Advanced General Aviation Transport Experiments

Transcription

1 Advanced General Aviation Transport Experiments B Basis Design Allowables for Epoxy Based Prepreg Fiberite 8-Harness Graphite Fabric T65 K-5-8H / 774 AGATE-WP.-5- September J. Tomblin, J. McKenna, Y. Ng, K. S. Raju National Institute for Aviation Research Wichita State University Wichita, KS 676-9

2 TABLE OF CONTENTS. INTRODUCTION...5. Scope Symbols Used Acronyms and Definitions References Methodology Test Matrix Environmental Conditioning Fluid Sensitivity Screening Normalization Procedures Statistical Analysis Material Performance Envelope and Interpolation Interpolation Example FIBERITE T65 K-5-8H / 774 PREPREG PROPERTIES...8. Prepreg Documentation by Prepreg Lot Process Specification.... FIBERITE T65 K-5-8H / 774 LAMINATE PROPERTIES.... Test Results..... Summary..... Individual Test Summaries Tension, -axis Tension, -axis Compression, -axis Compression, -axis Shear, axis Shear, axis..... Individual Test Charts Tension, -axis Tension, -axis Compression, -axis Compression, -axis Shear, axis Shear, axis... 7

3 . Raw Data Raw Data Spreadsheets and Scatter Charts Fluid Sensitivity Raw Data Spreadsheets and Scatter Charts Representative Shear Stress-Strain Curve Statistical Results Plot by Condition Plot of Pooled Data....4 Moisture Conditioning History Charts....5 Physical Test Results TESTING AND REPORTING COMMENTS...9 APPENDIX A. PHYSICAL TEST DATA SUPPLIED BY MATERIAL VENDOR... APPENDIX B. DATES OF PANEL MANUFACTURE AND COPY OF FAA FORM

4 . INTRODUCTION. Scope The test methods and results described in this document are intended to provide basic composite properties essential to most methods of analysis. These properties are considered to provide the initial base of the building block approach. Additional coupon level tests and subelement tests may be required to fully substantiate the full-scale design. The test methods and results contained in this document are consistent with MIL- HDBK-7-E,D,E - Military Handbook for Polymer Matrix Composites. All material, specimens, fixtures and test results contained within this document were traceable and conformed by the Federal Aviation Administration (FAA). It should be noted that before application of the basis values presented in this document to design, demonstration of the ability to consistently produce equivalent material properties as that evaluated during this program should be substantiated through an acceptable test program. 5

5 . Symbols Used tu c E t E c E t E su F su F cu F tu F cu F tu F s G major Poisson s ratio, tension micro-strain compressive modulus, longitudinal tensile modulus, longitudinal compressive modulus, transverse tensile modulus, transverse in plane shear strength apparent interlaminar shear strength compressive strength, longitudinal tensile strength, longitudinal compressive strength, transverse tensile strength, transverse in plane shear modulus Superscripts c cu s su t tu compression compression ultimate shear shear ultimate tension tension ultimate Subscripts axis; longitudinal (parallel to warp direction of reinforcement) axis; transverse (parallel to fill direction of reinforcement) in plane shear interlaminar shear (apparent) 6

6 . Acronyms and Definitions A Basis 95% lower confidence limit on the first population percentile AGATE Advanced General Aviation Transport Experiments ASTM American Society for Testing and Materials B Basis 95% lower confidence limit on the tenth population percentile C. V. coefficient of variation CTD cold temperature dry CPT cured ply thickness DMA dynamic mechanical analysis dry specimen tested with an as fabricated moisture content ETD elevated temperature dry ETW elevated temperature wet FAR Federal Aviation Regulations FAW fiber areal weight Gr/Ep Graphite/Epoxy NASA National Aeronautics and Space Administration RTD room temperature dry SACMA Suppliers of Advanced Composite Materials Association SRM SACMA Recommended Method T g glass transition temperature t ply cured ply thickness wet specimen tested with an equilibrium moisture content per section.5. 7

7 .4 References ASTM Standards D9-95 Tensile Properties of Polymer Matrix Composite Materials D579-9 Shear Properties of Composite Materials by the V-Notched Beam Method D44-89 Apparent Interlaminar Shear Strength of Parallel Fiber Composites by Short Beam Method D79-9 Density and Specific Gravity (Relative Density) of Plastics by Displacement D74-94 Void Content of Reinforced Plastics D7-9 Fiber Content of Resin Matrix Composites by Matrix Digestion D695-9 Compressive Properties of Rigid Plastics SACMA Standards SRM -94 SRM 8-94 SRM 8-94 Compressive Properties of Oriented Fiber-Resin Composites Short Beam Shear Strength of Oriented Fiber-Resin Composites Glass Transition Temperature (T g ) Determination by DMA of Oriented Fiber-Resin Composites Other Documents FAA Document DOT/FAA/AR-/47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems, J.S. Tomblin, Y.C. Ng and K.S. Raju,. MIL-HDBK-7 E, D, E Military Handbook for Polymer Matrix Composites Cessna Aircraft Company, Document # : B-Basis Design Allowables Test Plan for Preimpregnated Carbon/Epoxy Broadgoods, Revision B, January

8 .5 Methodology.5. Test Matrix Testing was performed according to the test methods delineated in the test matrix, with modifications as referenced in the AGATE report, Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. The test matrix for properties included in this document is listed on the next page, with the following notation cited in each column: # x # where the first # represents the required number of prepreg batches, defined as: Prepreg containing T65 K-5 8-Harness Graphite Fabric from one mill roll, impregnated with one batch of resin in one continuous manufacturing operation with traceability to all components. The second # represents the required number of replicates per prepreg batch. For example, x 6 refers to three prepreg batches of material and six specimens per prepreg batch for a total requirement of 8 test specimens. 9

