
7.086
6.415
3.757
Std.dev
1.163
0.595
0.570
0.319
% Co. Variation
15.137
8.394
8.880
8.492
Minimum
5.772
5.546
4.814
2.831
Maximum
9.190
8.656
7.370
4.683
Kb
1.965
1.447
1.684
1.447
Ka
3.027
2.542
2.755
2.542
Mean
B-Basis Value
6.389
6.207
5.488
3.291
A-Basis Value
5.689
5.541
4.900
2.938
O.S.L
Normality is
0.640
0.455
0.109
0.435
Acceptable
Acceptable
Acceptable
Acceptable
0.1310
r
2
Normality is
0.969
0.996
0.940
0.995
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9961
ADK
2.484
1.436
0.802
2.068
ADC
2.105
1.363
1.501
1.363
NO
NO
YES
NO
SAME POPULATION
N/A
α LEVEL
0.05
3.00
0.025
0.01
F CALCULATED
F
2.794
3.320
4.005
CRITICAL
COMMENTS
* Equality of C.V.s not satisfied at a significance level of 0.05
Pooling of data across test environments not permissible
Use Mil-Hdbk-17e method for generating allowables
168
COMPANY
Toray
MATERIAL
PROPERTY
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
18
18
25
No. of Batches
2
6
6
6
202.546
209.999
204.285
177.255
Std.dev
9.808
12.917
12.904
14.664
% Co. Variation
4.842
6.151
6.317
8.273
Minimum
189.803
189.006
174.420
135.486
Maximum
213.689
236.592
224.300
197.022
Kb
2.019
1.748
1.748
1.695
Ka
3.145
2.904
2.904
2.860
Mean
B-Basis Value
174.601
184.914
179.882
156.723
A-Basis Value
159.017
168.338
163.757
142.618
O.S.L
Normality is
0.603
0.751
0.068
0.016
Acceptable
Acceptable
Acceptable
Acceptable
0.0825
r
2
Normality is
0.978
0.993
0.947
0.947
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9778
ADK
2.484
1.011
1.266
2.264
ADC
2.105
1.501
1.501
1.540
NO
YES
YES
NO
SAME POPULATION
N/A
α LEVEL
0.05
0.59
0.025
0.01
F CALCULATED
F
2.910
3.495
4.278
CRITICAL
COMMENTS
169
COMPANY
Toray
MATERIAL
PROPERTY
0° Compression - Normalized Strength
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
18
18
25
No. of Batches
2
6
6
6
202.546
210.272
204.549
174.041
Std.dev
9.808
12.419
12.408
14.175
% Co. Variation
4.842
5.906
6.066
8.145
Minimum
189.803
190.936
174.311
134.781
Maximum
213.689
234.916
222.711
192.097
Kb
2.019
1.748
1.748
1.695
Ka
3.145
2.904
2.904
2.860
Mean
B-Basis Value
175.305
185.786
180.730
154.388
A-Basis Value
160.113
169.607
164.991
140.888
O.S.L
Normality is
0.603
0.654
0.038
0.001
Acceptable
Acceptable
Acceptable
Questionable
0.0213
r
2
Normality is
0.978
0.991
0.938
0.929
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9736
ADK
2.484
1.017
1.155
2.242
ADC
2.105
1.501
1.501
1.540
NO
YES
YES
NO
SAME POPULATION
N/A
α LEVEL
0.05
0.71
0.025
0.01
F CALCULATED
F
2.910
3.495
4.278
CRITICAL
COMMENTS
170
COMPANY
Toray
MATERIAL
PROPERTY
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
18
18
18
No. of Batches
2
6
6
6
Mean
40.964
28.814
21.425
16.886
Std.dev
3.595
1.364
1.081
0.854
% Co. Variation
8.777
4.732
5.046
5.055
Minimum
35.123
26.641
19.042
15.233
Maximum
43.986
31.121
23.472
18.490
Kb
2.028
1.758
1.758
1.758
Ka
3.163
2.925
2.925
2.925
B-Basis Value
36.594
26.149
19.443
15.324
A-Basis Value
34.147
24.380
18.128
14.287
O.S.L
Normality is
0.176
0.462
0.576
0.690
Acceptable
Acceptable
Acceptable
Acceptable
0.6746
r
2
Normality is
0.913
0.986
0.983
0.992
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9934
ADK
1.018
0.983
0.916
1.067
ADC
2.105
1.501
1.501
1.501
YES
YES
YES
YES
SAME POPULATION
N/A
α LEVEL
0.05
0.76
0.025
0.01
F CALCULATED
F
2.929
3.524
4.323
CRITICAL
COMMENTS
171
COMPANY
Toray
MATERIAL
PROPERTY
In-Plane Shear
COMMENTS
DATE
December 26, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
18
18
18
No. of Batches
2
6
6
6
Mean
23.136
22.443
18.610
13.811
Std.dev
0.266
0.633
0.547
0.596
% Co. Variation
1.151
2.819
2.938
4.313
Minimum
22.758
21.020
17.752
12.767
Maximum
23.423
23.379
19.400
14.683
Kb
2.028
1.758
1.758
1.758
Ka
3.163
2.925
2.925
2.925
B-Basis Value
21.634
21.180
17.563
13.034
A-Basis Value
20.793
20.342
16.868
12.518
O.S.L
Normality is
0.475
0.570
0.037
0.170
Acceptable
Acceptable
Acceptable
Acceptable
0.1907
r
2
Normality is
0.963
0.984
0.964
0.976
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9897
ADK
0.470
1.015
1.582
1.675
ADC
2.105
1.501
1.501
1.501
YES
YES
NO
NO
SAME POPULATION
N/A
α LEVEL
0.05
4.98
0.025
0.01
F CALCULATED
F
2.929
3.524
4.323
CRITICAL
COMMENTS
* Equality of C.V.s not satisfied at a significance level of 0.05
Pooling of data across test environments not permissible
COV of CTD test samples will be modified to 4.00% using the method prescibed
in Appendix E.
172
COMPANY
Toray
MATERIAL
PROPERTY
In-Plane Shear
COMMENTS
DATE
December 26, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
CTD
RTD
ETD
ETW
Sample Size
6
18
18
18
No. of Batches
2
6
6
6
Mean
23.136
22.443
18.610
13.811
Std.dev
0.925
0.633
0.547
0.596
% Co. Variation
4.000
2.819
2.938
4.313
Minimum
21.823
21.020
17.752
12.767
Maximum
24.135
23.379
19.400
14.683
Kb
2.028
1.758
1.758
1.758
Ka
3.163
2.925
2.925
2.925
B-Basis Value
21.546
21.106
17.501
12.988
A-Basis Value
20.655
20.218
16.765
12.442
O.S.L
Normality is
0.475
0.570
0.037
0.170
Acceptable
Acceptable
Acceptable
Acceptable
0.0239
r
2
Normality is
0.963
0.984
0.964
0.976
Acceptable
Acceptable
Acceptable
Acceptable
2
0.9840
ADK
0.470
1.015
1.582
1.675
ADC
2.105
1.501
1.501
1.501
YES
YES
NO
NO
SAME POPULATION
N/A
α LEVEL
0.05
2.14
0.025
0.01
F CALCULATED
F
2.929
3.524
4.323
CRITICAL
COMMENTS
COV of CTD test samples is modified to 4.00% using the method prescibed in
Appendix E.
173
COMPANY
Toray
MATERIAL
PROPERTY
Apparent Interlaminar Shear
COMMENTS
DATE
December 24, 2002
DATA SUMMARY
TEST CONDITION
STATISTIC
RTD
Sample Size
170
No. of Batches
14
Mean
12.489
Std.dev
0.920
% Co. Variation
7.368
Minimum
10.226
Maximum
15.029
Kb
1.464
Ka
2.593
B-Basis Value
11.142
A-Basis Value
10.103
O.S.L
Normality is
0.751
Acceptable
0.7505
r
2
0.999
Normality is
Acceptable
2
0.9989
ADK
3.963
ADC
1.364
SAME POPULATION
NO
N/A
N/A
N/A
N/A
α LEVEL
F CALCULATED
F
0.05
N/A*
0.025
0.01
CRITICAL
COMMENTS
*. Number of test conditions < 2, equality of c.v not applicable
N/A*
Pooling of data across
test environments not permissible
174
APPENDIX E. METHOD FOR TRANSFORMING VARIANCES OF TEST
SAMPLES (SUPPLEMENT TO DOT/FAA/AR-47/00)
175
The following Appendix describes a procedure to supplement the process described
in DOT/FAA/AR-47/00 for the case in which the variances are found to be unequal
per section 5.3.1.3 of that document. A supplemental is given below which provides
guidance in the situation of unequal variances and describes procedures to obtain a
conservative design allowable. Note that these procedures must be combined with
engineering judgment and that the failure modes must remain the same across
environments.
The follow excerpt is taken from DOT/FAA/AR-47/00, section 5.3.1.3 and is used as
the basis for this procedure:
In general, a coefficient of variation between 4% and 10% is typical of
composite materials. Experiences with large data sets have shown that this
range is representative of most composite material systems. Lower
coefficients of variation may be caused by the specimen fabrication and
testing by a single laboratory while higher coefficients may point to lack of
material and processing control. In cases where the coefficients of variation
of the pooled data set are higher or lower than this range, the reason for the
higher or lower coefficient of variation should be investigated before
determining design allowable values from the pooled data set. For the
coefficient of variation lower than 4%, an assigned value of 4% may be
considered as an alternative engineering solution.
Using this philosophy, the data in this report, which demonstrates unequal variances
per section 5.3.1.3 of DOT/FAA/AR-47/00 will be modified by the supplemental
procedure described in this appendix with the revised presented below. The
coefficient of variation to be used in this case will be 4% as suggested by
DOT/FAA/AR-47/00.
176
Check Equality of Variance per
section 5.3.1.3
NO
Variance
Equal ?
Using "engineering judgement",
assess the degree of inequality using
α = 0.05, 0.025 and 0.01
ACCEPTABLE
YES
QUESTIONABLE
Identify dataset problem looking at
Coefficients of Variations (CV)
HIGH CV
LOW CV
analyze "problem" dataset using
procedure per supplemental section
5.3.1.4 - substitute with modified
dataset
Proceed with analysis as presented in
section 5.3.1
Use A and B basis allowables as
generated
Figure E.1. Procedures to obtain design allowables in the case of variance
inequality
177
A simple procedure for modifying the variance of a test sample to any desired value
is presented. This procedure is useful in the case in which an environmental pooled
dataset does not pass the equality of variance test per section 5.3.1.3 of
DOT/FAA/AR-47/00. Consider a test sample xi of n specimens with an average
value of x . Let the variance of this sample be CV which is given by
n
CV =
∑(x
i =1
− x)
i
2
eq. 1
n −1
Let the desired variance of the sample be CV * . Consider a transformation of the
form
xi* = xi + α (xi )∆
eq. 2
where xi* is the transformed data, ∆ is a constant and α ( x i ) is a weighting function.
Let the weighting function be
α (xi ) = (xi − x)
eq. 3
The new variance for the transformed data is then given by
∑ (x
n
CV * =
i =1
*
i
− x*
)
2
eq. 4
n −1
where x * is the average value of the transformed sample. Substituting equations (2)
and (3) into equation (4) we obtain
∑ [{x + (x − x )∆}− x ]
n
CV * =
i =1
* 2
i
i
n −1
If we further let x * = x , equation (5) reduces to
178
eq. 5
n
CV * =
(1 + ∆ )2 ∑ ( xi − x )2
i =1
eq. 6
n −1
which gives
CV *
∆=
−1
CV
eq. 7
Thus, a sample with a known variance CV can be transformed using equation (2) to
obtain the desired variance CV*. The constant for transformation ∆ , can be
calculated using equation (7).
For example, consider a typical test sample of size n=10 with an average value of
146.27 and a corresponding CV of 0.0184 as shown in the table E.1. The sample is
transformed as per the previous discussions to obtain a transformed sample with a
CV* of 0.04 (desired value). The transformation is illustrated using a probability of
survival plot shown in Figure E.2. It can be observed that the original normal curve
has been rotated and stretched due to the transformation.
Table E.1: A typical data sample and transformed data.
i
xi
xi − x
x*i
1
2
3
4
5
6
7
8
9
10
142.3
143.2
144.1
144.8
145.9
146.8
147.5
148.2
149.6
150.3
-3.97
-3.07
-2.17
-1.47
-0.37
0.53
1.23
1.93
3.33
4.03
137.63
139.59
141.55
143.07
145.46
147.42
148.95
150.47
153.52
155.04
x
146.27
CV
0.0184
x*
CV*
∆=
0 .040
− 1 = 1.174
0. 0184
146.27
0.040
In order to further investigate the effects of the above transformation on
normality of the data, the Anderson- Darling test for normality was conducted
both the original and transformed data. The test indicated no change in
Observed Significance Level (O.S.L = 0.758) for both the samples. Thus,
179
the
for
the
the
transformation not only maintains the average value of the sample but also retains
the normality of the sample.
1
ORIGINAL DATA
TRANSFORMED DATA
PROBABIL ITY OF SURVIVAL
0.8
0.6
0.4
( xi − x )∆
0.2
0
130
140
150
160
PROPERTY
Figure E.2: Original and transformed data points
Once this sample has been transformed to the desired coefficient of variation, it may
replaced and the data analyzed per the method described in section 5.3.1 of
DOT/FAA/AR-47/00. It should be noted that this “replacement” is only for the
calculation of basis values and the original data should be retained for all follow-on
testing concerning material equivalence and acceptance.
180
APPENDIX F. RAW TESTING SUMMARIES
181
0° Tension Properties, -65°F (Dry)
Material Type: P707AG-15
Batch Number: AB991033
Test Method: ASTM D3039
Test Operator: Bryan Mines, Emmanuel Domingo
Test Frame: I
Loading Rate: 0.05 in/min
Control Mode: Stroke
Strain Gage: One biaxial gage (CEA-06-125UT-350)
Specimen Preconditioning: as machined
Test Conditions: -65°F/Dry
Ply Orientation: (0)8
Testing Facility: Intec
Test Date: 12/17/1999, 2/23/00
Specimen
Number
Specimen
Thickness
A1-910-041-1-1
A2-910-041-1-1
B1-910-041-1-1
B2-910-041-1-1
A1-910-041-1-2
B1-910-041-1-2
Average
Std. Dev.
COV, %
(in.)
0.0474
0.0477
0.0474
0.0480
0.0481
0.0475
0.0477
0.0003
0.64
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4980
6180
0.4980
5730
0.4970
5420
0.4980
5830
0.4990
5590
0.5000
5590
0.4983
5723
0.0010
264
0.21
4.61
Fiber Volume(normalizing):
Load @
0.1%
Strain
(lbs.)
418.1
408.3
446.8
438.2
-
A1-910-041-1-10
A1-910-041-1-11
A1-910-041-1-12
A2-910-041-1-10
A2-910-041-1-11
A2-910-041-1-12
B1-910-041-2-3
B1-910-041-2-4
B1-910-041-2-5
B2-910-041-2-3
B2-910-041-2-4
B2-910-041-2-5
Average
Std. Dev.
COV, %
(in.)
0.0500
0.0505
0.0507
0.0480
0.0576
0.0473
0.0480
0.0479
0.0476
0.0482
0.0483
0.0483
0.0493
0.0028
5.73
CPT (average):
Fiber Volume(batch average):
A1-910-042-2-3
B1-910-042-2-4
B2-910-042-2-1
A1-910-042-2-2
A2-910-042-2-1
B2-910-042-2-3
Average
Std. Dev.
COV, %
(in.)
0.0490
0.0480
0.0483
0.0487
0.0488
0.0483
0.0485
0.0004
0.81
Explosive failure in gage
55.1%
0.0060 in.
