Material Property Data Acquisition and Qualification Test Plan For Hexcel 8552 IM7 Unidirectional Prepreg at 190 gsm & 35% RC

Transcription

1 Material Supplier Contact: Steve Ellery Marketing Manager, Americas Matrix Hexcel Corporation Tel: (801) Fax: (801) Cessna Aircraft Company Contact: Engin Sabuncu Cessna Aircraft Company 5800 E Pawnee Wichita, KS Document No.: NTP 1828Q1 Material Property Data Acquisition and Qualification Test Plan For Hexcel 8552 IM7 Unidirectional Prepreg at 190 gsm & 35% RC FAA Special Project Number SP4614WI-Q Prepared by: Yeow Ng, John Tomblin, Ric Abbott Reviewed by: John Adelmann, Kit Bowman, Bret Brummer (Raytheon Aircraft), Allison Crockett (General Atomics), Susan Daggett (ATK), Jim Diepenbrock, Rich Fields, Warren Hatfield (Raytheon Aircraft), Jeff Hendrix, Ed Hooper, Robert Glenn (Gulfstream), Dana Granville (U.S. Army), Erkan Kececi (Cessna), Jim Krone (Cessna), Guillermo Mayorga, William McCarvill (Commercial Chemistries), Mark Ofsthun (Spirit AeroSystems), David Ostrodka (FAA), Glen Otzinger (Toyota Aircraft), Dusty Penn (ACG), Chris Ridgard (ACG), Carl Rousseau (Lockheed Martin Aero), Engin Sabuncu (Cessna), Peter Shyprykevich (FAA), Mario Simard (Bombardier), Brent Stevenson (Texas Comp istin Strole (NCAMP), Melanie Violette (Raytheon Aircraft), Stephen Ward (SW Composites), Bill Webb (Cytec), Cytec Engineered Materials, Hexcel Corporation, Spirit AeroSystems. Approved by: Page 1 of 41

2 TABLE OF CONTENTS 1. INTRODUCTION USE OF FIBER FROM MULTIPLE FIBER MANUFACTURING LINES, PRODUCED BY THE SAME VENDOR WITH THE SAME FIBER TRADE NAME CFR REGULATIONS TEST METHODS PANEL AND SPECIMEN IDENTIFICATION UNCURED PREPREG AND RESIN TESTING CURED LAMINATE PHYSICAL TESTING CURED LAMINA AND LAMINATE MECHANICAL PROPERTY TESTING ENVIRONMENTAL CONDITIONING NON-AMBIENT TESTING PROCESS DEFINITION LAMINA LEVEL TESTS LAMINATE LEVEL TESTS (DESIGN GUIDANCE PROPERTIES) FLUID SENSITIVITY SCREENING FREEZER STORAGE LIFE AND OUT-TIME VERIFICATION OTHER TEST PROCEDURES TACK TEST (REF. CESSNA AIRCRAFT COMPANY SPECIFICATION CPTI003): DRAPE TEST NOMINAL CURED PLY THICKNESS AND NORMALIZATION INSPECTION, CONFORMANCE, W ITNESSING, AND SHIPPING DATA REDUCTION AND REPORTING SPECIFICATIONS REFERENCES REVISIONS APPENDIX APPENDIX APPENDIX Page 2 of 41

3 ACO AMS ANOVA ASAP ASME ASTM BMI CLC CMH-17 CPT CTD CV DAR DER DMA DMIR DoD DSC ETW FAA FAW FTIR FV HPLC IAB IR ILT MIDO NASA NCAMP NDI NIAR NIST OEM PCD QA QC QI RH RTD SACMA SAE SBS Tg ABBREVIATIONS AND ACRONYMS Aircraft Certification Office Aerospace Material Specification Analysis of Variance Agate Statistical Analysis Program American Society of Mechanical Engineers American Society for Testing and Materials Bismaleimide Combined Loading Compression Composite Materials Handbook 17 (formerly MIL-HDBK-17) Cured Ply Thickness Cold Temperature Dry Coefficient of Variation Designated Airworthiness Representative Designated Engineering Representative Dynamic Mechanical Analysis Designated Manufacturing Inspection Representative Department of Defense Differential Scanning Calorimetry Elevated Temperature Dry Elevated Temperature Wet Federal Aviation Administration Fiber Areal Weight Fourier Transform Infrared Spectroscopy Fiber Volume fraction High Performance Liquid Chromatography Industry Advisory Board (an NCAMP Board) Infrared spectroscopy Inter-Laminar Tension Manufacturing Inspection District Office National Aeronautics and Space Administration National Center for Advanced Materials Performance Non-Destructive Inspection National Institute for Aviation Research National Institute of Standards and Technology Original Equipment Manufacturer Process Control Document Quality Assurance Quality Control Quasi-Isotropic Relative Humidity Room Temperature Dry Suppliers of Advanced Composite Materials Association Society of Automotive Engineers Short Beam Strength Glass Transition Temperature Page 3 of 41

4 TGA WSU Thermogravimetric Analyzer Wichita State University 1. Introduction This document is a qualification test plan for Hexcel 8552 IM7 unidirectional prepreg, procured to NCAMP material specification NMS 128/2. The test panels are fabricated per NCAMP process specification NPS using baseline M cure cycle. The plan is designed to provide material properties and basis values to be shared across a wide range of projects. The test matrices are based around the recom dations of references 1, 2, and 3, which do not address all the needs of any specific company's programs. The test matrices are intended to generate base level building block lamina and laminate data that are of common usefulness. Specific properties, environments, laminate architecture, and loading situations that individual companies may need may require additional testing. The data generated under this program is intended for general distribution to the public, either freely or at a price that does not exceed the cost of reproduction (e.g. printing) and distribution (e.g. postage). Data subjected to export control regulations, if any, will be made available on a case by case basis through written request to NCAMP. Panels using three batches of material will be fabricated by Cessna Aircraft Company in Wichita, Kansas. The three batches of material are designed to fulfi l base material qualification requirements. The following product forms will be characterized: Prepreg Name Hexcel 8552 IM7 unidirectional prepreg Description About the Prepreg Resin name: Hexcel 8552, Reinforcement: IM7 unidirectional prepreg, Sizing: 0.25% G, Fiber Areal Weight: 190 gsm, Resin Content: 35% The following material code will be used throughout this document to reference the prepreg: Material Code H12 Prepreg Name Hexcel 8552 IM7 unidirectional prepreg For each prepreg, qualification data will be generated on at least three separate prepreg batches. For unidirectional carbon fiber prepreg materials the prepreg batches will be defined as: Unidirectional Prepreg Batch A B C Fiber Lot Fiber Lot 1 Fiber Lot 2 Fiber Lot 3 Resin Batch Definitions of batches or lots will be in accordance with CMH-17 guidelines. A minimum of two additional prepreg batches with unique fiber lots and resin batches as shown above will be needed if significant batch-to-batch variability is observed, to allow for the use of ANOVA to generate b-basis values in accordance with latest CMH-17 guidelines. Page 4 of 41