9 Table.5.: Test Matrix and Standards Used TEST METHOD NO. OF REPLICATES PER TEST CONDITION CTD,5 RTD,5 ETW ETD 4,5 o (warp) Tension Strength ASTM D9-95 x4 x4 x4 x4 o (warp) Tension Modulus, ASTM D9-95 Strength and Poisson s Ratio x x x x 9 o (fill) Tension Strength ASTM D9-95 x4 x4 x4 x4 9 o (fill) Tension Modulus and ASTM D9-95 Strength x x x x o (warp) Compression Strength SACMA SRM -94 x6 x6 x6 x6 o (warp) Compression Modulus SACMA SRM -94 x x x x 9 o (fill) Compression Strength SACMA SRM -94 x6 x6 x6 x6 9 o (fill) Compression Modulus SACMA SRM -94 x x x x In-Plane Shear Strength ASTM D579-9 x4 x4 x4 x4 In-Plane Shear Modulus and ASTM D579-9 Strength x x x x Short Beam Shear ASTM D x Fiber Volume ASTM D7-9 One sample per panel Resin Volume ASTM D7-9 One sample per panel Void Content ASTM D74-94 One sample per panel Cured Neat Resin Density --- Supplied by manufacturer for material Glass Transition Temperature SACMA SRM 8-94 dry, wet per prepreg lot Notes : CTD: One prepreg lot of material tested (test temperature = o F, moisture content = as fabricated, soak time at 65 was min.) RTD: Three prepreg lots of material tested (test temperature = 7 o F, moisture content = as fabricated) ETW: Three prepreg lots of material tested (test temperature = 8 5 o F, moisture content = equilibrium per section.5., soak time at 8 was 6 sec.) 4 ETD: Three prepreg lots of material tested (test temperature = 8 5 o F, moisture content = as fabricated, soak time at 8 was 6 sec.) 5 Dry specimens are as fabricated specimens that have been maintained at ambient conditions in an environmentally controlled laboratory.

10 .5. Environmental Conditioning All wet conditioned samples were exposed to elevated temperature and humidity conditions to establish moisture saturation of the material. Specimens were exposed to 85 ± 5 % relative humidity and 45 ± 5 F until an equilibrium moisture weight gain of traveler, or witness coupons ( x x specimen thickness) was achieved. ASTM D59 and SACMA SRM were used as guidelines for environmental conditioning and moisture absorption. Effective moisture equilibrium was achieved when the average moisture content of the traveler specimen changed by less than.5% for two consecutive readings within a span of 7 ±.5 days and was expressed by: W i -W W b i - <.5 where W i = weight at current time W i- = weight at previous time W b = baseline weight prior to conditioning It is common to see small fluctuations in an unfitted plot of the weight gain vs. time curve. There were no fluctuations that made significant errors in results or caused rejection in the moisture equilibrium criteria. Once the traveler coupons passed the criteria for two consecutive readings, the samples were removed from the environmental chamber and placed in a sealed bag with a moist paper or cotton towel for a maximum of 4 days until mechanical testing. Strain gauged specimens were removed from the controlled environment for a maximum of hours for application of gages in ambient laboratory conditions..5. Fluid Sensitivity Screening All wet conditioned samples were exposed to elevated temperature and humidity conditions to establish moisture saturation of the material. Specimens were exposed to 85 ± 5 % relative humidity and 45 ± 5 F until an equilibrium moisture weight gain of traveler, or witness coupons ( x x specimen thickness) was achieved. ASTM D59 and SACMA SRM were used as guidelines for environmental conditioning and moisture absorption. Effective moisture equilibrium was achieved when the average moisture content of the traveler specimen changed by less than.5% for two consecutive readings within a span of 7 ±.5 days and was expressed by:

11 W i -W W b i - <.5 where W i = weight at current time W i- = weight at previous time W b = baseline weight prior to conditioning It is common to see small fluctuations in an unfitted plot of the weight gain vs. time curve. There were no fluctuations that made significant errors in results or caused rejection in the moisture equilibrium criteria. Once the traveler coupons passed the criteria for two consecutive readings, the samples were removed from the environmental chamber and placed in a sealed bag with a moist paper or cotton towel for a maximum of 4 days until mechanical testing. Strain gauged specimens were removed from the controlled environment for a maximum of hours for application of gages in ambient laboratory conditions..5.4 Normalization Procedures The normalization procedure attempts to reduce variability in fiber-dominated material properties by adjusting raw test values to a specified fiber volume content. Only the following properties were normalized: (warp) Tensile Strength and Modulus 9 (fill) Tensile Strength and Modulus (warp) Compressive Strength and Modulus 9 (fill) Compressive Strength and Modulus The normalization procedure was adopted from MIL-HDBK-7-E, section.4... The procedure which was used to normalize the data is based on two primary assumptions: The relationship between fiber volume fraction and ultimate laminate strength is linear over the entire range of fiber/resin ratios. (It neglects the effects of resin starvation at high fiber contents.) Fiber volume is not commonly measured for each test sample, so this method accounts for the fiber volume variation between individual test specimens by utilizing a relationship between fiber volume fraction and laminate cured ply thickness. This relationship is virtually linear in the.45 to.65 fiber volume fraction range.

12 Additional information is detailed in FAA Document DOT/FAA/AR-/47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems. For all normalized data contained in this document, the test values are normalized by cured ply thickness according to: where: CPT Normalized Value Test Value CPT specimen normalizing Average Sample Thickness CPT specimen # of plies

13 .5.5 Statistical Analysis When compared to metallic materials, fiber reinforced composite materials exhibit a high degree of material property variability. This variability is due to many factors, including but not limited to: raw material and prepreg manufacture, material handling, part fabrication techniques, ply stacking sequence, environmental conditions, and testing techniques. This inherent variability drives up the cost of composite testing and tends to render smaller data sets than those produced for metallic materials. This necessitates the usage of statistical techniques for determining reasonable design allowables for composites. The analyses and design allowable generation for both A and B basis values were performed using the procedure detailed in section 5. of FAA Document DOT/FAA/AR- /47: Material Qualification and Equivalency for Polymer Matrix Composite Material Systems..5.6 Material Performance Envelope and Interpolation Using the B-basis numbers, a material performance envelope may be generated for the material system by plotting these values as a function of temperature. Figure.5. shows an example material performance envelope using B-basis values. 4

14 Actual Basis Value Estimated Value B-Basis Strength Values (ksi) 8 6 CTD Material Performance Envelope RTD RTW ETD ETW Temperature ( o F) Figure.5. Material performance envelope. Since each specific aircraft application of the qualified material may have different Material Operational Limits (MOL) than those tested in the material qualification (which is usually the upper limit), some applications may require a reduced MOL. In this case, simple linear interpolation may be used to obtain the corresponding basis values at the new application MOL. This interpolation may be accomplished using the following simple relationships assuming T RTD < T MOL < T ETD : For the corresponding MOL dry basis value, the interpolated basis value using the qualification data is B MOL B RTD BRTD BETD TRTD TMOL T T RTD ETD where B MOL = new application basis value interpolated to T MOL 5

