qualification test plan for 5215 t40-800 unitape · · 2009-02-06clc combined loading compression...

October 29, 2008 NTP 3668Q1 Rev A

Material Supplier Contact:Bob Geyer Designated Technical Service Engineer for NCAMP

Material Supplier Contact: Wei Kwan Cytec Cycom 5215 Specialist Cytec Engineered Materials

office: 636-821-3020 Cytec Engineered Materials mobile: 314-393-7111 Tel: (714) 666-4393 Email: [email protected]

Document No.: NTP 3668Q1

Material Property Data Acquisition and Qualification Test Plan For

Cytec Cycom 5215 T40-800 Unitape Gr 145 RC 33%

FAA Special Project Number SP4612WI-Q

Prepared by: Yeow Ng, John Tomblin, Ric Abbott Reviewed by: John Adelmann, Kit Bowman, Bret Brummer (Hawker Beechcraft Corp), Allison Crockett (General Atomics), Susan Daggett (ATK), Jim Diepenbrock, Rich Fields, Warren Hatfield (Hawker Beechcraft Corp), Jeff Hendrix, Ed Hooper, Kim Gingras (Cytec), Robert Glenn (Gulfstream), Dana Granville (U.S. Army), Erkan Kececi (Cessna), Jim Krone (Cessna), Wei Kwan (Cytec), Guillermo Mayorga, William McCarvill (Commercial Chemistries), Jessie MacLeod (Cytec), 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 Composite), Kristin Strole (NCAMP), Melanie Violette (Hawker Beechcraft Corp), Stephen Ward (SW Composites), Bill Webb (Cytec), Cytec Engineered Materials, Hexcel Corporation, Spirit AeroSystems. Approved by:

Email: [email protected]

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TABLE OF CONTENTS 1. INTRODUCTION ............................................................................................................................................... 5

66

7

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11

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12131316171920

22

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25

26

27

33

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1.1 USE OF FIBER FROM MULTIPLE FIBER MANUFACTURING LINES, PRODUCED BY THE SAME VENDOR WITH THE SAME FIBER TRADE NAME .................................................................................................................................. 1.2 14CFR REGULATIONS ...............................................................................................................................

2. TEST METHODS .............................................................................................................................................. 3. PANEL AND SPECIMEN IDENTIFICATION................................................................................................ 4. UNCURED PREPREG AND RESIN TESTING............................................................................................ 5. CURED LAMINATE PHYSICAL TESTING ................................................................................................ 6. CURED LAMINA AND LAMINATE MECHANICAL PROPERTY TESTING ........................................

6.1 ENVIRONMENTAL CONDITIONING ............................................................................................................. 6.2 NON-AMBIENT TESTING............................................................................................................................ 6.3 PROCESS DEFINITION .............................................................................................................................. 6.4 LAMINA LEVEL TESTS ............................................................................................................................... 6.5 LAMINATE LEVEL TESTS (DESIGN GUIDANCE PROPERTIES) .................................................................. 6.6 FLUID SENSITIVITY SCREENING ............................................................................................................... 6.7 FREEZER STORAGE LIFE AND OUT-TIME VERIFICATION .........................................................................

7. OTHER TEST PROCEDURES ..................................................................................................................... 7.1 TACK TEST (REF. CESSNA AIRCRAFT COMPANY SPECIFICATION CPTI003): ....................................... 7.2 DRAPE TEST .............................................................................................................................................

8. NOMINAL CURED PLY THICKNESS AND NORMALIZATION............................................................. 9. INSPECTION, CONFORMANCE, WITNESSING, AND SHIPPING ....................................................... 10. DATA REDUCTION AND REPORTING................................................................................................. 11. SPECIFICATIONS ..................................................................................................................................... 12. REFERENCES............................................................................................................................................ 13. REVISIONS ................................................................................................................................................. APPENDIX 1 ............................................................................................................................................................. APPENDIX 2 ............................................................................................................................................................. APPENDIX 3 .............................................................................................................................................................

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

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TGA Thermogravimetric Analyzer WSU Wichita State University

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1. Introduction

This document is a qualification test plan for Cytec 5215 T40-800 unidirectional prepreg, procured to NCAMP material specification NMS 323/1. The test panels are fabricated per NCAMP process specification NPS 81323. 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 recommendations 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 Cytec Engineered Materials, 1440 N. Kraemer Blvd, Anaheim, CA 92806. The three batches of material are designed to fulfill base material qualification requirements. The following product forms will be characterized:

Prepreg Name Description About the Prepreg

Cytec 5215 T40-800 unidirectional prepreg

Resin name: Cytec 5215, Reinforcement: 12K T40-800, unidirectional prepreg, Sizing: 0.2% AP200, Fiber Areal Weight: 145 gsm, Resin Content: 33%

The following material code will be used throughout this document to reference the prepreg:

Material Code Prepreg Name C11 Cytec 5215 T40-800 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 1 2 3 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. Should additional batches of prepreg beyond the first 5 batches be used for data generation,

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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 statistically 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.

1.2 14CFR Regulations

Test results will be analyzed to produce allowables that can be employed by a qualified organization to show compliance with 14CFR 23.613, 25.613, 27.613 or 29.613.