54.2%
Test Operator:
Test Frame:
Test Speed: 0.05 in/min
Testing Facility: NIAR Wichita State University
Test Date: 6/27/2000
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4988
6608
0.4997
6425
0.4982
6390
0.4999
6603
0.4980
5296
0.4993
5253
0.4990
6096
0.0008
643
0.16
10.54
Failure Location
&
Comments
Failure Location
&
Comments
Specimen
Thickness
Poisson's
Ratio
(0.1-0.3%)
strain)
0.330
0.310
0.310
0.320
0.318
0.010
3.02
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
246
256
227
239
215
227
230
230
199
239
245
241
222
222
254
253
275
272
242
243
228
229
265
267
237
243
21.5
16.0
9.05
6.58
Specimen
Number
54.2%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.6
18.3
18.3
18.2
18.2
18.0
18.4
18.4
18.4
18.2
0.14
0.18
0.78
0.98
Strain Gage: N/A
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.5000
6140
0.5027
5760
0.4977
5420
0.4997
5510
0.5022
5760
0.4976
5760
0.4984
5310
0.4997
6080
0.5021
6560
0.4990
5820
0.4996
5500
0.5022
6440
0.5001
5838
0.0018
396
0.36
6.79
Load @
0.3%
Strain
(lbs.)
1306
1277
1311
1320
-
Test Operator: Kin Chu
Test Frame: I
Specimen
Thickness
0.0060 in.
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
262
259
241
240
230
227
244
244
233
233
235
233
241
239
11.5
11.1
4.76
4.63
Specimen
Number
55.1%
CPT (average):
CPT (average):
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
270
276
268
268
265
267
271
275
218
222
218
219
252
255
26.3
26.7
10.44
10.49
55.1%
0.0060 in.
54.1%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.3
18.7
18.6
18.6
18.8
18.9
18.4
18.6
18.2
18.5
18.3
18.4
18.4
18.7
0.22
0.14
1.18
0.77
182
Poisson's
Ratio
(0.1-0.3%)
strain)
0.338
0.395
0.388
0.380
0.396
0.334
0.372
0.028
7.63
Failure Location
&
Comments
0° Tension Properties, -65°F (Dry) - Concluded
Test Operator:
Test Frame:
Test Speed: 0.05 in/min
Ply Orientation: (0) 8
Testing Facility: NIAR Wichita State University
CPT (average):
Specimen
Number
Specimen
Thickness
A2-910-043-1-7
A2-910-043-1-8
A2-910-043-1-9
B1-910-043-2-1
B1-910-043-2-2
B2-910-043-2-1
Average
Std. Dev.
COV, %
(in.)
0.0490
0.0489
0.0485
0.0484
0.0483
0.0480
0.0485
0.0004
0.79
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4988
5663
0.5012
5340
0.5000
6456
0.4990
5079
0.5003
5948
0.4987
5993
0.4997
5746
0.0010
495
0.20
8.61
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
232
237
218
222
266
269
210
212
246
248
250
250
237
240
21.0
20.6
8.87
8.60
55.1%
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.1
18.5
18.4
18.7
18.4
18.6
18.7
18.9
18.5
18.6
18.6
18.6
18.5
18.7
0.21
0.15
1.12
0.80
183
Poisson's
Ratio
(0.1-0.3%)
strain)
0.358
0.365
0.343
0.396
0.330
0.310
0.350
0.030
8.52
Failure Location
&
Comments
0° Tension Properties, 75°F (Dry)
Test Operator: John Smith
Test Frame: Instron 4505
Test Conditions: RT/Dry
Testing Facility: Toray Composites (America)
Test Date: 11/28/1999, 2/14/00
Specimen
Number
Specimen
Thickness
A1-910-041-1-3
A2-910-041-1-3
B1-910-041-1-3
B2-910-041-1-3
A1-910-041-1-8
B1-910-041-2-2
Average
Std. Dev.
COV, %
(in.)
0.0486
0.0478
0.0476
0.0481
0.0478
0.0481
0.0480
0.0004
0.76
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4992
7786
0.4988
8009
0.4985
7593
0.4987
7280
0.4996
7674
0.4998
7895
0.4991
7706
0.0005
257
0.10
3.33
Load @
0.1%
Strain
(lbs.)
425.9
471.7
453.2
441.3
-
Load @
0.1%
Strain
(lbs.)
434.1
473.3
446.9
452.8
-
54.1%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.9
17.9
18.0
18.1
18.2
18.2
18.3
18.5
18.1
18.2
0.19
0.23
1.03
1.27
Poisson's
Ratio
(0.1-0.3%)
strain)
0.305
0.305
0.315
0.310
0.309
0.005
1.55
Failure Location
&
Comments
CPT (average):
Test Date: 11/28/1999, 2/14/00
(in.)
0.0484
0.0491
0.0484
0.0483
0.0473
0.0481
0.0483
0.0006
1.25
Load @
0.3%
Strain
(lbs.)
1292
1340
1319
1337
-
A1-910-043-1-1
A2-910-043-1-1
B1-910-043-1-1
B2-910-043-1-1
A1-910-043-1-6
B1-910-043-1-6
Average
Std. Dev.
COV, %
0.0060 in.
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
252
253
301
302
293
295
347
351
298
294
332
332
304
304
33.3
34.0
11.0
11.2
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4982
6644
0.4978
7846
0.4981
7687
0.4975
7951
0.4978
7529
0.4974
8111
0.4978
7628
0.0003
523
0.07
6.85
55.1%
CPT (average):
Test Date: 11/28/1999, 2/14/00
Specimen
Thickness
Specimen
Number
Failure Location
&
Comments
(in.)
0.0482
0.0482
0.0482
0.0485
0.0473
0.0480
0.0481
0.0004
0.82
Poisson's
Ratio
(0.1-0.3%)
strain)
0.330
0.300
0.305
0.305
0.310
0.014
4.37
B1-910-042-1-1
B2-910-042-1-1
A1-910-042-1-1
A2-910-042-1-1
A1-910-042-1-6
B1-910-042-1-6
Average
Std. Dev.
COV, %
54.2%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.6
18.8
18.4
18.4
18.3
18.1
18.0
18.1
18.3
18.3
0.23
0.33
1.27
1.82
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
0.4982
6048
0.4982
7222
0.4982
7043
0.4981
8389
0.4977
7018
0.4975
7929
0.4980
7275
0.0003
812
0.06
11.16
Load @
0.3%
Strain
(lbs.)
1327
1351
1321
1306
-
Specimen
Thickness
0.0060 in.
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
321
325
336
334
320
317
304
304
321
320
328
329
322
322
10.7
10.6
3.34
3.29
Specimen
Number
55.1%
CPT (average):
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
275
278
321
328
319
322
331
333
320
315
339
340
318
319
22.1
22.0
7.0
6.91
Load @
0.1%
Strain
(lbs.)
458.9
458.1
474.5
478.6
-
184
Load @
0.3%
Strain
(lbs.)
1322
1321
1358
1328
-
55.1%
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.9
18.0
17.7
18.1
18.3
18.5
17.7
17.8
17.9
18.1
0.31
0.29
1.73
1.58
Poisson's
Ratio
(0.1-0.3%)
strain)
0.335
0.300
0.305
0.290
0.308
0.019
6.30
Failure Location
&
Comments
Test Conditions: 180°F/Dry
Test Date: 11/28/1999, 2/17/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-4
A2-910-041-1-4
B1-910-041-1-4
B2-910-041-1-4
A2-910-041-1-9
B2-910-041-2-2
Average
Std. Dev.
COV, %
(in.)
0.0494
0.0476
0.0476
0.0481
0.0479
0.0480
0.0481
0.0007
1.40
(in.)
0.5002
0.4996
0.4993
0.4995
0.4983
0.4998
0.4994
0.0006
0.12
Ultimate
Tensile
Load
(lbs.)
7608
7800
7318
7960
6922
7725
7556
378
5.00
Load @
0.1%
Strain
(lbs.)
460.0
447.7
445.4
451.3
-
Ultimate
Tensile
Load
(lbs.)
6899
7966
8447
7377
8090
7360
7690
573
7.45
Load @
0.1%
Strain
(lbs.)
477.2
475.7
452.2
464.6
-
Failure Location
&
Comments
CPT (average):
Test Date: 11/28/1999, 2/17/00
(in.)
0.5000
0.4996
0.4999
0.5021
0.4975
0.4980
0.4995
0.0016
0.33
Poisson's
Ratio
(0.1-0.3%)
strain)
0.325
0.310
0.330
0.305
0.318
0.012
3.75
(in.)
0.0482
0.0492
0.0485
0.0483
0.0488
0.0476
0.0484
0.0005
1.13
54.1%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.0
18.1
18.2
18.4
18.2
18.1
17.4
17.5
17.9
18.0
0.39
0.36
2.15
2.02
A1-910-043-1-2
A2-910-043-1-2
B1-910-043-1-2
B2-910-043-1-2
A2-910-043-1-6
B2-910-043-1-6
Average
Std. Dev.
COV, %
Load @
0.3%
Strain
(lbs.)
1344
1355
1321
1303
-
Specimen
Width
0.0060 in.
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
287
288
330
333
353
353
306
308
344
340
309
309
321
322
25.2
24.0
7.83
7.47
Specimen
Thickness
55.1%
CPT (average):
Test Date: 11/28/1999, 2/17/00
Specimen
Number
(in.)
0.4999
0.4997
0.4998
0.4997
0.4975
0.4975
0.4990
0.0012
0.24
Failure Location
&
Comments
(in.)
0.0481
0.0483
0.0479
0.0483
0.0473
0.0479
0.0480
0.0004
0.77
Poisson's
Ratio
(0.1-0.3%)
strain)
0.310
0.305
0.295
0.315
0.306
0.009
2.79
A1-910-042-1-2
A2-910-042-1-2
B1-910-042-1-2
B2-910-042-1-2
A2-910-042-1-6
B2-910-042-1-6
Average
Std. Dev.
COV, %
54.2%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.3
17.9
17.9
17.9
17.6
17.5
18.0
18.1
17.7
17.8
0.31
0.23
1.75
1.27
Specimen
Width
Load @
0.3%
Strain
(lbs.)
1316
1300
1282
1314
-
Specimen
Thickness
0.0060 in.
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
308
318
328
327
308
307
332
334
290
291
322
324
315
317
15.7
15.5
5.00
4.91
Specimen
Number
55.1%
CPT (average):
Ultimate
Tensile
Load
(lbs.)
8313
7552
7681
7386
7744
7925
7767
323
4.16
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
345
346
307
315
317
320
305
306
319
324
335
332
321
324
15.6
13.9
4.85
4.28
Load @
0.1%
Strain
(lbs.)
448.6
479.0
478.2
489.6
-
185
Load @
0.3%
Strain
(lbs.)
1297
1337
1314
1345
-
55.1%
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.6
17.7
17.5
17.9
17.3
17.4
17.6
17.7
17.5
17.7
0.17
0.20
0.99
1.12
Poisson's
Ratio
(0.1-0.3%)
strain)
0.315
0.290
0.325
0.285
0.304
0.019
6.36
Failure Location
&
Comments
0° Tension Properties, 180°F (Wet)
Specimen Preconditioning: per Section 3.2 of AGATE Methodology
Test Conditions: 180°F
Test Date: 3/6/2000
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-5
A2-910-041-1-5
B1-910-041-1-5
B2-910-041-1-5
A1-910-041-1-6
B1-910-041-1-6
Average
Std. Dev.
COV, %
(in.)
0.0506
0.0474
0.0478
0.0481
0.0512
0.0475
0.0488
0.0017
3.47
(in.)
0.5028
0.5021
0.5018
0.5020
0.4978
0.4979
0.5007
0.0023
0.45
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
277
293
329
326
318
318
315
318
259
277
333
331
305
311
30.2
20.8
9.90
6.71
Load @
0.1%
Strain
(lbs.)
445.6
455.4
435.4
463.7
-
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
343
343
345
344
355
356
347
350
319
317
353
355
344
344
12.9
14.4
3.75
4.18
Load @
0.1%
Strain
(lbs.)
403.6
428.4
408.9
435.2
-
Failure Location
&
Comments
CPT (average):
(in.)
0.4989
0.4983
0.4993
0.4998
0.4998
0.5000
0.4993
0.0007
0.13
Poisson's
Ratio
(0.1-0.3%)
strain)
0.304
0.335
0.331
0.321
0.322
0.014
4.29
(in.)
0.0481
0.0493
0.0484
0.0481
0.0478
0.0478
0.0483
0.0005
1.10
54.1%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.4
17.4
17.1
17.1
17.7
17.7
17.3
17.5
17.4
17.4
0.24
0.26
1.36
1.50
A1-910-043-1-3
A2-910-043-1-3
B1-910-043-1-3
B2-910-043-1-3
A1-910-043-1-4
B1-910-043-1-4
Average
Std. Dev.
COV, %
Load @
0.3%
Strain
(lbs.)
1235
1246
1256
1270
-
Specimen
Width
0.0060 in.
Ultimate
Tensile
Load
(lbs.)
8180
8232
8500
8357
7593
8495
8226
337
4.10
Specimen
Thickness
55.1%
CPT (average):
Specimen
Number
(in.)
0.4987
0.4991
0.4988
0.4987
0.5002
0.4995
0.4992
0.0006
0.12
Failure Location
&
Comments
(in.)
0.0478
0.0478
0.0480
0.0484
0.0476
0.0482
0.0480
0.0003
0.59
Poisson's
Ratio
(0.1-0.3%)
strain)
0.340
0.340
0.320
0.275
0.319
0.031
9.59
A1-910-042-1-3
A2-910-042-1-3
B1-910-042-1-3
B2-910-042-1-3
A1-910-042-1-4
B1-910-042-1-4
Average
Std. Dev.
COV, %
54.2%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
17.2
18.2
18.1
18.0
17.7
17.7
17.9
18.0
17.7
18.0
0.40
0.21
2.28
1.19
Specimen
Width
Load @
0.3%
Strain
(lbs.)
1320
1317
1283
1328
-
Specimen
Thickness
0.0060 in.
Ultimate
Tensile
Load
(lbs.)
7046
7816
7611
7618
6596
7883
7428
503
6.77
Specimen
Number
55.1%
CPT (average):
Ultimate
Tensile
Load
(lbs.)
7937
7419
7805
7497
8468
8458
7931
454
5.73
Ultimate Tensile
Strength
Actual
Norm.
(ksi)
(ksi)
331
331
302
310
323
326
312
313
354
353
354
352
329
331
21.4
18.7
6.50
5.64
Load @
0.1%
Strain
(lbs.)
460.7
456.8
434.9
478.7
-
186
Load @
0.3%
Strain
(lbs.)
1327
1319
1283
1345
-
55.1%
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
18.1
18.1
17.6
18.0
17.5
17.7
18.0
18.1
17.8
18.0
0.27
0.19
1.54
1.03
Poisson's
Ratio
(0.1-0.3%)
strain)
0.346
0.353
0.312
0.298
0.327
0.027
8.14
Failure Location
&
Comments
90° Tension Properties, -65°F (Dry)
Test Operator: Bryan Mines, Emmanuel Domingo
Test Frame: I
Strain Gage: One axial gage (CEA-06-125UW-350)
Ply Orientation: (90)1 8
Test Date: 12/17/1999, 2/23/00
Specimen
Number
Specimen
Thickness
A1-910-041-1-1
A2-910-041-1-1
B1-910-041-1-1
B2-910-041-1-1
A1-910-041-1-2
B1-910-041-1-2
Average
Std. Dev.
COV, %
(in.)
0.1049
0.1062
0.1048
0.1085
0.1065
0.1062
0.1062
0.0013
1.27
Specimen Ultimate
Width
Tensile
Load
(in.)
(lbs.)
1.0000
964
0.9990
902
1.0000
802
1.0000
789
1.0020
823
1.0000
613
1.0002
816
0.0010
120
0.10
14.66
CPT (average):
Ultimate
Tensile
Strength
(ksi)
9.19
8.50
7.65
7.27
7.71
5.77
7.68
1.16
15.14
Load @
0.1%
Strain
(lbs.)
154.3
143.2
133.9
145.6
-
187
Load @
0.3%
Strain
(lbs.)
439.8
426.8
405.9
419.8
-
0.0060 in.
54.2%
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.35
1.34
1.30
1.26
1.31
0.04
3.13
Failure Location
&
Comments
Failure in gage area
Failure in tab area
Failure in tab area
Strain Gage: One axial gage (C-960401-A)
Test Date: 12/4/1999, 2/14/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-3
A2-910-041-1-3
B1-910-041-1-3
B2-910-041-1-3
A1-910-041-1-8
B1-910-041-1-8
Average
Std. Dev.