15 B RTD = basis RTD strength value B ETD = basis ETD strength value T RTD = RTD test temperature T ETD = ETD test temperature T MOL = new application MOL temperature For the corresponding MOL wet basis value, an estimated Room Temperature Wet (RTW) value must be calculated. This may be accomplished by the simple relation B RTW B RTD ( B B ) ETW ETD The interpolated wet basis value using the qualification data may then be obtained by B MOL B RTW BRTW BETW TRTW TMOL T T RTW ETW where: B MOL = new application basis value interpolated to T MOL B RTW = estimated basis RTW strength value B ETW = basis ETW strength value T RTW = RTW (i.e., RTD) test temperature T ETW = ETW test temperature T MOL = new application MOL temperature These equations may also be used for interpolated mean strengths as well as A-basis values with the appropriate substitutions. It should be noted that because unforeseen material property drop-offs with respect to temperature and environment can occur, extrapolation to a higher MOL should not be attempted without additional testing and verification. In addition, the interpolation equations shown above are practical for materials obeying typical mechanical behavior. In most cases, some minimal amount of testing may also be required to verify the interpolated values Interpolation Example This section provides an example of linear interpolations to a specific application environment less than the tested upper material limit used in qualification. Assuming a specific application environment of 5 o F, Figure.5. depicts the linear interpolation of the B-basis design allowable to this environment. Using the above equations along with the nominal testing temperatures (see Table.5.), the interpolated basis values at 5 o F become ETD : B MOL = 75.6 ksi 6

16 ETW : B MOL = ksi Actual Basis Value Estimated Value CTD RTD B-Basis Strength Values (ksi) 8 6 RTW ETD ETW Temperature ( o F) Figure.5. Example of 5 o F interpolation for B-basis values. 7

17 . FIBERITE T65 K-5-8H / 774 PREPREG PROPERTIES 8

18 . Prepreg Documentation by Prepreg Lot Prepreg Documentation Prepreg Manufacturer & Product ID: HMF 774/T65-5-K-8HS-7-4 Impregnation Method: SOLVENT Prepreg Batch or Lot # Batch (Lot) ID as labeled on samples Date of Manufacture Expiration Date Resin Content [%] 7 % 9 % 8 % Reinforcement Areal Weight & Test Method 7 g/sq m 68 g/sq m 69 g/sq m Resin Flow & Test Conditions psi psi psi Gel Time & Test Conditions 4 77 C 77 C 77 C Volatile Content.9..9 Reinforcement Documentation Fiber/Fabric Manufacturer & Product ID: T65/5 K 9NT Precursor Type: PAN Nominal Filament Count: K Finish/Sizing Type and %: UC9,,.9.4% Nominal tow or yarn count/inch: Twist: not available Fabric Batch or Lot #, Warp BS6, 75, 8, 84, 8 BS6, 75, 8, 84, 8 BS Sizing weight, %.9,.4,.97,.,.9 %.9,.4,.97,.,.9 %. % Fabric Batch or Lot #, Fill BS8, 84, 8 BS8, 84, 8 BS Sizing weight, %.97,.,.9 %.97,.,.9 %. % Date of Manufacture Average Fiber Density per Lot & Test Method.775 (warp),.776 ( fill ) g/cc.775 (warp),.776 ( fill ) g/cc.76 g/cc Matrix Documentation Resin Manufacturer & Product ID: Matrix Batch or Lot # Date of Manufacture Average Neat Resin Density by Lot & Test Method.7 g/ccm.7 g/ccm.7 g/ccm 9

19 . Process Specification This specification does not address issues relating to safety, quality control, bagging material selection, bagging procedure, tool preparation, or equipment selection. Although these may affect overall part quality, it is the responsibility of the end user to develop procedures related to these issues in a manner that produces parts with high quality and consistency. The following autoclave cure procedures are excerpts from Cessna process specification CSAC5. The exception to this specification is the cure cycle and ply orientation tolerance. The cure cycle for panel fabrication is 5 F, ± : for minutes, +6, -; 45 psi, ±5. Individual ply orientation is ± with respect to the tooled reference edge. The detailed cure cycle procedure is given below. All test specimens were cured per this specification by Cessna Aircraft Company. However, the effects of the upper and lower limits of vacuum, temperature, cure time, heat-up rate and hold temperature on the mechanical and thermal properties have not been investigated. () Apply in-hg of vacuum minimum to vacuum bag. Initiate autoclave pressure psi/minute minimum, vent bag at ± psig. Final vessel pressure 45±5 psi. () From F to 4 F, a minimum heat up rate of. F/minute is acceptable. () All thermocouples shall be at temperature

20 . FIBERITE T65 K-5-8H / 774 LAMINATE PROPERTIES

21 . Test Results

22 .. Summary MATERIAL: Fiberi te 774/T65 K-5-8H Graphi te Fabri c 774/T65 K-5-8H PREPREG: Fiberi te HMF 774/T65-5-K-8HS-7-4 Summary FIBER: Amoco T65/5 K 9NT RESIN: Fi berite HMF 774 T g (dry): 9.85 F T g (wet): 8. F T g METHOD: DMA (SRM 8-94) PROCESSING: Autocl ave cure: 5 F for 6, mi 45 5 psi Date of fiber manufacture 4//97 8/97 Date of testing /4/99 4//99 Date of resin manufacture //97 Date of data submittal 8/99 Date of prepreg manufacture //97 Date of analysis //99 4//99 Date of composite manufacture /9/98 4/6/98 F tu E t (ksi) 5.7 (6.4) LAMINA MECHANICAL PROPERTY SUMMARY Data Reported as: Measured (Normalized by CPT=.5 in) CTD RTD ETD ETW B-Basis Mean B-Basis Mean B-Basis Mean B-Basis Mean 5.79 (6.5) (Msi) ---. (.9).89 (.).5 (.49) (.4) 9.95 (.).4 (.4) (9.89).76 (.59).77 (.45) (9.8) tu F tu t E F cu E c cu F c E F su (ksi).78 (.9).55 (.) (Msi) (.75) (ksi) 85.6 (8.49).9 (.6) (Msi) (9.4) (ksi) 97. (96.7).7 (.5) (Msi) (9.8) 6.8 (6.9) 5. (5.74) (9.86) 88. (86.7).8 (.55) (9.4) 9. (9.6) 5.9 (6.56) (9.9) 6. (6.5) 5.4 (5.9) (9.48) 68.8 (67.9) 8. (8.) (9.4) 69. (68.7) (78.) (9.) 4.9 (4.6).48 (.65) (9.44) (47.89) 56.5 (56.6) (9.6) 44.9 (44.9) 5. (5.) (9.5) (ksi) G s (Msi) F su** (ksi) ** Apparent i nterl ami nar shear strength