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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 D6415-06ae1 – 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 as mandatory. Any deviations from the standards must be approved by the FAA and documented in the final test report. 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 -0.000 +0.003 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,

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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, NTP3668Q1-CYT-C11-CES-LT-A-C1-2-TT-RTD-3] denotes Prepregger: Cytec, Prepreg Name: Cytec 5215 T40-800 unidirectional prepreg, Fabricator: Cessna, Intended Test Type: Longitudinal Tension, Prepreg Batch: A, Cure Cycle: C1, 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:

Prepregger ID

Cytec: CYT

Material Code Prepreg Name C11 Cytec T40-800 unidirectional prepreg

Fabricator ID (Company that layup, bag, and cure the test panels) Cessna: CES

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

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(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: C1, C2, C3, etc.: Cure Cycle 1, 2, 3, etc. Note: Cure Cycle ID 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: CTD, RTD, ETD, ETW (cold temp. dry moisture, room temp. dry moisture,

etc., see section 6, if testing at more than one elevated temperature use ETD1, ETD2 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) Specimen Number: 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 Cytec. 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 D792-00 6 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)

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Flow ASTM D3531-99(2004) 6 (Note 3) Gel Time ASTM D3532-99(2004) 6 HPLC (Note 4) SACMA SRM 20R-94 3 FTIR (Note 4) ASTM E168-06, ASTM

E1252-98(2002) 3

Chemical reactivity and degree of advancement by DSC (Note 2 & 4)

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 is not available, 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.

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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 D3171-06 All data from

mechanical test specimens

Laminate Density ASTM D792-00 3 Fiber Volume, % by Volume ASTM D3171-06(Note 2) 3 Resin Content, % by Weight ASTM D3171-06(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)

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.

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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 ETD = 180±5°F, dry ETW = 180±5°F, wet (equilibrium moisture content) 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 specimens are tested within 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. 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 0.02% for two consecutive determinations which are 7 ±0.5 days apart and may be expressed by:

0002.01 <− −

b

ii

WWW

where: Wi = weight at current time Wi – 1 = weight at previous time Wb = baseline weight prior to conditioning

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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 15 grams may be used to establish weight gain measurements. If the specimens or traveler coupons pass the criteria for two consecutive determinations 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 start minutes after the specimen has reached the test temperature. During the test, the temperature, as measured on the specimen, shall be within ±5°F of the required test temperature.

105 +−

For wet specimens, the moisture loss shall be determined by subjecting representative specimens to the same amount of time required to heat-up and fail the specimens. For filled-hole or bearing specimens, remove the fasteners prior to conducting moisture loss measurements. For tabbed specimens, representative coupons without tabs and having the same number of plies should be used to conduct the moisture loss measurements. A minimum of one specimen or representative coupon shall be used to measure the moisture loss for every combination of test temperature and stacking sequence.

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 gage section. The test should start minutes after the specimen has reached the test temperature. During the test, the temperature, as measured on the specimen, shall be within ±5°F of the required test temperature.

1 0 5 +

−

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

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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.

PER ENVIRONMENTAL CONDITION AND TEST METHOD

MaterialBatch

PanelManufacturing& IndependentCure Process

Number ofSpecimens

Required perTest Method &Environment

BATCH 2

PANEL 4

3 spec.

PANEL 3

3 spec.

BATCH 3

PANEL 6

3 spec.

PANEL 5

3 spec.

BATCH 1

PANEL 2

3 spec.

PANEL 1

3 spec.

18 SPECIMENS TOTAL

Figure 1 Specimen Selection Methodology

All panels will be fabricated in accordance with NCAMP process specification NPS 81323. 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.

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Figure 2 – Specimen Traceability Line

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6.4 Lamina Level Tests

Table 3 summarizes the lamina level testing to be performed.

Table 3 Lamina Level Tests

Number of Batches x No. of Panels x No. of Specimens Test Temperature/Moisture

Condition Layup Test Type and Direction Property

CTD RTD ETD ETW

[0]8 ASTM D3039 0° Tension

Strength, Modulus and Poisson’s Ratio

3x2x3 3x2x3 3x2x3

[0]20 ASTM D6641 0° Compression (Note 1) Modulus 3x2x3 3x2x3 3x2x3 3x2x3

[90]16 ASTM D3039 90° Tension

Strength and Modulus 3x2x3 3x2x3 3x2x3

[90]20 ASTM D6641 90° Compression (Note 1)


[0/90]3S ASTM D3039 0° Tension (see Note 2)


[90/0/90]7 ASTM D6641 0° Compression (see Note 1 & 2)

Strength and Modulus 3x2x3 3x2x3 3x2x3 3x2x3

[45/-45]4S ASTM D3518 In-Plane Shear


[0]45 ASTM D2344 Short Beam Strength 3x2x3 3x2x3 3x2x3 3x2x3

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 the strain gage. Note 2: Derive the 0° lamina tensile or compressive strength as follows F0

uplieso

wh

PBF

f

uplies =F0o

[ ] ( )

( )[ ] [ ] ( )EEVEVEVEV

EEVEVEBF

2122

1020200 1

2122

10201

)1(1

)1(

ν

ν

−−+−+

−−+=

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Where BF = Back-out factor obtained using linear classical lamination theory Pf = 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

ν12 = 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, careful 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.