5 Should additional batches of prepreg beyond the first 5 batches be used for data generation, each batch shall contain unique resin batches but may incorporate any or none of the original fiber lots. The purpose is to capture as much realistic material variability as possible in the original qualification program. 1.1 Use of fiber from multiple fiber manufacturing lines, produced by the same vendor with the same fiber trade name All the fiber lots for fabric and unidirectional prepreg qualifications shall be produced by the same vendor with the same fiber trade name. If desired, up to three fiber manufacturing lines (may be at different locations), with each producing at least one third of the total fibers, may be used to produce the fiber lots. In addition, the following shall be observed: 1. Prior to using fibers from more than one fiber manufacturing line, historical fiber data from at least 10 fiber lots manufactured over a reasonable and representative time span from each fiber manufacturing line shall be statistica ly compared. NCAMP shall perform the analysis and communicate with its members prior to such prepreg qualification process. 2. After the qualification program, there shall be an ongoing comparison of fiber properties to ensure that the fiber manufacturing lines continue to produce equivalent fibers. NCAMP shall be involved in this ongoing effort and develop a system to maintain consistent communication with its members. This form of communication should apply to and include prepreg properties as well. 3. The fiber manufacturing process controls and parameters, raw materials, management system, employee training, quality system, and other key elements of the production process should essentially be identical for all the fiber manufacturing lines. 4. Fibers from all the fiber manufacturing lines shall meet the same fiber detail specification requirements. Fibers manufactured by separate fiber manufacturing lines will be listed as separate products under the qualified products list within the same detail specification. 5. Additional requirements will be specified in the NCAMP carbon fiber specification, and will be subjected to member review. The use of multiple fiber manufacturing lines may be desirable in a shared material database environment, although it may increase the variability in the data which may result in lower material basis values and allowables. In addition, there is an increased risk of significant batch-to-batch variability. If significant batch-to-batch variability is detected, per the latest CMH-17 guidelines, the use of ANOVA and a minimum of five material batches will be required to generate b-basis values CFR Regulations Test results will be analyzed to produce allowables that can be employed by a qualified organization to show compliance with 14CFR , , or Page 5 of 41

6 2. Test Methods All testing will be in accordance with nationally recognized standards, methods and procedures. Specific mechanical property test methods applicable to the test program in this document include: ASTM D2344/D2344M-00(2006) Standard Test Method for Short-Beam Strength of Polymer Matrix Composite Materials and Their Laminates ASTM D3039/D3039M-00(2006) Standard Test Method for Tensile Properties of Polymer Matrix Composite Materials ASTM D3518/D3518M-94(2001) Standard Test Method for In-Plane Shear Response of Polymer Matrix Composite Materials by Tensile Test of a ± 45º Laminate In-Plane Shear Strength and Modulus ASTM D5766/D5766M-02a Standard Test Method for Open Hole Tensile Strength of Polymer Matrix Composite Laminates ASTM D5961/D5961M-05e1 Standard Test Method for Bearing Response of Polymer Matrix Composite Laminates ASTM D ae1 Standard Test Method for Measuring the Curved Beam Strength of a Fiber-Reinforced Polymer-Matrix Composite ASTM D6484/D6484M-04 Standard Test Method for Open-Hole Compressive Strength of Polymer Matrix Composite Laminates ASTM D6641/D6641M-01e1 Standard Test Method for Determining the Compressive Properties of Polymer Matrix Composite Laminates Using a Combined Loading Compression (CLC) Test Fixture ASTM D6742/D6742M-02 Standard Practice for Filled-Hole Tension and Compression Testing of Polymer Matrix Composite Laminates ASTM D7136/D7136M-05e1 Standard Test Method for Measuring the Damage Resistance of a Fiber-Reinforced Polymer Matrix Composite to a Drop-Weight Impact Event ASTM D7137/D7137M-05e1 Standard Test Method for Compressive Residual Strength Properties of Damaged Polymer Matrix Composite Plates Unless otherwise specified in this test plan or its related documentation, all recommendations of the standards shall be considered a datory. Any deviations from the standards must be approved by the FAA and documented in the final tes port. For all ASTM D3039 tension (cross-ply and laminate) and ASTM D6641 compression specimens, tabs are optional and shall be used only if an acceptable failure mode cannot be achieved without tabs. The test report shall include the completed forms in PMC_Data_Collection_Template.xls to document the specific test procedures and specimen configurations used. For filled-hole and bearing tests, the hole diameter will be 0.25 in in. The following fasteners should be used: 1) NASM21296 bolts with MS21085 nuts and MS21299 washers, 2) NASM21297 bolts with MS21084 nuts and MS21206 washers, Page 6 of 41