23 .. Individual Test Summaries 4

24 ... Tension, -axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: - 8 wt% Comp. density: g/cc Fiber volume: 5-59 vol% Void content:. to.6 % Ply thickness: in. Ply range: 7 plies Tension, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [] 7 Test method: D9-95 Modulus calculation: linear fit from - Normalized by:.5 in. ply thickness CTD (B) RTD (A) ETD (G) ETW (F) Test Temperature [ F] Moisture Conditioning dry dry dry 64 days,.6-.7% wt gain Equilibrium at T, RH as fabricated as fabricated as fabricated 45 F, 85 % Source code BDJXXXXB BDJXXXXA BDJXXXXG BDJXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F tu (ksi) B-value A-value E t (Msi) t No. Specimens No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens No. Prepreg Lots Mean No. Specimens No. Prepreg Lots 5

25 ... Tension, -axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: - 8 wt% Comp. density: g/cc Fiber volume: 5-59 vol% Void content:.4 to 4. % Ply thickness: in. Ply range: 7 plies Tension, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [] 7 Test method: D9-95 Modulus calculation: linear fit from - Normalized by:.5 in. ply thickness CTD (B) RTD (A) ETD (G) ETW (F) Test Temperature [ F] Moisture Conditioning dry dry dry 5 days,.6-.68% wt gain Equilibrium at T, RH as fabricated as fabricated as fabricated 45 F, 85 % Source code BDUXXXXB BDUXXXXA BDUXXXXG BDUXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F tu (ksi) B-value A-value E t (Msi) No. Specimens No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens No. Prepreg Lots 6

26 ... Compression, -axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: - 4 wt% Comp. density: g/cc Fiber volume: 5-6 vol% Void content:.6 to.9 % Ply thickness: in. Ply range: 8 plies Compression, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [] 8 Test method: SRM -94, D695-9 (mod) Modulus calculation: linear fit from - Normalized by:.5 in. ply thickness CTD (B) RTD (A) ETD (G) ETW (F) Test Temperature [ F] Moisture Conditioning dry dry dry 6-66 days,.7-.78% wt gain Equilibrium at T, RH as fabricated as fabricated as fabricated 45 F, 85 % Source code BDKXXXXB BDKXXXXA BDKXXXXG BDKXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F cu (ksi) B-value A-value E c (Msi) No. Specimens No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens 6 6 No. Prepreg Lots 6 7

27 ...4 Compression, -axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: 7-9 wt% Comp. density: g/cc Fiber volume: 5-59 vol% Void content:. to.9 % Ply thickness: in. Ply range: 8 plies Compression, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [] 8 Test method: SRM -94, D695-9 (mod) Modulus calculation: linear fit from - Normalized by:.5 in. ply thickness CTD (B) RTD (A) ETD (G) ETW (F) Test Temperature [ F] Moisture Conditioning dry dry dry 6-66 days,.68-.8% wt gain Equilibrium at T, RH as fabricated as fabricated as fabricated 45 F, 85 % Source code BDWXXXXB BDWXXXXA BDWXXXXG BDWXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F cu (ksi) B-value A-value E c (Msi) No. Specimens No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens 6 6 No. Prepreg Lots 6 8

28 ...5 Shear, axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: - 6 wt% Comp. density: g/cc Fiber volume: 54-6 vol% Void content:.7 to 4. % Ply thickness: in. Ply range: 9 plies Shear, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [(/9) //(9/) ] Test method: D579-9 Modulus calculation: linear fit from - 6 Normalized by: N/A CTD (B) RTD (A) ETD (G) ETW (F) Test Temperature [ F] Moisture Conditioning dry dry dry 64 days, % wt gain Equilibrium at T, RH as fabricated as fabricated as fabricated 45 F, 85 % Source code BDNXXXXB BDNXXXXA BDNXXXXG BDNXXXXF Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean Minimum Maximum C.V.(%) F su (ksi) B-value A-value G s (Msi) No. Specimens 6 8 No. Prepreg Lots Mean Minimum Maximum C.V.(%) No. Specimens 6 6 No. Prepreg Lots 6 9

29 ...6 Shear, axis Material: Fiberite 774/T65 K-5-8H Graphite Fabric Resin content: - 9 wt% Comp. density: g/cc Fiber volume: 5-59 vol% Void content:. to. % Ply thickness: in. Ply range: 7 plies Shear, -axis G/Ep Fiberite 774/T65 K-5-8H Graphite Fabric [] 7 Test method: D44-89 Modulus calculation: N/A Normalized by: N/A Test Temperature [ F] Moisture Conditioning Equilibrium at T, RH Source code CTD (B) RTD (A) ETD (G) ETW (F) 75 dry as fabricated BDQXXXXA Normalized Measured Normalized Measured Normalized Measured Normalized Measured Normalized Measured Mean.9 Minimum 9.6 Maximum. C.V.(%).85 F su (ksi) B-value 9.6 A-value 9. No. Specimens 8 No. Prepreg Lots NOTES: These values represent the apparent interlaminar shear properties and are to be used for quality control purposes only. Do not use these values for interlaminar shear strength design values.

30 .. Individual Test Charts

31 ... Tension, -axis Tension -- Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric 6 4 Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. The 8 dry and wet data has been staggered for clarity

32 ... Tension, -axis 9 Tension -- Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric 6 4 Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. The 8 dry and wet data has been staggered for clarity.

33 ... Compression, -axis Compression -- Normalized Strength Fiberite 774/T65 K-5-8H Graphite Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. The 8 dry and wet data has been staggered for clarity 4

34 ...4 Compression, -axis 9 Compression -- Normalized Strength Fiberite 774/T65 K-5-8H Graphite 4 Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. The 8 dry and wet data has been staggered for clarity. 5

35 ...5 Shear, axis In-Plane Shear -- Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric 8 4 Strength (ksi) Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. The 8 dry and wet data has been staggered for clarity. 6

36 ...6 Shear, axis Apparent Interlaminar Shear -- Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric 6 Strength (ksi) 8 4 Conditioning X Dry O Wet Temperature ( F) NOTE: The symbols represent the pooled average of all tests, and the bars represent the upper and lower limit of the data. 7