Extensometer shim same thickness as specimenSpecimen

Shim of similar stiffness and equal thickness to specimen. One shim per panel. Shim is held in place with grip pressure o ly n

Clip extensometer here

Figure 3. Modified ASTM D5961 Single Shear Bearing

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Table 4 Laminate Level Tests

Number of Batches x Number of Panels x Number of Test

Specimens Test Temperature/Moisture

Condition

(%0º/%±45º/%90º) Actual Test Type

Test Type and Layup (5) Property

CTD RTD ETW (25/50/25 - QI) UNT1

ASTM D3039 Un-notched Tension [45/0/-45/90]2S

Strength & modulus 3x2x3 3x2x3 3x2x3

(10/80/10) UNT2

ASTM D3039 Un-notched Tension [45/-45/0/45/-45/90/45/-45/45/-45]S


(50/40/10) UNT3

ASTM D3039 Un-notched Tension [0/45/0/90/0/-45/0/45/0/-45]S


(25/50/25 - QI) UNC1

ASTM D6641 Un-notched Compression (4) [45/0/-45/90]3S

Strength & modulus 3x2x3 3x2x3

(10/80/10) UNC2

ASTM D6641 Un-notched Compression (4) [45/-45/0/45/-45/90/45/-45/45/-45]S


(50/40/10) UNC3

ASTM D6641 Un-notched Compression (4) [45/0/90/0/-45/0/45/0/-45/0]S


(25/50/25 - QI) SBS1

ASTM D2344 Short Beam (specimens may be taken from panels designed for (25/50/25 - QI) CAI1)

Strength 3x2x3 3x2x3

(25/50/25 - QI) OHT1

ASTM D5766 Open Hole Tension (1) [45/0/-45/90]2S Strength 3x2x3 3x2x3 3x2x3

(10/80/10) OHT2

ASTM D5766 Open Hole Tension (1) [45/-45/0/45/-45/90/45/-45/45/-45]S Strength 3x2x3 3x2x3 3x2x3

(50/40/10) OHT3

ASTM D5766 Open Hole Tension (1) [0/45/0/90/0/-45/0/45/0/-45]S Strength 3x2x3 3x2x3 3x2x3

(25/50/25 - QI) FHT1

ASTM D6742 Filled Hole Tension (2) [45/0/-45/90]2S Strength 3x2x3 3x2x3 3x2x3

(10/80/10) FHT2

ASTM D6742 Filled Hole Tension (2) [45/-45/0/45/-45/90/45/-45/45/-45]S Strength 3x2x3 3x2x3 3x2x3

(50/40/10) FHT3

ASTM D6742 Filled Hole Tension (2) [0/45/0/90/0/-45/0/45/0/-45]S Strength 3x2x3 3x2x3 3x2x3

(25/50/25 - QI) OHC1

ASTM D6484 Open Hole Compression (1)(4) [45/0/-45/90]4S Strength 3x2x3 3x2x3

(10/80/10) OHC2

ASTM D6484 Open Hole Compression (1)(4) [45/-45/0/45/-45/90/45/-45/45/-45]2S Strength 3x2x3 3x2x3

(50/40/10) OHC3

ASTM D6484 Open Hole Compression (1)(4) [0/45/0/90/0/-45/0/45/0/-45]2S Strength 3x2x3 3x2x3

(25/50/25 - QI) FHC1

ASTM D6484 Filled Hole Compression (2) [45/0/-45/90]4S Strength 3x2x3 3x2x3

(10/80/10) FHC2

ASTM D6484 Filled Hole Compression (2) [45/-45/0/45/-45/90/45/-45/45/-45]2S Strength 3x2x3 3x2x3

(50/40/10) FHC3

ASTM D6484 Filled Hole Compression (2) [0/45/0/90/0/-45/0/45/0/-45]2S Strength 3x2x3 3x2x3

(25/50/25 - QI) SSB1

ASTM D5961 Single Shear Bearing (3) (6) [45/0/-45/90]2S

Strength & Deformation 3x2x3 3x2x3

(10/80/10) SSB2

ASTM D5961 Single Shear Bearing (3) (6) [45/-45/0/45/-45/90/45/-45/45/-45]S


(50/40/10) SSB3

ASTM D5961 Single Shear Bearing (3) (6) [0/45/0/90/0/-45/0/45/0/-45]S


(100/0/0) ILT

ASTM D6415 Interlaminar Tension [0]30 Strength 1x1x6 1x1x6 1x1x6

(25/50/25 - QI) CAI1

ASTM D7136 & D7137 Compression After Impact (1500 in.lb/in) (4) [45/0/-45/90]4S

Strength 1x1x6

(1) Open-hole configuration: 0.25” hole diameter, 1.5 inch width.

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(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: hole diameter, 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 3

6.6 Fluid Sensitivity Screening

Table 5 lists the requirements for fluid sensitivity screening, which requires ASTM D2344 Short Beam Strength testing on [0°]45 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.

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Table 5 Fluid Sensitivity Screening

Extended Contact: Exposure Test Condition Code

90 days min. @ 70°F±10°F 70°F FS11RT 100 Low Lead Aviation Fuel (ASTM D910) 90 days min. @ 70°F±10°F 180°F FS11ET

90 days min. @ 70°F±10°F 70°F FS12RT SAE AMS 2629 Jet Reference Fluid 90 days min. @ 70°F±10°F 180°F FS12ET 90 days min. @ 70°F±10°F 70°F FS13RT MIL-PRF-5606 Hydraulic Oil 90 days min. @ 70°F±10°F 180°F FS13ET 90 days min. @ 70°F±10°F 70°F FS14RT MIL-PRF-83282 Hydraulic Oil 90 days min. @ 70°F±10°F 180°F FS14ET 90 days min. @ 70°F±10°F 70°F FS15RT MIL-PRF-7808 Engine Oil 90 days min. @ 70°F±10°F 180°F FS15ET 90 days min. @ 70°F±10°F 70°F FS16RT MIL-PRF-23699, Class STD Engine