COV, %
(in.)
0.1072
0.1078
0.1073
0.1086
0.1078
0.1072
0.1076
0.0006
0.51
(in.)
1.0012
1.0000
1.0019
1.0014
0.9991
0.9995
1.0005
0.0011
0.11
Ultimate
Tensile
Load
(lbs.)
867
692
750
786
767
782
774
57
7.38
CPT (average):
Ultimate
Tensile
Strength
(ksi)
8.08
6.42
6.98
7.23
7.12
7.31
7.19
0.54
7.51
Load @
0.1%
Strain
(lbs.)
154.2
153.5
141.7
149.8
-
0.0060 in.
54.2%
Load @
0.3%
Strain
(lbs.)
415.0
408.8
396.2
402.9
-
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.22
1.18
1.18
1.16
1.19
0.02
1.79
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
CPT (average):
Test Date: 12/4/1999, 2/14/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-1
A2-910-042-1-1
B1-910-042-1-1
B2-910-042-1-1
A1-910-042-1-8
B1-910-042-1-8
Average
Std. Dev.
COV, %
(in.)
0.1056
0.1064
0.1049
0.1048
0.1084
0.1086
0.1065
0.0017
1.56
(in.)
0.9997
0.9996
0.9999
0.9993
1.0012
1.0012
1.0002
0.0008
0.08
Ultimate
Tensile
Load
(lbs.)
892
797
882
907
753
640
812
104
12.76
Ultimate
Tensile
Strength
(ksi)
8.45
7.49
8.41
8.66
6.94
5.89
7.64
1.08
14.17
Load @
0.1%
Strain
(lbs.)
145.3
157.0
148.8
150.9
-
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
399.9
417.9
408.7
413.2
-
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.21
1.23
1.24
1.25
1.23
0.02
1.61
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
Test Date: 12/4/1999, 2/14/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-1
A2-910-043-1-1
B1-910-043-1-1
B2-910-043-1-1
A1-910-043-1-6
B1-910-043-1-6
Average
Std. Dev.
COV, %
(in.)
0.1050
0.1055
0.1057
0.1062
0.1084
0.1078
0.1064
0.0014
1.30
(in.)
0.9999
0.9969
0.9997
0.9999
1.0010
1.0010
0.9997
0.0015
0.15
Ultimate
Tensile
Load
(lbs.)
698
757
864
793
687
730
755
66
8.75
CPT (average):
Ultimate
Tensile
Strength
(ksi)
6.66
7.20
8.18
7.46
6.33
6.77
7.10
0.66
9.36
Load @
0.1%
Strain
(lbs.)
145.9
147.4
151.4
149.3
-
188
Load @
0.3%
Strain
(lbs.)
404.6
408.3
412.2
415.5
-
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.23
1.24
1.23
1.25
1.24
0.01
0.77
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
90° Tension Properties, 75°F (Dry) - continued
Material Type:
Batch Number:
Test Method:
Specimen
Panel Coupon
A-3
A-3
A-3
A-3
A-5
A-5
A-5
A-5
A-3
A-3
A-3
A-3
A-5
A-5
A-5
A-5
B-4
B-4
B-4
B-4
B-6
B-6
B-6
B-6
B-4
B-4
B-4
B-4
B-6
B-6
B-6
B-6
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
Material Type:
Batch Number:
Test Method:
Specimen
Panel Coupon
A-15
A-15
A-15
A-15
A-17
A-17
A-17
A-17
A-15
A-15
A-15
A-15
A-17
A-17
A-17
A-17
B-16
B-16
B-16
B-16
B-18
B-18
B-18
B-18
B-16
B-16
B-16
B-16
B-18
B-18
B-18
B-18
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
P707AG-15
AB010955
ASTM D3039
Specimen Specimen
Thickness Width
(in.)
(in.)
0.10703
0.10998
0.10945
0.10757
0.10788
0.10837
0.10822
0.10830
0.10822
0.10970
0.10878
0.10653
0.10845
0.10830
0.10845
0.10707
0.10843
0.10930
0.10925
0.10897
0.10750
0.10850
0.10880
0.10820
0.10927
0.10922
0.10910
0.10767
0.10810
0.10877
0.10865
0.10673
1.00053
1.00082
1.00060
1.00058
1.00042
1.00155
1.00077
1.00072
1.00068
1.00057
1.00073
1.00153
1.00080
1.00067
1.00068
1.00167
1.00042
1.00135
0.99997
1.00012
1.00057
1.00110
1.00043
1.00042
1.00090
1.00087
1.00008
1.00158
1.00055
1.00040
1.00042
1.00117
P707AG-15
AB020234
ASTM D3039
Specimen Specimen
Thickness Width
(in.)
(in.)
0.10743
0.10850
0.10752
0.10785
0.10757
0.10833
0.10852
0.10813
0.10815
0.10810
0.10747
0.10603
0.10815
0.10855
0.10843
0.10670
0.10758
0.10838
0.10835
0.10805
0.10723
0.10862
0.10767
0.10872
0.10805
0.10842
0.10822
0.10683
0.10785
0.10838
0.10838
0.10738
0.99982
0.99978
0.99972
0.99977
1.00025
1.00058
1.00062
0.99977
0.99978
0.99992
0.99972
0.99960
1.00068
1.00050
0.99995
1.00075
1.00063
1.00042
1.00093
1.00063
1.00027
1.00073
1.00060
0.99983
1.00097
1.00055
1.00067
1.00078
1.00065
1.00042
1.00047
1.00073
Panel Fabrication: TCA - vacuum bagged at 270°F
Ultimate Tensile
Failure
Testing
Test Conditions
Test
Test
Test
Load
Strength
Location
Facility
Temp
RH
Operator
Frame
Date
(lbs)
(ksi)
(°F)
(%)
7.51
804.6
Lateral, At grip/tab, Bottom
TCA
73
50
John S. Inst 4505 6/10/2002
6.49
714.4
Lateral, Gage, Middle
TCA
73
50
John S. Inst 4505 6/10/2002
822.2
7.51
TCA
73
50
John S. Inst 4505 6/10/2002
817.0
7.59
Lateral, <1W from grip/tab, Top
TCA
73
50
John S. Inst 4505 6/10/2002
749.1
6.94
TCA
73
50
Debra W. Inst 4505 6/10/2002
759.7
7.00
TCA
73
50
Debra W. Inst 4505 6/10/2002
786.0
7.26
TCA
73
50
Debra W. Inst 4505 6/10/2002
802.6
7.41
TCA
73
50
Debra W. Inst 4505 6/10/2002
860.7
7.95
Lateral, <1W from grip/tab, Bottom
NIAR
74
68
Ken G. MTS 318.25 6/17/2002
6.53
717.0
NIAR
74
68
Ken G. MTS 318.25 6/17/2002
6.78
737.8
Lateral, At grip/tab, Top
NIAR
74
68
Ken G. MTS 318.25 6/17/2002
896.6
8.40
NIAR
74
68
Ken G. MTS 318.25 6/17/2002
776.8
7.16
NIAR
73
69
Ken G. MTS 318.25 6/17/2002
726.6
6.70
NIAR
73
69
Ken G. MTS 318.25 6/17/2002
733.1
6.76
Lateral, <1W from grip/tab, Top & Bottom
NIAR
73
69
Ken G. MTS 318.25 6/17/2002
838.8
7.82
NIAR
73
69
Ken G. MTS 318.25 6/17/2002
806.2
7.43
TCA
73
50
Debra W. Inst 4505 6/10/2002
785.4
7.18
TCA
73
50
Debra W. Inst 4505 6/10/2002
781.3
7.15
Lateral, < 1W from grip/tab, Top
TCA
73
50
Debra W. Inst 4505 6/10/2002
787.3
7.22
TCA
73
50
Debra W. Inst 4505 6/10/2002
7.84
843.7
TCA
73
50
John S. Inst 4505 6/10/2002
750.3
6.91
TCA
73
50
John S. Inst 4505 6/10/2002
759.1
6.97
TCA
73
50
John S. Inst 4505 6/10/2002
697.5
6.44
TCA
73
50
John S. Inst 4505 6/10/2002
761.6
6.96
NIAR
76
64
Shin MTS 318.25 6/17/2002
808.7
7.40
NIAR
76
64
Shin MTS 318.25 6/17/2002
810.0
7.42
NIAR
76
64
Shin MTS 318.25 6/17/2002
917.6
8.51
NIAR
76
64
Shin MTS 318.25 6/17/2002
795.1
7.35
NIAR
75
66
Shin MTS 318.25 6/17/2002
715.4
6.57
NIAR
75
66
Shin MTS 318.25 6/17/2002
7.07 Lateral, <1W from grip/tab, Top & Gage, Middle NIAR
75
66
Shin MTS 318.25 6/17/2002
768.8
764.9
7.16
NIAR
75
66
Shin MTS 318.25 6/17/2002
7.23
0.505
6.98
Ultimate Tensile
Failure
Load
Strength
Location
(lbs)
(ksi)
788.0
657.7
755.8
669.2
743.6
799.3
672.9
740.9
719.2
708.2
811.2
853.7
721.5
715.9
750.4
812.8
801.1
742.0
774.5
794.4
710.0
685.6
740.9
715.5
738.4
793.3
719.2
807.3
752.0
769.1
749.8
770.6
7.34
6.06
7.03
6.21
6.91
7.37
6.20
6.85
6.65
6.55
7.55
8.05
6.67
6.59
6.92
7.61
7.44
6.84
7.14
7.35
6.62
6.31
6.88
6.58
6.83
7.31
6.64
7.55
6.97
7.09
6.92
7.17
6.94
0.458
6.60
189
Testing
Test Conditions
Test
Test
Facility
Temp
RH
Operator
Frame
(°F)
(%)
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
73
73
73
73
73
73
73
73
78
78
78
78
77
77
77
77
73
73
73
73
73
73
73
73
76
76
76
76
77
77
77
77
50
50
50
50
50
50
50
50
60
60
60
60
63
63
63
63
50
50
50
50
50
50
50
50
66
66
66
66
63
63
63
63
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Shin
Shin
Shin
Shin
Shin
Shin
Shin
Shin
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Shin
Shin
Shin
Shin
Shin
Shin
Shin
Shin
Test
Date
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
Inst 4505 6/10/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
MTS 318.25 6/17/2002
90° Tension Properties, 75°F (Dry) - continued
Material Type:
Batch Number:
Test Method:
Specimen
Panel Coupon
A-27
A-27
A-27
A-27
A-29
A-29
A-29
A-29
A-27
A-27
A-27
A-27
A-29
A-29
A-29
A-29
B-28
B-28
B-28
B-28
B-30
B-30
B-30
B-30
B-28
B-28
B-28
B-28
B-30
B-30
B-30
B-30
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
Material Type:
Batch Number:
Test Method:
Specimen
Panel Coupon
A-39
A-39
A-39
A-39
A-41
A-41
A-41
A-41
A-39
A-39
A-39
A-39
A-41
A-41
A-41
A-41
B-40
B-40
B-40
B-40
B-42
B-42
B-42
B-42
B-40
B-40
B-40
B-40
B-42
B-42
B-42
B-42
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
P707AG-15
AB020436
ASTM D3039
Specimen Specimen
Thickness Width
(in.)
(in.)
0.11040 1.00055
0.11142 1.00047
0.11177 1.00053
0.11107 0.99945
0.11025 1.00030
0.11133 1.00017
0.11152 1.00053
0.11098 1.00035
0.11123 1.00045
0.11173 1.00037
0.11160 0.99857
0.10875 1.00033
0.11083 1.00090
0.11145 1.00040
0.11122 1.00048
0.10960 1.00060
0.11047 1.00032
0.11117 1.00208
0.11147 1.00028
0.11100 1.00007
0.11063 1.00043
0.11163 1.00030
0.11120 1.00030
0.11082 1.00037
0.11073 1.00058
0.11137 0.99995
0.11152 0.99987
0.10935 1.00050
0.11128 1.00063
0.11137 1.00035
0.11132 1.00023
0.10978 1.00053
Ultimate Tensile
Failure
Load
Strength
Location
(lbs)
(ksi)
837.1
7.58
774.8
6.95
765.1
6.84
741.4
6.68
852.3
7.73
822.7
7.39
809.7
7.26
6.72
746.0
855.7
7.69
766.0
6.85
769.7
6.91
857.9
7.89
833.4
7.51
732.7
6.57
787.2
7.07
8.02
879.3
789.4
7.14
747.8
6.71
809.8
7.26
789.6
7.11
823.0
7.44
771.3
6.91
846.3
7.61
7.42
822.5
847.8
7.65
742.8
6.67
815.4
7.31
871.5
7.97
742.6
6.67
854.8
7.67
728.9
6.55
901.9
8.21
7.25
0.469
6.47
Testing
Test Conditions
Test
Test
Test
Facility
Temp
RH
Operator
Frame
Date
(°F)
(%)
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
72
55
Ken G. MTS 318.25 6/14/2002
NIAR
72
55
Ken G. MTS 318.25 6/14/2002
NIAR
72
55
Ken G. MTS 318.25 6/14/2002
NIAR
72
55
Ken G. MTS 318.25 6/14/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
NIAR
76
63
Shin MTS 318.25 6/17/2002
NIAR
76
63
Shin MTS 318.25 6/17/2002
NIAR
76
63
Shin MTS 318.25 6/17/2002
NIAR
76
63
Shin MTS 318.25 6/17/2002
NIAR
78
61
Shin MTS 318.25 6/17/2002
NIAR
78
61
Shin MTS 318.25 6/17/2002
NIAR
78
61
Shin MTS 318.25 6/17/2002
NIAR
78
61
Shin MTS 318.25 6/17/2002
P707AG-15
AB020552
ASTM D3039
Specimen Specimen
Thickness Width
(in.)
(in.)
0.10647 1.00053
0.10832 1.00077
0.10833 1.00047
0.10815 0.99942
0.10693 1.00062
0.10903 1.00053
0.10873 1.00052
0.10835 0.99987
0.10748 1.00075
0.10845 1.00055
0.10817 0.99998
0.10508 1.00088
0.10832 1.00095
0.10903 1.00043
0.10858 0.99982
0.10532 1.00053
0.10698 1.00053
0.10793 1.00093
0.10832 1.00042
0.10798 1.00022
0.10758 1.00068
0.10822 1.00043
0.10818 1.00067
0.10782 1.00080
0.10758 1.00047
0.10832 1.00037
0.10808 0.99955
0.10648 1.00057
0.10835 1.00070
0.10833 1.00063
0.10818 1.00067
0.10712 1.00055
Ultimate Tensile
Failure
Load
Strength
Location
(lbs)
(ksi)
779.4
7.32
733.0
6.76
683.9
6.31
600.1
5.55
851.7
7.96
700.0
6.42
707.1
6.50
7.57
820.5
662.0
6.15
623.3
5.74
632.3
5.85
685.6
6.52
807.3
7.45
763.3
7.00
731.8
6.74
770.6
7.31
811.7
7.58
777.8
7.20
6.81
738.5
7.33
791.7
747.0
6.94
705.5
6.52
600.4
5.55
742.0
6.88
722.9
6.72
639.9
5.91
677.8
6.27
839.3
7.88
732.0
6.75
749.4
6.91
7.17
776.5
843.0
7.87
6.79
0.666
9.80
Testing
Test Conditions
Test
Test
Test
Facility
Temp
RH
Operator
Frame
Date
(°F)
(%)
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
78
60
Shin MTS 318.25 6/17/2002
NIAR
77
62
Shin MTS 318.25 6/17/2002
NIAR
77
62
Shin MTS 318.25 6/17/2002
NIAR
77
62
Shin MTS 318.25 6/17/2002
NIAR
77
62
Shin MTS 318.25 6/17/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
Debra W. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
TCA
73
50
John S. Inst 4505 6/10/2002
NIAR
77
63
Shin MTS 318.25 6/17/2002
NIAR
77
63
Shin MTS 318.25 6/17/2002
NIAR
77
63
Shin MTS 318.25 6/17/2002
NIAR
77
63
Shin MTS 318.25 6/17/2002
NIAR
77
61
Shin MTS 318.25 6/17/2002
NIAR
77
61
Shin MTS 318.25 6/17/2002
NIAR
77
61
Shin MTS 318.25 6/17/2002
NIAR
77
61
Shin MTS 318.25 6/17/2002
190
CPT (average):
Test Date: 12/7/1999, 2/17/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A2-910-041-1-4
A1-910-041-1-4
B1-910-041-1-4
B2-910-041-1-4
A2-910-041-1-8
B2-910-041-1-8
Average
Std. Dev.