7 3) NASM14181 bolts with MS14182 nuts and MS14183 washers, or equivalent The grip length will be specified and reported for each different specimen thickness. For filled-hole tension tests, the fasteners shall be installed to 85±5 in-lb. For filled-hole compression and bearing tests, the fasteners shall be installed to 30±5 in-lb. Fasteners will be installed after moisture conditioning. Unless otherwise specified, a tolerance of ±5 F will apply to all temperature conditions specified in this document. 3. Panel and Specimen Identification All panels and specimens shall be uniquely identified by an 11 code reference system, cross referenced with descriptive identification information as follows: This Document Number- Prepregger ID-Material Code-Fabricator ID-Intended Test Type-Batch ID-Cure Cycle ID- Test Panel ID-Actual Test Type-Test Condition-Specimen Number. For example, NTP1828Q1-HXL-H12-CES-LT-A-M1-2-TT-RTD-3] denotes Prepregger: Hexcel, Prepreg Name: Hexcel 8552 IM7 unidirectional prepreg, Fabricator: Cessna, Intended Test Type: Longitudinal Tension, Prepreg Batch: A, Cure Cycle: Medium Temperature Cycle 1, Test Panel ID: 2, Actual Test Method: Transverse Tension, Test Condition: Room Temperature Dry, and Specimen Number: 3. The testing lab may assign a separate identification code but must reference the 11 code reference system and uniquely identify the panels and specimens. Panels to be manufactured are listed in Appendix 2 and will follow the same I.D. above, inherently omitting the actual test type, test condition and specimen number. The above parameters can have the following values: Hexcel: HXL Material Code H12 Cessna: CES Prepregger ID Prepreg Name Hexcel 8552 IM7 unidirectional prepreg Fabricator ID (Company that layup, bag, and cure the test panels) Intended Test Type WT: Warp tension UNT1, UNT2...: Un-notched Tension Layup 1, Layup 2, etc. FT: Fill Tension OHT1, OHT2...: Open Hole Tension Layup 1, Layup 2, etc. WC: Warp Compression OHC1, OHC2...: Open Hole Compression Layup 1 etc. FC: Fill Compression FHT1, FHT2 : Filled Hole Tension Layup 1, Layup 2 etc. IPS: In Plane Shear FHC1, FHC2 : Filled Hole Compression Layup 1, Layup 2 etc. SBS: Short Beam Strength SSB1, SSB2 : Single Shear Pin Bearing Layup 1, Layup 2..etc. LT: Longitudinal Tension CAI1: Compression After Impact Layup 1, Layup 2, etc. TT: Transverse Tension FSL: Freezer and Out Life Verification LC: Longitudinal Compression DMA: Dynamic Mechanical Analysis TC: Transverse Compression DSC: Differential Scanning Calorimetry ILT: Interlaminar Tension TGA: Thermogravimetric Analysis QI: Quasi Isotropic SBS1: Short Beam Strength Layup 1 Page 7 of 41

8 (Note that the layup numbers 1, 2 and 3 correspond to those designated as quasi isotropic, soft and hard respectively. In addition, the 0 /90 cross-plied laminates used for the unidirectional materials only are designated Layup 0 ). Batch ID: A, B, C, D, E, F etc. (to be cross referenced with prepreg batch numbers as shown in appendix 3) Cure Cycle ID: (see NPS 81228) M1, M2, M3, etc.: Medium/Baseline Temp. Cure Cycle 1, 2, 3, etc. AH1, AH2, AH3, etc.: Alternate High Pressure Cure Cycle 1, 2, 3, etc. AL1, AL2, AL3, etc.: Alternate Low Pressure Cure Cycle 1, 2, 3, etc. Note: Cure Cycle numbers 1, 2, 3, etc. in Appendix 2 are for reference only. Actual numbers may vary depending on the actual cure cycle runs. Test Panel ID: 1,2,3,4,5,6,7,8,9,A,B,C.. etc. (restart from 1 for every Cure Cycle ID) Actual Test Type WT: Warp tension UNT1, UNT2...: Un-notched Tension Layup 1, Layup 2, etc. FT: Fill Tension OHT1, OHT2...: Open Hole Tension Layup 1, Layup 2, etc. WC: Warp Compression OHC1, OHC2...: Open Hole Compression Layup 1 etc. FC: Fill Compression FHT1, FHT2 : Filled Hole Tension Layup 1, Layup 2 etc. IPS: In Plane Shear FHC1, FHC2 : Filled Hole Compression Layup 1, Layup 2 etc. SBS: Short Beam Strength PB1, PB2 : Single Shear Pin Bearing Layup 1, Layup 2..etc. LT: Longitudinal Tension CAI1: Compression After Impact Layup 1, Layup 2, etc. TT: Transverse Tension FSL: Freezer and Out Life Verification LC: Longitudinal Compression DMA: Dynamic Mechanical Analysis TC: Transverse Compression DSC: Differential Scanning Calorimetry ILT: Interlaminar Tension Layup TGA: Thermogravimetric Analysis QI: Quasi Isotropic SBS1: Short Beam Strength Layup 1 Test Condition: Specimen Number: CTD, RTD,, ETW (cold temp. dry moisture, room temp. dry moisture, etc., see section 6, if testing at more than one elevated temperature use 1, 2 etc.) FS11RT, FS12RT, FS13RT, etc. (fluid sensitivity test - see Table 5) 0/1, 0/5, 0/7, 0/10, etc. (Freezer and Out Life Verification see Table 6b) D, W (dry, wet conditions for DMA) 1,2,3,4,5,6,7,8,9,A,B,C.. etc. 4. Uncured Prepreg and Resin Testing The following tests will be conducted on each batch of prepreg or resin. The tests will be conducted by Hexcel. The test results, along with specific test procedures, such as test temperature and specimen size used to acquire the data (see Note 1 below), will be sent to NCAMP for inclusion in the final report. Table 1 Property Method (Note 1) Min Replicates per batch (Note 5) Cured neat resin density ASTM D Fiber content/areal weight SACMA SRM 23R-94 6 (Note 3) Resin content ASTM D3529/D3529M-97(2003)e1 6 (Note 3) Volatile content ASTM D3530/D3530M-97(2003) 6 (Note 3) Page 8 of 41

9 Flow ASTM D (2004) 6 (Note 3) Gel Time ASTM D (2004) 6 HPLC (Note 4) SACMA SRM 20R-94 3 FTIR (Note 4) ASTM E168-06, ASTM E Chemical reactivity and degree of advancement by DSC (Note 2 & 4) 98(2002) SACMA SRM 25R-94 3 Notes 1: Where the applicable standard allows variations in specimen form or test method, the specific parameters to be used will be specified in the test work instructions and reported in the final test report. 2: When performed on a prepreg, if possible, perform TGA on the specimens after DSC to determine the actual specimen resin content so that the heat of reaction can be normalized according to resin content. If TGA ilable, normalize the heat of reaction to resin content as determined from ASTM D3529. Report the onset temperature, peak temperature and total heat of reaction. 3: Three specimens must be taken across the width of the prepreg, preferably at locations covering the entire length of the prepreg roll from which test panels are taken from. 4: Graphical results along with test procedures such as heating rate and sample weight should be sent to NCAMP for inclusion in the test report. 5: If the quality control lab is separate from the engineering lab, both labs must perform the tests. Page 9 of 41