Oil 90 days min. @ 70°F±10°F 180°F FS16ET 90 days min. @ 70°F±10°F 70°F FS17RT Sea Water (ASTM D1141 or equiv.) 90 days min. @ 70°F±10°F 180°F FS17ET 90 days min. @ 70°F±10°F 70°F FS18RT Skydrol LD-4 (SAE AS1241, Type

IV, Class 1) 90 days min. @ 70°F±10°F 180°F FS18ET 90 days min. @ 70°F±10°F 70°F FS19RT 50% Water with 50% Skydrol LD-4

(SAE AS1241, Type IV, Class 1) 90 days min. @ 70°F±10°F 180°F FS19ET

Short Duration Contact: 90 minutes min. @ 70°F±10°F 70°F FS21RT MEK washing fluid. ASTM D740 90 minutes min. @ 70°F±10°F 180°F FS21ET 90 minutes min. @ 70°F±10°F 70°F FS22RT Polypropylene Glycol Deicer (Type

I) Mil-A-824 3 90 minutes min. @ 70°F±10°F 180°F FS22ET 48±4 hours @70°F±10°F 70°F FS23RT Isopropyl Alcohol Deicing Agent

(TT-I-735) 48±4 hours @70°F±10°F 180°F FS23ET Control Tests:

90 days min. at 70°F±10°F 70°F FS31RT Distilled Water 90 days min. at 70°F±10°F 180°F FS31ET Dry per section 6.1 70°F FS32RT Dry Dry per section 6.1 180°F FS32ET Per section 6.1 70°F FS33RT 85% Relative Humidity Per section 6.1 180°F FS33ET

6.7 Freezer Storage Life and Out-Time Verification

In order to verify freezer and out-time characteristics of 5215, Cytec 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.

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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 D2344-00(2006), RTD 5 Gel Time ASTM D3532-99(2004) 3

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 D3531-99(2004) 3 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 content determination

Reference MIL-HDBK-17-1F section 6.6.7.3 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 Cytec.

Note 3: Stop counting out-time when the cure cycle begins. 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


6/1

6/7 6/12

6/21 9 months freezer Code

9/1

9/7 9/12


12/1

12/5

12/7

12/10

12/12

12/15

12/21

* Additional tests at three day intervals to determine limit of out life, up to 45 days. [testing for freezer storage may be increased also]

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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 material 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

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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 Table 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

Material supplier shall perform all the batch release tests per NMS 323/1 prior to shipping the prepreg to the panel fabricator. The panel fabricator shall perform prepreg receiving inspection per NMS 323 paragraph 4.5.1. However, for the purpose of this program, the tests in paragraph 4.5.2 need not be repeated by the panel fabricator. 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

6.3. 2. 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

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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. Wichita, KS 67260-0093 USA Tel: 316-978-5212 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 Cytec 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 Cytec prepreg Process Control Document 21970132 latest revision using the nominal parameters given in section 1 above, and in accordance with

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NMS 323/1. 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. The prepreg PCD will be prepared by Cytec 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 Cytec and the members prior to such review. Cytec will notify the members about the review period and allow adequate time for such prepreg PCD review. The NCAMP prepreg material specification NMS 323/1 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 4%, use an assumed 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

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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.

13. Revisions

Revision Date Description - 5/22/2007 Initial Release A October 29, 2008 Revised sections 6.1 and 6.2.

Appendix 1

Cytec 5215 T40-800 Unidirectional Prepreg Qualification Tests

Prepreg Batch A B C 145 gsm Unidirectional

Cure Cycle Property

Orientation Cond.

C1 C2 C1 C2 C1 C2Longitudinal Tensile Properties (100/0/0) CTD 3 3 3 3 3 3

Strength & Modulus & Poisson's ratio (extensometer OR one CEA-00-125UT-350 OR two CEA-XX-250UW-350) [0]8 RTD 3 3 3 3 3 3

ASTM D 3039 ETD 0.50 x 10.00 (0°) in. (tabs required) ETW 3 3 3 3 3 3

Longitudinal Compression Properties (100/0/0) CTD 3 3 3 3 3 3

Modulus (extensometer OR CEA-XX-125UT-350) [0]20 RTD 3 3 3 3 3 3 ASTM D 6641 ETD 3 3 3 3 3 3

0.50 x 5.50 (0°) in. ETW 3 3 3 3 3 3

Transverse Tensile Properties (0/0/100) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR CEA-XX-250UW-350) [90]16 RTD 3 3 3 3 3 3

ASTM D 3039 ETD 1.00 x 10.00 (90°) in. (tabs optional) ETW 3 3 3 3 3 3

Transverse Compression Properties (0/0/100) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR CEA-XX-125UT-350) [90]20 RTD 3 3 3 3 3 3 ASTM D 6641 ETD

0.50 x 5.50 (90°) in. ETW 3 3 3 3 3 3

Unnotched Tensile Properties 0 (50/0/50) CTD 3 3 3 3 3 3 Strength & Modulus (extensometer OR CEA-XX-250UW-350) [0/90]3S RTD 3 3 3 3 3 3