37 . Raw Data Specimen Naming Convention Test coupons were identified using an eight-digit specimen code, with the significance of each digit delineated below. A representative sample ID is shown for reference purposes. B D J 5 F st Character: Fabricator B designates Cessna nd Character: Material System D designates T65 K-5-8H / 774 rd Character: Test Type J designates Tension Strength and Modulus, other test types will be clearly labeled at the top of each sheet 4 th Character: Prepreg Batch ID See Table. for Fiberite Batch ID / Sample Batch ID correlation. 5 th Character: Panel Number The panel(s) fabricated for a specific test method. 6 th Character: Subpanel Number The sub-panel(s) cut from each panel, with subpanel numbers labeled increasing from reference edge. 7 th Character: Sample Number The sample(s) cut from each subpanel, with sample numbers labeled increasing from reference edge. 8 th Character: Test Condition A --- RTD B --- CTD F --- ETW G --- ETD See Table.5. for condition parameters. 8

38 .. Raw Data Spreadsheets and Scatter Charts 9

39 Tension -- (RTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] BDJXA BDJXA BDJXA BDJ4XA BDJ4XA BDJ4XA BDJX6A BDJX7A BDJX8A BDJX6A BDJX7A BDJX8A BDJX6A BDJX7A BDJX8A BDJX6A BDJX7A BDJX8A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec Number of Spec

40 Tension -- (RTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.494 [ksi] Pooled Standard Deviation = 4.9 [ksi] Pooled Coeff. of Variation =.687 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 6 Tension -- (RTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.4 [Msi] Pooled Standard Deviation =.58 [Msi] Pooled Coeff. of Variation =.57 [%] 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 4

41 Tension -- (CTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] BDJX5B BDJX6B BDJX7B BDJ4X5B BDJ4X6B BDJ4X7B BDJX5B BDJX6B BDJX7B BDJ4X5B BDJ4X6B BDJ4X7B BDJX6B BDJX7B BDJX8B BDJ4X6B BDJ4X8B BDJ4X9B Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec Number of Spec

42 Tension -- (CTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 6.5 [ksi] Pooled Standard Deviation = 8.58 [ksi] Pooled Coeff. of Variation = 6.87 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 6 Tension -- (CTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.86 [Msi] Pooled Standard Deviation =. [Msi] Pooled Coeff. of Variation =.9 [%] 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 4

43 Tension -- (ETW) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] BDJX5F BDJX6F BDJX7F BDJX8F BDJX9F BDJX5F BDJX6F BDJX7F BDJX8F BDJX9F BDJXF BDJXF BDJXF BDJX4F BDJX5F BDJXF BDJXF BDJXF BDJX4F BDJX5F BDJXF BDJXF BDJXF BDJX4F BDJX5F BDJXF BDJXF BDJXF BDJX4F BDJX5F Average Average norm Standard Dev Standard Dev. norm.7.6 Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 6 6 Number of Spec. 6 44

44 Tension -- (ETW) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.446 [ksi] Pooled Standard Deviation =.7 [ksi] Pooled Coeff. of Variation =.8 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 6 Tension -- (ETW) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.86 [Msi] Pooled Standard Deviation =.6 [Msi] Pooled Coeff. of Variation =.675 [%] 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 45

45 Tension -- (ETD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Poisson's Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Ratio Thickn. [in] Laminate [in] [ksi] [Msi] BDJXG BDJXG BDJXG BDJXG BDJXG BDJXG BDJXG BDJXG BDJXG BDJ4XG BDJ4XG BDJ4X8G BDJXG BDJXG BDJXG BDJ4XG BDJ4XG BDJ4XG Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec Number of Spec

46 Tension -- (ETD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.8 [ksi] Pooled Standard Deviation = 7.88 [ksi] Pooled Coeff. of Variation = [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] Tension -- (ETD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = [Msi] Pooled Standard Deviation =.87 [Msi] Pooled Coeff. of Variation =.89 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 47

47 9 Tension-- (RTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDUXA BDUXA BDUXA BDU4XA BDU4XA BDU4XA BDUX6A BDUX7A BDUX8A BDUX6A BDUX7A BDUX8A BDUXA BDUXA BDUXA BDU4X5A BDU4X6A BDU4X7A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

48 6 9 Tension -- (RTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 5.79 [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = [%] 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 9 Tension -- (RTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.86 [Msi] Pooled Standard Deviation =.4 [Msi] Pooled Coeff. of Variation =.444 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 49

49 9 Tension-- (CTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDUX5B BDUX6B BDUX7B BDU4X5B BDU4X6B BDU4X7B BDU4X5B BDU4X6B BDU4X7B BDUX5B BDUX6B BDUX7B BDUX6B BDUX7B BDUX8B BDUX6B BDUX7B BDUX8B Average.55.6 Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max..9. Max Number of Spec. 8 6 Number of Spec

50 9 Tension -- (CTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.96 [ksi] Pooled Standard Deviation = 5.79 [ksi] Pooled Coeff. of Variation = 4.98 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 9 Tension -- (CTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.746 [Msi] Pooled Standard Deviation =.474 [Msi] Pooled Coeff. of Variation = 4.46 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 5

51 9 Tension-- (ETW) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabricite normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDUXF BDUXF BDUXF BDUX4F BDUX5F BDUXF BDUXF BDUXF BDUX4F BDUX5F BDUXF BDUXF BDUXF BDUX4F BDUX5F BDUXF BDUXF BDUXF BDUX4F BDUX5F BDUXF BDUXF BDUXF BDUX4F BDUX5F BDUXF BDUXF BDUXF BDUX4F BDUX5F Average Average norm Standard Dev Standard Dev. norm 6.. Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 6 Number of Spec. 6 5

52 9 Tension -- (ETW) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.65 [ksi] Pooled Standard Deviation = 6. [ksi] Pooled Coeff. of Variation = [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 9 Tension -- (ETW) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.49 [Msi] Pooled Standard Deviation =. [Msi] Pooled Coeff. of Variation =.89 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 5

53 9 Tension-- (ETD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDUX6G BDUX7G BDUX8G BDUX6G BDUX7G BDUX8G BDUXG BDUXG BDUXG BDU4XG BDU4XG BDU4XG BDUX5G BDUX6G BDUX7G BDU4XG BDU4XG BDU4XG Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

54 9 Tension -- (ETD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 5.9 [ksi] Pooled Standard Deviation = 4.87 [ksi] Pooled Coeff. of Variation =.868 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Tension Strength [ksi] 9 Tension -- (ETD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.48 [Msi] Pooled Standard Deviation =.57 [Msi] Pooled Coeff. of Variation =.656 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Tension Modulus [Msi] 55

55 Compression -- (RTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDK6A BDK7A BDK8A BDLX6A BDK9A BDKAA BDKBA BDLX6A BDK6A BDK7A BDK8A BDLX6A BDK7A BDK8A BDK9A BDL6A BDK6A BDK8A BDK9A BDLX6A BDKA BDKA BDK4A BDLX6A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