COV, %
(in.)
0.1082
0.1079
0.1079
0.1083
0.1086
0.1077
0.1081
0.0003
0.29
(in.)
0.9988
0.9996
1.0014
1.0009
0.9994
0.9984
0.9998
0.0012
0.12
Ultimate
Tensile
Load
(lbs.)
720
687
723
671
670
677
691
24
3.49
Ultimate
Tensile
Strength
(ksi)
6.66
6.37
6.69
6.19
6.17
6.30
6.40
0.23
3.57
Load @
0.1%
Strain
(lbs.)
139.9
141.7
141.3
138.9
-
0.0060 in.
54.2%
Load @
0.3%
Strain
(lbs.)
367.6
374.4
369.4
367.1
-
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.05
1.08
1.06
1.05
1.06
0.01
1.17
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
Test Date: 12/7/1999, 2/17/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-2
A2-910-042-1-2
B1-910-042-1-2
B2-910-042-1-2
A2-910-042-1-6
B2-910-042-1-6
Average
Std. Dev.
COV, %
(in.)
0.1067
0.1071
0.1066
0.1066
0.1080
0.1095
0.1074
0.0011
1.07
(in.)
1.0013
0.9993
0.9998
0.9987
1.0010
1.0004
1.0001
0.0010
0.10
Ultimate
Tensile
Load
(lbs.)
738
789
726
734
684
618
715
58
8.11
CPT (average):
Ultimate
Tensile
Strength
(ksi)
6.91
7.37
6.81
6.89
6.33
5.64
6.66
0.60
8.98
Load @
0.1%
Strain
(lbs.)
138.1
143.3
140.1
144.5
-
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
366.7
376.5
373.6
380.5
-
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.07
1.09
1.10
1.11
1.09
0.02
1.47
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
Test Date: 12/7/1999, 2/17/00
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-2
A2-910-043-1-2
B1-910-043-1-2
B2-910-043-1-2
A2-910-043-1-6
B2-910-043-1-6
Average
Std. Dev.
COV, %
(in.)
0.1068
0.1067
0.1063
0.1075
0.1092
0.1075
0.1073
0.0010
0.97
(in.)
1.0013
0.9987
0.9993
0.9996
1.0005
1.0007
1.0000
0.0010
0.10
Ultimate
Tensile
Load
(lbs.)
720
678
737
669
526
651
664
75
11.27
CPT (average):
Ultimate
Tensile
Strength
(ksi)
6.73
6.37
6.94
6.23
4.81
6.05
6.19
0.75
12.10
Load @
0.1%
Strain
(lbs.)
147.1
142.5
142.2
134.1
-
191
Load @
0.3%
Strain
(lbs.)
383.3
378.3
374.3
367.9
-
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
1.10
1.11
1.09
1.09
1.10
0.01
0.80
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
90° Tension Properties, 180°F (Wet)
CPT (average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-5
A2-910-041-1-5
B1-910-041-1-5
B2-910-041-1-5
A2-910-041-1-7
B2-910-041-1-7
Average
Std. Dev.
COV, %
(in.)
0.1080
0.1088
0.1081
0.1089
0.1088
0.1081
0.1084
0.0004
0.38
(in.)
0.9997
0.9988
0.9998
0.9995
1.0004
1.0009
0.9998
0.0007
0.07
Ultimate
Tensile
Load
(lbs.)
418
429
400
398
436
412
416
16
3.73
Ultimate
Tensile
Strength
(ksi)
3.87
3.95
3.71
3.65
4.01
3.81
3.83
0.14
3.61
Load @
0.1%
Strain
(lbs.)
140.4
123.8
130.8
116.9
-
0.0060 in.
54.2%
Load @
0.3%
Strain
(lbs.)
333.4
321.1
333.1
313.2
-
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
0.89
0.91
0.94
0.90
0.91
0.02
2.02
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-3
A2-910-042-1-3
B1-910-042-1-3
B2-910-042-1-3
A1-910-042-1-4
B1-910-042-1-4
Average
Std. Dev.
COV, %
(in.)
0.1072
0.1077
0.1080
0.1079
0.1079
0.1085
0.1078
0.0004
0.38
(in.)
1.0011
1.0010
1.0013
1.0002
0.9993
1.0012
1.0007
0.0008
0.08
Ultimate
Tensile
Load
(lbs.)
407
394
418
373
412
404
401
16
4.01
CPT (average):
Ultimate
Tensile
Strength
(ksi)
3.79
3.66
3.87
3.46
3.82
3.72
3.72
0.15
3.99
Load @
0.1%
Strain
(lbs.)
120.4
120.2
122.9
124.1
-
CPT (average):
(in.)
1.0011
1.0003
1.0006
1.0009
0.9993
0.9994
1.0003
0.0008
0.08
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
(in.)
0.1077
0.1070
0.1077
0.1077
0.1079
0.1076
0.1076
0.0003
0.30
Failure
Failure
Failure
Failure
Failure
Failure
A1-910-043-1-3
A2-910-043-1-3
B1-910-043-1-4
B2-910-043-1-4
A1-910-043-1-4
B1-910-043-1-5
Average
Std. Dev.
COV, %
Failure Location
&
Comments
Specimen
Width
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
0.94
0.93
0.94
0.93
0.93
0.01
0.70
Specimen
Thickness
Load @
0.3%
Strain
(lbs.)
321.8
320.6
326.6
324.4
-
Specimen
Number
0.0060 in.
54.1%
Ultimate
Tensile
Load
(lbs.)
401
400
383
372
412
355
387
21
5.53
Ultimate
Tensile
Strength
(ksi)
3.72
3.74
3.55
3.45
3.82
3.30
3.60
0.20
5.54
Load @
0.1%
Strain
(lbs.)
121.9
123.6
143.3
122.0
-
192
Load @
0.3%
Strain
(lbs.)
323.6
326.1
332.9
315.4
-
0.0060 in.
54.9%
Tensile Modulus
(0.1-0.3% strain)
Actual
(msi)
0.94
0.95
0.88
0.90
0.91
0.03
3.43
Failure Location
&
Comments
Failure
Failure
Failure
Failure
Failure
Failure
in
in
in
in
in
in
gage
gage
gage
gage
gage
gage
area
area
area
area
area
area
90° Tension - Strength
(180°F/Wet)
Toray Composites (America), Inc.
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
TC1616SE-A-12
TCQAL-T-1018 Rev. A - Test Plan
P707AG-15
AB010955
ASTM D3039
TCA - vacuum bagged at 270°F
(90) 18
Specimen
Thickness
(in.)
Specimen Ultimate
Width
Load
(in.)
(lbs)
A-7
A-7
A-7
A-9
A-9
A-9
A-9
A-9
A-11
A-11
A-11
A-11
A-11
A-11
A-11
"A" Panel
3
5
7
1
3
5
7
8
2
4
6
8
3
5
7
Average
Std, Dev.
COV, %
0.11007
0.10952
0.10963
0.10815
0.10860
0.10873
0.10832
0.10702
0.10907
0.10928
0.10853
0.10768
0.10953
0.10908
0.10892
1.00113
1.00058
1.00000
1.00025
1.00125
1.00083
1.00012
1.00163
1.00020
1.00035
0.99972
1.00050
1.00052
1.00057
0.99952
381.7
386.1
398.7
449.3
430.9
415.2
441.9
477.6
375.2
421.1
414.3
413.1
390.3
430.0
400.6
B-8
B-8
B-8
B-8
B-10
B-10
B-10
B-10
B-8
B-8
B-8
B-8
B-10
B-10
B-10
B-10
"B" Panel
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
0.10788
0.10837
0.10868
0.10875
0.10762
0.10903
0.10933
0.10893
0.10800
0.10832
0.10900
0.10737
0.10833
0.10925
0.10918
0.10645
1.00067
1.00153
1.00075
1.00013
1.00035
1.00102
1.00038
1.00013
1.00088
1.00065
0.99988
1.00153
1.00075
1.00033
1.00032
1.00105
505.5
465.2
444.4
436.5
435.7
385.2
390.0
399.7
496.9
446.8
488.1
479.8
455.6
388.4
389.2
402.5
TCA Process Specification:
TCA Material Specification:
Test Conditions:
Specimen Preconditioning:
Loading Rate:
Control Mode:
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07 Rev. B
180°F
moisture saturation per SACMA SRM SRM-11-94
0.05 in/min
Stroke
Tensile
Strength
(ksi)
Failure Location
&
Comments
Testing
Facility
3.46
3.52
3.64
4.15
3.96
3.82
4.08
4.46
3.44
3.85
3.82
3.83
3.56
3.94
3.68
3.81
0.280
7.34
4.68
4.29
4.09
4.01
4.05
3.53
3.57
3.67
4.60
4.12
4.48
4.46
4.20
3.55
3.56
3.78
4.04
0.395
9.79
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180
180
180
180
180
180
180
180
180
180
180
180
180
180
180
±
±
±
±
±
±
±
±
±
±
±
±
±
±
±
5°F Debra W. Inst 4505 8/26/2002
5°F Debra W. Inst 4505 8/26/2002
5°F Debra W. Inst 4505 8/26/2002
5°F John S.
Inst 4505 8/23/2002
5°F John S.
Inst 4505 8/23/2002
5°F John S.
Inst 4505 8/23/2002
5°F John S.
Inst 4505 8/23/2002
5°F Ken G. MTS 318.10 8/28/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
5°F Ken G. MTS 318.10 9/16/2002
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180
180
180
180
180
180
180
180
180
180
180
180
180
180
180
180
±
±
±
±
±
±
±
±
±
±
±
±
±
±
±
±
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
5°F
193
Test
Temp
(°F)
Test
Operator
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Test
Frame
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
Test
Date
8/23/2002
8/23/2002
8/23/2002
8/23/2002
9/9/2002
9/9/2002
9/9/2002
9/9/2002
8/28/2002
8/28/2002
8/28/2002
8/28/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
(180°F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
TC1616SE-A-12
P707AG-15
AB020234
ASTM D3039
(90)18
Test Conditions:
Loading Rate:
Control Mode:
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07 Rev. B
180°F
0.05 in/min
Stroke
Specimen
Thickness
(in.)
Specimen
Width
(in.)
Ultimate
Load
(lbs)
Tensile
Strength
(ksi)
Failure Location
&
Comments
Testing
Facility
Test
Temp
(°F)
Test
Operator
Test
Frame
Test
Date
3.99
3.36
3.40
3.99
3.96
3.24
3.70
3.68
4.08
3.57
3.82
4.09
3.65
3.65
3.50
3.69
3.71
0.261
7.05
4.06
3.49
3.43
3.32
3.55
3.57
3.42
3.31
3.50
3.18
3.37
4.01
3.71
3.39
3.50
3.81
3.54
0.245
6.92
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
8/26/2002
8/26/2002
8/26/2002
8/26/2002
9/5/2002
9/5/2002
9/5/2002
9/5/2002
8/28/2002
8/28/2002
8/28/2002
8/28/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
9/5/2002
9/5/2002
9/5/2002
9/5/2002
9/9/2002
9/9/2002
9/9/2002
9/9/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
A-19
A-19
A-19
A-19
A-21
A-21
A-21
A-21
A-19
A-19
A-19
A-19
A-21
A-21
A-21
A-21
"A" Panel
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
0.10662
0.10923
0.10987
0.10703
0.10745
0.10828
0.10842
0.10787
0.10793
0.10970
0.10845
0.10578
0.10782
0.10842
0.10827
0.10695
1.00043
1.00080
1.00043
0.99958
1.00050
1.00053
1.00050
1.00017
1.00057
1.00047
0.99990
1.00085
1.00057
1.00052
1.00033
1.00082
425.7
367.0
373.9
426.9
425.8
351.3
401.0
396.9
440.3
392.0
413.8
433.5
394.3
395.6
378.8
395.0
B-20
B-20
B-20
B-20
B-22
B-22
B-22
B-22
B-20
B-20
B-20
B-20
B-22
B-22
B-22
B-22
"B" Panel
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
0.10695
0.10917
0.10932
0.10810
0.10728
0.10798
0.10823
0.10787
0.10860
0.10935
0.10852
0.10605
0.10770
0.10855
0.10823
0.10658
1.00048
1.00043
1.00073
1.00062
1.00047
1.00047
1.00097
1.00053
1.00070
1.00073
1.00060
1.00090
1.00068
1.00043
1.00052
1.00093
433.9
381.5
375.0
359.4
380.5
386.2
371.0
356.7
380.9
348.5
366.0
425.6
399.3
368.5
378.7
406.9
194
(180°F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
TC1616SE-A-12
P707AG-15
AB020436
ASTM D3039
(90)18
Test Conditions:
Loading Rate:
Control Mode:
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07 Rev. B
180°F
0.05 in/min
Stroke
Specimen
Thickness
(in.)
Specimen
Width
(in.)
Ultimate
Load
(lbs)
Tensile
Strength
(ksi)
Failure Location
&
Comments
Testing
Facility
Test
Temp
(°F)
Test
Operator
Test
Frame
Test
Date
3.91
3.47
3.63
3.49
4.11
3.82
3.71
4.28
3.70
3.25
3.91
3.76
3.85
4.28
4.08
4.36
3.85
0.316
8.20
4.42
3.60
3.66
3.94
4.09
3.84
3.88
4.00
3.64
3.76
3.86
3.84
3.27
3.80
3.88
4.35
3.86
0.277
7.16
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
9/9/2002
9/9/2002
9/9/2002
9/9/2002
8/23/2002
8/23/2002
8/23/2002
8/23/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
8/28/2002
8/28/2002
8/28/2002
8/28/2002
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
8/23/2002
8/23/2002
8/23/2002
8/23/2002
8/26/2002
8/26/2002
8/26/2002
8/26/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
A-31
A-31
A-31
A-31
A-33
A-33
A-33
A-33
A-31
A-31
A-31
A-31
A-33
A-33
A-33
A-33
"A" Panel
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
0.11080
0.11133
0.11145
0.11097
0.11155
0.11130
0.11097
0.11112
0.11108
0.11153
0.11138
0.10992
0.11193
0.11102
0.11098
0.11022
1.00040
1.00058
1.00048
1.00013
1.00037
1.00038
1.00023
0.99953
1.00045
1.00010
1.00035
1.00040
1.00023
1.00028
1.00025
1.00028
433.4
386.2
404.8
387.5
458.8
425.6
412.1
475.1
411.0
362.2
435.2
414.0
431.0
475.5
452.8
480.9
B-32
B-32
B-32
B-32
B-34
B-34
B-34
B-34
B-36
B-36
B-36
B-36
B-36
B-36
B-36
B-36
"B" Panel
1
3
5
7
1
3
5
7
1
3
5
7
2
4
6
8
Average
Std, Dev.
COV, %
0.10963
0.11243
0.11203
0.11018
0.10988
0.11098
0.11128
0.11093
0.11010
0.11147
0.11072
0.11087
0.11113
0.11130
0.11053
0.10875
1.00047
1.00055
0.99987
0.99945
1.00053
1.00043
1.00028
1.00000
1.00038
0.99997
1.00048
1.00005
1.00057
1.00030
1.00043
1.00023
484.6
405.3
410.3
433.6
450.1
425.8
431.8
443.5
400.4
419.4
427.8
425.7
363.8
423.3
429.2
473.2
195
(180°F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
TC1616SE-A-12
P707AG-15
AB020552
ASTM D3039
(90)18
Test Conditions:
Loading Rate:
Control Mode:
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07 Rev. B
180°F
0.05 in/min
Stroke
Specimen
Thickness
(in.)
Specimen
Width
(in.)