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Unnotched Compression Properties 0 (33/0/67) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR CEA-XX-125UT-350) [90/ 0/90]7 RTD 3 3 3 3 3 3 ASTM D 6641 ETD 3 3 3 3 3 3

0.50 x 5.50 (0°) in. ETW 3 3 3 3 3 3 In-Plane Shear Properties (0/100/0) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR one CEA-00-125UT-350 OR two CEA-XX-250UW-350) [45/-45]4S RTD 3 3 3 3 3 3


Short Beam Strength Properties (100/0/0) CTD 3 3 3 3 3 3

Strength [ 0]45 RTD 3 3 3 3 3 3 ASTM D 2344 ETD 3 3 3 3 3 3

0.50 x 1.50 (0°) in. ETW 3 3 3 3 3 3

Unnotched Tensile Properties 1 ( 25/50/25 - QI) CTD 3 3 3 3 3 3 Strength & Modulus (extensometer OR CEA-XX-250UW-350) [45/0/-45/90]2S RTD 3 3 3 3 3 3


Unnotched Tensile Properties 2 (10/80/10) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR CEA-XX-250UW-350) [45/-45/0/45/-45/90/45/-45/45/-45]S RTD 3 3 3 3 3 3 ASTM D 3039 ETD

1.00 x 10.00 (0°) in. (tabs optional) ETW 3 3 3 3 3 3 Unnotched Tensile Properties 3 (50/40/10) CTD 3 3 3 3 3 3

Strength & Modulus (extensometer OR CEA-XX-250UW-350) [0/45/0/90/0/-45/0/45/0/-45]S RTD 3 3 3 3 3 3 ASTM D 3039 ETD

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1.00 x 10.00 (0°) in. (tabs optional) ETW 3 3 3 3 3 3

Unnotched Compression Properties 1 ( 25/50/25 - QI) CTD

Strength & Modulus (extensometer OR CEA-XX-125UT-350) [45/0/-45/90]3S RTD 3 3 3 3 3 3 ASTM D 6641 ETD

0.50 x 5.50 (0°) in. ETW 3 3 3 3 3 3 Unnotched Compression Properties 2 (10/80/10) CTD

Strength & Modulus (extensometer OR CEA-XX-125UT-350) [45/-45/0/45/-45/90/45/-45/45/-45]S RTD 3 3 3 3 3 3 ASTM D 6641 ETD

0.50 x 5.50 (0°) in. ETW 3 3 3 3 3 3

Unnotched Compression Properties 3 (50/40/10) CTD

Strength & Modulus (extensometer OR CEA-XX-125UT-350) [45/0/90/0/-45/0/45/0/-45/0]S RTD 3 3 3 3 3 3 ASTM D 6641 ETD

0.50 x 5.50 (0°) in. ETW 3 3 3 3 3 3 Open Hole Tension Properties 1 (25/50/25 - QI) CTD 3 3 3 3 3 3

Strength [45/0/-45/90]2S RTD 3 3 3 3 3 3 ASTM D 5766 ETD

1.5 x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3 Open Hole Tension Properties 2 (10/80/10) CTD 3 3 3 3 3 3

Strength [45/-45/0/45/-45/90/45/-45/45/-45]S RTD 3 3 3 3 3 3 ASTM D 5766 ETD

1.5 x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3

Open Hole Tension Properties 3 (50/40/10) CTD 3 3 3 3 3 3 Strength [0/45/0/90/0/-45/0/45/0/-45]S RTD 3 3 3 3 3 3

ASTM D 5766 ETD 1.5 x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3

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Filled Hole Tensile Properties 1 (25/50/25 - QI) CTD 3 3 3 3 3 3

Strength [45/0/-45/90]2S RTD 3 3 3 3 3 3


Protruding head fastener Filled Hole Tensile Properties 2 (10/80/10) CTD 3 3 3 3 3 3

Strength [45/-45/0/45/-45/90/45/-45/45/-45]S RTD 3 3 3 3 3 3 ASTM D 6742 ETD

1.5 x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3 Protruding head fastener

Filled Hole Tensile Properties 3 (50/40/10) CTD 3 3 3 3 3 3

Strength [0/45/0/90/0/-45/0/45/0/-45]S RTD 3 3 3 3 3 3 ASTM D 6742 ETD


Open Hole Compression Properties 1 (25/50/25 - QI) CTD


1.5 x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3 Open Hole Compression Properties 2 (10/80/10) CTD

Strength [45/-45/0/45/-45/90/45/-45/45/-45]2S RTD 3 3 3 3 3 3


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Open Hole Compression Properties 3 (50/40/10) CTD

Strength [0/45/0/90/0/-45/0/45/0/-45]2S RTD 3 3 3 3 3 3 ASTM D 6484 ETD

1.5x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3

Filled Hole Compression Properties 1 (25/50/25 - QI) CTD



Filled Hole Compression Properties 2 (10/80/10) CTD

Strength [45/-45/0/45/-45/90/45/-45/45/-45]2S RTD 3 3 3 3 3 3


Protruding head fastener

Filled Hole Compression Properties 3 (50/40/10) CTD

Strength [0/45/0/90/0/-45/0/45/0/-45]2S RTD 3 3 3 3 3 3 ASTM D 6484 ETD

1.5x 12.0 (0°) in., 0.25 in. dia hole ETW 3 3 3 3 3 3 Protruding head fastener

Single Shear Bearing Properties 1 (25/50/25 - QI) CTD

Strength & Deformation (Extensometer) [45/0/-45/90]2S RTD 3 3 3 3 3 3 ASTM D 5961 ETD