56 Compression -- (RTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Pooled Average =.554 [ksi] Pooled Standard Deviation = 4.68 [ksi] Pooled Coeff. of Variation = [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] Compression -- (RTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Pooled Average = 9.97 [Msi] Pooled Standard Deviation =. [Msi] Pooled Coeff. of Variation =.5 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 57

57 Compression -- (CTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDK5B BDK6B BDK7B BDLX9B BDKB BDK4B BDK5B BDLX9B Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 6 Number of Spec. 6 58

58 Compression -- (CTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Pooled Average =.6 [ksi] Pooled Standard Deviation = 5.55 [ksi] Pooled Coeff. of Variation = [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] 6 Compression -- (CTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Pooled Average = 9.4 [Msi] Pooled Standard Deviation =.75 [Msi] Pooled Coeff. of Variation =.8 [%] 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 59

59 Compression -- (ETW) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDKF BDKF BDKF BDK4F BDK5F BDLXF BDKF BDKF BDKF BDK4F BDK5F BDLXF BDKF BDKF BDKF BDK4F BDK5F BDLF BDKF BDKF BDKF BDK4F BDK5F BDLXF BDKF BDKF BDKF BDK4F BDK5F BDLXF BDK5F BDK7F BDK8F BDKAF BDKBF BDLXF Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 6 Number of Spec. 6 6

60 6 Compression -- (ETW) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Pooled Average = [ksi] Pooled Standard Deviation = 6.95 [ksi] Pooled Coeff. of Variation =.77 [%] 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] Compression -- (ETW) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Pooled Average = 9.66 [Msi] Pooled Standard Deviation =.65 [Msi] Pooled Coeff. of Variation = 6.77 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 6

61 Compression -- (ETD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDKG BDKG BDK4G BDLXCG BDK7G BDK8G BDK9G BDLXCG BDKG BDKG BDKG BDLX9G BDKG BDK4G BDK6G BDL9G BDKX5G BDKX6G BDKX7G BDLX9G BDKG BDK4G BDK5G BDLX9G Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

62 Compression -- (ETD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Pooled Average = 8. [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = 6. [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] Compression -- (ETD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Pooled Average = 9.46 [Msi] Pooled Standard Deviation =.47 [Msi] Pooled Coeff. of Variation = 5.9 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 6

63 9 Compression -- (RTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDW6A BDW7A BDW8A BDZX6A BDW6A BDW7A BDW8A BDZX6A BDWA BDWA BDW4A BDZX6A BDW6A BDW7A BDW8A BDZX6A BDWA BDWA BDWA BDW6A BDW7A BDW8A BDZX6A BDZX6A Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

64 9 Compression -- (RTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 6.56 [ksi] Pooled Standard Deviation = [ksi] Pooled Coeff. of Variation = 5.8 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] 9 Compression -- (RTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.87 [Msi] Pooled Standard Deviation =.7 [Msi] Pooled Coeff. of Variation =.4 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 65

65 9 Compression -- (CTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDW7B BDW9B BDWAB BDZX9B BDW7B BDW8B BDW9B BDZX9B Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 6 Number of Spec. 6 66

66 9 Compression -- (CTD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.499 [ksi] Pooled Standard Deviation = 5.89 [ksi] Pooled Coeff. of Variation = 5.6 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] 9 Compression -- (CTD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.85 [Msi] Pooled Standard Deviation =.58 [Msi] Pooled Coeff. of Variation =.6 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 67

67 9 Compression -- (ETW) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDWF BDWF BDWF BDW4F BDW5F BDZXF BDWF BDWF BDWF BDW4F BDW5F BDZXF BDW8F BDW9F BDWAF BDWBF BDWCF BDZXF BDWF BDWF BDW4F BDW5F BDZXF BDWF BDWF BDWF BDW4F BDZXF BDWAF BDWF BDWF BDWF BDW4F BDW5F BDZXF Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 9 6 Number of Spec

68 9 Compression -- (ETW) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 5.5 [ksi] Pooled Standard Deviation = 4.4 [ksi] Pooled Coeff. of Variation = 8.46 [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] 9 Compression -- (ETW) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9.55 [Msi] Pooled Standard Deviation =.4 [Msi] Pooled Coeff. of Variation =.568 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 69

69 9 Compression -- (ETD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric normalizing t ply [in].5 Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Strength norm Modulus norm Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] [ksi] [Msi] BDWG BDW4G BDW5G BDZXCG BDWG BDW4G BDW5G BDZXDG BDWG BDWG BDWG BDZX9G BDWG BDWG BDWG BDZX9G BDW5G BDW6G BDW7G BDWG BDW4G BDW5G BDZX9G BDZX9G Average Average norm Standard Dev Standard Dev. norm Coeff. of Var. [%] Coeff. of Var. [%] norm Min Min Max Max Number of Spec. 8 6 Number of Spec

70 9 Compression -- (ETD) Normalized Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 78.8 [ksi] Pooled Standard Deviation = 5.49 [ksi] Pooled Coeff. of Variation = 7. [%] 6 5 ASAP Batch # 4 Prepeg Lot # Compression Strength [ksi] 9 Compression -- (ETD) Normalized Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 9. [Msi] Pooled Standard Deviation =.46 [Msi] Pooled Coeff. of Variation =.75 [%] 6 5 ASAP Batch # 4 Prepreg Lot # Compression Modulus [Msi] 7

71 In-Plane Shear -- (RTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] BDNA BDNA BDN4A BDN5A BDN8A BDN9A BDNAA BDNA BDNA BDN4A BDN5A BDN6A BDN9A BDNAA BDNA BDN5A BDN6A BDNA BDNA BDN4A Average Standard Dev Coeff. of Var. [%] Min Min..47 Max Max..5 Number of Spec. 6 7

72 In-Plane Shear -- (RTD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average 8.88 [ksi] Pooled Standard Deviation =.487 [ksi] Pooled Coeff. of Variation =.69 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Strength [ksi] In-Plane Shear -- (RTD) Measured Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.6 [Msi] Pooled Standard Deviation =.45 [Msi] Pooled Coeff. of Variation = 7.87 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Modulus [Msi] 7

73 In-Plane Shear -- (CTD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] BDN5B BDN6B BDN7B BDNB BDN4B BDN5B Average Standard Dev Coeff. of Var. [%] Min...75 Min..4 Max Max..5 Number of Spec. 6 74

74 In-Plane Shear -- (CTD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.987 [ksi] Pooled Standard Deviation =.8 [ksi] Pooled Coeff. of Variation =.574 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Strength [ksi] In-Plane Shear -- (CTD) Measured Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.789 [Msi] Pooled Standard Deviation =.56 [Msi] Pooled Coeff. of Variation = 7.6 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Modulus [Msi] 75