Ultimate
Load
(lbs)
Tensile
Strength
(ksi)
Failure Location
&
Comments
Testing
Facility
Test
Temp
(°F)
Test
Operator
Test
Frame
Test
Date
3.59
3.20
3.69
3.08
3.68
3.35
3.08
3.43
3.85
3.86
3.53
3.66
3.55
3.31
3.99
3.87
3.55
0.283
7.99
3.85
3.68
3.40
3.93
3.98
3.65
3.97
3.98
3.48
3.63
3.40
3.94
4.05
4.24
3.92
3.73
3.80
0.244
6.42
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
9/9/2002
9/9/2002
9/9/2002
9/9/2002
9/5/2002
9/5/2002
9/5/2002
9/5/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
180 ± 5°F
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
MTS 318.10
9/5/2002
9/5/2002
9/5/2002
9/5/2002
8/26/2002
8/26/2002
8/26/2002
8/26/2002
9/16/2002
9/16/2002
9/16/2002
9/16/2002
8/28/2002
8/28/2002
8/28/2002
8/28/2002
A-43
A-43
A-43
A-43
A-45
A-45
A-45
A-45
A-43
A-43
A-43
A-45
A-45
A-45
A-45
A-47
"A" Panel
1
3
5
7
1
3
5
7
2
4
8
2
4
6
8
2
Average
Std, Dev.
COV, %
0.10752
0.10697
0.10785
0.10938
0.10763
0.10777
0.10913
0.10842
0.10757
0.10713
0.10723
0.10758
0.10825
0.10892
0.10695
0.10827
0.99990
0.99990
0.99953
0.99967
1.00048
1.00065
1.00095
1.00058
0.99975
0.99993
0.99987
1.00052
1.00058
1.00017
1.00100
1.00040
386.2
342.4
398.0
337.2
396.2
361.1
336.2
372.4
413.7
413.4
378.9
394.3
384.0
361.0
427.2
419.0
B-44
B-44
B-44
B-44
B-48
B-48
B-48
B-48
B-44
B-44
B-44
B-44
B-48
B-48
B-48
B-48
"B" Panel
1
3
5
7
1
3
5
7
2
4
6
8
2
4
6
8
Average
Std, Dev.
COV, %
0.10727
0.10795
0.10825
0.10775
0.10790
0.10833
0.10842
0.10825
0.10760
0.10823
0.10835
0.10670
0.10825
0.10855
0.10837
0.10738
1.00072
1.00055
1.00077
1.00052
0.99998
1.00033
1.00057
1.00027
1.00093
1.00055
1.00063
1.00092
1.00083
1.00018
1.00035
1.00078
413.3
397.8
368.1
423.8
429.6
395.9
430.8
430.6
375.1
393.5
368.6
420.6
439.0
460.4
424.9
400.6
196
0° Compression Properties, -65°F (Dry)
Test Method: SACMA SRM 1-94
Strain Gage: N/A
Preconditioning: as machined
Testing Facility: TCA
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-1
A1-910-041-1-2
A1-910-041-1-3
B1-910-041-1-3
B1-910-041-1-2
B1-910-041-1-4
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0000
0.00
(in.)
0.4991
0.5013
0.4986
0.5046
0.5000
0.5012
0.5008
0.0022
0.43
Ult.
Comp.
Load
(kips)
5.12
5.12
4.93
4.60
4.68
4.77
4.87
0.22
4.59
Strain Gage: One axial gage (CEA-06-125UN-350)
Test Date: 12/17/1999
55.0%
0.0060 in.
54.2%
Ult. Comp.
Strength
Actual
Norm.
(ksi)
(ksi)
213.69
213.69
212.69
212.69
206.09
206.09
189.80
189.80
194.78
194.78
198.22
198.22
202.55
202.55
9.81
9.81
4.84
4.84
Test Operator: Joel Patterson
Test Frame: H
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Specimen
Number
FV(normalizing):
CPT (average):
FV(batch average):
Specimen Specimen
Thickness
Width
A1-910-041-1-1
B1-910-041-1-1
(in.)
0.0481
0.0473
(in.)
0.4990
0.4990
Average
Std. Dev.
COV, %
0.0477
0.0006
1.19
0.4990
0.0000
0.00
197
Load @
0.1%
Strain
(lbs.)
624.8
641.5
55.1%
0.0060 in.
54.2%
Load @
0.3%
Strain
(lbs.)
1413
1436
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
16.4
16.4
16.8
16.6
16.6
0.29
1.72
16.5
0.09
0.54
0° Compression Properties, 75°F (Dry)
Strain Gage: N/A
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-11
A2-910-041-1-9
A2-910-041-1-10
B1-910-041-1-11
B2-910-041-1-9
B2-910-041-1-10
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0480
0.0477
0.0477
0.0477
0.0478
0.0002
0.37
(in.)
0.5031
0.4995
0.5010
0.5024
0.4995
0.5005
0.5010
0.0015
0.30
Ult.
Comp.
Load
(kips)
4.69
4.92
5.06
5.14
5.63
5.31
5.12
0.33
6.36
Test Date: 11/30/1999
55.1%
54.2%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-7
A2-910-042-1-7
A2-910-042-1-8
B1-910-042-1-7
B2-910-042-1-7
B2-910-042-1-8
Average
Std. Dev.
COV, %
(in.)
0.0485
0.0485
0.0485
0.0480
0.0480
0.0480
0.0482
0.0003
0.59
(in.)
0.4989
0.4988
0.5031
0.4987
0.4991
0.5005
0.4998
0.0017
0.35
Ult.
Comp.
Load
(kips)
5.30
4.57
5.45
5.01
5.42
4.76
5.08
0.37
7.19
54.1%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-7
A2-910-043-1-7
A2-910-043-1-8
B1-910-043-1-7
B2-910-043-1-7
B2-910-043-1-8
Average
Std. Dev.
COV, %
(in.)
0.0485
0.0485
0.0485
0.0479
0.0479
0.0479
0.0482
0.0003
0.71
(in.)
0.4988
0.4987
0.5030
0.4991
0.4989
0.5006
0.4998
0.0017
0.33
Ult.
Comp.
Load
(kips)
4.93
4.90
4.68
4.83
5.23
5.07
4.94
0.19
3.86
(in.)
0.0481
0.0473
(in.)
0.5003
0.4999
Average
Std. Dev.
COV, %
0.0477
0.0005
1.13
0.5001
0.0002
0.05
Specimen
Number
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
198
Comp. Mod.
(0.1-0.3% strain)
Actual Norm.
(msi)
(msi)
16.3
16.3
16.5
16.2
16.3
0.05
0.29
Strain Gage: One axial gage (FAE-12S-AS-S6EL-2)
FV(normalizing):
CPT (average):
FV(batch average):
A1-911-042-1-1
B1-911-042-1-1
(in.)
0.0480
0.0480
(in.)
0.4972
0.4979
Average
Std. Dev.
COV, %
0.0480
0.0001
0.12
0.4976
0.0005
0.10
Specimen
Number
54.2%
Load @
0.3%
Strain
(lbs.)
1256
1240
Specimen Specimen
Thickness
Width
Test Date: 11/30/1999
55.1%
Load @
0.1%
Strain
(lbs.)
473.3
461.0
55.1%
0.0060 in.
16.4
0.14
0.84
Load @
0.1%
Strain
(lbs.)
448.4
437.2
55.1%
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
1224
1215
Comp. Mod.
(0.1-0.3% strain)
Actual Norm.
(msi)
(msi)
16.3
16.2
16.3
16.3
16.3
0.00
0.01
16.3
0.02
0.11
0.0060 in.
54.9%
Ult. Comp.
Strength
Actual Norm.
(ksi)
(ksi)
204
206
203
205
192
194
202
202
219
218
211
211
205
206
9.2
8.3
4.49
4.04
A1-910-041-1-2
B1-910-041-1-2
Strain Gage: N/A
FV(batch average):
Specimen Specimen
Thickness
Width
Test Date: 11/30/1999
55.1%
CPT (average):
0.0060 in.
Ult. Comp.
Strength
Actual Norm.
(ksi)
(ksi)
219
221
189
191
223
226
210
209
226
226
198
198
211
212
14.9
15.0
7.05
7.07
Specimen
Number
FV(normalizing):
Strain Gage: N/A
0.0060 in.
Ult. Comp.
Strength
Actual Norm.
(ksi)
(ksi)
194
194
205
205
210
210
215
213
237
235
223
221
214
213
14.6
13.9
6.83
6.54
FV(normalizing):
CPT (average):
FV(batch average):
Specimen Specimen
Thickness
Width
A1-910-043-1-1
B1-910-043-1-1
(in.)
0.0482
0.0473
(in.)
0.4984
0.4985
Average
Std. Dev.
COV, %
0.0478
0.0006
1.30
0.4985
0.0001
0.01
Load @
0.1%
Strain
(lbs.)
465.3
466.0
55.1%
0.0060 in.
54.9%
Load @
0.3%
Strain
(lbs.)
1250
1244
Comp. Mod.
(0.1-0.3% strain)
Actual Norm.
(msi)
(msi)
16.3
16.4
16.5
16.3
16.4
0.11
0.68
16.3
0.10
0.62
Strain Gage: N/A
FV(normalizing):
55.1%
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-13
A1-910-041-1-14
A2-910-041-1-11
B1-910-041-1-13
B1-910-041-1-14
B2-910-041-1-11
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0480
0.0477
0.0477
0.0477
0.0478
0.0002
0.37
(in.)
0.4987
0.5011
0.5030
0.4992
0.5009
0.5028
0.5010
0.0018
0.35
Ult.
Comp.
Load
(kips)
4.77
4.82
5.13
5.28
5.36
5.01
5.06
0.24
4.72
0.0060 in.
54.2%
Ult. Comp.
Strength
Actual
Norm.
(ksi)
(ksi)
199
199
200
200
213
213
222
220
224
223
209
208
211
210
10.5
9.9
4.97
4.70
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-8
A1-910-042-1-9
A2-910-042-1-9
B1-910-042-1-8
B1-910-042-1-9
B2-910-042-1-9
Average
Std. Dev.
COV, %
(in.)
0.0485
0.0485
0.0485
0.0480
0.0480
0.0480
0.0482
0.0003
0.59
(in.)
0.5013
0.4997
0.5011
0.5010
0.4993
0.4998
0.5003
0.0008
0.17
Ult.
Comp.
Load
(kips)
4.85
5.25
4.85
4.19
5.07
4.85
4.85
0.36
7.39
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-8
A1-910-043-1-9
A2-910-043-1-9
B1-910-043-1-8
B1-910-043-1-9
B2-910-043-1-9
Average
Std. Dev.
COV, %
(in.)
0.0485
0.0485
0.0485
0.0479
0.0479
0.0479
0.0482
0.0003
0.71
(in.)
0.5011
0.4995
0.5009
0.5006
0.4999
0.4994
0.5002
0.0007
0.15
Ult.
Comp.
Load
(kips)
4.95
4.81
4.31
4.89
4.99
5.08
4.84
0.27
5.68
Specimen
Width
A1-910-041-1-3
B1-910-041-1-3
(in.)
0.0480
0.0477
(in.)
0.4990
0.4990
Average
Std. Dev.
COV, %
0.0478
0.0002
0.43
0.4990
0.0000
0.00
54.9%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
199
Load @
0.3%
Strain
(lbs.)
1221
1254
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
16.4
16.4
17.0
16.9
16.7
0.37
2.21
FV(normalizing):
55.1%
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-2
B1-910-042-1-2
(in.)
0.0485
0.0481
(in.)
0.5023
0.5021
Average
Std. Dev.
COV, %
0.0483
0.0003
0.59
0.5022
0.0001
0.03
Load @
0.1%
Strain
(lbs.)
434.9
443.0
0.0060 in.
54.2%
16.7
0.44
2.64
Load @
0.1%
Strain
(lbs.)
459.6
454.0
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
1280
1252
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
16.8
17.0
16.5
16.6
16.7
0.22
1.35
16.8
0.32
1.93
55.1%
0.0060 in.
Ult. Comp.
Strength
Actual
Norm.
(ksi)
(ksi)
204
206
198
200
177
179
204
203
208
208
213
212
201
201
12.4
11.6
6.16
5.74
Specimen
Thickness
Control Mode: 0.05 in/min
Strain Gage: N/A
Specimen
Number
54.1%
CPT (average):
FV(batch average):
0.0060 in.
Ult. Comp.
Strength
Actual
Norm.
(ksi)
(ksi)
200
202
217
219
200
202
174
174
211
211
202
202
201
202
14.6
15.1
7.29
7.49
FV(normalizing):
55.1%
Strain Gage: N/A
FV(normalizing):
55.1%
FV(normalizing):
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-2
B1-910-043-1-2
(in.)
0.0483
0.0475
(in.)
0.5003
0.5000
Average
Std. Dev.
COV, %
0.0479
0.0006
1.25
0.5002
0.0002
0.04
Load @
0.1%
Strain
(lbs.)
459.2
473.9
55.1%
0.0060 in.
54.9%
Load @
0.3%
Strain
(lbs.)
1260
1412
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
16.6
16.7
19.8
19.5
18.2
2.26
12.45
18.1
2.03
11.21
0° Compression - Strength
(180F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
A1
A1
A1
A6
A6
A6
"A"
B6
B6
B6
"B"
Panel
Fiber
Volume
(%)
910-041-1-3
54.2
910-041-1-4
54.2
910-041-1-5
54.2
910-041-1-8
51.3
910-041-1-9
51.3
910-041-1-11
51.3
Average
Std, Dev.
COV, %
910-041-1-7
51.3
910-041-1-8
51.3
910-041-1-11
51.3
Average
Std, Dev.
COV, %
TC1616SE-A-12
TCQAL-T-1018 - Test Plan
P707AG-15
AB991033
SACMA SRM 1-94
(0) 8
Specimen
Thickness
Specimen Ultimate
Width
Load
(in.)
0.04530
0.04700
0.04600
0.04775
0.04740
0.04755
(in.)
0.49865
0.49938
0.49928
0.50035
0.49928
0.50308
(lbs)
3753
3890
3766
3237
3734
3785
0.04680
0.04695
0.04735
0.49823
0.50203
0.50027
4594
4402
4402
Test Conditions:
Loading Rate:
Control Mode:
CPT (average):
Fiber Volume (normalizing):
Compression
Failure
Strength
Location
Actual Normalized
& Comments
(ksi)
(ksi)
166
157
failure in gage
166
162
failure in gage
164
157
failure in gage
135
135
failure in gage
158
156
failure in gage
158
157
failure in gage
158
154
11.6
9.7
7.32
6.28
197
192
failure in gage
187
183
failure in gage
186
183
failure in gage
190
186
6.21
5.26
3.27
2.83
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07
180 ± 5 °F
145°F ± 5°F, 85 ± 5%RH
moisture equilibrium per SACMA SRM 11-94
0.05 in/min
Stroke
0.0060
in.
55.1
%
Testing
Test
Test
Test
Facility
Temp
Operator Frame
Test
Date
NIAR
NIAR
NIAR
TCA
TCA
TCA
(°F)
180°F
180°F
180°F
180°F
180°F
180°F
Yap
Yap
Yap
John S.
John S.
John S.
6/27/2000
6/27/2000
6/27/2000
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
TCA
TCA
TCA
180°F
180°F
180°F
John S.
John S.
John S.
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
(180F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
A1
A6
A6
A6
"A"
B1
B6
B6
B6
"B"
Panel
Fiber
Volume
(%)
910-042-1-1
54.1
910-042-1-7
51.3
910-042-1-10
51.3
910-042-1-11
51.3
Average
Std, Dev.
COV, %
910-042-1-3
54.1
910-042-1-8
51.3
910-042-1-9
51.3
910-042-1-11
51.3
Average
Std, Dev.
COV, %
TC1616SE-A-12
P707AG-15
AB991034
SACMA SRM 1-94
(0) 8
Specimen
Thickness
Specimen Ultimate
Width
Load
(in.)
0.04683
0.04645
0.04640
0.04660
(in.)