1.5 x 6.0 (0°) in., 0.25 in. dia hole, e/D = 3 ETW 3 3 3 3 3 3

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Protruding head fastener Single Shear Bearing Properties 2 (10/80/10) CTD

Strength & Deformation (Extensometer) [45/-45/0/45/-45/90/45/-45/45/-45]S RTD 3 3 3 3 3 3 ASTM D 5961 ETD

1.5 x 6.0 (0°) in., 0.25 in. dia hole, e/D = 3 ETW 3 3 3 3 3 3 Protruding head fastener

Single Shear Bearing Properties 3 (50/40/10) CTD

Strength & Deformation (Extensometer) [0/45/0/90/0/-45/0/45/0/-45]S RTD 3 3 3 3 3 3 ASTM D 5961 ETD

1.5 x 6.0 (0°) in., 0.25 in. dia hole, e/D = 3 ETW 3 3 3 3 3 3 Protruding head fastener

Interlaminar Tension Strength (100/0/0) CTD 6

Strength [0]30 RTD 6 ASTM D6415 ETD

Angle Bend ETW 6

Compression Strength after Impact 1* (25/50/25- QI) CTD Strength [45/0/-45/90]4S RTD 6

ASTM D7136 & D7137 ETD 4.0 x 6.0 (0°) in. ETW

1500 in-lb/in

Short Beam Strength Properties 1* ( 25/50/25 - QI) CTD Strength [45/0/-45/90]4S RTD 3 3 3 3 3 3

ASTM D 2344 ETD 0.26 x 0.79 (0°) in. ETW 3 3 3 3 3 3

* Short Beam Strength Properties 1 specimens to be taken from Compression Strength After Impact 1 panel

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Appendix 2

Cytec 5215 T40-800 Unidirectional Prepreg Qualification Panels

145 gsm carbon uni CPT= 0.005492" approx Length Width

ID Table Batch (%0/%±45/%90) Layup #

Plies Qty inch direction inch direction NTP3668Q1-CYT-C11-CYT- LT-A-C1-1 3 A (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LT-A-C2-1 3 A (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LT-B-C1-1 3 B (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LT-B-C2-1 3 B (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LT-C-C1-1 3 C (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LT-C-C2-1 3 C (100/0/0) [0]8 8 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- LC-A-C1-1 3 A (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- LC-A-C2-1 3 A (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- LC-B-C1-1 3 B (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- LC-B-C2-1 3 B (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- LC-C-C1-1 3 C (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- LC-C-C2-1 3 C (100/0/0) [0]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TT-A-C1-1 3 A (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TT-A-C2-1 3 A (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TT-B-C1-1 3 B (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TT-B-C2-1 3 B (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TT-C-C1-1 3 C (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TT-C-C2-1 3 C (0/0/100) [90]16 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- TC-A-C1-1 3 A (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TC-A-C2-1 3 A (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TC-B-C1-1 3 B (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TC-B-C2-1 3 B (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TC-C-C1-1 3 C (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- TC-C-C2-1 3 C (0/0/100) [90]20 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNT0-A-C1-1 3 A (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT0-A-C2-1 3 A (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º

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NTP3668Q1-CYT-C11-CYT- UNT0-B-C1-1 3 B (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT0-B-C2-1 3 B (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT0-C-C1-1 3 C (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT0-C-C2-1 3 C (50/0/50) [0/90]3S 12 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-A-C1-1 3 A (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-A-C2-1 3 A (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-B-C1-1 3 B (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-B-C2-1 3 B (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-C-C1-1 3 C (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC0-C-C2-1 3 C (33/0/67) [90/0/90]7 21 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- IPS-A-C1-1 3 A (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- IPS-A-C2-1 3 A (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- IPS-B-C1-1 3 B (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- IPS-B-C2-1 3 B (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- IPS-C-C1-1 3 C (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- IPS-C-C2-1 3 C (0/100/0) [45/-45]4S 16 1 12 any 24 any NTP3668Q1-CYT-C11-CYT- SBS-A-C1-1 3 A (100/0/0) [0]45 45 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- SBS-A-C2-1 3 A (100/0/0) [0]45 45 1 6 along 90º 8 along 0º NTP3668Q1-CYT-C11-CYT- SBS-B-C1-1 3 B (100/0/0) [0]45 45 1 6 along 90º 8 along 0º NTP3668Q1-CYT-C11-CYT- SBS-B-C2-1 3 B (100/0/0) [0]45 45 1 6 along 90º 8 along 0º NTP3668Q1-CYT-C11-CYT- SBS-C-C1-1 3 C (100/0/0) [0]45 45 1 6 along 90º 8 along 0º NTP3668Q1-CYT-C11-CYT- SBS-C-C2-1 3 C (100/0/0) [0]45 45 1 6 along 90º 8 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 24 along 0º

NTP3668Q1-CYT-C11-CYT- UNT2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º

NTP3668Q1-CYT-C11-CYT- UNT2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º

NTP3668Q1-CYT-C11-CYT- UNT2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º

NTP3668Q1-CYT-C11-CYT- UNT2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º

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NTP3668Q1-CYT-C11-CYT- UNT2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º