10 5. Cured Laminate Physical Testing The properties in Table 2 shall be determined for each panel used for test coupons with the exception of Tg by DMA which will be conducted on one laminate per batch from each oven cure conducted where that batch is present. The tests will be performed by the National Institute for Aviation Research (NIAR) Composites Laboratory under the supervision of NCAMP. These tests may be repeated by the participating fabricators. Table 2 Property Condition/Method (Note 1) Min Replicates per panel Cured Ply Thickness ASTM D All data from mechanical test specimens Laminate Density ASTM D Fiber Volume, % by Volume ASTM D (Note 2) 3 Resin Content, % by Weight ASTM D (Note 2) 3 Ultrasonic Through Transmission, C-Scan MIL-HDBK-787A (Note 3) 1 Glass Transition Temperature, Tg by DMA Dry and Wet SACMA SRM 18R-94 1 Dry, 1 Wet (Note 4) Glass Transition Temperature, Tg by TMA Dry and Wet - HSP-T2 Rev 1 (by TMA)(Note 5) 1 Dry, 1 Wet (Note 4) Notes 1: Where the applicable standard allows variations in specimen form or test method, the specific parameters to be used will be specified in the test work instructions and reported in the final test report. 2: Method II, except for laminates of materials where actual fiber weight is not accurately known prior to impregnation, as in the case for unidirectional materials. For these materials, in order to verify Method II is accurate, a minimum of 12 samples per batch shall be tested by Method I, Procedure B. 3: Five MHz is preferred for solid laminates. Panels with anomaly should be segregated. Microscopy images may be taken from questionable areas. NCAMP must be involved in the review of all C-scans. 4: Minimum total of 24 dry and 24 wet for each material system. 5: HSP-T2 Revision 1 is a Hexcel non-proprietary test method standard which may be obtained from NCAMP. HSP-T2 is similar but not equivalent to ASTM E2092. Page 10 of 41

11 6. Cured Lamina and Laminate Mechanical Property Testing The following tests will be performed by the NIAR Composites Laboratory under the supervision of NCAMP. Specimen dimensions should be taken before moisture conditioning. Test environments are defined as: CTD = -65±5 F, dry RTD = 70±10 F, room temperature dry = 250±5 F, dry ETW = 250±5 F, wet (equilibrium moisture content) Elevated temperature level of 250±5 F must be reduced if wet glass transition temperature is not 300 F or higher. The elevated temperature level will be adjusted to 50 F below the measured wet glass transition temperature. All failure modes must be clearly identified. Testing shall achieve appropriate failure modes. Within each test method and test environment, the failure mode shall be evaluated immediately after each test by an FAA ACO engineer or FAA DER. Obvious improper failure modes shall be logged. If a second improper failure mode occurs, testing shall cease until the test setup and test data can be reviewed by the FAA and NCAMP. Retain the samples until data review is complete and the test report is finalized. All tested specimens shall be digitally photographed after each test in order to pictorially document failure modes. Representative photos shall be included in the final report. 6.1 Environmental Conditioning For dry testing, specimens will be dried at 160 F±5 F for 120 to 130 hours. After drying, specimens should be kept in a desiccator until mechanical testing. Alternatively, the specimens may be left at ambient laboratory condition for a maximum of 14 days until mechanical testing (no drying will be required if spec 14 days from the date they were cured). Ambient laboratory condition is defined as 70 F±10 F. Since moisture absorption and desorption rate for epoxy is very slow at ambient temperature, there is no requirement to maintain relative humidity levels. Page 11 of 41

12 For wet conditioning, specimens will be dried at 160 F±5 F for 120 to 130 hours before being conditioned to equilibrium at 160 F±5 F and 85% ± 5%. Effective moisture equilibrium is achieved when the average moisture content of the traveler specimen changes by less than 0.05% for three consecutive readings which are 7 ±0.5 days apart and may be expressed by: W i -W W b i - 1 < where: W i = weight at current time W i 1 = weight at previous time = baseline weight prior to conditioning W b When representative specimens may not be measured to determine the moisture content (due to size, fastener and tab effects), traveler coupons of at least 1 by 1 by specimen thickness and weighing at least 5 grams may be used to establish weight gain measurements. If the specimens or traveler coupons pass the criteria for three consecutive readings which are 7 ±0.5 days apart, the specimens may be kept in the environmental chamber for up to an additional 60 days. Alternatively, the specimens may be removed from the environmental chamber and placed in a sealed plastic bag along with a moist cotton towel for a maximum of 14 days until mechanical testing. Strain-gaged specimens may be removed from the controlled environment for a maximum of 2 hours for application of gages in ambient laboratory conditions. 6.2 Non-ambient Testing The chamber should be of adequate size so that all test fixtures and load frame grips may be contained within the chamber. For elevated temperature testing, the temperature chamber, test fixture, and grips should be preheated to the specified temperature. Each specimen should be heated to the required test temperature as verified by a thermocouple in direct contact with and taped to the specimen gage section. The heat-up time of the specimen shall not exceed 5 minutes. The test should + 1 start 2 minutes after the specimen has reached the test temperature. During the test, the 0 temperature, as measured on the specimen, shall be within ± 5 F of the required test temperature. For subzero temperature testing, each specimen should be cooled to the required test temperature as verified by a thermocouple in direct contact with and taped to the specimen + 1 gage section. The test should start 5 minutes after the specimen has reached the test 0 temperature. During the test, the temperature, as measured on the specimen, shall be within ± 5 F of the required test temperature. Page 12 of 41