0.50195
0.49872
0.49895
0.50023
(lbs)
4305
4352
4506
4486
0.04683
0.04670
0.04710
0.04790
0.49952
0.50248
0.50003
0.50020
4294
4472
4093
3756
Test Conditions:
Loading Rate:
Control Mode:
CPT (average):
Compression
Failure
Strength
Location
Actual Normalized
& Comments
(ksi)
(ksi)
183
179
failure in gage
188
182
failure in gage
195
188
failure in gage
192
187
failure in gage
190
184
5.10
4.41
2.69
2.40
184
179
failure in gage
191
185
failure in gage
174
171
failure in gage
157
156
failure in gage
176
173
14.7
12.5
8.32
7.25
200
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07
180 ± 5 °F
145°F ± 5°F, 85 ± 5%RH
0.05 in/min
Stroke
0.0060
in.
55.1
%
Testing
Test
Test
Test
Facility
Temp
Operator Frame
Test
Date
NIAR
TCA
TCA
TCA
(°F)
180°F
180°F
180°F
180°F
Lamia
John S.
John S.
John S.
6/27/2000
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
NIAR
TCA
TCA
TCA
180°F
180°F
180°F
180°F
Lamia
John S.
John S.
John S.
6/27/2000
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
(180F/Wet)
FAA Project No:
Test Plan Document:
Material Type:
Batch Number:
Test Method:
Panel Fabrication:
Ply Orientation:
Specimen
Panel
Coupon
A6
A6
A6
"A"
B1
B1
B6
B6
B6
"B"
Panel
Fiber
Volume
(%)
910-043-1-11
51.3
910-043-1-12
51.3
910-043-1-7
51.3
Average
Std, Dev.
COV, %
910-043-1-1
54.9
910-043-1-2
54.9
910-043-1-9
51.3
910-043-1-8
51.3
910-043-1-7
51.3
Average
Std, Dev.
COV, %
TC1616SE-A-12
P707AG-15
AB991035
SACMA SRM 1-94
(0) 8
Specimen
Thickness
Specimen Ultimate
Width
Load
(in.)
0.04765
0.04755
0.04805
(in.)
0.50250
0.49890
0.49813
(lbs)
4413
4347
4433
0.04567
0.04817
0.04795
0.04750
0.04720
0.49947
0.49952
0.49980
0.50318
0.49857
4280
4314
4060
4360
4240
Test Conditions:
Loading Rate:
Control Mode:
CPT (average):
Compression
Failure
Strength
Location
Actual Normalized
& Comments
(ksi)
(ksi)
184
183
failure in gage
183
182
failure in gage
185
185
failure in gage
184
183
0.98
1.96
0.53
1.07
188
179
failure in gage
179
180
failure in gage
169
169
failure in gage
182
181
failure in gage
180
177
failure in gage
180
177
6.64
4.57
3.69
2.58
201
TCSPF-T-UD06 Rev. 3
TCSPF-T-UD07
180 ± 5 °F
145°F ± 5°F, 85 ± 5%RH
0.05 in/min
Stroke
0.0060
in.
55.1
%
Testing
Test
Test
Test
Facility
Temp
Operator Frame
Test
Date
TCA
TCA
TCA
(°F)
180°F
180°F
180°F
John S.
John S.
John S.
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
NIAR
NIAR
TCA
TCA
TCA
180°F
180°F
180°F
180°F
180°F
Lamia
Lamia
John S.
John S.
John S.
6/27/2000
6/27/2000
Inst 4510 6/29/2001
Inst 4510 6/29/2001
Inst 4510 6/29/2001
90° Compression Properties, -65°F (Dry)
Strain Gage: N/A
Test Date: 12/23/1999
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-7
A2-910-041-1-7
A2-910-041-1-8
B1-910-041-1-7
B2-910-041-1-7
B2-910-041-1-8
Average
Std. Dev.
COV, %
(in.)
0.0475
0.0475
0.0475
0.0480
0.0480
0.0480
0.0478
0.0003
0.63
(in.)
0.4988
0.4987
0.5007
0.4989
0.4990
0.5005
0.4994
0.0009
0.18
Ult.
Comp.
Load
(kips)
1.01
1.03
1.01
1.05
0.909
0.844
0.977
0.082
8.37
Test Operator: Emmanuel Domingo
Test Frame: I
Strain Gage: One axial gage (CEA-06-125UN-350)
0.0060 in.
Test Date: 12/17/1999
54.2%
Ult. Comp.
Strength
Actual
(ksi)
42.7
43.5
42.5
44.0
37.9
35.1
41.0
3.60
8.78
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Specimen
Number
CPT (average):
FV(batch average):
Specimen Specimen
Thickness
Width
A1-910-041-1-1
B1-910-041-1-1
(in.)
0.0473
0.0477
(in.)
0.4980
0.4980
Average
Std. Dev.
COV, %
0.0475
0.0003
0.60
0.4980
0.0000
0.00
202
Load @
0.1%
Strain
(lbs.)
213.9
218.9
0.0060 in.
54.2%
Load @
0.3%
Strain
(lbs.)
296
330
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.74
2.34
2.04
0.42
20.62
Strain Gage: N/A
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-9
A1-910-041-1-10
A2-910-041-1-11
B1-910-041-1-9
B1-910-041-1-10
B2-910-041-1-11
Average
Std. Dev.
COV, %
(in.)
0.0475
0.0475
0.0475
0.0480
0.0480
0.0480
0.0478
0.0003
0.63
(in.)
0.4995
0.5004
0.5031
0.4996
0.5011
0.5031
0.5011
0.0016
0.33
0.0060 in.
54.2%
Ult. Comp.
Strength
Actual
(ksi)
27.7
28.2
28.7
29.4
29.3
28.6
28.7
0.66
2.29
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
FV(batch average):
Specimen
Thickness
Specimen
Width
A1-910-042-1-7
A1-910-042-1-8
A2-910-042-1-7
B1-910-042-1-7
B1-910-042-1-8
B2-910-042-1-7
Average
Std. Dev.
COV, %
(in.)
0.0494
0.0494
0.0494
0.0487
0.0487
0.0487
0.0490
0.0003
0.70
(in.)
0.4992
0.5007
0.4991
0.4989
0.5006
0.4990
0.4996
0.0008
0.17
Ult.
Comp.
Load
(kips)
0.759
0.769
0.701
0.675
0.650
0.748
0.717
0.049
6.83
0.0060 in.
54.1%
Ult. Comp.
Strength
Actual
(ksi)
30.8
31.1
28.5
27.8
26.6
30.7
29.3
1.89
6.46
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-7
A1-910-043-1-8
A2-910-043-1-7
B1-910-043-1-7
B1-910-043-1-8
B2-910-043-1-7
Average
Std. Dev.
COV, %
(in.)
0.0488
0.0488
0.0488
0.0488
0.0488
0.0488
0.0488
0.0000
0.03
(in.)
0.4987
0.5004
0.4990
0.4988
0.5006
0.4987
0.4994
0.0009
0.18
Ult.
Comp.
Load
(kips)
0.707
0.663
0.745
0.682
0.658
0.714
0.695
0.033
4.79
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-2
B1-910-041-1-2
(in.)
0.0474
0.0480
(in.)
0.5004
0.5001
Average
Std. Dev.
COV, %
0.0477
0.0004
0.85
0.5003
0.0002
0.04
54.9%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
54.2%
Load @
0.3%
Strain
(lbs.)
196
153
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.44
1.59
Test Date: 11/30/1999
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-1
B1-910-042-1-1
(in.)
0.0486
0.0483
(in.)
0.4982
0.4983
Average
Std. Dev.
COV, %
0.0484
0.0002
0.47
0.4983
0.0001
0.02
Load @
0.1%
Strain
(lbs.)
72.4
72.9
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
142
144
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.43
1.48
1.46
0.03
2.35
Test Date: 11/30/1999
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-1
B1-910-043-1-1
(in.)
0.0479
0.0483
(in.)
0.4983
0.4983
Average
Std. Dev.
COV, %
0.0481
0.0003
0.69
0.4983
0.0000
0.00
203
Load @
0.1%
Strain
(lbs.)
127.2
76.2
0.0060 in.
1.52
0.11
7.07
0.0060 in.
Ult. Comp.
Strength
Actual
(ksi)
29.0
27.2
30.6
28.0
27.0
29.3
28.5
1.40
4.90
Test Date: 11/30/1999
Strain Gage: N/A
FV(batch average):
Strain Gage: N/A
Specimen
Number
Ult.
Comp.
Load
(kips)
0.657
0.670
0.686
0.706
0.706
0.691
0.686
0.020
2.85
Load @
0.1%
Strain
(lbs.)
83.1
72.0
0.0060 in.
54.9%
Load @
0.3%
Strain
(lbs.)
151
141
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
1.43
1.44
1.44
0.01
0.41
Strain Gage: N/A
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-11
A2-910-041-1-13
A2-910-041-1-14
B1-910-041-1-11
B2-910-041-1-13
B2-910-041-1-14
Average
Std. Dev.
COV, %
(in.)
0.0475
0.0475
0.0475
0.0480
0.0480
0.0480
0.0478
0.0003
0.63
(in.)
0.5031
0.4991
0.5005
0.5030
0.4988
0.5005
0.5008
0.0019
0.37
0.0060 in.
54.2%
Ult. Comp.
Strength
Actual
(ksi)
20.5
21.9
20.5
21.7
23.0
23.5
21.8
1.25
5.72
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
FV(batch average):
Specimen
Thickness
Specimen
Width
A1-910-042-1-9
A2-910-042-1-8
A2-910-042-1-9
B1-910-042-1-9
B2-910-042-1-8
B2-910-042-1-14
Average
Std. Dev.
COV, %
(in.)
0.0494
0.0494
0.0494
0.0487
0.0487
0.0487
0.0490
0.0003
0.70
(in.)
0.4997
0.5009
0.4998
0.4996
0.5006
0.4998
0.5001
0.0005
0.10
Ult.
Comp.
Load
(kips)
0.549
0.524
0.470
0.525
0.536
0.503
0.518
0.028
5.40
Specimen
Number
54.1%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
(in.)
0.0483
0.0476
(in.)
0.4991
0.4998
Average
Std. Dev.
COV, %
0.0480
0.0005
1.05
0.4994
0.0004
0.09
Specimen
Number
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-9
A2-910-043-1-8
A2-910-043-1-9
B1-910-043-1-9
B2-910-043-1-8
B2-910-043-1-14
Average
Std. Dev.
COV, %
(in.)
0.0488
0.0488
0.0488
0.0488
0.0488
0.0488
0.0488
0.0000
0.03
(in.)
0.4998
0.5004
0.4993
0.4996
0.5027
0.5005
0.5004
0.0012
0.25
Ult.
Comp.
Load
(kips)
0.497
0.545
0.521
0.494
0.528
0.541
0.521
0.021
4.11
54.9%
Ult. Comp.
Strength
Actual
(ksi)
20.4
22.3
21.4
20.3
21.5
22.1
21.3
0.86
4.02
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
A1-910-042-1-2
B1-910-042-1-6
(in.)
0.0489
0.0487
(in.)
0.5004
0.4982
Average
Std. Dev.
COV, %
0.0488
0.0001
0.26
0.4993
0.0015
0.30
Specimen
Number
Load @
0.1%
Strain
(lbs.)
62.2
58.2
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
124
118
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.25
1.22
1.24
0.02
1.75
CPT (average):
FV(batch average):
Specimen Specimen
Thickness
Width
A1-910-043-1-2
B1-910-043-1-2
(in.)
0.0486
0.0486
(in.)
0.5007
0.5006
Average
Std. Dev.
COV, %
0.0486
0.0000
0.00
0.5007
0.0001
0.01
204
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.25
1.20
1.23
0.04
2.88
FV(batch average):
Specimen Specimen
Thickness
Width
54.2%
Load @
0.3%
Strain
(lbs.)
118
108
0.0060 in.
Load @
0.1%
Strain
(lbs.)
57.2
50.3
0.0060 in.
Strain Gage: N/A
CPT (average):
Specimen Specimen
Thickness
Width
A1-910-041-1-3
B1-910-041-1-3
CPT (average):
FV(batch average):
0.0060 in.
Ult. Comp.
Strength
Actual
(ksi)
22.3
21.2
19.0
21.6
22.0
20.7
21.1
1.16
5.50
Strain Gage: N/A
Specimen
Number
Ult.
Comp.
Load
(kips)
0.489
0.518
0.487
0.525
0.551
0.564
0.522
0.032
6.06
Load @
0.1%
Strain
(lbs.)
61.3
56.3
0.0060 in.
54.9%
Load @
0.3%
Strain
(lbs.)
120
117
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
1.21
1.24
1.23
0.03
2.10
90° Compression Properties, 180°F (Wet)
Strain Gage: N/A
Preconditioning: Section 3.2 of AGATE
Test Date: 6/5/2000
CPT (average):
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-041-1-2
A1-910-041-1-3
B1-910-041-1-2
B1-910-041-1-1
B1-910-041-1-3
A2-910-041-1-1
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0000
0.00
(in.)
0.5004
0.5006
0.5024
0.5023
0.5021
0.5014
0.5015
0.0009
0.18
Ult.
Comp.
Load
(kips)
0.386
0.415
0.432
0.422
0.446
0.403
0.417
0.021
5.10
0.0060 in.
54.2%
Ult. Comp.
Strength
Actual
(ksi)
16.1
17.3
17.9
17.5
18.5
16.7
17.3
0.86
4.97
Test Date: 6/6/2000
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-042-1-1
A1-910-042-1-3
A2-910-042-1-2
B1-910-042-1-1
B1-910-042-1-3
B2-910-042-1-1
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0480
0.0000
0.00
(in.)
0.5033
0.5036
0.5009
0.5006
0.5008
0.5002
0.5016
0.0015
0.30
Ult.
Comp.
Load
(kips)
0.412
0.368
0.401
0.389
0.398
0.434
0.400
0.022
5.50
Test Date: 3/7/2000
Specimen
Number
54.1%
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
(in.)
0.0475
0.0483
(in.)
0.5005
0.5003
Average
Std. Dev.
COV, %
0.0479
0.0006
1.21
0.5004
0.0002
0.03
Test Date: 3/7/2000
Specimen
Number
FV(batch average):
Specimen
Number
Specimen
Thickness
Specimen
Width
A1-910-043-1-1
A1-910-043-1-2
A2-910-043-1-1
B1-910-043-1-1
B1-910-043-1-2
B2-910-043-1-1
Average
Std. Dev.
COV, %
(in.)
0.0480
0.0480
0.0475
0.0480
0.0480
0.0480
0.0479
0.0002
0.43
(in.)
0.4995
0.4996
0.5004
0.4994
0.4993
0.5012
0.4999
0.0007
0.15
Ult.
Comp.
Load
(kips)
0.393
0.376
0.423
0.399
0.399
0.410
0.400
0.016
3.97
54.9%
Ult. Comp.
Strength
Actual
(ksi)
16.4
15.7
17.8
16.6
16.6
17.0
16.7
0.70
4.21
Failure
Location
&
Comments
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
Failure in gage
CPT (average):
A1-910-042-1-3
B1-910-042-1-3
(in.)
0.0494
0.0487
(in.)
0.4992
0.4992
Average
Std. Dev.
COV, %
0.0490
0.0004
0.91
0.4992
0.0000
0.01
Specimen
Number
Load @
0.1%
Strain
(lbs.)
52.9
47.7
0.0060 in.
54.1%
Load @
0.3%
Strain
(lbs.)
109
100
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.14
1.08
1.11
0.04
3.56
CPT (average):
FV(batch average):
Specimen Specimen
Thickness
Width
A1-910-043-1-3
B1-910-043-1-3
(in.)
0.0491
0.0487
(in.)
0.4990
0.4992
Average
Std. Dev.
COV, %
0.0489
0.0002
0.46
0.4991
0.0001
0.03
205
Comp. Mod.
(0.1-0.3% strain)
Actual
(msi)
1.19
1.12
1.15
0.05
4.69
FV(batch average):
Specimen Specimen
Thickness
Width
Test Date: 3/3/2000
54.2%
Load @
0.3%
Strain
(lbs.)
110
116
0.0060 in.
Load @
0.1%
Strain
(lbs.)
53.2
62.0
0.0060 in.