NTP3668Q1-CYT-C11-CYT- UNT2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNT3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 24 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]3S 24 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- UNC2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-A-C1-1 4 A (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-A-C2-1 4 A (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-B-C1-1 4 B (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-B-C2-1 4 B (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-C-C1-1 4 C (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- UNC3-C-C2-1 4 C (50/40/10) [45/0/90/0/-45/0/45/0/-45/0]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- OHT1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º

of 42

NTP3668Q1-CYT-C11-CYT- OHT1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHT2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHT3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHT2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHT2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHT2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHT2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHT2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º

of 42

NTP3668Q1-CYT-C11-CYT- FHT2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHT3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- OHC2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- OHC3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º

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NTP3668Q1-CYT-C11-CYT- FHC1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º

NTP3668Q1-CYT-C11-CYT- FHC2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- FHC3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]2S 40 1 14 along 90º 28 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-A-C2-1 4 A ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-B-C1-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-B-C2-1 4 B ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-C-C1-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB1-C-C2-1 4 C ( 25/50/25 - QI) [45/0/-45/90]2S 16 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- SSB2-A-C1-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- SSB2-A-C2-1 4 A (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- SSB2-B-C1-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- SSB2-B-C2-1 4 B (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º

NTP3668Q1-CYT-C11-CYT- SSB2-C-C1-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/-

45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB2-C-C2-1 4 C (10/80/10) [45/-45/0/45/-45/90/45/-45/45/- 20 1 12 along 90º 13 along 0º

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45]S NTP3668Q1-CYT-C11-CYT- SSB3-A-C1-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB3-A-C2-1 4 A (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB3-B-C1-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB3-B-C2-1 4 B (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB3-C-C1-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- SSB3-C-C2-1 4 C (50/40/10) [0/45/0/90/0/-45/0/45/0/-45]S 20 1 12 along 90º 13 along 0º NTP3668Q1-CYT-C11-CYT- ILT-A-C1-1 4 A ( 100/0/0) [0]30 30 1 36 along 90º 6 along 0º NTP3668Q1-CYT-C11-CYT- CAI1-A-C1-1 4 A ( 25/50/25 - QI) [45/0/-45/90]4S 32 1 14 along 90º 28 along 0º

Appendix 3

(Below are sample pictures from NCAMP’s “PMC_Data_Collection_Template.xls”. Please use the actual templates to record the information)

General Material Description (To be completed by the material supplier)

COMPOSITE MATERIALDATA COLLECTION TEMPLATE

Required EntryGENERAL MATERIAL DESCRIPTION Required Entry if ApplicableTO BE COMPLETED BY MATERIAL SUPPLIER Optional

COMPOSITE Unit or FormatComposite Common NameComposite Source (Supplier and/or supplier location)Composite Product Name (Supplier's catalog name)Composite Material Form – General < select from pull-downReinforcement Form or Fabric Weave Style < select from pull-downNominal Fiber Areal Weight (of tape, fabric, or preform) g/m2

Nominal Resin Solids Content (of prepreg) wt. %Composite Specification NumberComposite Specification Dash NumberScrim Material Common NameScrim Weave Style < select from pull-downScrim Source (Supplier)Nominal Cured Ply Thickness Related to I9 inch

MATRIXMatrix Type < select from pull-downMatrix Common NameMatrix Source (Supplier)Matrix Nominal Density (cured) g/cm3

Matrix Specification Number

REINFORCEMENTFiber Type < select from pull-downFiber Common NameFiber SourceFiber Nominal Density g/cm3

Fiber Length (for discontinuous reinforcement) inchTow Twist (0 = no twist) turns/inchFiber Surface Treatment (Yes or No) < select from pull-downFiber Sizing/Finish TypeFiber Sizing/Finish NameSizing/Finish Content, Nominal wt. %Filament Count per Tow ##kTow Denier denierNominal Tow Yield (forms used as tow) linear ft./lb.Fiber Specification Number

PREFORM (Including Fabrics)Preform Source (Weaver, Braider, or Stitcher)Tackifier TypeTackifier Common NameTackifier SourceYarn Count, Nominal (Warp x Fill for Fabrics) yarns/inchStitching Count stitches/inchStitching Yarn Row Spacing inchPreform Specification NumberTackifier Specification Number

NOTESMaterial Description Note or Comment

ASTM E1434Item No.

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Material Batch Information (To be completed by the material supplier)


SPECIFIC BATCH INFORMATIONTO BE COMPLETED BY MATERIAL SUPPLIER

PREPREG Batch 1 Batch 2 Batch 3 Batch 4 Batch 5 Unit or FormatComposite Material (Prepreg) Batch Number(assign number for liquid molding)Composite Batch Date of Manufacture mm/dd/yyyyBatch Average Fiber Areal Weight g/m2

Batch Average Resin (solids) Content (of prepreg) wt. %Batch Avg. Volatile Content (of prepreg or RTM resin) wt. %Volatile Test Temperature °FBatch Average Flow (of prepreg) wt. %Flow Test Temperature °FFlow Test Pressure psiBatch Average Gel Time (of RTM or prepreg resin) minutesGel Test Temperature °FTack (Low, Medium, or High for prepreg)Drape (Low, Medium, or High for prepreg)

MATRIXMatrix Lot or Batch NumberMatrix Lot Date of Manufacture mm/dd/yyyyMatrix Density, Lot Average g/cm3

REINFORCEMENT

0° (Warp) Direction FibersFiber Lot Number(s)Fiber Lot Date of Manufacture mm/dd/yyyyFiber Lot Avg. Density g/cm3