13 6.3 Process Definition For each combination of test, batch and condition, the specimens are to be selected from a minimum of two separate panels cured separately as shown in Figure 1 unless otherwise specified. Panels 1, 3, and 5 may be cured in a single cure cycle. Panels 2, 4, and 6 may be cured in a single cure cycle separate from panels 1, 3, and 5. The term "cure cycle" means a single run through the autoclave or oven, with same processing parameters. The specimen selection methodology in Figure 1 will be presented in Number of Batches x Number of Cure Process x Number of Specimens format throughout this document. Specifically, Figure 1 depicts a 3x2x3 specimen selection methodology. If more than 2 panels are required to obtain the minimum specimens, the additional panel(s) shall be labeled accordingly (see section 3) and approximately equal number of specimens should be tested from each panel. TRACEABILITY PER ENVIRONM ENTAL CONDITION AND TEST M ETHOD Material Batch BATCH 1 BATCH 2 BATCH 3 Panel Manufacturing & Independent Cure Process PANEL 1 PANEL 2 PANEL 3 PANEL 4 PANEL 5 PANEL 6 Number of Specimens Required per Test Method & Environment 3 spec. 3 spec. 3 spec. 3 spec. 3 spec. 3 spec. 18 SPECIM ENS TOTAL Figure 1 Specimen Selection Methodology All panels will be fabricated in accordance with NCAMP Process Specification NPS Fabrication of NMS 128 Qualification, Equivalency, and Acceptance Test Panels. In the tables which follow, the number of plies is chosen to produce a laminate thickness appropriate for the test method in question. This is also called out in Appendices 1 and 2. The panel dimensions listed in Appendix 2 are minima and refer to the size of the caul sheets. Larger panels may be manufactured. In order to facilitate individual specimen traceability, individual specimen numbering and/or skewed lines must be written or drawn across each sub-panel as shown in Figure 2. Page 13 of 41

14 Figure 2 Specimen Traceability Line Page 14 of 41

15 6.4 Lamina Level Tests Table 3 summarizes the lamina level testing to be performed. Table 3 Lamina Level Tests Layup Test Type and Direction Property [0] 6 ASTM D Tension ASTM D [0] 14 Compression (Note 1) ASTM D [90] 11 Tension ASTM D [90] 14 Compression (Note 1) ASTM D [0/90] 2S Tension (see Note 2) ASTM D [90/0/90] 5 Compression (see Note 1 & 2) ASTM D3518 In-Plane [45/-45] 3S Shear ASTM D2344 Short [0] 34 Strength, Modulus and Poisson s Ratio Number of Batches x No. of Panels x No. of Specimens Test Temperature/Moisture Condition CTD RTD ETW 3x2x3 3x2x3 3x2x3 Modulus 3x2x3 3x2x3 3x2x3 3x2x3 Strength and Modulus Strength and Modulus Strength and Modulus Strength and Modulus Strength and Modulus 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 3x2x3 Beam Note 1: Back-to-back strain gages are needed on the first two specimens of each environment. If no buckling is observed, the remaining modulus specimens will require a strain gage on one side of the specimens only. An appropriate extensometer may be used in place of strain gage. u Note 2: Derive the 0 lamina tensile or compressive strength F 0 o plies as follows u F 0 o = plies BF P f wh BF = [ ] ( ) 2 E1 V 0 E 2 + (1 V 0) E1 n 12 E 2 2 [ V0E + ( 1 1 V 0) E 2][ V 0 E 2 + (1 V 0) E1] ( n 12 E 2) Page 15 of 41

16 Where BF = Back-out factor obtained using linear classical lamination theory P f = Peak load carried by the test specimen (usually at failure) w = specimen gage width, mm [in.] h = specimen gage thickness, mm [in.] V0 = fraction of 0 plies in the cross-ply laminate (1/2 for [0/90]ns and 1/3 for [90/0/90]n) E1 = axial tensile or compressive stiffness of 0 plies, from an average of all batches E2 = transverse tensile or compressive stiffness of 0 plies, from an average of all batches n12 = major Poisson s ratio of 0 plies, from an average of all batches 6.5 Laminate Level Tests (Design Guidance Properties) Table 4 summarizes the laminate level tests to be carried out. The layup angles 0º, 45º, -45º, and 90º refer to the orientation of the fiber direction. The laminate stacking sequences in this program are not specific to any design. Therefore, car consideration should be given to the validity of properties derived from this program based on the design specific laminates in a structure to be certified. Table 4 emphasizes those properties and test condition combinations believed to constitute the worst case, which in general is cold dry for tension and hot wet for compression and other matrix dominated properties. For the single shear bearing tests, the ASTM D5961 will be used with one of the pairs of specimens replaced by a steel fixture. The modified configuration is shown in Figure 3. Specimen Clip extensometer here Extensometer shim same thickness as specimen Shim of similar stiffness and equal thickness to specimen. One shim per panel. Shim is held in place with grip pressure only Figure 3. Modified ASTM D5961 Single Shear Bearing Page 16 of 41