75 In-Plane Shear -- (ETW) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] BDNF BDN4F BDN7F BDN8F BDN9F BDNF BDN4F BDN5F BDN6F BDN7F BDN6F BDN7F BDN8F BDN9F BDNAF BDNF BDNF BDN4F BDN6F BDN7F BDN7F BDN9F BDN7F BDN9F BDNAF BDN6F BDN7F BDN8F BDN9F BDNAF Average Standard Dev Coeff. of Var. [%] Min Min..44 Max..9.5 Max..54 Number of Spec. 6 76

76 In-Plane Shear -- (ETW) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average 8.86 [ksi] Pooled Standard Deviation =.577 [ksi] Pooled Coeff. of Variation = 6.5 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Strength [ksi] In-Plane Shear -- (ETW) Measured Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.8 [Msi] Pooled Standard Deviation =.4 [Msi] Pooled Coeff. of Variation = 4.48 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Modulus [Msi] 77

77 In-Plane Shear -- (ETD) Strength & Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Cure Prepreg ASAP Strength Modulus Avg. Specimen # Plies in Avg. t ply Number Cycle Lot # Batch # [ksi] [Msi] Thickn. [in] Laminate [in] BDNG BDNG BDNG BDN7G BDN8G BDN9G BDNG BDNG BDN4G BDNG BDN4G BDN5G BDNG BDNG BDN4G BDN5G BDN6G BDN7G Average Standard Dev Coeff. of Var. [%] Min Min..47 Max Max..54 Number of Spec

78 In-Plane Shear -- (ETD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.75 [ksi] Pooled Standard Deviation =.54 [ksi] Pooled Coeff. of Variation = 4.4 [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Strength [ksi] In-Plane Shear -- (ETD) Measured Modulus Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.4 [Msi] Pooled Standard Deviation =.7 [Msi] Pooled Coeff. of Variation = [%] 6 5 ASAP Batch # 4 Prepreg Lot # In-Plane Shear Modulus [Msi] 79

79 Apparent Interlaminar Shear -- (RTD) Strength Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Cure Prepreg ASAP Strength Avg. Specimen # Plies in Avg. t ply Number Cycle Lot # Batch # [ksi] Thickn. [in] Laminate [in] BDQA BDQA BDQA BDQ4A BDQ5A BDQA BDQA BDQA BDQA BDQ4A BDQ5A BDQA BDQA BDQA BDQA BDQ4A BDQ5A BDQA Average.95.5 Standard Dev..4 Coeff. of Var. [%].848 Min Min..4 Max..7 Max..69 Number of Spec. 8 8

80 Apparent Interlaminar Shear -- (RTD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.95 [ksi] Pooled Standard Deviation =.4 [ksi] Pooled Coeff. of Variation =.848 [%] ASAP Batch # Prepreg Lot # Apparent Interlaminar Shear Strength [ksi] 8

81 .. Fluid Sensitivity Raw Data Spreadsheets and Scatter Charts 8

82 In-Plane Shear -- (MEK - RTD) Strength Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Batch Strength Avg. Specimen # Plies in Avg. t ply Number Number [ksi] Thickn. [in] Laminate [in] BDN8T BDN9T BDNAT BDNT BDN5T Average Standard Dev..9 Coeff. of Var. [%].5 Min Min..48 Max Max..5 Number of Spec. 5 In-Plane Shear -- (MEK - RTD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average = 8.8 [ksi] Pooled Standard Deviation =.9 [ksi] Pooled Coeff. of Variation =.5 [%] Batch # In-Plane Shear Strength [ksi] 8

83 In-Plane Shear -- (JP-4 JET FUEL - ETD) Strength Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Batch Strength Avg. Specimen # Plies in Avg. t ply Number Number [ksi] Thickn. [in] Laminate [in] BDN6R BDN7R BDN8R BDN9R BDNR Average.4.5 Standard Dev..89 Coeff. of Var. [%].4 Min..985 Min..5 Max..778 Max..55 Number of Spec. 5 In-Plane Shear -- (JP-4 JET FUEL - ETD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.4 [ksi] Pooled Standard Deviation =.89 [ksi] Pooled Coeff. of Variation =.4 [%] Batch # In-Plane Shear Strength [ksi] 84

84 In-Plane Shear -- (Hydraulic Fluid - ETD) Strength Fiberite 774/T65 K-5-8H Graphite Fabric Specimen Batch Strength Avg. Specimen # Plies in Avg. t ply Number Number [ksi] Thickn. [in] Laminate [in] BDN7V BDN8V BDNAV BDN9V BDNAV Average Standard Dev.. Coeff. of Var. [%].945 Min..79 Min..4 Max..9 Max..5 Number of Spec. 5 In-Plane Shear -- (Hydraulic Fluid - ETD) Measured Strength Fiberite 774/T65 K-5-8H Graphite Fabric Pooled Average =.997 [ksi] Pooled Standard Deviation =. [ksi] Pooled Coeff. of Variation =.945 [%] Batch # In-Plane Shear Strength [ksi] 85

85 Fluid Sensitivity Comparison: Average In-Plane Shear Strength with Fluid (ksi) MEK (RTD) Same Environment In-Plane Shear Strength without Fluid (ksi) (RTD) Worst Case Environment In-Plane Shear Strength (ksi) (ETW) The RTD average in-plane shear strength was not reduced after exposure to MEK Average In-Plane Shear Strength with Fluid (ksi) JP-4 JET FUEL (ETD).4 Same Environment In-Plane Shear Strength without Fluid (ksi) (ETD).8 Worst Case Environment In-Plane Shear Strength (ksi) (ETW) 8.86 The ETD average in-plane shear strength was reduced by 6% after exposure to JP-4 Jet Fuel. However it remained 9% higher than water exposure in ETW conditions. Average In-Plane Shear Strength with Fluid (ksi) HYDRAULIC FLUID (ETD) Same Environment In-Plane Shear Strength without Fluid (ksi) (ETD) Worst Case Environment In-Plane Shear Strength (ksi) (ETW)..8 The ETD average in-plane shear strength was reduced by 8% after exposure to Hydraulic Fluid. However, it remained 5% higher than water exposure in ETW conditions