Fiber Lot Avg. Tensile Strength ksiFiber Lot Avg. Tensile Modulus Msi

90° (Fill) Direction FibersFiber Lot Number(s)Fiber Lot Date of Manufacture mm/dd/yyyyFiber Lot Avg. Density g/cm3


Through Thickness Direction FibersFiber Lot Number(s)Fiber Lot Date of Manufacture mm/dd/yyyyFiber Lot Avg. Density g/cm3


Bias (θ°) Direction FibersFiber Lot Number(s)Fiber Lot Date of Manufacture mm/dd/yyyyFiber Lot Avg. Density g/cm3


Stitching FibersFiber Lot Number(s)Fiber Lot Date of Manufacture mm/dd/yyyyFiber Lot Avg. Density g/cm3


PREFORM (Including Fabrics)Preform or Fabric Lot Number (e.g.: weaver lot number)Preform or Fabric Date of Manufacture mm/dd/yyyyTackifier Lot NumberTackifier Lot Date of Manufacture mm/dd/yyyyTackifier Content wt. %

NOTESBatch Information Note or Comment

Required EntryRequired Entry if Applicable

ASTM E1434Item No.

Optional

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Test Panel Data (To be completed by the panel fabricator)


TEST PANEL (OR SUB-PANEL) DATASubpanels must be identified to indicate the parent panel

PANEL DESCRIPTION (TO BE COMPLETED BY PANEL FABRICATOR) Unit or Format Panel 1 Panel 2 Panel 3 PanePanel or Sub-panel Identification Number(used for the consolidated and fully processed panel)Panel Description (type of test for which the panel is to be used)Panel FabricatorComposite Material Batch NumberNumber of Layers (plies) I7Layup Stacking Sequence CMH-17 format Related to H7Composite Material Lot Number (subset of batch)Composite Material Roll Number

PANEL PROCESSING (TO BE COMPLETED BY PANEL FABRICATOR)Lay-up Method select from pull-down >Type of curing or final consolidation process select from pull-down >Autoclave, Oven, or Press IDHeating Rate to Cure Temperature °F/minuteCure Temperature °FCure Pressure (enter 0 for vacuum only) psigCure Time minutesCure Vacuum Maintained Throughout Cure? No or YesCooling Rate After Cure °F/minutePanel Removal Tool Temperature °FCure Vacuum Vent Pressure psigPostcure Temperature °FPostcure Time minutesRTM Vacuum Used? (Yes or No) No or YesRTM/VARTM Resin Temperature at Injection °FRTM/VARTM Preform Degas Procedure Text or ReferenceRTM/VARTM Preform Temperature at Insertion °FRTM/VARTM Tool Temperature Prior to Injection °FRTM/VARTM Resin Injection Rate lb./min. or ml/min.

Required EntryRequired Entry if Applicable

If Applicable to All Panels on this Sheet, Enter for Panel 1 Only and Check Here ASTM E1434

Item No.

Optional

Test Panel Data, continued (To be completed by the testing lab) SECONDARY PANEL OPERATIONS (TO BE COMPLETED BY TESTING LAB)Bonded Tab (doubler) Material I48Bonded Tab (doubler) Layup (stacking sequence) CMH-17 format I50Bonded Tab (doubler) Nominal Thickness inch I51Bonded Tab (doubler) Bevel Angle degrees I52Bonded Tab (doubler) Nominal Length inch I53Bonded Tab (doubler) Bonding Adhesive I49Bonded Tab (doubler) Bond Cycle Temperature °F I54Bonded Tab (doubler) Bond Cycle Time minutes I55Bonded Tab (doubler) Bond Cycle Pressure psiType of Equipment Used for Bonding Tabs select from pull-down >Are Tabs Bonded to Individual Specimens or to Entire Panel? select from pull-down >Sandwich Panel Core Common Name I26Sandwich Panel Core Material Type select from pull-down > I27Sandwich Panel Core Material I28Sandwich Panel Core Material Manufacturer I29Sandwich Panel Core Material Lot Number I30Nominal Sandwich Core Cell Size (for honeycomb hexcore) inch I31Nominal Sandwich Core Cell Count (for honeycomb OX or flexible core) cells per inch I31Nominal Sandwich Core Density lb./ft.3 I32Nominal Sandwich Core Thickness inchNon-test Sandwich Face MaterialNon-test Sandwich Face Nominal Thickness inchSandwich Bonding Adhesive Common Name I34Sandwich Bonding Adhesive Manufacturer I36Sandwich Bonding Adhesive Lot Number I37Sandwich Bonding Adhesive Date of Manufacture mm/dd/yyyy I38Sandwich Secondary Bond Cycle Time/Temp./Pressure

PANEL PROPERTIES (Prior to Secondary Operations) (TO BE COMPLETED BY TESTING LAB)Panel Thickness (panel average) inchPanel Density g/cm3

Panel Density Test MethodPanel Fiber Volume (panel average) vol.% M7Panel Fiber Volume Test MethodPanel Dry Glass Transition Temperature °FPanel Wet Glass Transition Temperature °FPanel Glass Transition Test MethodPanel Void Content vol.%Panel Void Content Test Method

NOTESPanel Data Note or Comment

Additional reporting requirements are related to testing procedures and are to be

completed by the testing labs. The templates may be found in NCAMP’s “PMC_Data_Collection_Template.xls”

qualification test plan for 5215 t40-800 unitape · · 2009-02-06clc combined loading compression...

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