17 Table 4 Laminate Level Tests (%0º/%±45º/%90º) Actual Test Type Test Type and Layup (5) Property (25/50/25 - QI) UNT1 (10/80/10) UNT2 (50/40/10) UNT3 (25/50/25 - QI) UNC1 (10/80/10) UNC2 (50/40/10) UNC3 (25/50/25 - QI) SBS1 (25/50/25 - QI) OHT1 (10/80/10) OHT2 (50/40/10) OHT3 (25/50/25 - QI) FHT1 (10/80/10) FHT2 (50/40/10) FHT3 (25/50/25 - QI) OHC1 (10/80/10) OHC2 (50/40/10) OHC3 (25/50/25 - QI) FHC1 (10/80/10) FHC2 (50/40/10) FHC3 (25/50/25 - QI) SSB1 (10/80/10) SSB2 (50/40/10) SSB3 (100/0/0) ILT (25/50/25 - QI) CAI1 ASTM D3039 Un-notched Tension [45/0/-45/90]2S ASTM D3039 Un-notched Tension [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D3039 Un-notched Tension [0/45/0/90/0/-45/0/45/0/-45]S ASTM D6641 Un-notched Compression (4) [45/0/-45/90]2S ASTM D6641 Un-notched Compression (4) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D6641 Un-notched Compression (4) [45/0/90/0/-45/0/45/0/-45/0]S ASTM D2344 Short Beam (specimens may be taken from panels designed for (25/50/25 - QI) CAI1) ASTM D5766 Open Hole Tension (1) [45/0/-45/90]2S ASTM D5766 Open Hole Tension (1) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D5766 Open Hole Tension (1) [0/45/0/90/0/-45/0/45/0/-45]S ASTM D6742 Filled Hole Tension (2) [45/0/-45/90]2S ASTM D6742 Filled Hole Tension (2) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D6742 Filled Hole Tension (2) [0/45/0/90/0/-45/0/45/0/-45]S ASTM D6484 Open Hole Compression (1)(4) [45/0/-45/90]3S ASTM D6484 Open Hole Compression (1)(4) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D6484 Open Hole Compression (1)(4) [0/45/0/90/0/-45/0/45/0/-45]S ASTM D6484 Filled Hole Compression (2) [45/0/-45/90]3S ASTM D6484 Filled Hole Compression (2) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D6484 Filled Hole Compression (2) [0/45/0/90/0/-45/0/45/0/-45]S ASTM D5961 Single Shear Bearing (3) (6) [45/0/-45/90]2S ASTM D5961 Single Shear Bearing (3) (6) [45/-45/0/45/-45/90/45/-45/45/-45]S ASTM D5961 Single Shear Bearing (3) (6) [0/45/0/90/0/-45/0/45/0/-45]S ASTM D6415 Interlaminar Tension [0]22 ASTM D7136 & D7137 Compression After Impact (1500 in.lb/in) (4) [45/0/-45/90]3S (1) Open-hole configuration: 0.25 hole diameter, 1.5 inch width. Strength & modulus Strength & modulus Strength & modulus Strength & modulus Strength & modulus Strength & modulus Number of Batches x Number of Panels x Number of Test Specimens Test Temperature/Moisture Condition CTD RTD ETW 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength 3x2x3 3x2x3 Strength & Deformation Strength & Deformation Strength & Deformation 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 3x2x3 Strength 1x1x6 1x1x6 1x1x6 Strength 1x1x6 Page 17 of 41

18 (2) Filled-hole test configuration: 0.25 diameter, see section 2 for fastener callout, 1.5 width. (3) Single shear bearing test configuration: 0.25: hol er, 1.5 width, see section 2 for fastener callout, e/d=3 (4) Back-to-back strain gages needed on the first two specimens of each environment. If no buckling is observed, the remaining modulus specimens will require strain gage on one side of the specimens only. Appropriate extensometer may be used in place of the strain gage. (5) Loading direction is generally along the 0-degree direction (6) Use modified ASTM D5961 per Figure Fluid Sensitivity Screening Table 5 lists the requirements for fluid sensitivity screening, which requires ASTM D2344 Short Beam Strength testing on [0 ] 34 lamina level specimens dried at 160 F±5 F for 120 to 130 hours before being subjected to the conditions indicated, five replicates per fluid and one cure cycle. Specimens should be cleaned with a dry towel prior to the tests. In addition to short beam strength, load versus displacement curves shall be plotted to aid in the identification of matrix/resin softening. Since load versus displacement curves are influenced by test machine and fixture compliance, all the tests should be performed with the identical machine and fixture, preferably through a single setup. It is intended that the fluid resistance testing be performed on a limited number of reinforcement types and that engineering judgment be used to determine the necessity of repetition for other reinforcement configurations. Experience suggests that for the vast majority of epoxy resins, water is the fluid with the most deleterious effect on properties. Should screening tests for fluid sensitivity indicate this to be the case, further testing of this type would be unnecessary since exposure to water moisture to equilibrium level is an inherent part of the multi batch allowables test program. Page 18 of 41

19 Table 5 Fluid Sensitivity Screening Extended Contact: Exposure Test Condition Code 100 Low Lead Aviation Fuel 90 days 70 F±10 F 70 F FS11RT (ASTM D910) 90 days 70 F±10 F 250 F* FS11ET SAE AMS 2629 Jet Reference Fluid 90 days 70 F±10 F 70 F FS12RT 90 days 70 F±10 F 250 F* FS12ET MIL-PRF-5606 Hydraulic Oil 90 days 70 F±10 F 70 F FS13RT 90 days 70 F±10 F 250 F* FS13ET MIL-PRF Hydraulic Oil 90 days 70 F±10 F 70 F FS14RT 90 days 70 F±10 F 250 F* FS14ET MIL-PRF-7808 Engine Oil 90 days 70 F±10 F 70 F FS15RT 90 days 70 F±10 F 250 F* FS15ET MIL-PRF-23699, Class STD Engine 90 days 70 F±10 F 70 F FS16RT Oil 90 days 70 F±10 F 250 F* FS16ET Salt Water (ASTM D1141 or equiv.) 90 days 70 F±10 F 70 F FS17RT 90 days 70 F±10 F 250 F* FS17ET Skydrol LD-4 (SAE AS1241, Type 90 days 70 F±10 F 70 F FS18RT IV, Class 1) 90 days 70 F±10 F 250 F* FS18ET 50% Water with 50% Skydrol LD-4 90 days 70 F±10 F 70 F FS19RT (SAE AS1241, Type IV, Class 1) 90 days 70 F±10 F 250 F* FS19ET Short Duration Contact: MEK washing fluid. ASTM D minutes 70 F±10 F 70 F FS21RT 90 minutes 70 F±10 F 250 F* FS21ET Polypropylene Glycol Deicer (Type 90 minutes 70 F±10 F 70 F FS22RT I) Mil-A minutes 70 F±10 F 250 F* FS22ET Isopropyl Alcohol Deicing Agent 48±4 F±10 F 70 F FS23RT (TT-I-735) 48±4 F±10 F 250 F* FS23ET Control Tests: Distilled Water Dry 85% Relative Humidity 90 days min. at 70 F±10 F 70 F FS31RT 90 days min. at 70 F±10 F 250 F* FS31ET Dry per section F FS32RT Dry per section F* FS32ET Per section F FS33RT Per section F* FS33ET * Elevated temperature level of 250±5 F must be reduced if wet glass transition temperature is not 300 F or higher. The elevated temperature level will be adjusted to 50 F below the measured wet glass transition temperature. Page 19 of 41