Strain Gage: N/A
CPT (average):
Specimen Specimen
Thickness
Width
A1-910-041-1-4
B1-910-041-1-4
CPT (average):
FV(batch average):
0.0060 in.
Ult. Comp.
Strength
Actual
(ksi)
17.0
15.2
16.7
16.2
16.6
18.1
16.6
0.94
5.64
Strain Gage: N/A
CPT (average):
Test Date: 6/6/2000
Load @
0.1%
Strain
(lbs.)
69.1
69.8
0.0060 in.
54.9%
Load @
0.3%
Strain
(lbs.)
126
129
Comp. Mod.
(0.1-0.3% strain)
Actual
Norm.
(msi)
(msi)
1.17
1.21
1.19
0.03
2.48
Iosipescu In-plane Shear Properties, -65°F (Dry)
Test Operator: Joel Patterson, Bryan Mines
Test Frame: H
Strain Gage: One biaxial gage (EA-06-062TV-350)
Ply Orientation: (0/90)6S
CPT (average):
Test Date: 12/17/99, 2/23/00
0.0060 in.
54.2%
Specimen
Specimen
Notch
Ultimate
In-plane Shear
IPS Modulus (1)
Failure Location
Number
Thickness
Width
Load
(0.25-0.65%) (2)
&
Comments
A1-910-041-1-1
A2-910-041-1-2
B1-910-041-1-1
B2-910-041-1-2
A1-910-041-1-3
B1-910-041-1-3
Average
Std. Dev.
COV, %
(in.)
0.1421
0.1431
0.1415
0.1418
0.1438
0.1419
0.1424
0.0009
0.62
(in.)
0.4520
0.4520
0.4530
0.4540
0.4530
0.4530
0.4528
0.0008
0.17
(lbs.)
1498
1473
1468
1501
1510
1510
1493
18
1.23
Strength
Actual
(ksi)
23.3
22.8
22.9
23.3
23.2
23.5
23.2
0.27
1.18
(1)
Modulus is determined to be the slope of the Stress-Shear Strain curve.
(2)
0.25 ~ 0.65% strain range per ASTM D5379-98, Section 12.3.1
(msi)
0.775
0.743
0.760
0.751
0.757
0.014
1.81
206
Shear failure in gage
Iosipescu In-plane Shear Properties, 75°F (Dry)
Strain Gage: One biaxial gage (EA-06-125-TW-120)
Ply Orientation: (0/90) 6S
CPT (average):
Test Date: 11/29/99, 1/27/00
0.0060 in.
54.2%
Specimen
Specimen
Notch
Ultimate
In-plane Shear
IPS Modulus (1)
Failure Location
Number
Thickness
Width
Load
(0.25-0.65%) (2)
&
Comments
A1-910-041-1-32
A1-910-041-1-33
B1-910-041-1-32
B1-910-041-1-33
A1-910-041-1-5
B1-910-041-1-5
Average
Std. Dev.
COV, %
(in.)
0.1430
0.1427
0.1434
0.1431
0.1443
0.1424
0.1431
0.0007
0.47
(in.)
0.4536
0.4449
0.4531
0.4530
0.4533
0.4527
0.4517
0.0034
0.75
(lbs.)
1400
1412
1423
1457
1421
1453
1428
23
1.59
Strength
Actual
(ksi)
21.6
22.2
21.9
22.5
21.7
22.5
22.1
0.40
1.83
(msi)
0.625
0.638
0.613
0.615
0.623
0.011
1.84
CPT (average):
Test Date: 11/29/99, 1/27/00
0.0060 in.
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
A1-910-042-1-11
A1-910-042-1-12
B1-910-042-1-11
B1-910-042-1-12
A1-910-042-1-1
B1-910-042-1-1
Average
Std. Dev.
COV, %
(in.)
0.1438
0.1415
0.1439
0.1405
0.1411
0.1404
0.1419
0.0016
1.11
(in.)
0.4527
0.4549
0.4522
0.4548
0.4535
0.4544
0.4537
0.0012
0.25
(lbs.)
1467
1471
1432
1479
1496
1439
1464
24
1.66
Strength
Actual
(ksi)
22.5
22.9
22.0
23.1
23.4
22.6
22.7
0.49
2.14
54.1%
IPS Modulus
(1)
(0.25-0.65%) (2)
(msi)
0.646
0.639
0.605
0.593
0.621
0.026
4.15
Failure Location
&
Comments
CPT (average):
Test Date: 11/29/99, 1/27/00
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
A1-910-043-1-11
A1-910-043-1-12
B1-910-043-1-11
B1-910-043-1-12
A1-910-043-1-1
B1-910-043-1-1
Average
Std. Dev.
COV, %
(in.)
0.1437
0.1443
0.1437
0.1424
0.1433
0.1401
0.1429
0.0015
1.07
(in.)
0.4533
0.4527
0.4532
0.4528
0.4536
0.4555
0.4535
0.0010
0.22
(lbs.)
1463
1373
1445
1497
1506
1464
1458
47
3.26
Strength
Actual
(ksi)
22.5
21.0
22.2
23.2
23.2
23.0
22.5
0.83
3.69
(1)
(2)
0.0060 in.
54.9%
IPS Modulus (1)
(0.25-0.65%)
(2)
(msi)
0.593
0.526
0.602
0.665
0.597
0.057
9.54
IPS Modulus was calculated from only +45° strain channel due to inaccurate data collected on -45° channel.
The +45° channel was multiplied by 2 to determine the shear strain. Modulus is then determined to be the slope of the Stress-Shear Strain curve.
207
Failure Location
&
Comments
Iosipescu In-plane Shear Properties, 180°F (Dry)
CPT (average):
Test Date: 11/29/99, 1/28/00
0.0060 in.
54.2%
Specimen
Specimen
Notch
Ultimate
In-plane Shear
IPS Modulus (1)
Failure Location
Number
Thickness
Width
Load
(0.25-0.65%) (2)
&
Comments
A1-910-041-1-29
A1-910-041-1-30
B1-910-041-1-29
B1-910-041-1-30
A1-910-041-1-7
B1-910-041-1-7
Average
Std. Dev.
COV, %
(in.)
0.1435
0.1436
0.1434
0.1435
0.1444
0.1429
0.1435
0.0005
0.35
(in.)
0.4536
0.4541
0.4541
0.4550
0.4535
0.4528
0.4538
0.0007
0.16
(lbs.)
1164
1173
1182
1208
1185
1236
1191
26
2.22
Strength
Actual
(ksi)
17.9
18.0
18.2
18.5
18.1
19.1
18.3
0.45
2.47
(msi)
0.512
0.507
0.493
0.498
0.503
0.009
1.71
CPT (average):
Test Date: 11/29/99, 1/28/00
0.0060 in.
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
A1-910-042-1-13
A1-910-042-1-15
B1-910-042-1-13
B1-910-042-1-14
A1-910-042-1-3
B1-910-042-1-3
Average
Std. Dev.
COV, %
(in.)
0.1422
0.1431
0.1411
0.1423
0.1424
0.1425
0.1423
0.0006
0.45
(in.)
0.4549
0.4549
0.4543
0.4543
0.4537
0.4548
0.4545
0.0005
0.10
(lbs.)
1232
1171
1226
1254
1234
1245
1227
29
2.38
Strength
Actual
(ksi)
19.1
18.0
19.1
19.4
19.1
19.2
19.0
0.50
2.64
54.1%
IPS Modulus
(1)
(0.25-0.65%) (2)
(msi)
0.525
0.497
0.520
0.522
0.516
0.013
2.49
Failure Location
&
Comments
CPT (average):
Test Date: 11/29/1999, 1/28/00
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
A1-910-043-1-13
A1-910-043-1-14
B1-910-043-1-13
B1-910-043-1-14
A1-910-043-1-3
B1-910-043-1-3
Average
Std. Dev.
COV, %
(in.)
0.1442
0.1447
0.1401
0.1411
0.1447
0.1422
0.1428
0.0020
1.39
(in.)
0.4540
0.4557
0.4544
0.4546
0.4536
0.4539
0.4544
0.0007
0.16
(lbs.)
1205
1207
1130
1230
1228
1228
1205
38
3.17
Strength
Actual
(ksi)
18.4
18.3
17.8
19.2
18.7
19.0
18.6
0.52
2.81
(1)
(2)
0.0060 in.
54.9%
IPS Modulus
(1)
(0.25-0.65%) (2)
(msi)
0.486
0.491
0.512
0.543
0.508
0.026
5.10
IPS Modulus was calculated from only +45° strain channel due to inaccurate data collected on -45° channel.
The +45° channel was multiplied by 2 to determine the shear strain. Modulus is then determined to be the slope of the Stress-Shear Strain curve.
208
Failure Location
&
Comments
Iosipescu In-plane Shear Properties, 180°F (Wet)
CPT (average):
Test Date: 3/9/2000
0.0060 in.
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
B1-910-041-1-10
A1-910-041-1-13
A1-910-041-1-12
B1-910-041-1-12
A1-910-041-1-11
B1-910-041-1-11
Average
Std. Dev.
COV, %
(in.)
0.1428
0.1426
0.1419
0.1423
0.1440
0.1420
0.1426
0.0008
0.55
(in.)
0.4536
0.4533
0.4526
0.4522
0.4525
0.4522
0.4527
0.0006
0.13
(lbs.)
951
927
921
901
881
917
916
24
2.59
Strength
Actual
(ksi)
14.7
14.3
14.3
14.0
13.5
14.3
14.2
0.39
2.78
54.2%
IPS Modulus (1)
(0.25-0.65%)
(2)
(msi)
0.471
0.505
0.456
0.443
0.469
0.027
5.70
Failure Location
&
Comments
CPT (average):
Test Date: 3/9/2000
0.0060 in.
54.1%
Specimen
Specimen
Notch
Ultimate
In-plane Shear
IPS Modulus (1)
Failure Location
Number
Thickness
Width
Load
(0.25-0.65%) (2)
&
Comments
A1-910-042-1-5
A1-910-042-1-6
B1-910-042-1-5
B1-910-042-1-6
A1-910-042-1-7
B1-910-042-1-7
Average
Std. Dev.
COV, %
(in.)
0.1432
0.1434
0.1444
0.1447
0.1440
0.1440
0.1440
0.0006
0.40
(in.)
0.4542
0.4540
0.4545
0.4544
0.4544
0.4543
0.4543
0.0002
0.04
(lbs.)
866
831
873
857
842
875
857
18
2.05
Strength
Actual
(ksi)
13.3
12.8
13.3
13.0
12.9
13.4
13.1
0.26
1.97
(msi)
0.443
0.426
0.440
0.445
0.439
0.009
1.96
CPT (average):
Specimen
Specimen
Notch
Ultimate
In-plane Shear
Number
Thickness
Width
Load
B1-910-043-1-5
B1-910-043-1-6
A1-910-056-1-8
A1-910-056-1-9
A1-910-056-1-7
B1-910-056-1-7
Average
Std. Dev.
COV, %
(in.)
0.1436
0.1439
0.1444
0.1447
0.1440
0.1440
0.1441
0.0004
0.26
(in.)
0.4540
0.4542
0.4540
0.4536
0.4540
0.4537
0.4539
0.0002
0.05
(lbs.)
935
903
914
907
948
938
924
18
2.00
Strength
Actual
(ksi)
14.3
13.8
13.9
13.8
14.5
14.4
14.1
0.30
2.13
0.0060 in.
54.9%
IPS Modulus
(1)
(0.25-0.65%) (2)
(msi)
0.451
0.446
0.458
0.447
0.451
0.005
1.21
(1)
Modulus is determined to be the slope of the Stress-Shear Strain curve.
(2)
209
Failure Location
&
Comments
Iosipescu In-plane Shear Strength, Fluid Sensitivity
Fluid: Jet Fuel
Specimen Preconditioning: at RT for 500 hrs
Test Temperature: 180°F
Strain Gage: N/A
CPT (average):
Test Date: 12/30/1999
Specimen
Number
Specimen
Thickness
Notch
Width
Ultimate
Load
A1-910-041-1-15
A1-910-041-1-16
B1-910-041-1-15
B1-910-041-1-16
B1-910-041-1-17
Average
Std. Dev.
COV, %
(in.)
0.1439
0.1444
0.1427
0.1431
0.1434
0.1435
0.0007
0.47
(in.)
0.4534
0.4533
0.4535
0.4537
0.4533
0.4534
0.0002
0.04
(lbs.)
1186
1163
1169
1185
1215
1184
20
1.71
0.0060 in.
54.2%
In-plane Shear
Strength
Actual
(ksi)
18.2
17.8
18.1
18.3
18.7
18.2
0.34
1.84
Failure Location
&
Comments
Fluid: Hydraulic Fluid
Specimen Preconditioning: at RT for 60 - 90 minutes
Test Temperature: 180°F
Strain Gage: N/A
CPT (average):
Specimen
Number
Specimen
Thickness
Notch
Width
Ultimate
Load
A1-910-041-1-19
A1-910-041-1-20
A1-910-041-1-21
B1-910-041-1-19
B1-910-041-1-20
Average
Std. Dev.
COV, %
(in.)
0.1446
0.1447
0.1441
0.1436
0.1438
0.1441
0.0005
0.32
(in.)
0.4531
0.4568
0.4531
0.4536
0.4543
0.4542
0.0015
0.34
(lbs.)
1159
1185
1178
1196
1212
1186
20
1.67
0.0060 in.
54.2%
In-plane Shear
Strength
Actual
(ksi)
17.7
17.9
18.0
18.4
18.6
18.1
0.34
1.90
Failure Location
&
Comments
Fluid: MEK Solvent
Specimen Preconditioning: at RT for 60 - 90 minutes
Test Temperature: RT
Strain Gage: N/A
CPT (average):
Specimen
Number
Specimen
Thickness
Notch
Width
Ultimate
Load
A1-910-041-1-23
A1-910-041-1-24
B1-910-041-1-23
B1-910-041-1-24
B1-910-041-1-25
Average
Std. Dev.
COV, %
(in.)
0.1404
0.1413
0.1420
0.1422
0.1424
0.1417
0.0008
0.59
(in.)
0.4510
0.4538
0.4542
0.4539
0.4545
0.4535
0.0014
0.31
(lbs.)
1424
1422
1453
1472
1441
1442
21
1.45
0.0060 in.
54.2%
In-plane Shear
Strength
Actual
(ksi)
22.5
22.2
22.5
22.8
22.3
22.5
0.25
1.11
210
Failure Location
&
Comments
Apparent Interlaminar Shear Strength, 75°F (Dry)
-
Test Date: 12/5/1999, 4/3/02
Specimen
Number
Specimen
Depth
Specimen
Width
A1-910-041-1-1
A1-910-041-1-2
A1-910-041-1-3
A1-910-041-1-4
A1-910-041-1-5
A1-910-041-1-6
B1-910-041-1-1
B1-910-041-1-2
B1-910-041-1-3
B1-910-041-1-4
B1-910-041-1-5
B1-910-041-1-6
Average
Std. Dev.
COV, %
(in.)
0.10640
0.10585
0.10670
0.10520
0.10660
0.10525
0.10515
0.10530
0.10430
0.10445
0.10515
0.10580
0.10551
0.00078
0.74
(in.)
0.25010
0.25005
0.25015
0.25050
0.25010
0.25060
0.25025
0.24965
0.24870
0.25045
0.24985
0.25015
0.25005
0.00050
0.20
Test Frame: Instron 4510 & 4505
Strain Gage: N/A
CPT (average):
Span:
Thickness
Ratio
0.0060 in.
54.2%
Ultimate
Load
Short Beam
Shear
Strength
(ksi)
13.2
13.5
13.5
13.7
12.6
13.1
12.6
13.7
13.4
13.3
12.9
11.9
13.1
0.547
4.17
(kips)
469.4
476.0
482.0
482.2
449.1
459.8
442.1
480.6
464.1
464.7
453.2
418.6
461.8
18.9
4.10
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
Failure Location
&
Comments
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Strain Gage: N/A
Test Date: 12/5/1999, 4/3/02
Specimen
Number
Specimen
Depth
Specimen
Width
A1-910-042-1-1
A1-910-042-1-2
A1-910-042-1-3
A1-910-042-1-4
A1-910-042-1-5
A1-910-042-1-6
B1-910-042-1-1
B1-910-042-1-2
B1-910-042-1-3
B1-910-042-1-4
B1-910-042-1-5
B1-910-042-1-6
Average
Std. Dev.