86 .. Representative Shear Stress-Strain Curve The following stress-strain curve is representative of the T65 K-5-8H / 774 prepreg system. The tension and compression stress-strain curves are not presented in graphical form. If strain design allowables from these tests are required, simple one-dimensional linear stress-strain relationships may be used to obtain corresponding strain design values. This process should approximate tensile and compressive strain behavior relatively well but may produce extremely conservative strain values in shear due to the nonlinear behavior. A more realistic approach for shear strain design allowables is to use a maximum strain value of 5% (reference MIL-HDBK-7-E, section 5.7.6). If a nonlinear analysis of the material s shear behavior is required, the curve-fit of the shear stress-strain curve may be used. The representative shear stress-strain curve was obtained by taking the average of all the sample shear curves and determining the best-fit line through the data. The actual data points also presented on the chart to demonstrate material variability. 87

87 Shear Stress vs. Shear Strain, RTD 4 Shear Stress [psi] y - = a+blnx/x r = a = e-5 b = -.675e Shear Strain [in/in] 88

88 . Statistical Results 89

89 .. Plot by Condition 9

90 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Tension - BDJXXXXX Measured 9

91 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Tension - BDJXXXXX Normalized 9

92 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Tension - BDUXXXXX Measured 9

93 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Tension - BDUXXXXX Normalized 94

94 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Compression - BDKXXXXX Measured 95

95 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Compression - BDKXXXXX Normalized 96

96 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Compression - BDWXXXXX Measured 97

97 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Compression - BDWXXXXX Normalized 98

98 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE In-Plane Shear - BDNXXXXX Measured 99

99 DISTRIBUTION OF GROUPED DATA FOR DIFFERENT TEST CONDITIONS PROBABILITY OF SURVIVAL Fiberite 774/T65 K-5-8H Graphite Fabric Cessna CTD RTD ETD ETW NO DATA NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE NORMAL CURVE Apparent Interlaminar Shear - BDQXXXXX Measured

100 .. Plot of Pooled Data

101 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna Tension - BDJXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE

102 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna Tension - BDJXXXXX Normalized..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE

103 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna 9 Tension - BDUXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE 4

104 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna 9 Tension - BDUXXXXX Normalized..9.8 PROBABILITY OF SURVIVAL NORMALIZED VALUE 5

105 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna Compression - BDKXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORMALIZED VALUE 6

106 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna Compression - BDKXXXXX Normalized..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE 7

107 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna 9 Compression - BDWXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE 8

108 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna 9 Compression - BDWXXXXX Normalized..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE 9

109 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna In-Plane Shear - BDNXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORM ALIZED VALUE

110 DISTRIBUTION OF POOLED DATA Fiberite 774/T65 K-5-8H Graphite Fabric Cessna Apparent Interlaminar Shear - BDQXXXXX Measured..9.8 PROBABILITY OF SURVIVAL NORMALIZED VALUE

111 .4 Moisture Conditioning History Charts

112 Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric BDJX BDJX BDJX BDJX BDJX BDJX BDJX Time (days) Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric BDUX BDUX BDUX BDUX BDUX BDUX BDUX Time (days)

113 Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric Time (days) BDK BDK BDK BDK BDK BDK BDK Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric Time (days) BDLX BDLX BDLX BDLX BDLX BDLX BDLX 4

114 Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric BDWX BDWX BDWX BDWX BDWX BDWX BDWX Time (days) Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric Time (days) BDNX BDNX BDNX BDNX BDNX BDNX BDNX 5

115 Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric Time (days) BDZX BDZX BDZX BDZX BDZX BDZX BDZX Conditioning History Cessna Fiberite 774/T65 K-5-8H Graphite Fabric Time (days) BDD BDD BDD 6

116 .5 Physical Test Results 7

117 Physical Test Summary Fiberite 774/T65 K-5-8H Graphite Fabric Composite Resin Fiber Void Density Content Volume Content [g/cc] [wt%] [vol%] [vol%] Tension (BDJXXXXX) No. of Specimens Mean Standard Deviation Tension (BDUXXXXX) No. of Specimens Mean Standard Deviation Compression (BDKXXXXX) No. of Specimens Mean Standard Deviation Compression (BDWXXXXX) No. of Specimens Mean Standard Deviation In-Plane Shear (BDNXXXXX) No. of Specimens Mean Standard Deviation Interlaminar Shear (BDQXXXXX) No. of Specimens Mean Standard Deviation Overall No. of Specimens Overall Mean Overall Std. Deviation

118 COMPANY : MATERIAL SYSTEM : PROJECT : Cessna Fiberite 774/T65 K-5-8H Graphite Fabric 9849C DMA Results -- Onset Storage Modulus DRY WET As Fabricated Moisture Equilibirum at 85% RH Sample # Tg [ C] Tg [ F] Sample # Tg [ C] Tg [ F] BDDXFA BDDXBC BDDXGA BDDXCC BDDXHA.85.5 BDDXDC BDDXGA BDDXBC BDDXHA BDDXCC BDDXIA BDDXFC BDDXFA BDDXBC BDDXGA..5 BDDXCC BDDXHA BDDXDC Average [ F] 9.85 Average [ F] 8. Standard Dev. [ F] 6.96 Standard Dev. [ F].8 Coeff. Of Var. [%]. Coeff. Of Var. [%].54 DRY DMA Results - Peak Tan Delta As Fabricated Moisture Equilibirum at 85% RH Sample # Tg [ C] Tg [ F] Sample # Tg [ C] Tg [ F] BDDXFA BDDXBC BDDXGA BDDXCC BDDXHA BDDXDC BDDXGA BDDXBC BDDXHA BDDXCC BDDXIA BDDXFC BDDXFA BDDXBC BDDXGA BDDXCC BDDXHA BDDXDC WET Average [ F] Average [ F] 7.5 Standard Dev. [ F]. Standard Dev. [ F].4 Coeff. Of Var. [%].79 Coeff. Of Var. [%].45 9

119 BDDXFA BDDXGA

120 BDDXHA BDDXGA

121 BDDXHA BDDXIA

122 BDDXFA BDDXGA

123 BDDXHA BDDXBC 4

124 BDDXCC BDDXDC 5

125 BDDXBC BDDXCC 6

126 BDDXFC BDDXBC 7

127 BDDXCC BDDXDC 8

128 4. TESTING AND REPORTING COMMENTS 9

129 All tests were conformed under Designated Option Authority (DOA) by Cessna Aircraft Co. Inc.

130 APPENDIX A. PHYSICAL TEST DATA SUPPLIED BY MATERIAL VENDOR

131

132

133 4

134 5

135 6

136 7

137 8

138 9

139 4

140 4

141 APPENDIX B. DATES OF PANEL MANUFACTURE AND COPY OF FAA FORM 8-4

142 4