20 6.7 Freezer Storage Life and Out-Time Verification In order to verify freezer and out-time characteristics of 8552, Hexcel will perform the following tests in Table 6a after the freezer and out time accumulations shown in Table 6b. Only one batch of prepreg will be tested. The out time and freezer storage specified in Table 6b are reference only; actual out time and freezer storage will be documented in the final test report. Table 6a Property Tests to Verify Prepreg Out Time and Freezer Storage Life Property Method/Condition # Replicates per condition Short Beam Strength (Note 3) ASTM D , RTD 5 Gel Time ASTM D Tack See section 7.1 or use material supplier recommended method 3 Drape See section 7.2 or use material supplier recommended method 3 Flow ASTM D HPLC (Note 2) SACMA SRM 20R-94 2 Chemical Reactivity and degree of advancement by DSC (Note 1 & 2) SACMA SRM 25R-94 2 Photomicrography and void Reference MIL-HDBK-17-1F content determination section As needed Note 1: If possible, perform TGA on the specimens after DSC to determine the actual specimen resin content so that the heat of reaction can be normalized according to resin content. If TGA is not available, normalize the heat of reaction according to the resin content as determined from Table 1. Report the onset temperature, peak temperature and total heat of reaction. Note 2: Graphical results should be sent to NCAMP for inclusion in the test report. HPLC Peak Ratio s should be defined and any changes due to out-time and freezer storage should be reported by Hexcel. Note 3: Stop counting out-time when the cure cycle begins. Page 20 of 41

21 Table 6b Verification of Out Time and Freezer Storage Life Characteristics Out Time at 70 ± 10 F and 0-60% RH Freezer Storage Time <10 F < 1 day 5 days 7 days 10 days 12 days 15 days 21 days* As manufactured Code 0/1 0/5 0/7 0/10 0/12 0/15 0/21 3 months freezer Code 3/1 3/7 3/12 6 months freezer Code 6/1 6/7 6/12 6/21 9 months freezer Code 9/1 9/7 9/12 12 months freezer 12/1 12/5 12/7 12/10 12/12 12/15 12/21 Code * Additional tests at three day intervals to determine limit of out life, up to 45 days. [testing for freezer storage may be increased also] Page 21 of 41

22 7. Other Test Procedures 7.1 Tack Test (Ref. Cessna Aircraft Company Specification CPTI003): The purpose of this test method is to determine the level of prepreg tack through its ability to adhere to itself and to a vertical surface. Equipments needed are (1) A corrosion resistant steel plate with a commercial 2D finish and (2) A squeegee or 1-inch diameter by 1-inch wide roller. Procedure: 1. This tack test shall be performed at 70 F±10 F and 0-60% RH. Cut two 3-inch by 1-inch specimens from the prepreg. The 3-inch dimension shall be in the 0º or warp direction. 2. Attach one piece of the prepreg specimen to the plate with light pressure using a squeegee or roller. 3. Remove the backing and apply the next strip to the first one. Tack in a similar manner. Remove the backing from the second strip. 4. Position the plate vertically. 5. Determine the tack level as follows: a. Tack level I Low tack, prepreg is stiff and boardy b. Tack level II Dry but slight drape c. Tack level III - Slight tack sticks to itself but not to a vertical surface. Unable to adhere to the vertical tool surface for 30 minutes. d. Tack level IV - Good tack, prepreg sticks to itself and vertical tool. Adhered to the vertical tool surface for more than 30 minutes. e. Tack level V Sticks to hands or gloves but no resin transfer. f. Tack level VI High tack, wet, and sloppy with resin transfer. 7.2 Drape Test The drape of the prepreg shall be determined at 70 F±10 F and 0-60% RH as follows: 1. Cut sufficient material to obtain three specimens that are a minimum of 2-inches long by a minimum of 3-inches wide, and remove any release paper or film. 2. Complete wrapping each specimen separately over a 0.25 inch diameter mandrel within 15 seconds of initiation, with fiber direction transverse to mandrel centerline. 3. Remove each specimen from the mandrel and inspect for evidence of cracks, wrinkles, folds, or tears on the surface of the material. Evidence of these defects in cut edges extending less than 0.13 inch inward maximum from the edge shall not be considered rejectable. If no evidence of filament breakage can be visually observed, the specimen has met the requirements for drape. Report as pass or fail. 8. Nominal Cured Ply Thickness and Normalization The final nominal cured ply thicknesses for each mater l form will be computed from the average test laminate thickness. Most lamina level tension and compression strength and modulus properties, and all laminate level properties will be normalized according to fiber volume fraction. Lamina level properties that will not be normalized include 90º tensile Page 22 of 41

23 strength and modulus (unidirectional only), 90º compressive strength and modulus (unidirectional only), in-plane shear strength and modulus, Poisson s ratio, SBS, and ILT. After normalizing, data scatter should reduce or remain the same. If data scatter increases significantly after normalizing, the reason should be investigated. Wherever properties are normalized, both measured and normalized data will be reported. For unidirectional materials the fiber areal weight cannot be measured in advance of impregnation, hence Method I of ASTM D3171, utilizing acid digestion, will be used to verify the CPT method in accordance with note (2) of Tab 2. Normalized Value = Measured Value x Nominal V%F / Measured V%F In cases where the fabric areal weight can be shown to be very close to nominal, normalization by cured ply thickness (CPT) may be used, i.e.: Normalized Value = Measured Value x Measured CPT / Nominal CPT 9. Inspection, Conformance, Witnessing, and Shipping The 3-batch qualification panels shall be fabricated according to the process definition in section 6.3. At minimum, the following panel information should be conformed by the FAA: 1. Process control data such as temperature, pressure, and vacuum as required by section Panel identification and labeling per section 3, section 6.3, and appendix 2. Stacking sequence may not be verified on cured panel level unless staggered tabs were cut into the prepregs prior to layup. The above FAA conformity will be performed at the panel fabricator site before the panels are sent to NCAMP. The panel conformity must be performed by FAA MIDO (Manufacturing Inspection District Office) inspectors at the request of FAA ACO (Aircraft Certification Office) engineers. The MIDO inspector may elect to delegate this responsibility to a Designated Manufacturing Inspection Representative (DMIR) or Designated Airworthiness Representative (DAR). Prior to shipping the panels, verify the following: 1. The appropriate sections in the Panel Data sheet of PMC_Data_Collection_Template.xls file has been completed. 2. In-process monitoring data such as part temperature, autoclave temperature, autoclave pressure, autoclave vacuum, and part vacuum readings, preferably in electronic format, is included 3. FAA conformity record (if needed), is included. 4. The panel names match the names listed in Appendix 2 of the test plan Send the panels along with the in-process monitoring data and FAA conformity records to: Wichita State University NIAR NCAMP, Attn: Yeow Ng 1845 Fairmount Ave. Page 23 of 41