COV, %
(in.)
0.10905
0.10870
0.10960
0.10930
0.10940
0.10840
0.10860
0.10865
0.10690
0.10665
0.10780
0.10760
0.10839
0.00096
0.89
(in.)
0.25040
0.25050
0.25045
0.25045
0.25045
0.25050
0.25000
0.25020
0.25035
0.25050
0.24980
0.25020
0.25032
0.00022
0.09
CPT (average):
Span:
Thickness
Ratio
0.0060 in.
54.1%
Ultimate
Load
Short Beam
Shear
Strength
(ksi)
13.6
14.1
13.7
12.9
12.7
12.2
14.7
14.2
15.0
14.0
14.5
14.2
13.8
0.851
6.17
(kips)
493.4
512.5
499.6
469.2
462.3
443.4
533.1
514.9
536.3
498.1
519.8
509.1
499.3
28.4
5.69
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
Failure Location
&
Comments
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Strain Gage: N/A
Test Date: 12/5/1999, 4/3/02
Specimen
Number
Specimen
Depth
Specimen
Width
A1-910-043-1-1
A1-910-043-1-2
A1-910-043-1-3
A1-910-043-1-4
A1-910-043-1-5
A1-910-043-1-6
B1-910-043-1-1
B1-910-043-1-2
B1-910-043-1-3
B1-910-043-1-4
B1-910-043-1-5
B1-910-043-1-6
Average
Std. Dev.
COV, %
(in.)
0.10825
0.10790
0.10845
0.10800
0.10805
0.10845
0.10680
0.10855
0.10795
0.10660
0.10830
0.10755
0.10790
0.00063
0.58
(in.)
0.25035
0.25170
0.25025
0.25025
0.25015
0.25080
0.25065
0.25020
0.25010
0.25065
0.25000
0.25010
0.25043
0.00047
0.19
CPT (average):
Span:
Thickness
Ratio
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
4:1
211
Ultimate
Load
(kips)
502.2
502.6
513.5
491.4
484.3
491.7
490.4
499.2
485.8
470.3
477.6
463.2
489.4
14.3
2.93
0.0060 in.
54.9%
Short Beam
Shear
Strength
(ksi)
13.9
13.9
14.2
13.6
13.4
13.6
13.7
13.8
13.5
13.2
13.2
12.9
13.6
0.353
2.60
Failure Location
&
Comments
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Shear Failure
Apparent Interlaminar Shear Strength, 75°F (Dry) - continued
Test Method: ASTM D2344-00
Specimen
Panel
Coupon
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
A-1
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
B-2
1-1
1-3
1-5
4-7
4-9
4-11
8-13
8-15
1-2
1-4
1-6
4-8
4-10
4-12
8-14
8-16
1-1
1-3
1-5
4-7
4-9
4-11
8-13
8-15
1-2
1-4
1-6
4-8
4-10
4-12
8-14
8-16
8-18
Average
Std, Dev.
COV, %
Specimen
Depth
(in.)
Specimen
Width
(in.)
Span
(in.)
Ultimate
Load
(lbs)
Initial
Load
(lbs)
Total
Load
(lbs)
0.10705
0.10750
0.10840
0.10795
0.10765
0.10870
0.10765
0.10880
0.10665
0.10790
0.10860
0.10700
0.10855
0.10910
0.10785
0.10845
0.10795
0.10890
0.10925
0.10770
0.10850
0.10855
0.10740
0.10810
0.10850
0.10900
0.10855
0.10815
0.10855
0.10850
0.10775
0.10820
0.10825
0.25075
0.25050
0.25025
0.24950
0.24935
0.24925
0.24980
0.24960
0.25075
0.25030
0.25020
0.24960
0.24930
0.24925
0.24970
0.24950
0.25070
0.25015
0.25015
0.25080
0.25035
0.25005
0.24975
0.24975
0.25060
0.25030
0.25010
0.25075
0.25050
0.25040
0.24985
0.24960
0.24950
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
464.9
435.5
435.0
482.2
465.6
438.2
450.7
476.5
454.0
426.4
430.4
462.9
457.7
419.2
456.6
432.6
499.2
482.3
486.7
494.4
463.1
476.0
437.0
402.1
449.0
435.1
447.1
447.7
436.5
477.9
409.8
397.1
409.4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
464.9
435.5
435.0
482.2
465.6
438.2
450.7
476.5
459.2
431.6
435.6
468.1
462.9
424.4
461.8
437.8
499.2
482.3
486.7
494.4
463.1
476.0
437.0
402.1
454.2
440.3
452.3
452.9
441.7
483.1
415.0
402.3
414.6
Specimen
Panel
Coupon
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
A-13
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
B-14
2-1
2-3
2-5
5-7
5-9
5-11
7-13
7-15
2-2
2-4
2-6
5-8
5-10
5-12
7-14
7-16
7-18
2-1
2-3
2-5
5-7
5-9
5-11
7-13
7-15
2-2
2-4
2-6
5-8
5-10
5-12
7-14
7-16
Average
Std, Dev.
COV, %
SBS
Strength
(ksi)
13.0
12.1
12.0
13.4
13.0
12.1
12.6
13.2
12.9
12.0
12.0
13.1
12.8
11.7
12.9
12.1
13.8
13.3
13.4
13.7
12.8
13.2
12.2
11.2
12.5
12.1
12.5
12.5
12.2
13.3
11.6
11.2
11.5
12.5
0.704
5.61
Failure
Location
Testing
Facility
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
Specimen
Depth
(in.)
0.10805
0.10660
0.10820
0.10725
0.10735
0.10855
0.10720
0.10805
0.10745
0.10730
0.10865
0.10675
0.10815
0.10905
0.10700
0.10785
0.10870
0.10670
0.10695
0.10715
0.10730
0.10785
0.10745
0.10815
0.10810
0.10710
0.10705
0.10750
0.10725
0.10805
0.10790
0.10785
0.10815
Specimen
Width
(in.)
0.25055
0.25035
0.25015
0.25040
0.25040
0.25020
0.24960
0.25035
0.24945
0.25030
0.25020
0.24990
0.25020
0.25020
0.25020
0.25010
0.25010
0.25030
0.25040
0.25030
0.24955
0.25035
0.25035
0.24995
0.24970
0.25035
0.25035
0.25025
0.25060
0.25045
0.25020
0.24950
0.24935
Span
(in.)
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
Ultimate
Load
(lbs)
428.0
475.7
436.1
463.4
484.5
447.2
481.9
466.9
429.9
456.5
446.9
442.9
416.1
408.5
436.2
412.9
387.6
495.6
470.1
455.4
454.9
441.0
460.4
412.5
430.0
436.2
450.0
463.6
449.1
413.4
428.3
423.3
423.1
Initial
Load
(lbs)
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
Total
Load
(lbs)
428.0
475.7
436.1
463.4
484.5
447.2
481.9
466.9
435.1
461.7
452.1
448.1
421.3
413.7
441.4
418.1
392.8
495.6
470.1
455.4
454.9
441.0
460.4
412.5
430.0
441.4
455.2
468.8
454.3
418.6
433.5
428.5
428.3
Test Conditions
Temp
RH
(°F)
(%)
73
73
73
73
73
73
73
73
78
78
78
78
78
78
78
78
73
73
73
73
73
73
73
73
77
77
77
77
77
77
77
77
77
50
50
50
50
50
50
50
50
65
65
65
65
65
65
65
65
50
50
50
50
50
50
50
50
66
66
66
66
66
66
66
66
66
Test
Operator
Test
Frame
Test
Date
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
5/21/2002
5/21/2002
5/21/2002
5/21/2002
5/17/2002
5/17/2002
5/17/2002
5/17/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
5/17/2002
5/17/2002
5/17/2002
5/17/2002
5/21/2002
5/21/2002
5/21/2002
5/21/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
Test
Operator
Test
Frame
Test
Date
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
Inst 4510
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
5/21/2002
5/21/2002
5/21/2002
5/21/2002
5/17/2002
5/17/2002
5/17/2002
5/17/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
5/17/2002
5/17/2002
5/17/2002
5/17/2002
5/21/2002
5/21/2002
5/21/2002
5/21/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
SBS
Strength
(ksi)
11.9
13.4
12.1
12.9
13.5
12.3
13.5
12.9
12.2
12.9
12.5
12.6
11.7
11.4
12.4
11.6
10.8
13.9
13.2
12.7
12.7
12.2
12.8
11.4
11.9
12.3
12.7
13.1
12.7
11.6
12.0
11.9
11.9
12.4
0.700
5.63
212
Failure
Location
Testing
Facility
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
Test Conditions
Temp
RH
(°F)
(%)
73
50
73
50
73
50
73
50
73
50
73
50
73
50
73
50
77
66
77
66
77
66
77
66
77
66
77
66
77
66
77
66
77
66
73
50
73
50
73
50
73
50
73
50
73
50
73
50
73
50
81
62
78
65
78
65
78
65
78
66
77
66
77
66
77
66
Apparent Interlaminar Shear Strength, 75°F (Dry) - continued
Specimen
Panel
Coupon
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
A-25
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
B-26
3-1
3-3
3-5
6-7
6-9
6-11
8-13
8-15
3-2
3-4
3-6
6-8
6-10
6-12
8-14
8-16
8-18
3-1
3-3
3-5
6-7
6-9
6-11
8-13
8-15
3-2
3-4
3-6
6-8
6-10
6-12
8-14
8-16
8-18
Average
Std, Dev.
COV, %
Specimen
Depth
(in.)
Specimen
Width
(in.)
Span
0.11110
0.10990
0.11135
0.11075
0.11040
0.11130
0.11040
0.11020
0.11055
0.11075
0.11165
0.11045
0.11135
0.11085
0.11025
0.11040
0.11065
0.11080
0.11075
0.11150
0.11105
0.11130
0.11165
0.11175
0.11180
0.11145
0.11095
0.11125
0.11145
0.11145
0.11205
0.11195
0.11225
0.11250
0.25095
0.25095
0.25080
0.25090
0.25020
0.24995
0.25025
0.25015
0.25125
0.25090
0.25090
0.24990
0.24985
0.25000
0.24995
0.24985
0.24970
0.25105
0.25080
0.25075
0.25030
0.25000
0.24995
0.25040
0.25010
0.25080
0.25080
0.25065
0.25000
0.25010
0.25000
0.25010
0.25020
0.25010
Initial
Load
(lbs)
Total
Load
(lbs)
SBS
Strength
(ksi)
Failure
Location
Testing
Facility
(in.)
Ultimate
Load
(lbs)
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
0.446
471.8
501.1
434.2
483.7
478.5
452.9
449.8
460.6
462.2
484.3
414.7
425.1
422.8
447.9
396.6
412.3
427.8
495.5
469.0
480.0
462.9
475.8
457.0
450.5
430.2
446.2
427.5
425.2
449.5
452.9
447.6
401.8
386.4
407.9
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
471.8
501.1
434.2
483.7
478.5
452.9
449.8
460.6
467.4
489.5
419.9
430.3
428.0
453.1
401.8
417.5
433.0
495.5
469.0
480.0
462.9
475.8
457.0
450.5
430.2
451.4
432.7
430.4
454.7
458.1
452.8
407.0
391.6
413.1
12.7
13.6
11.7
13.1
13.0
12.2
12.2
12.5
12.6
13.2
11.2
11.7
11.5
12.3
10.9
11.4
11.8
13.4
12.7
12.9
12.5
12.8
12.3
12.1
11.5
12.1
11.7
11.6
12.2
12.3
12.1
10.9
10.5
11.0
12.1
0.758
6.26
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
Specimen
Panel
Coupon
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
A-37
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
B-38
1-1
1-3
1-5
3-7
3-9
3-11
8-13
8-15
1-2
1-4
1-6
3-8
3-10
3-12
8-14
8-16
8-18
1-1
1-3
1-5
3-7
3-9
3-11
8-13
8-15
1-2
1-4
1-6
3-8
3-10
3-12
8-14
8-16
8-18
Average
Std, Dev.
COV, %
73
73
73
73
73
73
73
73
80
80
80
80
80
80
80
80
80
73
73
73
73
73
73
73
73
81
81
81
81
81
81
81
81
81
50
50
50
50
50
50
50
50
65
65
65
65
65
65
65
63
63
50
50
50
50
50
50
50
50
61
61
61
61
61
61
61
61
61
Test
Operator
Test
Frame
Test
Date
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Ken G.
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
Test
Operator
Test
Frame
Test
Date
Debra W.
Debra W.
Debra W.
Debra W.
John S.
John S.
John S.
John S.
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
John S.
John S.
John S.
John S.
Debra W.
Debra W.
Debra W.
Debra W.
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Ken G
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
Inst 4505
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
MTS 318.1
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
5/20/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
6/3/2002
Specimen
Depth
(in.)
Specimen
Width
(in.)
Span
Ultimate
Load
(lbs)
Initial
Load
(lbs)
Total
Load
(lbs)
SBS
Strength
(ksi)
Failure
Location
Testing
Facility
(in.)
0.10725
0.10695
0.10680
0.10725
0.10670
0.10680
0.10715
0.10700
0.10670
0.10680
0.10720
0.10655
0.10685
0.10691
0.10715
0.10700
0.10735
0.10825
0.10800
0.10870
0.10780
0.10755
0.10840
0.10675
0.10715
0.10800
0.10885
0.10850
0.10740
0.10835
0.10835
0.10720
0.10710
0.10785
0.24980
0.24945
0.24950
0.24990
0.24955
0.24960
0.25040
0.24905
0.24980
0.24960
0.24945
0.24950
0.24970
0.24940
0.24980
0.24970
0.24995
0.25030
0.25050
0.25030
0.25005
0.24990
0.24975
0.25050
0.25040
0.25060
0.25030
0.25010
0.24945
0.24975
0.24970
0.24995
0.25030
0.25020
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
0.432
436.0
452.1
421.1
442.6
413.7
444.7
418.3
401.4
431.5
429.1
410.9
445.7
415.0
426.4
369.9
397.0
385.4
451.6
415.6
403.2
470.0
479.9
446.7
405.3
396.3
417.4
407.8
423.2
448.6
419.4
418.7
360.2
372.2
382.1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
5.2
436.0
452.1
421.1
442.6
413.7
444.7
418.3
401.4
436.7
434.3
416.1
450.9
420.2
431.6
375.1
402.2
390.6
451.6
415.6
403.2
470.0
479.9
446.7
405.3
396.3
422.6
413.0
428.4
453.8
424.6
423.9
365.4
377.4
387.3
12.2
12.7
11.9
12.4
11.7
12.5
11.7
11.3
12.3
12.2
11.7
12.7
11.8
12.1
10.5
11.3
10.9
12.5
11.5
11.1
13.1
13.4
12.4
11.4
11.1
11.7
11.4
11.8
12.7
11.8
11.7
10.2
10.6
10.8
11.8
0.750
6.36
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
Interlaminar Shear
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
TCA
TCA
TCA
TCA
TCA
TCA
TCA
TCA
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
NIAR
213
Test Conditions
Temp
RH
(°F)
(%)
Test Conditions
Temp
RH
(°F)
(%)
73
73
73
73
73
73
73
73
79
79
79
79
79
79
79
79
79
73
73
73
73
73
73
73
73
79
79
79
79
79
79
79
79
79
50
50
50
50
50
50
50
50
64
64
64
64
64
64
64
64
64
50
50
50
50
50
50
50
50
66
66
66
66
66
66
66
66
66
APPENDIX G. DATES OF PANEL MANUFACTURE AND COPY OF FAA FORM
8130-3
214
215
216
217
218
219
220
221
222
223
224
225
226
227
228
229
230
231
232
233
234
235
236
237
238
239
240
241
242
243
244
245
246
247
248
249
250
251
252
253
254
255
256
257
258
259
260
261
262
263
264
265
266
267
268
269
270
271
272
273
274
275
276
277
278
279
280
281
282

TORAY T700GC-12K-31E/#2510 - National Institute for Aviation

Transcription

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