24 Wichita, KS USA Tel: Prior to testing, test specimen conformity must be performed by MIDO inspectors at the request of ACO engineers. The MIDO inspector may elect to delegate this responsibility to a DMIR or DAR. Testing must be witnessed by the FAA (except for those in sections 4 and 6.7). Witnessing can be performed by ACO engineers, or they may delegate this responsibility to a DER, MIDO inspector, DMIR or DAR. Mechanical testing will be carried out at the National Institute for Aviation Research, Wichita State University. The test setup and procedures in sections 4 and 6.7 will be reviewed by NCAMP IAB and NCAMP staff during facility audit. 10. Data Reduction and Reporting All data necessary for full traceability, such as fiber and fabric certifications, prepreg analysis (Table 1), section 6.7, and appropriate information in appendices 3 and 4 will be provided by Hexcel to NCAMP for inclusion in the final report. The mechanical property data (Tables 3 and 4) will be reduced according to the methodology of reference 2, modified in accordance with the latest CMH-17 recommendations. Specifically, the ASAP computer program will be used to generate basis values. Since this procedure involves combining data across both batches and test environments, subject to passing statistical checks of the validity of this process, it is possible that certain data may not pass such tests. In such cases the methodology of CMH-17 will be used as embodied in the Stat17 software. If batch poolability cannot be demonstrated, data from at least two more material batches will be generated to allow the use of ANOVA method to generate basis values. If deemed appropriate, the single batch equivalency data may be pooled into the three batch qualification data to generate material properties that are more representative of the overall material performance. The final test report including the data reduction spreadsheets for each specimen (in Microsoft Excel or compatible format) will be available to all NCAMP members as soon as the test report is approved by the FAA and DoD, subject to export control regulations. 11. Specifications All materials will be manufactured to Hexcel prepreg Process Control Document PCD- NMS128 latest revision using the nominal parameters given in section 1 above, and in accordance with NMS 128/2. All critical process parameters must be specified, and the prepreg PCD must be under revision control. After the completion of this program, the prepreg PCD must be finalized and signed by NCAMP before the NCAMP prepreg specification is released. Page 24 of 41

25 The prepreg PCD will be prepared by Hexcel in accordance with NRP 101 Prepreg Process Control Document (PCD) Preparation Guide before the production of the three batch material qualification prepregs. In general, only NCAMP IAB members who are interested in the materials (generally, those who are fabricating test panels and their customers) will be invited to the PCD review and approval process. A proper non-disclosure agreement, if needed, will be prepared and signed by Hexcel and the members prior to such review. Hexcel will notify the members about the review period and allow adequate time for such prepreg PCD review. The NCAMP prepreg material specification NMS 128/2 will be released at the conclusion of this program in accordance with DOT/FAA/AR-02/109. The specification limits will be derived from the data generated in this test plan using the methodology of reference 2. For a temporary period of time, before sufficient number of batches are produced and tested following the material qualification program, higher than measured Coefficient of Variation (CV) will be assumed in the calculation of basis values and specification limits. The following formula will be used: 1) If the measured CV at a given test condition is 0% to CV of 6% or the pooled CV, whichever is greater. 2) If the measured CV at a given test condition is between 4% and 8%, use an assumed CV = 0.5*(measured individual CV) + 4% or the pooled CV, whichever is greater. 3) If the measured CV at a given test condition is 8% to 10%, use the measured CV or the pooled CV, whichever is greater. 4) If the measured CV at a given test condition is 10% or greater, question the data. And for setting specification requirement use a maximum CV of 10%. When a sufficient number of production batches have been produced and tested (approximately 8 to 15 batches), the basis values and specification limits may be adjusted higher. 12. References Reference 1. DOT/FAA/AR-02/109 Recommended criteria and Guidelines for the Development of a Material Specification for Carbon/Epoxy Prepregs to be used on FAA Certified Structures. Reference 2. DOT/FAA/AR-03/19 Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. Reference 3. MIL-HDBK-17 Rev. F, Composite Materials Handbook Reference 4. DOT/FAA/AR-02/110 Recommendations and Guidelines for the Development of a Process Specification for the Fabrication of Carbon Fiber Reinforced Epoxy Composite Structures. Page 25 of 41

26 13. Revisions Revision Date Description - 2/5/2007 Initial Release A 2/9/2007 Added the following to section 1.: The test panels are fabricated per NCAMP process specification NPS using baseline M cure cycle. B 6/7/2007 Added panel shipping information to section 9. In many sections, updated reference to ASTM revisions. In section 6, elevated temperature level will be adjusted to 50 F below the measured wet glass transition temperature (Tg) if the wet Tg is below 300 F. Page 26 of 41

27 Appendix 1 Hexcel 8552 IM7 unidirectional prepreg Qualification Tests 190 gsm Unidirectional Property Longitudinal Tensile Properties Strength & Modulus & Poisson's ratio (extensometer OR one CEA UT-350 OR two CEA-XX-250UW-350) ASTM D 3039 Prepreg Batch Orientation Cond. A B C Cure Cycle M1 M2 M1 M2 M1 M2 (100/0/0) CTD [0]6 RTD x (0 ) in. (tabs required) ETW Longitudinal Compression Prope rties (100/0/0) CTD Modulus (extensometer OR CEA-XX-125UT-350) [0]14 RTD ASTM D x 5.50 (0 ) in. ETW Transverse Tensile Properties (0/0/100) CTD Strength & Modulus (extensometer OR CEA-XX-250UW-350) [90]11 RTD ASTM D x (90 ) in. (tabs optional) ETW Transverse Compression Properties (0/0/100) CTD Strength & Modulus (extensometer OR CEA-XX-125UT-350) [90]14 RTD ASTM D x 5.50 (90 ) in. ETW Unnotched Tensile Properties 0 (50/0/50) CTD Page 27 of 41